Flight Simulation Training Device Initial and Continuing Qualification and Use, 63392-63640 [06-8677]
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63392
Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Parts 1, 11, 60, and 121
[Docket No. FAA–2002–12461; Amendment
Nos. 1–54, 11–52, 60–1, 121–327]
RIN 2120–AH07
Flight Simulation Training Device
Initial and Continuing Qualification and
Use
Small Business Regulatory Enforcement
Fairness Act
Federal Aviation
Administration (FAA), DOT.
ACTION: Final Rule.
AGENCY:
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SUMMARY: The FAA is amending the
regulations to establish a new part to set
forth qualification requirements for
flight simulation training devices
(FSTD). The new part consolidates and
updates FSTD requirements that
currently exist in different parts of the
FAA’s regulations and in advisory
circulars. In addition, the FAA is
requiring that sponsors of FSTDs have a
Quality Management System. These
changes are necessary to promote
standardization and accountability for
FSTD qualification, maintenance, and
evaluation. The intended effect of the
new part is to ensure that users of
FSTDs receive training in devices that
closely match the performance and
handling characteristics of the aircraft
being simulated.
EFFECTIVE DATE: These amendments
become effective October 30, 2007.
FOR FURTHER INFORMATION CONTACT: Ed
Cook, Air Transportation Division
(AFS–200), Flight Standards Service,
Federal Aviation Administration, 100
Hartsfield Centre Parkway, Suite 400,
Atlanta, GA 30354; telephone: 404–832–
4700.
SUPPLEMENTARY INFORMATION:
Availability of Rulemaking Documents
You can get an electronic copy using
the Internet by:
(1) Searching the Department of
Transportation’s electronic Docket
Management System (DMS) Web page
(https://dms.dot.gov/search);
(2) Visiting the FAA’s Regulations and
Policies Web page at https://
www.faa.gov/regulations_policies/; or
(3) Accessing the Government
Printing Office’s Web page at https://
www.gpoaccess.gov/fr/.
You can also get a copy by sending a
request to the Federal Aviation
Administration, Office of Rulemaking,
ARM–1, 800 Independence Avenue
SW., Washington, DC 20591, or by
calling (202) 267–9680. Make sure to
identify the amendment number or
docket number of this rulemaking.
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Anyone is able to search the
electronic form of all comments
received into any of our dockets by the
name of the individual submitting the
comment (or signing the comment, if
submitted on behalf of an association,
business, labor union, etc.). You may
review DOT’s complete Privacy Act
statement in the Federal Register
published on April 11, 2000 (Volume
65, Number 70; Pages 19477–78) or you
may visit https://dms.dot.gov.
The Small Business Regulatory
Enforcement Fairness Act (SBREFA) of
1996 requires FAA to comply with
small entity requests for information or
advice about compliance with statutes
and regulations within its jurisdiction. If
you are a small entity and you have a
question regarding this document, you
may contact its local FAA official, or the
person listed under FOR FURTHER
INFORMATION CONTACT. You can find out
more about SBREFA on the Internet at
https://www.faa.gov/
regulations_policies/rulemaking/
sbre_act/.
Authority for This Rulemaking
The FAA’s authority to issue rules
regarding aviation safety is found in
Title 49 of the United States Code.
Subtitle I, Section 106 describes the
authority of the FAA Administrator.
Subtitle VII, Aviation Programs,
describes in more detail the scope of the
agency’s authority.
This rulemaking is promulgated
under the authority described in
Subtitle VII, Part A, subpart I, 49 U.S.C.
44701. Under that section, the FAA is
charged with regulating air commerce in
a way that best promotes safety.
Background
For many years the flightcrew training
regulations in 14 CFR part 121 subparts
N and O allowed simulator training as
an enhancement to training and testing
in the aircraft, but not as a complete
replacement for training in the aircraft.
Due to improvements in flight simulator
performance, appendix H was added to
part 121 in 1980. Appendix H permitted
and expanded use of simulators by air
carriers that took advantage of the new
simulator performance through an
‘‘Advanced Simulation Training
Program.’’ Appendix H permits
simulators to be used for varying
amounts (up to 100%) of the training,
testing, and checking required by the
FAA. The amount of training permitted
depends on the simulator’s qualification
level.
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As the state-of-the-art in simulator
technology has advanced, more effective
use has been made of the aircraft
simulator in training, checking, and
certification of flight crewmembers.
Using flight simulators rather than
aircraft in training allows for more indepth training, including the practice of
critical emergency procedures, in a safer
environment. Not only do simulators
provide improvements in safety and in
safer training operations, they also
provide such benefits as reducing noise,
air pollution and air traffic congestion,
and conserving petroleum resources.
Since 1980 appendix H of 14 CFR part
121 has provided an Advanced
Simulation plan outlining the steps
toward optimum use of flight
simulators. Most major air carriers have
taken advantage of appendix H and
conduct most or all of their training and
checking in simulators.
The FAA originally placed simulator
technical requirements in appendix H
because part 121 air carriers were the
primary users of aircraft simulators. As
the larger aviation community became
interested in using simulators, the FAA
in 1980 provided guidance in an
advisory circular AC 121–14C, Aircraft
Simulator and Visual System Evaluation
and Approval. The AC more fully
described what the technical
capabilities of simulators should be,
how those capabilities might be verified,
and how all these capabilities might be
incorporated into training programs.
Over the next several years following
publication of AC 121–14C, the FAA, in
consultation with the aviation industry,
refined and republished its guidance
material several times. Because the
regulations regarding advanced
simulators remained in part 121,
appendix H, certificate holders who
operated under parts other than 121
(such as parts 125 and 135) had to
obtain exemptions in order to use
simulators as provided in part 121,
appendix H. The number of these
operators has continued to grow.
The ability to manage the increasing
number of exemptions, each one with
slightly different provisions, conditions
and limitations, became increasingly
difficult. The development of 14 CFR
part 142, Certification of Training
Centers, was seen to be a logical and
necessary way to deal with those
operators who wished to conduct
training for flight crewmembers but who
did not operate under any of the part
121, 125 or 135 rules. However, the
regulatory requirements for the
technical criteria for a majority of the
simulators coming into the U.S. aviation
inventory has remained in the part 121
operating rule.
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
Notice of Proposed Rulemaking
The FAA published a Notice of
Proposed Rulemaking (NPRM) for part
60 and related amendments on
September 25, 2002, (67 FR 60284) and
published a correction to the NPRM on
October 25, 2002 (67 FR 65524). From
December 2 until December 13, 2002,
the FAA hosted an on-line public
forum, which provided an opportunity
for the public to answer specific
questions posed by the FAA and
allowed the FAA to respond with
clarifying information. After an
extension requested by commenters, the
comment period closed on February 24,
2003.
In the NPRM the FAA proposed to
remove the technical requirements for
flight simulation devices (FSD) (flight
simulators and flight training devices)
from part 121 and place them in a new
part 60, titled ‘‘Flight Simulation Device
Initial and Continuing Qualification and
Use.’’ The NPRM proposed to establish
FSTD requirements for anyone
conducting flight crewmember training,
evaluation, and flight experience under
any of the Federal Aviation Regulations.
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Flight Simulation Device Aviation
Rulemaking Committee (ARC)
In order to resolve comments and
provide a forum for the FAA and the
aviation community to discuss issues
regarding Flight Simulation Training
Devices (FSTDs), the FAA established
the Flight Simulation Device Aviation
Rulemaking Committee (ARC) on July 2,
2003. The ARC included participants
from: Air Line Pilots Association,
Aircraft Owners and Pilots Association,
American Airlines, Alteon, Atlas Air,
Boeing, CAE Electronics, Continental
Airlines, Delta Air Lines, Federal
Express, FlightSafety International,
Northwest Airlines, Pan Am Flight
Academy, Thales Training and
Simulation, United Airlines, U.S.
Airways, and FAA.
The general goal of the ARC was to
provide advice, guidance, and
recommendations on FSTD issues
including, but not limited to, safety of
flight; the suitability and the application
of the simulation to flight crewmember
training, testing, or checking activities;
and implementation of technical
changes or scientific advancements in
simulation. The ARC provided a forum
for the FAA and affected members of the
aviation community to discuss issues.
The ARC also allowed members of the
aviation community to reach consensus
on certain recommendations that would
be submitted to the FAA and to develop
resolutions to facilitate the evolution of
FSTDs. The ARC’s initial task was to
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review the FAA’s September 25, 2002,
proposed rule. On November 24, 2003,
the ARC submitted to the FAA its
recommendations on how the proposed
rule language should be clarified and
reorganized. After the FAA received
recommendations from the ARC the
comment period was reopened on
February 10, 2004, to permit interested
persons to review these
recommendations and submit additional
comments. The recommendations from
the ARC are available online at https://
dms.dot.gov by searching for entry 84 in
docket number FAA–2002–12461. The
comment period closed on March 11,
2004. The overwhelming majority of the
clarifications and revisions contained in
the final rule are consistent with the
ARC recommendations.
Summary of the Final Rule
New part 60 contains the
requirements for the evaluation,
qualification, and maintenance of
FSTDs. These requirements are based on
the current guidance regarding the
capability and performance of
simulators in appendix H of part 121
and § 121.407. As part of this
rulemaking project, the FAA has
amended appendix H of part 121 and
removed the Simulator Requirements
and the Visual Requirements for Level
B, C and D devices. These requirements
are now outlined in the appropriate
Qualification Performance Standards
(QPS) appendices. In a separate
rulemaking project that will follow this
final rule, the FAA will propose to move
Training and Checking Requirements of
appendix H to a new subpart of part
121, and to delete appendix H.
Part 60 also contains items (such as
frequency, content, and method of
evaluation) previously found in the
advisory material in AC 120–40B,
Airplane Flight Simulator Qualification,
in AC 120–45A, Airplane Flight
Training Device Qualification, and in
AC 120–63, Helicopter Simulator
Qualification. Standards from this
advisory material and specific items that
are subject to change through
technological advancements are being
placed into one of the first four
appendices to part 60:
• Appendix A, ‘‘Qualification
Performance Standards for Airplane
Full Flight Simulators.’’
• Appendix B, ‘‘Qualification
Performance Standards for Airplane
Flight Training Devices.’’
• Appendix C, ‘‘Qualification
Performance Standards for Helicopter
Full Flight Simulators.’’
• Appendix D, ‘‘Qualification
Performance Standards for Helicopter
Flight Training Devices.’’
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In addition, the FAA has reorganized
and clarified some material from the
original NPRM into two appendices,
Appendix E, ‘‘Qualification
Performance Standards for Quality
Management Systems for Flight
Simulation Training Devices,’’ and
Appendix F, ‘‘Definitions and
Abbreviations.’’ Appendix E will
become the single appendix for
reference to Quality Management
System (QMS) programs for FSTDs
under this part. Appendix F will
become the single appendix for
definitions and abbreviations for terms
used throughout part 60 and the QPS
appendices.
Some of the terms and abbreviations
listed in the new appendix F and added
to part 1 are clarifications of terms that
appeared in the September 25, 2002,
NPRM. For example, FSD has been
replaced with the more internationally
compatible term—FSTD. The term
FSTD more accurately addresses the full
range of uses for these devices as
addressed in part 60 and also
harmonizes with the Joint Aviation
Authorities (JAA) of Europe. In
addition, to more appropriately describe
the devices, the term Flight Simulator
has been changed to Full Flight
Simulator (FFS). Another clarification
the FAA has made with respect to terms
and definitions is that the Quality
Assurance Program (QAP) is now called
a QMS.
The QPS requirements in appendices
A through E are regulatory. Future
changes and additions to these
standards are subject to notice and
comment rulemaking procedures under
the Administrative Procedure Act,
unless ‘‘good cause’’ (see 5 U.S.C.
553(b)(B)) exists to justify proceeding
without notice and comment. In
addition, the FAA has issued FAA
Order 1110.136, ‘‘Flight Simulation
Device Aviation Rulemaking
Committee.’’
What Action Is the Agency Taking?
The FAA is adding part 60 to Title 14
of the Code of Federal Regulations to
establish qualification requirements for
flight simulation training devices
(FSTD). These requirements are based
on the current requirements found in
appendix H of part 121 and § 121.407
for the capability and performance of
aircraft simulators. The new rule also
incorporates certain existing practices
that were previously described in the
following Advisory Circulars: AC 120–
40B, Airplane Flight Simulator
Qualification, AC 120–45A, Airplane
Flight Training Device Qualification,
and AC 120–63, Helicopter Simulator
Qualification.
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Why Is the Rule Necessary?
The rule is necessary to promote
standardization and accountability for
FSTD maintenance, qualification and
evaluation for use in an FAA approved
flight training program. FSTDs are often
used in lieu of aircraft to train and
check individuals for purposes of
issuing airmen certificates and ratings.
FSTDs are also used to meet FAA air
carrier training requirements for flight
crewmembers. In fact, depending on the
status of the airman and the
sophistication of the device, an FSTD
may be used for 100% of the training,
testing, and checking required by the
FAA. Training in an FSTD is most
effective when the FSTD closely
matches the performance and handling
characteristics of the aircraft being
simulated. This rule sets forth the
regulatory process for establishing the
qualification level of the FSTD and for
the continuous review and inspection of
FSTD performance to identify potential
problems with FSTD maintenance and
operation. The new rule will improve
flight crewmember training, reduce
operational errors and increase safety. It
will also provide the standards that
must be reached in order for a device to
be qualified at a certain level (i.e., Level
A, B, C, or D Simulators and Level 4, 5,
or 6 Training Devices).
Generally speaking, the amount of
training and testing that can be
conducted in an FSTD for the purpose
of meeting FAA airmen certification or
training requirements is directly
proportional to the qualification level of
the device. Thus, a device with a higher
qualification level (e.g., Level D) will be
eligible for more certification and
training credits than a device with a
lower qualification level (e.g., Level A).
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Qualification Performance Standards
(QPS)
One of the unique features of the part
60 rule is the incorporation of QPS. The
QPS is an appendix to the regulation
and outlines requirements and other
information regarding the qualification,
performance, evaluation and
maintenance of FSTDs. The QPS
contains several charts. Some of the
charts prescribe regulatory
requirements, while others outline
general information and examples to
assist the user in meeting the regulatory
requirements.
The charts containing regulatory
material are labeled ‘‘QPS
Requirements.’’ Compliance with the
criteria in these charts is mandatory in
order to receive and maintain approval
from the FAA for the qualification level
and use of an FSTD. Changes to a QPS
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Requirement are subject to notice and
comment rulemaking procedures under
the Administrative Procedure Act,
unless ‘‘good cause’’ (see 5 U.S.C.
553(b)(B)) exists to justify proceeding
without notice and comment. The charts
containing general information and
examples are labeled ‘‘Information.’’
Compliance with the material contained
in these charts is not mandatory, and
changes to an Information section are
generally not subject to notice and
comment rulemaking procedures. The
Information charts are included simply
to provide additional guidance to the
user.
Incorporating both the regulatory and
advisory material into the QPS
consolidates all of the relevant
information and makes it available in
one location. This promotes ease of use
and greater uniformity among those
involved in every aspect of FSTD
performance, including manufacturers,
airmen, training providers and
regulators. Moreover, it gives greater
insight to the regulated community
regarding the FAA’s intent behind the
regulation, and the required and
approved methods of compliance.
Comments
The FAA received 54 comments in
response to the NPRM. Commenters
included industry associations, airlines,
training centers and schools, aircraft
manufacturers, simulator and flight
training device manufacturers, pilot
associations, governmental
organizations, and individuals. The
major concerns of the commenters were
harmonization of FAA standards with
those of International Civil Aviation
Organization (ICAO) and the JAA, the
cost of complying with the new
requirements, grandfathering existing
simulators and other flight training
devices, the requirement for a Quality
Assurance Program (QAP), and the
proposed requirements to be approved
by the FAA as an FSTD ‘‘sponsor.’’
The FAA reviewed all comments.
They are more fully explained in the
Discussion section to follow. With
respect to the major concerns raised by
commenters, the FAA took the
following actions:
• Revised certain sections of the QPS
Requirements to incorporate ICAO/JAA
standards that were within the scope of
the original NPRM. Changes that are
beyond the scope will be incorporated
in future revisions to the QPS
Requirements.
• Revised certain requirements where
appropriate in order to reduce costs.
The FAA notes, however, that part 60 is
largely a codification of existing
practices, and therefore, the agency does
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not anticipate that sponsors will incur
many new or additional costs. The
FAA’s cost projection is outlined in the
Regulatory Evaluation.
• Excluded Levels 2 and –3 Flight
Training Devices from this rulemaking
effort. The FAA will review its existing
advisory material and determine the
best method to continue to evaluate and
qualify these devices.
• Replaced the QAP proposal with a
Quality Management System (QMS).
The QMS is significantly less costly
than the proposed QAP.
• Eliminated the 600-hour annual use
requirement for sponsorship eligibility.
Persons are now permitted to sponsor
an FSTD as long as the device is used
at least once per year in an FAA
approved training program, or at least
once per year a pilot, appropriately
qualified on the aircraft being
simulated, flies the FSTD and confirms
that the performance and handling
qualities are like the aircraft.
Many other detailed comments of an
editorial nature were also provided.
These are not included in the summary,
but have been carefully reviewed by the
FAA in preparing the Final Rule. In
addition, the specific comments on the
QPS appendices are not summarized in
the Final Rule summary, but have been
carefully reviewed and incorporated,
where appropriate, into the Final Rule.
The FAA made certain changes to the
QPS appendices from the proposed
language to include technical
corrections and clarifications that did
not adversely affect safety and were
within the scope of the NPRM. There
were other technical changes that the
FAA did not incorporate into this final
rule because they were beyond the
scope of the NPRM. The FAA will issue
another NPRM to incorporate the
changes that were beyond the scope of
the original NPRM, and will incorporate
these changes before the rule becomes
effective. All of the comments are
available for review at https://
dms.dot.gov. The Docket Number is
12461.
Abbreviations Used in this Preamble
AC Advisory Circular
ALPA Airline Pilots Association
AOPA Aircraft Owners and Pilots
Association
ARC Aviation Rulemaking Committee
ATA Air Transport Association
ATOS Air Transportation Oversight System
CBT Computer Based Training
DPE Designated Pilot Examiner
EASA European Aviation Safety Authority
(formerly Joint Aviation Authorities (JAA)
FFS Full Flight Simulator
FOQA Flight Operations Quality Assurance
FSB Flight Safety Boeing
FSD Flight Simulation Device
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FSDO Flight Standards District Office
FSI FlightSafety International
FSTD Flight Simulation Training Device
FTD Flight Training Device
ICAO International Civil Aviation
Organization
MQTG Master Qualification Test Guide
MR Management Representative
NAFI National Association of Flight
Instructors
NATA National Air Transport Association
NBAA National Business Aviation
Association
NDB Non-Directional Beacon
NPRM Notice of Proposed Rulemaking
NSP National Simulator Program
NSPM National Simulator Program
Manager
POI Principal Operations Inspector
QPS Qualification Performance Standards
QAP Quality Assurance Program
QMS Quality Management System
QS Quality System
QTG Qualification Test Guide
RAA Regional Airline Association
SITC Simulation and Instrument Training
Center, Inc.
SOQ Statement of Qualification
TCPM Training Center Program Managers
Thales Thales Training & Simulation
TPAA Training Program Approval
Authority
UA United Airlines
UAA University Aviation Association
UPS United Parcel Service
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General Issues
General Comments
Eclipse, NLX Corporation, JAA, and
an individual, applaud and appreciate
the FAA’s attempt to amend the
regulations for FSTDs. JAA writes that
the ‘‘proposal takes care of the legal
concern that regulations in this area
have to have a mandatory basis * * *
and it concentrates all related material
in one document.’’ This commenter
states that this proposal did not address
the latest modifications applied to the
ICAO Manual and questions if using an
FSTD instead of an aircraft would be
made mandatory. An individual writes
that simplification and consolidation of
these regulations are appropriate and
more detailed regulations and device
inspection will force flight training
schools to improve and that ‘‘somewhat
of a loophole’’ in flight training in flight
simulators and flight training devices
would be closed. NLX indicates that
these new regulations are a step forward
in the overall process of FSTD
qualifications. An individual believes
that statistics proving that the use of
simulator training has reduced aviation
accidents or incidents are needed.
FAA Response: This final rule does
not mandate the use of FSTDs instead
of aircraft for training. This rule simply
establishes FSTD qualification
requirements. The FAA is developing an
NPRM that proposes to revise the QPS
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appendices to achieve the desired level
of harmonization.
Disposition of Level 7 Flight Training
Devices
Regional Airline Association states
that the preamble should discuss the
disposition of Level 7 FTDs.
FAA Response: The original premise
for the Level 7 FTD was that there was
to be an aircraft entering service that
would not have an ‘‘on-set motion cue’’
with the failure of an engine, and that
the pilots training in an FSTD for that
airplane type could be trained and
checked on such an engine failure
without requiring a force (motion)
cueing system. The FAA determined
that a Level C simulator aerodynamic
data package would be required for the
level 7 FTD to accurately simulate such
an aircraft. However, the airplane never
entered service and the requirements for
the Level 7 FTD quickly became
superfluous. Level 6 and Level 7 FTDs
had the same authorizations (except for
one area involving ‘‘icing
accountability’’), but the Level 7 FTD
continued to require significantly more
aerodynamic data for no more value
than the Level 6 FTD. The elimination
of the Level 7 FTD does not preclude
any Level 6 FTD from incorporating a
Level C data package and having
essentially the same kind of device as
the originally described Level 7 device.
However, there has been essentially no
difference between the two levels in
authorized use, and it made little sense
to continue with a Level 7 FTD when
there was little difference between a
Level 6 and Level 7 FTD.
The FAA is considering future
rulemaking to develop standards for
Level 7 FTDs for helicopters. Any new
requirements would be subject to notice
and comment.
Rule vs. QPS
Continental asserts that there is a
conflict between the rule and the
Qualification Performance Standards
(QPS). Continental states that the rule
addresses a number of technical issues
that would be best delegated to the QPS,
and also notes that parts of the rule and
its application have different definitions
than the QPS.
FAA Response: In the final rule, we
eliminated the repetition of the rule
language in the QPS appendices because
it was never the FAA’s intent to have
different definitions for terms in the rule
and the QPS appendices. The FAA has
also revised the rule language and the
QPS appendices so that technical
information is presented in the most
appropriate sections and formats.
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Codified Design Criteria
Northwest writes, ‘‘The proposed
regulation should be streamlined to
centrally codify simulator design and
qualification criteria.’’
FAA Response: The FAA deems it
appropriate to stop short of establishing
a regulation mandating the design and
construction criteria for these devices.
While the FAA has type certificate
requirements for aircraft instead of
individual qualification requirements
like we have for FSTDs, the FAA is not
including such requirements in this
final rule. We believe requiring a type
certificate process would create the
potential for enormous cost increases
with virtually no gain in the quality of
the devices.
Clarification of Requirements and
Oversight Responsibilities
TWA and CAE were concerned with
the lack of clarity in the rule language.
Specifically, TWA wants the rule
rewritten clearly stating FAA’s
intentions and adding that the National
Simulator Program Manager (NSPM) has
full authority over FSTDs and all results
of other inspections must go through the
NSPM before action can be taken. CAE
expressed a similar concern.
FAA Response: The FAA revised the
part 60 rule language and QPS
appendices to ensure the requirements
are clear. The QPS appendices provide
examples and additional information
and criteria outlining the method of
compliance with the regulations. In
addition, the FAA has clarified the
NSPM will exercise oversight
responsibility for the evaluation and
qualification of all FSTDs included in
part 60.
Use of FSTDs in the Course of Training
FlightSafety Boeing (FSB) believes
part 60 ‘‘should be limited to the
definition, design criteria, required
documentation and record-keeping of
Flight Simulation Devices, and the
evaluation process to assure continued
functionality as designed, for the
respective level of device.’’ In FSB’s
opinion the authority on planned or
actual use of FSTDs in the course of
training should remain with the
respective sponsor of the device and the
Training Program Approval Authority
(TPAA) as presently required in existing
regulations. Also, FSB writes that all
proposed wording addressing the
continued use of a device be eliminated,
including the words ‘‘and use’’ in the
title of the proposal.
FAA Response: The final rule
addresses the definition, required
documentation and record keeping for
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FSTDs. It also outlines the evaluation
process to assure continued
functionality of FSTDs, including the
objective and subjective requirements.
However, as stated earlier, the FAA has
determined it is not appropriate to
include FSTD ‘‘design criteria’’ in the
final rule. Also, the phrase ‘‘and use’’ in
the title of the part 60 rule does not
apply to the actual ‘‘use’’ of an FSTD in
the course of training approved by the
TPAA. Rather, the term refers to those
uses of the FSTD for which
representatives of the NSPM have
qualified a specific FSTD.
NSP Office
TechniFlite states, ‘‘There should be
an official (rather than implied or
assumed) FAA office established at the
Washington level to be responsible for
the oversight of the National Simulation
Program. This office could be
responsible for reviewing appeals when
disputes with the NSP arise.’’
FAA Response: The NSP is part of the
Flight Standards Service. Specifically, it
is part of the Air Transportation
Division, AFS–200, and answers
directly to the AFS–200 manager in
Washington, DC. An appeals process is
outlined in §§ 60.5(d) and 60.29(b). In
both cases, the Director of the Flight
Standards Service, AFS–1, is the
person/office to whom appeals should
be made.
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Level of Detail in Regulations
Thales Training & Simulation (Thales)
‘‘objects to the way that our regulations
are becoming so overly prescriptive.’’
FAA Response: The part 60 rule is, for
the most part, a codification of existing
practices. However, there are new
requirements such as the QMS
requirement in § 60.5. The FAA,
working with the ARC, including
Thales, developed requirements that
balance safety concerns without being
overly burdensome.
Necessity of the Rule
Several commenters question whether
this rule is needed. American Airlines
states that it has worked closely with
the NSPM to develop its simulator
program and it believes it has the
highest quality simulator program in the
world. American sees ‘‘nothing in the
NPRM that will result in an increase in
the quality or effectiveness of the
American Airlines training program.’’
Similarly the National Business
Aviation Association (NBAA) does not
think the rule will result in a safety
enhancement, stating that, ‘‘there has
been no evidence that the current
system of certifying and maintaining
flight simulator devices has
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compromised safety in any way.’’ The
Aircraft Owners and Pilots Association
(AOPA) states that the proposed rule
‘‘places an unnecessary regulatory
burden on the aviation industry, and it
does not address a safety problem or
provide a net safety benefit.’’ Storm
Haven Aviation and a flight instructor
make similar comments.
FAA Response: Codifying simulation
qualification standards provides for a
‘‘level playing field’’ among FSTD
manufacturers and sponsors in the
United States and a harmonization of
interests internationally. Further, these
provisions, together with the provision
for a QMS, will provide each sponsor a
clear understanding of what is required
of them for a satisfactory FSTD. The
FAA also notes that part 60 is largely a
codification of existing practices, and
does not impose significantly new
burdens. The FAA recognizes the close
working relationship that exists between
the NSPM and a large portion of the
aviation training community. That close
working relationship continues with
this rulemaking effort and should
continue after the rule becomes
effective. The FAA believes that the rule
will result in an increase in the quality
and effectiveness of flight training
programs without an undue burden on
the industry.
Withdraw NPRM
Air Transport Association (ATA)
requests the immediate withdrawal of
the NPRM and the formation of an
industry-government advisory
committee to develop a new proposed
rule. In support of this request, ATA
states five general concerns with the
NPRM:
1. If published as currently written, the
NPRM would eliminate the use of a
significant number of simulators until they
could be qualified or replaced.
2. The proposed rule ignores
harmonization efforts between the FAA, the
JAA, and the simulator industry.
3. The FAA currently is revising Subparts
N & O of FAR Part 121, which deal directly
with crew training and the practical use of
FSTD. However, the NPRM overlaps and
implicates training requirements, and thus it
is impossible to determine the overall
impacts of the NPRM until the training
requirements of Subparts N & O are revised
or clarified.
4. The NSP, or each responsible TPAA,
would have to be manned on a 24 hour/7
days per week basis to administer the
proposed FAR Part 60 requirements in order
to prevent unnecessary FSTD downtime.
5. The NPRM places a severe financial
burden on U.S. airlines. The cost of the
NPRM is not justified by its benefits.
Several other commenters, including
Bombardier, FedEx, American Trans
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Air, TWA, Continental, and DHL agree
with ATA’s position that the NPRM
should be immediately withdrawn and
that an industry-government advisory
committee should be convened to
develop a new proposed rule. Other
commenters did not specifically cite the
ATA position, but did suggest that a
more effective rule would be achieved
through government and industry
collaboration.
FAA Response: Rather than withdraw
the NPRM, the FAA established the
ARC. The overwhelming majority of the
ARC members, including ATA members
and an ATA representative, participated
in the development of recommendations
to the FAA. As proposed in the NPRM,
each currently qualified FSTD will
continue to be evaluated against the
criteria current at the time of that FSTDs
original evaluation (67 FR 60291). No
currently qualified FSTDs will be
disqualified because of the new part 60
evaluation requirements. Therefore, the
FAA does not expect that anyone will
be ‘‘driven back into the airplane’’ for
training, testing, or checking because of
the part 60 final rule.
In addition, the standards contained
in the final rule have been modified so
they are more in line with ICAO and
JAA standards. Also, as mentioned
previously, the FAA is continuing its
efforts to achieve the desired level of
harmonization. The FAA would like to
note that part 60 is not interdependent
with and does not overlap the
rulemaking effort to revise 14 CFR part
121, Subparts N and O. The part 121,
Subparts N and O rulemaking deals
directly with flight crewmember
training and the practical use of FSTDs,
while part 60 deals with the standards
for FSTD qualification and evaluation.
Cost of the Proposed Rule
A group of commenters cite cost as
the reason the NPRM should be
withdrawn. AOPA states that the
proposed rule places an unnecessary
regulatory burden by imposing a large
cost without properly identifying the
cost impact. TechniFlite explains that
with the cooperation of the FAA and
industry, initiatives can be taken to
make significant reductions in the cost
of simulators thereby making simulators
more available to the broader needs of
the industry. Professional Instrument
Courses believes that the proposed rule
would add needless expense to their
company with no gain in the quality of
safety of their program and would put
their successful 22-year-old instrument
flight training company out of business.
FAA Response: The FAA continues to
believe that training in an FSTD is most
effective when the FSTD closely
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matches the performance and handling
characteristics of the aircraft being
simulated. Accordingly, training and
checking activities should be
accomplished only in those devices that
are objectively and subjectively
evaluated. The rule creates no new
technical requirements for qualification
of the basic levels of FTDs. The NSPM
has maintained an open and continuous
dialogue with aircraft simulator
manufacturers and users. This dialogue
continues to enhance the quality of
simulation, improve the evaluation of
simulation devices, and reduce the costs
of acquiring, evaluating, and using these
devices for flight crewmember training
and checking. It is the FAA’s intent to
maintain this on-going effort.
Advisory Circulars vs. Regulations
(Appendices A–D)
Three commenters disagree with
including the advisory language that
currently exists in the Advisory
Circulars (ACs) for airplane simulators
and flight training devices in the
proposed rule. Delta states that the
advisory language is very lengthy and
detailed and that after incorporating this
language into the rule, the FAA and
users will need to strictly abide by it
and any changes would need to go
through a lengthy revision process.
Regional Airline Association (RAA) says
the proposed QPS appendices are
written as ‘‘engineering standards,’’ as
opposed to performance standards. RAA
believes the FAA should adopt
performance based regulations
whenever possible because they allow
for flexibility and freedom for
innovation. RAA states its concern that
even seemingly minor requests for
deviations from the QPS appendices
content will require that operators/
owners petition the FAA for deviation
approval, a process it says takes weeks
and most often months for approval. In
addition, RAA notes, ‘‘no specific
instances of the proposal were
mentioned as to industry’s failure to
constructively use and follow the
content of the AC’s.’’ FSI says the NPRM
preamble incorrectly explains that the
FAA is proposing to remove the
technical requirements from part 121
and place them in the new part 60. FSI
maintains that these requirements have
always been advisory and not
regulatory, and recommends that the
FAA clearly acknowledge that a major
purpose of this rulemaking is to make
previously advisory material mandatory.
The National Association of Flight
Instructors (NAFI) agrees completely
with moving the requirements into the
proposed rule. It applauds and
unequivocally supports the FAA’s
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efforts to make these requirements
regulatory rather than advisory.
FAA Response: The FAA disagrees
that the QPS appendices are written as
an engineering standard, rather than as
a performance standard. The QPS
appendices are a codification of existing
advisory material that was used to
determine whether or not a specific
FSTD met FAA requirements. These
standards have always been
‘‘performance standards,’’ involving an
objective and subjective evaluation of
the device in comparison to the aircraft.
There has never been a requirement for
an ‘‘engineering standard’’ in simulation
beyond that which is necessary to meet
the stated performance objectives. Part
60 does not change these requirements.
The decision to codify FSTD
qualification requirements was made
after careful consideration of facts and
circumstances. This decision is not a
result of ‘‘industry’s failure to
constructively use and follow the
content of the AC’s.’’ Rather, the FAA
has determined that continued oversight
through the issuance and application of
ACs is not appropriate. Executive Order
12866 states ‘‘(e)ach agency shall draft
its regulations to be simple and easy to
understand, with the goal of minimizing
the potential for uncertainty and
litigation arising from such uncertainty’’
[section 1(b)(12)]. Additionally, Section
5–1 of FAA Order 1320.46A, ‘‘Advisory
Circular System,’’ states that
AC’s are not regulations and may not
impose or lessen a burden on anyone, nor
have a mandatory effect. AC’s may not be
used to add to, interpret, or relieve a duty
imposed by a Federal Aviation Regulation
(FAR). Advisory circulars may set forth
‘acceptable means’ or ‘methods of
compliance’ with a particular FAR. However,
the language used to explain the compliance
methods in the AC must not imply that it is
the only or minimum acceptable means, nor
require other methods of compliance to be
‘equivalent’ to the one described in the AC.
In order to be legally valid, a
regulation must establish a requirement
or standard that is sufficiently clear to
persons required to comply with it so
that they can have a reasonable
understanding of what is expected of
them, without having to resort to
material not published in the rule. In
other words, the regulation must be able
to stand on its own. The regulations that
support the current set of ACs
describing simulation standards are
found in 14 CFR part 121, Subpart N
and, since 1980, part 121, appendix H.
However, in neither of these rule
sections is the regulatory language
sufficient to meet the requirement that
persons would not have to resort to
additional material not published in the
rule. Additionally, while FSTD
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63397
qualification standards have been
contained in ACs, they have been
treated as though they were regulatory.
Clearly, this practice is not in
compliance with either the EO or the
FAA Order. Therefore, the development
of a rule for the qualification of FSTDs
was imperative.
Due to a comment, the FAA
recognized that it did not have rule
language in the part 60 NPRM that
proposed to remove technical FSTD
requirements from part 121. In the final
rule, we have removed from part 121
those technical FSTD requirements that
are in part 60. It was an administrative
oversight that we neglected to propose
removing technical FSTD requirements
from part 121, but we were clear in the
NPRM that part 60 would serve as the
regulatory part for FSTD qualification
and evaluation.
The FAA is aware that there are
differences in the application of what
may be authorized under an advisory
circular concept and what may be
required or authorized under a
regulatory concept. However, the
language of this final rule has been
carefully constructed to accommodate
‘‘operations and engineering judgment’’
when applying flight test data to
objective test requirements and
tolerances. The goal was to allow the
logical application of this judgment
while, at the same time, not allow
complete ‘‘free play’’ with FAA
standards.
QPS Document
FSI states ‘‘The Qualification
Performance Standard (QPS) contains
regulatory language that appears only in
the QPS. The combination of
information, data, and regulatory
language will create misunderstanding
between FAA and the industry.’’ In
addition, FSI believes that the ‘‘tabular
technical requirements in the QPS are
also confusing due to the outdated
condition of the tolerances and test
descriptions.’’ FSI further states, ‘‘The
most glaring of the unrealistic
requirements in the QPS is the motion
system ‘specifications.’ In the past when
rules have attempted to define hardware
and software simulator system
‘specifications,’ the rules became
obsolete before they were published.’’
Therefore, FSI recommends the QPS
define tolerances, not design
specifications.
TWA states that the ‘‘direct quote or
a paraphrasing of the Part 60 rule’’ in
the QPS documents is sometimes very
confusing and sometimes they are in
disagreement with the rule. TWA
recommends removing them to make
the QPS smaller and easier to use.
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FAA Response: The FAA has revised
the final rule to eliminate the motion
system standards published in the
NPRM. Additionally, the FAA has
removed the part 60 rule language from
the QPS appendices to avoid confusion
and repetition. The FAA recognizes the
necessity of additional modifications to
certain sections of the QPS appendices
that are beyond the scope of the NPRM.
The FAA is continuing to revise the
QPS, and any recommendations for
changes to part 60 will be available for
public review and comment as an
NPRM prior to being adopted. It is the
FAA’s intent the part 60 final rule not
be effective until the first revision of the
QPS appendices have been published in
the Federal Register as a final rule.
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Related to N&O Rulemaking
FSI notes that the preamble states ‘‘In
a separate rulemaking project that will
follow this proposal, other portions of
appendix H would be moved to a new
subpart of part 121, and appendix H
would be deleted.’’ Concerned that
timely action may not be taken and
considering the length of time for
rulemakings, FSI requests that the FAA
make the necessary and proper
conforming changes now and amend
§ 121.407 and delete appendix H.
Air Transport Association (ATA)
states that this NPRM and subparts N
and O of part 121 are very closely
linked, and ‘‘recommends that any
proposed changes to Subparts N and O
be coordinated with this rulemaking
and, in particular, that any changes to
Subparts N and O precede this
rulemaking.’’
FAA Response: The FAA recognizes
14 CFR part 121, appendix H has both
technical requirements and operational
authorizations. By ‘‘removing and
reserving’’ certain sections in the
current part 121, appendix H, (i.e., those
sections dealing with technical
requirements of FFSs) without canceling
the entire appendix, the remaining
sections of appendix H will continue to
serve operational necessities until such
time as appendix H is cancelled. The
requirements contained in 14 CFR
121.407 are not contrary to the
requirements contained in part 60.
Changes to 14 CFR part 121, Subparts
N and O will include references to
FSTDs, but only to the extent of
defining what tasks may be authorized
for part 121 flight crewmembers in a
given level of FSTD. Part 60, including
all of the evaluation and qualification
requirements, is not dependent upon or
interdependent with, any future
Subparts N and O changes that may be
proposed or adopted.
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Harmonization and ICAO
Many commenters address the issue
of harmonization of FAA’s FSD
qualification standards with those of
ICAO and the JAA. Boeing, United,
Continental, American, FSI, FSB, NLX,
CAE, and Eclipse are concerned that the
NPRM does not include recent industry
efforts to harmonize the latest regulatory
standards for the qualification of FSDs.
Delta commented that an opportunity to
revise the rule would provide a chance
to define an improved revision process
for the advisory material and to
incorporate harmonization with the
ICAO Manual of Criteria for the
Qualification of Flight Simulators.
Eclipse states that the ICAO Manual of
the Criteria for the Qualification of
Flight Simulators, 2nd edition, which
was endorsed by the FAA, should be
incorporated into the QPS appendices.
Continental states that a lack of
harmonization will impose a financial
burden on the carriers when they
sponsor or use FSDs that are currently
approved under the ICAO standard.
American states that, instead of
matching the ICAO criteria, the NPRM
appendices contain a version of the
criteria contained in the Draft AC 120–
40C, modified with additional
requirements. American states that since
the FAA is on record as planning to
eventually adopt the ICAO criteria,
there is no reason not to do it in this
rule.
NLX comments that although
updating the QPS should not require the
lengthy time frames experienced with
changes like AC 120–40C, the industry
has no assurance this will occur. NLX
is concerned that after the rule is in
place, updating the QPS will result in
an extended time frame of possibly
several years during which the industry
must comply with the obsolete
requirements. NLX states that, without
some guarantee that this will not be the
case, it recommends that the QPS be
updated to reflect the latest JAR/ICAO
material before the rule is put into
effect.
FSB states that the proposed FAA
standards are significantly different
from the JAR STD 1A requirements,
which are stricter. FSB urges the FAA
to reconsider the timetable so as to
include the recent updates to the ICAO
9625, JAR STD 1A and to remove
changes to the motion standards in
appendix A, which were vigorously
disapproved by industry when added to
the AC 120–40C. If the plan is to go
forth with the rulemaking process with
the existing differences, FSB strongly
suggests that the FAA comment on an
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implementation plan and timetable for
complete harmonization to take place.
United comments that the proposed
standards decouple the functional and
subjective test requirements from the
FSD qualification level and require an
FSD qualification task list without
offering any criteria against which such
tasks would be approved. United states
that this is a break from past FAA
practice, from the current JAA practice,
and from the recommendations in the
ICAO Manual.
Boeing comments that considerable
industry time and expense has been
expended over the past years to
harmonize the standards. The results of
these efforts have been incorporated
into the ICAO Manual and are in the
process of being incorporated into the
JAA’s JAR–STD 1A document,
Aeroplane Flight Simulators. In
addition, Boeing states, a set of ‘‘best
practices’’ advisory material has been
developed and is being included in both
JAR–STD 1A and ICAO Document 9625.
According to Boeing,
The latest standards and best practices
material has not been included in the FAA’s
proposed Part 60. If the NPRM were to go
forward as proposed, there would be two
different sets of standards for the regulated
public to comply with. This would impose
an unnecessary adverse economic impact on
the industry, including the data provider. We
consider that the proposed Part 60, as
currently structured, would be unacceptable
to the industry, and both difficult and costly
for the FAA to administer. We strongly
recommend that the FAA revise the NPRM
prior to any further action.
Boeing includes in its comments an
extensive history of the harmonization
efforts and detailed suggestions on how
to harmonize the NPRM with the JAA
and ICAO material.
CAE comments that ‘‘The United
States has been a leading voice in
encouraging other countries to adopt
and maintain international standards;
implementation of Part 60 regulations
that are inconsistent with ICAO
standards would undermine the U.S.
Government’s credibility in making
these arguments to other countries.’’
Several commenters disagreed with
the statement in the NPRM paragraph
on ‘‘International Compatibility’’ that
the FAA had identified ‘‘no differences’’
between the proposal and the ICAO
Standards and Recommended Practices.
Thales Training and Simulation states
‘‘where there are major deviations
between the proposed Part 60 standards
and the latest agreed ICAO standards,
the motion requirements being a good
example, industry needs to be aware of
how the Part 60 standards will evolve
towards the ICAO standards. It is
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unreasonable for industry to be
expected to expend major investment to
meet a standard that may only be in
existence for a few months.’’ CAE states
there are several instances in which the
proposed rule significantly differs from
ICAO standards, including areas such as
latency, tolerances, organization of
validation test cases, numbering, and
definitions. CAE recommends that the
FAA identify and clarify the differences
between the two standards and confirm
whether the ICAO standards could be
used as an acceptable alternative for
obtaining FAA qualification of an FSD.
ATA states that the rule should not be
published until the QPS documents are
updated to reflect the ICAO guidance.
FAA Response: The FAA recognizes it
is necessary for simulator qualification
technical requirements to reflect
international standards as appropriate.
The FAA plans to harmonize the
simulator qualification technical
requirements as part of the first revision
of the QPS appendices.
Impacts on General Aviation
Several commenters are concerned
about the impact of the proposed rule
on the use of FSDs by general aviation,
particularly with respect to Level 1–3
FTDs.
FSI states that the NPRM preamble
language stating that ‘‘other certificate
holders may seek approval to use the
same FSD’’ seems to eliminate noncertificate holders, such as corporate or
private operators under part 91, from
doing the same thing. FSI comments
that fractional ownership operators
would be precluded from being
sponsors by the same wording.
Fidelity comments that due to the
recent advent of affordable, significant
computing power, general aviation is
able to use advanced simulation and
that part 61 allows for a significant
usage of FSDs. Fidelity comments that
the proposed rule is unclear as to
whether a sponsor must be a certificate
holder in order to use the FSD for part
61 training.
NAFI is also concerned about the
potential impact of the proposed rule on
general aviation flight instruction. NAFI
states that the required level of actual
aircraft emulation for high-end, full
motion simulation should be vastly
different from general aviation flight
training devices, and this proposed rule
appears to lump them together.
Specifically, NAFI states, smaller
operators with less sophisticated FTDs
will be unnecessarily burdened by the
required establishment of the QAP and
daily inspections.
National Air Transportation
Association (NATA) comments that the
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proposal seems to give consideration
only to training that targets commercial
and high-end corporate aircraft
operators and makes no attempt to
provide a framework that enables the
greater deployment of these devices for
light general aviation and corporate
aircraft. Furthermore, NATA states that
placing the responsibility for
qualification of FSDs and FTDs with the
National Simulator Program Office will
limit the ability of the aviation industry
to use such devices.
FAA Response: Only those persons
required to have an FAA approved flight
training program or otherwise
authorized under § 60.7 are eligible to
sponsor an FSTD. The FAA
acknowledges that Fractional
Ownership Program Managers are
required by § 91.1073 to have an FAA
approved flight training program.
However, this requirement did not exist
when the proposed part 60 was being
drafted because the fractional program
regulations had not been finalized. It is
beyond the scope of this rulemaking
project to include Fractional Ownership
Program Managers as eligible FSTD
sponsors. Therefore, the FAA will
initiate a separate rulemaking project to
incorporate Fractional Ownership
Program Managers into the class of
persons eligible to sponsor FSTDs. The
FAA does not intend to allow other part
91 operators to be FSTD sponsors
because they are not required to have an
FAA approved flight training program.
The FAA has not included the
qualification requirements for Level 2
and 3 FTDs in this final rule. The FAA
has determined that these devices
should continue to be monitored and
qualified under advisory material. The
FAA has posted, for comment, an
Advisory Circular providing guidance
about the evaluation and approval of
Basic Aircraft Training Devices and
Advanced Aircraft Training Devices. To
view and comment on the Advisory
Circular go to the following Web
address: https://www.faa.gov/aircraft/
draft_docs
Conforming Changes (Parts 61, 63, 125,
137, 141, and 142)
FSI states that training, testing, and
checking requirements of parts 125 and
137 may be accomplished in FSDs, but
there is no reference to these parts. FSI
suggests that the FAA clearly state the
permitted uses of FSDs.
FSI, NATA, University Aviation
Association (UAA), and Purdue
University comment that the NPRM
states that the devices described in
§ 61.4 may be used only for private pilot
certification and instrument ratings.
These commenters state that training for
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63399
a commercial pilot certificate and
training under part 141, Pilot Schools,
can also be done in an approved
training device; they ask the FAA to
verify the uses permitted for approved
training devices under parts 61 and 141.
FSI states that it is mandatory to
withdraw appendix H of part 121 in
order for part 60 to be possible. FSI also
cites other sections that should be
changed (e.g., §§ 121.407, 135.335,
142.59, 141.41, 135.324, 135.321, and
121.402). FSI suggests that the FAA
conduct a comprehensive review of all
rules that may be in contradiction to
part 60 and make the appropriate
changes.
FAA Response: The permitted uses of
FSTDs for credit purposes (i.e., to meet
airmen certification standards or certain
commercial operator training
requirements) are a topic for a different
rule. Part 60 addresses only the
requirements for the evaluation and
qualification of FSTDs. Section 61.4
does not state that FSTDs may only be
used for private pilot certification and
the instrument rating. Rather, § 61.4(a)
specifically refers to ‘‘any training,
testing, or checking requirement under
this chapter.’’ ‘‘This chapter’’ refers to
Chapter I, Subchapter D (Airmen), and
specifically, all airmen, certificates, and
ratings falling under the purview of part
61, Certification of pilots, flight
instructors, and ground instructors.
It is not necessary to withdraw all of
14 CFR part 121, appendix H because of
part 60. As stated earlier, the FAA is
‘‘removing and reserving’’ appropriate
sections of appendix H to eliminate
those technical requirements that have
been moved into part 60 and is retaining
those operational requirements in
appendix H until such time as those
sections are combined in a subsequent
rulemaking effort and appendix H is
cancelled. Additionally, the
requirements contained in §§ 121.407,
135.335, 141.41, and 142.59 are not
contrary to the requirements contained
in part 60. The FAA has reviewed all
other sections to see if any additional
conforming changes need to be made
because of part 60.
In addition, the FAA has determined
that the conforming changes to parts 61,
141, and 142 proposed in the NPRM are
no longer necessary since Level 2 and 3
FTDs are not included in this final rule.
Impact on Part 142
FSI states that when part 142 was
issued, training centers were given
regulatory assurance that if they did
certain things, the Administrator was
obligated to issue a certificate under that
part. FSI believes that for the FAA to
propose now that another step is
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required, i.e., gaining approval as a
sponsor, is improper. Also, FSI states
training centers were told they would
not be required to have any specific
relationship with an air carrier, yet
under this proposal a training center
may have to have an air carrier client as
the sponsor of the FSD, for example, to
meet the minimum annual usage
requirement.
FAA Response: The FAA eliminated
the hourly usage requirements for
sponsor qualification. The FAA
eliminated the proposed requirement for
sponsor utilization of additional
simulators, except for the initial FSTD
to qualify an applicant for a part 142
Training Certificate or the initial FSTD
as part of a part 119 FAA-approved
flight training program. The FAA has
determined that these proposed
requirements are not necessary because
the requirements for an FAA approved
training program are sufficiently robust
to ensure safety.
Elimination of Exemptions
AOPA states that the proposal places
additional regulatory burdens on the
entire aviation industry, including small
pilot training centers, simply to allow
the FAA to rid itself of the burden of
issuing exemptions to part 125 and 135
operators who wish to use Level A–D
flight simulators under part 121,
appendix H. Instead, AOPA suggests
making the appropriate changes in parts
125, 135, and 142 by cross referencing
part 121, appendix H. According to
AOPA, the proposal should then be
modified to address only part 125 and
135 operators and Level A–D flight
simulators.
FAA Response: The purpose of this
final rule is not to relieve the FAA of the
task of issuing exemptions. The
requirements set out under part 60 are
for the evaluation and qualification of
FSTDs, a task that the FAA has to
perform regardless of whether the
device will be used in air carrier
operations or not. This final rule
codifies existing practices and provides
uniform standards for all FSTDs
regardless of where they will be used.
Authorized uses under any individual
part of 14 CFR are contained in the
respective part. Therefore, even if a
device is evaluated and qualified for
certain tasks and maneuvers, the FAA,
independent of part 60, will still need
to determine whether the device is
suitable for use in a particular FAA
approved training program.
Comments Regarding Definitions
ATA states that the definition of flight
simulator uses the term ‘‘series’’ of
aircraft, while the definition of flight
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training device uses ‘‘set’’ of aircraft.
Since proposed § 60.3 does not define
‘‘series’’ of aircraft and since an aircraft
series meets the proposed definition for
‘‘set of aircraft’’ and a definition for ‘‘set
of aircraft’’ is already proposed, ATA
recommends that the term ‘‘series’’
should be deleted and replaced with the
term ‘‘set of aircraft’’ throughout the
document. In addition, the term
‘‘ground operation’’ should be replaced
with the term ‘‘surface operation,’’ since
surface operation is utilized in
Attachment 3 to appendix A as
operational task b. ‘‘Surface
Operations.’’ Also, ATA notes that the
definition of flight training device uses
the term ‘‘full size replica,’’ while
appendix B does not use this term in
describing the FTD requirements. ATA
recommends using the language in
appendix B, while Delta suggests using
‘‘realistic replica’’ instead of ‘‘full size
replica.’’
CAE states that in the definition of
‘‘evaluation’’ in the use of ‘‘etc.’’ is open
to interpretation and should be
removed. Likewise, CAE claims that the
word ‘‘performance’’ is used in a very
general sense in the definition of ‘‘flight
test data’’ and in many other places.
CAE states, ‘‘Performance in simulators
has traditionally meant airplane
performance with regard to thrust/drag
relationships, climb, range, etc.’’ CAE
recommends defining ‘‘Approved data
supplier’’ as ‘‘the aircraft manufacturer
or other supplier of data acceptable to
the NSPM.’’ CAE also recommends
defining ‘‘Performance’’ as ‘‘the overall
performance of the FSD to include
aerodynamic performance as well as
flight and ground handling.’’
Additionally, CAE recommends
changing the definition for ‘‘flight test
data’’ to ‘‘Actual aircraft performance
data collected by an approved data
supplier during an aircraft flight test
program. This includes the aircraft on
the ground test data as well as in the
air.’’
FSI states that the definition of ‘‘flight
experience’’ is at odds with § 61.1 and
other parts of 14 CFR. FSI recommends
deleting this definition or more
accurately defining it.
Boeing recommends changing the
phrase ‘‘actual or predicted aircraft
performance data’’ in the definition of
‘‘objective test’’ to ‘‘final test or
approved aircraft data’’ because it is not
clear what is meant by ‘‘actual’’ or
‘‘predicted’’ data. Boeing states that
‘‘predicted data’’ should apply to data
that are truly predicted, i.e., data that
are estimated for regions of the flight
envelope where there are no relevant
flight test data (for example, for very
high angle of attack), or for a new
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airplane configuration that has not yet
been flight-tested. Boeing believes the
definition should exclude engineering
simulation data from a simulation that
has been flight test updated and that the
definition of ‘‘predicted data’’ should
not include all aircraft performance data
derived from sources other than flight
data.
ATA states that the definition of
‘‘Qualification Performance Standard’’
should refer to ‘‘the collection of
procedures and regulatory criteria’’
instead of ‘‘the collection of procedures
and criteria.’’ ATA further recommends
that the definition of ‘‘Qualification Test
Guide’’ refer to ‘‘initial’’ evaluation and
that ‘‘approved objective data’’ be added
to the list of contents. Also, ‘‘MQTG is
the reference document for subsequent
evaluations’’ should be added to the
definition of ‘‘Master Qualification Test
Guide.’’
Boeing asks whether ‘‘set of aircraft’’
is a derivative series of models
produced by the same manufacturer or
does it encompass a class of aircraft,
such as a medium twin-engine jet
transport? CAE states that in the
definition of ‘‘Set of Aircraft,’’ a
reference is made to ‘‘handling,’’ when
in all previous places ‘‘performance’’
has been used to cover both the
conventional aerodynamic performance
and handling. To be more consistent,
CAE recommends replacing ‘‘handling’’
with ‘‘performance.’’
FSB believes that the term ‘‘Sponsor’’
must be more clearly defined to include
who may be or must be the ‘‘Sponsor’’
of a particular simulator (FSD). FSB
states, ‘‘There are many proposed
references in the NPRM that place a
requirement, responsibility, or burden
on the actual owner of the FSD that will
effectively eliminate the ability to
acquire and maintain U.S. certification
of the FSD. The overall impact of this
NPRM, if adopted without major
changes, could potentially eliminate
Part 142 Certificate Holders as providers
of U.S. certified FSDs.’’ FSB
recommends that the entity that is the
financially responsible owner of the
FSD, and is a certificate holder, must be
the sponsor of the FSD. The rule must
not disqualify this entity as the sponsor
because of arbitrary conditions such as
how or how much the FSD will be used
as long as the device continues to meet
applicable qualification standards.
ATA states that the definition of
‘‘Subjective test’’ is inconsistent with
appendix A, Attachment 3, Item 3,
Simulator Systems. CAE states that in
the definition of ‘‘Subjective test,’’ it is
stated ‘‘FSD performs and handles.’’
CAE recommends changing the
definition of ‘‘Subjective test’’ as
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follows: ‘‘A qualitative comparison to
determine the extent to which the FSD
performs like the aircraft being
simulated.’’
CAE states, in reference to the
definition for ‘‘Training Program
Approval Authority,’’ that parts 121,
135, and 142 are currently established
as to who may approve training
programs. In CAE’s opinion, no new
authority needs to be introduced or
created by part 60.
FAA Response: The FAA wishes to
clarify the distinction between a
‘‘series’’ and a ‘‘set of aircraft.’’ An
example of ‘‘series’’ would be the
Boeing B–737 aircraft, where –200 is a
‘‘series’’ (e.g., –222, or –252, or –265 are
part of the –200 ‘‘series’’) as opposed to
a –300 aircraft in the same make and
model (Boeing, B–737 line). ‘‘Set of
aircraft,’’ is defined as ‘‘aircraft that
share similar handling and operating
characteristics and similar operating
envelopes and have the same number
and type of engines or power plants.’’
While aircraft in the same ‘‘series’’ can
certainly be described as being within
the same ‘‘set of aircraft,’’ it is not true
that aircraft that are legitimately in the
same ‘‘set’’ are necessarily in the same
‘‘series.’’ For example, we can consider
the Boeing B–737–222, the Boeing B–
757–252, and the Embraer EMB–170–
100 within the same ‘‘set’’ of aircraft
(i.e., they share similar handling and
operating characteristics and similar
operating envelopes and have the same
number and type of engines); however,
it is obvious that these three are not the
same ‘‘series’’ of aircraft. A ‘‘series’’ of
an aircraft make and model is not the
same as a ‘‘set’’ of aircraft.
The FAA has clarified the definition
of ‘‘set of aircraft.’’ In response to
Boeing’s question about set of aircraft,
the FAA notes that while a ‘‘set of
aircraft’’ may include a derivative series
of models produced by the same
manufacturer, the definition does not
restrict ‘‘set’’ to derivative series. Rather,
‘‘set’’ encompasses aircraft with similar
handling and operating characteristics, a
similar operating envelope, as well as
the same number and type of engines or
power plants as in the commenter’s
example of a ‘‘medium twin engine jet.’’
In the NPRM, the FAA used the terms
‘‘ground operation’’ and ‘‘surface
operation’’ interchangeably. The FAA
recognizes that this could be confusing
and has clarified the final rule to use the
term ‘‘surface operations’’ throughout
the document to be consistent with
international harmonization.
In the final rule, we changed
references from ‘‘full size replica’’ to the
more simple term ‘‘replica’’ and
clarified the definition by changing the
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phrase ‘‘ground and flight operations’’
to ‘‘operations in ground and flight
conditions.’’ We made a similar change
to the definition of ‘‘Flight Training
Device (FTD)’’ where we used the
simplified term ‘‘replica’’ instead of the
term ‘‘full size replica’’ and to the
phrase ‘‘aircraft in ground and flight
conditions’’ where we used ‘‘aircraft
operations in ground and flight
conditions’’ for consistency with the
definition of an FFS.
To avoid the confusion of including
‘‘etc.’’ in the definition of ‘‘evaluation’’
as raised by CAE, we have included
‘‘e.g.’’ instead so the sentence now reads
‘‘With respect to an FSTD, the
qualification activities (e.g., the
objective and subjective tests, the
inspections, the continuing qualification
evaluations) associated with the
requirements of this part.’’
We have added a definition of ‘‘FSTD
Performance’’ to read ‘‘The overall
performance of the FSTD includes
aircraft performance (e.g., thrust/drag
relationships, climb, range) as well as
flight and ground handling.’’
The definition of flight experience is
limited to part 60. Therefore, it does not
conflict with other parts. The FAA has
clarified the definitions of ‘‘flight test
data,’’ ‘‘objective test’’ and ‘‘predicted
data’’ to be more precise. The FAA notes
that the use of engineering simulation,
as an engineering analysis tool, may be
integrally involved in the development
of aircraft performance predictions.
The FAA did not revise the definition
of ‘‘Qualification Performance Standard
(QPS)’’ except to include a reference to
appendix E, Quality Management
System for Flight Simulation Training
Devices. Also, the FAA did not revise
the definition for Master Qualification
Test Guide (MQTG); however, we did
clarify the definition of Qualification
Test Guide (QTG). The FAA did not
revise the definition of ‘‘sponsor.’’ The
FAA has not substantively changed the
definitions of QPS, MQTG, QTG, and
sponsor from the definitions as
proposed in the NPRM. However, the
FAA has addressed the concerns raised
by the commenters by making other
appropriate changes to part 60 and the
QPS appendices. The definitions of
these terms are consistent with the
recommendations made by the ARC.
The FAA has reformatted the material
originally located in appendix A,
Attachment 3. That material is now
found in a table entitled ‘‘Table of
Functions and Subjective Tests,’’ and is
consistent with the title of the appendix.
Additionally, the FAA has clarified the
definition of ‘‘subjective test.’’ The
changes are consistent with the ARC
recommendation.
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63401
The FAA is not proposing to establish
a new entity to approve training
programs. The term Training Program
Approval Authority (TPAA) was
introduced as a ‘‘shorthand’’ way of
listing the various combinations of titles
of those who are currently authorized to
provide such approvals; i.e., ‘‘Principal
Operations Inspectors (POI), Training
Center Program Managers (TCPM), or
Flight Standards District Office (FSDO)
operations inspectors assigned the
duties of training program oversight and
approval.’’ The FAA has not changed
the definition of TPAA as proposed in
the NPRM.
Comments Regarding Abbreviations
CAE suggests adding new
abbreviations to differentiate between
airplanes and helicopters, as follows:
AFSD—Airplane Flight Simulation
Device
HFSD—Helicopter Flight Simulation
Device
AFTD—Airplane Flight Training Device
HFTD—Helicopter Flight Training
Device
FAA Response: The FAA has not
added these abbreviations and does not
consider them necessary for clarity.
Comments Regarding the Applicability
of the Part 60 Rule and the Use of Flight
Simulators
Use of FSTDs
ATA states:
This rule provides regulatory information
and further guidance to those who wish to
become Sponsors of one or more FSDs and
how a Sponsor must act to qualify and
maintain the qualification of an FSD. In
addition, it provides the technical
requirements for an FSD to be awarded a
specific level of qualification. This rule
should not address how an FSD is used. That
information is contained within other parts
of this Chapter and should be between the
Training Program Approval Authority
(TPAA), the Sponsor, and the user.
United agrees with ATA’s
recommendation to remove the words
‘‘and use’’ from the title of part 60 and
§ 60.1(a).
FAA Response: This rule is not
intended to infringe upon the FAA
designated TPAA. The phrase ‘‘and use’’
in the title of the part 60 rule has
specific and limited application: (1) To
the ‘‘use’’ requirements for simulator
sponsorship; (2) to the ‘‘use’’ limitations
with missing, malfunctioning, or
inoperative components; (3) to those for
whom ‘‘use’’ of the FSTD is authorized
and for whom its ‘‘use’’ may apply; and
(4) to those ‘‘uses’’ of the FSTD for
which representatives of the NSPM have
evaluated and qualified a specific FSTD
and may be referenced in the Statement
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of Qualification, Non-Qualified
Maneuvers, Procedures, and Tasks (as
listed by exception to those maneuvers,
procedures, and tasks listed in the
subjective evaluation contents found in
Attachment 3 to each of the applicable
QPS appendices). Examples might
include a circling approach; windshear
training in accordance with 14 CFR
121.409(d); Surface Movement and
Guidance System (SMGS); or Weather
Radar System. These ‘‘uses’’ are not to
be confused with the uses for which a
specific FSTD may or may not be
approved by the FAA designated TPAA.
Qualified FSDs
ATA states:
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* * * this applies to ALL FSDs. It does not
address the use of FSDs that are not qualified
by the FAA but are used as part of an
approved training program even though no
training credits are granted. For example, one
carrier has used their B727 CPT and a DC–
10 Level 4 equivalent device for training in
an approved training program even though
neither was qualified by the NSP * * *. This
paragraph should be changed to allow for the
use of non-qualified FSDs as training aids in
an approved training program. This is then
under the jurisdiction of the POI. This could
be done in paragraph 1.1, definitions, to
exclude unapproved devices from the
definition of FSDs. Similarly, the rules,
requirements, and penalties associated with
using an FSD that is not qualified should
themselves be clarified to allow for the use
of non-qualified FSDs with TPAA approval.
FAA Response: The FAA recognizes
the functionality of many pieces of
equipment (e.g., FSTDs, books,
Computer Based Training Aids) that can
be used in an effective pilot or other
flight crewmember training program.
This final rule does not prohibit a POI
from authorizing the use of any training
aid that will provide valuable
instruction to flight crewmembers.
While these devices can be authorized
for use in a training program, only those
devices that meet the definitional
requirements in part 60 (i.e., that have
been evaluated and found to be
qualified at a stated level) can be
referred to as ‘‘FSTDs.’’ To be called an
FSTD, and to fall under this part, the
device has to meet the stated definition
and evaluation requirements. Other
equipment that may or may not be
found to be suitable for use in a pilot
training curriculum, whether or not that
curriculum is approved by the FAA,
may not be called FSTDs (either FFSs or
FTDs) when the device being referenced
does not meet the definition or
evaluation requirements of an FSTD.
Clarification of Terms
FSI states that the preamble statement
regarding ‘‘operating experience’’ makes
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it unclear what is prohibited in an FSD.
FSI recommends that the FAA list the
sections of 14 CFR for which an FSD
may not be used.
Two commenters address the term
‘‘each person’’ in paragraphs (b) and (c).
JAA states, ‘‘It is still difficult to
understand why an individual of an
FSD user organization, which does not
(necessarily) own the FSD, would be
responsible for the quality of the FSD
and not the FSD operator.’’ CAE
recommends that in paragraph (c) ‘‘each
person’’ should be the sponsor or a
person leasing the equipment.
FAA Response: The FAA did not
adopt a specific list of sections in 14
CFR for which an FSTD may not be
used. The TPAA determines what the
FSTD may be used for on a case by case
basis. However, the FSTD may never be
used for satisfying the operating
experience requirements of § 121.434 or
§ 135.244.
The term ‘‘person’’ is a multiple use
term that, in the vernacular, might be
read ‘‘the appropriate party.’’ It is
important to note that the term
‘‘person,’’ as used in the referenced
sections (i.e., ‘‘each person using’’ and
‘‘each person who uses’’), is defined in
14 CFR part 1 as ‘‘an individual, firm,
partnership, corporation, company,
association, joint-stock association, or
governmental entity. It includes a
trustee, receiver, assignee, or similar
representative of any of them.’’
Comments Regarding the Applicability
of Sponsor Rules to Persons Who
Conduct Sponsor Activities Without
Being Qualified Sponsors (§ 60.2)
FSI states that, contrary to the NPRM
preamble discussion, the issue of a nonsponsor using or allowing the use of an
FSD is clearly an administrative rule,
not a safety rule; even the discussion
uses the word ‘‘inappropriately,’’ not
‘‘unsafely.’’ FSI further states that the
FAA goes on to illustrate in the actual
proposed section text with examples of
permitted practices rather than listing
prohibited practices. FSI recommends
that the FAA clearly articulate those
practices that are prohibited in the
actual text, and accurately discuss
applicability of this section to nonsponsors. In addition, FSI states that
paragraph (a)(1) adds another step in the
process of being able to use an FSD, i.e.,
separate approval as a sponsor.
CAE states that the use of the term
‘‘causes’’ in § 60.2(a) is too general. For
example, a technician asked to switch
the motion pump on cannot be
considered to be the cause for the use
of the device for unauthorized training.
CAE recommends changing the text to
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be more specific about the persons to
which this rule applies.
FAA Response: The purpose of the
rule language in § 60.2(a) is to give the
FAA a legal means by which it could
charge a nonsponsor with violations of
the safety rules if that person
inappropriately used or caused the use
of an FSTD for the purpose of meeting
an airmen certification or training
requirement under the Federal Aviation
Regulations. The FAA believes that a
safety issue could be raised if a nonsponsor uses or allows the use of an
FSTD because the quality of the device
could be called into question. Therefore,
the FAA believes that the prohibition on
non-sponsor use of a device is a safety
rule and did not adopt changes to this
section other than changing the term
‘‘FSD’’ to FSTD.’’
The FAA does not consider the term
‘‘causes’’ in paragraph (a) to be too
general. The FAA does not consider
someone who merely turns on the
hydraulic motion pump to be the person
who ‘‘causes’’ the use of the FSTD. An
example of ‘‘causing’’ the use of the
device would be someone fraudulently
holding themselves out as a sponsor,
thereby ‘‘causing’’ an unqualified device
to be used in an FAA approved training
program.
Comments Regarding Quality
Management System (§ 60.5)
JAA notes with appreciation that the
FAA is introducing a mandatory QAP.
JAA suggests making the QAP into a full
Quality System (QS) and adding the
components that are found in the
required JAA QS.
CAE supports the requirement that
each sponsor implement a QAP, but
believes that the sponsor should be
allowed to use its own quality assurance
processes to meet the NSP standards.
CAE states, ‘‘It would be inefficient and
costly to force all sponsors to adopt
quality assurance measures based on a
specific, FAA-selected QAP as
described in Section 60.5. Companies
must be given the flexibility to
implement a QAP that is consistent with
their operations and business practices
and plans.’’
FAA Response: To harmonize with
ICAO, the FAA changed the title of
§ 60.5 Quality Assurance Program to
Quality Management System (QMS).
The new title is not just a name change,
but is in fact a complete revision of the
quality assurance program that is
significantly less costly and onerous
than what the FAA originally proposed.
The specific requirements for the QMS
are outlined in a new appendix to the
QPS requirements entitled Appendix E,
Quality Management Systems for Flight
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Simulation Training Devices. This new
appendix does not add new
requirements outside the scope of the
requirements proposed in the NPRM,
but expands on the rule language of
§ 60.5, Quality Management System.
The requirements contained in
appendix E have been carefully
designed to allow each FSTD sponsor
the capability of using its own QMS
process to meet the described standards.
Justification for Quality Programs
ATA does not oppose the concept of
a QAP, but states that the FAA has not
offered any evidence that there
currently exists a quality control
problem in the way part 121 operators
maintain their FSDs. For example, an
analysis of nine years of FAA
evaluations at one major carrier yielded
a discrepancy rate of 2.8 discrepancies
per evaluation. ATA believes the other
regulations would allow the NSPM to
take action against an operator that does
not meet minimum quality levels. ATA
and FedEx believe the incremental
benefit of creating and administering a
QAP will not be worth the cost of doing
so. NLX makes a similar comment,
citing the present state of the airline
industry.
FAA Response: The FAA did not
propose to incorporate a quality
assurance program, which differs from a
traditional ‘‘quality control’’ program, to
rectify bad or deteriorating maintenance
practices for individual FSTDs or at
specific FSTD sponsor locations. As
described in the original NPRM, the
basic precept of the program is for the
sponsor ‘‘to say what it does; to do what
it says; and to keep good records.’’ The
QMS program will require each sponsor
to develop a working knowledge of the
requirements of part 60 and the relevant
QPS document. This knowledge will be
demonstrated to the NSPM through a
written description of how, how often,
when, where, and with what resources
the sponsor’s organization plans to
comply with the requirements of part
60.
By having this written description,
the NSPM and the sponsor will be able
to compare what is actually done with
what the sponsor says is done regarding
FSTD repair, modification, regular
maintenance, and daily readiness. The
FAA has determined that the
standardization required for such
satisfactory comparisons will add to the
already existing efficiency and
effectiveness of the FSTD—regardless of
the level of that existing efficiency and
effectiveness. Through the added
reliability of the maintenance and the
daily readiness provided by a sound
QMS program, any flight crewmember
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training, evaluation, and flight
experience should be able to be
accomplished with less interruption,
more accuracy and more reliability. The
QMS program will help provide
consistency in the current training and
the availability of repetitive practice in
the desirable environment of accurate
and realistic simulation. The FAA
continues to believe that under such
circumstances the students will more
easily retain the knowledge and skills
learned through such an increase in
reliability and through such
uninterrupted training.
There are three areas of significance
in this regard:
The first, in two parts. Part one is an
already existing precedence for the
regulatory requirement for a QMS
program found in the regulations
covering air carrier aircraft
maintenance. Part two is that several air
carriers currently participate in
voluntary quality programs (involving
FFSs and FTDs) due to their
participation in the FAA’s Air
Transportation Oversight System
(ATOS).
The second area is that of existing
FSTD sponsors already obtaining
advantages from either developing an
FSTD QMS program or contemplating
doing so. One major airline, in
comments made to this NPRM, stated
that while reviewing the proposed QMS
program requirements they recognized
that ‘‘the proposed (QMS) did provide a
vehicle for developing a more efficient
management tool for simulator
maintenance and control.’’
The third area is one of international
perspective. The FAA has not noticed
that many of the world’s regulatory
authorities are beginning to embrace
QMS programs or quality management
systems as a means of conducting their
regulatory responsibilities. Example of
such regulatory authorities include the
individual regulatory authorities in
Europe, under the auspices of the
European Aviation Safety Authority
(EASA) and several regulatory
authorities in the Pacific Rim (the
Australian CAA and the Singapore
CAAC are two examples), who are
aiming to pattern their systems after that
of the JAA. Additionally, if FAA
requirements are to be truly
‘‘harmonized’’ with the JAA, then it
must be noted that the JAA’s JAR–STD–
1A document, Aeroplane Flight
Simulators, requires an FSTD operator
to have, and operate under, a quality
management program, which is far more
demanding than the QMS that we
adopted under part 60.
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Cost Consequences of Quality Programs
RAA requests the removal of the
proposed QAP requirement from the
final rule. RAA states that the FAA has
made no effort to evaluate the necessity
or effectiveness of the proposed QAP.
RAA believes the QAP would require
airline operators to maintain technical
staff on site, which would be
particularly cost prohibitive for regional
airline operators who often buy time on
simulators at distant and even foreign
locations. TechniFlite makes a similar
comment. If the FAA retains the
requirement, RAA suggests allowing the
owner-operator to designate a simulator
evaluator or to outsource QAP duties.
FAA Response: Neither the original
NPRM nor the revised wording in the
final rule would require an airline to
maintain their own technical employees
at the FSTD site, if that airline is using
another sponsor’s FSTD, for QMS issues
any more than the current practice of
arranging with another party to provide
for maintenance, upkeep, modification,
evaluation, evaluation scheduling of an
FSTD it sponsors. In either case, the
sponsor would be the responsible party
concerning issues with the FSTD that
relate to technical aspects or to the QMS
program.
Six Month Time Limit
UPS objects to the 6 month time limit
for submission and approval of a QAP,
stating that the NSPM would have an
influx of approximately 66 proposals
from sponsors to review, comment and
approve within that timeframe. Also
UPS states that 6 months is an
insufficient amount of time for UPS to
develop and implement a program that
would meet the requirements. UPS
recommends an 18 month timeframe, 6
months to submit a proposed program,
6 months for the FAA to review and
approve, and 6 months for the sponsor
to implement the program. American
makes a similar comment. ATA suggests
a longer timeframe, one year for
submitting a proposal, 6 months for the
FAA to review and approve, and one
year to implement and audit the QAP.
FAA Response: The FAA has revised
this time frame to 24 months. The FAA
has determined that this is a sufficient
amount of time to implement the QMS.
Dry Lease of Simulators
FSI suggests a problem with the
concept of a sponsor for operators who
dry lease flight simulators that are used
by several air carrier certificate holders.
FSI states, ‘‘Under the proposed
concept, quality would be assured for
only one (sponsor) user, but not for
other users.’’ FSI believes that the
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purpose of a QAP should be to ensure
that any training provider (i.e., not just
the sponsor) is capable of providing
FSDs that continually meet the training,
testing, checking, and experience
requirements of its client’s FAAapproved flight training programs. FSB
makes a similar comment, stating,
‘‘Particularly in a part 142 operation,
this would result in each device within
a single facility being subject to a
different Sponsor’s QA program.’’ In
this situation FSB believes the owner/
certificate holder should qualify as the
sponsor, even if they don’t otherwise
meet the sponsorship qualifications,
because they have ultimate
responsibility for the devices under the
QAP.
regarding sponsor qualification
requirements to address the concerns
and recommendations raised by
commenters. The QMS program assures
that any given FSTD continually meets
the training, testing, checking, and
experience requirements of the
respective FAA-approved flight training
program in which it is used.
Conflict With Other Quality Programs
ATA and United comment that
inclusion of this quality program places
airlines under two dissimilar quality
programs; that required by § 60.5 and
the Air Transport Oversight System
(ATOS) item 4.2.8, Simulators/Training
Devices. Since the goal of these two
quality requirements are the same—
system safety—ATA and United suggest
that these two quality program
requirements should be appropriately
harmonized so that a sponsor now
subject to part 60 and ATOS will be
required to meet the standards of only
one FSD quality program.
FAA Response: The FAA has revised
the ATOS inspection checklists and
eliminated the Airworthiness SAI/EPI
components for an FSS or an FTD
inspection to avoid different quality
management programs for aircraft
simulators. The changes to the ATOS
program checklists will become
effective at the same time as this final
rule.
sroberts on PROD1PC70 with RULES
Conflict Between NPRM Preamble and
Rule
Several commenters address an
inconsistency between the preamble
discussion of proposed § 60.5 and the
rule text itself. Paragraphs (b) and (d), as
described in the preamble, do not
appear in the rule text.
FAA Response: The FAA recognizes
that an error occurred with the original
publication of the NPRM. We removed
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paragraph (d) that appeared in the
NPRM and incorporated the
requirements of that paragraph into
§ 60.9 in the final rule. The FAA has
reinserted as § 60.5(d) the correct
paragraph (d) that was described in the
NPRM preamble. This paragraph reads
the same as a similar paragraph
published in the NPRM under
§ 60.29(b).
NSPM have not agreed to accept each
other’s QMS programs, the sponsor then
will be required to reach an agreement
with the NSPM regarding those aspects
of the sponsor’s QMS program that may
be met by the sponsor in regard to this
specific FSTD.
Location of Simulator
ATA comments that the paragraph
described in the preamble that
addressed the location of the simulator
would be impossible to comply with.
ATA cites as an example, an operator
who sponsors a foreign owned simulator
located in an area of the world where it
bases pilots. It is cost-effective to use
that simulator rather than bring pilots
back to the U.S. for training. ATA states
the paragraph would require operators
to impose a QAP on the foreign
simulator owner, which would be
impossible for the FAA to enforce.
Similarly, FedEx believes the
requirement should not appear in the
final rule or should be modified to
facilitate the use of foreign simulators.
FAA Response: Prior to the use of any
FSTD, regardless of its location
(domestic or foreign), the certificate
holder is responsible for determining
that the FSTD meets the appropriate
training program requirements and that
supplemental ‘‘differences’’ training is
accomplished to accommodate any
differences that may exist. Similarly, the
certificate holder is responsible for
ensuring that the current maintenance
and operational status of the FSTD is
such that the planned activities can be
successfully accomplished or other
arrangements are suitably made. This
level of familiarity with the FSTD and
this level of interaction with the owner/
operator of the FSTD should certainly
support the QMS program requirements.
The FAA has revised the requirements
so that when a sponsor includes a
‘‘foreign simulator’’ (i.e., one
maintained by a non-U.S. certificate
holder) under its sponsorship, the
sponsor will continue to be responsible
for the QMS program for that simulator;
however, if that foreign simulator is
maintained under a QMS program
accepted by that foreign regulatory
authority and that authority and the
NSPM have agreed to accept each
other’s QMS programs (e.g., QMS
programs approved by the Joint
Aviation Authorities of Europe), no
additional requirements must be met.
Alternatively, if that foreign simulator is
not maintained under a QMS program
accepted by that foreign regulatory
authority or that authority and the
ATA believes the final rule should
include another paragraph described in
the preamble, but not included in the
proposed rule, which addressed an
appeal process for sponsors who
disagree with an FAA requirement to
modify a QAP. Boeing, CAE, and FSI
make similar comments. FSI requests
more specific statements on how the
determination of an emergency would
be made and whether any sanctions
would apply to just one FSD or all FSDs
operated by the sponsor.
FAA Response: As stated earlier, the
FAA has now included the material that
was referenced in the original NPRM
preamble language but which was
inadvertently omitted in the originally
proposed rule language. The FAA is
reluctant to provide a list of what might
constitute an ‘‘emergency’’ in that all
such possibilities simply cannot be
accurately listed. The purpose of this
rule is to provide for FSTDs that meet
the established criteria to allow flight
crewmembers to acquire proper and
complete training, testing, checking, and
experience for the particular aircraft for
which they will be or are type rated.
While it is true that the FAA may have
the authority to take certificate action or
seek monetary penalties for violations of
the rules, or seek to remove the
qualification of an FSTD, or disqualify
an FSTD sponsor from sponsoring
FSTDs, these types of actions are a last
resort taken only when absolutely
necessary. When, how, to what, and to
whom any such sanctions might apply
would be governed by the circumstance,
and therefore, the FAA is unable to
provide specifics for such possibilities.
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Appeal Process and Determination of
Emergency
Quality Program Guidance
ATA comments that neither the rule
nor the QPS provide information on
how the QAP should be set up and
administered. ATA also comments that
there is no reference to the current
guidance documents that appear on the
NSP Web site. ATA suggests that the
FAA reorganize the QAP requirements
by combining proposed § 60.5(b), (c),
and (d) with the QAP requirements in
appendix A, section 5, and moving them
to a new appendix E, which would be
a QPS for a QAP. ATA recommends that
the new appendix contain appropriate
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components of the current guidance and
sample of an acceptable SQAP.
FAA Response: The FAA has
reorganized the QMS requirements in
the QPS appendices and established one
QMS appendix, appendix E, to provide
greater clarity and avoid redundancy.
sroberts on PROD1PC70 with RULES
Identification of Deficiencies
CAE believes the language of
proposed § 60.5(b) is too vague and that
the FAA should specify the level of
detail required in the documentation for
correcting deficiencies in the QAP. CAE
suggests changing the words ‘‘deficiency
in the program’’ to ‘‘an issue that has a
direct impact on the quality.’’ American
states that it is unclear whether the
deficiencies being identified are in the
QAP or in the FSD maintenance
program. ATA states that if the
deficiency being identified is in the
QAP, then the FAA process should
specify how it is to be changed.
FAA Response: The FAA has made
clarifications to § 60.5. The language of
§ 60.5, Quality Management System,
was chosen to allow for future revisions
to the QMS program, as described in
appendix E. One of the major precepts
of any quality management system is
that of continual improvement—
improvement as defined by the
organization utilizing the quality
management system that can be
recognized by an outside observer. An
improvement might manifest itself in
the improved maintenance or the
reliability of the FSTD; it might manifest
itself in an increased efficiency in being
able to track some aspect of the on-going
maintenance functions; or it might
manifest itself in a more detailed
description of a job function or more
clearly defined documentation or a
better way to ensure that management is
involved in decisions regarding the
QMS program or the quality
management system.
Grace Period for Required Changes
ATA suggests that § 60.5(c) provide a
12 month time limit within which the
sponsor must make the required
changes to the QAP, so that it is not
immediately in violation after being
notified of the required change. CAE
makes a similar comment. ATA and
United request clarification of whether
paragraph (c) addresses the pre-approval
process or the process when program
deficiencies are discovered during an
audit.
FAA Response: The FAA made minor
clarifications to § 60.5(c). The FAA did
not adopt specific time limits as
recommended by commenters, because
such revisions are outside the scope of
the NPRM. However, in future changes
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to the QPS requirements, the FAA will
consider adding specific timeframes as
recommended by commenters. Such
changes would be subject to notice and
comment. In addition, the FAA notes
that § 60.5(d) allows sponsors to appeal
to the Director of Flight Standards
(Director) if the sponsor disagrees with
the NSPM’s deficiency notice. The filing
of an appeal stays the NSPM’s notice
pending the Director’s decision. Thus, a
sponsor can appeal to the Director if it
believes that the NSPM has not allowed
adequate time to resolve a deficiency.
Management Representative
FSI comments that identifying an
employee of the sponsor to be the
management representative, under
proposed paragraph (d), may result in
delayed or confused communication if
that person is someone other than the
training center’s designee. American
Trans Air asks whether the management
representative under this section could
be the same person as the liaison with
the manufacturer designated under
§ 60.9(b)(3).
FAA Response: As previously
mentioned, the FAA moved proposed
paragraph (d) to § 60.9(c) in the final
rule. (See the discussion in § 60.9 for
additional responsibilities of the
sponsor). In the NPRM, the FAA
proposed that a sponsor maintain
liaison with the aircraft manufacturer or
the holder of the type certificate if the
manufacturer was out of business. The
FAA notes that maintaining a liaison
with the aircraft manufacturer does not
mean that the sponsor must designate a
specific person to serve as a ‘‘liaison.’’
The Management Representative (MR)
may perform this duty if necessary.
There is no requirement that the MR be
the training center designee. The only
requirement is that the person so
designated as the MR by the sponsor
have the responsibility and authority to
accomplish duties outlined in § 60.9(c).
Comments Regarding Sponsor
Qualification Requirements (§ 60.7)
Many commenters are concerned
about the concept of FSD sponsorship as
proposed in § 60.7(a) and (b). Some
commenters request the FAA delete,
change, or clarify the sponsorship
requirements.
RAA states that § 60.7 proposes to
have individuals such as pilots,
instructors, and check airmen be
sponsors rather than a part 121 or part
135 (i.e., part 119) certificate holder.
RAA agrees that such individuals fit the
criteria sought by this proposal, but
believes that a collective body of
‘‘individuals’’ that comprise an air
carrier also fit the criteria. RAA states,
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63405
‘‘It makes no sense to make a distinction
between a person and a certificate
holder, particularly since both are
subject to loss of their certificate by the
FAA.’’ RAA requests that the concept of
‘‘sponsor’’ be eliminated from the
proposed rule.
FAA Response: The FAA has revised
and clarified the sponsorship
requirements of § 60.7.
The FAA defines the term ‘‘person’’ in
14 CFR part 1 as ‘‘an individual, firm,
partnership, corporation, company,
association, joint-stock association, or
governmental entity. It includes a
trustee, receiver, assignee, or similar
representative of any of them.’’ In § 60.7,
the FAA uses ‘‘person’’ in accordance
with the part 1 definition. Additionally,
as used in this particular situation, the
‘‘person’’ being referred to would hold
or be an applicant for a certificate under
part 119, 141, or 142, or have a course
of training approved under appendix C
of part 63. A ‘‘person’’ whether
corporate or individual, can hold a
certificate issued under part 119, 141, or
142. However, an individual person
who holds only an airman certificate
(e.g., issued under part 61), would not
qualify to be an FSTD sponsor.
The National Simulator Program has
operated under the concept of
‘‘sponsor’’ for over two decades.
However, the National Simulator
Program has never been specific
regarding the definition of the term, nor
has the agency been diligent in ensuring
that all of the precepts of FSTD
utilization were scrupulously followed.
The FAA believes that it is time that this
concept is completely understood by
everyone in the industry.
Sponsorship Qualification
Requirements
FSB believes that the proposed
sponsorship qualification criteria will
seriously affect third party operations
and that the NPRM, if adopted without
major changes, could potentially
eliminate part 142 certificate holders as
providers of U.S. certified FSDs.
Examples of situations that FSB believes
would no longer be allowed are cases
where the FSD is owned by a part 142
certificate holder but is used principally
by other certificate holders. If neither
the owner nor any of the other users met
the specified minimum threshold of
hours under their approved training
programs, none of these users would
meet the sponsorship standards, even
though the FSD might serve many U.S.
certificated operators. Also, the owner
might be forced to change the
sponsorship of some FSDs from time to
time in order to continue to have a
sponsor who meets the conditions of
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sponsorship. FSB recommends that if
the owner is a U.S. certificate holder,
that the responsible certificate holder
should be the sponsor of the FSD,
without having to meet all the
requirements in this section.
Further, FSB comments that there are
circumstances in part 142 operations
where FSD certification is necessary,
but there is no plan by the FSD owner
to conduct training. FSB states, ‘‘This
proposal is a case where a prerequisite
for Sponsorship is based on intended
use of the device. It is the opinion of
FSB that the proposed regulation should
focus on the quality and functionality of
the device and that approvals for how
the device will be used should be left
[to] the Principle Operations Inspector
(POI), or the Training Center Program
Manager (TCPM), or other appropriate
approval authority.’’ FSB recommends
that § 60.7(a)(2) be deleted.
FSI objects to the NPRM preamble
statements that the sponsorship and
approval process proposed is similar to
the current practice. FSI states,
‘‘Currently, there are no ‘sponsors’ of
simulation. The FAA has never defined
the term; there has never been a
requirement to have or to be a sponsor.
The term, concept, and obligation is
proposed in this Notice of Proposed
Rulemaking for the first time. The
implication that sponsors exist now and
have been required tends to minimize
the operational and economic impact of
the current proposal.’’ Further, FSI
comments, ‘‘The process outlined in the
proposed part 60 is not at all similar to
current practice in one of the major
features of the proposed rule. That is,
the current practice, (and practice for
the past many years), has been for the
FAA to evaluate, qualify, and then
approve for use FSDs for a certificate
holder having an approved training
program. Now the FAA would add the
major step of approving a person, not
necessarily the developer, owner, or
custodian of an FSD as a sponsor. This
is a major departure from current
practice.’’ FSI recommends that the
FAA delete any requirement for a
sponsor to be a certificate holder and
specify that a training center may
continue to fulfill all proposed roles of
a sponsor and the term sponsor be
eliminated.
ATA states that proposed § 60.7 does
not explain or provide a process for
gaining sponsorship approval. ATA
recommends that the sponsorship
qualifications and systems and
processes needed to manage the new
requirements be established in a predefined order over a certain period as
part 60 goes into effect.
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In regard to proposed § 60.7(b), FSI
asks for clarification of the relationship
between the four conditions in this
paragraph, i.e., whether the sponsor
must meet any or all of the four
conditions. ATA identifies an
inconsistency between proposed
§ 60.5(a), which allows a sponsor 6
months to develop a QAP after the final
rule is effective, and § 60.7(b)(3), which
states that a sponsor must have an
approved QAP. ATA recommends a
long period of phase-in for the final rule
and an automatic qualification for items
that were in good standing before the
effective date. ATA also comments that
proposed § 60.7(b)(4) gives the NSPM
full veto power over a candidate
sponsorship, with no definitions of how
the NSPM will evaluate the candidate
sponsor’s acceptability to the NSPM.
FAA Response: The changes to the
sponsorship requirements discussed
previously adequately address the
issues raised by the commenters. In the
final rule, the FAA eliminated the
proposed requirement that a sponsor
use the device for 600 hours per year.
We are now requiring that at least one
FSTD is used at least once per year
within the sponsor’s FAA-approved
flight training program. Also, the final
rule permits the sponsor to sponsor
additional FSTDs, beyond the first
FSTD, without having a ‘‘use’’
requirement. If a sponsor sponsors an
additional FSTD that is not used within
its approved training program then one
of the following conditions must be met:
(1) The FSTD must be used in another
FAA-approved flight training program.
(2) The sponsor must provide the
FAA with a written statement from a
qualified pilot having flown the airplane
that is simulated at least once during the
previous 12 months. The statement
must indicate that the configuration,
performance, and handling of the FSTD
are appropriately representative of those
features of the airplane being simulated.
Additionally, while it is true that the
FAA does not currently use the specific
term ‘‘sponsor,’’ the agency, under its
existing practices, does assign someone
to ‘‘oversee’’ each qualified FSTD. Thus,
the requirements in § 60.7 are simply a
codification of the agency’s current
policies.
The rule language is clear about what
is necessary for a person to become an
FSTD sponsor and what requirements of
part 60 will apply to existing FSTDs.
With limited exceptions, the continuing
qualification requirements for existing
FSTDs will not change.
Role of TPAA
Eclipse states that the proposed rule
puts the sponsor in a precarious
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position between the NSPM and the
sponsor’s specific TPAA. Eclipse
Aviation would like to see a better
delineation of duties and a more
formalized coordination process within
the FAA between these two bodies.
FAA Response: The FAA has
modified its processes regarding
coordination and communication with
Principal Operations Inspectors (POI)
and Training Center Program Managers
(TCPM). The NSPM will provide a
Statement of Qualification directly to
the sponsor (copying the POI/TCPM)
and will receive materials directly from
the sponsor (provided parallel
communication is maintained with the
POI/TCPM).
Part 61 Flight Schools
Fidelity states that the proposed rule
does not allow a part 61 flight school to
sponsor an FSD or FTD. Fidelity
believes if an organization is capable of
maintaining the quality control program
specified by part 60, and if the local
POI, FSDO, or TPAA is satisfied, then
the FAA should allow part 61 schools
to sponsor an FSD. Fidelity cites
specific sections in part 61 that allow
for FSD usage.
FAA Response: FSTD sponsorship is
a very unique responsibility and one
that is irrevocably linked to an FAAapproved flight training program along
with other equally unique requirements.
As a result, the FAA has determined it
would be inappropriate to allow a part
61 operator, with no requirement for
FAA-approved training programs or
other required FAA oversight, to
sponsor an FSTD.
Sponsor Responsibility
UPS states that it may not be feasible
to place responsibility for the
qualification of an FSD owned,
operated, and maintained by another
business entity on the sponsor because
the sponsor would have no direct
control of that entity’s operation. UPS
believes this requirement would further
constrain the business of flight
simulator training and should be
deleted.
In regard to proposed § 60.7(a)(2),
DHL agrees with the apparent intent of
the rule to give the users who hold
vested interest in the simulators (the
carriers) the responsibility and
motivation to guarantee quality
assurance of the simulators. Further,
DHL states, ‘‘It is also apparent that the
FAA is shifting the responsibility from
the National Simulator Program Team
(AFS–205) to other entities (the
sponsors) and allowing AFS–205 to
provide oversight. It is unclear,
however, if this is a cost savings
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measure for the Federal Government,
which would place a financial burden
on the sponsors.’’
FAA Response: The FAA is not
shifting any responsibility with this
section of the rule, but is simply
clarifying that to be a sponsor, one
would have to have an FSTD qualified
and used as part of their own FAAapproved training program.
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Sponsors with Multiple Certificates
United comments that it holds
certificates under both parts 119 and
142, offering contract training for
aircraft currently flown by United and
aircraft no longer flown by United.
United requests that the FAA clarify the
wording to allow a sponsor who
operates FSDs under multiple
certificates to be the sole sponsor of
those FSDs with only one quality
program and one management
representative.
FAA Response: The FAA has added
information to appendix E. The QMS
requirements should not be read to
preclude a given QMS program from
being applicable to more than one
certificate holder (e.g., part 119 and part
142 or two part 119 certificate holders).
It should also not be read to preclude an
individual from being a Management
Representative (MR) for more than one
certificate holder (e.g., part 119 and part
142 or two part 119 certificate holders)
as long as the other QMS program
requirements and the other MR
requirements are met for each certificate
holder.
Use of Qualified FSDs
TechniFlite states that limiting the
use of a qualified FSD to an approved
course unduly limits the use of the FSD.
TechniFlite states, ‘‘A Designated Pilot
Examiner (DPE) should be allowed to
use a qualified FSD for all or part of a
check ride in accordance with the
practical test standards. * * *’’ If a pilot
applicant has the experience and has
otherwise received the appropriate
training outside of a 142 training
program, that pilot or his employer
should not be required to pay for the
expense of the 142 program. Many
corporate flight departments have
excellent in-house training programs. If
a qualified FSD is available, the
Designated Pilot Examiner should be
allowed to utilize the device.’’
TechniFlite believes part 61 training
should not be denied access to FSDs.
FAA Response: There may have been
a misunderstanding of the proposal. Part
60 does not impose any limitations or
prohibitions regarding the use of a
qualified FSTD for any appropriate,
authorized usage. A DPE certificated
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under part 61 may use an FSTD for any
authorized purpose, but a DPE may not
sponsor an FSTD.
Minimum of 600 Hours
Most of the commenters on this
section object to the proposed
requirement in § 60.7(c)(1) that an FSD
be used a minimum of 600 hours per
year in the sponsor’s training program.
Commenters state that the proposed
minimum hour requirement is arbitrary,
unfair, financially burdensome, and
creates an unfair financial advantage for
large training centers.
FAA Response: As discussed
previously, the FAA eliminated the 600hour requirement. Instead, the sponsor
must use at least one FSTD at least once
per year in an FAA approved training
program. Any additional FSTD
sponsored by the sponsor must be used
in another FAA-approved flight training
program or the sponsor must provide
the FAA with a written statement from
a qualified pilot having flown the
airplane being simulated at least once
during the previous 12 months. The
statement must indicate that the
configuration, performance, and
handling of the FSTD is appropriately
representative of those features of the
airplane being simulated. The revised
rule language resolves the concerns
raised by commenters.
Sponsorship Under Parts 125 or 137
FSI suggests including parts 125 and
137 in the definition of ‘‘Certificate
Holder’’ in § 60.3 and in § 60.7(c)(2) to
allow for future use of simulation under
those parts.
FAA Response: As stated previously,
only those persons required to have an
FAA approved flight training program
are eligible to sponsor an FSTD. The
FAA has established an Aviation
Rulemaking Committee to review part
125. The FAA will review the
recommendations of this Aviation
Rulemaking Committee when they are
received to determine if an FAA
approved training program will be
required under the new rules. The FAA
will initiate formal rulemaking at that
time if warranted by the
recommendations. Also, operations
conducted under part 137 (Agricultural
Aircraft Operations) require the use of
pilots with either commercial or airline
transport pilot certificates and a rating
for the aircraft that is to be used in the
agricultural operation. There is no
requirement, however, for a part 137
operator to have an FAA approved flight
training program. Therefore, it is not
appropriate for those operators to
sponsor an FSTD.
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63407
Dequalified Simulators
In regard to proposed § 60.7(c)(3)(ii),
CAE believes that someone else may
apply to sponsor the dequalified
simulator immediately, since only the
current sponsor cannot reapply.
American states that this paragraph has
the potential for significant impact on
sponsors of foreign simulators.
American further states that if a valid
training requirement for a device exists,
the FAA should not be in a position of
impacting business decisions. Similarly,
ATA opposes any attempt to require
that an FSD remain out of service for
any enforced period of time. ATA
suggests removing the sponsor’s
qualification, not the FSDs. United and
Delta make similar comments.
FAA Response: As discussed
previously, the FAA has rewritten the
sponsor qualification requirements,
specifically the use requirements.
Therefore it is highly unlikely that
sponsorship will be taken away for nonuse of an FSTD. The revisions to § 60.7
adequately address the concerns raised
in this area. The FAA has modified
§ 60.7(c) to remove the statement ‘‘The
FSD is not qualified.’’
Comments Regarding Additional
Responsibilities of the Sponsor (§ 60.9)
Several commenters object to the
proposal in § 60.9(a) that sponsors must
allow ‘‘immediate’’ inspection of the
FSD, citing the disruption and extra cost
if training is interrupted without notice.
The amount of notice requested by
commenters ranges from 24 hours to
seven days. ATA provides proposed
revised rule language, allowing 48 hours
notice. Several commenters state the
NPRM does not provide any rationale
for the change in approach from the
current language in §§ 142.29 and
142.73, which provides for inspection of
facilities, equipment, and records ‘‘at a
reasonable time.’’ ATA and United state
that if the FAA needs authority to
conduct ‘‘emergency’’ no-notice
inspections, it should add a paragraph
containing guidelines for when such
emergency inspection might be
required.
FAA Response: The FAA has revised
the rule language to require that
sponsors allow the NSPM upon request
to inspect the FSTD ‘‘as soon as
practicable.’’ In addition, the FAA has
clarified in the Information section of
the QPS that the phrase ‘‘as soon as
practicable’’ means without
unnecessarily disrupting or delaying
beyond a reasonable time the training,
evaluation, or experience being
conducted in the FSTD. These revisions
should address the commenters’
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concerns. The FAA did not intend for
proposed § 60.9 to imply that the FAA
would have the right to conduct
‘‘emergency’’ no-notice inspections.
Comments Regarding Foreign Devices
FedEx and ATA state that paragraph
§ 60.9(a) should be applicable to FSDs
that are directly under the sponsor’s
control, and not applicable to those
FSDs where the sponsor is not the
operator of the FSD.
FAA Response: The FAA appreciates
those situations where a sponsor is
sponsoring an FSTD owned and
operated by a foreign airline or foreign
training center located outside of the
United States. It is not the FAA’s intent
to conduct inspections on these FSTDs
outside of those times when such an
FSTD is being used by the sponsor or
another U.S. certificate holder.
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Collecting Comments on the FSD
Several commenters state that the
proposed requirements in § 60.9(b)(1)
and (2) to collect and take action on
comments on the FSD and its operation
would duplicate the maintenance and
discrepancy log requirements elsewhere
in part 60 and should be removed.
Commenters fear that this paragraph
would create the potential for irrelevant,
non-factual, personal or pejorative
comments, which would be difficult to
examine, classify, and take action on,
resulting in unnecessary expenditure of
time and resources. Commenters
particularly state that flight
crewmembers might offer comments
that reflect the trainee’s difficulty and
not the performance of the simulator.
Such comments should be provided to
the instructor or evaluator and not be a
requirement under this section.
FAA Response: The FAA adopted
revisions to the comment collection
provisions in this section. The intent of
this requirement is to provide a
mechanism for comments to be
provided and for the sponsor to be able
to review those comments and take
whatever action it deems appropriate.
The FAA did not specify the method
used to collect this information.
However, a maintenance log or an
addendum to a maintenance log would
suffice to meet this requirement. It was
the FAA’s intent not only to allow, but
to encourage comments. If a sponsor
determines that a particular comment is
motivated by the trainee’s difficulty and
not the performance of the FSTD, then
the sponsor should indicate that fact.
Providing a source for comments such
as these is logical and has merit.
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Liaison with Aircraft Manufacturer
DHL and FSI state that the proposed
requirement in § 60.9(b)(3) to maintain a
liaison with the aircraft manufacturer
would be difficult when the
manufacturer is out of business or when
the aircraft is no longer being
manufactured. FSI points out that the
manufacturers would also incur a cost
from this requirement and would
probably prefer to maintain a liaison
only with the FSD manufacturer, and
not with every sponsor for a particular
FSD. ATA states that the relationship
the air carriers and their training
departments maintain with the
manufacturers should be sufficient and
for independent training centers, there
should be more specific direction on
what constitutes liaison.
FAA Response: The FAA has revised
this section of the rule by eliminating
the language that was referenced in
these comments. However, the FAA has
included the following language in the
applicable QPS appendices, in the QPS
Requirements section addressing
§ 60.13: The FSTD ‘‘sponsor must
maintain a liaison with the
manufacturer of the aircraft being
simulated (or with the holder of the
aircraft type certificate for the aircraft
being simulated if the manufacturer is
no longer in business), and/or, if
appropriate, with the person having
supplied the aircraft data package for
the’’ FSTD ‘‘in order to facilitate the
notification described in this
paragraph.’’
Posting of Statement of Qualification
ATA, FedEx, and United request that
the FAA allow for electronic posting of
the document.
FAA Response: The FAA has
determined that electronic posting
would be helpful to the sponsor and the
user. Therefore, we have modified § 60.9
to allow for the electronic posting of the
Statement of Qualification. In addition,
as a result of other changes to this
section we have moved the
requirements in proposed § 60.9(b)(4) to
§ 60.9(b)(2).
Comments Regarding FSD use (§ 60.11)
Delta Air Lines (Delta) suggests that
§ 60.11(a) be reworded to make the
sponsor’s responsibility limited to not
knowingly allowing the FSD to be
misused. Delta states that a sponsor
cannot ensure that, for example, a rental
crew is not using an FSD for training for
a system for which the FSD is not
approved. Delta also suggests that the
preamble statement providing that other
persons or certificate holders may
arrange to use a sponsor’s FSD without
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an additional qualification process be
added to § 60.11(a).
FAA Response: The requirements of
this section of the rule do not require
that a sponsor keep a lessee from
improperly using the FSTD. Rather, this
section is to require that the sponsor
will not use the FSTD or allow the
FSTD to be used unless it: 1) Is properly
sponsored (paragraph (a)); 2) is qualified
as described in the Statement of
Qualification (paragraph (b)); 3) remains
qualified (paragraph (c)); 4) is used with
the original or properly modified
programming (paragraph (d)); and 5) is
used in accordance with missing,
malfunctioning, and inoperative
component requirements of § 60.25
(paragraph (e)). The standard briefing
provided to those who ‘‘dry lease’’ an
FSTD is sufficient to address the
concerns raised here.
Confusion About ‘‘Type, Make, Model,
and Series’’
FSI states that the language of
paragraph (b) is a significant departure
from current § 142.59(a)(1), because that
section does not require that an FSD
represent a specific ‘‘configuration’’ or
even ‘‘variant within type.’’ FSI states,
‘‘The intermingling of type, make,
model, and series, and ‘‘configuration’’
is confusing, contradictory, and not
consistent with the FAA’s own aircraft
nomenclature system. It would preclude
using a simulator representing a type of
aircraft, for training or testing for
another of a common type rating, and
then using the FAA’s own differences
training scheme to address differences.’’
FSI states that FAA has not justified the
change in the proposed section and has
not evaluated the cost of the impact.
FSB makes a similar comment, stating
that, ‘‘Many aircraft have multiple
configurations, which could potentially
create the need for multiple Statements
of Qualification.’’
FAA Response: The FAA has removed
the terms ‘‘make, model, and series of
aircraft or set of aircraft’’ from the rule
language in paragraph (b). In the final
rule, we only reference the Statement of
Qualification. However, the use of these
terms is not a departure from the current
requirement in § 142.59(a)(1) where the
requirement is that approval for use of
an FSTD be based on ‘‘each maneuver
and procedure for the make, model, and
series of aircraft, set of aircraft, or
aircraft type simulated, as applicable.’’
These requirements are completely
compatible and not interdependent.
There is nothing in any part 60
requirement, including the particular
section referenced, that would preclude
the use of an FSTD representing a type
of aircraft for training or testing for a
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common type rating, and then using an
FAA-approved differences training
program to address any differences that
may exist. The FAA reiterates that the
requirement is for the qualification of
the FSTD. While it is certainly true that
many aircraft types have many different
configurations, it is also true that each
FSTD will reflect a single aircraft type
(make, model, and series) and reflect
one configuration. There are provisions
for ‘‘convertible’’ FSTDs and each
configuration to which the FSTD is
convertible will be annotated on the
configuration list as part of the
Statement of Qualification. Indeed,
some convertible FSTDs are so different
they warrant a separate FAA
Identification number and a different
series of evaluations. The requirement
here is that each FSTD meet the
requirements stated in part 60,
including the applicable QPS appendix,
to be qualified. How that FSTD is
authorized for use has, and will
continue to, come under the jurisdiction
of the TPAA.
Required Features
Regarding paragraph (b)(2), Delta
states that an FSD should not be
required to have all features—just those
for which training credits are desired.
Delta suggests that paragraph (b)(2) be
changed to ‘‘For all tasks and
configurations approved in the
sponsor’s or user’s FAA approved Flight
Training Program.’’
FAA Response: The FAA has removed
paragraph (b)(2). There is no
requirement that any FSTD be
configured to match all possible
configurations of a single aircraft type
nor that it be able to be used for
training, testing or checking for all the
tasks that the simulated airplane type
may be able to accomplish.
Changes in Software
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ATA objects to proposed § 60.11(d),
stating that,
It will be impossible for the FSD to operate
with the ‘‘same software and active
programming’’ that was evaluated by the
NSPM. After the initial eval and each
recurrent eval, the operator continues to
make software changes to improve the utility
of the training device (adding malfunctions
and features), to fix faults, to improve
reliability and maintainability, and to keep
the simulator current with the aircraft. Other
sections in this Part 60 deal with how
changes are to be evaluated and monitored by
the NSPM. These are sufficient and do not
need to be duplicated in this clause * * *.
As worded, this paragraph implies that the
FSD software and active programming must
remain static between NSPM evaluations.
One could also infer that the NSPM must
evaluate every combination of engine and
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avionic software variation available in the
FSD prior to that software being used for
training * * *. This clause should be
deleted.
United, FedEx, Delta, FSI, Fidelity,
and CAE make similar comments. FSI
states that changes might be the result
of the requirements in § 60.19(c) or
§ 60.23 and that most modern
simulators require the modification of
software parameters to control the
simulator mechanics. CAE states that
the clause potentially removes the
capability of allowing different users to
emphasize specific aspects of the
training, for example the sponsor may
have introduced one effect that is
unacceptable to another user who
requires a different implementation of
cues. United, FSI, and CAE provide
suggested language to modify paragraph
(d).
FSI questions the meaning of the
terms ‘‘active programming’’ and
‘‘regular flight crewmember’’ in the
preamble discussion of § 60.11(d).
FAA Response: The reference to
‘‘regular flight crewmember training’’
was used in the original part 60
preamble language to refer to the
normally conducted, or routine training
of flight crewmembers. However, the
FAA has modified this section of the
rule language such that the FSTD would
have to be operated ‘‘with the software
and hardware that was evaluated as
satisfactory by the NSPM and, if
modified, modified only in accordance
with the provisions of this part’’
(§ 60.11(d)). This change addresses the
concerns raised by commenters.
Comments Regarding FSTD Objective
Data Requirements (§ 60.13)
ATA comments that the requirement
in proposed § 60.13(a) for aircraft
manufacturers’ flight test data and all
data developed after the type certificate
was issued is too broad, impractical,
and likely impossible to satisfy. ATA
comments that the sponsor has no
control over the data product and states,
‘‘The aircraft manufacturer does not
provide ‘all data’ as part of a data
package; rather, they only provide
certain cases and sets of data. The flight
test data package can consist of
numerous volumes (particularly for
older airplanes), only a portion of which
are included in the Qualification Test
Guide (QTG). The data the sponsor does
have is available for review during the
initial evaluation if a case is
questionable; however, the logistics of
submitting the entire flight test package
to the NSPM are prohibitive.’’ ATA
suggests the data referred to in this
section should be limited to those data
that are sufficient to validate the
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63409
performance, handling qualities, or
other characteristics of the aircraft,
including data related to any relevant
changes occurring after type
certification. Further, according to ATA,
other than paragraph (b), the sponsor
should have no role in this section. It
must be the responsibility of the aircraft
manufacturer or other data provider to
supply the appropriate validation data
for use by the sponsor in the QTG.
Finally, ATA concludes, as a minimum,
the NSPM should pre-approve the
airplane manufacturer’s or data
provider’s validation data roadmap (see
the ICAO document, Manual of Criteria
for the Qualification of Flight
Simulators, 2nd edition, Attachment D)
prior to allowing the data to be used for
validation of a FSD.
NLX, Delta, American, and CAE make
similar comments. ATA believes the
burden of responsibility for providing
these data should be upon the aircraft
manufacturer or data provider, for use
by the sponsor/operator in the QTG or
as additional reference data. (ATA
provides suggested new rule text for the
entire section.)
FAA Response: The FAA, revised the
language of this section to say the
following: ‘‘The data made available to
the NSPM (the validation data package)
must include the aircraft manufacturer’s
flight test data and all relevant data
developed after the type certificate was
issued (e.g., data developed in response
to an airworthiness directive) if such
data results from a change in
performance, handling qualities,
functions, or other characteristics of the
aircraft that must be considered for
flight crewmember training, evaluation,
or for meeting experience requirements
of this chapter.’’
The FAA understands the position
described by NLX, Delta, American, and
CAE regarding the burden of
responsibility for providing aircraft
data; however, at this juncture, the
scope of this rule does not permit the
FAA to levy simulation data
requirements on those not falling under
the regulatory jurisdiction of part 60
(such as aircraft manufacturers). As a
result, the organizations that do fall
directly under the provisions of part 60
are the sponsors—and it makes sense to
levy these requirements on them. The
FAA acknowledges that close
coordination must exist between the
sponsor and the data provider (aircraft
manufacturer, simulator manufacturer,
or other data supplier) to ensure that the
set of data ultimately made available for
FSTD evaluation will meet the part 60
requirements as indicated. However, the
FAA may task the ARC to consider
alternative approaches to this issue and
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make recommendations. The FAA may
consider these recommendations for
inclusion a future NPRM.
Validation Data
TWA states that the rule should
require that a manufacturer receive
NSPM approval for the aerodynamic,
engine and proof of match data on all
new aircraft types. This would provide
for commonality between the
performances of various simulators and
reduce the time required by National
Simulator Program engineers to review
the data because for each new type of
aircraft they would need to review only
one data package. TWA says that the
sponsors of new type aircraft would
then know they are working with
approved data and could proceed
accordingly.
United comments that this proposal
continues to place the sponsor between
the FAA and the FSD data provider,
thereby codifying the FAA’s ability to
withhold FSD qualification because of
poor data from the data provider.
CAE believes this paragraph is geared
to commercial operators and not to
business jet airplane manufacturers.
CAE recommends revising the text of
§ 60.13(a) to read: ‘‘Except as noted in
paragraphs (b) and (c) of this section, for
the purposes of validating FSD
performance during evaluation for
qualification, the sponsor must submit
to the NSPM the flight test data used to
define the performance standards of the
FSD.’’
FAA Response: The FAA adopted
revisions to the ‘‘exception’’ phrase to
clarify that the wording in this section
is geared to sponsors and not to
commercial operators, airplane
manufacturers or individual persons
receiving training in a FSTD. The FAA
recognizes that the new rule places the
sponsor between the FAA and the FSTD
data provider, thereby codifying the
FAA’s ability to withhold qualification
of the device if the data provided is
inadequate. The FAA notes, however,
that it has no authority to compel
information from a data provider, which
in most cases is proprietary information
used, produced, and marketed under
exclusive legal right of the airplane
manufacturer or other data provider.
The FAA expects that sponsors will be
able to obtain necessary data through
the dictates of the marketplace, similar
to the current practices for the
acquisition of other types of proprietary
information such as the technical
requirements for a Supplemental Type
Certificate. Sponsors and data suppliers
have a mutual interest in ensuring that
the FAA has the data it needs to qualify
a FSTD, and the agency encourages both
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parties to work together to achieve that
end.
Data Related to Modifications
FSB comments that once a FSD is
qualified under initial certification test
data, only the additional data related to
modifications need be submitted to
NSPM. FSB believes this data must fully
support the proposed modification and
must include appropriate
manufacturers’ flight test data that
relates to performance, handling
qualities, functions and aircraft
characteristics required for flight
crewmember training, evaluation, or
experience requirements.
FAA Response: The FAA has
modified § 60.13(a) to include language
indicating that ‘‘all relevant data
developed after the type certificate was
issued’’ will be required. An example of
such data is data developed in response
to an airworthiness directive.
Previously Approved Data
Thales Training and Simulation
comments that the requirement for prior
submission of data to the NSPM for
approval does not allow the use of data
previously approved by the NSPM by
way of the Validation Data Roadmap.
FAA Response: The term ‘‘Validation
Data Roadmap’’ is used in the
Information Section of the QPS to
describe the document that contains the
plan for acquiring the validation data
and the data sources. The Information
Sections are advisory and provide
general guidance to the user. The
Validation Data Roadmap will assist the
user in meeting the regulatory
requirements.
Use of Flight Test Data
FSI comments that instead of using
aircraft certification data, aircraft
manufacturers should work with
simulator manufacturers to produce
flight test data specifically for the
development of accurate simulation and
math models. FSI believes aircraft
certification data are generally
incomplete for modeling purposes, that
aircraft certification and simulator
development have different and specific
data requirements, and data developed
for one purpose should not be
considered acceptable for the other.
Regarding proposed § 60.13(e), ATA
comments that this paragraph, as
written, could be used to place the
sponsor in a position to require the
aircraft manufacturer to provide
additional flight test data. This has been
the case in the recent past and has
resulted in sponsors continuing to carry
data discrepancies that are years old.
ATA believes that, if the NSPM requires
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additional flight testing, that should be
strictly between the NSPM and the data
provider. In addition, this paragraph
could subject the sponsor to large costs
to obtain data as required by the NSPM.
This requirement seems inappropriate
and too broad, according to ATA.
American and CAE make similar
comments and request that the FAA
provide additional guidance on when
additional flight test data might be
required.
FAA Response: While the data
acquisition processes specifically
designed for simulation modeling and
subsequent validation would be highly
desirable, the FAA acknowledges that
the existing practices were developed to
minimize the cost of flight testing and
to take maximum advantage of the flight
testing already required as a function of
aircraft certification. Additionally,
while flight testing limited strictly to
simulation purposes has never been
discouraged, the FAA recognizes that a
shift in requirements as suggested here
might have an unwanted and perhaps
unnecessary impact on the cost versus
quality of the data as presently acquired
and accepted for simulation purposes.
The FAA is interested in having each
FSTD mimic as closely as possible the
performance and handling of the
simulated aircraft. As such, when new
generation aircraft are designed, built,
and placed into service, it is possible
that the existing set of data requirements
or the methods used to acquire those
data may be found to be inadequate in
some way. ATA is correct that certain
situations have resulted in some
sponsors carrying data discrepancies for
much longer than the FAA would
desire. The NSPM, the aircraft
manufacturer, and other interested
parties (e.g., foreign regulatory
authorities with the same or similar
concerns, and other sponsors) continue
to research the best and most acceptable
way of addressing the shortcomings. As
solutions to these data discrepancies are
developed, the FAA may make
appropriate changes to the QPS
appendices. These changes would be
subject to notice and comment.
Use of Flight Operations Quality
Assurance (FOQA) Data
In regard to proposed § 60.13(b), ATA
comments that some sponsors have on
rare occasion used de-identified flight
recorder data available from the aircraft
onboard FOQA data recorder. These
data, usually an averaging of many
flights within certain specified
parameters, have been used to verify the
handling qualities and performance of
the FSTD simulation where there is not
a good match between the simulation
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and the manufacturer-supplied objective
data in the MQTG. ATA states that this
paragraph, as written, makes no
allowances for such data, limiting data
types to engineering or flight test data.
FAA Response: The FAA recognizes
this limited but potentially important
source of simulation data. We have
made an appropriate adjustment in the
alternative data source allowances by
adding language that addresses on-board
FOQA recorder data into QPS Appendix
A, ‘‘Qualification Performance
Standards for Airplane Full Flight
Simulators.’’
Engineering Simulation Data
Boeing suggests adding ‘‘engineering
simulation data’’ to proposed § 60.13(c)
because it believes engineering data are
an important source of alternative data.
Also, Boeing states that engineering
simulation data are not necessarily
‘‘predicted’’ data if they are produced by
a well-validated engineering simulation,
and should not be grouped under the
heading ‘‘predicted data.’’
FAA Response: The FAA recognizes
that engineering simulation data is a
valid source of data. Therefore, the FAA
revised the rule language to allow for
the appropriate use of this type of data.
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Form and Manner of Providing Data
ATA states that the form and manner
that is acceptable to the NSPM under
proposed § 60.13(d) should be defined.
ATA states that the sponsor has no
direct control over the form and manner
of data provided and that the
requirement should be placed on the
aircraft manufacturer or the STC holder.
FAA Response: The ‘‘form and
manner’’ acceptable to the NSPM is
described in detail in the applicable
QPS appendix and resolves the issues
raised by the commenter. For example,
the QPS appendix states that the
information must be in a manner that is
clearly readable and annotated correctly
and completely with resolution
sufficient to determine compliance with
the applicable tolerances.
Notification Process
ATA states that if each sponsor
follows the requirement in proposed
§ 60.13(f), the NSPM will receive many
notifications from all the various
sponsors whenever a common change
occurs, such as flight data, avionics
data, 28-day navigational ‘‘Jepp’’ data
updates, visual system database
updates. American makes a similar
comment. ATA believes this paragraph
should clearly identify the scope of data
covered by this notification process.
Delta suggests limiting the requirement
to data ‘‘relevant to flight or ground
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dynamics, performance or handling
characteristics or additional aircraft
appliances.’’ Boeing believes it should
be the responsibility of the aircraft
manufacturer or data provider to
provide the notification, to avoid
redundant notifications from multiple
sponsors. However, FSI states that the
aircraft manufacturer is not required to
provide such data to the sponsors and
in many cases would not even know
who the sponsor or sponsors operating
FSDs representing its aircraft are.
Therefore FSI thinks this provision is
unenforceable.
Delta and FSI object to the
requirement for ‘‘immediate’’
notification. Delta suggests allowing at
least 30 days to provide the sponsor
time to determine if the change will
affect the FSTD in the context of
§ 60.13(a).
FAA Response: The commenters raise
two main issues with respect to
notifying the FAA of new data. The first
issue is that the commenters were
worried that we were requiring a
notification every time they receive any
kind of new data. The second issue is
that the commenters were concerned
that they would need to make a
determination about how the data
affected the FSTD before submitting the
notification. This second issue was a
concern for the commenters because of
the proposed requirement that the
notification to the FAA be ‘‘immediate.’’
They were concerned that they could
not provide ‘‘immediate’’ notice to the
FAA regarding how the data would
impact the use of the simulators in their
training programs.
In response to the first issue, the FAA
has revised paragraph (f) to clarify the
type of data we are requesting. The data
providers need only provide notice for
data related to the handling and
performance of the FSTD. The FAA has
also added language to the applicable
QPS appendices to help clarify the type
of data we are requesting. The language
states ‘‘[t]he data referred to in this subsection are those data that are used to
validate the performance, handling
qualities, or other characteristics of the
aircraft, including data related to any
relevant changes occurring after the type
certification is issued.’’
With respect to the second issue, the
FAA has also clarified that we are not
asking data providers to make a
determination about the effect of the
new data before sending the notice to
the FAA. The final rule only requires
that the sponsors give the FAA notice
that new data exists that ‘‘may relate to
FSTD performance or handling
characteristics.’’ The applicable QPS
appendices provide more information
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63411
about the type of dialogue the sponsors
should have with the NSPM regarding
the determinations to be made about the
effect of the new data on FSTDs. In
addition the FAA has removed the word
‘‘immediately’’ from paragraph (f) and
provided the timeframe in the
applicable QPS appendices. Instead of
‘‘immediately’’ the FAA is requiring that
the sponsor notify the FAA within 10
working days of receiving notice of the
new data.
Comments Regarding Special
Equipment and Personnel Requirements
for Qualification of the FSTD (§ 60.14)
Flight Safety Boeing (FSB) states that
this section places a burden on the
sponsor that really should be a burden
on the entity that owns and maintains
the FSD.
FAA Response: A sponsor may
contract with another person for
services such as maintenance and
scheduling. However, the sponsor still
retains the responsibility of ensuring
that all of the actions are completed as
required. This responsibility extends to
initial and recurrent evaluation of the
FSTD, including any special equipment
and/or personnel.
24 Hour Notice Requirement
Commenters are concerned about the
amount of notice before a sponsor must
make special equipment and personnel
available under § 60.14, stating that the
24 hours notice mentioned in the NPRM
preamble and in the QPS is impractical.
ATA and Fidelity recommend at least 7
days notice, while FSI recommends at
least 10 calendar days notice to prepare
special test equipment, such as sound,
motion, or control measurement
equipment and make operating
personnel available. NBAA, CAE, and
an individual make similar comments.
FAA Response: The FAA recognizes it
takes time for a sponsor to arrange for
special equipment and personnel to be
made available to the FAA. Therefore,
the FAA has modified the language in
the applicable QPS appendices to state
that ‘‘the NSPM will make every attempt
to notify the sponsor at least one (1)
week, but in no case less than 72 hours,
in advance of the evaluation.’’
Specifically Trained Persons
FSI questions whether the
requirement for specifically trained
persons is not required for recurring
evaluations and recommends that the
FAA state if there is a requirement for
a person current and qualified in the
type of aircraft simulated to be present
and a part of the subjective testing and
declarations for recurrent evaluations.
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FAA Response: The FAA has removed
the word ‘‘specifically’’ in reference to
qualified personnel. Qualified personnel
are those persons qualified to install or
use any special equipment when its use
is required. The major focus of this
section is on equipment not necessarily
used on a regular basis for recurring
evaluations of the FSTD. Language in
the Information section in the
applicable QPS appendices for this
section includes examples of special
equipment (e.g., spot photometers, flight
control measurement devices, sound
analyzer).
Special Evaluation
NBAA asks what would constitute a
special evaluation.
FAA Response: A special evaluation
is an evaluation other than a regularly
scheduled initial or continuing
(recurrent) evaluation or an evaluation
that is considered to be a regular nonotice (or limited notice) evaluation.
Special evaluations are conducted
where it is determined that a question
exists regarding an FSTD’s qualification
and the answer is not immediately
available through any means other than
an on-site evaluation. The depth and
duration of a special evaluation will
depend on the question that exists and
the detail that must be acquired to
adequately address that question. This
term is described in the § 60.14
discussion in appendices A, B, C, and
D, and is defined in appendix F.
sroberts on PROD1PC70 with RULES
Comments Regarding Initial
Qualification Requirements (§ 60.15)
RAA, FSB, and United disagree with
the proposal in § 60.15(a) that a request
for initial FSD evaluation be submitted
first to the TPAA. These commenters
believe TPAA inspectors do not have
the expertise to review a QTG and that
the application should be made directly
to the NSPM, with a copy sent to the
TPAA. United suggests that the TPAA
be asked to send a concurring letter to
the NSPM.
FAA Response: The FAA revised this
section to require the sponsor to send
the request directly to the NSPM and
simultaneously request the TPAA to
forward a concurring letter to the
NSPM. This clarifies the process for
initial qualification of the FSTD.
Request for Initial Qualification
ATA comments that the requirements
of proposed § 60.15(b) are unnecessarily
burdensome. For example, ATA states
that paragraph (b)(2) requires a
description of a procedure that should
have already been accepted under the
QAP. Delta and CAE make similar
comments. ATA suggests limiting the
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requirement to the ‘‘statement’’ outlined
in paragraph (b)(1).
NLX states that paragraph (b) does not
appear to allow for a sponsor to request
an initial evaluation until the FSD or
FTD is completely tested, all items
functional and all tests passing. NLX
states that with the lengthy time
required to get an initial evaluation
scheduled, it is not practical to get an
FSD or FTD completely finished and
then wait for the evaluation. Within
reason, the FAA must allow for some
items to not be completed when the
request for an initial evaluation is
submitted with the understanding that
they will be before the evaluation starts,
according to NLX. Similarly, CAE
requests clarification of the timeline for
the activities in paragraph (b) and
references the ‘‘Sample Request for
Initial Evaluation Date’’ letter in the
appendix.
In regard to proposed § 60.15(b)(2),
FSI states that the maintenance required
by proposed § 60.19(c) may also require
changes to the configuration of the
software or hardware present during the
evaluation, in addition to modifications
performed under proposed § 60.23.
FAA Response: The FAA has revised
paragraph (b)(2) to delete the
requirement concerning procedures.
Instead, the FAA is requiring a
statement from the Management
Representative (MR) that is focused on
the operation of the FSTD (performance
and handling qualities) assessed by a
pilot meeting the requirements of part
60. The QMS must contain the
procedure that the MR will use to
generate this statement.
In response to the points raised
regarding timing of the testing and of
the statement being sent, the FAA has
slightly modified the proposed language
and has added language in the
applicable QPS appendices. This
additional language provides that the
statement may contain a confirmation
that the sponsor will forward to the
NSPM (either by traditional or
electronic means) the complete
statement described in § 60.15(b) in
such time as to be received no later than
5 business days prior to the scheduled
evaluation. The language also describes
what must be communicated when or if
required maintenance results in
modification to hardware or software
that was present and functioning at the
time of the initial evaluation.
Pilot Statement
FSI states that pilots, particularly
those of dry lease customers, may be
reluctant to sign the statement required
by proposed § 60.15(b)(3) because of
perceived potential liability. FSI
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suggests that this provision be made
advisory and moved to the QPS or that
an appropriately qualified FAA official
should sign such statements. Similarly,
ATA comments that the terms used in
paragraphs (b)(3)(i)–(iii) (‘‘function
equivalently,’’ ‘‘are equivalent to,’’ and
‘‘conforms to’’) require pilots to make
assertions in writing that they cannot
realistically support. ATA states, ‘‘This
is particularly true in the case where
pilots are required to make these
assertions for aircraft types not yet
issued a type certificate, a situation
addressed in paragraph (d). Also, there
are many operations tasks that pilots
have never experienced in the aircraft,
like a takeoff with an engine
malfunction or a windshear encounter
during approach.’’ ATA suggests using
the phrase ‘‘adequately represents’’
instead of a form of ‘‘equivalent’’ or
‘‘conforms.’’ ATA provides suggested
rule text and sample Letter of Request
text, using the suggested terms. Delta
makes a similar comment.
FSB states that, regarding proposed
§ 60.15(b)(3), it needs to have the
flexibility to have both a primary
designated evaluation pilot and an
alternate, either of whom are certified
by the FAA to conduct the evaluation.
FSB recommends changing § 60.15(b)(3)
to permit any designated pilot to
perform the subjective tests and sign the
statement that the listed requirements
have been met.
FAA Response: In the final rule, the
FAA requires that an appropriately
qualified pilot must make the
comparisons as described. The FAA also
adopted revisions to this section to
require the appropriately qualified pilot
to comment on the performance and
handling qualities of the FSTD with
respect to the aircraft (or set of aircraft)
simulated but only within the normal
operating envelope of the aircraft. The
pilot making this determination must
have flown all of the operational tasks
listed in the Table of Functions and
Subjective Tests set out in the FSTD
subjective tests attachment to the
applicable QPS appendix relevant to the
qualification level of the FSTD.
Additionally, the FAA has modified the
requirement to note if any exceptions
are necessary.
The FAA is not prescribing the
individuals who must perform the
required subjective testing, other than to
require that the pilot be appropriately
qualified and that he/she has actually
flown the subject aircraft within the
previous 12 month period. It would be
a safety concern to have a pilot attest to
the correct performance and handling of
the subject FSTD if that pilot is not
familiar with the performance and
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handling qualities of the aircraft being
simulated.
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Tasks Not Tested
ATA comments that the requirements
outlined in § 60.15(b)(4) would prevent
an operator from requesting an initial
evaluation until all of the referenced
tasks, systems, and tests are complete
and functional. This would result in
project schedules being extended by
several months, adding a significant
financial burden to every certification
project. ATA requests the operator be
permitted to list under this paragraph
any item that, for whatever reason,
cannot be tested at the time of the
submittal.
Also, ATA and United cite numerous
specific problems with this paragraph
and state that the concept of requiring
such a list is fraught with problems,
such as mixing tasks with systems and
maneuvers. ATA recommends that the
requirement for the table of Qualified/
Non-qualified tasks be deleted.
FAA Response: The FAA has revised
and reorganized § 60.15 to accommodate
the large portion of the
recommendations originally made by
commenters. As rewritten, the sponsor
makes the request for initial evaluation
after an appropriately qualified pilot has
flown all of the Operations Tasks listed
in the applicable QPS appendix relevant
to the qualification level of the FSTD. If
the sponsor does not subjectively test a
task, it must note that in its request for
initial evaluation. The FAA also revised
this section to separate operational
piloting tasks from systems and cockpit
configuration determinations and to
allow for pilots and for persons other
than pilots to make these
determinations.
Qualification Test Guide
TechniFlite comments that the NSPM
should provide specific guidance on the
outline and format of the QTG required
by proposed § 60.15(b)(5), stating that
the acceptance of the QTG often appears
to be subjective and the sponsor is not
provided a clear understanding of what
is required for compliance. TechniFlite
further suggests that the NSPM should
be required to respond to the
submission of a QTG within 30 days
and be required to complete the
qualification process within 90 days.
In regard to proposed § 60.15(b)(5)(iv),
ATA comments that this list will define
the equipment that must be kept
calibrated in accordance with appendix
A. According to ATA, most new FSDs
have internal test equipment built into
them; this internal test equipment
would have to be removed to be
calibrated in the traditional sense. ATA
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recommends allowing the sponsor to
develop repeatability tests with
tolerances as part of a quality system.
Also ATA recommends changing
‘‘description’’ of the equipment to ‘‘list’’
of the equipment.
FAA Response: The FAA removed the
QTG language that was in proposed
§ 60.15(b)(5) and placed specific
guidance regarding the format and
content of the QTG in the applicable
QPS appendix. Regarding the NSPM
response time for scheduling a QTG
evaluation, the FAA notes that typically,
the NSPM responds to a scheduling
request within days and very rarely
exceeds a week. Thus, under current
practice, the NSPM response time is
well under the 30 days recommended
by the commenter. The FAA intends to
continue this timely response. The
commenter also suggested that the
NSPM be required to complete the QTG
evaluation within 90 days. The current
practice consists of the sponsor being
able to request an evaluation up to 180
days in advance and provide an
‘‘essentially complete’’ QTG not later
than 45 days prior to that proposed
evaluation date. The submission of the
QTG at this point allows the QTG to be
assembled with data and tests that more
likely reflect the device’s final form and
provides adequate time for the NSPM to
review the document for compliance
with the appropriate standards and
advise the sponsor if questions arise
regarding either the quality or quantity
of data or the justifications used for
comparisons. This timing allows the
sponsor to make necessary corrections,
re-run tests, provide additional data,
and then provide a response with
sufficient time for the NSPM to evaluate
this additional information for clarity
and completeness. This 180-day process
provides the best timing and allocation
of resources for the sponsor and the
FAA personnel. Various processes have
been tested over the past 20 years, and
the 180 day timeframe has yielded the
best results.
New or Changed Standards
In response to proposed § 60.15(c)(1),
CAE and ATA question what the effect
of new standards would be on FSTDs
that have been ordered, but not yet
delivered to the sponsor. They suggest
that the NSPM be required to notify all
sponsors when a change to an existing
standard or a new standard is
published. The sponsor should then be
given more time, e.g., 60 or 90 days, to
determine whether the FSTD should
comply with the new standards or the
standards that were in effect when the
FSTD was ordered.
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63413
FAA Response: If the FAA changes
the standards for initial qualification, a
sponsor may request that the NSPM
apply the standards that were in effect
when the FSTD was ordered for delivery
or apply the changed standards. The
FAA recognizes that the sponsor needs
time to evaluate the changes to
determine the standards under which
the device should be evaluated.
Therefore, the FAA has revised the rule
language to give the sponsor 90 days to
notify the NSPM which standards to
apply.
In the NPRM, proposed
§ 60.15(c)(1)(iii) included the phrase
‘‘unless circumstances beyond the
control of the sponsor prevent the
evaluation from occurring within that
time.’’ In the final rule, the FAA has
removed this phrase. The intent of the
language was to prevent the sponsor
from being penalized for extraordinary
circumstances that were beyond its
control such as a labor dispute, natural
disasters, or NSPM scheduling conflicts.
The FAA has determined that it is more
appropriate to resolve these
extraordinary cases through the
exemption process rather than to
include a blanket authorization in the
regulation.
Evaluation Pilots
Several commenters have questions
and concerns about the evaluation pilot
requirements in proposed § 60.15(d).
ALPA is concerned about the
provision in proposed § 60.15(d) that
allows the testing pilot to be an
employee of the sponsor, but does not
require that the pilot be a line pilot.
CAE does not understand the process
and criteria for obtaining approval from
the TPAA. Further, CAE believes the
other requirements adequately cover the
qualification requirements for the
evaluation pilot. CAE recommends
removing this requirement.
ATA and United believe the
requirement is too restrictive because it
would be expensive to maintain line
pilots with current qualifications on
staff. United says that its experience has
shown that a non-qualified pilot with a
background in flight test is significantly
more effective than a qualified pilot
with no such background. Delta states
the proposal would make it difficult to
use retired or contract personnel for
simulator requirements testing.
American makes a similar comment.
Also ATA and United object to what
amounts to the TPAA’s veto power over
selection of a simulator test pilot.
United believes that the only
legitimate requirement for a pilot who is
current in the airplane is to evaluate the
subjective performance and handling
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qualities tests. United states that
requiring that this pilot sign an
overarching statement attesting to the
accuracy of other than the subjective
tests would be problematic, given the
threat to his license contained in
§ 60.33(b)(2), and prohibitively
expensive. United comments that
elsewhere in this part, the NSPM
requires the sponsor designate an MR to
be the primary point of contact with the
NSPM. United suggests that the MR
should be required to sign this
statement.
FAA Response: The FAA removed the
requirement that the pilot be approved
by the TPAA. Thus, the concern raised
by ATA and United is now moot. The
FAA did not adopt ALPA’s suggestion
to have a line-qualified pilot provide the
information required by this section.
The FAA understands the concern
raised by ALPA and others, but the
reason for the pilot assistance is to
ensure that the FSTD does, in fact,
perform and handle as the simulated
aircraft performs and handles. If the
sponsor is able to supply an
appropriately qualified pilot (whether or
not that pilot flies ‘‘the line’’) who is
able to make those determinations, the
NSPM is satisfied that the FSTD will be
adequately evaluated.
The FAA has revised the rule
language to require that the
confirmation statement reflect the
performance and handling qualities of
the FSTD within the aircraft’s (or set of
aircraft) normal operating envelope.
This determination will be made after
the pilot has flown all of the operations
tasks listed in the Table of Functions
and Subjective Tests set out in the FSTD
subjective tests attachment to the
applicable QPS appendix relevant to the
qualification level of the FSTD.
sroberts on PROD1PC70 with RULES
Statement of Qualification
FSI objects to the requirement in
proposed § 60.15(g) that specific details
for FSDs (make, model, series of aircraft,
configuration, e.g., engine model or
models, flight instruments, navigation
or other systems) be identified on the
Statement of Qualification. FSI states,
‘‘these specific details for FSDs are
unprecedented, not justified, and not
even addressed in this proposal. The
clear implication, if not actual
statement, would make each
qualification so specific that no other
variation in type, or differences in
cockpit configuration could be
accommodated.’’ FSI recommends that
FAA continue to allow variants within
type and cockpit configuration and
specifically to allow the use of a
differences training program.
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JAA asks why the Statement of
Qualification in proposed § 60.15(g)
contains the topics for which an FSTD
is not qualified, instead of all topics for
which the FSTD is qualified. Delta
suggests deleting the requirement for
‘‘all equipment and appliances’’ in
proposed § 60.35 and instead use the
Statement of Qualification to list the
equipment and appliances that are not
installed and therefore cannot be used
for training. Delta also requests
clarification as to whether the updated
QTG needs to be completed prior to the
issuance of the Statement of
Qualification.
FAA Response: The FAA has made
changes to the language describing the
content of the Statement of
Qualification (SOQ). The FAA has
concluded that listing the tasks for
which the FSTD is qualified would
likely be an extensive list and
redundant from FSTD to FSTD. A
shorter and more easily read and
understood listing as part of each FSTD
SOQ would include the tasks for which
that specific FSTD is not qualified. Also,
there is nothing in any part 60
requirement, including § 60.15(g) that
precludes the use of an FSTD
representing a type of aircraft for
training or testing for a common type
rating, and then using an FAA-approved
differences training program to address
any differences that may exist.
The FAA reiterates that the
requirement is for the qualification of
the FSTD. While it is certainly true that
many aircraft types have many different
configurations, it is also true that each
FSTD will reflect a single aircraft type
(make, model, and series) and reflect
one configuration. As previously
explained, there are provisions for
‘‘convertible’’ FSTDs and each
configuration to which the FSTD is
convertible, will be annotated on the
configuration list as part of the SOQ.
The TPAA will determine the
authorized use of the FSTD.
With respect to Delta’s question
whether the QTG needs to be updated
prior to the issuance of the SOQ, the
answer is no. The FAA recognizes that
there will be times when the SOQ will
be issued prior to the actual update of
the QTG to the Master QTG. However,
the FAA will not issue an SOQ until the
NSPM completes all required testing
and has found the test results to be
acceptable.
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Comments Regarding Additional
Qualifications for a Currently Qualified
FSD (§ 60.16)
Table of Qualified/Non-qualified Tasks
United comments that this entire
section seems to exist to only support
the requirement for the sponsor to
maintain the table of Qualified/NonQualified Tasks as required by proposed
§ 60.15(b)(4). United believes that, if the
FAA were to return to the ICAO- and
JAA-accepted practice of linking
functions and subjective tests to the FSD
qualification level, then this section
should be used only by those sponsors
wishing to remove a previously issued
exemption from the requirements of the
Table of Functions and Subjective Tests
and should be clearly titled as such.
FAA Response: The FAA has moved
the contents of the original § 60.15(b)(4)
to a new § 60.15(g) and made minor
clarifications. The FAA is familiar with
the ICAO and JAA practice of linking
the functions and subjective tests to the
FSTD qualification level, but also notes
that not all tasks may be classified as a
function of the level of FSTD involved.
For example, one Level D FSTD may be
qualified for circling approaches, while
another Level D FSTD may not be
qualified for circling approaches.
Therefore, simply stating that a
particular FSTD is qualified at Level D,
without listing specific tasks, does not
indicate which tasks can be
accomplished in that particular device.
Statement of Qualification
ATA comments that paragraph (a)
implies that any additional training,
evaluation, or flight experience
requirements not listed on the FSTD
SOQ will require that an extensive
amount of paperwork be submitted to
the NSPM in order to generate a new
SOQ even if this new training,
evaluation, or flight experience
requirement is valid within the initial
qualification level of the FSTD and
approved by the POI. ATA believes this
could present a significant delay in
implementing a new or updated training
program.
FAA Response: The SOQ is not
intended to be and will not be a
repository for training, evaluation, or
flight experience requirements. The
SOQ is merely a convenient place to
provide FSTD users with information
about whether or not the device is
qualified to be used to accomplish
certain tasks (e.g., windshear training,
circling approaches). Should the
sponsor wish to add ‘‘circling
approaches,’’ for example, to the list of
qualified tasks for a given FSTD, the
amount of paperwork involved would
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be a single letter and may be
accomplished after a verbal request. The
FAA would accomplish the evaluation
as soon as practical after receiving the
request. This would include a special
visit to the FSTD if is necessary, as is
done under current practice.
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Grandfathering Provisions
Delta suggests that the FAA add
language to this section clearly stating
that additional qualifications will
continue to be qualified under
grandfather provisions, and will not
require meeting the new part 60
requirements, as long as the original
qualification was completed prior to
issuance of part 60.
FAA Response: Under the final rule,
FSTDs qualified prior to the effective
date of part 60 will continue to be
qualified in accordance with the
original MQTG that was issued at the
time of qualification. The FAA did not
revise § 60.16 to add language stating
that new tasks would be qualified under
the grandfather provisions. If the
sponsor wants the FSTD qualified for a
new task, the NSPM will conduct the
initial qualification of the new task in
accordance with the part 60 standards
for that task. The part 60 standards for
the new task will be incorporated into
the existing MQTG. For example, a
sponsor has a currently qualified FSTD
and desires to have the FSTD qualified
for windshear training. The sponsor will
notify the NSPM of the modifications,
additions, or software or hardware
changes that will need to be added to
the FSTD in order to have it qualified
for windshear training. The NSPM will
then assess the FSTD to determine if it
meets the part 60 standards for
windshear training. Once that
determination is made, the MQTG will
be updated to include the windshear
training task. Nothing else in the MQTG
will change from the original
qualification basis. The FAA does point
out that NSPM qualification of
additional tasks does not constitute
authorization for the sponsor, or any
other user of the FSTD, to use the device
for credit in any manner other than that
approved by the appropriate TPAA.
Responsibility of NSPM vs. TPAA
TechniFlite states that the issue of
whether the FSTD faithfully replicates
the actual aircraft should be the
responsibility of the NSPM, while how
the FSTD is used should be the
responsibility of the training
organization and the TPAA (POI or
TCPM) as appropriate.
FAA Response: The NSPM is not
involved in the approval of a training
program for a sponsor or any other user
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of an FSTD. Instead, the NSPM qualifies
the device while the TPAA approves the
use of the device in a particular training
program. The qualification of a given
FSTD may or may not include
qualification for a specific task. For
example, if the NSPM does not evaluate
and qualify the FSTD for windshear
training, a TPAA may not approve that
FSTD for use in meeting windshear
training tasks required by regulation.
Comments Regarding Previously
Qualified FSDs (§ 60.17)
Delta requests clarification of ‘‘other
applicable provisions’’ in paragraph (a),
and several commenters state that
paragraph (a) and (b) of proposed
§ 60.17 appear to be at odds with each
other. For example, ATA states that in
§ 60.17(a), the FAA appears to be
allowing for grandfathering along the
terms that have been used by the
industry and the FAA for the past 20 or
30 years. However, in § 60.17(b),
requiring the SOQ implies that the
grandfathering is only good for the 6
year period, i.e., that the FAA would
require the FSTD to meet the new QPS
standards. ATA strongly opposes
removing grandfather rights for
previously qualified FSTDs, stating that
6 years is an insufficient time and will
be cost prohibitive. Similarly, RAA
states that for operators who use older
aircraft, it is important that they not lose
their ability to access simulators that
may not meet current standards. TWA,
American, and FSB make similar
comments.
FSI states that if the FAA’s intent was
not to remove the grandfathering, but
instead to unilaterally issue a new SOQ
to every currently qualified FSTD, the
language of the final rule should make
that intention clear. ATA and Delta ask
why the FAA would allow 6 years, if the
intention was merely to issue new
paperwork. Delta further requests
clarification of ‘‘Configuration List’’ in
paragraph (b). CAE makes a similar
comment.
FAA Response: In response to Delta’s
question regarding ‘‘other applicable
provisions,’’ the FAA notes that certain
requirements in part 60 apply to all
FSTDs. For example, all FSTDs must
have an official sponsor that meets the
requirements of this part, and all
sponsors must develop and implement
a QMS. The FAA added language to the
applicable QPS requirements to clarify
this issue.
The FAA does not intend to eliminate
the practice of grandfathering. All
FSTDs qualified prior to the effective
date of part 60 will retain their
qualification as long as they continue to
meet the standards under which they
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63415
were originally qualified. Although the
FAA is not eliminating grandfathering,
the FAA is requiring all sponsors to
obtain an SOQ for each FSTD. The
purpose of the SOQ is to provide a
complete picture of the simulator
inventory regulated by the FAA,
including the configuration list and the
limitations to authorizations. The
issuance of the SOQ will not require any
additional evaluation or require any
adjustment to the qualification basis for
the simulator. The FAA added
information in the applicable QPS
appendices to clarify this requirement.
Under the final rule, sponsors have 6
years to obtain an SOQ. This allows the
sponsors sufficient time to meet the
§ 60.17(b) requirements and reduces the
sponsor’s costs of implementing part 60.
Simulators Not Requalified Within 2
Years
Several commenters object to the
requirement in proposed § 60.17(c) that
a simulator that has lost its qualification
and is not requalified within 2 years,
would have to meet the standards in
effect at the time of application for
requalification. DHL states that if one of
its simulators became disqualified and
then had to requalify under the new
standards, the simulator would have to
be shut down, even if it has provided
effective training for decades. DHL
states that the disqualification of older
simulators would severely cripple their
fleet. TechniFlite CAE, American, ATA,
and FSI make similar comments.
FAA Response: The requirements
contained in this section do not
significantly differ from the FAA’s
policy on out of service simulators. For
over 22 years, the FAA’s policy has been
that if an FSTD is taken out of service
for an ‘‘extended period of time,’’ it
must under go an evaluation prior to
being returned to service. Current
practice is that if this ‘‘out of service
time’’ is in excess of 12 months, the
NSPM will review the qualification
basis and may require the evaluation to
be in accordance with the standards in
existence at the time of requalification.
The part 60 rule doubles the ‘‘out of
service time’’ that would likely result in
evaluation in accordance with the
current standards at the time of
requalification. The FAA recognizes that
there may be situations where a sponsor
of a device that has been unqualified for
2 or more years would desire
requalification under the standards that
were previously in effect. However,
these are rare and extraordinary
situations that are best resolved by the
exemption process.
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Downgraded FSTDs
ATA and TWA comment that
proposed § 60.17(e) does not address the
process for a downgraded FSTD to
regain its previous qualification level.
ATA and TWA believe the FSTD should
be evaluated using the same
qualification standards under which it
was originally qualified.
FAA Response: The FAA wishes to
clarify the distinction between a
downgraded FSTD and an FSTD that is
unable to function at its qualification
level due to missing, malfunctioning or
inoperative parts. A downgraded FSTD
is a device that has had a permanent
change of qualification level. On the
other hand, an FSTD may not be able to
function at its qualification level
because of missing, malfunctioning or
inoperative parts. For example, if the
daylight visual system is inoperative on
a level D FSTD, the FSTD may only be
able to function as a level C device. In
this situation, the NSPM would
temporarily restrict the tasks that can be
accomplished in the device, and impose
other requirements in accordance with
§ 60.25. However, this temporary
restriction is not a ‘‘downgrade’’ of the
device. Instead, it is a limitation that
can and is removed when the device is
repaired and able to function as
originally qualified.
Finally, the FAA wishes to clarify
what it means to upgrade an FSTD. An
upgraded FSTD is a device that was
originally qualified at one level and is
being upgraded to a higher level, i.e.,
Level C to Level D. An upgraded FSTD
is required to undergo an evaluation in
accordance with the standards in
existence at the time of the upgrade.
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Comments Regarding Inspection,
Recurrent Evaluation, and Maintenance
Requirements (§ 60.19)
Streamlining the Process
TechniFlite comments that the § 60.19
process is a burden and an undue
expense. TechniFlite suggests that a
panel outside of the NSPM should be
formed to overhaul the entire process,
for example, a streamlined process
could include automated tests that the
NSPM could access as required online.
FAA Response: The FAA did not
adopt changes to this section as
recommended by the commenter. The
FAA has been conducting at least
annual inspections of each FSTD and a
review of the quarterly tests
accomplished by the sponsor. This
practice has been successful for over 20
years and should not present a
significant new burden or increase in
expense for the sponsor. The NSPM is
considering the feasibility of ‘‘on-line’’-
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testing and review of FSTDs. If the FAA
determines ‘‘on-line’’ testing has
immediate or long term applicability, it
would be incorporated into the
regulations in accordance with notice
and comment rulemaking procedures.
Level of Reliability
An individual suggests that to ensure
good, uninterrupted training the FAA
should require a minimum average level
of reliability as evidenced by Mean
Time Between Failures, Mean Time
Between Unscheduled Maintenance, or
some other objective, definable criteria.
FAA Response: The FAA has
determined that each individual
sponsor should have some flexibility to
ensure satisfactory FSTD reliability on
its own. This flexibility, together with a
viable QMS, will provide each sponsor
with a clearer picture of what is actually
happening and allow the sponsor (and
the FAA) to determine whether or not
the sponsor has an acceptable level of
reliability.
Performance Demonstrations
ATA, CAE, and FSI state that it is
unclear which ‘‘performance
demonstrations’’ in Attachment 1 are
being referred to in § 60.19(a)(1).
Commenters also state that breaking up
the tests into four evenly spaced
inspections would increase costs and
lose training time for the sponsors. ATA
cites the example of sound tests that are
normally all done in one quarter since
it requires a complex test setup using
special equipment. TWA suggests
allowing sponsors to group tests that
require complex test setups or special
equipment. Similarly, American states
that the order in which the tests are
performed should not require NSPM
approval. ATA states that the NSPM
should not have approval rights, only
review rights and that the exact timing
of the inspections should be left up to
the sponsor. Similarly, Delta states that
since the FAA has already approved the
QAP process, there is no need for a
separate approval of the quarterly
checks.
FAA Response: The FAA has removed
the reference to ‘‘Attachment 1
performance demonstrations’’ and
‘‘Attachment 2’’ from paragraph (a)(1).
The intent of paragraph (a)(1) is to
address only objective tests.
Performance demonstrations have been
renamed as objective tests or subjective
tests and placed in the applicable QPS
attachments. During quarterly
inspections the sponsor is only required
to perform objective tests. The FAA has
also removed the requirement that the
NSPM approve the objective test
sequence and content of each quarterly
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inspection for each sponsor. Instead, the
requirement is that the sponsor
develops the objective test sequence and
content of each quarterly inspection,
which must be acceptable to the NSPM.
We changed the term from ‘‘approved’’
to ‘‘acceptable’’ to clarify that the
sponsor can perform the quarterly
inspections without prior FAA review
and approval. If after review of the
objective test sequence and content of
the inspections the FAA finds
something not acceptable, the FAA will
notify the sponsor of the deficiency and
require the sponsor to make appropriate
changes.
Inspections for Mobile Simulators
Professional Instrument Courses
describes its maintenance and repair
process for its ATC 610J simulators,
which are moved around the country
routinely, for reasons such as the
location of instructors or maintenance
needs. PIC states that inspecting and
testing each simulator quarterly would
be impossible due to the mobile nature
of its instrument training service.
FAA Response: All FSTDs are
required to undergo the quarterly
inspections. However, the FAA removed
the requirement that the quarterly
inspection plan for each sponsor be
approved by the NSPM. Instead, the
sponsor must develop a quarterly
inspection plan that is acceptable to the
NSPM.
Preflight Test
FSI states that the requirement in
proposed § 60.19(a)(2) for a functional
preflight test before the first FSTD use
each calendar day would be a burden
for training operators using simulators
that operate close to 24 hours a day,
because the simulator would need to be
shut down until a technician could
complete the work. If the sponsor could
conduct one check in each calendar day
the sponsor could spread the simulator
technicians’ work across the entire day,
thereby saving labor costs. FSB and
Embry-Riddle make similar comments.
Embry-Riddle asks whether the preflight
could be conducted by the instructor
pilot and whether there are special
training requirements for the person
conducting the preflight. United
requests that it be allowed to use an
‘‘operational’’ day instead of a
‘‘calendar’’ day, since it schedules
training between 0600 and 0200 the
following morning.
ATA, United, Delta, NBAA, and
American state that the preflight check
is sufficient if the FSTD hasn’t been
checked in the previous 24 hours. These
commenters also state that the 7-day
functional check requirement in
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proposed § 60.19(a)(3) would be
difficult to track and makes no
provision for an FSTD that is being
modified, overhauled, or is not being
used for some other reason. DHL states
that this provision should be expanded
to allow periods of down time that
would not disqualify the simulator.
Since DHL does more revenue flying in
November and December, it plans its
pilot training to occur from January
through October. Paragraph (a)(3) would
require needless checks during periods
when its instructors are needed for line
operations and the simulators are not
being used, according to DHL. United
makes a similar suggestion.
FAA Response: The FAA adopted
several changes to the time
requirements in this section so that use
of the FSTD will now require the
completion of a ‘‘functional preflight
inspection’’ within the previous 24
hours. In addition, the FAA has
determined that the 24-hour functional
preflight inspection is sufficient, and
therefore has not included the proposed
7-day functional check.
Recurrent Evaluations
In regard to proposed § 60.19(b), JAA
questions why the term ‘‘recurrent
evaluation’’ is used here, when
‘‘continuing evaluation’’ is used
elsewhere.
ATA believes that requiring the
sponsor to initiate the scheduling for
recurrent evaluations, as required in
paragraph (b)(2), is not logical because
the NSPM will still be required to
maintain resources and an internal
process for managing the scheduling.
ATA recommends continuing the
current practice of the sponsor
submitting a letter to the NSPM with
requested evaluation dates.
ATA comments that paragraph (b)(3)
has no restriction on the amount of
FSTD time the NSPM can use for the
recurrent evaluations. ATA knows of no
historical evidence that the traditional 1
day of FSD availability is in any way
insufficient. ATA suggests retaining the
current practice of specifying that the
testing period will be 1 day, unless
otherwise agreed to by the evaluator and
sponsor. American states that the QPS
doubles the amount of time that the
simulator must be available for the
recurrent evaluations. American
suggests that the NSPM provide a list of
those tests required to be run so that
they can be accomplished before the
start of the evaluation.
FSB believes the specification of time
of day and day of week in paragraph
(b)(3) is not appropriate for a regulatory
document and should be deleted. FSI
comments that the FAA limits its
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availability to the work week under this
paragraph, but requires the industry to
be available seven days a week, under
§ 60.9(a).
ATA and Delta object to the NSPM
having full power over how often it
wishes to impose recurrent testing,
through its approval of the MQTG.
Since the FAA switched from a
biannual evaluation to an annual
evaluation for FSDs two years ago and
the average number of FAA
discrepancies has not increased, ATA
and Delta believe the FAA should retain
the practice of a 12-month recurrent
evaluation period. CAE recommends
changing ‘‘MQTG’’ in this paragraph to
‘‘QAP.’’
ATA recommends adding ‘‘or within
the timeframe mentioned in (b)(5)’’ to
paragraph (b)(6) so that training can
continue during the grace period.
ATA comments that it appears that a
significant number of the FSTD
maintenance and reporting
requirements in the proposed rule are
designed for a Sponsor who operates
their FSTDs at a slower pace than a
large carrier, which operates around the
clock in excess of 360 days each year.
ATA states the NSPM must allow for a
high volume user to operate
unencumbered by artificially tight
timelines and record keeping
requirements. If some of the
requirements remain unchanged, ATA
believes the NSPM would have to staff
its office around the clock or
immediately move to grant Designee
authority to large select high-volume
Sponsors. ATA also comments that the
section title is confusing by including
the word ‘‘inspection,’’ implying
preventive maintenance, when the
section really addresses required
recurrent tests. ATA suggests using
‘‘Required QPS testing’’ in the section
heading instead.
FAA Response: The FAA has replaced
references to ‘‘recurrent’’ evaluations
with ‘‘continuing’’ evaluations. The
FAA has removed the references to time
of day and day of week and has added
‘‘or within the grace period as described
in paragraph (b)(5) of this section’’ to
§ 60.19(b)(6). Additionally, the FAA has
included language in the QPS
appendices that specifically sets out the
normal time and testing requirements
for such evaluations. In this final rule
the FAA continues the existing practice
of having the sponsor and NSPM
coordinate the best times to conduct the
required evaluations.
The final rule codifies the existing
authority to impose continuing testing
through approval of the MQTG;
therefore the FAA has not revised the
language regarding this issue. The FAA
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63417
has retained the reference to ‘‘MQTG’’
in paragraph (b)(4) instead of changing
the reference to ‘‘QMS’’ (formerly QAP
in the NPRM), because the MQTG is the
FAA approved test guide, whereas the
QMS is for quality assurance purposes.
Also the FAA has retained the term
‘‘inspection’’ in the title because a
continuing qualification evaluation
includes not only an evaluation of the
device, but also an inspection of records
pertinent to the FSTD.
Continuing Corrective and Preventive
Maintenance
Delta requests a clarification of the
reference to proposed § 60.15(b) in
paragraph (c), citing a possible
interpretation that a qualified pilot
would be required to sign off on each
recurrent evaluation and on each change
made to the FSTD. ATA suggests
changing ‘‘requirements of § 60.15’’ to
‘‘requirements of all applicable
provisions of appropriate QPS.’’ Delta
believes the pilot’s input should not be
required unless a change is made that
affects handling qualities. FSB states
that this paragraph places a burden on
the sponsor that should really be a
burden on the entity that owns and
maintains the FSD.
FAA Response: The FAA reorganized
§ 60.19 for greater clarity and ease of
understanding. The FAA revised this
section to clarify that the sponsor is
responsible for continuing corrective
and preventive maintenance on the
FSTD to ensure that it continues to meet
the requirements of this part and the
applicable QPS appendix. The FAA also
removed the reference to § 60.15(b). In
addition, the FAA has clarified when a
sponsor may use, allow the use of, or
offer the use of an FSTD for flight
crewmember training, evaluation, or
flight experience. The FAA notes that
part 60 is geared toward the sponsor.
The sponsor may contract out
maintenance, but it still remains
responsible for meeting the
requirements in this part no matter who
owns or maintains the FSTD.
Discrepancy List
In regard to proposed § 60.19(a)(4)
and (a)(5), ATA requests that the FAA
define specifically what constitutes a
discrepancy that must be maintained on
a list in or immediately adjacent to the
FSD and states that historically, most
FSD departments have posted all
discrepancies that have the possibility
of impacting training or checking. ATA
states that if the intent is for every
discrepancy written by the flightcrew,
preflight checker, or observer to be
included on the list, the list would be
unnecessarily long. Furthermore, ATA
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states that almost all of the new
documentation required under part 60
evolved or was taken directly from the
Simulation Quality Assurance Program
for 2000 (SQAP 2000) and asks which
parts, if any, of SQAP 2000 will
continue to be in effect.
ATA also comments that the wording
of paragraph (a)(5)(i) can be construed to
mean that discrepancies older than 30
days should specifically not be in the
log. ATA suggests changing the wording
to ‘‘until at least 30 days.’’
ATA suggests that the entry required
under paragraph (a)(5)(ii) should also
include the name of the individual
doing the corrective action. Pan Am
states that there is nothing to be gained
by maintaining the record of the
corrective action for 30 days and
suggests reducing the time period to no
more than 10 days.
ATA states that the requirement in
paragraph (a)(5)(iii) to keep the
discrepancy log in a ‘‘form and manner
acceptable to the Administrator’’ gives
the NSPM full veto power over a
sponsor’s log system, with no definition
of what constitutes an acceptable
system.
FAA Response: The FAA has changed
the time requirements so that discrepant
items will remain in the log book until
corrected, instead of including a specific
length of time. The requirements
regarding the recording and correction
of discrepancies are now found in
§ 60.19(c)(2)(i) through (iii). The FAA
has revised § 60.19(c)(2)(ii) (formerly
§ 60.19(a)(5)(ii)) to include the name of
the individual doing the corrective
action. Also the FAA has modified
§ 60.19(c)(2)(iii) to permit electronic
record keeping.
For clarification the FAA has added a
definition of the term ‘‘discrepancy’’ in
appendix F. Discrepancy means ‘‘an
aspect of the FSTD that is not correct
with respect to the aircraft being
simulated.’’ The use of a discrepancy
log is not new. Sponsors have been
documenting the discrepancies found
during the operation of an FSTD for
decades. The only difference here is that
this process is now coming under a
regulatory requirement rather than just
being consistent with FAA guidance
and good operating practice.
SQAP 2000 is a voluntary QMS
program. Under the final rule, the QMS
is mandatory and must meet the
requirements of appendix E of this part.
The phrase ‘‘form and manner
acceptable to the Administrator’’ is
intended to be permissive rather than
restrictive. However, an acceptable
discrepancy log will have at least the
following characteristics: (1) Be easily
maintained by the sponsor; (2) be easily
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audited; and (3) entries may not be
easily altered or removed. Although the
FAA is not requiring a specific format,
the FAA may request additional
information to clarify entries on the
discrepancy log if necessary.
Comments Regarding Logging FSD
Discrepancies (§ 60.20)
Delta comments that this section
should only require discrepancy log
write-ups for items that would adversely
affect training or which indicate a
conflict with the Statement of
Qualification. According to Delta, this
section could be interpreted to mean
that equipment or appliances not
simulated would have to be written up
every time. An individual comments
that this section does not appear to
allow maintaining a separate
maintenance-only discrepancy log. The
commenter states that if discrepancy
reports unrelated to the operation of the
simulator or simulated aircraft are
included (such as shop type supplies,
touchup paint, and seat covers), a user
might overlook a discrepancy report that
might be of significance to their
training. Also the commenter asks if the
log could be computerized with a
terminal at or near the simulator. FSI
questions the phrase ‘‘flight experience
for flightcrew member certification or
qualification,’’ stating that its use in this
section is inconsistent with the
definition of the term in § 60.3. FSI
recommends changing ‘‘training or
evaluation, or observing flight
experience’’ to ‘‘training, testing, or
checking’’ to be consistent with the
other rules.
FAA Response: The requirement in
§ 60.20 does not preclude an FSTD
sponsor from maintaining a separate log
of items that are in need of repair or
replacement, the contents of which do
not affect the operation of the FSTD and
do not affect the purposes for which the
FSTD may be used. However, the FAA
does require that all discrepancies are
recorded in a log. The FAA has removed
the phrase ‘‘for flightcrew member
certification or qualification’’ to be more
clear. Additionally, the phrase
‘‘conducting training, evaluation, or
flight experience’’ is consistent with
other rules in this part. The term
‘‘evaluation’’ is defined for use in part
60 as follows: ‘‘with respect to an
individual, the checking, testing, or
review associated with flight
crewmember qualification, training, and
certification under parts 61, 63, 121, or
135 of this chapter.’’ Also, the FAA
modified § 60.19(c)(2)(iii) to permit
keeping the discrepancy log in an
electronic format.
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Comments Regarding Interim
Qualification of FSDs for New Aircraft
Types or Models (§ 60.21)
Boeing states that the phrase ‘‘even
though the flight test data used has not
received final approval by the aircraft
manufacturer’’ in paragraph (a) should
be changed to ‘‘even though the aircraft
manufacturer’s flight test data may be
considered preliminary’’ because this
data has been approved. CAE suggests
changing ‘‘aircraft manufacturer’’ with
‘‘approved data supplier’’ to allow other
reliable sources to produce data for this
interim level of qualification. CAE states
that other sources are often used to
produce data for business jet aircraft.
Boeing suggests revising paragraph
(a)(1) to more accurately describe the
type of data that would be acceptable for
an interim qualification.
FAA Response: In the final rule, the
FAA has revised § 60.21 to allow a
sponsor to apply for and the NSPM to
issue an interim qualification level for
an FSTD for a new type or model of
aircraft, even though the aircraft
manufacturer’s aircraft data package is
preliminary. The additional safeguards
in the final rule regarding the use of
preliminary data are sufficient to ensure
safety until the final data package is
released.
The FAA recognizes that in some
instances there may be other ‘‘data
providers’’ who will become involved
with development of data, data
packages, or the development of
simulation models. The FAA did not
change the term ‘‘aircraft
manufacturer.’’ The FAA recognizes that
some of the data used might come from
prediction or other methodologies
developed by another ‘‘data provider’’
that would allow for the ‘‘interim’’
classification without having full flight
test data. However, all such non-flight
test data would be dependent on at least
some flight test data from the airplane
manufacturer. In these cases, the FAA
would want not only the aircraft
manufacturer’s preliminary data, but
also the other data and the justification
for that other data supplied by whoever
supplies that data.
In addition, the FAA revised
paragraph (a)(1) to more clarify the type
of data that would be acceptable for an
interim qualification.
Limit for Interim Qualification
Several commenters object to the oneyear limit for interim qualification in
paragraphs (b) and (c). ATA states, ‘‘The
number of factors that affect a new
aircraft type or model is sufficiently
complex and unpredictable that there
should not be a simple 1-year death
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penalty on the interim qualification.
This issue needs to remain as flexible as
possible in order to facilitate new
aircraft types and models, because to do
otherwise will delay training to the
point that too much training will be
needed in too little time, resulting in
decreased air safety, not increased.’’ FSI,
Delta, TWA, and Boeing make similar
comments. TWA suggests the interim
qualification should last six months
after the release of the final flight test
data package, unless specific conditions
warrant a longer period as approved by
the NSPM. Boeing states that ‘‘six
months after release of final flight data’’
is typically at least 18 months after the
end of the flight test program and is
much later than one year after the
issuance of the interim qualification
status. Boeing suggests using language
equivalent to paragraph 1.6 of
Attachment A of the 2nd Edition to the
ICAO Manual of Criteria for the
Qualification of Flight Simulators.
FAA Response: The FAA has revised
paragraph (c) to increase the time frame
to obtain final qualification. The FAA
has reworded the requirement to allow
12 months from the release of the final
aircraft data package by the aircraft
manufacturer, but no later than 2 years
after the issuance of the interim
qualification status, for the sponsor to
incorporate the final aircraft data
package and have the NSPM conduct an
evaluation of the FSTD with the new
data to remove the ‘‘interim’’ status of
the FSTD qualification. The FAA
considers 2 years to be an adequate
amount of time for the sponsor to
incorporate the final aircraft data
package.
Comments Regarding Modifications to
FSTDs (§ 60.23)
ATA, Continental, FSI, Delta, United,
and several other commenters ask for a
more specific definition of the term
modification in proposed § 60.23,
stating that the term is subject to a wide
range of interpretation and judgment.
Commenters believe that as proposed,
§ 60.23 would place a severe burden on
both the FAA and all FSTD sponsors if
the FAA does not provide greater
clarification.
Boeing and FSI question how the FAA
will determine when a modification
impacts safety of flight. Also FSI asks
that the FAA clearly define the
circumstances under which it would
produce an FSTD Directive and whether
the FSTD manufacturer or FSTD user
has any recourse.
FAA Response: The FAA revised this
section to address commenters’
concerns about the definition of
modification and the cost implications
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if the term is defined too broadly. The
FAA clarified the definition of
modification and reorganized this
section. While the content of the section
has essentially remained the same, the
rewrite has reduced the length of the
section and included sub-headings that
should help the reader understand how
the main paragraphs and subparagraphs
are related. The rewrite has significantly
clarified the original intent of this
section.
The FAA has not revised the words
‘‘safety of flight’’ in § 60.23(b) as
requested by commenters. An FSTD
Directive would only be issued if safety
of flight was at issue and the effect of
the FSTD Directive would be to amend
the qualification basis for the FSTD. As
stated in the NPRM (67 FR 60284,
60286) an FSTD Directive would only
be issued in response to a recognized
safety-of-flight issue. For example, the
FAA may issue an FSTD Directive if a
manufacturer or the FAA discovers that
the existing data for an aircraft is not
accurate and consequently would
adversely affect FSTD performance and
handling. The FAA will publish each
FSTD Directive in the Federal Register
and will comply with the
Administrative Procedure Act
requirements.
Comments regarding Operation with
Missing, Malfunctioning, or Inoperative
Components (§ 60.25)
Many commenters object to the
requirement in proposed § 60.25(b) that
each missing, malfunctioning, or
inoperative component must be repaired
or replaced within 7 calendar days. UPS
believes this would be an unreasonable
burden on both the sponsor and the
FAA. UPS predicts that FAA will be
burdened with a daily onslaught of
routine requests to deviate from this
provision. ATA recommends the rule
should be written such that if no
response to a request to authorize
deviation from the rule is received
within 2 hours, then it is granted. Also,
the commenters note that many
simulator-specific parts cannot be
obtained within a seven-day timeframe.
Further, if the problem is not a
malfunctioning part, but rather a
computer programming fault, then
research, data, or other contractor
assistance may be required. American
Trans Air makes a similar comment.
American states that if the NSPM or
TPAA are not available, unnecessary
training down time could result.
DHL states that the proposal would,
in many cases, be more restrictive than
a Minimum Equipment List (MEL) for
an actual aircraft. DHL notes there are
no safety of flight issues in an FSD. DHL
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63419
suggests counting only ‘‘training days’’
so that the FSD would not need to be
repaired during periods of inactivity or
when the training facility was not open.
CAE provides the example of an
unserviceable third VHF radio: The real
aircraft can dispatch in this situation,
while the simulator would be grounded
under this paragraph.
Several commenters believe the FAA
would be burdened by an obligation to
provide an inspector 24 hours a day, 7
days a week. TWA believes that the
sponsors would not wait to find out if
they will receive the parts until the
seventh day. Rather they would notify
the NSPM early, resulting in thousands
of notifications, which would
unnecessarily burden the NSPM.
Delta, Eclipse, Evans and Sutherland,
ATA, Fidelity, and FSI state that the
proposed rule allows only seven days
for repairing or replacing missing,
malfunctioning, or inoperative
components, while the appendix states
30 days is allowed. These commenters
say the 30 day period is more realistic.
RAA believes the rule should be
written in a form similar to the MMEL
requirements for an airplane, where
specific time requirements are not
referenced in the rule itself.
United suggests allowing the sponsor
to develop a discrepancy prioritizing
system, with the time allowed for
replacement or repair dependent on the
priority.
FAA Response: In the final rule the
FAA will require missing,
malfunctioning, or inoperative
components to be repaired or replaced
within 30 calendar days (instead of the
originally required 7 days), while
maintaining the original ‘‘unless
otherwise required or authorized by the
NSPM’’ phrasing. Additionally, as
stated in the QPS, the FAA will
consider a discrepancy prioritizing
system where the length of time
authorized to repair or replace any given
missing, malfunctioning, or inoperative
component is based on the level of
impact on the capability of the
simulator to provide the required
training, evaluation, or flight
experience, with the larger impact on
this capability associated with a higher
priority for repair or replacement.
The rewrite of this section provides
adequate requirements without getting
into the specifics of individual
components. This is not an
airworthiness issue, but is rather a
training efficacy issue that is adequately
accommodated with the revisions
indicated.
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Discrepancies that Directly Affect
Training
Eclipse also believes the proposed
requirement is too stringent. Eclipse
believes this issue should be left to the
discretion of the sponsor or the sponsor
in coordination with the TPAA for
equipment discrepancies that directly
affect training. CAE and FSB make
similar suggestions.
NBAA states that the provision makes
no allowance for components that may
be inoperable but are not required for
training. NBAA recommends that
training be allowed to continue for
components that are not training
critical. ATA suggests a reference to
equipment required in the current
training scenario. Delta makes a similar
comment.
FAA Response: The purpose of this
section is to allow for the operation of
the FSTD with missing, malfunctioning,
or inoperative components. If a missing,
malfunctioning, or inoperative
component is not required to be present
and correctly operating for the
satisfactory completion of a specific
maneuver, procedure, or task being
performed during the training, the FSTD
can be used for that maneuver,
procedure or task.
Simulator MEL
FSI states that both appendix H of
part 121 and § 142.59 provide a
simulator minimum equipment list and
that handbook guidance issued to FAA
inspectors gives lengthy guidance. FSI
recommends that FAA withdraw
appendix H and make a conforming
change to § 142.59.
FAA Response: In this final rule, the
FAA is modifying existing part 121,
appendix H, to eliminate all technical
requirements regarding FSTDs,
including the requirement for a
‘‘simulator MEL.’’ The language of this
section is not in conflict with and does
not require any modification to § 142.59.
Additionally, with the provisions of this
section, the FAA Handbook guidance
issued to FAA inspectors regarding
operation of FFSs and FTDs with
missing, malfunctioning, or inoperative
components will be withdrawn.
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Placarding
ATA comments that proposed
paragraph (c) would require a
maintenance technician to be at the
ready (to perform the placarding) when
each FSD period is scheduled to begin,
adding an enormous financial burden
for no perceived gain in training value.
ATA and United suggest that the
requirement in paragraph (c) to have a
list of missing, malfunctioning, or
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inoperative components available
should suffice for daily operations. ATA
adds that the placard system is very
time consuming and adds nothing to the
training, if the item is already in the
discrepancy log, which is read before
each training session starts.
Pan Am comments that the
requirement to placard items in the FSD
that do not work should only apply to
those items that are missing or
malfunctioning, and not to items which
are not simulated by design. Systems or
controls that are non-functional will be
indicated on the qualified or not
qualified list in the FSD Statement or
Qualification.
FAA Response: The FAA has removed
the placarding requirement. Having the
list of missing, malfunctioning, and
inoperative equipment available for
users of the FSTD is sufficient.
Comments Regarding Automatic Loss of
Qualification and Procedures for
Restoration of Qualification (§ 60.27)
Continental states that the
requirement to get NSPM approval prior
to putting a FSD back into service
following any work that makes the
device ‘‘unusable’’ has the potential to
place severe restrictions on the airline’s
ability to schedule and use the device
for training. It would also mandate that
the NSPM be available 24/7 to provide
this approval in a timely manner.
FAA Response: The FAA has clarified
the requirements that must be met prior
to returning an FSTD to qualified
service. The revisions include
§ 60.27(b)(2), which provides that the
NSPM may authorize the FSTD to return
to service without completing an
evaluation.
Qualified Use of FSTDs
ATA and FSB believe that the cross
reference to § 60.9(b)(4) in proposed
§ 60.27(a)(1) is in error, because that
paragraph refers to posting the
Statement of Qualification, not to the
sponsor’s training program. TechniFlite
and Fidelity object to paragraph (a)(1)
because it implies that FSDs used for
part 61 training, for personal practice, or
even for another certificate holder’s
training program are not qualified.
FAA Response: The FAA has
reviewed cross references and has
corrected them. A person is eligible to
be a sponsor if the person holds, or is
an applicant for, a certificate under part
119, 141, or 142; or holds, or is an
applicant for, an approved flight
engineer course in accordance with part
63. Therefore, a part 61 Fixed Base
Operator (FBO) that conducts training in
accordance with part 61 may not
sponsor an FSTD, but the regulations do
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not restrict anyone from using a
qualified FSTD in accordance with that
FSTD’s authorizations. Also, an FSTD
may be used for training in another
certificate holder’s training program as
approved by the TPAA.
Moved or Disassembled FSTDs
Several commenters disagree with the
proposed language of § 60.27(a)(3) and
(a)(4), stating that it is not necessary to
disqualify an FSTD in all cases when it
is moved or disassembled. Fidelity
states that lower level FTDs can be
moved without affecting their
capabilities. CAE believes that if a
simulator is moved but has been
maintained in accordance with the
approved SQAP, then requalification
should be conducted under the existing
qualification basis of the simulator.
United and TechniFlite state they have
moved simulators with no adverse
impact on their integrity. United
proposes that the requirement only
apply if a simulator needs to be
reinstalled, e.g., if the wiring is
disconnected and reconnected.
Eclipse states that simple regular
maintenance on the FSTD would result
in ‘‘disassemble for repair’’ and thus
require the sponsor to contact the TPAA
or NSPM on an almost daily basis. CAE
requests clarification or removal of this
provision, since whenever maintenance
is done, the FSTD is not able to be used
for training at that time. ATA states that
once an FSTD is reassembled, obtaining
FAA approval for returning the device
to training will place a major burden on
both the sponsor and the FAA. United
comments that the requirement should
be rewritten to allow normal FSTD
maintenance activities. Delta, American,
FSB, and FSI make similar comments.
FAA Response: The FAA has revised
§ 60.27(a) to address those FSTDs that
have been moved and reinstalled in a
different location. When an FSTD,
regardless of level, is moved and
reinstalled in a different location, it
must be re-evaluated by the NSPM to be
sure that it continues to meet the
requirements for its original
qualification. This is true even in the
example of an FSTD that was originally
mounted in a transportable conveyance.
The final rule lists four specific
situations that result in automatic loss
of qualification. Disassembly is not one
of them. The proposed language about
disassembly does not appear in the final
rule. For information on modifications,
see § 60.23. Although ‘‘disassembly’’
does not appear in § 60.27 of the final
rule, the FAA recognizes that
disassembly may occur in the course of
routine or non-routine repairs and
maintenance. We want to emphasize
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that the sponsor is responsible to ensure
that the FSTD continues to meet the
requirements of this part and the
applicable QPS appendix at the
completion of any repair or
maintenance in accordance with
§ 60.19(c).
Restoration of Qualification
ATA states that proposed
§ 60.27(b)(1)(i) would eliminate
grandfather rights for older FSDs any
time they are moved, repaired, or
modified. ATA recommends changing
the requirement so that the initial
requalification is in accordance with the
standards that the FSD was most
recently qualified under. ATA suggests
including the provisions of § 60.17(c),
which provides up to two years before
requiring requalification based on
current standards. CAE makes a similar
comment.
FAA Response: There is nothing in
the language that would indicate that
moving an FSTD would necessarily
require re-evaluation in accordance with
newer standards. The FAA notes,
however, that when an FSTD is taken
out of service, this does not
automatically guarantee that
reevaluation for qualification will be
against the original qualification basis.
The NSPM will conduct a review to
determine the care and under what
circumstances the FSTD has been
maintained before determinations of
qualification basis may be made.
Moreover, if the FSTD was out of
service for 2 or more years, the FAA
would require a reevaluation under
current standards that may be different
than the standards under which the
FSTD was originally qualified.
sroberts on PROD1PC70 with RULES
Authority to Waive Evaluation
ATA and United request that the FAA
clarify the lines of authority in proposed
§ 60.27(b)(2). United suggests removing
the reference to the TPAA and allowing
only the NSPM the authority to waive
the evaluation requirement.
FAA Response: The FAA has clarified
the lines of authority by removing the
TPAA from exercising authority to
waive the evaluation requirement.
Requalification Criteria
ATA and United believe the FAA
should develop objective criteria for
proposed § 60.27(c). For example, how
would the FAA assess the ‘‘care that had
been taken of the device since the last
evaluation?’’ United suggests the FAA
specify the number of normally
scheduled evaluations that can be
missed and the performance of the
particular FSD against the sponsor’s
quality measurements in its QAP.
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FAA Response: The FAA has added
language to the Information section of
the QPS indicating that one of the
factors the FAA uses to determine what
amount of testing will be required for
requalification is how the simulator is
maintained during its out-of-service
period (e.g., periodic exercise of
mechanical, hydraulic, and electrical
systems; routine replacement of
hydraulic fluid; and control of the
environmental factors in which the
simulator is to be maintained).
Comments Regarding Other Losses of
Qualification and Procedures for
Restoration of Qualification (§ 60.29)
ATA and United comment that this
section blurs the lines of authority
between the NSPM and the TPAA. The
commenters believe only the NSPM
should have jurisdiction over the
qualification of any FSD covered by this
part and only the TPAA should have
jurisdiction over the use of a qualified
FSD in an FAA-approved training
program. United suggests removing all
references to the TPAA from this
section. ATA recommends adding a
paragraph (d) to include the procedures
for restoring the qualification lost under
this section since this issue is not
addressed in the proposed rule
language.
In regard to the process for handling
emergencies under paragraph (c), FSI
comments that no emergency in
simulation is so dangerous that there is
no time to consult with the TPAA. FSI
states that the NSPM should not be
allowed to suspend the use of an FSD
in an approved training program
without agreement from the TPAA.
Delta suggests changing ‘‘7 days’’ in
paragraph (a)(2) to ‘‘30 days’’ to be
consistent with other references to 30
days in this section.
FAA Response: The FAA has removed
all references to the TPPA in § 60.29.
Additionally, the FAA inadvertently left
out of the NPRM the sub-paragraph
addressing procedures for restoring the
qualification lost under this section as
described by the commenter. The FAA
has added such a paragraph in the final
rule.
The FAA did not adopt the suggestion
to replace ‘‘7 days’’ with ‘‘30 days’’ in
§ 60.29(a)(2). The final rule provides
time for the sponsor to object to the
notification that the FSTD no longer
meets some or all of its qualification
standards. The 7-day period was
originally selected to provide the NSPM
up to 23 days between the receipt of the
sponsor’s objections and justifications
and the effective date of any action
regarding the FSTD. This provides the
most benefit to all affected parties.
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63421
Comments Regarding Recordkeeping
and Reporting (§ 60.31)
Regarding paragraph (a), ATA states
that there will be an additional
administrative and storage location
overhead cost to maintain previous
copies of the MQTG, each of which may
be over 10 volumes. Also, ATA suggests
changing the wording to require that the
sponsor have a system to trace the
current version of the simulator back to
the original qualification software/
hardware and deleting the requirement
for maintaining the actual copy of the
programming. United and Delta make
similar comments. Also, ATA requests
that the FAA clarify that, for currently
qualified simulators, only records made
after the effective date of the rule would
be required. Similarly, FSI states that
the FAA appears to have little concept
of the magnitude and cost of proposed
paragraph (a)(2). FSI suggests that
instead, the NSPM track changes to the
FSD via the modification requirement in
§ 60.23(e). ATA and United suggest
shortening the required time period
proposed in § 60.31(a)(3)(iv) to 18
months and Delta suggests deleting
paragraph (a)(3)(iv).
ATA suggests that proposed
§ 60.31(a)(4) also require that sponsors
keep the name of the person who
determines that a discrepancy is
corrected.
Delta suggests rewording proposed
§ 60.31(a)(5) to say ‘‘initial or upgrade
qualification’’ to cover upgrade
situations that are in effect new ‘‘initial’’
qualifications. ATA suggests that ‘‘FSD
hardware configurations’’ in paragraph
(a)(5) should be changed to ‘‘FSD
hardware configurations, restricted to
ground or flight dynamics or
performance and handling or aircraft
system function.’’
FAA Response: In the NPRM,
§ 60.31(a)(2) proposed to require the
sponsor to maintain a copy of the
programming used during the
evaluations for initial and upgrade
qualifications and a copy of all
programming changes made since the
evaluation for initial qualification.
Revised § 60.31(a)(2) requires the
sponsor to maintain a record of all FSTD
modifications affected under § 60.23
since the issuance of the original
Statement of Qualification. The revision
to § 60.31(a)(2) captures the software
and hardware changes required in
proposed § 60.31(a)(2) and (a)(5). We
have therefore deleted § 60.31(a)(5).
Also, the FAA has modified
§ 60.31(a)(4) to require that sponsors
keep the name of the person who
determines that a discrepancy is
corrected.
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Record of FSD Users
ATA and United state that proposed
§ 60.31(b) places an unnecessary burden
on the FSD sponsor. Instead they
believe the burden should be placed on
the user in coordination with their
respective TPAA. ATA and United
suggest deleting this requirement or
requiring that sponsors have 7 days to
provide the report upon request of the
NSPM. FSB and CAE suggest that such
a list of certificate holders may be
considered proprietary business
information. FSB states that ‘‘This is
another instance where the ongoing use
of the FSD has been proposed as within
the purview of the NSPM as opposed to
the operational responsibility remaining
with the certificate holder sponsor with
the approval of either the TCPM or POI
under existing regulations.’’
FAA Response: The FAA has
eliminated the requirement to maintain
the records of users of the FSTD. If the
FAA needs such records, it would
acquire them through normal FAA
oversight channels.
Form of Records
In regard to proposed § 60.31(c), ATA
and United state that most airlines have
record systems that have proven
effective and accurate in actual use.
ATA and United state that the NSPM’s
approval of these systems should be
immediate and that the rule language
should be changed to add ‘‘information,
with appropriate security or controls to
prevent the illegal or inappropriate
alteration of such records after the fact.’’
FAA Response: The FAA added
language in the QPS appendix that
provides for the preservation and
retrieval of this information with
appropriate security or controls to
prevent the illegal or inappropriate
alteration of such records after the fact.
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Annual Report
ATA, UPS, Delta, United, FSI,
American, Eclipse, American Trans Air,
and CAE object to proposed § 60.31(d),
stating that the annual report would be
redundant.
FAA Response: The FAA has
eliminated the requirement for an
annual report that was in proposed
§ 60.31(d). The other requirements of
part 60, including the discrepancy log,
the recurring inspections, the
modification notification and approval,
and the QMS are sufficient to ensure
that FSTDs are operating at their
qualification level.
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Comments Regarding Applications,
Logbooks, Reports, and Records: Fraud,
Falsification, or Incorrect Statements
(§ 60.33)
ATA is concerned that the language
contained in this section does not
provide a clearly defined method for
complying with requirements like the
quality assurance program, log books,
reports, and requests. ATA comments
that paragraph (c) provides the authority
to remove qualification simply on the
basis of an incorrect statement, which
could be made by any individual at any
level of the organization. According to
ATA, while the NSPM has always
maintained a cooperative relationship
with the industry, others, such as ATOS
inspectors, only apply the strict
interpretation of requirements and often
apply rules without the benefit of the
required knowledge of the flight training
device industry. ATA further states that,
‘‘This section threatens not only our
qualifications but also our personal
livelihood. A simple misstatement,
mistake, or omission without a clearly
demonstrated intent to mislead should
not be a basis for action. It should be
applied to the intent of the operator
and/or sponsor not the individual.’’
ATA suggests changing ‘‘No person may
make’’ to ‘‘No sponsor may knowingly
make’’ and deleting paragraph (c).
Similarly DHL states that the
omission of recording malfunctions or
inaccurate statements in logbook entries
is very subjective. DHL is concerned
that honest mistakes and oversights
could lead to the revocation of an
airman’s ATP, and states ‘‘Such
perceived liability could cause the ranks
of qualified instructors to dwindle.’’
Fidelity, FSI, CAE, and Delta make
similar comments.
FAA Response: This section is not
intended to address a simple
misstatement, mistake, or omission as
suggested might occur. The language is
included to provide notice to those who
are involved with or use FSTDs that the
records and reports that are kept, made,
or used to show compliance with this
part, or to exercise any privileges with
respect to FSTD upon which the FAA
relies or could rely, is a serious matter
and that fraudulent practices will carry
consequences. The elements for a charge
of making a false statement are: (1) A
knowing, (2) misrepresentation, (3) of a
material fact. The elements for a
fraudulent statement are the same as for
a false statement, plus: (4) made with
the intent to deceive, and (5)
detrimentally relied upon. See FAA v.
Bell, NTSB Order No. 4764 (May 11,
1999). Thus, for either charge, the FAA
must have evidence that it was a
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knowing misstatement and that the
misstatement was material (i.e., about
an important matter). See FAA v.
Twomey, 821 F.2d 63 (1st Cir. 1987). We
have added the word ‘‘material’’ to the
phrase ‘‘known omission’’ to clarify that
only important, known omissions will
constitute a violation and this will put
the violation on par with the fraud and
intentionally false statement violation.
Comments Regarding Specific Full
Flight Simulator Compliance
Requirements (§ 60.35)
Many commenters address the impact
of proposed § 60.35 on Level A
simulators. The ATA strongly opposes
degrading the qualification of all level A
simulators after a 2 year period. ATA
believes that as long as there are valid
training objectives that can be
accomplished in a level A simulator it
should be the sponsor’s business
decision as to when the device is no
longer viable and not determined by the
NSPM. Pan Am states that elimination
of the Level A qualification would
create specific issues for those aircraft
that are no longer manufactured, but
continue to operate. Pan Am states,
‘‘These simulators are typically not cost
effective to upgrade to current
technology standards but have
demonstrated and been used for many
years as effective training devices * *.
We believe these simulators and the
training permitted in them should be
grand-fathered in any new rule.’’ Pan
Am, FSI and Aerospace Aviation are
also concerned that this provision
would result in a return to using aircraft
for training, which would have a
negative impact on both the training,
safety, and pollution.
FSI addresses the impact on certain
aircraft, stating, ‘‘The bottom line would
be that users of many aircraft, such as
the older King Air, Turbo Commander,
Lear 25, Gulfstream I, Jetstar, etc., would
have no simulation device at all
available to them. The time-tested
safety-driven need for these simulators
will be there as long as the aircraft they
represent are flying. It is obvious that
new simulators, Level B through D, will
not be developed for these older aircraft,
so the withdrawal option is to withdraw
all simulation safety advantage from this
segment of the aviation population.’’ In
addition, FSI states that to convert the
Level A simulators to Level 6 FTDs
‘‘would be to lose the advantage of
motion, which the FAA, in particular
the NSPM, has strongly favored and
embraced for realism in training and
testing, as opposed to simulation with
visual cues only. Continuing to
maintain a motion system for a Level 6
FTD, for no credit in addition to that
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afforded a Level 6 FTD, would represent
a huge cost with no benefit to offset it.’’
FSI further comments, ‘‘Just as the FAA
would not propose that all operators of
those aircraft abandon their aircraft, it
should not propose that Training
Centers abandon the representative
simulators.’’
Similarly, TWA states, ‘‘This
paragraph puts an undue burden on the
sponsors of older flight simulators. The
cost to make all aircraft appliances
functional whenever they upgrade an
older simulator will effectively
eliminate all upgrades. This would
severely limit modernization and
improvements to these simulators.
There is no reason for devices in an FSD
to be functional if they are never to be
used by the approved training
program.’’ ATA makes a similar
comment.
Several commenters question to what
extent the FAA expects the entire
cockpit to be simulated, under
paragraph (a). Boeing states that for
some aircraft there is not enough room
in the simulator to simulate the entire
area directly behind the Captain and
First Officer. ATA and United comment
that sponsors with no captive fleet
would not have a specific cockpit
against which to match an FSD and
sponsors with their own fleet would
have differences between cockpits of
like aircraft. Delta and CAE make
similar comments.
DHL states that the language requiring
the FSD to simulate the operation of all
equipment or devices intended to
simulate aircraft appliances is too rigid.
DHL states, ‘‘This language would
require such devices such as radar and
TCAS systems to be fully functional.
These devices are often trained in such
devices as FTDs or Computer Based
Training (CBT) programs. The FAA
requires TCAS to be trained in a flight
simulator or CBT environment. DHL
argues that some devices are better
trained in other environments such as
CBT. This requirement also usurps the
intent of the Advanced Qualification
Program that would apply Instructional
Systems Design principles to conduct
training in lower level devices that may
not only be more cost effective but also
yield a higher level of learning.’’
UPS comments that paragraph (a)
would require that equipment not
related to flight training be installed at
considerable expense. UPS cites
examples such as ‘‘equipment used by
maintenance personnel, e.g., BIT type
diagnostic systems, or equipment used
by flight crew but not deemed essential
to flight training by the operator or its
TPAA, e.g., ACARS.’’ Evans and
Sutherland ask whether visual terrain
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and obstacle correlation over the entire
visual scene must be provided, e.g., for
future additions to the cockpit, such as
the Moving Map Display, or for aircraft
fitted with EGPWS or TWAS? Also, for
weather radar, must all 3D clouds,
storms, etc., on the visual scene
correlate with a dynamic radar sweep?
FSI states that proposed paragraph (a)
seems to say that 18 months after the
final rule is issued all simulators must
simulate everything in the aircraft they
represent. FSI asks, ‘‘Would this mean
that a Level B simulator must have color
weather radar simulated if the aircraft is
outfitted with color weather radar,
etc.?’’ FSI states that proposed QPS
requirements for FTD levels 4, 5, and 6,
as well as for simulator Levels A, B, and
C do not include simulating the
operation of all equipment and
appliances installed on the airplane
(aircraft) being simulated. FTDs could
fit the definition of a ‘‘simulator’’ and
therefore would not be compliant. FSI
recommends that FAA strike the all
encompassing term ‘‘all equipment or
devices’’ and clarify the intent of this
proposed section to include the
equipment simulation requirements for
each level of ‘‘flight simulator’’ as well
as specifically refer to FSD levels A–D
and clarify the definition of a ‘‘flight
simulator’’ to refer to FSD levels A–D.
ATA recommends that paragraph (b) be
changed to apply to ‘‘any level A
simulator’’ instead of to ‘‘any flight
simulator.’’
Delta suggests that § 60.35(b) or the
QPS should define the performance
criteria that will be used under
paragraph (b) and state that a Level A
simulator can be downgraded to a level
6 FTD without having to undergo an
additional evaluation.
FAA Response: The FAA adopted
several changes to this section that are
less restrictive than proposed and codify
existing practices. The revisions include
the following: Level A simulators will
not be eliminated as was proposed; the
requirement for Level C and Level D
simulators in § 60.35(a) will include the
equipment and appliances installed and
operating to the extent necessary for the
issuance of an airman certificate or
rating; the requirement for Level A and
Level B simulators in § 60.35(b) will
include the equipment and appliances
installed and operating to the extent
necessary for the training, testing, and
checking that comprise the simulation
portion of the requirements for issuance
of an airman certificate or rating. The
FAA has been careful to define FTD
levels and FSS levels and to use the
appropriate term in the appropriate
setting. This should eliminate any
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63423
confusion regarding qualification level
and required equipment.
Comments in Response to ARC
Recommendation
In order to give the public an
opportunity to comment on the
recommendations received from the
ARC, on February 10, 2004, the FAA
reopened the comment period for 30
days (69 FR 6216). The comment period
closed March 11, 2004. The FAA
received approximately 30 comments
during the reopened comment period.
However, instead of addressing the ARC
proposal, many of the commenters
addressed issues from the original
NPRM. These comments are similar to
comments that were previously
submitted. Other comments included
suggestions for minor editorial changes
from CAE Inc. and a question from the
Co-Chairman of the Air Transport
Association Simulator Technical Issues
Group asking if part 60 provides for self
disclosure of possible non-compliance
with part 60 requirements.
FAA Response: The FAA reviewed
the ARC recommendation and the
comments received in response to the
ARC recommendation. In response to
the comment regarding part 60 selfdisclosure programs, the FAA considers
the correct vehicle for such selfdisclosures to be Advisory Circular (AC)
00–58, Voluntary Disclosure Reporting
Program. The FAA recognizes that the
AC, as presently written, is applicable
only to certificate holders, but believes
sponsors qualified under part 60 could
develop a similar program based on the
available guidance in the advisory
material.
Delegation of Authority for Standards
Documents
The FAA has delegated in a separate
document, final authority to review and
issue amendments to appendices A–F to
part 60 from the Administrator to the
Director, Flight Standards Service.
Specifically, these appendices are the
Qualification Performance Standards
(QPS) documents for: Airplane Full
Flight Simulators; Airplane Flight
Training Devices; Helicopter Full Flight
Simulators; Helicopter Flight Training
Devices; Quality Management Systems
for FSTDs; and Definitions and
Abbreviations for FSTDs.
The FAA anticipates that these
documents will require routine changes
for a variety of reasons, e.g., increased
knowledge about human factors,
analysis of incident/accident data, and
changes in aircraft or simulation
technology. Because these standards
will be regulatory in nature, current
FAA policy provides for the
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Administrator to review changes before
final action on them is complete. This
process involves significant levels of
participation in the review process by
individuals at all levels of the agency.
The FAA expects that most future
changes to the QPS documents will be
published in the Federal Register as
NPRMs for public comment, just as they
are published as part of this NPRM. This
will be true unless ‘‘good cause’’ exists
under the Administrative Procedure Act
(APA), which would warrant the FAA
publishing a change to a QPS document
without following the standard notice
and comment procedures. Under the
APA, in order for the FAA to issue a
rule without following notice and
comment procedures, the FAA would
have to make a good cause finding that
following notice and comment
procedures would be impracticable,
unnecessary, or contrary to the public
interest.
The FAA does not expect that many
changes to the QPS documents will
justify the expenditure of time and
resources at the highest levels of the
agency that the standard procedures for
final review of rulemakings require.
Therefore, consistent with good
government, the FAA is streamlining
the process for making technical
changes to the QPS documents by
delegating authority for final review and
issuance from the Administrator to the
Director, Flight Standards Service. The
FAA believes that the delegation will
result in more timely responses to
incident and accident data and
advances in aircraft or simulation
technology.
Consistent with similar delegations of
authority, this authority will be
exercised with the concurrence of the
Office of the Chief Counsel. If, at any
time during the amendment process the
Administrator or the Director, Flight
Standards Service, determines that a
proposed amendment would not be
appropriate for this streamlined process,
the rulemaking project would proceed
in accordance with the agency’s normal
rulemaking procedures.
Paperwork Reduction Act
Information collection requirements
associated with this final rule have been
approved previously by the Office of
Management and Budget (OMB) under
the provisions of the Paperwork
Reduction Act of 1995 (44 U.S.C.
3507(d)), and have been assigned OMB
Control Number 2120–0680. This final
rule adds the OMB control number to
the table of OMB control numbers in 14
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CFR 11.201(b). An agency may not
collect or sponsor the collection of
information, nor may it impose an
information collection requirement
unless it displays a currently valid
Office of Management and Budget
(OMB) control number.
International Compatibility
In keeping with U.S. obligations
under the Convention on International
Civil Aviation, it is FAA policy to
comply with International Civil
Aviation Organization (ICAO) Standards
and Recommended Practices to the
maximum extent practicable. The FAA
has reviewed the corresponding ICAO
Standards and Recommended Practices
and has determined that additional
modifications to certain QPS sections
need to be made before the final rule
becomes effective. The FAA has not
included these QPS modifications in
this final rule because they are beyond
the scope of the NPRM. The FAA will
make these modifications before this
final rule becomes effective to comply
with ICAO Standards and
Recommended Practices to the
maximum extent practicable.
Regulatory Evaluation Summary
This final rule establishes 14 CFR part
60, which contains requirements for the
evaluation, qualification, and
maintenance of FSTDs.
Total Costs and Benefits of This
Rulemaking
The FAA has determined that the
total cost of implementing the new part
60 from 2006 to 2015 will be
approximately $1.3 million ($1.0
million, discounted). Nearly all of the
$1.3 million over the 10-year period will
be imposed on the industry. The FAA
10-year cost is estimated at $42,000.
The benefit of this rule is that it will
ensure that flight crewmembers using
FSTDs receive training in a device that
closely matches the performance and
handling characteristics of the aircraft
being simulated.
Who Is Potentially Affected by This
Rulemaking?
Sponsors of FSTDs, which includes
training centers and certain airlines, are
affected by this rulemaking.
Our Cost Assumptions and Sources of
Information
Discount rate: 7%.
Period of Analysis: 2006–2015.
Monetary Values expressed in 2004
dollars.
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Costs per individual action vary
depending on whether the sponsor is
small, medium, or large.
Regulatory Flexibility Determination
The Regulatory Flexibility Act of 1980
(RFA) establishes ‘‘as a principle of
regulatory issuance that agencies shall
endeavor, consistent with the objective
of the rule and of applicable statutes, to
fit regulatory and informational
requirements to the scale of the
business, organizations, and
governmental jurisdictions subject to
regulation.’’ To achieve that principle,
the Act requires agencies to solicit and
consider flexible regulatory proposals
and to explain the rationale for their
actions. The Act covers a wide-range of
small entities, including small
businesses, not-for-profit organizations
and small governmental jurisdictions.
Agencies must perform a review to
determine whether a proposed or final
rule will have a significant economic
impact on a substantial number of small
entities. If the determination is that it
will, the agency must prepare a
regulatory flexibility analysis as
described in the Act.
However, if an agency determines that
a proposed or final rule is not expected
to have a significant economic impact
on a substantial number of small
entities, section 605(b) of the 1980 act
provides that the head of the agency
may so certify and a regulatory
flexibility analysis is not required. The
certification must include a statement
providing the factual basis for this
determination, and the reasoning should
be clear.
The Small Business Administration
(SBA) recommends 1,500 or fewer
employees as the ‘‘small’’ size standard
that applies to Scheduled Passenger Air
Transportation (NAICS code 481111).
We believe that this size standard also
applies to simulator sponsors, which
include air carriers and simulator
training centers. For part 60, the FAA
identified a total of 11 simulator
sponsors that meet this size standard.
For each of these sponsors, the FAA
attempted to retrieve their annual
revenues and to calculate their
annualized costs. Annual revenue data
was only available for 5 out of the 11
sponsors. After calculating the prorated
annualized costs using the same
assumptions that were used in the cost
section, the FAA then compared
annualized costs with annualized
revenues (see Table 14 for details).
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TABLE 14.—SUMMARY OF RFA DETERMINATION OF ECONOMIC IMPACT
Annual revenues
Number of
employees
Sponsor
1
2
3
4
5
..............................
..............................
..............................
..............................
..............................
973
116
563
134
410
2000
2001
2002
n.a.
$63,902,519
274,420,131
48,765,676
224,249,551
$150,712,673
53,065,814
111,560,208
49,320,778
96,951,552
Annualized
cost of compliance 1
n.a.
$43,396,103
4,350,617
66,015,229
92,035,880
Compliance as percentage of
annual revenues
2000
$1,828
474
474
474
474
2001
n.a.
0.00
0.00
0.00
0.00
2002
0.00
0.00
0.00
0.00
0.00
n.a.
0.00
0.01
0.00
0.00
Significant economic impact?
y/n
2000
2001
n.a.
N
N
N
N
2002
N
N
N
N
N
n.a.
N
N
N
N
Source: U.S. Dept. of Trans., FAA, APO 310.
Notes: 1) Annualized using a capital recovery factor of 0.14238, over 10 years, using a 7 percent rate of interest.
For the 5 sponsors shown in Table 14,
annualized costs of the rule will be
considerably less than one-tenth of one
percent of their annual revenues. The
FAA contends that these costs will not
have a significant economic impact on
these small entities.
Accordingly, pursuant to the
Regulatory Flexibility Act, 5 U.S.C.
605(b), the Federal Aviation
Administration certifies that this rule
will not have a significant economic
impact on a substantial number of small
entities.
International Trade Impact Assessment
The Trade Agreements Act of 1979
prohibits Federal agencies from
engaging in any standards or related
activities that create unnecessary
obstacles to the foreign commerce of the
United States. Legitimate domestic
objectives, such as safety, are not
considered unnecessary obstacles. The
statute also requires consideration of
international standards and where
appropriate, that they be the basis for
U.S. standards.
In accordance with the above statute,
the FAA has assessed the potential
effect of this final rule and has
determined that it will have the same
impact on foreign sponsors as on
domestic sponsors and, therefore,
creates no obstacles to the foreign
commerce of the United States.
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Unfunded Mandates Assessment
The Unfunded Mandates Reform Act
of 1995 (the Act) is intended, among
other things, to curb the practice of
imposing unfunded Federal mandates
on State, local, and tribal governments.
Title II of the Act requires each Federal
agency to prepare a written statement
assessing the effects of any Federal
mandate in a proposed or final agency
rule that may result in an expenditure
of $100 million or more (adjusted
annually for inflation) in any one year
by State, local, and tribal governments,
in the aggregate, or by the private sector;
such a mandate is deemed to be a
‘‘significant regulatory action.’’ The
FAA currently uses an inflation-
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adjusted value of $128.1 million in lieu
of $100 million.
This final rule does not contain an
Unfunded Mandate. The requirements
of Title II do not apply.
14 CFR Part 11
Executive Order 13132, Federalism
Airmen, Aviation safety, Reporting
and recordkeeping requirements.
The FAA has analyzed this final rule
under the principles and criteria of
Executive Order 13132, Federalism. We
determined that this action will not
have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government. Therefore, we
determined that this final rule will not
have federalism implications.
Environmental Analysis
FAA Order 1050.1E identifies FAA
actions that are categorically excluded
from preparation of an environmental
assessment or environmental impact
statement under the National
Environmental Policy Act in the
absence of extraordinary circumstances.
The FAA has determined this
rulemaking action qualifies for the
categorical exclusion identified in
paragraph 312f and involves no
extraordinary circumstances.
Regulations that Significantly Affect
Energy Supply, Distribution, or Use
The FAA has analyzed this final rule
under Executive Order 13211, Actions
Concerning Regulations that
Significantly Affect Energy Supply,
Distribution, or Use (May 18, 2001). We
have determined that it is not a
‘‘significant energy action’’ under the
executive order because it is not a
‘‘significant regulatory action’’ under
Executive Order 12866, and it is not
likely to have a significant adverse effect
on the supply, distribution, or use of
energy.
List of Subjects
14 CFR Part 1
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Air transportation.
Frm 00035
Fmt 4701
Sfmt 4700
Administrative practice and
procedure, Reporting and recordkeeping
requirements.
14 CFR Part 60
14 CFR Part 121
Air carriers, Aircraft, Airmen, Alcohol
abuse, Aviation safety, Charter flights,
Drug abuse, Drug testing, Reporting and
recordkeeping requirements, Safety,
Transportation.
The Amendment
The Federal Aviation Administration
amends Title 14, Chapter I of the Code
of Federal Regulations as follows:
I
PART 1—DEFINITIONS AND
ABBREVIATIONS
1. The authority citation for part 1
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
2. Section 1.1 is amended by adding
new definitions in alphabetical order to
read as follows:
I
§ 1.1
General definitions.
*
*
*
*
*
Flight simulation training device
(FSTD) means a flight simulator or a
flight training device.
*
*
*
*
*
Flight training device (FTD) means a
replica of aircraft instruments,
equipment, panels, and controls in an
open flight deck area or an enclosed
aircraft cockpit replica. It includes the
equipment and computer programs
necessary to represent aircraft (or set of
aircraft) operations in ground and flight
conditions having the full range of
capabilities of the systems installed in
the device as described in part 60 of this
chapter and the qualification
performance standard (QPS) for a
specific FTD qualification level.
*
*
*
*
*
Full flight simulator (FFS) means a
replica of a specific type; or make,
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model, and series aircraft cockpit. It
includes the assemblage of equipment
and computer programs necessary to
represent aircraft operations in ground
and flight conditions, a visual system
providing an out-of-the-cockpit view, a
system that provides cues at least
equivalent to those of a three-degree-offreedom motion system, and has the full
range of capabilities of the systems
installed in the device as described in
part 60 of this chapter and the
qualification performance standards
(QPS) for a specific FFS qualification
level.
*
*
*
*
*
I 3. Section 1.2 is amended by adding
new abbreviations in alphabetical order
to read as follows:
§ 1.2
Abbreviations and symbols.
*
*
*
*
*
FFS means full flight simulator.
*
*
*
*
*
FSTD means flight simulation training
device.
FTD means flight training device.
*
*
*
*
*
PART 11—GENERAL RULEMAKING
PROCEDURES
4. The authority citation for part 11
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40101, 40103,
40105, 40109, 40113, 44110, 44502, 44701–
44702, 44711, and 46102.
5. Amend the table in § 11.201(b) by
adding an entry for part 60 to read as
follows:
I
§ 11.201 Office of Management and Budget
(OMB) control numbers assigned under the
Paperwork Reduction Act.
*
*
*
(b) * * *
*
*
14 CFR part or section identified and described
*
*
*
Part 60 ..................................
*
*
*
Current OMB
control number
*
*
2120–0680
*
6. Part 60 is added to subchapter D to
read as follows:
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PART 60—FLIGHT SIMULATION
TRAINING DEVICE INITIAL AND
CONTINUING QUALIFICATION AND
USE
Applicability.
Applicability of sponsor rules to
persons who are not sponsors and who
are engaged in certain unauthorized
activities.
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Definitions.
Qualification Performance Standards.
Quality management system.
Sponsor qualification requirements.
Additional responsibilities of the
sponsor.
60.11 FSTD use.
60.13 FSTD objective data requirements.
60.14 Special equipment and personnel
requirements for qualification of the
FSTD.
60.15 Initial qualification requirements.
60.16 Additional qualifications for a
currently qualified FSTD.
60.17 Previously qualified FSTDs.
60.19 Inspection, continuing qualification
evaluation, and maintenance
requirements.
60.20 Logging FSTD discrepancies.
60.21 Interim qualification of FSTDs for
new aircraft types or models.
60.23 Modifications to FSTDs.
60.25 Operation with missing,
malfunctioning, or inoperative
components.
60.27 Automatic loss of qualification and
procedures for restoration of
qualification.
60.29 Other losses of qualification and
procedures for restoration of
qualification.
60.31 Recordkeeping and reporting.
60.33 Applications, logbooks, reports, and
records: Fraud, falsification, or incorrect
statements.
60.35 Specific full flight simulator
compliance requirements.
60.37 FSTD qualification on the basis of a
Bilateral Aviation Safety Agreement
(BASA).
Appendix A to Part 60—Qualification
Performance Standards for Airplane Full
Flight Simulators
Appendix B to Part 60—Qualification
Performance Standards for Airplane
Flight Training Devices
Appendix C to Part 60—Qualification
Performance Standards for Helicopter
Full Flight Simulators
Appendix D to Part 60—Qualification
Performance Standards for Helicopter
Flight Training Devices
Appendix E to Part 60—Quality Management
Systems for Flight Simulation Training
Devices
Appendix F to Part 60—Definitions and
Abbreviations for Flight Simulation
Training Devices
Authority: 49 U.S.C. 106(g), 40113, and
44701.
*
I
Sec.
60.1
60.2
60.3
60.4
60.5
60.7
60.9
§ 60.1
Applicability.
(a) This part prescribes the rules
governing the initial and continuing
qualification and use of all aircraft flight
simulation training devices (FSTD) used
for meeting training, evaluation, or
flight experience requirements of this
chapter for flight crewmember
certification or qualification.
(b) The rules of this part apply to each
person using or applying to use an
FSTD to meet any requirement of this
chapter.
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(c) The requirements of § 60.33
regarding falsification of applications,
records, or reports also apply to each
person who uses an FSTD for training,
evaluation, or obtaining flight
experience required for flight
crewmember certification or
qualification under this chapter.
§ 60.2 Applicability of sponsor rules to
persons who are not sponsors and who are
engaged in certain unauthorized activities.
(a) The rules of this part that are
directed to a sponsor of an FSTD also
apply to any person who uses or causes
the use of an FSTD when—
(1) That person knows that the FSTD
does not have an FAA-approved
sponsor; and
(2) The use of the FSTD by that
person is nonetheless claimed for
purposes of meeting any requirement of
this chapter or that person knows or
should have known that the person’s
acts or omissions would cause another
person to mistakenly credit use of the
FSTD for purposes of meeting any
requirement of this chapter.
(b) A situation in which paragraph (a)
of this section would not apply to a
person would be when each of the
following conditions are met:
(1) The person sold or leased the
FSTD and merely represented to the
purchaser or lessee that the FSTD is in
a condition in which it should be able
to obtain FAA approval and
qualification under this part;
(2) The person does not falsely claim
to be the FAA-approved sponsor for the
FSTD;
(3) The person does not falsely make
representations that someone else is the
FAA-approved sponsor of the FSTD at
a time when that other person is not the
FAA-approved sponsor of the FSTD;
and
(4) The person’s acts or omissions do
not cause another person to
detrimentally rely on such acts or
omissions for the mistaken conclusion
that the FSTD is FAA-approved and
qualified under this part at the time the
FSTD is sold or leased.
§ 60.3
Definitions.
In addition to the definitions in part
1 of this chapter, other terms and
definitions applicable to this part are
found in appendix F of this part.
§ 60.4 Qualification Performance
Standards.
The Qualification Performance
Standards (QPS) are published in
appendices to this part as follows:
(a) Appendix A contains the QPS for
Airplane Flight Simulators.
(b) Appendix B contains the QPS for
Airplane Flight Training Devices.
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(c) Appendix C contains the QPS for
Helicopter Flight Simulators.
(d) Appendix D contains the QPS for
Helicopter Flight Training Devices.
(e) Appendix E contains the QPS for
Quality Management Systems for
FSTDs.
(f) Appendix F contains the QPS for
Definitions and Abbreviations for
FSTDs.
§ 60.5
Quality management system.
(a) After October 30, 2009, no sponsor
may use or allow the use of or offer the
use of an FSTD for flight crewmember
training or evaluation or for obtaining
flight experience to meet any
requirement of this chapter unless the
sponsor has established and follows a
quality management system (QMS),
currently approved by the National
Simulator Program Manager (NSPM), for
the continuing surveillance and analysis
of the sponsor’s performance and
effectiveness in providing a satisfactory
FSTD for use on a regular basis as
described in QPS appendix E of this
part.
(b) The QMS program must provide a
process for identifying deficiencies in
the program and for documenting how
the program will be changed to address
these deficiencies.
(c) Whenever the NSPM finds that the
QMS program does not adequately
address the procedures necessary to
meet the requirements of this part, the
sponsor must, after notification by the
NSPM, change the program so the
procedures meet the requirements of
this part. Each such change must be
approved by the NSPM prior to
implementation.
(d) Within 30 days after the sponsor
receives a notice described in paragraph
(c) of this section, the sponsor may file
a petition with the Director of Flight
Standards Service (the Director) for
reconsideration of the NSPM finding.
The sponsor must address its petition to
the Director, Flight Standards Service,
AFS–1, Federal Aviation
Administration, 800 Independence
Ave., SW., Washington, DC 20591. The
filing of such a petition to reconsider
stays the notice pending a decision by
the Director. However, if the Director
finds that there is a situation that
requires immediate action in the interest
of safety in air commerce, he may, upon
a statement of the reasons, require a
change effective without stay.
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§ 60.7
Sponsor qualification requirements.
(a) A person is eligible to apply to be
a sponsor of an FSTD if the following
conditions are met:
(1) The person holds, or is an
applicant for, a certificate under part
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119, 141, or 142 of this chapter; or
holds, or is an applicant for, an
approved flight engineer course in
accordance with part 63 of this chapter.
(2) The FSTD will be used, or will be
offered for use, in the sponsor’s FAAapproved flight training program for the
aircraft being simulated as evidenced in
a request for evaluation submitted to the
NSPM.
(b) A person is a sponsor if the
following conditions are met:
(1) The person is a certificate holder
under part 119, 141, or 142 of this
chapter or has an approved flight
engineer course in accordance with part
63 of this chapter.
(2) The person has—
(i) Operations specifications
authorizing the use of the specific
aircraft or set of aircraft and has an
FAA-approved training program under
which at least one FSTD, simulating the
aircraft or set of aircraft and for which
the person is the sponsor, is used by the
sponsor as described in paragraphs
(b)(5) or (b)(6) of this section; or
(ii) Training specifications or an FAAapproved course of training under
which at least one FSTD, simulating
that aircraft or set of aircraft and for
which the person is the sponsor, is used
by the sponsor as described in
paragraphs (b)(5) or (b)(6) of this
section.
(3) The person has a quality
management system currently approved
by the NSPM in accordance with § 60.5.
(4) The NSPM has accepted the
person as the sponsor of the FSTD and
that acceptance has not been withdrawn
by the FAA.
(5) At least one FSTD (as referenced
in paragraph (b)(2)(i) or (b)(2)(ii) of this
section) that is initially qualified on or
after October 30, 2007, is used within
the sponsor’s FAA-approved flight
training program for the aircraft or set of
aircraft at least once within the 12month period following the initial/
upgrade evaluation, and at least once
within each subsequent 12-month
period thereafter.
(6) At least one FSTD (as referenced
in paragraph (b)(2)(i) or (b)(2)(ii) of this
section) that was qualified before
October 30, 2007, is used within the
sponsor’s FAA-approved flight training
program for the aircraft or set of aircraft
at least once within the 12-month
period following the first continuing
qualification evaluation conducted by
the NSPM after October 30, 2007 and at
least once within each subsequent 12month period thereafter.
(c) If the use requirements of
paragraphs (b)(2) and either (b)(5) or
(b)(6) of this section are not met, the
person will forfeit the right to sponsor
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63427
that FSTD and that person will not be
eligible to apply to sponsor that FSTD
for at least 12 calendar months
following the expiration of the
qualification status.
(d) In addition to the FSTD described
in paragraph (b) of this section, an FSTD
sponsor may sponsor any number of
other FSTDs regardless of specific
aircraft or set of aircraft provided
either—
(1) During the preceding 12-month
period, all of the other FSTDs are used
within the sponsor’s or another
certificate holder’s FAA-approved flight
training program for the aircraft or set of
aircraft simulated; or
(2) The sponsor obtains a written
statement at least annually from a
qualified pilot who has flown the
aircraft or set of aircraft (as appropriate)
during the preceding 12-month period
stating that the subject FSTD’s
performance and handling qualities,
within the normal operating envelope,
represent the aircraft or set of aircraft
described in the FAA Type Certificate
and the type data sheet, if appropriate.
The sponsor must retain the two most
current written statements for review by
the NSPM.
§ 60.9 Additional responsibilities of the
sponsor.
(a) The sponsor must allow the NSPM
upon request to inspect the FSTD as
soon as practicable. This inspection may
include all records and documents
relating to the FSTD, to determine its
compliance with this part.
(b) The sponsor must do the following
for each FSTD:
(1) Establish a mechanism to receive
written comments regarding the FSTD
and its operation in accordance with the
QPS appendix E of this part.
(2) Post in or adjacent to the FSTD the
Statement of Qualification issued by the
NSPM. An electronic copy of the
Statement of Qualification that may be
accessed by an appropriate terminal or
display in or adjacent to the FSTD is
satisfactory.
(c) Each sponsor of an FSTD must
identify to the NSPM by name, one
individual to be the management
representative (MR).
(1) One person may serve as an MR
for more than one FSTD, but one FSTD
must not have more than one person
serving in this capacity.
(2) Each MR must be an employee of
the sponsor with the responsibility and
authority to—
(i) Monitor the on-going qualification
of assigned FSTDs to ensure that all
matters regarding FSTD qualification are
being carried out as provided for in this
part;
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(ii) Ensure that the QMS is properly
established, implemented, and
maintained by overseeing the structure
(and modifying where necessary) of the
QMS policies, practices, and
procedures; and
(iii) Regularly brief sponsor’s
management on the status of the ongoing FSTD qualification program and
the effectiveness and efficiency of the
QMS.
(3) The MR serves as the primary
contact point for all matters between the
sponsor and the NSPM regarding the
qualification of that FSTD as provided
for in this part.
(4) The MR may delegate the duties
described in paragraph (c)(2) and (c)(3)
of this section to an individual at each
of the sponsor’s locations.
§ 60.11
FSTD use.
No person may use or allow the use
of or offer the use of an FSTD for flight
crewmember training or evaluation or
for obtaining flight experience to meet
any of the requirements under this
chapter unless, in accordance with the
QPS for the specific device, the FSTD
meets all of the following:
(a) Has a single sponsor who is
qualified under § 60.7. The sponsor may
arrange with another person for services
of document preparation and
presentation, as well as FSTD
inspection, maintenance, repair, and
servicing; however, the sponsor remains
responsible for ensuring that these
functions are conducted in a manner
and with a result of continually meeting
the requirements of this part.
(b) Is qualified as described in the
Statement of Qualification.
(c) Remains qualified, through
satisfactory inspection, continuing
qualification evaluations, appropriate
maintenance, and use requirements in
accordance with this part and the
applicable QPS.
(d) Functions during day-to-day
training, evaluation, or flight experience
activities with the software and
hardware that was evaluated as
satisfactory by the NSPM and, if
modified, modified only in accordance
with the provisions of this part.
However, this section does not apply to
routine software or hardware changes
that do not fall under the requirements
of § 60.23.
(e) Is operated in accordance with the
provisions and limitations of § 60.25.
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§ 60.13
FSTD objective data requirements.
(a) Except as provided in paragraph
(b) and (c) of this section, for the
purposes of validating FSTD
performance and handling qualities
during evaluation for qualification, the
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data made available to the NSPM (the
validation data package) must include
the aircraft manufacturer’s flight test
data and all relevant data developed
after the type certificate was issued (e.g.,
data developed in response to an
airworthiness directive) if such data
results from a change in performance,
handling qualities, functions, or other
characteristics of the aircraft that must
be considered for flight crewmember
training, evaluation, or for meeting
experience requirements of this chapter.
(b) The validation data package may
contain flight test data from a source in
addition to or independent of the
aircraft manufacturer’s data in support
of an FSTD qualification, but only if this
data is gathered and developed by that
source in accordance with flight test
methods, including a flight test plan, as
described in the applicable QPS.
(c) The validation data package may
also contain predicted data, engineering
simulation data, data from pilot owner
or pilot operating manuals, or data from
public domain sources, provided this
data is acceptable to the NSPM. If found
acceptable the data may then be used in
particular applications for FSTD
qualification.
(d) Data or other material or elements
must be submitted in a form and
manner acceptable to the NSPM.
(e) The NSPM may require additional
objective data, which may include flight
testing if necessary, if the validation
data package does not support FSTD
qualification requirements as described
in this part and the applicable QPS
appendix.
(f) When an FSTD sponsor learns, or
is advised by an aircraft manufacturer or
other data provider, that an addition to,
an amendment to, or a revision of data
that may relate to FSTD performance or
handling characteristics is available, the
sponsor must notify the NSPM as
described in the applicable QPS.
§ 60.14 Special equipment and personnel
requirements for qualification of the FSTD.
When notified by the NSPM, the
sponsor must make available all special
equipment and qualified personnel
needed to accomplish or assist in the
accomplishment of tests during initial
qualification, continuing qualification,
or special evaluations.
§ 60.15
Initial qualification requirements.
(a) For each FSTD, the sponsor must
submit a request to the NSPM to
evaluate the FSTD for initial
qualification at a specific level and
simultaneously request the Training
Program Approval Authority (TPAA)
forward a concurring letter to the
NSPM. The request must be submitted
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in the form and manner described in the
applicable QPS.
(b) The management representative
described in § 60.9(c) must sign a
statement (electronic signature is
acceptable for electronic transmissions)
after confirming the following:
(1) The performance and handling
qualities of the FSTD represent those of
the aircraft or set of aircraft within the
normal operating envelope. This
determination must be made by a
pilot(s) meeting the requirements of
paragraph (d) of this section after having
flown all of the Operations Tasks listed
in the applicable QPS appendix relevant
to the qualification level of the FSTD.
Exceptions, if any, must be noted. The
name of the person(s) making this
determination must be available to the
NSPM upon request.
(2) The FSTD systems and subsystems (including the simulated
aircraft systems) functionally represent
those in the aircraft or set of aircraft.
This determination must be made by the
pilot(s) described in paragraph (b)(1) of
this section, or by a person(s) trained on
simulator systems/sub-systems and
trained on the operation of the
simulated aircraft systems, after having
exercised the operation of the FSTD and
the pertinent functions available
through the Instructor Operating
Station(s). Exceptions, if any, must be
noted. The name of the person(s)
making this determination must be
available to the NSPM upon request.
(3) The cockpit represents the
configuration of the specific type; or
aircraft make, model, and series aircraft
being simulated, as appropriate. This
determination must be made by the
pilot(s) described in paragraph (b)(1) of
this section, or by a person(s) trained on
the configuration and operation of the
aircraft simulated. Exceptions, if any,
must be noted. The name of the
person(s) making this determination
must be available to the NSPM upon
request.
(c) Except for those FSTDs previously
qualified and described in § 60.17, each
FSTD evaluated for initial qualification
must meet the standard that is in effect
at the time of the evaluation. However—
(1) If the FAA publishes a change to
the existing standard or publishes a new
standard for the evaluation for initial
qualification, a sponsor may request that
the NSPM apply the standard that was
in effect when an FSTD was ordered for
delivery if the sponsor—
(i) Within 30 days of the publication
of the change to the existing standard or
publication of the new standard, notifies
the NSPM that an FSTD has been
ordered;
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(ii) Within 90 days of the NSPM
notification described in paragraph
(c)(1)(i) of this section, requests that the
standard in effect at the time the order
was placed be used for the evaluation
for initial qualification; and
(iii) The evaluation is conducted
within 24 months following the
publication of the change to the existing
standard or publication of the new
standard.
(2) This notification must include a
description of the FSTD; the anticipated
qualification level of the FSTD; the
make, model, and series of aircraft
simulated; and any other pertinent
information.
(3) Any tests, tolerances, or other
requirements that are current at the time
of the evaluation may be used during
the initial evaluation, at the request of
the sponsor, if the sponsor provides
acceptable updates to the required
qualification test guide.
(4) The standards used for the
evaluation for initial qualification will
be used for all subsequent evaluations of
the FSTD.
(d) The pilot(s) who contributes to the
confirmation statement required by
paragraph (b) of this section must—
(1) Be designated by the sponsor; and
(2) Be qualified in—
(i) The aircraft or set of aircraft being
simulated; or
(ii) For aircraft not yet issued a type
certificate, or aircraft not previously
operated by the sponsor or not having
previous FAA-approved training
programs conducted by the sponsor, an
aircraft similar in size and
configuration.
(e) The subjective tests that form the
basis for the statements described in
paragraph (b) of this section and the
objective tests referenced in paragraph
(f) of this section must be accomplished
at the sponsor’s training facility, except
as provided for in the applicable QPS.
(f) The person seeking to qualify the
FSTD must provide the NSPM access to
the FSTD for the length of time
necessary for the NSPM to complete the
required evaluation of the FSTD for
initial qualification, which includes the
conduct and evaluation of objective and
subjective tests, including general FSTD
requirements, as described in the
applicable QPS, to determine that the
FSTD meets the standards in that QPS.
(g) When the FSTD passes an
evaluation for initial qualification, the
NSPM issues a Statement of
Qualification that includes all of the
following:
(1) Identification of the sponsor.
(2) Identification of the make, model,
and series of the aircraft or set of aircraft
being simulated.
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(3) Identification of the configuration
of the aircraft or set of aircraft being
simulated (e.g., engine model or models,
flight instruments, or navigation or
other systems).
(4) A statement that the FSTD is
qualified as either a full flight simulator
or a flight training device.
(5) Identification of the qualification
level of the FSTD.
(6) A statement that (with the
exception of the noted exclusions for
which the FSTD has not been
subjectively tested by the sponsor or the
NSPM and for which qualification is not
sought) the qualification of the FSTD
includes the tasks set out in the
applicable QPS appendix relevant to the
qualification level of the FSTD.
(h) After the NSPM completes the
evaluation for initial qualification, the
sponsor must update the Qualification
Test Guide (QTG), with the results of
the FAA-witnessed tests together with
the results of all the objective tests
described in the applicable QPS.
(i) Upon issuance of the Statement of
Qualification the updated QTG becomes
the Master Qualification Test Guide
(MQTG). The MQTG must be made
available to the NSPM upon request.
§ 60.16 Additional qualifications for a
currently qualified FSTD.
(a) A currently qualified FSTD is
required to undergo an additional
qualification process if a user intends to
use the FSTD for meeting training,
evaluation, or flight experience
requirements of this chapter beyond the
qualification issued for that FSTD. This
process consists of the following:
(1) The sponsor:
(i) Must submit to the NSPM all
modifications to the MQTG that are
required to support the additional
qualification.
(ii) Must describe to the NSPM all
modifications to the FSTD that are
required to support the additional
qualification.
(iii) Must submit to the NSPM a
confirmation statement as described in
§ 60.15(c) that a pilot, designated by the
sponsor in accordance with § 60.15(d),
has subjectively evaluated the FSTD in
those areas not previously evaluated.
(2) The FSTD must successfully pass
an evaluation—
(i) Consisting of all the elements of an
initial evaluation for qualification in
those circumstances where the NSPM
has determined that all the elements of
an initial evaluation for qualification is
necessary; or
(ii) Consisting of those elements of an
initial evaluation for qualification
designated as necessary by the NSPM.
(b) In making the determinations
described in paragraph (a)(2) of this
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section, the NSPM considers factors
including the existing qualification of
the FSTD, any modifications to the
FSTD hardware or software that are
involved, and any additions or
modifications to the MQTG.
(c) The FSTD is qualified for the
additional uses when the NSPM issues
an amended Statement of Qualification
in accordance with § 60.15(h).
(d) The sponsor may not modify the
FSTD except as described in § 60.23.
§ 60.17
Previously qualified FSTDs.
(a) Unless otherwise specified by an
FSTD Directive, further referenced in
the applicable QPS, or as specified in
paragraph (e) of this section, an FSTD
qualified before October 30, 2007 will
retain its qualification basis as long as
it continues to meet the standards,
including the objective test results
recorded in the MQTG and subjective
tests, under which it was originally
evaluated, regardless of sponsor. The
sponsor of such an FSTD must comply
with the other applicable provisions of
this part.
(b) For each FSTD qualified before
October 30, 2007, no sponsor may use
or allow the use of or offer the use of
such an FSTD after October 30, 2013 for
flight crewmember training, evaluation
or flight experience to meet any of the
requirements of this chapter, unless that
FSTD has been issued a Statement of
Qualification, including the
Configuration List and the List of
Qualified Tasks in accordance with the
procedures set out in the applicable
QPS.
(c) If the FSTD qualification is lost
under § 60.27 and—
(i) Restored under § 60.27 in less than
(2) years, then the qualification basis (in
terms of objective tests and subjective
tests) for the re-qualification will be
those against which the FSTD was
originally evaluated and qualified.
(ii) Not restored under § 60.27 for two
(2) years or more, then the qualification
basis (in terms of objective tests and
subjective tests) for the re-qualification
will be those standards in effect and
current at the time of re-qualification
application.
(d) Except as provided in paragraph
(e) of this section, any change in FSTD
qualification level initiated on or after
October 30, 2007 requires an evaluation
for initial qualification in accordance
with this part.
(e) A sponsor may request that an
FSTD be permanently downgraded. In
such a case, the NSPM may downgrade
a qualified FSTD without requiring and
without conducting an initial evaluation
for the new qualification level.
Subsequent continuing qualification
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evaluations will use the existing MQTG,
modified as necessary to reflect the new
qualification level.
(f) When the sponsor has appropriate
validation data available and receives
approval from the NSPM, the sponsor
may adopt tests and associated
tolerances described in the current
qualification standards as the tests and
tolerances applicable for the continuing
qualification of a previously qualified
FSTD. The updated test(s) and
tolerance(s) must be made a permanent
part of the MQTG.
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§ 60.19 Inspection, continuing
qualification evaluation, and maintenance
requirements.
(a) Inspection. No sponsor may use or
allow the use of or offer the use of an
FSTD for flight crewmember training,
evaluation, or flight experience to meet
any of the requirements of this chapter
unless the sponsor does the following:
(1) Accomplishes all appropriate
objective tests each year as specified in
the applicable QPS.
(2) Completes a functional preflight
check within the preceding 24 hours.
(b) Continuing qualification
evaluation.
(1) This evaluation consists of
objective tests, and subjective tests,
including general FSTD requirements,
as described in the applicable QPS or as
may be amended by an FSTD Directive.
(2) The sponsor must contact the
NSPM to schedule the FSTD for
continuing qualification evaluations not
later than 60 days before the evaluation
is due.
(3) The sponsor must provide the
NSPM access to the objective test results
in the MQTG and access to the FSTD for
the length of time necessary for the
NSPM to complete the required
continuing qualification evaluations.
(4) The frequency of NSPM-conducted
continuing qualification evaluations for
each FSTD will be established by the
NSPM and specified in the MQTG.
(5) Continuing qualification
evaluations conducted in the calendar
month before or after the calendar
month in which these continuing
qualification evaluations are required
will be considered to have been
conducted in the calendar month in
which they were required.
(6) No sponsor may use or allow the
use of or offer the use of an FSTD for
flight crewmember training or
evaluation or for obtaining flight
experience for the flight crewmember to
meet any requirement of this chapter
unless the FSTD has passed an NSPMconducted continuing qualification
evaluation within the time frame
specified in the MQTG or within the
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grace period as described in paragraph
(b)(5) of this section.
(c) Maintenance. The sponsor is
responsible for continuing corrective
and preventive maintenance on the
FSTD to ensure that it continues to meet
the requirements of this part and the
applicable QPS appendix. No sponsor
may use or allow the use of or offer the
use of an FSTD for flight crewmember
training, evaluation, or flight experience
to meet any of the requirements of this
chapter unless the sponsor does the
following:
(1) Maintains a discrepancy log.
(2) Ensures that, when a discrepancy
is discovered, the following
requirements are met:
(i) A description of each discrepancy
is entered in the log and remains in the
log until the discrepancy is corrected as
specified in § 60.25(b).
(ii) A description of the corrective
action taken for each discrepancy, the
identity of the individual taking the
action, and the date that action is taken
is entered in the log.
(iii) The discrepancy log is kept in a
form and manner acceptable to the
Administrator and is kept in or adjacent
to the FSTD. An electronic log that may
be accessed by an appropriate terminal
or display in or adjacent to the FSTD is
satisfactory.
§ 60.20
Logging FSTD discrepancies.
Each instructor, check airman, or
representative of the Administrator
conducting training, evaluation, or flight
experience, and each person conducting
the preflight inspection who discovers a
discrepancy, including any missing,
malfunctioning, or inoperative
components in the FSTD, must write or
cause to be written a description of that
discrepancy into the discrepancy log at
the end of the FSTD preflight or FSTD
use session.
§ 60.21 Interim qualification of FSTDs for
new aircraft types or models.
(a) A sponsor may apply for and the
NSPM may issue an interim
qualification level for an FSTD for a
new type or model of aircraft, even
though the aircraft manufacturer’s
aircraft data package is preliminary, if
the sponsor provides the following to
the satisfaction of the NSPM—
(1) The aircraft manufacturer’s data,
which consists of at least predicted data,
validated by a limited set of flight test
data;
(2) The aircraft manufacturer’s
description of the prediction
methodology used to develop the
predicted data; and
(3) The QTG test results.
(b) An FSTD that has been issued
interim qualification is deemed to have
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been issued initial qualification unless
the NSPM rescinds the qualification.
Interim qualification terminates two
years after its issuance, unless the
NSPM determines that specific
conditions warrant otherwise.
(c) Within twelve months of the
release of the final aircraft data package
by the aircraft manufacturer, but no later
than two years after the issuance of the
interim qualification status, the sponsor
must apply for initial qualification in
accordance with § 60.15 based on the
final aircraft data package approved by
the aircraft manufacturer, unless the
NSPM determines that specific
conditions warrant otherwise.
(d) An FSTD with interim
qualification may be modified only in
accordance with § 60.23.
§ 60.23
Modifications to FSTDs.
(a) Description of a modification. For
the purposes of this part, an FSTD is
said to have been modified when:
(1) Equipment or devices intended to
simulate aircraft appliances are added to
or removed from FSTD, which change
the Statement of Qualification or the
MQTG; or
(2) Changes are made to either
software or hardware that are intended
to impact flight or ground dynamics;
changes are made that impact
performance or handling characteristics
of the FSTD (including motion, visual,
control loading, or sound systems for
those FSTD levels requiring sound tests
and measurements); or changes are
made to the MQTG.
(b) FSTD Directive. When the FAA
determines that FSTD modification is
necessary for safety of flight reasons, the
sponsor of each affected FSTD must
ensure that the FSTD is modified
according to the FSTD Directive
regardless of the original qualification
standards applicable to any specific
FSTD.
(c) Using the modified FSTD. The
sponsor may not use, or allow the use
of, or offer the use of, the FSTD with the
proposed modification for flight
crewmember training or evaluation or
for obtaining flight experience for the
flight crewmember to meet any
requirement of this chapter unless:
(1) The sponsor has notified the
NSPM and the TPAA of their intent to
incorporate the proposed modification,
and one of the following has occurred;
(i) Twenty-one days have passed since
the sponsor notified the NSPM and the
TPAA of the proposed modification and
the sponsor has not received any
response from either the NSPM or the
TPAA;
(ii) Twenty-one days have passed
since the sponsor notified the NSPM
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and the TPAA of the proposed
modification and one has approved the
proposed modification and the other has
not responded;
(iii) Fewer than twenty-one days have
passed since the sponsor notified the
NSPM and the TPAA of the proposed
modification and the NSPM and TPAA
both approve the proposed
modification;
(iv) The sponsor has successfully
completed any evaluation the NSPM
may require in accordance with the
standards for an evaluation for initial
qualification or any part thereof before
the modified FSTD is placed in service.
(2) The notification is submitted with
the content as, and in a form and
manner as, specified in the applicable
QPS.
(d) User notification. When a
modification is made to an FSTD that
affects the Statement of Qualification,
the sponsor must post an addendum to
the Statement of Qualification until
such time as a permanent, updated
statement is posted.
(e) MQTG update. The MQTG must be
updated with current objective test
results in accordance with § 60.15(h)
and (i) and appropriate objective data in
accordance with § 60.13, each time an
FSTD is modified and an objective test
or other MQTG section is affected by the
modification. If an FSTD Directive is the
cause of this update, the direction to
make the modification and the record of
the modification completion must be
filed in the MQTG.
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§ 60.25 Operation with missing,
malfunctioning, or inoperative components.
(a) No person may knowingly use or
allow the use of or misrepresent the
capability of an FSTD for any maneuver,
procedure, or task that is to be
accomplished to meet training,
evaluation, or flight experience
requirements of this chapter for flight
crewmember certification or
qualification when there is a missing,
malfunctioning, or inoperative (MMI)
component that is required to be present
and correctly operate for the satisfactory
completion of that maneuver,
procedure, or task.
(b) Each MMI component as described
in paragraph (a) of this section, or any
MMI component installed and required
to operate correctly to meet the current
Statement of Qualification, must be
repaired or replaced within 30 calendar
days, unless otherwise required or
authorized by the NSPM.
(c) A list of the current MMI
components must be readily available in
or adjacent to the FSTD for review by
users of the device. Electronic access to
this list via an appropriate terminal or
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display in or adjacent to the FSTD is
satisfactory. The discrepancy log may be
used to satisfy this requirement
provided each currently MMI
component is listed in the discrepancy
log.
§ 60.27 Automatic loss of qualification and
procedures for restoration of qualification.
(a) An FSTD qualification is
automatically lost when any of the
following occurs:
(1) The FSTD is not used in the
sponsor’s FAA-approved flight training
program in accordance with § 60.7(b)(5)
or (b)(6) and the sponsor does not obtain
and maintain the written statement as
described in § 60.7(d)(2).
(2) The FSTD is not inspected in
accordance with § 60.19.
(3) The FSTD is physically moved
from one location and installed in a
different location, regardless of distance.
(4) The MQTG is missing or otherwise
not available and a replacement is not
made within 30 days.
(b) If FSTD qualification is lost under
paragraph (a) of this section,
qualification is restored when either of
the following provisions is met:
(1) The FSTD successfully passes an
evaluation:
(i) For initial qualification, in
accordance with §§ 60.15 and 60.17(c)
in those circumstances where the NSPM
has determined that a full evaluation for
initial qualification is necessary; or
(ii) For those elements of an
evaluation for initial qualification, in
accordance with §§ 60.15 and 60.17(c),
as determined to be necessary by the
NSPM.
(2) The NSPM advises the sponsor
that an evaluation is not necessary.
(c) In making the determinations
described in paragraph (b) of this
section, the NSPM considers factors
including the number of continuing
qualification evaluations missed, the
number of sponsor-conducted quarterly
inspections missed, and the care that
had been taken of the device since the
last evaluation.
§ 60.29 Other losses of qualification and
procedures for restoration of qualification.
(a) Except as provided in paragraph
(c) of this section, when the NSPM
determines that the FSTD no longer
meets qualification standards, the
following procedure applies:
(1) The NSPM notifies the sponsor in
writing that the FSTD no longer meets
some or all of its qualification
standards.
(2) The NSPM sets a reasonable
period (but not less than 7 days) within
which the sponsor may submit written
information, views, and arguments on
the FSTD qualification.
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(3) After considering all material
presented, the NSPM notifies the
sponsor about the determination with
regard to the qualification of the FSTD.
(4) When the NSPM notifies the
sponsor that some or all of the FSTD is
no longer qualified, the action described
in the notification becomes effective not
less than 30 days after the sponsor
receives that notice unless—
(i) The NSPM finds under paragraph
(c) of this section that there is an
emergency requiring immediate action
with respect to safety in air commerce;
or
(ii) The sponsor petitions the Director
of Flight Standards Service for
reconsideration of the NSPM finding
under paragraph (b) of this section.
(b) When a sponsor seeks
reconsideration of a decision from the
NSPM concerning the FSTD
qualification, the following procedure
applies:
(1) The sponsor must petition for
reconsideration of that decision within
30 days of the date that the sponsor
receives a notice that some or all of the
FSTD is no longer qualified.
(2) The sponsor must address its
petition to the Director, Flight Standards
Service, AFS–1, Federal Aviation
Administration, 800 Independence
Ave., SW., Washington, DC 20591.
(3) A petition for reconsideration, if
filed within the 30-day period, suspends
the effectiveness of the determination by
the NSPM that the FSTD is no longer
qualified unless the NSPM has found,
under paragraph (c) of this section, that
an emergency exists requiring
immediate action with respect to safety
in air commerce.
(c) If the NSPM find that an
emergency exists requiring immediate
action with respect to safety in air
commerce that makes the procedures set
out in this section impracticable or
contrary to the public interest:
(1) The NSPM withdraws
qualification of some or all of the FSTD
and makes the withdrawal of
qualification effective on the day the
sponsor receives notice of it.
(2) In the notice to the sponsor, the
NSPM articulates the reasons for its
finding that an emergency exists
requiring immediate action with respect
to safety in air transportation or air
commerce or that makes it impracticable
or contrary to the public interest to stay
the effectiveness of the finding.
(d) FSTD qualification lost under
paragraph (a) or (c) of this section may
be restored when either of the following
provisions are met:
(1) The FSTD successfully passes an
evaluation for initial qualification, in
accordance with §§ 60.15 and 60.17(c)
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in those circumstances where the NSPM
has determined that a full evaluation for
initial qualification is necessary; or
(2) The FSTD successfully passes an
evaluation for those elements of an
initial qualification evaluation, in
accordance with §§ 60.15 and 60.17(c),
as determined to be necessary by the
NSPM.
(e) In making the determinations
described in paragraph (d) of this
section, the NSPM considers factors
including the reason for the loss of
qualification, any repairs or
replacements that may have to have
been completed, the number of
continuing qualification evaluations
missed, the number of sponsorconducted quarterly inspections missed,
and the care that had been taken of the
device since the loss of qualification.
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§ 60.31
Recordkeeping and reporting.
(a) The FSTD sponsor must maintain
the following records for each FSTD it
sponsors:
(1) The MQTG and each amendment
thereto.
(2) A record of all FSTD modifications
affected under § 60.23 since the
issuance of the original Statement of
Qualification.
(3) A copy of all of the following:
(i) Results of the qualification
evaluations (initial and each upgrade)
since the issuance of the original
Statement of Qualification.
(ii) Results of the objective tests
conducted in accordance with § 60.19(a)
for a period of 2 years.
(iii) Results of the previous three
continuing qualification evaluations, or
the continuing qualification evaluations
from the previous 2 years, whichever
covers a longer period.
(iv) Comments obtained in accordance
with § 60.9(b) for a period of at least 90
days.
(4) A record of all discrepancies
entered in the discrepancy log over the
previous 2 years, including the
following:
(i) A list of the components or
equipment that were or are missing,
malfunctioning, or inoperative.
(ii) The action taken to correct the
discrepancy.
(iii) The date the corrective action was
taken.
(iv) The identity of the person
determining that the discrepancy has
been corrected.
(b) The records specified in this
section must be maintained in plain
language form or in coded form if the
coded form provides for the
preservation and retrieval of
information in a manner acceptable to
the NSPM.
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§ 60.33 Applications, logbooks, reports,
and records: Fraud, falsification, or
incorrect statements.
§ 60.37 FSTD qualification on the basis of
a Bilateral Aviation Safety Agreement
(BASA).
(a) No person may make, or cause to
be made, any of the following:
(1) A fraudulent or intentionally false
statement in any application or any
amendment thereto, or any other report
or test result required by this part.
(2) A fraudulent or intentionally false
statement in or a known omission from
any record or report that is kept, made,
or used to show compliance with this
part, or to exercise any privileges under
this chapter.
(3) Any reproduction or alteration, for
fraudulent purpose, of any report,
record, or test result required under this
part.
(b) The commission by any person of
any act prohibited under paragraph (a)
of this section is a basis for any one or
any combination of the following:
(1) A civil penalty.
(2) Suspension or revocation of any
certificate held by that person that was
issued under this chapter.
(3) The removal of FSTD qualification
and approval for use in a training
program.
(c) The following may serve as a basis
for removal of qualification of an FSTD
including the withdrawal of approval
for use of an FSTD; or denying an
application for a qualification:
(1) An incorrect statement, upon
which the FAA relied or could have
relied, made in support of an
application for a qualification or a
request for approval for use.
(2) An incorrect entry, upon which
the FAA relied or could have relied,
made in any logbook, record, or report
that is kept, made, or used to show
compliance with any requirement for an
FSTD qualification or an approval for
use.
(a) The evaluation and qualification of
an FSTD by a contracting State to the
Convention on International Civil
Aviation for the sponsor of an FSTD
located in that contracting State may be
used as the basis for issuing a U.S.
statement of qualification (see
applicable QPS, attachment 4, figure 4)
by the NSPM to the sponsor of that
FSTD in accordance with—
(1) A BASA between the United States
and the Contracting State that issued the
original qualification; and
(2) A Simulator Implementation
Procedure (SIP) established under the
BASA.
(b) The SIP must contain any
conditions and limitations on validation
and issuance of such qualification by
the U.S.
§ 60.35 Specific full flight simulator
compliance requirements.
(a) No device will be eligible for
initial or upgrade qualification to a FFS
at Level C or Level D under this part
unless it includes the equipment and
appliances installed and operating to
the extent necessary for the issuance of
an airman certificate or rating.
(b) No device will be eligible for
initial or upgrade qualification to a FFS
at Level A or Level B under this part
unless it includes the equipment and
appliances installed and operating to
the extent necessary for the training,
testing, and/or checking that comprise
the simulation portion of the
requirements for issuance of an airman
certificate or rating.
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Appendix A to Part 60—Qualification
Performance Standards for Airplane
Full Flight Simulators
lllllllllllllllllllll
Begin Information
This appendix establishes the standards for
Airplane Full Flight Simulator (FFS)
evaluation and qualification. The Flight
Standards Service, National Simulator
Program Manager (NSPM), is responsible for
the development, application, and
implementation of the standards contained
within this appendix. The procedures and
criteria specified in this appendix will be
used by the NSPM, or a person assigned by
the NSPM, when conducting airplane FFS
evaluations.
Table of Contents
1. Introduction.
2. Applicability (§§ 60.1 and 60.2).
3. Definitions (§ 60.3).
4. Qualification Performance Standards
(§ 60.4).
5. Quality Management System (§ 60.5).
6. Sponsor Qualification Requirements
(§ 60.7).
7. Additional Responsibilities of the
Sponsor (§ 60.9).
8. Simulator Use (§ 60.11).
9. Simulator Objective Data Requirements
(§ 60.13).
10. Special Equipment and Personnel
Requirements for Qualification of the
Simulator (§ 60.14).
11. Initial (and Upgrade) Qualification
Requirements (§ 60.15).
12. Additional Qualifications for a
Currently Qualified Simulator (§ 60.16).
13. Previously Qualified Simulators
(§ 60.17).
14. Inspection, Continuing Qualification
Evaluation, and Maintenance Requirements
(§ 60.19).
15. Logging Simulator Discrepancies
(§ 60.20).
16. Interim Qualification of Simulators for
New Airplane Types or Models (§ 60.21).
17. Modifications to Simulators (§ 60.23).
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18. Operations with Missing,
Malfunctioning, or Inoperative Components
(§ 60.25).
19. Automatic Loss of Qualification and
Procedures for Restoration of Qualification
(§ 60.27).
20. Other Losses of Qualification and
Procedures for Restoration of Qualification
(§ 60.29).
21. Record keeping and Reporting (§ 60.31).
22. Applications, Logbooks, Reports, and
Records: Fraud, Falsification, or Incorrect
Statements (§ 60.33).
23. Specific Full Flight Simulator
Compliance Requirements (§ 60.35).
24. [Reserved]
25. FSTD Qualification on the Basis of a
Bilateral Aviation Safety Agreement (BASA)
(§ 60.37).
Attachment 1 to Appendix A to Part 60—
General Simulator Requirements.
Attachment 2 to Appendix A to Part 60—
Full Flight Simulator (FFS) Objective Test.
Attachment 3 to Appendix A to Part 60—
Simulator Subjective Evaluation.
Attachment 4 to Appendix A to Part 60—
Sample Documents.
Attachment 5 to Appendix A to Part 60—
Simulator Qualification Requirements for
Windshear Training Program Use.
End Information
lllllllllllllllllllll
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1. Introduction
lllllllllllllllllllll
Begin Information
a. This appendix contains background
information as well as regulatory and
informative material as described later in this
section. To assist the reader in determining
what areas are required and what areas are
permissive, the text in this appendix is
divided into two sections: ‘‘QPS
Requirements’’ and ‘‘Information.’’ The QPS
Requirements sections contain details
regarding compliance with the part 60 rule
language. These details are regulatory, but are
found only in this appendix. The Information
sections contain material that is advisory in
nature, and designed to give the user general
information about the regulation.
b. Related Reading References.
(1) 14 CFR part 60.
(2) 14 CFR part 61.
(3) 14 CFR part 63.
(4) 14 CFR part 119.
(5) 14 CFR part 121.
(6) 14 CFR part 125.
(7) 14 CFR part 135.
(8) 14 CFR part 141.
(9) 14 CFR part 142.
(10) Advisory Circular (AC) 120–28C,
Criteria for Approval of Category III Landing
Weather Minima.
(11) AC 120–29, Criteria for Approving
Category I and Category II Landing Minima
for part 121 operators.
(12) AC 120–35B, Line Operational
Simulations: Line-Oriented Flight Training,
Special Purpose Operational Training, Line
Operational Evaluation.
(13) AC 120–41, Criteria for Operational
Approval of Airborne Wind Shear Alerting
and Flight Guidance Systems.
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(14) AC 120–57A, Surface Movement
Guidance and Control System (SMGS).
(15) AC 150/5300–13, Airport Design.
(16) AC 150/5340–1G, Standards for
Airport Markings.
(17) AC 150/5340–4C, Installation Details
for Runway Centerline Touchdown Zone
Lighting Systems.
(18) AC 150/5340–19, Taxiway Centerline
Lighting System.
(19) AC 150/5340–24, Runway and
Taxiway Edge Lighting System.
(20) AC 150/5345–28D, Precision
Approach Path Indicator (PAPI) Systems
(21) International Air Transport
Association document, ‘‘Flight Simulator
Design and Performance Data Requirements,’’
as amended.
(22) AC 25–7, as amended, Flight Test
Guide for Certification of Transport Category
Airplanes.
(23) AC 23–8A, as amended, Flight Test
Guide for Certification of Part 23 Airplanes.
(24) International Civil Aviation
Organization (ICAO) Manual of Criteria for
the Qualification of Flight Simulators, as
amended.
(25) Airplane Flight Simulator Evaluation
Handbook, Volume I, as amended and
Volume II, as amended, The Royal
Aeronautical Society, London, UK.
(26) FAA Publication FAA–S–8081 series
(Practical Test Standards for Airline
Transport Pilot Certificate, Type Ratings,
Commercial Pilot, and Instrument Ratings).
(27) The FAA Aeronautical Information
Manual (AIM). An electronic version of the
AIM is on the internet at https://www.faa.gov/
atpubs.
End Information
lllllllllllllllllllll
2. Applicability (§§ 60.1 & 60.2)
lllllllllllllllllllll
Begin Information
There is no additional regulatory or
informational material that applies to § 60.1,
Applicability, or to § 60.2, Applicability of
sponsor rules to persons who are not
sponsors and who are engaged in certain
unauthorized activities.
End Information
lllllllllllllllllllll
3. Definitions (§ 60.3)
lllllllllllllllllllll
Begin Information
See appendix F for a list of definitions and
abbreviations from part 1 and part 60,
including the appropriate appendices of part
60.
End Information
lllllllllllllllllllll
4. Qualification Performance Standards
(§ 60.4)
lllllllllllllllllllll
Begin Information
There is no additional regulatory or
informational material that applies to § 60.4,
Qualification Performance Standards.
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63433
End Information
lllllllllllllllllllll
5. Quality Management System (§ 60.5)
lllllllllllllllllllll
Begin Information
See appendix E for additional regulatory
and informational material regarding Quality
Management Systems.
End Information
lllllllllllllllllllll
6. Sponsor Qualification Requirements
(§ 60.7)
lllllllllllllllllllll
Begin Information
a. The intent of the language in § 60.7(b) is
to have a specific FFS, identified by the
sponsor, used at least once in an FAAapproved flight training program for the
airplane simulated during the 12-month
period described. The identification of the
specific FFS may change from one 12-month
period to the next 12-month period as long
as that sponsor sponsors and uses at least one
FFS at least once during the prescribed
period. There is no minimum number of
hours or minimum FFS periods required.
b. The following examples describe
acceptable operational practices:
(1) Example One.
(a) A sponsor is sponsoring a single,
specific FFS for its own use, in its own
facility or elsewhere—this single FFS forms
the basis for the sponsorship. The sponsor
uses that FFS at least once in each 12-month
period in that sponsor’s FAA-approved flight
training program for the airplane simulated.
This 12-month period is established
according to the following schedule:
(i) If the FFS was qualified prior to October
30, 2007 the 12-month period begins on the
date of the first continuing qualification
evaluation conducted in accordance with
§ 60.19 after October 30, 2007 and continues
for each subsequent 12-month period;
(ii) A device qualified on or after October
30, 2007 will be required to undergo an
initial or upgrade evaluation in accordance
with § 60.15. Once the initial or upgrade
evaluation is complete, the first continuing
qualification evaluation will be conducted
within 6 months. The 12 month continuing
qualification evaluation cycle begins on that
date and continues for each subsequent 12month period.
(b) There is no minimum number of hours
of FFS use required.
(c) The identification of the specific FFS
may change from one 12-month period to the
next 12-month period as long as that sponsor
sponsors and uses at least one FFS at least
once during the prescribed period.
(2) Example Two.
(a) A sponsor sponsors an additional
number of FFSs, in its facility or elsewhere.
Each additionally sponsored FFS must be—
(i) Used by the sponsor in the sponsor’s
FAA-approved flight training program for the
airplane simulated (as described in
§ 60.7(d)(1));
OR
(ii) Used by another FAA certificate holder
in that other certificate holder’s FAA-
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approved flight training program for the
airplane simulated (as described in
§ 60.7(d)(1)). This 12-month period is
established in the same manner as in
example one.
OR
(iii) Provided a statement each year from a
qualified pilot, (after having flown the
airplane, not the subject FFS or another FFS,
during the preceding 12-month period)
stating that the subject FFSs performance and
handling qualities represent the airplane (as
described in § 60.7(d)(2)). This statement is
provided at least once in each 12-month
period established in the same manner as in
example one.
(b) There is no minimum number of hours
of FFS use required.
(3) Example Three.
(a) A sponsor in New York (in this
example, a Part 142 certificate holder)
establishes ‘‘satellite’’ training centers in
Chicago and Moscow.
(b) The satellite function means that the
Chicago and Moscow centers must operate
under the New York center’s certificate (in
accordance with all of the New York center’s
practices, procedures, and policies; e.g.,
instructor and/or technician training/
checking requirements, record keeping, QMS
program).
(c) All of the FFSs in the Chicago and
Moscow centers could be dry-leased (i.e., the
certificate holder does not have and use
FAA-approved flight training programs for
the FFSs in the Chicago and Moscow centers)
because—
(i) Each FFS in the Chicago center and each
FFS in the Moscow center is used at least
once each 12-month period by another FAA
certificate holder in that other certificate
holder’s FAA-approved flight training
program for the airplane (as described in
§ 60.7(d)(1));
OR
(ii) A statement is obtained from a
qualified pilot (having flown the airplane,
not the subject FFS or another FFS during the
preceding 12-month period) stating that the
performance and handling qualities of each
FFS in the Chicago and Moscow centers
represents the airplane (as described in
§ 60.7(d)(2)).
End Information
lllllllllllllllllllll
7. Additional Responsibilities of the Sponsor
(§ 60.9)
lllllllllllllllllllll
Begin Information
The phrase ‘‘as soon as practicable’’ in
§ 60.9(a) means without unnecessarily
disrupting or delaying beyond a reasonable
time the training, evaluation, or experience
being conducted in the FSTD.
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End Information
lllllllllllllllllllll
8. Simulator Use (§ 60.11)
lllllllllllllllllllll
Begin Information
There is no additional regulatory or
informational material that applies to § 60.11,
Simulator Use.
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End Information
lllllllllllllllllllll
End QPS Requirements
lllllllllllllllllllll
9. Simulator Objective Data Requirements
(§ 60.13)
lllllllllllllllllllll
Begin Information
e. The FFS sponsor is encouraged to
maintain a liaison with the manufacturer of
the aircraft being simulated (or with the
holder of the aircraft type certificate for the
aircraft being simulated if the manufacturer
is no longer in business), and, if appropriate,
with the person having supplied the aircraft
data package for the FFS in order to facilitate
the notification required by § 60.13(f).
f. It is the intent of the NSPM that for new
aircraft entering service, at a point well in
advance of preparation of the Qualification
Test Guide (QTG), the sponsor should submit
to the NSPM for approval, a descriptive
document (a validation data roadmap)
containing the plan for acquiring the
validation data, including data sources. This
document should clearly identify sources of
data for all required tests, a description of the
validity of these data for a specific engine
type and thrust rating configuration, and the
revision levels of all avionics affecting the
performance or flying qualities of the aircraft.
Additionally, this document should provide
other information, such as the rationale or
explanation for cases where data or data
parameters are missing, instances where
engineering simulation data are used or
where flight test methods require further
explanations. It should also provide a brief
narrative describing the cause and effect of
any deviation from data requirements. The
aircraft manufacturer may provide this
document.
g. There is no requirement for any flight
test data supplier to submit a flight test plan
or program prior to gathering flight test data.
However, the NSPM notes that inexperienced
data gatherers often provide data that is
irrelevant, improperly marked, or lacking
adequate justification for selection. Other
problems include inadequate information
regarding initial conditions or test
maneuvers. The NSPM has been forced to
refuse these data submissions as validation
data for an FFS evaluation. It is for this
reason that the NSPM recommends that any
data supplier not previously experienced in
this area review the data necessary for
programming and for validating the
performance of the FFS, and discuss the
flight test plan anticipated for acquiring such
data with the NSPM well in advance of
commencing the flight tests.
h. In those cases where the objective test
results authorize a ‘‘snapshot test’’ or a
‘‘series of snapshot test’’ results in lieu of a
time-history result, Attachment 2 requires the
sponsor or other data provider to ensure that
a steady state condition exists at the instant
of time captured by the ‘‘snapshot.’’ This is
often verified by showing that a steady state
condition existed from some period of time
during which the snap shot is taken. The
time period most frequently used is 5
seconds prior through 2 seconds following
the instant of time captured by the snap shot.
This paragraph is primarily addressing the
source data and the method by which the
data provider ensures that the steady state
condition for the snap shot is representative.
i. The NSPM will consider, on a case-bycase basis, whether or not to approve
Begin QPS Requirements
a. Flight test data used to validate FFS
performance and handling qualities must
have been gathered in accordance with a
flight test program containing the following:
(1) A flight test plan consisting of:
(a) The maneuvers and procedures
required for aircraft certification and
simulation programming and validation
(b) For each maneuver or procedure—
(i) The procedures and control input the
flight test pilot and/or engineer used.
(ii) The atmospheric and environmental
conditions.
(iii) The initial flight conditions.
(iv) The airplane configuration, including
weight and center of gravity.
(v) The data to be gathered.
(vi) All other information necessary to
recreate the flight test conditions in the FFS.
(2) Appropriately qualified flight test
personnel.
(3) An understanding of the accuracy of the
data to be gathered using appropriate
alternative data sources, procedures, and
instrumentation that is traceable to a
recognized standard as described in
Attachment 2, Table A2D.
(4) Appropriate and sufficient data
acquisition equipment or system(s),
including appropriate data reduction and
analysis methods and techniques, as would
be acceptable to the FAA’s Aircraft
Certification Service.
b. The data, regardless of source, must be
presented:
(1) In a format that supports the FFS
validation process;
(2) In a manner that is clearly readable and
annotated correctly and completely;
(3) With resolution sufficient to determine
compliance with the tolerances set forth in
Attachment 2, Table A2A of this appendix.
(4) With any necessary instructions or
other details provided, such as yaw damper
or throttle position; and
(5) Without alteration, adjustments, or bias;
however the data may be re-scaled, digitized,
or otherwise manipulated to fit the desired
presentation.
c. After completion of any additional flight
test, a flight test report must be submitted in
support of the validation data. The report
must contain sufficient data and rationale to
support qualification of the FFS at the level
requested.
d. As required by § 60.13(f), the sponsor
must notify the NSPM when it becomes
aware that an addition to, an amendment to,
or a revision of data that may relate to FFS
performance or handling characteristics is
available. The data referred to in this
paragraph are those data that are used to
validate the performance, handling qualities,
or other characteristics of the aircraft,
including data related to any relevant
changes occurring after the type certificate
was issued. This notification must be made
within 10 working days.
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supplemental validation data derived from
flight data recording systems such as a Quick
Access Recorder or Flight Data Recorder.
End Information
lllllllllllllllllllll
10. Special Equipment and Personnel
Requirements for Qualification of the
Simulator (§ 60.14)
lllllllllllllllllllll
Begin Information
a. In the event that the NSPM determines
that special equipment or specifically
qualified persons will be required to conduct
an evaluation, the NSPM will make every
attempt to notify the sponsor at least one (1)
week, but in no case less than 72 hours, in
advance of the evaluation. Examples of
special equipment include spot photometers,
flight control measurement devices, and
sound analyzers. Examples of specially
qualified personnel include individuals
specifically qualified to install or use any
special equipment when its use is required.
b. Examples of a special evaluation include
an evaluation conducted after an FFS is
moved, at the request of the TPAA, or as a
result of comments received from FFS that
raise questions regarding the continued
qualification or use of the FFS.
End Information
lllllllllllllllllllll
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11. Initial (and Upgrade) Qualification
Requirements (§ 60.15)
lllllllllllllllllllll
Begin QPS Requirements
a. In order to be qualified at a particular
qualification level, the FFS must:
(1) Meet the general requirements listed in
Attachment 1;
(2) Meet the objective testing requirements
listed in Attachment 2; and
(3) Satisfactorily accomplish the subjective
tests listed in Attachment 3.
b. The request described in § 60.15(a) must
include all of the following:
(1) A statement that the FFS meets all of
the applicable provisions of this part and all
applicable provisions of the QPS.
(2) A confirmation that the sponsor will
forward to the NSPM the statement described
in § 60.15(b) in such time as to be received
no later than 5 business days prior to the
scheduled evaluation and may be forwarded
to the NSPM via traditional or electronic
means.
(3) A qualification test guide (QTG),
acceptable to the NSPM, that includes all of
the following:
(i) Objective data obtained from aircraft
testing or another approved source.
(ii) Correlating objective test results
obtained from the performance of the FFS as
prescribed in the applicable QPS.
(iii) The result of FFS subjective tests
prescribed in the applicable QPS.
(iv) A description of the equipment
necessary to perform the evaluation for initial
qualification and the continuing qualification
evaluations.
c. The QTG described in paragraph (a)(3)
of this section, must provide the documented
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proof of compliance with the simulator
objective tests in Attachment 2, Table A2A of
this appendix.
d. The QTG is prepared and submitted by
the sponsor, or the sponsor’s agent on behalf
of the sponsor, to the NSPM for review and
approval, and must include, for each
objective test:
(1) Parameters, tolerances, and flight
conditions;
(2) Pertinent and complete instructions for
the conduct of automatic and manual tests;
(3) A means of comparing the FFS test
results to the objective data;
(4) Any other information as necessary, to
assist in the evaluation of the test results;
(5) Other information appropriate to the
qualification level of the FFS.
e. The QTG described in paragraphs (a)(3)
and (b) of this section, must include the
following:
(1) A QTG cover page with sponsor and
FAA approval signature blocks (see
Attachment 4, Figure A4C, for a sample QTG
cover page).
(2) A continuing qualification evaluation
requirements page. This page will be used by
the NSPM to establish and record the
frequency with which continuing
qualification evaluations must be conducted
and any subsequent changes that may be
determined by the NSPM in accordance with
§ 60.19. See Attachment 4, Figure A4G, for a
sample Continuing Qualification Evaluation
Requirements page.
(3) A FFS information page that provides
the information listed in this paragraph (see
Attachment 4, Figure A4B, for a sample FFS
information page). For convertible FFSs, the
sponsor must submit a separate page for each
configuration of the FFS.
(a) The sponsor’s FFS identification
number or code.
(b) The airplane model and series being
simulated.
(c) The aerodynamic data revision number
or reference.
(d) The engine model(s) and its data
revision number or reference.
(e) The flight control data revision number
or reference.
(f) The flight management system
identification and revision level.
(g) The FFS model and manufacturer.
(h) The date of FFS manufacture.
(i) The FFS computer identification.
(j) The visual system model and
manufacturer, including display type.
(k) The motion system type and
manufacturer, including degrees of freedom.
(4) A Table of Contents.
(5) A log of revisions and a list of effective
pages.
(6) List of all relevant data references.
(7) A glossary of terms and symbols used
(including sign conventions and units).
(8) Statements of compliance and
capability (SOCs) with certain requirements.
SOCs must provide references to the sources
of information that show the capability of the
FFS to comply with the requirements. SOCs
must also provide a rationale explaining how
the referenced material is used, the
mathematical equations and parameter
values used, and the conclusions reached.
Refer to the ‘‘Additional Details’’ column in
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63435
Attachment 1, Table A1A, ‘‘Simulator
Standards,’’ or in the ‘‘Test Details’’ column
in Attachment 2, Table A2A, ‘‘Simulator
Objective Tests,’’ to see when SOCs are
required.
(9) Recording procedures or equipment
required to accomplish the objective tests.
(10) The following information for each
objective test designated in Attachment 2,
Table A2A, as applicable to the qualification
level sought:
(a) Name of the test.
(b) Objective of the test.
(c) Initial conditions.
(d) Manual test procedures.
(e) Automatic test procedures (if
applicable).
(f) Method for evaluating FFS objective test
results.
(g) List of all relevant parameters driven or
constrained during the automatically
conducted test(s).
(h) List of all relevant parameters driven or
constrained during the manually conducted
test(s).
(i) Tolerances for relevant parameters.
(j) Source of Validation Data (document
and page number).
(k) Copy of the Validation Data (if located
in a separate binder, a cross reference for the
identification and page number for pertinent
data location must be provided).
(l) Simulator Objective Test Results as
obtained by the sponsor. Each test result
must reflect the date completed and must be
clearly labeled as a product of the device
being tested.
f. A convertible FFS is addressed as a
separate FFS for each model and series
airplane to which it will be converted and for
the FAA qualification level sought. If a
sponsor seeks qualification for two or more
models of an airplane type using a
convertible FFS, the sponsor must submit a
QTG for each airplane model, or a
supplemented QTG for each airplane model.
The NSPM will conduct evaluations for each
airplane model.
g. Form and manner of presentation of
objective test results in the QTG:
(1) The sponsor’s FFS test results must be
recorded in a manner acceptable to the
NSPM, that allows easy comparison of the
FFS test results to the validation data (e.g.,
use of a multi-channel recorder, line printer,
cross plotting, overlays, transparencies).
(2) FFS results must be labeled using
terminology common to airplane parameters
as opposed to computer software
identifications.
(3) Validation data documents included in
a QTG may be photographically reduced only
if such reduction will not alter the graphic
scaling or cause difficulties in scale
interpretation or resolution.
(4) Scaling on graphical presentations must
provide the resolution necessary to evaluate
the parameters shown in Attachment 2, Table
A2A of this appendix.
(5) Tests involving time histories, data
sheets (or transparencies thereof) and FFS
test results must be clearly marked with
appropriate reference points to ensure an
accurate comparison between the FFS and
the airplane with respect to time. Time
histories recorded via a line printer are to be
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clearly identified for cross plotting on the
airplane data. Over-plots must not obscure
the reference data.
h. The sponsor may elect to complete the
QTG objective and subjective tests at the
manufacturer’s facility or at the sponsor’s
training facility. If the tests are conducted at
the manufacturer’s facility, the sponsor must
repeat at least one-third of the tests at the
sponsor’s training facility in order to
substantiate FFS performance. The QTG must
be clearly annotated to indicate when and
where each test was accomplished. Tests
conducted at the manufacturer’s facility and
at the sponsor’s training facility must be
conducted after the FFS is assembled with
systems and sub-systems functional and
operating in an interactive manner. The test
results must be submitted to the NSPM.
i. The sponsor must maintain a copy of the
MQTG at the FFS location.
j. All FFSs for which the initial
qualification is conducted after October 30,
2013 must have an electronic MQTG
(eMQTG) including all objective data
obtained from airplane testing, or another
approved source (reformatted or digitized),
together with correlating objective test results
obtained from the performance of the FFS
(reformatted or digitized) as prescribed in
this appendix. The eMQTG must also contain
the general FFS performance or
demonstration results (reformatted or
digitized) prescribed in this appendix, and a
description of the equipment necessary to
perform the initial qualification evaluation
and the continuing qualification evaluations.
The eMQTG must include the original
validation data used to validate FFS
performance and handling qualities in either
the original digitized format from the data
supplier or an electronic scan of the original
time-history plots that were provided by the
data supplier. A copy of the eMQTG must be
provided to the NSPM.
k. All other FFSs not covered in
subparagraph ‘‘j’’ must have an electronic
copy of the MQTG by October 30, 2013. A
copy of the eMQTG must be provided to the
NSPM. This may be provided by an
electronic scan presented in a Portable
Document File (PDF), or similar format
acceptable to the NSPM.
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End QPS Requirements
lllllllllllllllllllll
Begin Information
l. Only those FFSs that are sponsored by
a certificate holder as defined in appendix F
will be evaluated by the NSPM. However,
other FFS evaluations may be conducted on
a case-by-case basis as the Administrator
deems appropriate, but only in accordance
with applicable agreements.
m. The NSPM will conduct an evaluation
for each configuration, and each FFS must be
evaluated as completely as possible. To
ensure a thorough and uniform evaluation,
each FFS is subjected to the general
simulator requirements in Attachment 1, the
objective tests listed in Attachment 2, and the
subjective tests listed in Attachment 3 of this
appendix. The evaluations described herein
will include, but not necessarily be limited
to the following:
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(1) Airplane responses, including
longitudinal and lateral-directional control
responses (see Attachment 2 of this
appendix);
(2) Performance in authorized portions of
the simulated airplane’s operating envelope,
to include tasks evaluated by the NSPM in
the areas of surface operations, takeoff, climb,
cruise, descent, approach, and landing as
well as abnormal and emergency operations
(see Attachment 2 of this appendix);
(3) Control checks (see Attachment 1 and
Attachment 2 of this appendix);
(4) Cockpit configuration (see Attachment
1 of this appendix);
(5) Pilot, flight engineer, and instructor
station functions checks (see Attachment 1
and Attachment 3 of this appendix);
(6) Airplane systems and sub-systems (as
appropriate) as compared to the airplane
simulated (see Attachment 1 and Attachment
3 of this appendix);
(7) FFS systems and sub-systems,
including force cueing (motion), visual, and
aural (sound) systems, as appropriate (see
Attachment 1 and Attachment 2 of this
appendix); and
(8) Certain additional requirements,
depending upon the qualification level
sought, including equipment or
circumstances that may become hazardous to
the occupants. The sponsor may be subject to
Occupational Safety and Health
Administration requirements.
n. The NSPM administers the objective and
subjective tests, which includes an
examination of functions. The tests include
a qualitative assessment of the FFS by an
NSP pilot. The NSP evaluation team leader
may assign other qualified personnel to assist
in accomplishing the functions examination
and/or the objective and subjective tests
performed during an evaluation when
required.
(1) Objective tests provide a basis for
measuring and evaluating FFS performance
and determining compliance with the
requirements of this part.
(2) Subjective tests provide a basis for:
(a) Evaluating the capability of the FFS to
perform over a typical utilization period;
(b) Determining that the FFS satisfactorily
simulates each required task;
(c) Verifying correct operation of the FFS
controls, instruments, and systems; and
(d) Demonstrating compliance with the
requirements of this part.
o. The tolerances for the test parameters
listed in Attachment 2 of this appendix
reflect the range of tolerances acceptable to
the NSPM for FFS validation and are not to
be confused with design tolerances specified
for FFS manufacture. In making decisions
regarding tests and test results, the NSPM
relies on the use of operational and
engineering judgment in the application of
data (including consideration of the way in
which the flight test was flown and way the
data was gathered and applied) data
presentations, and the applicable tolerances
for each test.
p. In addition to the scheduled continuing
qualification evaluation, each FFS is subject
to evaluations conducted by the NSPM at any
time without prior notification to the
sponsor. Such evaluations would be
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accomplished in a normal manner (i.e.,
requiring exclusive use of the FFS for the
conduct of objective and subjective tests and
an examination of functions) if the FFS is not
being used for flight crewmember training,
testing, or checking. However, if the FFS
were being used, the evaluation would be
conducted in a non-exclusive manner. This
non-exclusive evaluation will be conducted
by the FFS evaluator accompanying the
check airman, instructor, Aircrew Program
Designee (APD), or FAA inspector aboard the
FFS along with the student(s) and observing
the operation of the FFS during the training,
testing, or checking activities.
q. Problems with objective test results are
handled as follows:
(1) If a problem with an objective test result
is detected by the NSP evaluation team
during an evaluation, the test may be
repeated or the QTG may be amended.
(2) If it is determined that the results of an
objective test do not support the level
requested but do support a lower level, the
NSPM may qualify the FFS at that lower
level. For example, if a Level D evaluation is
requested and the FFS fails to meet sound
test tolerances, it could be qualified at Level
C.
r. After an FFS is successfully evaluated,
the NSPM issues a statement of qualification
(SOQ) to the sponsor. The NSPM
recommends the FFS to the TPAA, who will
approve the FFS for use in a flight training
program. The SOQ will be issued at the
satisfactory conclusion of the initial or
continuing qualification. However, it is the
sponsor’s responsibility to obtain TPAA
approval prior to using the FSTD in an FAAapproved flight training program.
s. Under normal circumstances, the NSPM
establishes a date for the initial or upgrade
evaluation within ten (10) working days after
determining that a complete QTG is
acceptable. Unusual circumstances may
warrant establishing an evaluation date
before this determination is made. A sponsor
may schedule an evaluation date as early as
6 months in advance. However, there may be
a delay of 45 days or more in rescheduling
and completing the evaluation if the sponsor
is unable to meet the scheduled date. See
Attachment 4, Figure A4A, Sample Request
for Initial, Upgrade, or Reinstatement
Evaluation.
t. The numbering system used for objective
test results in the QTG should closely follow
the numbering system set out in Attachment
2, FFS Objective Tests, Table A2A.
u. Contact the NSPM or visit the NSPM
Web site for additional information regarding
the preferred qualifications of pilots used to
meet the requirements of § 60.15(d).
v. Examples of the exclusions for which
the FFS might not have been subjectively
tested by the sponsor or the NSPM and for
which qualification might not be sought or
granted, as described in § 60.15(g)(6), include
windshear training and circling approaches.
End Information
lllllllllllllllllllll
12. Additional Qualifications for a Currently
Qualified Simulator (§ 60.16)
There is no additional regulatory or
informational material that applies to § 60.16,
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Additional Qualifications for a Currently
Qualified FFS.
13. Previously Qualified Simulators (§ 60.17)
lllllllllllllllllllll
Begin QPS Requirements
a. In instances where a sponsor plans to
remove a FFS from active status for a period
of less than two years, the following
procedures apply:
(1) The NSPM must be notified in writing
and the notification must include an estimate
of the period that the FFS will be inactive;
(2) Continuing Qualification evaluations
will not be scheduled during the inactive
period;
(3) The NSPM will remove the FFS from
the list of qualified FSTDs on a mutually
established date not later than the date on
which the first missed continuing
qualification evaluation would have been
scheduled;
(4) Before the FFS is restored to qualified
status, it must be evaluated by the NSPM.
The evaluation content and the time required
to accomplish the evaluation is based on the
number of continuing qualification
evaluations and sponsor-conducted quarterly
inspections missed during the period of
inactivity.
(5) The sponsor must notify the NSPM of
any changes to the original scheduled time
out of service;
b. Simulators qualified prior to October 30,
2007, are not required to meet the general
simulation requirements, the objective test
requirements, and the subjective test
requirements of attachments 1, 2, and 3,
respectively, of this appendix.
c. [Reserved]
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End QPS Requirements
lllllllllllllllllllll
Begin Information
d. Other certificate holders or persons
desiring to use an FFS may contract with FFS
sponsors to use FFSs previously qualified at
a particular level for an airplane type and
approved for use within an FAA-approved
flight training program. Such FFSs are not
required to undergo an additional
qualification process, except as described in
§ 60.16.
e. Each FFS user must obtain approval
from the appropriate TPAA to use any FFS
in an FAA-approved flight training program.
f. The intent of the requirement listed in
§ 60.17(b), for each FFS to have a Statement
of Qualification within 6 years, is to have the
availability of that statement (including the
configuration list and the limitations to
authorizations) to provide a complete picture
of the FFS inventory regulated by the FAA.
The issuance of the statement will not
require any additional evaluation or require
any adjustment to the evaluation basis for the
FFS.
g. Downgrading of an FFS is a permanent
change in qualification level and will
necessitate the issuance of a revised
Statement of Qualification to reflect the
revised qualification level, as appropriate. If
a temporary restriction is placed on an FFS
because of a missing, malfunctioning, or
inoperative component or on-going repairs,
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the restriction is not a permanent change in
qualification level. Instead, the restriction is
temporary and is removed when the reason
for the restriction has been resolved.
h. It is not the intent of the NSPM to
discourage the improvement of existing
simulation (e.g., the ‘‘updating’’ of a visual
system to a newer model, or the replacement
of the IOS with a more capable unit) by
requiring the ‘‘updated’’ device to meet the
qualification standards current at the time of
the update. Depending on the extent of the
update, the NSPM may require that the
updated device be evaluated and may require
that an evaluation include all or a portion of
the elements of an initial evaluation.
However, the standards against which the
device would be evaluated are those that are
found in the MQTG for that device.
i. The NSPM will determine the evaluation
criteria for an FSTD that has been removed
from active status. The criteria will be based
on the number of continuing qualification
evaluations and quarterly inspections missed
during the period of inactivity. For example,
if the FFS were out of service for a 1 year
period, it would be necessary to complete the
entire QTG, since all of the quarterly
evaluations would have been missed. The
NSPM will also consider how the FFS was
stored, whether parts were removed from the
FFS and whether the FFS was disassembled.
j. The FFS will normally be requalified
using the FAA-approved MQTG and the
criteria that was in effect prior to its removal
from qualification. However, inactive periods
of 2 years or more will require requalification
under the standards in effect and current at
the time of requalification.
End Information
lllllllllllllllllllll
14. Inspection, Continuing Qualification
Evaluation, and Maintenance Requirements
(§ 60.19)
lllllllllllllllllllll
Begin QPS Requirements
a. The sponsor must conduct a minimum
of four evenly spaced inspections throughout
the year. The objective test sequence and
content of each inspection must be
developed by the sponsor and must be
acceptable to the NSPM.
b. The description of the functional
preflight inspection must be contained in the
sponsor’s QMS.
c. Record ‘‘functional preflight’’ in the FFS
discrepancy log book or other acceptable
location, including any item found to be
missing, malfunctioning, or inoperative.
End QPS Requirements
lllllllllllllllllllll
Begin Information
d. The sponsor’s test sequence and the
content of each quarterly inspection required
in § 60.19(a)(1) should include a balance and
a mix from the objective test requirement
areas listed as follows:
(1) Performance.
(2) Handling qualities.
(3) Motion system (where appropriate).
(4) Visual system (where appropriate).
(5) Sound system (where appropriate).
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63437
(6) Other FFS systems.
e. If the NSP evaluator plans to accomplish
specific tests during a normal continuing
qualification evaluation that requires the use
of special equipment or technicians, the
sponsor will be notified as far in advance of
the evaluation as practical; but not less than
72 hours. Examples of such tests include
latencies, control dynamics, sounds and
vibrations, motion, and/or some visual
system tests.
f. The continuing qualification evaluations,
described in § 60.19(b), will normally require
4 hours of FFS time. However, flexibility is
necessary to address abnormal situations or
situations involving aircraft with additional
levels of complexity (e.g., computer
controlled aircraft). The sponsor should
anticipate that some tests may require
additional time. The continuing qualification
evaluations will consist of the following:
(1) Review of the results of the quarterly
inspections conducted by the sponsor since
the last scheduled continuing qualification
evaluation.
(2) A selection of approximately 8 to 15
objective tests from the MQTG that provide
an adequate opportunity to evaluate the
performance of the FFS. The tests chosen
will be performed either automatically or
manually and should be able to be conducted
within approximately one-third (1⁄3) of the
allotted FFS time.
(3) A subjective evaluation of the FFS to
perform a representative sampling of the
tasks set out in attachment 3 of this
appendix. This portion of the evaluation
should take approximately two-thirds (2⁄3) of
the allotted FFS time.
(4) An examination of the functions of the
FFS may include the motion system, visual
system, sound system, instructor operating
station, and the normal functions and
simulated malfunctions of the airplane
systems. This examination is normally
accomplished simultaneously with the
subjective evaluation requirements.
g. The requirement established in
§ 60.19(b)(4) regarding the frequency of
NSPM-conducted continuing qualification
evaluations for each FFS is typically 12
months. However, the establishment and
satisfactory implementation of an approved
QMS for a sponsor will provide a basis for
adjusting the frequency of evaluations to
exceed 12-month intervals.
End Information
lllllllllllllllllllll
15. Logging Simulator Discrepancies
(§ 60.20)
There is no additional regulatory or
informational material that applies to § 60.20.
Logging FFS Discrepancies.
16. Interim Qualification of Simulators for
New Airplane Types or Models (§ 60.21)
There is no additional regulatory or
informational material that applies to § 60.21,
Interim Qualification of FFSs for New
Airplane Types or Models.
17. Modifications to Simulators (§ 60.23)
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Begin QPS Requirements
a. The notification described in
§ 60.23(c)(2) must include a complete
description of the planned modification, with
a description of the operational and
engineering effect the proposed modification
will have on the operation of the FFS and the
results that are expected with the
modification incorporated.
b. Prior to using the modified FFS:
(1) All the applicable objective tests
completed with the modification
incorporated, including any necessary
updates to the MQTG (e.g., accomplishment
of FSTD Directives) must be acceptable to the
NSPM; and
(2) The sponsor must provide the NSPM
with a statement signed by the MR that the
factors listed in § 60.15(b) are addressed by
the appropriate personnel as described in
that section.
End QPS Requirements
lllllllllllllllllllll
Begin Information
FSTD Directives are considered
modifications of an FFS. See Attachment 4
for a sample index of effective FSTD
Directives.
End Information
lllllllllllllllllllll
18. Operation With Missing, Malfunctioning,
or Inoperative Components (§ 60.25)
lllllllllllllllllllll
Begin Information
a. The sponsor’s responsibility with respect
to § 60.25(a) is satisfied when the sponsor
fairly and accurately advises the user of the
current status of an FFS, including any
missing, malfunctioning, or inoperative
(MMI) component(s).
b. If the 29th or 30th day of the 30-day
period described in § 60.25(b) is on a
Saturday, a Sunday, or a holiday, the FAA
will extend the deadline until the next
business day.
c. In accordance with the authorization
described in § 60.25(b), the sponsor may
develop a discrepancy prioritizing system to
accomplish repairs based on the level of
impact on the capability of the FFS. Repairs
having a larger impact on FFS capability to
provide the required training, evaluation, or
flight experience will have a higher priority
for repair or replacement.
End Information
lllllllllllllllllllll
19. Automatic Loss of Qualification and
Procedures for Restoration of Qualification
(§ 60.27)
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lllllllllllllllllllll
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Begin Information
If the sponsor provides a plan for how the
FFS will be maintained during its out-ofservice period (e.g., periodic exercise of
mechanical, hydraulic, and electrical
systems; routine replacement of hydraulic
fluid; control of the environmental factors in
which the FFS is to be maintained) there is
a greater likelihood that the NSPM will be
able to determine the amount of testing
required for requalification.
End Information
lllllllllllllllllllll
20. Other Losses of Qualification and
Procedures for Restoration of Qualification
(§ 60.29)
lllllllllllllllllllll
Begin Information
If the sponsor provides a plan for how the
FFS will be maintained during its out-ofservice period (e.g., periodic exercise of
mechanical, hydraulic, and electrical
systems; routine replacement of hydraulic
fluid; control of the environmental factors in
which the FFS is to be maintained) there is
a greater likelihood that the NSPM will be
able to determine the amount of testing
required for requalification.
End Information
lllllllllllllllllllll
21. Recordkeeping and Reporting (§ 60.31)
lllllllllllllllllllll
Begin QPS Requirements
a. FSTD modifications can include
hardware or software changes. For FSTD
modifications involving software
programming changes, the record required by
§ 60.31(a)(2) must consist of the name of the
aircraft system software, aerodynamic model,
or engine model change, the date of the
change, a summary of the change, and the
reason for the change.
b. If a coded form for record keeping is
used, it must provide for the preservation
and retrieval of information with appropriate
security or controls to prevent the
inappropriate alteration of such records after
the fact.
End QPS Requirements
lllllllllllllllllllll
22. Applications, Logbooks, Reports, and
Records: Fraud, Falsification, or Incorrect
Statements (§ 60.33)
There are no additional QPS requirements
or informational material that apply to
§ 60.33, Applications, Logbooks, Reports, and
Records: Fraud, Falsification, or Incorrect
Statements.
23. Specific Full Flight Simulator
Compliance Requirements (§ 60.35)
There are no additional QPS requirements
or informational material that apply to
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§ 60.35, Specific FFS Compliance
Requirements.
24. [Reserved]
25. FSTD Qualification on the Basis of a
Bilateral Aviation Safety Agreement (BASA)
(§ 60.37)
There are no additional QPS requirements
or informational material that apply to
§ 60.37, FSTD Qualification on the Basis of
a Bilateral Aviation Safety Agreement
(BASA).
Attachment 1 to Appendix A to Part 60—
General Simulator Requirements
lllllllllllllllllllll
Begin QPS Requirements
1. Requirements
a. Certain requirements included in this
appendix must be supported with a
Statement of Compliance and Capability
(SOC), which may include objective and
subjective tests. The SOC will confirm that
the requirement was satisfied, and describe
how the requirement was met, such as gear
modeling approach or coefficient of friction
sources. The requirements for SOCs and tests
are indicated in the ‘‘General Simulator
Requirements’’ column in Table A1A of this
appendix.
b. Table A1A describes the requirements
for the indicated level of FFS. Many devices
include operational systems or functions that
exceed the requirements outlined in this
section. However, all systems will be tested
and evaluated in accordance with this
appendix to ensure proper operation.
End QPS Requirements
lllllllllllllllllllll
Begin Information
2. Discussion
a. This attachment describes the general
simulator requirements for qualifying an
airplane FFS. The sponsor should also
consult the objective tests in attachment 2
and the examination of functions and
subjective tests listed in attachment 3 to
determine the complete requirements for a
specific level simulator.
b. The material contained in this
attachment is divided into the following
categories:
(1) General cockpit configuration.
(2) Simulator programming.
(3) Equipment operation.
(4) Equipment and facilities for instructor/
evaluator functions.
(5) Motion system.
(6) Visual system.
(7) Sound system.
c. Table A1A provides the standards for the
General Simulator Requirements.
End Information
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63439
TABLE A1A.—MINIMUM SIMULATOR REQUIREMENTS
<<>>
No.
Simulator levels
General simulator requirements
A
B
C
D
notes
For simulator purposes, the cockpit consists of all that
space forward of a cross section of the flight deck at
the most extreme aft setting of the pilots’ seats, including additional required crewmember duty stations
and those required bulkheads aft of the pilot seats.
For clarification, bulkheads containing only items
such as landing gear pin storage compartments, fire
axes or extinguishers, spare light bulbs, and aircraft
document pouches are not considered essential and
may be omitted.
1. General Cockpit Configuration
1.a .......
The simulator must have a cockpit that is a replica of
the airplane simulated with controls, equipment, observable cockpit indicators, circuit breakers, and bulkheads properly located, functionally accurate and replicating the airplane. The direction of movement of
controls and switches must be identical to the airplane. Pilot seats must allow the occupant to achieve
the design ‘‘eye position’’ established for the airplane
being simulated. Equipment for the operation of the
cockpit windows must be included, but the actual windows need not be operable. Additional equipment
such as fire axes, extinguishers, and spare light bulbs
must be available in the FFS but may be relocated to
a suitable location as near as practical to the original
position. Fire axes, landing gear pins, and any similar
purpose instruments need only be represented in silhouette.
An SOC is required.
X
X
X
X
1.b .......
Those circuit breakers that affect procedures or result in
observable cockpit indications must be properly located and functionally accurate.
An SOC is required.
X
X
X
X
2. Programming
2.a .......
A flight dynamics model that accounts for various combinations of drag and thrust normally encountered in
flight must correspond to actual flight conditions, including the effect of change in airplane attitude,
thrust, drag, altitude, temperature, gross weight, moments of inertia, center of gravity location, and configuration.
X
X
X
X
2.b .......
The simulator must have the computer capacity, accuracy, resolution, and dynamic response needed to
meet the qualification level sought.
An SOC is required.
X
X
X
X
2.c ........
Surface operations must be represented to the extent
that allows turns within the confines of the runway
and adequate controls on the landing and roll-out
from a crosswind approach to a landing.
X
A subjective test is required.
Ground handling and aerodynamic programming must
include the following:
An SOC is required.
2.d.1 ....
Ground effect ...................................................................
X
X
X
Ground effect includes modeling that accounts for
roundout, flare, touchdown, lift, drag, pitching moment, trim, and power while in ground effect.
2.d.2 ....
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2.d .......
Ground reaction ...............................................................
X
X
X
Ground reaction includes modeling that accounts for
strut deflections, tire friction, and side forces. This is
the reaction of the airplane upon contact with the runway during landing, and may differ with changes in
factors such as gross weight, airspeed, or rate of descent on touchdown.
2.d.3 ....
Ground handling characteristics, including aerodynamic
and ground reaction modeling including steering inputs, operations with crosswind, braking, thrust reversing, deceleration, and turning radius.
X
X
X
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TABLE A1A.—MINIMUM SIMULATOR REQUIREMENTS—Continued
<<>>
Simulator levels
General simulator requirements
2.e .......
C
D
notes
The simulator must employ windshear models that provide training for recognition of windshear phenomena
and the execution of recovery procedures. Models
must be available to the instructor/evaluator for the
following critical phases of flight:
(1) Prior to takeoff rotation.
(2) At liftoff.
(3) During initial climb.
(4) On final approach, below 500 ft AGL.
The QTG must reference the FAA Windshear Training
Aid or present alternate airplane related data, including the implementation method(s) used. If the alternate method is selected, wind models from the Royal
Windshear Training Aerospace Establishment (RAE),
the Joint Airport Weather Studies (JAWS) Project and
other recognized sources may be implemented, but
must be supported and properly referenced in the
QTG. Only those simulators meeting these requirements may be used to satisfy the training requirements of part 121 pertaining to a certificate holder’s
approved low-altitude windshear flight training program as described in § 121.409.
Objective tests are required for qualification; see Attachment 2 and Attachment 5 of this appendix.
X
X
If desired, Level A and B simulators may qualify for
windshear training by meeting these standards; see
Attachment 5 of this appendix. Windshear models
may consist of independent variable winds in multiple
simultaneous components. The FAA Windshear
Training Aid presents one acceptable means of compliance with simulator wind model requirements.
2.f ........
The simulator must provide for automatic testing of simulator hardware and software programming to determine compliance with simulator objective tests as
prescribed in Attachment 2.
An SOC is required.
X
X
Automatic ‘‘flagging’’ of out-of-tolerance situations is encouraged.
2.g .......
Relative responses of the motion system, visual system, and cockpit instruments, measured by latency
tests or transport delay tests. Motion onset should
occur before the start of the visual scene change (the
start of the scan of the first video field containing different information) but must occur before the end of
the scan of that video field. Instrument response may
not occur prior to motion onset. Test results must be
within the following limits:
2.g.1 ....
300 milliseconds of the airplane response ......................
Objective Tests are required.
2.g.2 ....
150 milliseconds of the airplane response ......................
Objective Tests are required.
X
X
2.h .......
The simulator must accurately reproduce the following
runway conditions:
(1) Dry.
(2) Wet.
(3) Icy.
(4) Patchy Wet.
(5) Patchy Icy.
(6) Wet on Rubber Residue in Touchdown Zone.
An SOC is required.
Objective tests are required only for dry, wet, and icy
runway conditions; see Attachment 2.
X
X
2.i .........
sroberts on PROD1PC70 with RULES
No.
The simulator must simulate:
(1) brake and tire failure dynamics, including antiskid failure.
(2) decreased brake efficiency due to high brake
temperatures, if applicable.
An SOC is required.
X
X
2.j .........
The simulator must replicate the effects of airframe
icing.
A Subjective Test is required.
X
X
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A
B
The intent is to verify that the simulator provides instrument, motion, and visual cues that are, within the
stated time delays, like the airplane responses. For
airplane response, acceleration in the appropriate,
corresponding rotational axis is preferred.
X
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X
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Simulator pitch, side loading, and directional control
characteristics should be representative of the airplane.
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63441
TABLE A1A.—MINIMUM SIMULATOR REQUIREMENTS—Continued
<<>>
No.
2.k ........
2.l .........
Simulator levels
General simulator requirements
The aerodynamic modeling in the simulator must
clude:
(1) Low-altitude level-flight ground effect;
(2) Mach effect at high altitude;
(3) Normal and reverse dynamic thrust effect
control surfaces;
(4) Aeroelastic representations; and
(5) Nonlinearities due to sideslip.
An SOC is required and must include references
computations of aeroelastic representations and
nonlinearities due to sideslip.
A
B
C
notes
X
in-
D
See Attachment 2, paragraph 4, for further information
on ground effect.
on
to
of
The simulator must have aerodynamic and ground reaction modeling for the effects of reverse thrust on directional control, if applicable.
An SOC is required.
X
X
X
3. Equipment Operation
3.a .......
All relevant instrument indications involved in the simulation of the airplane must automatically respond to
control movement or external disturbances to the
simulated airplane; e.g., turbulence or windshear. Numerical values must be presented in the appropriate
units.
A subjective test is required.
X
X
X
X
3.b .......
Communications, navigation, caution, and warning
equipment must be installed and operate within the
tolerances applicable for the airplane.
A subjective test is required.
X
X
X
X
3.c ........
Simulator systems must operate as the airplane systems operate under normal, abnormal, and emergency operating conditions on the ground and in flight.
A subjective test is required.
X
X
X
X
3.d .......
The simulator must provide pilot controls with control
forces and control travel that correspond to the simulated airplane. The simulator must also react in the
same manner as in the airplane under the same flight
conditions.
A objective test is required.
X
X
X
X
See Attachment 3 for further information regarding longrange navigation equipment.
4. Instructor or Evaluator Facilities
In addition to the flight crewmember stations, the simulator must have at least two suitable seats for the instructor/check airman and FAA inspector. These
seats must provide adequate vision to the pilot’s
panel and forward windows. All seats other than flight
crew seats need not represent those found in the airplane, but must be adequately secured to the floor
and equipped with similar positive restraint devices.
A subjective test is required.
X
X
X
X
4.b .......
sroberts on PROD1PC70 with RULES
4.a .......
The simulator must have controls that enable the instructor/evaluator to control all required system variables and insert all abnormal or emergency conditions into the simulated airplane systems as described in the sponsor’s FAA-approved training program; or as described in the relevant operating manual as appropriate.
A subjective test is required.
X
X
X
X
4.c ........
The simulator must have instructor controls for environmental conditions including wind speed and direction.
A subjective test is required.
X
X
X
X
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The NSPM will consider alternatives to this standard for
additional seats based on unique cockpit configurations.
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TABLE A1A.—MINIMUM SIMULATOR REQUIREMENTS—Continued
<<>>
Simulator levels
No.
General simulator requirements
A
4.d .......
B
The simulator must provide the instructor or evaluator
the ability to present ground and air hazards.
A subjective test is required.
C
D
notes
X
X
For example, another airplane crossing the active runway or converging airborne traffic.
X
X
For example, touchdown cues should be a function of
the rate of descent (RoD) of the simulated airplane.
X
X
X
X
X
X
X
X
5. Motion System
5.a .......
The simulator must have motion (force) cues perceptible to the pilot that are representative of the motion
in an airplane.
A subjective test is required.
X
X
5.b .......
The simulator must have a motion (force cueing) system with a minimum of three degrees of freedom (at
least pitch, roll, and heave).
An SOC is required.
X
X
5.c ........
The simulator must have a motion (force cueing) system that produces cues at least equivalent to those of
a six-degrees-of-freedom, synergistic platform motion
system (i.e., pitch, roll, yaw, heave, sway, and surge).
An SOC is required.
5.d .......
The simulator must provide for the recording of the motion system response time.
An SOC is required.
5.e .......
The simulator must provide motion effects programming
to include:
(1) Thrust effect with brakes set.
(2) Runway rumble, oleo deflections, effects of
ground speed, uneven runway, centerline lights,
and taxiway characteristics.
(3) Buffets on the ground due to spoiler/
speedbrake extension and thrust reversal.
(4) Bumps associated with the landing gear.
(5) Buffet during extension and retraction of landing
gear.
(6) Buffet in the air due to flap and spoiler/
speedbrake extension.
(7) Approach-to-Stall buffet.
(8) Representative touchdown cues for main and
nose gear.
(9) Nosewheel scuffing, if applicable.
(10) Mach and maneuver buffet.
A subjective test is required.
5.f ........
The simulator must provide characteristic motion vibrations that result from operation of the airplane if the
vibration marks an event or airplane state that can be
sensed in the cockpit.
A objective test is required.
X
X
The simulator should be programmed and instrumented
in such a manner that the characteristic buffet modes
can be measured and compared to airplane data.
6. Visual System
The simulator must have a visual system providing an
out-of-the-cockpit view.
A subjective test is required.
X
X
X
X
6.b .......
The simulator must have operational landing lights for
night scenes. Where used, dusk (or twilight) scenes
require operational landing lights.
A subjective test is required.
X
X
X
X
6.c ........
sroberts on PROD1PC70 with RULES
6.a .......
The simulator must have instructor controls for the following:
(1) Cloudbase.
(2) Visibility in statute miles (km) and runway visual
range (RVR) in ft. (m).
(3) Airport selection.
(4) Airport lighting.
X
X
X
X
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63443
TABLE A1A.—MINIMUM SIMULATOR REQUIREMENTS—Continued
<<>>
No.
Simulator levels
General simulator requirements
A
B
C
D
notes
A subjective test is required.
Each airport scene displayed must include the following:
(1) Airport runways and taxiways.
(2) Runway definition.
(i) Runway surface and markings.
(ii) Lighting for the runway in use, including
runway threshold, edge, centerline, touchdown zone, VASI or PAPI, and approach
lighting of appropriate colors, as appropriate.
(iii) Taxiway lights.
A subjective test is required.
X
X
X
X
6.e .......
The distances at which runway features are visible, as
measured from runway threshold to an airplane
aligned with the runway on an extended 3 ° glide
slope must not be less than listed below:
(1) Runway definition, strobe lights, approach
lights, runway edge white lights VASI or PAPI
system lights from 5 statute miles (8 kilometers
(km)) of the runway threshold.
(2) Runway centerline lights and taxiway definition
from 3 statute miles (4.8 km).
(3) Threshold lights and touchdown zone lights
from 2 statute miles (3.2 km).
(4) Runway markings within range of landing lights
for night scenes and as required by three (3) arcminutes resolution on day scenes.
A subjective test is required.
X
X
X
X
6.f ........
The simulator must provide visual system compatibility
with dynamic response programming.
A subjective test is required.
X
X
X
X
6.g .......
The simulator must show that the segment of the
ground visible from the simulator flight deck is the
same as from the airplane flight deck (within established tolerances) when at the correct airspeed, in the
landing configuration, at a main wheel height of 100
feet (30 meters) above the touchdown zone, and with
visibility of 1,200 ft (350 m) RVR.
An SOC is required.
An objective test is required.
X
X
X
X
6.h .......
The simulator must provide visual cues necessary to
assess sink rates (provide depth perception) during
takeoffs and landings, to include:
(1) Surface on runways, taxiways, and ramps.
(2) Terrain features.
A subjective test is required.
X
X
X
6.i .........
The simulator must provide for accurate portrayal of the
visual environment relating to the simulator attitude.
A subjective test is required.
X
X
X
6.j .........
The simulator must provide for quick confirmation of
visual system color, RVR, focus, and intensity.
An SOC is required.
A subjective test is required.
X
X
6.k ........
sroberts on PROD1PC70 with RULES
6.d .......
The simulator must provide a minimum of three airport
scenes including:
(1) Surfaces on runways, taxiways, and ramps.
(2) Lighting of appropriate color for all runways, including runway threshold, edge, centerline, VASI
or PAPI, and approach lighting for the runway in
use.
(3) Airport taxiway lighting.
X
X
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X
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This will show the modeling accuracy of RVR,
glideslope, and localizer for a given weight, configuration, and speed within the airplane’s operational envelope for a normal approach and landing.
Visual attitude vs. simulator attitude is a comparison of
pitch and roll of the horizon as displayed in the visual
scene compared to the display on the attitude indicator.
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TABLE A1A.—MINIMUM SIMULATOR REQUIREMENTS—Continued
<<>>
No.
Simulator levels
General simulator requirements
A
B
C
D
X
X
X
X
X
notes
X
(4) Ramps and buildings that correspond to the
sponsor’s Line Oriented scenarios, as appropriate.
A subjective test is required.
The simulator must be capable of producing at least 10
levels of occulting.
A subjective test is required.
6.m ......
Night Visual Scenes. When used in training, testing, or
checking activities, the simulator must provide night
visual scenes with sufficient scene content to recognize the airport, the terrain, and major landmarks
around the airport. The scene content must allow a
pilot to successfully accomplish a visual landing.
Scenes must include a definable horizon and typical
terrain characteristics such as fields, roads and bodies of water and surfaces illuminated by airplane
landing lights.
6.n .......
Dusk (or Twilight) Visual Scenes. When used in training, testing, or checking activities, the simulator must
provide dusk (or twilight) visual scenes with sufficient
scene content to recognize the airport, the terrain,
and major landmarks around the airport. The scene
content must allow a pilot to successfully accomplish
a visual landing. Scenes must include a definable horizon and typical terrain characteristics such as fields,
roads and bodies of water and surfaces illuminated
by airplane landing lights.
An SOC is required.
A subjective test is required.
6.o .......
Daylight Visual Scenes. The simulator must have night
dusk (twilight), and daylight visual scenes with sufficient scene content to recognize the airport, the terrain, and major landmarks around the airport. The
scene content must allow a pilot to successfully accomplish a visual landing. Any ambient lighting must
not ‘‘washout’’ the displayed visual scene.
Note: These requirements are applicable to any level of
simulator equipped with a ‘‘daylight’’ visual system.
An SOC is required.
A subjective test is required.
X
Brightness capability may be demonstrated with a test
pattern of white light using a spot photometer. Daylight visual system is defined as a visual system capable of producing, at a minimum, full color presentations, scene content comparable in detail to that
produced by 4,000 edges or 1,000 surfaces for daylight and 4,000 lightpoints for night and dusk scenes,
6 foot-lamberts (20 cd/m 2) of light measured at the
pilot’s eye position (highlight brightness) and a display which is free of apparent quantization and other
distracting visual effects while the simulator is in motion.
6.p .......
The simulator must provide operational visual scenes
that portray physical relationships known to cause
landing illusions to pilots.
A subjective test is required.
X
For example: short runways, landing approaches over
water, uphill or downhill runways, rising terrain on the
approach path, unique topographic features.
6.q .......
The simulator must provide special weather representations of light, medium, and heavy precipitation near a
thunderstorm on takeoff and during approach and
landing. Representations need only be presented at
and below an altitude of 2,000 ft. (610 m) above the
airport surface and within 10 miles (16 km) of the airport.
A subjective test is required.
X
6.r ........
sroberts on PROD1PC70 with RULES
6.l .........
The simulator must present visual scenes of wet and
snow-covered runways, including runway lighting reflections for wet conditions, partially obscured lights
for snow conditions, or suitable alternative effects.
A subjective test is required.
X
6.s ........
The simulator must present realistic
directionality of all airport lighting.
A subjective test is required.
X
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X
X
and
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
63445
TABLE A1A.—MINIMUM SIMULATOR REQUIREMENTS—Continued
<<>>
No.
Simulator levels
General simulator requirements
A
B
C
D
7.a .......
The simulator must provide cockpit sounds that result
from pilot actions that correspond to those that occur
in the airplane.
X
X
X
X
7.b .......
The simulator must accurately simulate the sound of
precipitation, windshield wipers, and other significant
airplane noises perceptible to the pilot during normal
operations, and include the sound of a crash (when
the simulator is landed in an unusual attitude or in
excess of the structural gear limitations); normal engine and thrust reversal sounds; and the sounds of
flap, gear, and spoiler extension and retraction.
An SOC is required.
A subjective test is required.
X
X
7.c ........
The simulator must provide realistic amplitude and frequency of cockpit noises and sounds. Simulator performance must be recorded, compared to amplitude
and frequency of the same sounds recorded in the
airplane, and be made a part of the QTG.
Objective tests are required.
notes
7. Sound System
Table A1B—[Reserved]
Attachment 2 to Appendix A to Part 60—
Full Flight Simulator (FFS) Objective Test
lllllllllllllllllllll
sroberts on PROD1PC70 with RULES
Begin Information
1. For the purposes of this attachment, the
flight conditions specified in the Flight
Conditions Column of Table A2A, are
defined as follows:
(a) Ground—on ground, independent of
airplane configuration;
(b) Take-off—gear down with flaps/slats in
any certified takeoff position;
(c) First segment climb— gear down with
flaps/slats in any certified takeoff position
(normally not above 50 ft AGL);
(d) Second segment climb—gear up with
flaps/slats in any certified takeoff position
(normally between 50 ft and 400 ft AGL);
(e) Clean—flaps/slats retracted and gear up;
(f) Cruise—clean configuration at cruise
altitude and airspeed;
(g) Approach—gear up or down with flaps/
slats at any normal approach position as
recommended by the airplane manufacturer;
and
(h) Landing—gear down with flaps/slats in
any certified landing position.
2. The format for numbering the objective
tests in appendix A, Attachment 2, Table
A2A, and the objective tests in appendix B,
Attachment 2, Table B2A, is identical.
However, each test required for FFSs is not
necessarily required for FTDs. Also, each test
required for FTDs is not necessarily required
for FFSs. Therefore, when a test number (or
series of numbers) is not required, the term
‘‘Reserved’’ is used in the table at that
location. Following this numbering format
provides a degree of commonality between
the two tables and substantially reduces the
potential for confusion when referring to
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X
objective test numbers for either FFSs or
FTDs.
3. The QPS Requirements section imposes
a duty on the sponsor or other data provider
to ensure that a steady state condition exists
at the instant of time captured by the
‘‘snapshot’’ for cases where the objective test
results authorize a ‘‘snapshot test’’ or a
‘‘series of snapshot tests’’ results in lieu of a
time-history. This is often verified by
showing that a steady state condition existed
from some period prior to, through some
period following, the snap shot. The time
period most frequently used is from 5
seconds prior through 2 seconds following
the instant of time captured by the snap shot.
Other time periods may be acceptable as
authorized by the NSPM.
4. The reader is encouraged to review the
Airplane Flight Simulator Evaluation
Handbook, Volumes I and II, published by
the Royal Aeronautical Society, London, UK,
and FAA Advisory Circulars (AC) 25–7, as
may be amended, Flight Test Guide for
Certification of Transport Category Airplanes,
and (AC) 23–8, as may be amended, Flight
Test Guide for Certification of Part 23
Airplanes, for references and examples
regarding flight testing requirements and
techniques.
5. If relevant winds are present in the
objective data, the wind vector should be
clearly noted as part of the data presentation,
expressed in conventional terminology, and
related to the runway being used for the test.
End Information
lllllllllllllllllllll
Begin QPS Requirements
1. Test Requirements
a. The ground and flight tests required for
qualification are listed in Table of A2A, FFS
Objective Tests. Computer generated
PO 00000
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simulator test results must be provided for
each test except where an alternative test is
specifically authorized by the NSPM. If a
flight condition or operating condition is
required for the test but does not apply to the
airplane being simulated or to the
qualification level sought, it may be
disregarded (e.g., an engine out missed
approach for a single-engine airplane or a
maneuver using reverse thrust for an airplane
without reverse thrust capability). Each test
result is compared against the validation data
described in § 60.13 and in this appendix.
Although use of a driver program designed to
automatically accomplish the tests is
encouraged for all simulators and required
for Level C and Level D simulators, it must
be possible to conduct each test manually
while recording all appropriate parameters.
The results must be produced on an
appropriate recording device acceptable to
the NSPM and must include simulator
number, date, time, conditions, tolerances,
and appropriate dependent variables
portrayed in comparison to the validation
data. Time histories are required unless
otherwise indicated in Table A2A. All results
must be labeled using the tolerances and
units given.
b. Table A2A in this attachment sets out
the test results required, including the
parameters, tolerances, and flight conditions
for simulator validation. Tolerances are
provided for the listed tests because
mathematical modeling and acquisition and
development of reference data are often
inexact. All tolerances listed in the following
tables are applied to simulator performance.
When two tolerance values are given for a
parameter, the less restrictive may be used
unless otherwise indicated.
c. Certain tests included in this attachment
must be supported with a Statement of
Compliance and Capability (SOC). In Table
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
A2A, requirements for SOCs are indicated in
the ‘‘Test Details’’ column.
d. When operational or engineering
judgment is used in making assessments for
flight test data applications for simulator
validity, such judgment must not be limited
to a single parameter. For example, data that
exhibit rapid variations of the measured
parameters may require interpolations or a
‘‘best fit’’ data selection. All relevant
parameters related to a given maneuver or
flight condition must be provided to allow
overall interpretation. When it is difficult or
impossible to match simulator to airplane
data throughout a time history, differences
must be justified by providing a comparison
of other related variables for the condition
being assessed.
e. It is not acceptable to program the FFS
so that the mathematical modeling is correct
only at the validation test points. Unless
otherwise noted, simulator tests must
represent airplane performance and handling
qualities at operating weights and centers of
gravity (CG) typical of normal operation. If a
test is supported by airplane data at one
extreme weight or CG, another test supported
by airplane data at mid-conditions or as close
as possible to the other extreme must be
included, except as may be authorized by the
NSPM. Certain tests that are relevant only at
one extreme CG or weight condition need not
be repeated at the other extreme. Tests of
handling qualities must include validation of
augmentation devices.
f. When comparing the parameters listed to
those of the airplane, sufficient data must
also be provided to verify the correct flight
condition and airplane configuration
changes. For example, to show that control
force is within the parameters for a static
stability test, data to show the correct
airspeed, power, thrust or torque, airplane
configuration, altitude, and other appropriate
datum identification parameters must also be
given. If comparing short period dynamics,
normal acceleration may be used to establish
a match to the airplane, but airspeed,
altitude, control input, airplane
configuration, and other appropriate data
must also be given. If comparing landing gear
change dynamics, pitch, airspeed, and
altitude may be used to establish a match to
the airplane, but landing gear position must
also be provided. All airspeed values must be
properly annotated (e.g., indicated versus
calibrated). In addition, the same variables
must be used for comparison (e.g., compare
inches to inches rather than inches to
centimeters).
g. The QTG provided by the sponsor must
clearly describe how the simulator will be set
up and operated for each test. Each simulator
subsystem may be tested independently, but
overall integrated testing of the simulator
must be accomplished to assure that the total
simulator system meets the prescribed
standards. A manual test procedure with
explicit and detailed steps for completing
each test must also be provided.
h. In those cases where the objective test
results authorize a ‘‘snapshot test’’ or ‘‘a
series of snapshot test’’ results in lieu of a
time-history result, the sponsor or other data
provider must ensure that a steady state
condition exists at the instant of time
captured by the ‘‘snapshot.’’
i. For previously qualified simulators, the
tests and tolerances of this attachment may
be used in subsequent continuing
qualification evaluations for any given test if
the sponsor has submitted a proposed MQTG
revision to the NSPM and has received
NSPM approval.
j. Simulators are evaluated and qualified
with an engine model simulating the airplane
data supplier’s flight test engine. For
qualification of alternative engine models
(either variations of the flight test engines or
other manufacturer’s engines) additional tests
with the alternative engine models may be
required. This Attachment contains
guidelines for alternative engines.
k. For testing Computer Controlled
Airplane (CCA) simulators, or other highly
augmented airplane simulators, flight test
data is required for the Normal (N) and/or
Non-normal (NN) control states, as indicated
in this Attachment. Where test results are
independent of control state, Normal or Nonnormal control data may be used. All tests in
Table A2A require test results in the Normal
control state unless specifically noted
otherwise in the Test Details section
following the CCA designation. The NSPM
will determine what tests are appropriate for
airplane simulation data. When making this
determination, the NSPM may require other
levels of control state degradation for specific
airplane tests. Where Non-normal control
states are required, test data must be
provided for one or more Non-normal control
states, and must include the least augmented
state. Where applicable, flight test data must
record Normal and Non-normal states for:
(1) Pilot controller deflections or
electronically generated inputs, including
location of input; and
(2) Flight control surface positions unless
test results are not affected by, or are
independent of, surface positions.
l. Tests of handling qualities must include
validation of augmentation devices. FFSs for
highly augmented airplanes will be validated
both in the unaugmented configuration (or
failure state with the maximum permitted
degradation in handling qualities) and the
augmented configuration. Where various
levels of handling qualities result from
failure states, validation of the effect of the
failure is necessary. Requirements for testing
will be mutually agreed to between the
sponsor and the NSPM on a case-by-case
basis.
m. Some tests will not be required for
airplanes using airplane hardware in the
simulator cockpit (e.g., ‘‘side stick
controller’’). These exceptions are noted in
Section 2 ‘‘Handling Qualities’’ in Table A2A
of this attachment. However, in these cases,
the sponsor must provide a statement that the
airplane hardware meets the appropriate
manufacturer’s specifications and the
sponsor must have supporting information to
that fact available for NSPM review.
n. For objective test purposes, ‘‘Near
maximum’’ gross weight is a weight chosen
by the sponsor or data provider that is not
less than the basic operating weight (BOW)
of the airplane being simulated plus 80% of
the difference between the maximum
certificated gross weight (either takeoff
weight or landing weight, as appropriate for
the test) and the BOW. ‘‘Light’’ gross weight
is a weight chosen by the sponsor or data
provider that is not more than 120% of the
BOW of the airplane being simulated or as
limited by the minimum practical operating
weight of the test airplane. ‘‘Medium’’ gross
weight is a weight chosen by the sponsor or
data provider that is approximately ±10% of
the average of the numerical values of the
BOW and the maximum certificated gross
weight. (Note: BOW is the empty weight of
the aircraft plus the weight of the following:
normal oil quantity; lavatory servicing fluid;
potable water; required crewmembers and
their baggage; and emergency equipment.
(References: Advisory Circular 120–27,
‘‘Aircraft Weight and Balance;’’ and FAA–H–
8083–1, ‘‘Aircraft Weight and Balance
Handbook.’’).
End QPS Requirements
lllllllllllllllllllll
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS
<<>>
Test
Tolerance
No.
Flight
Conditions
Simulator
Level
Test details
Title
A
1. Performance
sroberts on PROD1PC70 with RULES
1.a.
Taxi
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B
C
Information
notes
D
Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
63447
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Flight
Conditions
Tolerance
No.
Title
1.a.1 .......
Minimum Radius Turn .....
±3 ft (0.9 m) or 20% of airplane
turn radius.
Ground .....................
1.a.2 .......
Rate of Turn vs.
Nosewheel Steering
Angle (NWA).
±10% or ±2% sec. turn rate ......
Ground .....................
1.b ..........
Takeoff
1.b.1 .......
Ground Acceleration Time
andDistance.
±5% time and distance or ±5%
time and ±200 ft (61 m) of
distance.
Takeoff .....................
1.b.2 .......
sroberts on PROD1PC70 with RULES
Simulator
Level
Test details
Minimum Control
Speed—ground (Vmcg)
using aerodynamic controls only (per applicable airworthiness standard or alternative) or
engine inoperative test
to demonstrate ground
control characteristics.
±25% of maximum airplane lateral deviation or ±5 ft (1.5 m).
Additionally, for those simulators of airplanes with reversible flight control systems:
Rudder pedal force; ±10% or
±5 lb (2.2 daN).
Takeoff .....................
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A
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Information
notes
B
C
D
Record both Main
and Nose gear
turning radius. This
test is to be accomplished without
the use of brakes
and only minimum
thrust, except for
airplanes requiring
asymmetric thrust
or braking to turn.
X
X
X
Record a minimum of
two speeds, greater than minimum
turning radius
speed, with a
spread of at least 5
knots groundspeed.
X
X
X
X
X
X
X
May be combined
with normal takeoff
(1.b.4.) or rejected
takeoff (1.b.7.).
Plotted data should
be shown using
appropriate scales
for each portion of
the maneuver.
X
X
X
X
If a Vmcg test is not
available an acceptable alternative
is a flight test snap
engine deceleration
to idle at a speed
between V11 and
V1—10 knots, followed by control of
heading using aerodynamic control
only. Recovery
should be achieved
with the main gear
on the ground. To
ensure only aerodynamic control is
used, nosewheel
steering should be
disabled (i.e.,
castored) or the
nosewheel held
slightly off the
ground.
All commonly used
takeoff flap settings
are to be demonstrated at least
once in the tests
for minimum unstick (1.b.3.), normal takeoff (1.b.4.),
critical engine failure on takeoff
(1.b.5.), or crosswind takeoff
(1.b.6.).
Record acceleration
time and distance
for a minimum of
80% of the time
from brake release
to VR. Preliminary
aircraft certification
data may be used.
Engine failure speed
must be within ±1
knot of airplane engine failure speed.
Engine thrust
decay must be that
resulting from the
mathematical
model for the engine variant applicable to the full
flight simulator
under test. If the
modeled engine is
not the same as
the airplane manufacturer’s flight test
engine, a further
test may be run
with the same initial conditions
using the thrust
from the flight test
data as the driving
parameter.
E:\FR\FM\30OCR2.SGM
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63448
Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Flight
Conditions
Tolerance
No.
Title
1.b.3 .......
Minimum Unstick Speed
(Vmu) or equivalent test
to demonstrate early
rotation takeoff characteristics.
±3 kts airspeed, ±1.5° pitch
angle.
Takeoff .....................
1.b.4 .......
Normal Takeoff ................
±3 kts airspeed, ±1.5° pitch
angle, ±1.5° angle of attack,
±20 ft (6 m) height. Additionally, for those simulators of
airplanes with reversible flight
control systems: Stick/Column
Force; ±10% or ± 5 lb (2.2
daN).
1.b.5 .......
Critical Engine Failure on
Takeoff.
1.b.6 .......
sroberts on PROD1PC70 with RULES
Simulator
Level
Test details
Crosswind Takeoff ...........
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Information
notes
A
B
C
D
Record main landing
gear strut compression or equivalent
air/ground signal.
Record from 10 kt
before start of rotation until at least 5
seconds after the
occurrence of main
gear lift-off.
X
X
X
X
Vmu is defined as the
minimum speed at
which the last main
landing gear leaves
the ground. Main
landing gear strut
compression or
equivalent air/
ground signal
should be recorded. If a Vmu
test is not available, alternative
acceptable flight
tests are a constant high-attitude
take-off run
through main gear
lift-off of an early
rotation take-off.
Takeoff .....................
Record takeoff profile
from brake release
to at least 200 ft
(61 m) above
ground level (AGL).
If the airplane has
more than one certificated takeoff
configuration, a different configuration
must be used for
each weight. Data
are required for a
takeoff weight at
near maximum
takeoff weight with
a mid-center of
gravity and for a
light takeoff weight
with an aft center
of gravity, as defined in appendix F.
X
X
X
X
This test may be
used for ground
acceleration time
and distance
(1.b.1.). Plotted
data should be
shown using appropriate scales for
each portion of the
maneuver.
±3 kts airspeed, ±1.5° pitch
angle, ±1.5° angle of attack,
±20 ft (6 m) height, ±3° heading angle, ±2° bank angle, ±2°
sideslip angle. Additionally, for
those simulators of airplanes
with reversible flight control
systems: Stick/Column Force;
±10% or ±5 lb (2.2 daN);
Wheel Force; ±10% or ±3 lb
(1.3 daN); and Rudder Pedal
Force; ±10% or ±5 lb (2.2
daN).
Takeoff .....................
Record takeoff profile
at near maximum
takeoff weight from
prior to engine failure to at least 200
ft (61 m) AGL. Engine failure speed
must be within ±3
kts of airplane data.
X
X
X
X
±3 kts airspeed, ±1.5° pitch
angle, ±1.5° angle of attack,
±20 ft (6 m) height, ±2° bank
angle, ±2° sideslip angle; ±3°
heading angle. Additionally,
for those simulators of airplanes with reversible flight
control systems: Stick/Column
Force; ±10% or ±5 lb (2.2
daN)
stick/column
force,
±10% or ±3 lb (1.3 daN)
wheel force, ±10% or ±5 lb
(2.2 daN) rudder pedal force.
Takeoff .....................
Record takeoff profile
from brake release
to at least 200 ft
(61 m) AGL. Requires test data, including information
on wind profile for
a crosswind component of at least
60% of the maximum described in
the Airplane Flight
Manual (AFM), as
measured at 33 ft
(10 m) above the
runway.
X
X
X
X
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In those situations
where a maximum
crosswind or a
maximum demonstrated crosswind is not included in the AFM,
contact the NSPM.
Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
63449
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Flight
Conditions
Tolerance
No.
Simulator
Level
Test details
Title
Information
notes
A
B
C
D
X
X
X
X
Autobrakes will be
used where applicable.
X
X
For safety considerations, airplane
flight test may be
performed out of
ground effect at a
safe altitude, but
with correct airplane configuration
and airspeed.
Rejected Takeoff .............
±5% time or ±1.5 sec, ±7.5%
distance or ±250 ft (±76 m).
Takeoff .....................
Record time and distance from brake
release to full stop.
Speed for initiation
of the reject must
be at least 80% of
V1 speed. The airplane must be at or
near the maximum
takeoff gross
weight. Use maximum braking effort, auto or manual.
1.b.8 .......
Dynamic Engine Failure
After Takeoff.
±20% or ±2°/sec body angular
rates.
Takeoff .....................
Engine failure speed
must be within ±3
kts of airplane
data. Record
Hands Off from 5
secs. before to at
least 5 secs. after
engine failure or
30° Bank, whichever occurs first.
Engine failure may
be a snap deceleration to idle.
(CCA: Test in Normal and Non-normal control state.).
1.c. .........
1.c.1 .......
Climb
Normal Climb, all engines
operating.
±3 kts airspeed, ±5% or ±100
FPM (0.5 m/Sec.) climb rate.
Clean ........................
Flight test data is
preferred, however,
airplane performance manual data
is an acceptable alternative. Record
at nominal climb
speed and mid-initial climb altitude.
Flight simulator
performance must
be recorded over
an interval of at
least 1,000 ft.
(300m).
X
X
X
X
1.c.2 .......
One engine Inoperative ...
±3 kts airspeed, ±5% or ±100
FPM (0.5 m/Sec.) climb rate,
but not less than the FAAApprioved
Airplane
Flight
Manual (AFM) values.
For part 23 airplanes,
in accordance with
part 23. For part 25
airplanes, Second
Segment Climb.
Flight test data is
preferred, however,
airplane performance manual data
is an acceptable alternative. Test at
weight, altitude, or
temperature limiting conditions.
Record at nominal
climb speed. Flight
simulator performance must be recorded over an interval of at least
1,000 ft. (300m).
X
X
X
X
1.c.3 .......
sroberts on PROD1PC70 with RULES
1.b.7 .......
One Engine Inoperative
En route Climb.
±10% time, ±10%
±10% fuel used.
Clean ........................
Record results for at
least a 5000 ft
(1550 m) climb
segment. Flight
test data or airplane performance
manual data may
be used.
X
X
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63450
Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Flight
Conditions
Tolerance
No.
Title
1.c.4 .......
One Engine Inoperative
Approach Climb (if the
approved AFM requires
specific performance in
icing conditions).
1.d ..........
Information
notes
Cruise/Descent
1.d.1 .......
Simulator
Level
Test details
A
B
C
D
Approach ..................
Record results at
near maximum
gross landing
weight as defined
in appendix F.
Flight test data or
airplane performance manual data
may be used.
Flight simulator
performance must
be recorded over
an interval of at
least 1,000 ft.
(300m).
X
X
X
X
Level flight acceleration ...
±5% Time ...................................
Cruise .......................
Record results for a
minimum of 50 kts
speed increase
using maximum
continuous thrust
rating or equivalent.
X
X
X
X
1.d.2 .......
Level flight deceleration ..
±5% Time ...................................
Cruise .......................
Record results for a
minimum of 50 kts
speed decrease
using idle power.
X
X
X
X
1.d.3 .......
Cruise performance .........
±0.05 EPR or ±5% of N1, or
±5% of Torque, ±5% of fuel
flow.
Cruise .......................
May be a single
snapshot showing
instantaneous fuel
flow or a minimum
of 2 consecutive
snapshots with a
spread of at least 3
minutes in steady
flight.
X
X
1.e ..........
Stopping
1.e.1 .......
sroberts on PROD1PC70 with RULES
±3 kts airspeed, ±5% or ±100
FPM (0.5 m/Sec.) climb rate,
but not less than the climb
gradient requirements of 14
CFR parts 23 or 25 climb gradient, as appropriate.
Stopping time and distance, using manual
application of wheel
brakes and no reverse
thrust on a dry runway.
±5% of time. For distance up to
4000 ft (1220 m): ±200 ft (61
m) or ±10%, whichever is
smaller. For distance greater
than 4000 ft (1220 m): ±5% of
distance.
Landing .....................
Record time and distance for at least
80% of the total
time from touch
down to full stop.
Data is required for
weights at medium
and near maximum
landing weights.
Data for brake system pressure and
position of ground
spoilers (including
method of deployment, if used) must
be provided. Engineering data may
be used for the
medium gross
weight condition.
X
X
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X
30OCR2
X
The airplane should
be configured with
all anti-ice and deice systems operating normally, with
the gear up and
go-around flaps
set. All icing accountability considerations should be
applied in accordance with the AFM
for an approach in
icing conditions.
Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
63451
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Flight
Conditions
Tolerance
No.
Simulator
Level
Test details
Title
Information
notes
A
B
C
D
X
X
X
X
Stopping time and dis±5% time and the smaller of
tance, using reverse
±10% or ±200 ft (61 m) of disthrust and no wheel
tance.
brakes on a dry runway.
Landing .....................
Record time and distance for at least
80% of the total
time from initiation
of reverse thrust to
the minimum operating speed with
full reverse thrust.
Data is required for
medium and near
maximum landing
gross weights.
Data on the position of ground
spoilers, (including
method of deployment, if used) must
be provided. Engineering data may
be used for the
medium gross
weight condition.
1.e.3 .......
Stopping distance, using
wheel brakes and no
reverse thrust on a wet
runway.
±10% of distance or ±200 ft (61
m).
Landing .....................
Either flight test data
or manufacturer’s
performance manual data must be
used where available. Engineering
data based on dry
runway flight test
stopping distance
modified by the effects of contaminated runway braking coefficients are
an acceptable alternative.
X
X
1.e.4 .......
Stopping distance, using
wheel brakes and no
reverse thrust on an icy
runway.
±10% of distance or ±200 ft (61
m).
Landing .....................
Either flight test or
manufacturer’s performance manual
data must be used,
where available.
Engineering data
based on dry runway flight test stopping distance modified by the effects
of contaminated
runway braking coefficients are an
acceptable alternative.
X
X
1.f ...........
Engines
1.f.1 ........
sroberts on PROD1PC70 with RULES
1.e.2 .......
Acceleration .....................
±10% Tt and ±10% Ti, or ±0.25
sec.
Approach or landing
Record engine power
(N1, N2, EPR,
Torque) from flight
idle to go-around
power for a rapid
(slam) throttle
movement.
X
X
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X
30OCR2
X
T1 is the total time
from initial throttle
movement until
reaching a 10% response of engine
power.
Tt is the total time
from initial throttle
movement to
reaching 90% of go
around power.
63452
Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Flight
Conditions
Tolerance
No.
Title
1.f.2 ........
Deceleration ....................
Simulator
Level
Test details
A
±10% Tt and ±10% Ti, or ±0.25
sec.
B
C
Information
notes
D
Record engine power
(N1, N2, EPR,
Torque) from Max
T/O power to 90%
decay of Max T/O
power for a rapid
(slam) throttle
movement.
Ti is the total time
from initial throttle
movement until
reaching a 10% response of engine
power.
Tt is the total time
from initial throttle
movement to
reaching 90%
decay of maximum
takeoff power.
For simulators requiring Static or Dynamic tests at the controls (i.e., column, wheel, rudder pedal), special
test fixtures will not be required during initial or upgrade evaluations if the sponsor’s QTG/MQTG shows both
text fixture results and the results of an alternative approach, such as computer plots produced concurrently,
that provide satisfactory agreement. Repeat of the alternative method during the initial or upgrade evaluation
would then satisfy this test requirement. For initial and upgrade evaluations, the control dynamic characteristics must be measured at and recorded directly from the cockpit controls, and must be accomplished in takeoff, cruise, and landing flight conditions and configurations. Testing of position versus force is not applicable
if forces are generated solely by use of airplane hardware in the full flight simulator
Contact the NSPM
for clarification of
any issue regarding airplanes with
reversible controls.
Ground .....................
2. Handling Qualities
Static Control Tests
2.a.1.a ....
Pitch Controller Position
vs. Force and Surface
Position Calibration.
2.a.1.b ....
(Reserved)
2.a.2.a ....
Roll Controller Position
vs. Force Surface Position Calibration.
2.a.2.b. ...
(Reserved).
2.a.3.a. ...
sroberts on PROD1PC70 with RULES
2.a ..........
Rudder Pedal Position vs.
Force and Surface Position Calibration.
2.a.3.b. ...
(Reserved).
2.a.4 .......
Nosewheel Steering Controller Force & Position
Calibration.
VerDate Aug<31>2005
01:08 Oct 28, 2006
±2 lb (0.9 daN) breakout, ±10%
or ±5 lb (2.2 daN) force, ±2°
elevator.
Ground .....................
Record results for an
uninterrupted control sweep to the
stops.
X
X
X
X
Test results should
be validated
(where possible)
with in-flight data
from tests such as
longitudinal static
stability or stalls.
Static and dynamic
flight control tests
should be accomplished at the
same feel or impact pressures.
±2 lb (0.9 daN) breakout, ±10%
or ±3 lb (1.3 daN) force, ±2°
aileron, ±3° spoiler angle.
Ground .....................
Record results for an
uninterrupted control sweep to the
stops.
X
X
X
X
Test results should
be validated with
in-flight data from
tests such as engine out trims,
steady state or
sideslips. Static
and dynamic flight
control tests should
be accomplished at
the same feel or
impact pressures.
±5 lb (2.2 daN) breakout, ±10%
or ±5 lb (2.2 daN) force, ±21⁄2
rudder angle.
Ground .....................
Record results for an
uninterrupted control sweep to the
stops.
X
X
X
X
Test results should
be validated with
in-flight data from
tests such as engine out trims,
steady state or
sideslips. Static
and dynamic flight
control tests should
be accomplished at
the same feel or
impact pressures.
±2 lb (0.9 daN) breakout, ±10%
or ±3 lb (1.3 daN) force, ±21⁄2
nosewheel angle.
Ground .....................
Record results for an
uninterrupted control sweep to the
stops.
X
X
X
X
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
63453
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Flight
Conditions
Tolerance
No.
Simulator
Level
Test details
Title
Information
notes
A
B
C
D
2.a.5 .......
Rudder Pedal Steering
Calibration.
±°nosewheel angle ....................
Ground .....................
Record results for an
uninterrupted control sweep to the
stops.
X
X
X
X
2.a.6 .......
Pitch Trim Indicator vs.
Surface Position Calibration.
±0.5° of computed trim surface
angle.
Ground .....................
...................................
X
X
X
X
2.a.7 .......
(Reserved) .......................
.
2.a.8 .......
Alignment of Cockpit
Throttle Lever vs. Selected Engine Parameter.
±5° of throttle lever angle, or
±3% N1 or ±03 EPR, or ±
torque. For propeller-driven
airplanes where the propeller
control levers do not have angular travel, a tolerance of
±0.8 inch (±2 cm.) applies.
Ground .....................
Requires simultaneous recording for
all engines. The
tolerances apply
against airplane
data and between
engines. In the
case of propeller
powered airplanes,
if a propeller lever
is present, it must
also be checked.
For airplanes with
throttle ‘‘detents,’’
all detents must be
presented. May be
a series of snapshot test results..
X
X
X
X
2.a.9 .......
Brake Pedal Position vs.
Force and Brake System Pressure
Calibation.
±5 lb (2.2 daN) or 10% force,
±150 psi (1.0 MPa) or ±10%
brake system pressure.
Ground .....................
Hydraulic system
pressure must be
related to pedal position through a
ground static test.
X
X
X
X
Full flight simulator
computer output
results may be
used to show compliance.
2.b ..........
Dynamic Control Tests.
X
X
‘‘n’’ is the sequential
period of a full
cycle of oscillation.
Refer to paragraph
3 of this attachment for more information. Static
and dynamic flight
control tests should
be accomplished at
the same feel or
impact pressures.
For the alternate
method (see paragraph 3 of this attachment).
The slow sweep is
the equivalent to
the static test
2.a.1. For the moderate and rapid
sweeps: ±2 lb (0.9
daN) or ±10% dynamic increment
above the static
force.
The purpose of the
test is to compare
full flight simulator
against design data
or equivalent
(3) Tests 2.b.1., 2.b.2., and 2.b.3 are not applicable if dynamic response is generated solely by use of airplane hardware in the full flight simulator. Power setting is that required for level flight unless otherwise specified.
sroberts on PROD1PC70 with RULES
2.b.1 .......
Pitch Control ....................
VerDate Aug<31>2005
01:08 Oct 28, 2006
For
underdamped
systems
±10% of time from 90% of initial displacement (0.9 Ad) to
first zero crossing and ±10
(n+1)% of period thereafter
±10% amplitude of first overshoot applied to all overshoots greater than 5% of initial displacement (.05 Ad). ±1
overshoot (first significant
overshoot must be matched).
For overdamped systems: ±10%
of time from 90% of initial displacement (0.9 Ad) to 10% of
initial displacement (0.1 Ad)
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Data must show normal control displacement in both
directions. Tolerances apply
against the absolute values of each
period (considered
independently).
Normal control displacement for this
test is 25% to 50%
of the maximum allowable pitch controller deflection for
flight conditions
limited by the maneuvering load envelope.
E:\FR\FM\30OCR2.SGM
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Simulator
Level
Information
notes
Tolerance
No.
Flight
Conditions
Test details
C
D
Data must show normal control displacement in both
directions. Tolerances apply
against the absolute values of each
period (considered
independently).
Normal control displacement for this
test is 25% to 50%
of maximum allowable roll controller
deflection for flight
conditions limited
by the maneuvering load envelope.
X
X
‘‘n’’ is the sequential
period of a full
cycle of oscillation.
Refer to paragraph
3 of this attachment for more information. Static
and dynamic flight
control tests should
be accomplished at
the same feel or
impact pressures.
For the alternate
method (see paragraph 3 of this attachment).
The slow sweep is
the equivalent to
the static test
2.a.2. For the moderate and rapid
sweeps: ±2 lb (0.9
daN) or ±10% dynamic increment
above the static
force.
‘‘n’’ is the sequential
period of a full
cycle of oscillation.
Refer to paragraph
3 of this attachment for more information. Static
and dynamic flight
control tests should
be accomplished at
the same feel or
impact pressures.
For the alternate
method (see paragraph 3 of this attachment).
The slow sweep is
the equivalent to
the static test
2.a.3. For the moderate and rapid
sweeps: ±2 lb (0.9
daN) or ±10% dynamic increment
above the static
force.
Title
A
B
Roll Control .....................
For
underdamped
systems:
±10% of time from 90% of initial displacement (0.9 Ad) to
first zero crossing, and ±10
(n+1)% of period thereafter.
±10% amplitude of first overshoot, applied to all overshoots greater than 5% of initial displacement (.05 Ad), ±1
overshoot (first significant
overshoot must be matched)
For overdamped systems: ±10%
of time from 90% of initial displacement (0.9 Ad) to 10% of
initial displacement (0.1 Ad)
2.b.3 .......
Yaw Control .....................
For
underdamped
systems:
±10% of time from 90% of initial displacement (0.9 Ad) to
first zero crossing, and ±10
(n+1)% of period thereafter
±10% amplitude of first overshoot, applied to all overshoots greater than 5% of initial displacement (.05 Ad), ±1
overshoot (first significant
overshoot must be matched).
For overdamped systems: ±10%
of time from 90% of initial displacement (0.9 Ad) to 10% of
initial displacement (0.1 Ad)
Takeoff, Cruise, and
Landing.
Data must show normal control displacement in both
directions. Tolerances apply
against the absolute values of each
period (considered
independently).
Normal control displacement for this
test is 25% to 50%
of full throw.
X
X
2.b.4 .......
sroberts on PROD1PC70 with RULES
2.b.2 .......
Takeoff, Cruise, and
Landing.
Small Control Inputs—
Pitch.
±0.15°/sec body pitch rate or
±20% of peak body pitch rate
applied throughout the time
history.
Approach or Landing
Control inputs must
be typical of minor
corrections made
while established
on an ILS approach course (approximately 0.5°/
sec to 2°/sec pitch
rate). The test
must be in both directions, showing
time history data
from 5 seconds before until at least 5
seconds after initiation of control
input.
CCA: Test in normal
and non-normal
control states.
X
X
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
63455
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Simulator
Level
Information
notes
Tolerance
No.
Flight
Conditions
Test details
C
D
Control inputs must
be typical of minor
corrections made
while established
on an ILS approach course (approximately 0.5°/
sec to 2°/sec roll
rate). The test
must be run in only
one direction; however, for airplanes
that exhibit nonsymmetrical behavior, the test must
include both directions. Time history
data must be recorded from 5 seconds before until at
least 5 seconds
after initiation of
control input.
CCA: Test in normal
and non-normal
control states.
X
X
Control inputs must
be typical of minor
corrections made
while established
on an ILS approach course (approximately 0.5°/
sec to 2°/sec yaw
rate). The test
must be run in only
one direction; however, for airplanes
that exhibit nonsymmetrical behavior, the test must
include both directions. Time history
data must be recorded from 5 seconds before until at
least 5 seconds
after initiation of
control input.
CCA: Test in normal
and non-normal
control states.
X
X
Title
A
2.b.5 .......
Small Control Inputs—
Roll.
±0.15°/sec body roll rate or
±20% of peak body roll rate
applied throughout the time
history.
Approach or landing
2.b.6 .......
Small Control Inputs—
Yaw.
±0.15°/sec body yaw rate or
±20% of peak body yaw rate
applied throughout the time
history.
Approach or landing
2.c ..........
Longitudinal Control Tests
sroberts on PROD1PC70 with RULES
Power setting is that required for level flight unless otherwise specified
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63456
Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Flight
Conditions
Tolerance
No.
Title
2.c.1 .......
Power Change Dynamics
±3 kt airspeed, ±100 ft (30 m)
altitude, ±20% or ±1.5° pitch
angle.
Approach ..................
2.c.2 .......
Flap/Slat Change Dynamics.
±3 kt airspeed, ±100 ft (30 m)
altitude, ±20% or ±1.5° angle.
2.c.3 .......
Spoiler/Speedb rake
Change Dynamics.
2.c.4 .......
sroberts on PROD1PC70 with RULES
Simulator
Level
Test details
Gear Change Dynamics ..
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Information
notes
A
B
C
D
Power is changed
from the thrust setting required for
approach or level
flight to maximum
continuous thrust
or go-around
power setting.
Record the uncontrolled free response from at
least 5 seconds
before the power
change is initiated
to 15 seconds after
the power change
is completed.
CCA: Test in normal
and non-normal
control states.
X
X
X
X
Takeoff through initial
flap retraction, and
approach to landing.
Record the uncontrolled free response from at
least 5 seconds
before the configuration change is
initiated to 15 seconds after the configuration change is
completed.
CCA: Test in normal
and non-normal
control states.
X
X
X
X
±3 kt airspeed, ±100 ft (30 m)
altitude, ±20% or ±1.5° pitch
angle.
Cruise .......................
Record the uncontrolled free response from at
least 5 seconds
before the configuration change is
initiated to 15 seconds after the configuration change is
completed. Record
results for both extension and retraction.
CCA: Test in normal
and non-normal
control states.
X
X
X
X
±3 kt airspeed, ±100 ft (30 m)
altitude, ±20% or ±1.5° pitch
angle.
Takeoff (retraction),
and Approach (extension).
Record the time history of uncontrolled
free response for a
time increment
from at least 5 seconds before the
configuration
change is initiated
to 15 seconds after
the configuration
change is completed.
CCA: Test in normal
and non-normal
control states.
X
X
X
X
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
63457
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Flight
Conditions
Tolerance
Title
2.c.5 .......
Longitudinal Trim .............
±0.5° stabilizer, ±1° elevator,
±1° pitch angle, ±5% net
thrust or equivalent.
Cruise, Approach,
and Landing.
2.c.6 .......
Longitudinal Maneuvering
Stability (Stick Force/g).
±5 lb (±2.2 daN) or ±10% pitch
controller force..
Alternative method: ±1° or ±10%
change of elevator
2.c.7 .......
sroberts on PROD1PC70 with RULES
No.
Longitudinal .....................
±5 lb (±2.2 daN) or ±10% pitch
controller force..
Alternative method: ±1° or ±10%
change of elevator.
Simulator
Level
Test details
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Information
notes
A
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B
C
D
Record steady-state
condition with
wings level and
thrust set for level
flight. May be a series of snapshot
tests.
CCA: Test in normal
and non-normal
control states.
X
X
X
X
Cruise, Approach,
and Landing.
Continuous time history data or a series of snapshot
tests may be used.
Record results up
to approximately
30° of bank for approach and landing
configurations.
Record results for
up to approximately 45° of bank
for the cruise configuration. The
force tolerance is
not applicable if
forces are generated solely by
the use of airplane
hardware in the full
flight simulator.
The alternative method applies to airplanes that do not
exhibit ‘‘stick-forceper-g’’ characteristics.
CCA: Test in normal
and non-normal
control states.
X
X
X
X
Approach ..................
Record results for at
least 2 speeds
above and 2
speeds below trim
speed. May be a
series of snapshot
test results. The
force tolerance is
not applicable if
forces are generated solely by
the use of airplane
hardware in the full
flight simulator.
The alternative method applies to airplanes that do not
exhibit speed stability characteristics.
CCA: Test in normal
and non-normal
control states.
X
X
X
X
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63458
Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Flight
Conditions
Tolerance
Simulator
Level
Test details
No.
Title
2.c.8 .......
Stall Characteristics ........
±3 kt airspeed for initial buffet,
stall
warning,
and
stall
speeds. Additionally, for those
simulators with reversible
flight control systems: ±10%
or ±5 lb (2.2 daN)) Stick/Column force (prior to ‘‘g break’’
only).
Second Segment
Climb, and Approach or Landing.
2.c.9 .......
Phugoid Dynamics ..........
±10% period, ±10% of time to
1⁄2 or double amplitude or
±.02 of damping ratio.
2.c.10 .....
Short Period Dynamics ...
2.c.11 .....
(Reserved)
2.d
Information
notes
A
B
C
D
The stall maneuver
must be entered
with thrust at or
near idle power
and wings level
(1g). Record the
stall warning signal
and initial buffet, if
applicable. Time
history data must
be recorded for full
staff and initiation
of recovery. The
stall warning signal
must occur in the
proper relation to
buffet/stall. Full
flight simulators of
airplanes exhibiting
a sudden pitch attitude change or ‘‘g
break’’ must demonstrate this characteristic.
CCA: Test in normal
and non-normal
control states.
X
X
X
X
Cruise .......................
The test must include
whichever is less
of the following:
Three full cycles
(six overshoots
after the input is
completed), or the
number of cycles
sufficient to determine time to 1⁄2 or
double amplitude.
CCA: Test in Nonnormal and nonnormal control
states.
X
X
X
X
±1.5° pitch angle or ±2°/sec Cruise .......................
pitch rate, ±0.10g acceleration.
CCA: Test in Normal
and Non-normal
control states.
X
X
Lateral Directional Tests
X
X
...............................................
..............................
..............................
Power setting is that required for level flight unless otherwise specified
sroberts on PROD1PC70 with RULES
2.d.1 .......
Minimum Control Speed,
Air (Vmca or Vmcl), per
Applicable Airworthiness Standard or Low
Speed Engine Inoperative Handling Characteristics in the Air.
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Takeoff or Landing
(whichever is most
critical in the airplane).
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Takeoff thrust must
be used on the operating engine(s).
A time history or a
series of snapshot
tests may be used.
CCA: Test in Normal and Non-normal control states.
E:\FR\FM\30OCR2.SGM
X
30OCR2
X
Low Speed Engine
Inoperative Handling may be governed by a performance or control
limit that prevents
demonstration of
Vmca in the conventional manner.
Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
63459
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Flight
Conditions
Tolerance
No.
Title
2.d.2 .......
Roll Response (Rate) ......
±10% or ±2°/sec roll rate. Additionally, for those simulators
of airplanes with reversible
flight control systems: ±10%
or ±3lb (1.3 daN) wheel force.
Cruise, and Approach
or Landing.
2.d.3 .......
Roll Response to Cockpit
Roll Controller Step
Input.
±10% or ±2° bank angle ............
2.d.4 .......
Spiral Stability .................
2.d.5 .......
2.d.6 .......
sroberts on PROD1PC70 with RULES
Simulator
Level
Test details
Information
notes
A
B
C
D
Record results for
normal roll controller deflection
(about one-third of
maximum roll controller travel). May
be combined with
step input of flight
deck roll controller
test (2.d.3).
X
X
X
X
Approach or Landing
Record from initiation
of roll through 10
seconds after control is returned to
neutral and released. May be
combined with roll
response (rate) test
(2.d.2).
CCA: Test in Normal
and Non-normal
control states.
X
X
X
X
Correct trend and ±2° or ±10%
bank angle in 20 seconds.
Alternate test requires correct
trend and ±2° aileron.
Cruise .......................
Record results for
both directions. Airplane data averaged from multiple
tests may be used.
As an alternate test,
demonstrate the
lateral control required to maintain
a steady turn with
a bank angle of approximately 30°
CCA: Test in Normal
and Non-normal
control states.
X
X
X
X
Engine Inoperative Trim ..
±1° rudder angle or ±1° tab
angle or equivalent pedal, ±2°
sideslip angle.
Second Segment
Climb, and Approach or Landing.
May be a series of
snapshot tests.
X
X
X
X
Rudder Response ...........
±2°/sec or ±10% yaw rate .........
Approach or Landing
Record results for
stability augmentation system ON
and OFF. A rudder
step input of 20%–
30% rudder pedal
throw is used.
CCA: Test in Normal
and Non-normal
control states.
X
X
X
X
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30OCR2
With wings level,
apply a step roll
control input using
approximately onethird of the roll controller travel. When
reaching approximately 20° to 30°
of bank, abruptly
return the roll controller to neutral
and allow approximately 10 seconds
of airplane free response.
The test should be
performed in a
manner similar to
that for which a
pilot is trained to
trim an engine failure condition. Second segment climb
test should be at
takeoff thrust. Approach or landing
test should be at
thrust for level
flight.
63460
Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Flight
Conditions
Tolerance
Simulator
Level
Test details
Title
2.d.7 .......
Dutch Roll (Yaw Damper
OFF).
±0.5 sec or ±10% of period,
±10% of time to 1⁄2 or double
amplitude or ±.02 of damping
ratio. ±20% or ±1 sec of time
difference between peaks of
bank and sideslip.
Cruise, and Approach
or Landing.
Record results for at
least 6 complete
cycles with stability
augmentation OFF.
CCA: Test in Normal
and Non-normal
control states.
2.d.8 .......
Steady State Sideslip ......
For given rudder position, ±2°
bank angle, ±1° sideslip
angle, ±10% or ±2° aileron,
±10% or ±5° spoiler or equivalent roll, controller position or
force. Additionally, for those
simulators of airplanes with
reversible flight control systems: ±10% or ±3 lb (1.3 daN)
wheel force ±10% or ±5 lb
(2.2 daN) rudder pedal force.
Approach or Landing
May be a series of
snapshot test results using at least
two rudder positions. Propeller
driven airplanes
must test in each
direction.
2.e ..........
Landings
2.e.1 .......
Normal Landing ...............
±3 kt airspeed, ±1.5° pitch
angle, ±1.5° angle of attack,
±10% or ±10 ft (3 m) height.
Additionally, for those simulators of airplanes with reversible flight control systems:
±10% or ±5 lbs (±2.2 daN)
stick/column force.
Landing .....................
Record results from a
minimum of 200 ft
(61 m) AGL to
nose-wheel touchdown..
CCA: Test in Normal
and Non-normal
control states
2.e.2 .......
Miminum Flap Landing ....
±3 kt airspeed, ±1.5° pitch
angle, ±1.5° angle of attack,
±10% or ±10 ft (3 m) height.
Additionally, for those simulators of airplanes with reversible flight control systems:
±10% or ±5 lbs (2.2 daN)
stick/column force.
Minimum Certified
Landing Flap Configuration.
Record results from a
minimum of 200 ft
(61 m) AGL to
nosewheel touchdown with airplane
at near Maximum
Landing Weight.
2.e.3 .......
Crosswind Landing ..........
±3 kt airspeed, ±1.5° pitch
angle, ±1.5° angle of attack,
±10% or ±10 ft (3 m) height
±2° bank angle, ±2° sideslip
angle, ±3° heading angle. Additionally, for those simulators
of airplanes with reversible
flight control systems: ±10%
or ±3 lbs (1.3 daN) wheel
force ±10% or ±5 lb (2.2 daN)
rudder pedal force.
Landing .....................
Record results from a
minimum of 200 ft
(61 m) AGL,
through nosewheel
touchdown, to 50%
decrease in main
landing gear touchdown speed.
2.e.4 .......
One Engine Inoperative
Landing.
±3 kt airspeed, ±1.5° pitch
angle, ±1.5° angle of attack,
±10% height or ±10 ft (3 m);
±2° bank angle, ±2° sideslip
angle, ±3° heading.
Landing .....................
2.e.5 .......
sroberts on PROD1PC70 with RULES
No.
Autopilot landing (if applicable).
±5 ft (1.5m) flare height, ±0.5
sec Tf, ±140 ft/min (.7 m/sec)
rate of descent at touchdown. ±10 ft (3 m) lateral deviation during rollout.
Landing .....................
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A
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notes
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B
C
D
X
X
X
X
X
X
X
X
X
X
X
X
X
X
Record results from a
minimum of 200 ft
(61 m) AGL,
through nosewheel
touchdown, to 50%
decrease in main
landing gear touchdown speed or less.
X
X
X
If autopilot provides
rollout guidance,
record lateral deviation from touchdown to a 50% decrease in main
landing gear touchdown speed or
less. Time of autopilot flare mode engage and main
gear touchdown
must be noted.
X
X
X
E:\FR\FM\30OCR2.SGM
X
30OCR2
Tests should be conducted with two
normal landing flap
settings (if applicable). One should
be at or near maximum certificated
landing weight. The
other should be at
light or medium
landing weight.
Test data should include information
on wind profile, for
a crosswind component of 60% of
the maximum described in the AFM
as measured at 33
ft (10m) above the
runway.
Tf = duration of flare
Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
63461
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Flight
Conditions
Tolerance
No.
Simulator
Level
Test details
Title
A
Information
notes
B
C
D
All engines operating,
autopilot, go around.
±3 kt airspeed, ±1.5° pitch
angle, ±1.5° angle of attack.
As per AFM ..............
Normal, all-enginesoperating, Go
Around with the
autopilot engaged
(if applicable) at
medium landing
weight.
CCA: Test in Normal
and Non-normal
control states
X
X
X
2.e.7 .......
One engine inoperative
go around.
±3 kt airspeed, ±1.5° pitch
angle, ±1.5° angle of attack,
±2° bank angle, ±2° slideslip
angle.
As per AFM ..............
The one engine inoperative go around
is required at near
maximum certificated landing
weight with the critical engine inoperative using manual
controls. If applicable, an additional
engine inoperative
go around test
must be accomplished with the
autopilot engaged.
CCA: Test in Normal
and Non-normal
control states
X
X
X
2.e.8 .......
Directional control (rudder
effectiveness) with
symmetric reverse
thrust.
±2°/sec yaw rate, ±5 kts airspeed.
Landing .....................
Record results starting from a speed
approximating
touchdown speed
to the minimum
thrust reverser operation speed. With
full reverse thrust,
apply yaw control
in both directions
until reaching minimum thrust reverser operation
speed.
X
X
X
2.e.9 .......
Directional control (rudder
effectiveness) with
symmetric reverse
thrust.
±5 kt airspeed, ±3° heading
angle.
Landing .....................
Maintain heading with
yaw control with
full reverse thrust
on the operating
engine(s). Record
results starting
from a speed approximating touchdown speed to a
speed at which
control of yaw cannot be maintained
or until reaching
minimum thrust reverser operation
speed, whichever
is higher. The tolerance applies to the
low speed end of
the data recording.
X
X
X
2.f ...........
sroberts on PROD1PC70 with RULES
2.e.6 .......
Ground Effect.
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63462
Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Flight
Conditions
Tolerance
No.
Title
A
±1° elevator or stabilizer angle,
±5% net thrust or equivalent,
±1° angle of attack, ±10%
height or ±5 ft (1.5 m), ±3 kt
airspeed, ±1° pitch angle.
Test to demonstrate
Ground Effect.
2.g ..........
Landing .....................
Takeoff and Landing
B
C
D
X
X
X
See paragraph 4,
Ground Effect, in
this attachment for
additional information.
X
The Ground Effect
model must be
validated by the
test selected and a
rationale must be
provided for selecting the particular
test.
See Attachment 5 ......................
Information
notes
X
See Attachment 5 for
information related
to Level A and B
simulators.
Requires windshear
models that provide training in the
specific skills needed to recognize
windshear phenomena and to
execute recovery
procedures. See
Attachment 5 for
tests, tolerances,
and procedures.
Windshear
Four tests, two takeoff
and two landing, with
one of each conducted
in still air and the other
with windshear active
to demonstrate
windshear models.
2.h ..........
Simulator
Level
Test details
Flight Maneuver and Envelope Protection Functions
The requirements of tests h(1) through (6) of this attachment are applicable to computer controlled airplanes
only. Time history results are required for simulator response to control inputs during entry into envelope protection limits including both normal and degraded control states if the function is different. See thrust as required to reach the envelope protection function
2.h.1 .......
Overspeed .......................
±5 kt airspeed ............................
Cruise .......................
...................................
X
X
X
2.h.2 .......
Minimum Speed ..............
±3 kt airspeed ............................
Takeoff, Cruise, and
Approach or Landing.
...................................
X
X
X
2.h.3 .......
Load Factor .....................
±0.1g normal load factor ............
Takeoff, Cruise .........
...................................
X
X
X
2.h.4 .......
Pitch Angle ......................
±1.5° pitch angle ........................
Cruise, Approach ......
...................................
X
X
X
2.h.5 .......
Bank Angle ......................
±2° or ±10% bank angle ............
Approach ..................
...................................
X
X
X
2.h.6 .......
Angle of Attack ................
±1.5° angle of attack ..................
Second Segment
Climb, and Approach or Landing.
...................................
X
X
X
Based on Simulator Capability ..
N/A ...........................
The test must demonstrate frequency
response of the
motion system.
X
X
X
3. Motion System
3.a .......... Frequency response.
(Reserved)
3.c ..........
(Reserved)
3.d ..........
sroberts on PROD1PC70 with RULES
3.b ..........
X
Motion system repeatability
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This test is not required as part of
continuing qualification evaluations, and should
be part of the
MQTG.
Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
63463
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Flight
Conditions
Tolerance
No.
Simulator
Level
Test details
Title
A
±0.05g actual platform linear acceleration.
3.e ..........
None .........................
A demonstration is
required and must
be made part of
the MQTG. The assessment procedures must be designed to ensure
that the motion
system hardware
and software (in
normal flight simulator operating
mode) continue to
perform as originally qualified.
B
C
D
X
X
X
X
(Reserved)
3.f ...........
(Reserved)
4. Visual System
4.a .......... Visual System Response Time: Relative responses of the motion system, visual system, and cockpit instruments must be coupled closely to provide integrated sensory cues. Visual change may start before motion
response, but motion acceleration must be initiated before completion of the visual scan of the first video
field containing different information
4.a.1 .......
See paragraph 14 of
this attachment for
additional information.
Latency
These systems must respond to abrupt input at
the pilot’s position.
sroberts on PROD1PC70 with RULES
Information
notes
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The response must not be prior
to that time when the airplane
responds and may respond
300 ms (or less) after the airplane responds under the
same conditions.
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N/A ...........................
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Simultaneously
record: 1) the output from the pilot’s
controller(s); 2) the
output from an accelerometer attached to the motion system platform located at an
acceptable location
near the pilots’
seats; 3) the output
signal to the visual
system display (including visual system analog
delays); and 4) the
output signal to the
pilot’s attitude indicator or an equivalent test approved
by the Administrator.
E:\FR\FM\30OCR2.SGM
X
30OCR2
X
The intent is to verify
that the simulator
provides instrument, motion, and
visual cues that
are, within the stated time delays, like
the airplane responses. For airplane response,
acceleration in the
appropriate, corresponding rotational axis is preferred. Simulator
Latency is measured from the start
of a control input to
the appropriate
perceivable change
in flight instrument
indication; visual
system response;
or motion system
response (this
does not include
airplane response
time as per the
manufacturer’s
data).
63464
Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Flight
Conditions
Tolerance
No.
Simulator
Level
Test details
Title
A
The response must not be prior
to that time when the airplane
responds and may respond
150 ms (or less) after the airplane responds under the
same conditions.
C
D
X
Simultaneously
record: 1) the output from the pilot’s
controller(s); 2) the
output from an accelerometer attached to the motion system platform located at an
acceptable location
near the pilots’
seats; 3) the output
signal to the visual
system display (including visual system analog
delays); and 4) the
output signal to the
pilot’s attitude indicator or an equivalent test approved
by the Administrator.
As an alternative to the Latency requirement a transport delay objective test may be
used to demonstrate that the simulator system does not exceed the specified limit.
The sponsor must measure all the delay encountered by a step signal migrating from
the pilot’s control through the control loading electronics and interfacing through all
the simulation software modules in the correct order, using a handshaking protocol,
finally through the normal output interfaces to the instrument displays, the motion
system, and the visual system
An SOC is required.
4.a.2 .......
N/A ...........................
B
Information
notes
X
A recordable start
time for the test
must be provided
with the pilot flight
control input. The
migration of the
signal must permit
normal computation time to be consumed and must
not alter the flow of
information through
the hardware/software system.
Transport Delay
The transport delay is
the time between
the control input
and the individual
hardware (i.e., instruments, motion
system, visual system) responses. If
Transport Delay is
the chosen method
to demonstrate relative responses, it
is expected that,
when reviewing
those existing tests
where latency can
be identified (e.g.,
short period, roll
response, rudder
response) the
sponsor and the
NSPM will apply
additional scrutiny
to ensure proper
simulator response.
The response must not be prior
to that time when the airplane
responds and may respond
300 ms (or less) after controller movement.
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.....................................
4.b ..........
The transport delay is
the time between
the control input
and the individual
hardware (i.e., instruments, motion
system, visual system) responses. If
Transport Delay is
the chosen method
to demonstrate relative responses, it
is expected that,
when reviewing
those existing tests
where latency can
be identified (e.g.,
short period, roll
response, rudder
response) the
sponsor and the
NSPM will apply
additional scrutiny
to ensure proper
simulator response.
N/A ...........................
..............................
The response must not be prior
to that time when the airplane
responds and may respond
150 ms (or less) after controller movement.
The response must not be prior
to that time when the airplane
responds and may respond
150 ms (or less) after controller movement.
N/A ...........................
..............................
X
X
N/A ...........................
..............................
X
X
X
Field of View
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X
response, rudder response) the sponsor and the NSPM
will apply additional
scrutiny to ensure
proper simulator
response.
Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
63465
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Flight
Conditions
Tolerance
No.
Simulator
Level
Test details
Title
4.b.1 .......
Continuous collimated
visual field of view.
4.b.2. ......
D
X
(Reserved)
4.d. .........
X
C
(Reserved)
4.c. .........
B
(Reserved)
4.b.3. ......
A
Information
notes
Surface contrast ratio
N/A ...........................
The ratio is calculated by dividing
the brightness level
of the center, bright
square (providing
at least 2 foot-lamberts or 7 cd/m2)
by the brightness
level of any adjacent dark square.
This requirement is
applicable to any
level of simulator
equipped with a
daylight visual system.
X
X
Measurements
should be made
using a 1° spot
photometer and a
raster drawn test
pattern filling the
entire visual scene
(all channels) with
a test pattern of
black and white
squares, 5° per
square, with a
white square in the
center of each
channel. During
contrast ratio testing, simulator aftcab and flight deck
ambient light levels
should be zero.
N/A ...........................
Measure the brightness of a white
square while
superimposing a
highlight on that
white square. The
use of calligraphic
capabilities to enhance the raster
brightness is acceptable; however,
measuring
lightpoints is not
acceptable. This
requirement is applicable to any
level of simulator
equipped with a
daylight visual system.
X
X
Measurements
should be made
using a 1° spot
photometer and a
raster drawn test
pattern filling the
entire visual scene
(all channels) with
a test pattern of
black and white
squares, 5° per
square, with a
white square in the
center of each
channel.
Not greater than three (3) arc
minutes.
sroberts on PROD1PC70 with RULES
Required as part of
MQTG but not required as part of
continuing evaluations.
Not less than six (6) foot-lamberts (20 cd/m2).
4.f ...........
N/A ...........................
Not less than 5:1 .......................
4.e. .........
Minimum continuous collimated
field of view providing 45°
horizontal and 30° vertical
field of view for each pilot
seat. Both pilot seat visual
systems must be operable simultaneously.
N/A ...........................
An SOC is required
and must include
the relevant calculations and an
explanation of
those calculations.
This requirement is
applicable to any
level of simulator
equipped with a
daylight visual system.
X
X
The eye will subtend
two arc minutes
when positioned on
a 3° glide slope,
6,876 ft slant range
from the centrally
located threshold
of a black runway
surface painted
with white threshold bars that are
16 ft wide with 4foot gaps between
the bars.
A vertical field of
view of 30° may be
insufficient to meet
visual ground segment requirements.
Highlight brightness
Surface resolution
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63466
Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Flight
Conditions
Tolerance
No.
4.g. .........
Title
A
B
Information
notes
C
D
Light point size
.....................................
Light point contrast ratio
(Reserved)
For Level C and D simulators.
4.i ...........
Not greater than six (6) arc-minutes.
N/A ...........................
An SOC is required
and must include
the relevant calculations and an
explanation of
those calculations.
This requirement is
applicable to any
level of simulator
equipped with a
daylight visual system.
X
X
Light point size
should be measured using a test
pattern consisting
of a centrally located single row of
light points reduced
in length until modulation is just discernible in each
visual channel. A
row of 48 lights will
form a 4° angle or
less.
Not less than 25:1. ....................
N/A ...........................
An SOC is required
and must include
the relevant calculations.
X
X
A 1° spot photometer
is used to measure
a square of at least
1° filled with light
points (where light
point modulation is
just discernible)
and compare the
results to the
measured adjacent
background. During
contrast ratio testing, simulator aftcab and flight deck
ambient light levels
should be zero.
The QTG must contain appropriate calculations and a
drawing showing the pertinent
data used to establish the airplane location and the segment of the ground that is
visible considering design
eyepoint, the airplane attitude,
cockpit cut-off angle, and a
visibility of 1200 ft (350 m)
RVR. Simulator performance
must be measured against
the QTG calculations. Sponsors must provide this data
for each simulator (regardless
of
previous
qualification
standards) to qualify the simulator for all instrument approaches. The data submitted
must include at least the following:.
(1) Static airplane dimensions
as follows:
(i) Horizontal and vertical
distance from main landing
gear
(MLG)
to
glideslope reception antenna.
(ii) Horizontal and vertical
distance from MLG to pilot’s eyepoint.
(iii) Static cockpit cutoff
angle.
(2) Approach data as follows:
(i) Identification of runway.
(ii) Horizontal distance from
runway
threshold
to
glideslope intercept with
runway.
4.h. .........
4.h.1. ......
4.h.2 .......
sroberts on PROD1PC70 with RULES
Simulator
Level
Test details
..............................
X
X
Pre-position for this
test is encouraged
but may be
achieved via manual or autopilot
control to the desired position.
Visual ground segment
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The simulator must
be verified for visual ground segment and visual
scene content for
the airplane in
landing configuration and a main
wheel height of
100 ft (30m) above
the touchdown
zone, on glide
slope with an RVR
value set at 1,200
ft (350m).
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
63467
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Flight
Conditions
Tolerance
No.
Simulator
Level
Test details
Title
A
.....................................
B
C
Information
notes
D
(iii) Glideslope angle.
(iv) Airplane pitch angle on
approach.
(3) Airplane data for manual
testing:
(i) Gross weight.
(ii) airplane configuration.
(iii) Approach airspeed.
5. (Reserved)
lllllllllllllllllllll
Begin Information
2. General
a. If relevant winds are present in the
objective data, the wind vector should be
clearly noted as part of the data presentation,
expressed in conventional terminology, and
related to the runway being used for test near
the ground.
b. The reader is encouraged to review the
Airplane Flight Simulator Evaluation
Handbook, Volumes I and II, published by
the Royal Aeronautical Society, London, UK,
and FAA Advisory Circulars (AC) 25–7, as
may be amended, Flight Test Guide for
Certification of Transport Category Airplanes,
and (AC) 23–8, as may be amended, Flight
Test Guide for Certification of Part 23
Airplanes, for references and examples
regarding flight testing requirements and
techniques.
End Information
lllllllllllllllllllll
sroberts on PROD1PC70 with RULES
Begin Information
3. Control Dynamics
a. General. The characteristics of an
airplane flight control system have a major
effect on handling qualities. A significant
consideration in pilot acceptability of an
airplane is the ‘‘feel’’ provided through the
flight controls. Considerable effort is
expended on airplane feel system design so
that pilots will be comfortable and will
consider the airplane desirable to fly. In
order for a FFS to be representative, it should
‘‘feel’’ like the airplane being simulated.
Compliance with this requirement is
determined by comparing a recording of the
control feel dynamics of the FFS to actual
airplane measurements in the takeoff, cruise
and landing configurations.
(1) Recordings such as free response to an
impulse or step function are classically used
to estimate the dynamic properties of
electromechanical systems. In any case, it is
only possible to estimate the dynamic
properties as a result of only being able to
estimate true inputs and responses.
Therefore, it is imperative that the best
possible data be collected since close
matching of the FFS control loading system
to the airplane system is essential. The
required dynamic control tests are described
in Table A2A of this attachment.
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(2) For initial and upgrade evaluations, the
QPS requires that control dynamics
characteristics be measured and recorded
directly from the flight controls (Handling
Qualities—Table A2A). This procedure is
usually accomplished by measuring the free
response of the controls using a step or
impulse input to excite the system. The
procedure should be accomplished in the
takeoff, cruise and landing flight conditions
and configurations.
(3) For airplanes with irreversible control
systems, measurements may be obtained on
the ground if proper pitot-static inputs are
provided to represent airspeeds typical of
those encountered in flight. Likewise, it may
be shown that for some airplanes, takeoff,
cruise, and landing configurations have like
effects. Thus, one may suffice for another. In
either case, engineering validation or
airplane manufacturer rationale should be
submitted as justification for ground tests or
for eliminating a configuration. For FFSs
requiring static and dynamic tests at the
controls, special test fixtures will not be
required during initial and upgrade
evaluations if the QTG shows both test
fixture results and the results of an alternate
approach (e.g., computer plots that were
produced concurrently and show satisfactory
agreement). Repeat of the alternate method
during the initial evaluation would satisfy
this test requirement.
b. Control Dynamics Evaluation. The
dynamic properties of control systems are
often stated in terms of frequency, damping
and a number of other classical
measurements. In order to establish a
consistent means of validating test results for
FFS control loading, criteria are needed that
will clearly define the measurement
interpretation and the applied tolerances.
Criteria are needed for underdamped,
critically damped and overdamped systems.
In the case of an underdamped system with
very light damping, the system may be
quantified in terms of frequency and
damping. In critically damped or
overdamped systems, the frequency and
damping are not readily measured from a
response time history. Therefore, the
following suggested measurements may be
used:
(1) For Level C and D simulators. Tests to
verify that control feel dynamics represent
the airplane should show that the dynamic
damping cycles (free response of the
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controls) match those of the airplane within
specified tolerances. The NSPM recognizes
that several different testing methods may be
used to verify the control feel dynamic
response. The NSPM will consider the merits
of testing methods based on reliability and
consistency. One acceptable method of
evaluating the response and the tolerance to
be applied is described below for the
underdamped and critically damped cases. A
sponsor using this method to comply with
the QPS requirements should perform the
tests as follows:
(a) Underdamped response. Two
measurements are required for the period, the
time to first zero crossing (in case a rate limit
is present) and the subsequent frequency of
oscillation. It is necessary to measure cycles
on an individual basis in case there are nonuniform periods in the response. Each period
will be independently compared to the
respective period of the airplane control
system and, consequently, will enjoy the full
tolerance specified for that period. The
damping tolerance will be applied to
overshoots on an individual basis. Care
should be taken when applying the tolerance
to small overshoots since the significance of
such overshoots becomes questionable. Only
those overshoots larger than 5 per cent of the
total initial displacement should be
considered. The residual band, labeled T(Ad)
on Figure A2A is ±5 percent of the initial
displacement amplitude Ad from the steady
state value of the oscillation. Only
oscillations outside the residual band are
considered significant. When comparing FFS
data to airplane data, the process should
begin by overlaying or aligning the FFS and
airplane steady state values and then
comparing amplitudes of oscillation peaks,
the time of the first zero crossing and
individual periods of oscillation. The FFS
should show the same number of significant
overshoots to within one when compared
against the airplane data. The procedure for
evaluating the response is illustrated in
Figure A2A.
(b) Critically damped and overdamped
response. Due to the nature of critically
damped and overdamped responses (no
overshoots), the time to reach 90 percent of
the steady state (neutral point) value should
be the same as the airplane within ±10
percent. Figure A2B illustrates the procedure.
(c) Special considerations. Control systems
that exhibit characteristics other than
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
sroberts on PROD1PC70 with RULES
classical overdamped or underdamped
responses should meet specified tolerances.
In addition, special consideration should be
given to ensure that significant trends are
maintained.
(2) Tolerances.
(a) The following table summarizes the
tolerances, T, for underdamped systems, and
‘‘n’’ is the sequential period of a full cycle
of oscillation. See Figure A2A of this
attachment for an illustration of the
referenced measurements.
T(P0) ±10% of P0
T(P1) ±20% of P1
T(P2) ±30% of P2
T(Pn) ±10(n+1)% of Pn
T(An) ±10% of A1
T(Ad) ±5% of Ad = residual band
Significant overshoots First overshoot and
±1 subsequent overshoots
(b) The following tolerance applies to
critically damped and overdamped systems
only. See Figure A2B for an illustration of the
reference measurements:
T(P0) ±10% of P0
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c. Alternate method for Control Dynamics
Evaluation. Another acceptable method of
evaluating the response and the tolerance to
be applied for airplanes with hydraulically
powered flight controls and artificial feel
systems is described below. Instead of free
response measurements, the system is
validated by measurements of control force
and rate of movement. A sponsor using this
alternate method to comply with the QPS
requirements should perform the tests as
follows:
(1) For each axis of pitch, roll and yaw, the
control should be forced to its maximum
extreme position for the following distinct
rates. These tests would be conducted at
typical taxi, takeoff, cruise and landing
conditions.
(a) Static test. Slowly move the control
such that approximately 100 seconds are
required to achieve a full sweep. A full
sweep is defined as movement of the
controller from neutral to the stop (usually
aft or right stop), then to the opposite stop,
then to the neutral position.
(b) Slow dynamic test. Achieve a full
sweep in approximately 10 seconds.
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(c) Fast dynamic test. Achieve a full sweep
in approximately 4 seconds.
(Note: Dynamic sweeps may be limited to
forces not exceeding 100 lb (44.5 daN).
(2) Tolerances.
(a) Static test. Same as tests 2.a.1., 2.a.2.,
and 2.a.3. in Table A2A in this attachment.
(b) Dynamic test. ±2 lb (±0.9 daN)or ±10
per cent on dynamic increment above static
test.
(c) The NSPM are open to alternative
means such as the one described above. Such
alternatives, however, would have to be
justified and appropriate to the application.
For example, the method described here may
not apply to all manufacturers’ systems and
certainly not to airplanes with reversible
control systems. Hence, each case shall be
considered on its own merit on an ad hoc
basis. If the NSPM finds that alternative
methods do not result in satisfactory
performance, then more conventionally
accepted methods must be used.
End Information
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BILLING CODE 4910–73–P
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Begin Information
4. Ground Effect
a. For an FFS to be used for take-off and
landing (not applicable to Level A simulators
in that the landing maneuver may not be
credited in a Level A simulator) it should
reproduce the aerodynamic changes that
occur in ground effect. The parameters
chosen for FFS validation should indicate
these changes.
(1) A dedicated test should be provided
that will validate the aerodynamic ground
effect characteristics.
(2) The organization performing the flight
tests may select appropriate test methods and
procedures to validate ground effect.
However, the flight tests should be performed
with enough duration near the ground to
sufficiently validate the ground-effect model.
b. The NSPM will consider the merits of
testing methods based on reliability and
consistency. Acceptable methods of
validating ground effect are described below.
If other methods are proposed, rationale
should be provided to conclude that the tests
performed validate the ground-effect model.
A sponsor using the methods described
below to comply with the QPS requirements
should perform the tests as follows:
(1) Level fly-bys. The level fly-bys should
be conducted at a minimum of three altitudes
within the ground effect, including one at no
more than 10% of the wingspan above the
ground, one each at approximately 30% and
50% of the wingspan where height refers to
main gear tire above the ground. In addition,
one level-flight trim condition should be
conducted out of ground effect (e.g., at 150%
of wingspan).
(2) Shallow approach landing. The shallow
approach landing should be performed at a
glide slope of approximately one degree with
negligible pilot activity until flare.
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c. The lateral-directional characteristics are
also altered by ground effect. For example,
because of changes in lift, roll damping is
affected. The change in roll damping will
affect other dynamic modes usually
evaluated for FFS validation. In fact, Dutch
roll dynamics, spiral stability, and roll-rate
for a given lateral control input are altered by
ground effect. Steady heading sideslips will
also be affected. These effects should be
accounted for in the FFS modeling. Several
tests such as crosswind landing, one engine
inoperative landing, and engine failure on
take-off serve to validate lateral-directional
ground effect since portions of these tests are
accomplished as the aircraft is descending
through heights above the runway at which
ground effect is an important factor.
5. [Reserved]
6. [Reserved]
7. [Reserved]
8. [Reserved]
9. [Reserved]
10. [Reserved]
11. [Reserved]
12. [Reserved]
13. [Reserved]
14. [Reserved]
15. [Reserved]
End Information
lllllllllllllllllllll
Begin Information
16. Alternative Data Sources, Procedures,
and Instrumentation: Level A and Level B
Simulators Only
a. In recent years, considerable progress
has been made in the improvement of
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63469
aerodynamic modeling techniques.
Additionally, those who have demonstrated
success in combining these modeling
techniques with minimal flight testing have
incorporated the use of highly mature flight
controls models and have had extensive
experience in comparing the output of their
effort with actual flight test data.
b. It has become standard practice for
experienced simulator manufacturers to use
modeling techniques to establish databases
for new simulator configurations while
awaiting the availability of actual flight test
data. The data generated from the
aerodynamic modeling techniques is then
compared to the flight test data when it
becomes available. The results of such
comparisons have become increasingly
consistent, indicating that these techniques,
applied with the appropriate experience, are
dependable and accurate for the development
of aerodynamic models for use in Level A
and Level B simulators.
c. Based on this history of successful
comparisons, the NSPM has concluded that
those who are experienced in the
development of aerodynamic models may
use modeling techniques to alter the method
for acquiring flight test data for Level A or
Level B simulators.
d. The information in Table A2E
(Alternative Data Sources, Procedures, and
Instrumentation) is presented to describe an
acceptable alternative to data sources for
simulator modeling and validation and an
acceptable alternative to the procedures and
instrumentation traditionally used to gather
such modeling and validation data.
(1) Alternative data sources that may be
used for part or all of a data requirement are
the Airplane Maintenance Manual, the
Airplane Flight Manual (AFM), Airplane
Design Data, the Type Inspection Report
(TIR), Certification Data or acceptable
supplemental flight test data.
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(2) The sponsor should coordinate with the
NSPM prior to using alternative data sources
in a flight test or data gathering effort.
e. The NSPM position regarding the use of
these alternative data sources, procedures,
and instrumentation is based on the
following presumptions:
(1) Data gathered through the alternative
means does not require angle of attack (AOA)
measurements or control surface position
measurements for any flight test. However,
AOA can be sufficiently derived if the flight
test program ensures the collection of
acceptable level, unaccelerated, trimmed
flight data. All of the simulator time history
tests that begin in level, unaccelerated, and
trimmed flight, including the three basic trim
tests and ‘‘fly-by’’ trims, can be a successful
validation of angle of attack by comparison
with flight test pitch angle. (Note: Due to the
criticality of angle of attack in the
development of the ground effects model,
particularly critical for normal landings and
landings involving cross-control input
applicable to Level B simulators, stable ‘‘flyby’’ trim data will be the acceptable norm for
normal and cross-control input landing
objective data for these applications.)
(2) The use of a rigorously defined and
fully mature simulation controls system
model that includes accurate gearing and
cable stretch characteristics (where
applicable), determined from actual aircraft
measurements. Such a model does not
require control surface position
measurements in the flight test objective data
in these limited applications.
(3) The authorized uses of Level A and
Level B simulators (as listed in the
appropriate Commercial, Instrument, or
Airline Transport Pilot and/or Type Rating
Practical Test Standards) for ‘‘initial,’’
‘‘transition,’’ or ‘‘upgrade’’ training, still
requires additional flight training and/or
flight testing/checking in the airplane or in
a Level C or Level D simulator.
f. The sponsor is urged to contact the
NSPM for clarification of any issue regarding
airplanes with reversible control systems.
Table A2E is not applicable to Computer
Controlled Aircraft full flight simulators.
g. Utilization of these alternate data
sources, procedures, and instrumentation
does not relieve the sponsor from compliance
with the balance of the information
contained in this document relative to Level
A or Level B FFSs.
h. The term ‘‘inertial measurement system’’
is used in the following table to include the
use of a functional global positioning system
(GPS).
End Information
lllllllllllllllllllll
TABLE A2E.—ALTERNATIVE DATA SOURCES, PROCEDURES, AND INSTRUMENTATION
Information
Sim
level
Table of objective tests
Alternative data sources, procedures, and
instrumentation
Notes and reminders
Test reference number and title
A
B
1.a.1. Performance. Taxi. Minimum
Radius turn.
X
X
TIR, AFM, or Design data may be used.
X
Data may be acquired by using a constant tiller
position, measured with a protractor or full rudder pedal application for steady state turn, and
synchronized video of heading indicator. If less
than full rudder pedal is used, pedal position
must be recorded.
1.a.2. Performance. Taxi. Rate of
Turn vs. Nosewheel Steering
Angle.
X
X
Preliminary certification data may be used. Data
may be acquired by using a stopwatch, calibrated airspeed, and runway markers during a
takeoff with power set before brake release.
Power settings may be hand recorded. If an
inertial measurement system is installed,
speed and distance may be derived from acceleration measurements.
1.b.2. Performance. Takeoff. Minimum
Control
Speed—ground
(Vmcg) using aerodynamic controls
only (per applicable airworthiness
standard) or low speed, engine inoperative ground control characteristics.
X
X
Data may be acquired by using an inertial measurement system and a synchronized video of:
The calibrated airplane instruments and the
force/position measurements of cockpit controls..
1.b.3. Performance. Takeoff. Minimum Unstick Speed (Vmu) or
equivalent test to demonstrate
early rotation takeoff characteristics.
X
X
Data may be acquired by using an inertial measurement system and a synchronized video of:
The calibrated airplane instruments and the
force/position measurements of cockpit controls.
1.b.4. Performance. Takeoff. Normal
Takeoff.
sroberts on PROD1PC70 with RULES
1.b.1. Performance. Takeoff. Ground
Acceleration Time and Distance.
X
X
A single procedure may not be adequate for all airplane steering systems, therefore appropriate measurement procedures must be devised and proposed for NSPM
concurrence.
Data may be acquired by using an inertial measurement system and a synchronized video of:
The calibrated airplane instruments and the
force/position measurements of cockpit controls. AOA can be calculated from pitch attitude and flight path.
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Rapid throttle reductions at speeds
near Vmcg may be used while recording appropriate parameters.
The nose wheel must be free to
caster, or equivalently freed of
sideforce generation.
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TABLE A2E.—ALTERNATIVE DATA SOURCES, PROCEDURES, AND INSTRUMENTATION—Continued
Information
Sim
level
Table of objective tests
Alternative data sources, procedures, and
instrumentation
Notes and reminders
Test reference number and title
A
B
1.b.5. Performance. Takeoff. Critical
Engine Failure during Takeoff.
X
X
Data may be acquired by using an inertial measurement system and a synchronized video of:
The calibrated airplane instruments and the
force/position measurements of cockpit controls.
Record airplane dynamic response
to engine failure and control inputs
required to correct flight path.
1.b.6. Performance. Takeoff. Crosswind Takeoff.
X
X
Data may be acquired by using an inertial measurement system and a synchronized video of:
The calibrated airplane instruments and the
force/position measurements of cockpit controls.
The ‘‘1:7 law’’ to 100 feet (30 meters) is an acceptable wind profile.
1.b.7. Performance.
jected Takeoff.
X
X
Data may be acquired with a synchronized video
of: Calibrated airplane instruments, thrust lever
position, engine parameters, and distance
(e.g., runway markers). A stopwatch is required.
1.b.8. Dynamic Engine Failure After
Takeoff.
N/A
N/A
1.c.1. Performance. Climb. Normal
Climb all engines operating..
X
X
Data may be acquired with a synchronized video
of: Calibrated airplane instruments and engine
power throughout the climb range.
1.c.2. Performance. Climb. One engine Inoperative Climb.
X
X
Data may be acquired with a synchronized video
of: Calibrated airplane instruments and engine
power throughout the climb range.
N/A
N/A
1.c.4. Performance. Climb. One Engine Inoperative Approach Climb
(if approved AFM requires specific
performance in icing conditions).
X
X
Data may be acquired with a synchronized video
of calibrated airplane instruments and engine
power throughout the climb range.
1.d.1. Cruise/Descent. Level flight
acceleration..
X
X
Data may be acquired with a synchronized video
of: calibrated airplane instruments, thrust lever
position, engine parameters, and elapsed time.
1.d.2. Cruise/Descent. Level flight
deceleration.
X
X
Data may be acquired with a synchronized video
of: Calibrated airplane instruments, thrust lever
position, engine parameters, and elapsed time.
1.d.3. Cruise Performance ................
N/A
N/A
1.d.4. Cruise/Descent. Idle descent ..
X
X
Data may be acquired with a synchronized video
of: calibrated airplane instruments, thrust lever
position, engine parameters, and elapsed time.
1.d.5. Cruise/Descent.
Descent.
Emergency
X
X
Data may be acquired with a synchronized video
of: calibrated airplane instruments, thrust lever
position, engine parameters, and elapsed time.
1.e.1. Performance. Stopping. Deceleration time and distance, using
manual application of wheel
brakes and no reverse thrust on a
dry runway.
X
X
Data may be acquired during landing tests using
a stopwatch, runway markers, and a synchronized video of: Calibrated airplane instruments, thrust lever position and the pertinent
parameters of engine power.
1.e.2. Performance. Ground. Deceleration Time and Distance, using
reverse thrust and no wheel
brakes.
X
X
Data may be acquired during landing tests using
a stop watch, runway markers, and a synchronized video of: Calibrated airplane instruments, thrust lever position and the pertinent
parameters of engine power.
Takeoff.
sroberts on PROD1PC70 with RULES
1.c.3. One Engine
Enroute Climb.
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Applicable only to Level C or Level D FSTDs.
Applicable only to Level C or Level D FSTDs.
Applicable only to Level C or Level D FSTDs.
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TABLE A2E.—ALTERNATIVE DATA SOURCES, PROCEDURES, AND INSTRUMENTATION—Continued
Information
Sim
level
Table of objective tests
Alternative data sources, procedures, and
instrumentation
Notes and reminders
A
B
1.e.3. Stopping Distance—wheel
brakes, and no reverse thrust on a
wet runway.
N/A
N/A
Applicable only to Level C and Level D FSTDs.
1.e.4. Stopping Distance—wheel
brakes, and no reverse thrust on
an icy runway.
N/A
N/A
Applicable only to Level C and Level D FSTDs.
1.f.1. Performance. Engines. Acceleration.
X
X
Data may be acquired with a synchronized video
recording of: engine instruments and throttle
position.
1.f.2. Performance. Engines. Deceleration.
X
X
Data may be acquired with a synchronized video
recording of: Engine instruments and throttle
position.
2.a.1.a. Handling Qualities. Static
Control Checks. Pitch Controller
Position vs. Force and Surface Position Calibration.
X
X
Surface position data may be acquired from
flight data recorder (FDR) sensor or, if no FDR
sensor, at selected, significant column positions (encompassing significant column position data points), acceptable to the NSPM,
using a control surface protractor on the
ground (for airplanes with reversible control
systems, this function should be accomplished
with winds less than 5 kts.). Force data may
be acquired by using a hand-held force gauge
at the same column position data points.
2.a.2.a. Handling Qualities. Static
Control Checks. Roll Controller
Position vs. Force and Surface Position Calibration.
X
X
Surface position data may be acquired from
flight data recorder (FDR) sensor or, if no FDR
sensor, at selected, significant wheel positions
(encompassing significant wheel position data
points), acceptable to the NSPM, using a control surface protractor on the ground (for airplanes with reversible control systems, this
function should be accomplished with winds
less than 5 kts.). Force data may be acquired
by using a hand-held force gauge at the same
wheel position data points.
2.a.3.a. Handling Qualities. Static
Control Checks. Rudder Pedal Position vs. Force and Surface Position Calibration.
X
X
Surface position data may be acquired from
flight data recorder (FDR) sensor or, if no FDR
sensor, at selected, significant rudder pedal
positions (encompassing significant rudder
pedal position data points), acceptable to the
NSPM, using a control surface protractor on
the ground (for airplanes with reversible control systems, this function should be accomplished with winds less than 5 kts.). Force
data may be acquired by using a hand-held
force gauge at the same rudder pedal position
data points.
2.a.4. Handling Qualities. Static Control Checks. Nosewheel Steering
Controller Force & Position.
sroberts on PROD1PC70 with RULES
Test reference number and title
X
X
Breakout data may be acquired with a hand-held
force gauge. The remainder of the force to the
stops may be calculated if the force gauge
and a protractor are used to measure force
after breakout for at least 25% of the total displacement capability.
2.a.5. Handling Qualities. Static Control Checks. Rudder Pedal Steering Calibration.
X
X
Data may be acquired through the use of force
pads on the rudder pedals and a pedal position measurement device, together with design
data for nose wheel position.
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TABLE A2E.—ALTERNATIVE DATA SOURCES, PROCEDURES, AND INSTRUMENTATION—Continued
Information
Sim
level
Table of objective tests
Alternative data sources, procedures, and
instrumentation
Notes and reminders
A
B
2.a.6. Handling Qualities. Static Control Checks. Pitch Trim Indicator
vs. Surface Position Calibration.
X
X
Data may be acquired through calculations.
2.a.7. Handling qualities. Static control tests. Pitch trim rate..
X
X
Data may be acquired by using a synchronized
video of pitch trim indication and elapsed time
through range of trim indication.
2.a.8. Handling Qualities. Static Control tests. Alignment of Cockpit
Throttle Lever Angle vs. Selected
engine parameter.
X
X
Data may be acquired through the use of a temporary throttle quadrant scale to document
throttle position. Use a synchronized video to
record steady state instrument readings or
hand-record steady state engine performance
readings.
2.a.9. Handling qualities. Static control tests. Brake pedal position vs.
force and brake system pressure
calibration.
X
X
Use of design or predicted data is acceptable.
Data may be acquired by measuring deflection
at ‘‘zero’’ and ‘‘maximum’’ and calculating deflections between the extremes using the airplane design data curve.
2.c.1. Handling qualities. Longitudinal
control tests. Power change dynamics.
X
X
Data may be acquired by using an inertial measurement system and a synchronized video of:
The calibrated airplane instruments and throttle position.
2.c.2. Handling qualities. Longitudinal
control tests. Flap/slat change dynamics.
X
X
Data may be acquired by using an inertial measurement system and a synchronized video of:
Calibrated airplane instruments and flap/slat
position.
2.c.3. Handling qualities. Longitudinal
control tests. Spoiler/speedbrake
change dynamics.
X
X
Data may be acquired by using an inertial measurement system and a synchronized video of:
The calibrated airplane instruments and spoiler/speedbrake position.
2.c.4. Handling qualities. Longitudinal
control tests. Gear change dynamics.
X
X
Data may be acquired by using an inertial measurement system and a synchronized video of:
The calibrated airplane instruments and gear
position.
2.c.5. Handling qualities. Longitudinal
control tests. Longitudinal trim.
X
X
Data may be acquired through use of an inertial
measurement system and a synchronized
video of: The cockpit controls position (previously calibrated to show related surface position) and the engine instrument readings.
2.c.6. Handling qualities. Longitudinal
control tests. Longitudinal maneuvering stability (stick force/g).
X
X
Data may be acquired through the use of an inertial measurement system and a synchronized video of: The calibrated airplane instruments; a temporary, high resolution bank
angle scale affixed to the attitude indicator;
and a wheel and column force measurement
indication.
2.c.7. Handling qualities. Longitudinal
control tests. Longitudinal static
stability.
X
X
Data may be acquired through the use of a synchronized video of: the airplane flight instruments and a hand-held force gauge.
2.c.8. Handling qualities. Longitudinal
control tests. Stall characteristics.
sroberts on PROD1PC70 with RULES
Test reference number and title
X
X
Data may be acquired through a synchronized
video recording of: A stopwatch and the calibrated airplane airspeed indicator. Handrecord the flight conditions and airplane configuration.
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Airspeeds may be cross-checked
with those in the TIR and AFM.
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TABLE A2E.—ALTERNATIVE DATA SOURCES, PROCEDURES, AND INSTRUMENTATION—Continued
Information
Sim
level
Table of objective tests
Alternative data sources, procedures, and
instrumentation
Notes and reminders
Test reference number and title
A
B
2.c.9. Handling qualities. Longitudinal
control tests. Phugoid dynamics.
X
X
Data may be acquired by using an inertial measurement system and a synchronized video of:
The calibrated airplane instruments and the
force/position measurements of cockpit controls.
X
Data may be acquired by using an inertial measurement system and a synchronized video of:
The calibrated airplane instruments and the
force/position measurements of cockpit controls.
2.c.10. Handling qualities. Longitudinal control tests. Short period dynamics.
X
X
Data may be acquired by using an inertial measurement system and a synchronized video of:
The calibrated airplane instruments and the
force/position measurements of cockpit controls.
2.d.2. Handling qualities. Lateral directional tests. Roll response (rate).
X
X
Data may be acquired by using an inertial measurement system and a synchronized video of:
The calibrated airplane instruments and the
force/position measurements of cockpit lateral
controls.
2.d.3. Handling qualities. Lateral directional tests. Roll response to
cockpit roll controller step input.
X
X
Data may be acquired by using an inertial measurement system and a synchronized video of:
The calibrated airplane instruments and the
force/position measurements of cockpit lateral
controls..
2.d.4. Handling qualities. Lateral directional tests. Spiral stability.
X
X
Data may be acquired by using an inertial measurement system and a synchronized video of:
The calibrated airplane instruments; the force/
position measurements of cockpit controls;
and a stopwatch.
2.d.5. Handling qualities. Lateral directional tests. Engine inoperative
trim.
X
X
Data may be hand recorded in-flight using high
resolution scales affixed to trim controls that
have been calibrated on the ground using protractors on the control/trim surfaces with winds
less than 5 kts..
OR
Data may be acquired during second segment
climb (with proper pilot control input for an engine-out condition) by using a synchronized
video of: The calibrated airplane instruments;
and the force/position measurements of cockpit controls
2.d.6. Handling qualities. Lateral directional tests. Rudder response.
X
X
Data may be acquired by using an inertial measurement system and a synchronized video of:
The calibrated airplane instruments; the force/
position measurements of rudder pedals.
2.d.7. Handling qualities. Lateral directional tests. Dutch roll, (yaw
damper OFF).
sroberts on PROD1PC70 with RULES
2.d.1. Handling qualities. Lateral directional tests. Minimum control
speed, air (Vmca or Vmci), per applicable airworthiness standard or
Low speed engine inoperative
handling characteristics in the air.
X
X
Data may be acquired by using an inertial measurement system and a synchronized video of:
The calibrated airplane instruments; the force/
position measurements of cockpit controls.
X
Data may be acquired by using an inertial measurement system and a synchronized video of:
The calibrated airplane instruments; the force/
position measurements of cockpit controls.
Ground track and wind corrected heading may
be used for sideslip angle..
2.d.8. Handling qualities. Lateral directional tests. Steady state sideslip.
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May be combined with step input of
cockpit roll controller test, 2.d.3
Trimming during second segment
climb is not a certification task and
should not be conducted until a
safe altitude is reached.
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TABLE A2E.—ALTERNATIVE DATA SOURCES, PROCEDURES, AND INSTRUMENTATION—Continued
Information
Sim
level
Table of objective tests
Test reference number and title
A
Alternative data sources, procedures, and
instrumentation
Notes and reminders
B
2.e.1. Handling qualities. Landings.
Normal landing.
X
Data may be acquired by using an inertial measurement system and a synchronized video of:
The calibrated airplane instruments; the force/
position measurements of cockpit controls.
2.e.3. Handling qualities. Landings.
Crosswind landing.
X
Data may be acquired by using an inertial measurement system and a synchronized video of:
The calibrated airplane instruments; the force/
position measurements of cockpit controls.
2.e.4. Handling qualities. Landings.
One engine inoperative landing.
X
Data may be acquired by using an inertial measurement system and a synchronized video of:
The calibrated airplane instruments; the force/
position measurements of cockpit controls.
Normal and lateral accelerations may be recorded in lieu of AOA and sideslip.
2.e.5. Handling qualities. Landings.
Autopilot landing (if applicable).
X
Data may be acquired by using an inertial measurement system and a synchronized video of:
the calibrated airplane instruments; the force/
position measurements of cockpit controls.
Normal and lateral accelerations may be recorded in lieu of AOA and sideslip.
2.e.6. Handling qualities. Landings.
All engines operating, autopilot, go
around.
X
Data may be acquired by using an inertial measurement system and a synchronized video of:
The calibrated airplane instruments; the force/
position measurements of cockpit controls.
Normal and lateral accelerations may be recorded in lieu of AOA and sideslip.
2.e.7. Handling qualities. Landings.
One engine inoperative go around.
X
Data may be acquired by using an inertial measurement system and a synchronized video of:
The calibrated airplane instruments; the force/
position measurements of cockpit controls.
Normal and lateral accelerations may be recorded in lieu of AOA and sideslip.
2.e.8. Handling qualities. Landings.
Directional control (rudder effectiveness with symmetric thrust).
X
Data may be acquired by using an inertial measurement system and a synchronized video of:
The calibrated airplane instruments; the force/
position measurements of cockpit controls.
Normal and lateral accelerations may be recorded in lieu of AOA and sideslip.
2.e.9. Handling qualities. Landings.
Directional control (rudder effectiveness with asymmetric reverse
thrust).
Data may be acquired by using an inertial measurement system and a synchronized video of:
The calibrated airplane instruments; the force/
position measurements of cockpit controls.
Normal and lateral accelerations may be recorded in lieu of AOA and sideslip.
2.f. Handling qualities. Ground effect.
Test to demonstrate ground effect.
X
sroberts on PROD1PC70 with RULES
Attachment 3 to Appendix A to Part 60—
Simulator Subjective Evaluation
Begin Information
1. Discussion
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Data may be acquired by using calibrated airplane instruments, an inertial measurement
system, and a synchronized video of: The calibrated airplane instruments; the force/position
measurements of cockpit controls.
a. The subjective tests provide a basis for
evaluating the capability of the simulator to
perform over a typical utilization period;
determining that the simulator accurately
simulates each required maneuver,
procedure, or task; and verifying correct
PO 00000
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operation of the simulator controls,
instruments, and systems. The items listed in
the following Tables are for simulator
evaluation purposes only. They must not be
used to limit or exceed the authorizations for
use of a given level of simulator as described
on the Statement of Qualification or as may
be approved by the TPAA.
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
b. The tests in Table A3A, Operations
Tasks, in this attachment, address pilot
functions, including maneuvers and
procedures (called flight tasks), and is
divided by flight phases. The performance of
these tasks by the NSPM includes an
operational examination of the visual system
and special effects. There are flight tasks
included to address some features of
advanced technology airplanes and
innovative training programs. For example,
‘‘high angle-of-attack maneuvering’’ is
included to provide a required alternative to
‘‘approach to stalls’’ for airplanes employing
flight envelope protection functions.
c. The tests in Table A3A, Operations
Tasks, and Table A3G, Instructor Operating
Station of this attachment, address the
overall function and control of the simulator
including the various simulated
environmental conditions; simulated
airplane system operations (normal,
abnormal, and emergency); visual system
displays; and special effects necessary to
meet flight crew training, evaluation, or flight
experience requirements.
d. All simulated airplane systems functions
will be assessed for normal and, where
appropriate, alternate operations. Normal,
abnormal, and emergency operations
associated with a flight phase will be
assessed during the evaluation of flight tasks
or events within that flight phase. Simulated
airplane systems are listed separately under
‘‘Any Flight Phase’’ to ensure appropriate
attention to systems checks. Operational
navigation systems (including inertial
navigation systems, global positioning
systems, or other long-range systems) and the
associated electronic display systems will be
evaluated if installed. The NSP pilot will
include in his report to the TPAA, the effect
of the system operation and any system
limitation.
e. Simulators demonstrating a satisfactory
circling approach will be qualified for the
circling approach maneuver and may be
approved for such use by the TPAA in the
sponsor’s FAA-approved flight training
program. To be considered satisfactory, the
circling approach will be flown at maximum
gross weight for landing, with minimum
visibility for the airplane approach category,
and must allow proper alignment with a
landing runway at least 90° different from the
instrument approach course while allowing
the pilot to keep an identifiable portion of the
airport in sight throughout the maneuver
(reference—14 CFR 91.175(e)).
f. At the request of the TPAA, the NSPM
may assess a device to determine if it is
capable of simulating certain training
activities in a sponsor’s training program,
such as a portion of a Line Oriented Flight
Training (LOFT) scenario. Unless directly
related to a requirement for the qualification
level, the results of such an evaluation would
not affect the qualification level of the
simulator. However, if the NSPM determines
that the simulator does not accurately
simulate that training activity, the simulator
would not be approved for that training
activity.
g. Previously qualified simulators with
certain early generation Computer Generated
Image (CGI) visual systems, are limited by
either the capability of the Image Generator
or the display system used. These systems
are:
(1) Early CGI visual systems that are
excepted from the requirement of including
runway numbers as a part of the specific
runway marking requirements are:
(a) Link NVS and DNVS.
(b) Novoview 2500 and 6000.
(c) FlightSafety VITAL series up to, and
including, VITAL III, but not beyond.
(d) Redifusion SP1, SP1T, and SP2.
(2) Some early CGI visual systems are
excepted from the requirement of including
runway numbers, unless the runways are
used for LOFT training sessions. These LOFT
airport models require runway numbers but
only for the specific runway end (one
direction) used in the LOFT session. The
systems required to display runway numbers
only for LOFT scenes are:
(a) FlightSafety VITAL IV.
(b) Redifusion SP3 and SP3T.
(c) Link-Miles Image II.
(3) The following list of previously
qualified CGI and display systems are
incapable of generating blue lights. These
systems are not required to have accurate
taxi-way edge lighting:
(a) Redifusion SP1.
(b) FlightSafety Vital IV.
(c) Link-Miles Image II and Image IIT.
(d) XKD displays (even though the XKD
image generator is capable of generating blue
colored lights, the display cannot
accommodate that color).
The NSPM will evaluate each device to
determine the appropriate qualification level
based on the limitations of the visual system.
End Information
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TABLE A3A.—FUNCTIONS AND SUBJECTIVE TESTS
<<< QPS requirements >>>
Simulator level
Item
No.
Operations tasks
A
B
C
D
Tasks in this table are subjecgt to evaluation if appropriate for the airplane simulated as indicated in the SOQ Configuration List and/or the level of simulator qualification involved. Items not installed or not functional on the simulator and, therefore, not appearing on the SOQ Configuration List, are not required to be listed as exceptions on the SOQ.
1. ............................
Preparation For Flight.
Preflight. Accomplish a functions check of all switches, indicators, systems, and equipment at all crewmembers’ and instructors’ stations and determine that the flight deck design and functions are identical to that of the airplane simulated.
2. ............................
X
X
X
Surface Operations (Pre-Take-Off).
2.a. .........................
X
Engine Start.
Normal start .................................................................................................................................................
X
X
X
X
2.a.2. .......
Alternate start procedures ...........................................................................................................................
X
X
X
X
2.a.3. .......
Abnormal starts and shutdowns (e.g., hot/hung start, tail pipe fire) ...........................................................
X
X
X
X
2.b. ..................
sroberts on PROD1PC70 with RULES
2.a.1. .......
Pushback/Powerback ..................................................................................................................................
X
X
X
2.c. ..................
Taxi.
2.c.1. ........
Thrust response ...........................................................................................................................................
X
X
X
X
2.c.2. ........
Power lever friction ......................................................................................................................................
X
X
X
X
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
TABLE A3A.—FUNCTIONS AND SUBJECTIVE TESTS—Continued
<<< QPS requirements >>>
Simulator level
Item
No.
Operations tasks
A
B
C
D
X
X
X
X
X
X
2.c.3. ........
Ground handling ..........................................................................................................................................
2.c.4. ........
Nose wheel scuffing ....................................................................................................................................
2.c.5. ........
Brake operation (normal and alternate/emergency) ....................................................................................
X
X
X
X
2.c.6. ........
Brake fade (if applicable) .............................................................................................................................
X
X
X
X
3. ............................
3.a. ..................
Take-off.
Normal.
3.a.1. .......
Airplane/engine parameter relationships .....................................................................................................
X
X
X
X
3.a.2. .......
Acceleration characteristics (motion) ...........................................................................................................
X
X
X
X
3.a.3. .......
Nose wheel and rudder steering .................................................................................................................
X
X
X
X
3.a.4. .......
Crosswind (maximum demonstrated) ..........................................................................................................
X
X
X
X
3.a.5. .......
Special performance (e.g., reduced V1, max de-rate, short field operations) ............................................
X
X
X
X
3.a.6. .......
Low visibility take-off ...................................................................................................................................
X
X
X
X
3.a.7. .......
Landing gear, wing flap leading edge device operation .............................................................................
X
X
X
X
3.a.8. .......
Contaminated runway operation .................................................................................................................
X
X
3.b. ..................
Abnormal/emergency
3.b.1. .......
Rejected Take-off ........................................................................................................................................
X
X
X
X
3.b.2. .......
Rejected special performance (e.g., reduced V1, max de-rate, short field operations) ..............................
X
X
X
X
3.b.3. .......
With failure of most critical engine at most critical point, continued take-off ..............................................
X
X
X
X
3.b.4. .......
With wind shear ...........................................................................................................................................
X
X
X
X
3.b.5. .......
Flight control system failures, reconfiguration modes, manual reversion and associated handling ..........
X
X
X
X
3.b.6. .......
Rejected takeoff with brake fade .................................................................................................................
X
X
3.b.7. .......
Rejected, contaminated runway ..................................................................................................................
X
X
(i).
4. ............................
Climb.
4.a. ..................
Normal. ........................................................................................................................................................
X
X
X
X
4.b. ..................
One or more engines inoperative ................................................................................................................
X
X
X
X
5. ............................
Cruise.
5.a. ..................
Performance characteristics (speed vs. power) ..........................................................................................
X
X
X
X
5.b. ..................
High altitude handling ..................................................................................................................................
X
X
X
X
5.c. ..................
High Mach number handling (Mach tuck, Mach buffet) and recovery (trim change) .................................
X
X
X
X
5.d. ..................
Overspeed warning (in excess of Vmo or Mmo) ...........................................................................................
X
X
X
X
5.e. ..................
High IAS handling ........................................................................................................................................
X
X
X
X
sroberts on PROD1PC70 with RULES
6. ............................
Maneuvers.
6.a. ..................
High angle of attack, approach to stalls, stall warning, buffet, and g-break (take-off, cruise, approach,
and landing configuration).
X
X
X
X
6.b. ..................
Flight envelope protection (high angle of attack, bank limit, overspeed, etc) ............................................
X
X
X
X
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
TABLE A3A.—FUNCTIONS AND SUBJECTIVE TESTS—Continued
<<< QPS requirements >>>
Simulator level
Item
No.
Operations tasks
A
B
C
D
6.c. ..................
Turns with/without speedbrake/spoilers deployed .......................................................................................
X
X
X
X
6.d. ..................
Normal and steep turns ...............................................................................................................................
X
X
X
X
6.e. ..................
In flight engine shutdown and restart (assisted and windmill) ....................................................................
X
X
X
X
6.f. ...................
Maneuvering with one or more engines inoperative, as appropriate ..........................................................
X
X
X
X
6.g. ..................
Specific flight characteristics (e.g., direct lift control) ..................................................................................
X
X
X
X
6.h. ..................
Flight control system failures, reconfiguration modes, manual reversion and associated handling ..........
X
X
X
X
7. ............................
Descent.
7.a. ..................
Normal .........................................................................................................................................................
X
X
X
X
7.b. ..................
Maximum rate (clean and with speedbrake, etc) ........................................................................................
X
X
X
X
7.c. ..................
With autopilot ...............................................................................................................................................
X
X
X
X
7.d. ..................
Flight control system failures, reconfiguration modes, manual reversion and associated handling ..........
X
X
X
X
8. ............................
Instrument Approaches and Landing.
Those instrument approach and landing tests relevant to the simulated airplane type are selected from
the following list. Some tests are made with limiting wind velocities, under windshear conditions, and
with relevant system failures, including the failure of the Flight Director. If Standard Operating Procedures allow use autopilot for non-precision approaches, evaluation of the autopilot will be included.
Level A simulators are not authorized to credit the landing maneuver.
8.a. ..................
Precision.
8.a.1. ...............
PAR .............................................................................................................................................................
X
X
X
X
8.a.2. ...............
CAT I/GBAS (ILS/MLS) published approaches ...........................................................................................
X
X
X
X
(i) Manual approach with/without flight director including landing ..............................................................
X
X
X
X
(ii) Autopilot/autothrottle coupled approach and manual landing ................................................................
X
X
X
X
(iii) Manual approach to DH and go-around all engines. ............................................................................
X
X
X
X
(iv) Manual one engine out approach to DH and go-around ......................................................................
X
X
X
X
(v) Manual approach controlled with and without flight director to 30 m (100 ft) below CAT I minima.
A. With cross-wind (maximum demonstrated) .....................................................................................
B. With windshear ................................................................................................................................
X
X
X
X
X
X
X
X
(vi) Autopilot/autothrottle coupled approach, one engine out to DH and go-around approach, one engine out to DH and go-around.
X
X
X
X
(vii) Approach and landing with minimum/standby electrical power ...........................................................
X
X
X
X
CAT II/GBAS (ILS/MLS) published approaches. .........................................................................................
X
X
X
X
(i) Autopilot/autothrottle coupled approach to DH and landing ...................................................................
X
X
X
X
(ii) Autopilot/autothrottle coupled approach to DH and go-around .............................................................
X
X
X
X
(iii) Autocoupled approach to DH and manual go-around ..........................................................................
X
X
X
X
(iv) Category II published approach (auto-coupled, autothrottle) ................................................................
X
X
X
X
CAT III/GBAS (ILS/MLS) published approaches .........................................................................................
X
X
X
X
(i) Autopilot/autothrottle coupled approach to land and rollout ...................................................................
X
X
X
X
(ii) Autopilot/autothrottle coupled approach to DH/Alert Height and go-around .........................................
X
X
X
X
sroberts on PROD1PC70 with RULES
8.a.3. .......
8.a.4. .......
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
TABLE A3A.—FUNCTIONS AND SUBJECTIVE TESTS—Continued
<<< QPS requirements >>>
Simulator level
Item
No.
Operations tasks
A
C
D
(iii) Autopilot/autothrottle coupled approach to land and rollout with one engine out .................................
X
X
X
X
(iv) Autopilot/autothrottle coupled approach to DH/Alert Height and go-around with one engine out .......
X
X
X
X
(v) Autopilot/autothrottle coupled approach (to land or to go around) ........................................................
A. With generator failure ......................................................................................................................
B. With 10 knot tail wind ......................................................................................................................
C. With 10 knot crosswind ...................................................................................................................
8.b. ..................
B
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
Non-precision.
8.b.1. .......
NDB .............................................................................................................................................................
X
X
X
X
8.b.2. .......
VOR, VOR/DME, VOR/TAC ........................................................................................................................
X
X
X
X
8.b.3. .......
RNAV (GNSS/GPS) ....................................................................................................................................
X
X
X
X
8.b.4. .......
ILS LLZ (LOC), LLZ(LOC)/BC .....................................................................................................................
X
X
X
X
8.b.5. .......
ILS offset localizer .......................................................................................................................................
X
X
X
X
8.b.6. .......
Direction finding facility (ADF/SDF) .............................................................................................................
X
X
X
X
8.b.7. .......
Airport surveillance radar (ASR) ..................................................................................................................
X
X
X
X
9. ............................
Visual Approaches (Visual Segment) And Landings
Flight simulators with visual systems, which permit completing a special approach procedure in accordance with applicable
regulations, may be approved for that particular approach procedure
Maneuvering, normal approach and landing, all engines operating with and without visual approach aid
guidance.
X
X
X
X
9.b. ..................
Approach and landing with one or more engines inoperative ....................................................................
X
X
X
X
9.c. ..................
Operation of landing gear, flap/slats and speedbrakes (normal and abnormal) ........................................
X
X
X
X
9.d. ..................
Approach and landing with crosswind (max. demonstrated) ......................................................................
X
X
X
X
9.e. ..................
Approach to land with windshear on approach ...........................................................................................
X
X
X
X
9.f. ...................
Approach and landing with flight control system failures, reconfiguration modes, manual reversion and
associated handling (most significant degradation which is probable).
X
X
X
X
9.g. ..................
Approach and landing with trim malfunctions .............................................................................................
X
X
X
X
9.g.1. .......
Longitudinal trim malfunction .......................................................................................................................
X
X
X
X
9.g.2. .......
Lateral-directional trim malfunction ..............................................................................................................
X
X
X
X
9.h. ..................
Approach and landing with standby (minimum) electrical/hydraulic power ................................................
X
X
X
X
9.i. ...................
Approach and landing from circling conditions (circling approach) ............................................................
X
X
X
X
9.j. ...................
Approach and landing from visual traffic pattern ........................................................................................
X
X
X
X
9.k. ..................
Approach and landing from non-precision approach ..................................................................................
X
X
X
X
9.l. ...................
Approach and landing from precision approach .........................................................................................
X
X
X
X
9.m. .................
sroberts on PROD1PC70 with RULES
9.a. ..................
Approach procedures with vertical guidance (APV), e.g., SBAS. ...............................................................
X
X
X
X
10. ..........................
Missed Approach.
10.a. ................
All engines ...................................................................................................................................................
X
X
X
X
10.b. ................
One or more engine(s) out ..........................................................................................................................
X
X
X
X
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
TABLE A3A.—FUNCTIONS AND SUBJECTIVE TESTS—Continued
<<< QPS requirements >>>
Simulator level
Item
No.
Operations tasks
A
10.c. ................
11. ..........................
With flight control system failures, reconfiguration modes, manual reversion and associated handling ...
B
C
D
X
X
X
X
Surface Operations (Landing roll and taxi).
11.a. ................
Spoiler operation .........................................................................................................................................
X
X
X
X
11.b. ................
Reverse thrust operation .............................................................................................................................
X
X
X
X
11.c. ................
Directional control and ground handling, both with and without reverse thrust ..........................................
X
X
X
11.d. ................
Reduction of rudder effectiveness with increased reverse thrust (rear pod-mounted engines) .................
X
X
X
11.e. ................
Brake and anti-skid operation with dry, wet, and icy conditions .................................................................
X
X
11.f. .................
Brake operation, to include auto-braking system where applicable ...........................................................
12. ..........................
12.a. ................
X
X
X
X
Any Flight Phase.
Airplane and engine systems operation.
Air conditioning and pressurization (ECS) ..................................................................................................
X
X
X
X
12.a.2. .....
De-icing/anti-icing ........................................................................................................................................
X
X
X
X
12.a.3. .....
Auxiliary power unit (APU) ..........................................................................................................................
X
X
X
X
12.a.4. .....
Communications ..........................................................................................................................................
X
X
X
X
12.a.5. .....
Electrical ......................................................................................................................................................
X
X
X
X
12.a.6. .....
Fire and smoke detection and suppression ................................................................................................
X
X
X
X
12.a.7. .....
Flight controls (primary and secondary) ......................................................................................................
X
X
X
X
12.a.8. .....
Fuel and oil, hydraulic and pneumatic ........................................................................................................
X
X
X
X
12.a.9. .....
Landing gear ................................................................................................................................................
X
X
X
X
12.a.10. ...
Oxygen ........................................................................................................................................................
X
X
X
X
12.a.11. ...
Engine ..........................................................................................................................................................
X
X
X
X
12.a.12. ...
Airborne radar ..............................................................................................................................................
X
X
X
X
12.a.13. ...
Autopilot and Flight Director ........................................................................................................................
X
X
X
X
12.a.14. ...
Collision avoidance systems. (e.g., (E)GPWS, TCAS) ...............................................................................
X
X
X
X
12.a.15. ...
Flight control computers including stability and control augmentation .......................................................
X
X
X
X
12.a.16. ...
Flight display systems .................................................................................................................................
X
X
X
X
12.a.17. ...
Flight management computers ....................................................................................................................
X
X
X
X
12.a.18. ...
Head-up guidance, head-up displays ..........................................................................................................
X
X
X
X
12.a.19. ...
Navigation systems .....................................................................................................................................
X
X
X
X
12.a.20. ...
Stall warning/avoidance ...............................................................................................................................
X
X
X
X
12.a.21. ...
Wind shear avoidance equipment ...............................................................................................................
X
X
X
X
12.a.22. ...
sroberts on PROD1PC70 with RULES
12.a.1. .....
Automatic landing aids ................................................................................................................................
X
X
X
X
X
X
X
X
X
X
12.b. ................
Airborne procedures
12.b.1. .....
Holding .........................................................................................................................................................
12.b.2. .....
Air hazard avoidance (Traffic, Weather) .....................................................................................................
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
TABLE A3A.—FUNCTIONS AND SUBJECTIVE TESTS—Continued
<<< QPS requirements >>>
Simulator level
Item
No.
Operations tasks
A
B
C
D
12.b.3. .....
Windshear. ...................................................................................................................................................
X
X
12.b.4. .....
Effects of airframe ice ..................................................................................................................................
X
X
12.c. ................
Engine shutdown and parking.
12.c.1. ......
Engine and systems operation ....................................................................................................................
X
X
X
X
12.c.2. ......
Parking brake operation ..............................................................................................................................
X
X
X
X
Table A3B [Reserved]
Table A3C [Reserved]
Table A3D [Reserved]
Table A3E [Reserved]
Table A3F [Reserved]
TABLE A3G.— FUNCTIONS AND SUBJECTIVE TESTS
<<< QPS requirements >>>
Simulator level
Item
number
Operations tasks
A
B
C
D
Functions in this table are subject to evaluation only if appropriate for the airplane and/or the system is installed on the
specific simular.
1. ............................
Simulator Power Switch(es) ........................................................................................................................
2. ............................
X
X
X
X
Airplane conditions.
2.a. ..................
Gross weight, center of gravity, fuel loading and allocation .......................................................................
X
X
X
X
2.b. ..................
Airplane systems status ...............................................................................................................................
X
X
X
X
2.c. ..................
Ground crew functions (e.g., ext. power, push back) .................................................................................
X
X
X
X
3. ............................
Airports.
3.a. ..................
Number and selection ..................................................................................................................................
X
X
X
X
3.b. ..................
Runway selection ........................................................................................................................................
X
X
X
X
3.c. ..................
Runway surface condition (e.g., rough, smooth, icy, wet) ..........................................................................
X
X
3.d. ..................
Preset positions (e.g., ramp, gate, #1 for takeoff, takeoff position, over FAF) ...........................................
X
X
X
X
3.e. ..................
Lighting controls ..........................................................................................................................................
X
X
X
X
4. ............................
Environmental controls.
Visibility (statute miles (kilometers)) ............................................................................................................
X
X
X
X
4.b. ..................
Runway visual range (in feet (meters)) .......................................................................................................
X
X
X
X
4.c. ..................
Temperature ................................................................................................................................................
X
X
X
X
4.d. ..................
Climate conditions (e.g., ice, snow, rain) ....................................................................................................
X
X
X
X
4.e. ..................
Wind speed and direction ............................................................................................................................
X
X
X
X
4.f. ...................
Windshear ....................................................................................................................................................
X
X
4.g. ..................
sroberts on PROD1PC70 with RULES
4.a ...................
Clouds (base and tops) ...............................................................................................................................
X
X
X
X
5. ............................
Airplane system malfunctions (Inserting and deleting malfunctions into the simulator) .............................
X
X
X
X
6. ............................
Locks, Freezes, and Repositioning
X
X
X
X
6.a. ..................
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
TABLE A3G.— FUNCTIONS AND SUBJECTIVE TESTS—Continued
<<< QPS requirements >>>
Simulator level
Item
number
Operations tasks
A
B
C
D
6.b. ..................
Position (geographic) freeze/release ...........................................................................................................
X
X
X
X
6.c. ..................
Repositioning (locations, freezes, and releases). .......................................................................................
X
X
X
X
6.d. ..................
Ground speed control ..................................................................................................................................
X
X
X
X
7. ............................
Remote IOS .................................................................................................................................................
X
X
X
X
8. ............................
Sound Controls On/ off/ adjustment ............................................................................................................
X
X
X
X
9. ............................
Motion / Control Loading System.
9.a. ..................
On / off / emergency stop ............................................................................................................................
X
X
X
X
9.b. ..................
Crosstalk (motion response in a given degree of freedom not perceptible in other degrees of freedom)
X
X
X
X
9.c. ..................
Smoothness (no perceptible ‘‘turn-around bump’’ as the direction of motion reverses with the simulator
being ‘‘flown’’ normally).
X
X
X
X
10. ...................
Observer Seats / Stations. Position / Adjustment / Positive restraint system. ...........................................
X
X
X
X
lllllllllllllllllllll
Begin Information
sroberts on PROD1PC70 with RULES
1. Introduction
a. The following is an example test
schedule for an Initial/Upgrade evaluation
that covers the majority of the requirements
set out in the Functions and Subjective test
requirements. It is not intended that the
schedule be followed line by line, rather, the
example should be used as a guide for
preparing a schedule that is tailored to the
airplane, sponsor, and training task.
b. Functions and subjective tests should be
planned. This information has been
organized as a reference document with the
considerations, methods, and evaluation
notes for each individual aspect of the
simulator task presented as an individual
item. In this way the evaluator can design
their own test plan, using the appropriate
sections to provide guidance on method and
evaluation criteria. Two aspects should be
present in any test plan structure:
(1) An evaluation of the simulator to
determine that it replicates the aircraft and
performs reliably for an uninterrupted period
equivalent to the length of a typical training
session.
(2) The simulator should be capable of
operating reliably after the use of training
device functions such as repositions or
malfunctions.
c. A detailed understanding of the training
task will naturally lead to a list of objectives
that the simulator should meet. This list will
form the basis of the test plan. Additionally,
once the test plan has been formulated, the
initial conditions and the evaluation criteria
should be established. The evaluator should
consider all factors that may have an
influence on the characteristics observed
during particular training tasks in order to
make the test plan successful.
VerDate Aug<31>2005
01:08 Oct 28, 2006
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2. Events
a. Initial Conditions.
(1) Airport;
(2) QNH;
(3) Temperature;
(4) Wind/Crosswind;
(5) Zero Fuel Weight/Fuel/Gross Weight/
Center of Gravity
b. Initial Checks.
(1) Documentation of Simulator.
(a) Simulator Acceptance Test Manuals.
(b) Simulator Approval Test Guide.
(c) Technical Logbook Open Item List.
(d) Daily Functional Pre-flight Check.
(2) Documentation of User/Carrier Flight
Logs.
(a) Simulator Operating/Instructor Manual.
(b) Difference List (Aircraft/Simulator).
(c) Flight Crew Operating Manuals.
(d) Performance Data for Different Fields.
(e) Crew Training Manual.
(f) Normal/Abnormal/Emergency
Checklists.
(3) Simulator External Checks.
(a) Appearance and Cleanliness.
(b) Stairway/Access Bridge.
(c) Emergency Rope Ladders.
(d) ‘‘Motion On’’/’’Flight in Progress’’
Lights.
(4) Simulator Internal Checks.
(a) Cleaning/Disinfecting Towels (for
cleaning oxygen masks).
(b) Cockpit Layout (compare with
difference list).
(5) Equipment.
(a) Quick Donning Oxygen Masks.
(b) Head Sets.
(c) Smoke Goggles.
(d) Sun Visors.
(e) Escape Rope.
(f) Chart Holders.
(g) Flashlights.
(h) Fire Extinguisher (inspection date).
(i) Crash Axe.
(j) Gear Pins.
c. Power Supply and APU Start Checks.
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(1) Batteries and Static Inverter.
(2) APU Start with Battery.
(3) APU Shutdown using Fire Handle.
(4) External Power Connection.
(5) APU Start with External Power.
(6) Abnormal APU Start/Operation.
d. Cockpit Checks.
(1) Cockpit Preparation Checks.
(2) FMC Programming.
(3) Communications and Navigational Aids
Checks.
e. Engine Start.
(1) Before Start Checks.
(2) Battery Start with Ground Air Supply
Unit.
(3) Engine Crossbleed Start.
(4) Normal Engine Start.
(5) Abnormal Engine Starts.
(6) Engine Idle Readings.
(7) After Start Checks.
f. Taxi Checks.
(1) Pushback/Powerback.
(2) Taxi Checks.
(3) Ground Handling Check:
(a) Power required to initiate ground roll.
(b) Thrust response.
(c) Nose Wheel and Pedal Steering.
(d) Nosewheel Scuffing.
(e) Perform 180 degree turns.
(f) Brakes Response and Differential
Braking using Normal, Alternate and
Emergency.
(g) Brake Systems.
(h) Eye height and fore/aft position.
(4) Runway Roughness.
g. Visual Scene—Ground Assessment.
(Select 3 different visual models and
perform the following checks with Day, Dusk
and Night selected, as appropriate):
(1) Visual Controls.
(a) Daylight, Dusk, Night Scene Controls.
(b) Cockpit ‘‘Daylight’’ ambient lighting.
(c) Environment Light Controls.
(d) Runway Light Controls.
(e) Taxiway Light Controls.
(2) Scene Content.
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(a) Ramp area for buildings, gates,
airbridges, maintenance ground equipment,
parked aircraft.
(b) Daylight shadows, night time light
pools.
(c) Taxiways for correct markings, taxiway/
runway, marker boards, CAT I & II/III hold
points, taxiway shape/grass areas, taxiway
light (positions and colors).
(d) Runways for correct markings, lead-off
lights, boards, runway slope, runway light
positions, and colors, directionality of
runway lights.
(e) Airport environment for correct terrain
and, significant features.
(f) Visual scene aliasing, color, and
occulting levels.
(3) Ground Traffic Selection.
(4) Environment Effects.
(a) Low cloud scene.
(i) Rain:
(A) Runway surface scene.
(B) Windshield wiper—operation and
sound.
(ii) Hail:
(A) Runway surface scene.
(B) Windshield wiper—operation and
sound.
(b) Lightning/thunder.
(c) Snow/ice runway surface scene.
(d) Fog.
h. Takeoff.
(Select one or several of the following test
cases):
(1) T/O Configuration Warnings.
(2) Engine Takeoff Readings.
(3) Rejected Takeoff (Dry/Wet/Icy Runway)
and check the following:
(a) Autobrake function.
(b) Anti-skid operation.
(c) Motion/visual effects during
deceleration.
(d) Record stopping distance (use runway
plot or runway lights remaining).
(Continue taxiing along the runway while
applying brakes and check the following).
(e) Center line lights alternating red/white
for 2000 feet/600 meters.
(f) Center line lights all red for 1000 feet/
300 m.
(g) Runway end, red stop bars.
(h) Braking fade effect.
(i) Brake temperature indications.
(4) Engine Failure between VI and V2.
(5) Normal Takeoff:
(a) During ground roll check the following:
(i) Runway rumble.
(ii) Acceleration cues.
(iii) Groundspeed effects.
(iv) Engine sounds.
(v) Nosewheel and rudder pedal steering.
(b) During and after rotation, check the
following:
(i) Rotation characteristics.
(ii) Column force during rotation.
(iii) Gear uplock sounds/bumps.
(iv) Effect of slat/flap retraction during
climbout.
(6) Crosswind Takeoff (check the
following):
(a) Tendency to turn into or out of the
wind.
(b) Tendency to lift upwind wing as
airspeed increases.
(7) Windshear during Takeoff (check the
following):
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(a) Controllable during windshear
encounter.
(b) Performance adequate when using
correct techniques.
(c) Windshear Indications satisfactory.
(d) Motion cues satisfactory (particularly
turbulence).
(8) Normal Takeoff with Control
Malfunction.
(9) Low Visibility T/O (check the
following):
(a) Visual cues.
(b) Flying by reference to instruments.
(c) SID Guidance on LNAV.
i. Climb Performance.
Select one or several of the following test
cases:
(1) Normal Climb—Climb while
maintaining recommended speed profile and
note fuel, distance and time.
(2) Single Engine Climb—Trim aircraft in
a zero wheel climb at V2.
Note: Up to 5° bank towards the operating
engine(s) is permissible. Climb for 3 minutes
and note fuel, distance, and time. Increase
speed toward en route climb speed and
retract flaps. Climb for 3 minutes and note
fuel, distance, and time.
j. Systems Operation During Climb.
Check normal operation and malfunctions
as appropriate for the following systems:
(1) Air conditioning/Pressurization/
Ventilation.
(2) Autoflight.
(3) Communications.
(4) Electrical.
(5) Fuel.
(6) Icing Systems.
(7) Indicating and Recording systems.
(8) Navigation/FMS.
(9) Pneumatics.
k. Cruise Checks.
(Select one or several of the following test
cases):
(1) Cruise Performance.
(2) High Speed/High Altitude Handling
(check the following):
(a) Overspeed warning.
(b) High Speed buffet.
(c) Aircraft control satisfactory.
(d) Envelope limiting functions on
Computer Controlled Airplanes.
(Reduce airspeed to below level flight
buffet onset speed, start a turn, and check the
following:)
(e) High Speed buffet increases with G
loading.
(Reduce throttles to idle and start descent,
deploy the speedbrake, and check the
following:)
(f) Speedbrake indications.
(g) Symmetrical deployment.
(h) Airframe buffet.
(i) Aircraft response hands off.
(3) Yaw Damper Operation.
(Switch off yaw dampers and autopilot.
Initiate a Dutch roll and check the following:)
(a) Aircraft dynamics.
(b) Simulator motion effects.
(Switch on yaw dampers, re-initiate a
Dutch roll and check the following:)
(c) Damped aircraft dynamics.
(4) APU Operation.
(5) Engine Gravity Feed.
(6) Engine Shutdown and Driftdown
Check: FMC operation Aircraft performance.
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(7) Engine Relight.
l. Descent.
Select one of the following test cases:
(1) Normal Descent Descend while
maintaining recommended speed profile and
note fuel, distance and time.
(2) Cabin Depressurization/Emergency
Descent
m. Medium Altitude Checks.
(Select one or several of the following test
cases)
(1) High Angle of Attack/Stall. Trim the
aircraft at 1.4 Vs, establish 1 kt/sec2
deceleration rate, and check the following—
(a) System displays/operation satisfactory.
(b) Handling characteristics satisfactory.
(c) Stall and Stick shaker speed.
(d) Buffet characteristics and onset speed.
(e) Envelope limiting functions on
Computer Controlled Airplanes.
(Recover to straight and level flight and
check the following:)
(f) Handling characteristics satisfactory.
(2) Turning Flight.
(Roll aircraft to left, establish a 30° to 45°
bank angle, and check the following:)
(a) Stick force required, satisfactory.
(b) Wheel requirement to maintain bank
angle.
(c) Slip ball response, satisfactory.
(d) Time to turn 180°.
(Roll aircraft from 45° bank one way to 45°
bank the opposite direction while
maintaining altitude and airspeed—check the
following:)
(e) Controllability during maneuver.
(3) Degraded flight controls.
(4) Holding Procedure (check the
following:)
(a) FMC operation.
(b) Auto pilot auto thrust performance.
(5) Storm Selection (check the following:)
(a) Weather radar controls.
(b) Weather radar operation.
(c) Visual scene corresponds with WXR
pattern.
(Fly through storm center, and check the
following:)
(d) Aircraft enters cloud.
(e) Aircraft encounters representative
turbulence.
(f) Rain/hail sound effects evident.
(As aircraft leaves storm area, check the
following:)
(g) Storm effects disappear.
(6) TCAS (check the following:)
(a) Traffic appears on visual display.
(b) Traffic appears on TCAS display(s).
(As conflicting traffic approaches, take
relevant avoiding action, and check the
following:)
(c) Visual and TCAS system displays.
n. Approach And Landing.
Select one or several of the following test
cases while monitoring flight control and
hydraulic systems for normal operation and
with malfunctions selected:
(1) Flaps/Gear Normal Operation (Check
the following:)
(a) Time for extension/retraction.
(b) Buffet characteristics.
(2) Normal Visual Approach and Landing.
Fly a normal visual approach and
landing—check the following:
(a) Aircraft handling.
(b) Spoiler operation.
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(c) Reverse thrust operation.
(d) Directional control on the ground.
(e) Touchdown cues for main and nose
wheel.
(f) Visual cues.
(g) Motion cues.
(h) Sound cues.
(i) Brake and Anti-skid operation.
(3) Flaps/Gear Abnormal Operation or with
hydraulic malfunctions.
(4) Abnormal Wing Flaps/Slats Landing.
(5) Manual Landing with Control
Malfunction.
(a) Aircraft handling.
(b) Aircraft handling.
(c) Radio Aids and instruments.
(d) Visual scene content and cues.
(e) Motion cues.
(f) Sound cues.
(6) Non-precision Approach—All Engines
Operating.
(a) Aircraft handling.
(b) Aircraft handling.
(c) Radio Aids and instruments.
(d) Visual scene content and cues.
(e) Motion cues.
(f) Sound cues.
(7) Circling Approach.
(a) Aircraft handling.
(b) Aircraft handling.
(c) Radio Aids and instruments.
(d) Visual scene content and cues.
(e) Motion cues.
(f) Sound cues.
(8) Non-precision Approach—One Engine
Inoperative.
(a) Aircraft handling.
(b) Aircraft handling.
(c) Radio Aids and instruments.
(d) Visual scene content and cues.
(e) Motion cues.
(f) Sound cues.
(9) One Engine Inoperative Go-around.
(a) Aircraft handling.
(b) Aircraft handling.
(c) Radio Aids and instruments.
(d) Visual scene content and cues.
(e) Motion cues.
(f) Sound cues.
(10) CAT I Approach and Landing with
raw-data ILS.
(a) Aircraft handling.
(b) Aircraft handling.
(c) Radio Aids and instruments.
(d) Visual scene content and cues.
(e) Motion cues.
(f) Sound cues.
(11) CAT I Approach and Landing with
Limiting Crosswind.
(a) Aircraft handling.
(b) Aircraft handling.
(c) Radio Aids and instruments.
(d) Visual scene content and cues.
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(e) Motion cues.
(f) Sound cues.
(12) CAT I Approach with Windshear.
Check the following:
(a) Controllable during windshear
encounter.
(b) Performance adequate when using
correct techniques.
(c) Windshear indications/warnings.
(d) Motion cues (particularly turbulence).
(13) CAT II Approach and Automatic GoAround.
(14) CAT III Approach and Landing—
System Malfunctions.
(15) CAT III Approach and Landing—1
Engine Inoperative.
(16) GPWS evaluation.
o. Visual Scene—In-Flight Assessment.
Select three (3) different visual models and
perform the following checks with ‘‘day,’’
‘‘dusk,’’ and ‘‘night’’ (as appropriate)
selected. Reposition the aircraft at or below
2000 feet within 10 nm of the airfield. Fly the
aircraft around the airport environment and
assess control of the visual system and
evaluate the visual scene content as
described below:
(1) Visual Controls.
(a) Daylight, Dusk, Night Scene Controls.
(b) Cockpit ambient lighting during
‘‘daylight’’ conditions.
(c) Environment Light Controls.
(d) Runway Light Controls.
(e) Taxiway Light Controls.
(f) Approach Light Controls.
(2) Scene Content.
(a) Airport environment for correct terrain
and significant features.
(b) Runways for correct markings, runway
slope, directionality of runway lights.
(c) Visual scene for aliasing, colour, and
occulting.
Reposition the aircraft to a long, final
approach for an ‘‘ILS runway.’’ Select flight
freeze when the aircraft is 5-statute miles
(sm)/8-kilometers (km) out and on the glide
slope.
Check the following:
(3) Scene content.
(a) Airfield features.
(b) Approach lights.
(c) Runway definition.
(d) Runway definition.
(e) Runway edge lights and VASI lights.
(f) Strobe lights.
Release flight freeze. Continue flying the
approach with NP engaged. Select flight
freeze when aircraft is 3 sm/5 km out and on
the glide slope. Check the following:
(4) Scene Content.
(a) Runway centerline light.
(b) Taxiway definition and lights.
Release flight freeze and continue flying
the approach with A/P engaged. Select flight
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freeze when aircraft is 2 sm/3 km out and on
the glide slope. Check the following:
(5) Scene content.
(a) Runway threshold lights.
(b) Touchdown zone lights. At 200 ft radio
altitude and still on glide slope, select Flight
Freeze. Check the following:
(6) Scene content.
(a) Runway markings.
Set the weather to Category I conditions
and check the following:
(7) Scene content.
(a) Visual ground segment.
Set the weather to Category II conditions,
release Flight Freeze, re-select Flight Freeze
at 100 feet radio altitude, and check the
following:
(8) Scene content.
(a) Visual ground segment.
Select night/dusk (twilight) conditions and
check the following:
(9) Scene content.
(a) Runway markings visible within
landing light lobes.
Set the weather to Category III conditions,
release Flight Freeze, re-select Flight Freeze
at 50 feet radio altitude and check the
following:
(10) Scene content.
(a) Visual ground segment.
Set WX to ‘‘missed approach’’ conditions,
release Flight Freeze, re-select Flight Freeze
at 15 feet radio altitude, and check the
following:
(11) Scene content.
(a) Visual ground segment.
When on the ground, stop the aircraft. Set
0 feet RVR, ensure strobe/beacon lights are
switched on and check the following:
(12) Scene content.
(a) Visual effect of strobe and beacon.
Reposition to final approach, set weather to
‘‘Clear,’’ continue approach for an automatic
landing, and check the following:
(13) Scene content.
(a) Visual cues during flare to assess sink
rate.
(b) Visual cues during flare to assess Depth
perception.
(c) Cockpit height above ground.
p. After Landing Operations.
(1) After Landing Checks.
(2) Taxi back to gate (Check the following:)
(a) Visual model satisfactory.
(b) Parking brake operation satisfactory.
(3) Shutdown Checks.
q. Crash Function.
(1) Gear-up Crash.
(2) Excessive rate of descent Crash.
(3) Excessive bank angle Crash.
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Table of Contents
Title of Sample
Figure A4A—Sample Letter, Request for
Initial, Upgrade, or Reinstatement
Evaluation
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Figure A4B—Attachment: FSTD Information
Form
Figure A4C—Sample Qualification Test
Guide Cover Page
Figure A4D—Sample Statement of
Qualification—Certificate
Figure A4E—Sample Statement of
Qualification—Configuration List
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Figure A4F—Sample Statement of
Qualification ‘‘ List of Qualified Tasks
Figure A4G—Sample Continuing
Qualification Evaluation Requirements
Page
Figure A4H—Sample MQTG Index of
Effective FSTD Directives
BILLING CODE 4910–73–P
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Sample Documents
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Attachment 5 to Appendix A to Part 60—
Simulator Qualification Requirements for
Windshear Training Program Use
1. Applicability
lllllllllllllllllllll
Begin QPS Requirements
This attachment applies to all simulators,
regardless of qualification level, that are used
to satisfy the training requirements of an
FAA-approved low-altitude windshear flight
training program, or any FAA-approved
training program that addresses windshear
encounters.
End QPS Requirements
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2. Statement of Compliance and Capability
(SOC)
lllllllllllllllllllll
Begin QPS Requirements
a. The sponsor must submit an SOC
confirming that the aerodynamic model is
based on flight test data supplied by the
airplane manufacturer or other approved data
provider. The SOC must also confirm that
any change to environmental wind
parameters, including variances in those
parameters for windshear conditions, once
inserted for computation, result in the correct
simulated performance. This statement must
also include examples of environmental
wind parameters currently evaluated in the
simulator (such as crosswind takeoffs,
crosswind approaches, and crosswind
landings).
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b. For simulators without windshear
warning, caution, or guidance hardware in
the original equipment, the SOC must also
state that the simulation of the added
hardware and/or software, including
associated cockpit displays and
annunciations, replicates the system(s)
installed in the airplane. The statement must
be accompanied by a block diagram depicting
the input and output signal flow, and
comparing the signal flow to the equipment
installed in the airplane.
End QPS Requirements
lllllllllllllllllllll
3. Models
lllllllllllllllllllll
Begin QPS Requirements
The windshear models installed in the
simulator software used for the qualification
evaluation must do the following:
a. Provide cues necessary for recognizing
windshear onset and potential performance
degradation requiring a pilot to initiate
recovery procedures. The cues must include
all of the following, as may be appropriate for
the appropriate portion of the flight
envelope:
(1) Rapid airspeed change of at least ±15
knots (kts).
(2) Stagnation of airspeed during the
takeoff roll.
(3) Rapid vertical speed change of at least
±500 feet per minute (fpm).
(4) Rapid pitch change of at least ±5°.
b. Be adjustable in intensity (or other
parameter to achieve an intensity effect) to at
least two (2) levels so that upon encountering
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the windshear the pilot may identify its
presence and apply the recommended
procedures for escape from such a
windshear.
(1) If the intensity is lesser, the
performance capability of the simulated
airplane in the windshear permits the pilot
to maintain a satisfactory flightpath; and
(2) If the intensity is greater, the
performance capability of the simulated
airplane in the windshear does not permit
the pilot to maintain a satisfactory flightpath
(crash).
Note: The means used to accomplish the
‘‘nonsurvivable’’ scenario of paragraph 3.b.(2)
of this attachment, that involve operational
elements of the simulated airplane, must
reflect the dispatch limitations of the
airplane.
c. Be available for use in the FAAapproved windshear flight training program.
End QPS Requirements
lllllllllllllllllllll
4. Demonstrations
lllllllllllllllllllll
Begin QPS Requirements
a. The sponsor must identify one
survivable takeoff windshear training model
and one survivable approach windshear
training model. The wind components of the
survivable models must be presented in
graphical format so that all components of
the windshear are shown, including
initiation point, variance in magnitude, and
time or distance correlations. The simulator
must be operated at the same gross weight,
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airplane configuration, and initial airspeed in
all of the following situations:
(1) Takeoff—through calm air.
(2) Takeoff—through the first selected
survivable windshear.
(3) Approach—through calm air.
(4) Approach—through the second selected
survivable windshear.
b. In each of these four situations, at an
‘‘initiation point’’ (i.e., where windshear
onset is or should be recognized), the
recommended procedures for windshear
recovery are applied and the results are
recorded as specified in paragraph 5 of this
attachment.
c. These recordings are made without
inserting programmed random turbulence.
Turbulence that results from the windshear
model is to be expected, and no attempt may
be made to neutralize turbulence from this
source.
d. The definition of the models and the
results of the demonstrations of all four (4)
cases described in paragraph 4.a of this
attachment, must be made a part of the
MQTG.
End QPS Requirements
lllllllllllllllllllll
5. Recording Parameters
lllllllllllllllllllll
Begin QPS Requirements
a. In each of the four MQTG cases, an
electronic recording (time history) must be
made of the following parameters:
(1) Indicated or calibrated airspeed.
(2) Indicated vertical speed.
(3) Pitch attitude.
(4) Indicated or radio altitude.
(5) Angle of attack.
(6) Elevator position.
(7) Engine data (thrust, N1, or throttle
position).
(8) Wind magnitudes (simple windshear
model assumed).
b. These recordings must be initiated at
least 10 seconds prior to the initiation point,
and continued until recovery is complete or
ground contact is made.
End QPS Requirements
lllllllllllllllllllll
6. Equipment Installation and Operation
lllllllllllllllllllll
Begin QPS Requirements
All windshear warning, caution, or
guidance hardware installed in the simulator
must operate as it operates in the airplane.
For example, if a rapidly changing wind
speed and/or direction would have caused a
windshear warning in the airplane, the
simulator must respond equivalently without
instructor/evaluator intervention.
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End QPS Requirements
lllllllllllllllllllll
7. Qualification Test Guide
lllllllllllllllllllll
Begin QPS Requirements
a. All QTG material must be forwarded to
the NSPM.
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b. A simulator windshear evaluation will
be scheduled in accordance with normal
procedures. Recurrent evaluation schedules
will be used to the maximum extent possible.
c. During the on-site evaluation, the
evaluator will ask the operator to run the
performance tests and record the results. The
results of these on-site tests will be compared
to those results previously approved and
placed in the QTG or MQTG, as appropriate.
d. QTGs for new (or MQTGs for upgraded)
simulators must contain or reference the
information described in paragraphs 2, 3, 4,
and 5 of this attachment.
End QPS Requirements
lllllllllllllllllllll
8. Subjective Evaluation
lllllllllllllllllllll
Begin Information
The NSPM will fly the simulator in at least
two of the available windshear scenarios to
subjectively evaluate simulator performance
as it encounters the programmed windshear
conditions.
a. One scenario will include parameters
that enable the pilot to maintain a
satisfactory flightpath.
b. One scenario will include parameters
that will not enable the pilot to maintain a
satisfactory flightpath (crash).
c. Other scenarios may be examined at the
NSPM’s discretion.
End Information
lllllllllllllllllllll
9. Qualification Basis
lllllllllllllllllllll
Begin Information
The addition of windshear programming to
a simulator in order to comply with the
qualification for required windshear training
does not change the original qualification
basis of the simulator.
End Information
lllllllllllllllllllll
10. Demonstration Repeatability
lllllllllllllllllllll
Begin Information
For the purposes of demonstration
repeatability, it is recommended that the
simulator be flown by means of the
simulator’s autodrive function (for those
simulators that have autodrive capability)
during the demonstrations.
End Information
lllllllllllllllllllll
Appendix B to Part 60—Qualification
Performance Standards for Airplane
Flight Training Devices
lllllllllllllllllllll
Begin Information
This appendix establishes the standards for
Airplane Flight Training Device (FTD)
evaluation and qualification at Level 4, Level
5, or Level 6. The Flight Standards Service,
National Simulator Program Manager
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Frm 00108
Fmt 4701
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(NSPM), is responsible for the development,
application, and implementation of the
standards contained within this appendix.
The procedures and criteria specified in this
appendix will be used by the NSPM, or a
person or persons assigned by the NSPM
when conducting airplane FTD evaluations.
Table of Contents
1. Introduction
2. Applicability (§ 60.1) and Applicability of
sponsor rules to persons who are not
sponsors and who are engaged in certain
unauthorized activities (§ 60.2)
3. Definitions (60.3)
4. Qualification Performance Standards
(§ 60.4)
5. Quality Management System (§ 60.5)
6. Sponsor Qualification Requirements
(§ 60.7)
7. Additional Responsibilities of the Sponsor
(§ 60.9)
8. FSTD Use (§ 60.11)
9. FSTD Objective Data Requirements
(§ 60.13)
10. Special Equipment and Personnel
Requirements for Qualification of the FTD
(§ 60.14)
11. Initial (and Upgrade) Qualification
Requirements (§ 60.15)
12. Additional Qualifications for Currently
Qualified FTDs (§ 60.16)
13. Previously Qualified FTDs (§ 60.17)
14. Inspection, Continuing Qualification
Evaluation, and Maintenance
Requirements (§ 60.19)
15. Logging FTD Discrepancies (§ 60.20)
16. Interim Qualification of FTDs for New
Airplane Types or Models (§ 60.21)
17. Modifications to FTDs (§ 60.23)
18. Operations With Missing,
Malfunctioning, or Inoperative
Components (§ 60.25)
19. Automatic Loss of Qualification and
Procedures for Restoration of
Qualification (§ 60.27)
20. Other Losses of Qualification and
Procedures for Restoration of
Qualification (§ 60.29)
21. Record Keeping and Reporting (§ 60.31)
22. Applications, Logbooks, Reports, and
Records: Fraud, Falsification, or
Incorrect Statements (§ 60.33)
23. [Reserved]
24. Levels of FTD
25. FSTD Qualification on the Basis of a
Bilateral Aviation Safety Agreement
(BASA) (§ 60.37)
Attachment 1 to Appendix B to Part 60—
General FTD Requirements
Attachment 2 to Appendix B to Part 60—
Flight Training Device (FTD) Objective
Tests
Attachment 3 to Appendix B to Part 60—
Flight Training Device (FTD) Subjective
Evaluation
Attachment 4 to Appendix B to Part 60—
Sample Documents
End Information
lllllllllllllllllllll
1. Introduction
lllllllllllllllllllll
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Begin Information
a. This appendix contains background
information as well as regulatory and
informative material as described later in this
section. To assist the reader in determining
what areas are required and what areas are
permissive, the text in this appendix is
divided into two sections: ‘‘QPS
Requirements’’ and ‘‘Information.’’ The QPS
Requirements sections contain details
regarding compliance with the part 60 rule
language. These details are regulatory, but are
found only in this appendix. The Information
sections contain material that is advisory in
nature, and designed to give the user general
information about the regulation.
b. Related Reading References.
(1) 14 CFR part 60.
(2) 14 CFR part 61.
(3) 14 CFR part 63.
(4) 14 CFR part 119.
(5) 14 CFR part 121.
(6) 14 CFR part 125.
(7) 14 CFR part 135.
(8) 14 CFR part 141.
(9) 14 CFR part 142.
(10) Advisory Circular (AC) 120–28C,
Criteria for Approval of Category III Landing
Weather Minima.
(11) AC 120–29, Criteria for Approving
Category I and Category II Landing Minima
for part 121 operators.
(12) AC 120–35B, Line Operational
Simulations: Line-Oriented Flight Training,
Special Purpose Operational Training, Line
Operational Evaluation.
(13) AC 120–41, Criteria for Operational
Approval of Airborne Wind Shear Alerting
and Flight Guidance Systems.
(14) AC 120–57A, Surface Movement
Guidance and Control System (SMGS).
(15) AC 150/5300–13, Airport Design.
(16) AC 150/5340–1G, Standards for
Airport Markings.
(17) AC 150/5340–4C, Installation Details
for Runway Centerline Touchdown Zone
Lighting Systems.
(18) AC 150/5340–19, Taxiway Centerline
Lighting System.
(19) AC 150/5340–24, Runway and
Taxiway Edge Lighting System.
(20) AC 150/5345–28D, Precision
Approach Path Indicator (PAPI) Systems.
(21) International Air Transport
Association document, ‘‘Flight Simulator
Design and Performance Data Requirements,’’
as amended.
(22) AC 25–7, as amended, Flight Test
Guide for Certification of Transport Category
Airplanes.
(23) AC 23–8A, as amended, Flight Test
Guide for Certification of Part 23 Airplanes.
(24) International Civil Aviation
Organization (ICAO) Manual of Criteria for
the Qualification of Flight Simulators, as
amended.
(25) Airplane Flight Simulator Evaluation
Handbook, Volume I, as amended and
Volume II, as amended, The Royal
Aeronautical Society, London, UK.
(26) FAA Publication FAA–S–8081 series
(Practical Test Standards for Airline
Transport Pilot Certificate, Type Ratings,
Commercial Pilot, and Instrument Ratings).
(27) The FAA Aeronautical Information
Manual (AIM). An electronic version of the
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AIM is on the internet at https://www.faa.gov/
atpubs.
End Information
lllllllllllllllllllll
2. Applicability (§§ 60.1 & 60.2)
There is no additional regulatory or
informational material that applies to § 60.1,
Applicability, or to § 60.2, Applicability of
sponsor rules to person who are not sponsors
and who are engaged in certain unauthorized
activities.
3. Definitions (§ 60.3)
lllllllllllllllllllll
Begin Information
See appendix F of this part for a list of
definitions and abbreviations from part 1,
part 60, and the QPS appendices of part 60.
End Information
lllllllllllllllllllll
4. Qualification Performance Standards
(§ 60.4)
There is no additional regulatory or
informational material that applies to § 60.4,
Qualification Performance Standards.
5. Quality Management System (§ 60.5)
lllllllllllllllllllll
Begin Information
Additional regulatory material and
informational material regarding Quality
Management Systems for FTDs may be found
in appendix E of this part.
End Information
lllllllllllllllllllll
6. Sponsor Qualification Requirements
(§ 60.7)
lllllllllllllllllllll
Begin Information
a. The intent of the language in § 60.7(b) is
to have a specific FTD, identified by the
sponsor, used at least once in an FAAapproved flight training program for the
airplane simulated during the 12-month
period described. The identification of the
specific FTD may change from one 12-month
period to the next 12-month period as long
as that sponsor sponsors and uses at least one
FTD at least once during the prescribed
period. There is no minimum number of
hours or minimum FTD periods required.
b. The following examples describe
acceptable operational practices:
(1) Example One.
(a) A sponsor is sponsoring a single,
specific FTD for its own use, in its own
facility or elsewhere—this single FTD forms
the basis for the sponsorship. The sponsor
uses that FTD at least once in each 12-month
period in that sponsor’s FAA-approved flight
training program for the airplane simulated.
This 12-month period is established
according to the following schedule:
(i) If the FTD was qualified prior to October
30, 2007 the 12-month period begins on the
date of the first continuing qualification
evaluation conducted in accordance with
§ 60.19 after October 30, 2007 and continues
for each subsequent 12-month period;
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63499
(ii) A device qualified on or after October
30, 2007 will be required to undergo an
initial or upgrade evaluation in accordance
with § 60.15. Once the initial or upgrade
evaluation is complete, the first continuing
qualification evaluation will be conducted
within 6 months. The 12 month continuing
qualification evaluation cycle begins on that
date and continues for each subsequent 12month period.
(b) There is no minimum number of hours
of FTD use required.
(c) The identification of the specific FTD
may change from one 12-month period to the
next 12-month period as long as that sponsor
sponsors and uses at least one FTD at least
once during the prescribed period.
(2) Example Two.
(a) A sponsor sponsors an additional
number of FTDs, in its facility or elsewhere.
Each additionally sponsored FTD must be—
(i) Used by the sponsor in the sponsor’s
FAA-approved flight training program for the
airplane simulated (as described in
§ 60.7(d)(1));
OR
(ii) Used by another FAA certificate holder
in that other certificate holder’s FAAapproved flight training program for the
airplane simulated (as described in
§ 60.7(d)(1)). This 12-month period is
established in the same manner as in
example one.
OR
(iii) Provided a statement each year from a
qualified pilot, (after having flown the
airplane, not the subject FTD or another FTD,
during the preceding 12-month period)
stating that the subject FTD’s performance
and handling qualities represent the airplane
(as described in § 60.7(d)(2)). This statement
is provided at least once in each 12-month
period established in the same manner as in
example one.
(b) There is no minimum number of hours
of FTD use required.
(3) Example Three.
(a) A sponsor in New York (in this
example, a Part 142 certificate holder)
establishes ‘‘satellite’’ training centers in
Chicago and Moscow.
(b) The satellite function means that the
Chicago and Moscow centers must operate
under the New York center’s certificate (in
accordance with all of the New York center’s
practices, procedures, and policies; e.g.,
instructor and/or technician training/
checking requirements, recordkeeping, QMS
program).
(c) All of the FTDs in the Chicago and
Moscow centers could be dry-leased (i.e., the
certificate holder does not have and use
FAA-approved flight training programs for
the FTDs in the Chicago and Moscow
centers) because—
(i) Each FTD in the Chicago center and
each FTD in the Moscow center is used at
least once each 12-month period by another
FAA certificate holder in that other
certificate holder’s FAA-approved flight
training program for the airplane (as
described in § 60.7(d)(1));
OR
(ii) A statement is obtained from a
qualified pilot (having flown the airplane,
not the subject FTD or another FTD during
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
the preceding 12-month period) stating that
the performance and handling qualities of
each FTD in the Chicago and Moscow centers
represents the airplane (as described in
§ 60.7(d)(2)).
End Information
lllllllllllllllllllll
7. Additional Responsibilities of the Sponsor
(§ 60.9)
lllllllllllllllllllll
Begin Information
The phrase ‘‘as soon as practicable’’ in
§ 60.9(a) means without unnecessarily
disrupting or delaying beyond a reasonable
time the training, evaluation, or experience
being conducted in the FSTD.
End Information
lllllllllllllllllllll
8. FSTD Use (§ 60.11)
There is no additional regulatory or
informational material that applies to § 60.11,
FSTD use.
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9. FTD Objective Data Requirements
(§ 60.13)
lllllllllllllllllllll
Begin QPS Requirements
a. Flight test data used to validate FTD
performance and handling qualities must
have been gathered in accordance with a
flight test program containing the following:
(1) A flight test plan consisting of:
(a) The maneuvers and procedures
required for aircraft certification and
simulation programming and validation.
(b) For each maneuver or procedure—
(i) The procedures and control input the
flight test pilot and/or engineer used.
(ii) The atmospheric and environmental
conditions.
(iii) The initial flight conditions.
(iv) The airplane configuration, including
weight and center of gravity.
(v) The data to be gathered.
(vi) All other information necessary to
recreate the flight test conditions in the FTD.
(2) Appropriately qualified flight test
personnel.
(3) An understanding of the accuracy of the
data to be gathered using appropriate
alternative data sources, procedures, and
instrumentation that is traceable to a
recognized standard as described in
Attachment 2, Table B2F.
(4) Appropriate and sufficient data
acquisition equipment or system(s),
including appropriate data reduction and
analysis methods and techniques, as would
be acceptable to the FAA’s Aircraft
Certification Service.
b. The data, regardless of source, must be
presented:
(1) In a format that supports the FTD
validation process;
(2) In a manner that is clearly readable and
annotated correctly and completely;
(3) With resolution sufficient to determine
compliance with the tolerances set forth in
Attachment 2, Table B2A appendix.
(4) With any necessary guidance
information provided; and
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(5) Without alteration, adjustments, or bias;
however the data may be re-scaled, digitized,
or otherwise manipulated to fit the desired
presentation.
c. After completion of any additional flight
test, a flight test report must be submitted in
support of the validation data. The report
must contain sufficient data and rationale to
support qualification of the FTD at the level
requested.
d. As required by § 60.13(f), the sponsor
must notify the NSPM when it becomes
aware that an addition to or a revision of the
flight related data or airplane systems related
data is available if this data is used to
program and operate a qualified FTD. The
data referred to in this sub-section are those
data that are used to validate the
performance, handling qualities, or other
characteristics of the aircraft, including data
related to any relevant changes occurring
after the type certification is issued. This
notification must be made within 10 working
days.
End QPS Requirements
lllllllllllllllllllll
Begin Information
e. The FTD sponsor is encouraged to
maintain a liaison with the manufacturer of
the aircraft being simulated (or with the
holder of the aircraft type certificate for the
aircraft being simulated if the manufacturer
is no longer in business), and if appropriate,
with the person having supplied the aircraft
data package for the FTD in order to facilitate
the notification described in this paragraph.
f. It is the intent of the NSPM that for new
aircraft entering service, at a point well in
advance of preparation of the Qualification
Test Guide (QTG), the sponsor should submit
to the NSPM for approval, a descriptive
document (a validation data roadmap)
containing the plan for acquiring the
validation data, including data sources. This
document should clearly identify sources of
data for all required tests, a description of the
validity of these data for a specific engine
type and thrust rating configuration, and the
revision levels of all avionics affecting the
performance or flying qualities of the aircraft.
Additionally, this document should provide
other information such as the rationale or
explanation for cases where data or data
parameters are missing, instances where
engineering simulation data are used, or
where flight test methods require further
explanations. It should also provide a brief
narrative describing the cause and effect of
any deviation from data requirements. The
aircraft manufacturer may provide this
document.
g. There is no requirement for any flight
test data supplier to submit a flight test plan
or program prior to gathering flight test data.
However, the NSPM notes that inexperienced
data gatherers often provide data that is
irrelevant, improperly marked, lacking
adequate justification for selection. Other
problems include inadequate information
regarding initial conditions or test
maneuvers. The NSPM has been forced to
refuse these data submissions as validation
data for an FTD evaluation. It is for this
reason that the NSPM recommends that any
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data supplier not previously experienced in
this area review the data necessary for
programming and for validating the
performance of the FTD and discuss the
flight test plan anticipated for acquiring such
data with the NSPM well in advance of
commencing the flight tests.
h. In those cases where the objective test
results authorize a ‘‘snapshot test’’ or a
‘‘series of snapshot tests’’ results in lieu of a
time-history result, Attachment 2 requires the
sponsor or other data provider to ensure that
a steady state condition exists at the instant
of time captured by the ‘‘snapshot.’’ This is
often verified by showing that a steady state
condition existed from some period of time
during which the snap shot is taken. The
time period most frequently used is 5
seconds prior through 2 seconds following
the instant of time captured by the snap shot.
This paragraph is primarily addressing the
source data and the method by which the
data provider ensures that the steady state
condition for the snap shot is representative.
i. The NSPM will consider, on a case-bycase basis, whether or not to approve
supplemental validation data derived from
flight data recording systems such as a Quick
Access Recorder or Flight Data Recorder.
End Information
lllllllllllllllllllll
10. Special Equipment and Personnel
Requirements for Qualification of the FTD
(§ 60.14)
lllllllllllllllllllll
Begin Information
a. In the event that the NSPM determines
that special equipment or specifically
qualified persons will be required to conduct
an evaluation, the NSPM will make every
attempt to notify the sponsor at least one (1)
week, but in no case less than 72 hours, in
advance of the evaluation. Examples of
special equipment include flight control
measurement devices, accelerometers, or
oscilloscopes. Examples of specially
qualified personnel include individuals
specifically qualified to install or use any
special equipment when its use is required.
b. Examples of a special evaluation include
an evaluation conducted after an FTD is
moved; at the request of the TPAA; or as a
result of comments received from FTD users
that raise questions regarding the continued
qualification or use of the FTD.
End Information
lllllllllllllllllllll
11. Initial (and Upgrade) Qualification
Requirements (§ 60.15)
lllllllllllllllllllll
Begin QPS Requirement
a. In order to be qualified at a particular
qualification level, the FTD must:
(1) Meet the general requirements listed in
Attachment 1;
(2) Meet the objective testing requirements
listed in Attachment 2 (Level 4 FTDs do not
require objective tests); and
(3) Satisfactorily accomplish the subjective
tests listed in Attachment 3.
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b. The request described in § 60.15(a) must
include all of the following:
(1) A statement that the FTD meets all of
the applicable provisions of this part and all
applicable provisions of the QPS.
(2) A confirmation that the sponsor will
forward to the NSPM the statement described
in § 60.15(b) in such time as to be received
no later than 5 business days prior to the
scheduled evaluation and may be forwarded
to the NSPM via traditional or electronic
means.
(3) Except for a Level 4 FTD, a qualification
test guide (QTG), acceptable to the NSPM,
that includes all of the following:
(a) Objective data obtained from aircraft
testing or another approved source.
(b) Correlating objective test results
obtained from the performance of the FTD as
prescribed in the applicable QPS.
(c) The result of FTD subjective tests
prescribed in the applicable QPS.
(d) A description of the equipment
necessary to perform the evaluation for initial
qualification and the continuing qualification
evaluations.
c. The QTG described in paragraph a(3) of
this section, must provide the documented
proof of compliance with the FTD objective
tests in Attachment 2,Table B2A of this
appendix.
d. The QTG is prepared and submitted by
the sponsor, or the sponsor’s agent on behalf
of the sponsor, to the NSPM for review and
approval, and must include, for each
objective test:
(1) Parameters, tolerances, and flight
conditions;
(2) Pertinent and complete instructions for
conducting automatic and manual tests;
(3) A means of comparing the FTD test
results to the objective data;
(4) Any other information as necessary to
assist in the evaluation of the test results;
(5) Other information appropriate to the
qualification level of the FTD.
e. The QTG described in paragraphs (a)(3)
and (b) of this section, must include the
following:
(1) A QTG cover page with sponsor and
FAA approval signature blocks (see
Attachment 4, Figure B4C, for a sample QTG
cover page).
(2) A continuing qualification evaluation
requirements page. This page will be used by
the NSPM to establish and record the
frequency with which continuing
qualification evaluations must be conducted
and any subsequent changes that may be
determined by the NSPM in accordance with
§ 60.19. See Attachment 4, Figure B4G, for a
sample Continuing Qualification Evaluation
Requirements page.
(3) An FTD information page that provides
the information listed in this paragraph, if
applicable (see Attachment 4, Figure B4B, for
a sample FTD information page). For
convertible FTDs, the sponsor must submit a
separate page for each configuration of the
FTD.
(a) The sponsor’s FTD identification
number or code.
(b) The airplane model and series being
simulated.
(c) The aerodynamic data revision number
or reference.
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(d) The engine model(s) and its data
revision number or reference.
(e) The flight control data revision number
or reference.
(f) The flight management system
identification and revision level.
(g) The FTD model and manufacturer.
(h) The date of FTD manufacture.
(i) The FTD computer identification.
(j) The visual system model and
manufacturer, including display type.
(k) The motion system type and
manufacturer, including degrees of freedom.
(4) A Table of Contents.
(5) A log of revisions and a list of effective
pages.
(6) List of all relevant data references.
(7) A glossary of terms and symbols used
(including sign conventions and units).
(8) Statements of compliance and
capability (SOCs) with certain requirements.
SOCs must provide references to the sources
of information that show the capability of the
FTD to comply with the requirement, a
rationale explaining how the referenced
material is used, mathematical equations and
parameter values used, and the conclusions
reached; i.e., that the FTD complies with the
requirement. Refer to the ‘‘General FTD
Requirements’’ column, Table B1A, in
Attachment 1, or in the ‘‘Alternative Data
Sources, Procedures, and Instrumentation’’
column, Table B2F, in Attachment 2, to see
when SOCs are required.
(9) Recording procedures or equipment
required to accomplish the objective tests.
(10) The following information for each
objective test designated in Attachment 2, as
applicable to the qualification level sought:
(a) Name of the test.
(b) Objective of the test.
(c) Initial conditions.
(d) Manual test procedures.
(e) Automatic test procedures (if
applicable).
(f) Method for evaluating FTD objective test
results.
(g) List of all relevant parameters driven or
constrained during the automatic test(s).
(h) List of all relevant parameters driven or
constrained during the manual test(s).
(i) Tolerances for relevant parameters.
(j) Source of Validation Data (document
and page number).
(k) Copy of the Validation Data (if located
in a separate binder, a cross reference for the
identification and page number for pertinent
data location must be provided).
(l) FTD Objective Test Results as obtained
by the sponsor. Each test result must reflect
the date completed and must be clearly
labeled as a product of the device being
tested.
f. A convertible FTD is addressed as a
separate FTD for each model and series
airplane to which it will be converted and for
the FAA qualification level sought. The
NSPM will conduct an evaluation for each
configuration. If a sponsor seeks qualification
for two or more models of an airplane type
using a convertible FTD, the sponsor must
provide a QTG for each airplane model, or a
supplemented QTG for each airplane model.
The NSPM will conduct evaluations for each
airplane model.
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g. The form and manner of presentation of
objective test results in the QTG must
include the following:
(1) The sponsor’s FTD test results must be
recorded in a manner acceptable to the
NSPM, that allows easy comparison of the
FTD test results to the validation data (e.g.,
use of a multi-channel recorder, line printer,
cross plotting, overlays, transparencies).
(2) FTD results must be labeled using
terminology common to airplane parameters
as opposed to computer software
identifications.
(3) Validation data documents included in
a QTG may be photographically reduced only
if such reduction will not alter the graphic
scaling or cause difficulties in scale
interpretation or resolution.
(4) Scaling on graphical presentations must
provide the resolution necessary to evaluate
the parameters shown in Attachment 2, Table
B2A of this appendix.
(5) Tests involving time histories, data
sheets (or transparencies thereof) and FTD
test results must be clearly marked with
appropriate reference points to ensure an
accurate comparison between FTD and
airplane with respect to time. Time histories
recorded via a line printer are to be clearly
identified for cross-plotting on the airplane
data. Over-plots must not obscure the
reference data.
h. The sponsor may elect to complete the
QTG objective and subjective tests at the
manufacturer’s facility or at the sponsor’s
training facility. If the tests are conducted at
the manufacturer’s facility, the sponsor must
repeat at least one-third of the tests at the
sponsor’s training facility in order to
substantiate FTD performance. The QTG
must be clearly annotated to indicate when
and where each test was accomplished. Tests
conducted at the manufacturer’s facility and
at the sponsor’s training facility must be
conducted after the FTD is assembled with
systems and sub-systems functional and
operating in an interactive manner. The test
results must be submitted to the NSPM.
i. The sponsor must maintain a copy of the
MQTG at the FTD location.
j. All FTDs for which the initial
qualification is conducted after October 30,
2013 must have an electronic MQTG
(eMQTG) including all objective data
obtained from airplane testing, or another
approved source (reformatted or digitized),
together with correlating objective test results
obtained from the performance of the FTD
(reformatted or digitized) as prescribed in
this appendix. The eMQTG must also contain
the general FTD performance or
demonstration results (reformatted or
digitized) prescribed in this appendix, and a
description of the equipment necessary to
perform the initial qualification evaluation
and the continuing qualification evaluations.
The eMQTG must include the original
validation data used to validate FTD
performance and handling qualities in either
the original digitized format from the data
supplier or an electronic scan of the original
time-history plots that were provided by the
data supplier. A copy of the eMQTG must be
provided to the NSPM.
k. All other FTDs (not covered in
subparagraph ‘‘j’’) must have an electronic
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copy of the MQTG by and after October 30,
2013. A copy of the eMQTG must be
provided to the NSPM. This may be provided
by an electronic scan presented in a Portable
Document File (PDF), or similar format
acceptable to the NSPM.
sroberts on PROD1PC70 with RULES
End QPS Requirements
lllllllllllllllllllll
Begin Information
l. Only those FTDs that are sponsored by
a certificate holder as defined in appendix F
will be evaluated by the NSPM. However,
other FTD evaluations may be conducted on
a case-by-case basis as the Administrator
deems appropriate, but only in accordance
with applicable agreements.
m. The NSPM will conduct an evaluation
for each configuration, and each FTD must be
evaluated as completely as possible. To
ensure a thorough and uniform evaluation,
each FTD is subjected to the general FTD
requirements in Attachment 1, the objective
tests listed in Attachment 2, and the
subjective tests listed in Attachment 3 of this
appendix. The evaluations described herein
will include, but not necessarily be limited
to the following:
(1) Airplane responses, including
longitudinal and lateral-directional control
responses (see Attachment 2 of this
appendix);
(2) Performance in authorized portions of
the simulated airplane’s operating envelope,
to include tasks evaluated by the NSPM in
the areas of surface operations, takeoff, climb,
cruise, descent, approach and landing, as
well as abnormal and emergency operations
(see Attachment 2 of this appendix);
(3) Control checks (see Attachment 1 and
Attachment 2 of this appendix);
(4) Cockpit configuration (see Attachment
1 of this appendix);
(5) Pilot, flight engineer, and instructor
station functions checks (see Attachment 1
and Attachment 3 of this appendix);
(6) Airplane systems and sub-systems (as
appropriate) as compared to the airplane
simulated (see attachment 1 and attachment
3 of this appendix);
(7) FTD systems and sub-systems,
including force cueing (motion), visual, and
aural (sound) systems, as appropriate (see
Attachment 1 and Attachment 2 of this
appendix); and
(8) Certain additional requirements,
depending upon the qualification level
sought, including equipment or
circumstances that may become hazardous to
the occupants. The sponsor may be subject to
Occupational Safety and Health
Administration requirements.
n. The NSPM administers the objective and
subjective tests, which includes an
examination of functions. The tests include
a qualitative assessment of the FTD by an
NSP pilot. The NSP evaluation team leader
may assign other qualified personnel to assist
in accomplishing the functions examination
and/or the objective and subjective tests
performed during an evaluation when
required.
(1) Objective tests provide a basis for
measuring and evaluating FTD performance
and determining compliance with the
requirements of this part.
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(2) Subjective tests provide a basis for:
(a) Evaluating the capability of the FTD to
perform over a typical utilization period;
(b) Determining that the FTD satisfactorily
simulates each required task;
(c) Verifying correct operation of the FTD
controls, instruments, and systems; and
(d) Demonstrating compliance with the
requirements of this part.
o. The tolerances for the test parameters
listed in Attachment 2 of this appendix
reflect the range of tolerances acceptable to
the NSPM for FTD validation and are not to
be confused with design tolerances specified
for FTD manufacture. In making decisions
regarding tests and test results, the NSPM
relies on the use of operational and
engineering judgment in the application of
data (including consideration of the way in
which the flight test was flown and way the
data was gathered and applied) data
presentations, and the applicable tolerances
for each test.
p. In addition to the scheduled continuing
qualification evaluation, each FTD is subject
to evaluations conducted by the NSPM at any
time without prior notification to the
sponsor. Such evaluations would be
accomplished in a normal manner (i.e.,
requiring exclusive use of the FTD for the
conduct of objective and subjective tests and
an examination of functions) if the FTD is not
being used for flight crewmember training,
testing, or checking. However, if the FTD
were being used, the evaluation would be
conducted in a non-exclusive manner. This
non-exclusive evaluation will be conducted
by the FTD evaluator accompanying the
check airman, instructor, Aircrew Program
Designee (APD), or FAA inspector aboard the
FTD along with the student(s) and observing
the operation of the FTD during the training,
testing, or checking activities.
q. Problems with objective test results are
handled as follows:
(1) If a problem with an objective test result
is detected by the NSP evaluation team
during an evaluation, the test may be
repeated or the QTG may be amended.
(2) If it is determined that the results of an
objective test do not support the qualification
level requested but do support a lower level,
the NSPM may qualify the FTD at a lower
level. For example, if a Level 6 evaluation is
requested, but the FTD fails to meet the spiral
stability test tolerances, it could be qualified
at Level 5.
r. After an FTD is successfully evaluated,
the NSPM issues a statement of qualification
(SOQ) to the sponsor, The NSPM
recommends the FTD to the TPAA, who will
approve the FTD for use in a flight training
program. The SOQ will be issued at the
satisfactory conclusion of the initial or
continuing qualification. However, it is the
sponsor’s responsibility to obtain TPAA
approval prior to using the FTD in an FAAapproved flight training program.
s. Under normal circumstances, the NSPM
establishes a date for the initial or upgrade
evaluation within ten (10) working days after
determining that a complete QTG is
acceptable. Unusual circumstances may
warrant establishing an evaluation date
before this determination is made. A sponsor
may schedule an evaluation date as early as
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6 months in advance. However, there may be
a delay of 45 days or more in rescheduling
and completing the evaluation if the sponsor
is unable to meet the scheduled date. See
Attachment 4, Figure B4A, Sample Request
for Initial, Upgrade, or Reinstatement
Evaluation.
t. The numbering system used for objective
test results in the QTG should closely follow
the numbering system set out in Attachment
2, FTD Objective Tests, Table B2A.
u. Contact the NSPM or visit the NSPM
Web site for additional information regarding
the preferred qualifications of pilots used to
meet the requirements of § 60.15(d).
v. Examples of the exclusions for which
the FTD might not have been subjectively
tested by the sponsor or the NSPM and for
which qualification might not be sought or
granted, as described in § 60.15(g)(6), include
engine out maneuvers or circling approaches.
End Information
lllllllllllllllllllll
12. Additional Qualifications for Currently
Qualified FTDs (§ 60.16)
There is no additional regulatory or
informational material that applies to § 60.16,
Additional Qualifications for a Currently
Qualified FTD.
13. Previously Qualified FTDs (§ 60.17)
lllllllllllllllllllll
Begin QPS Requirements
a. In instances where a sponsor plans to
remove an FTD from active status for a
period of less than two years, the following
procedures apply:
(1) The NSPM must be notified in writing
and the notification must include an estimate
of the period that the FTD will be inactive;
(2) Continuing Qualification evaluations
will not be scheduled during the inactive
period;
(3) The NSPM will remove the FTD from
the list of qualified FSTDs on a mutually
established date not later than the date on
which the first missed continuing
qualification evaluation would have been
scheduled;
(4) Before the FTD is restored to qualified
status, it must be evaluated by the NSPM.
The evaluation content and the time required
to accomplish the evaluation is based on the
number of continuing qualification
evaluations and sponsor-conducted quarterly
inspections missed during the period of
inactivity.
(5) The sponsor must notify the NSPM of
any changes to the original scheduled time
out of service;
b. FTDs qualified prior to October 30, 2007,
are not required to meet the general FTD
requirements, the objective test requirements,
and the subjective test requirements of
Attachments 1, 2, and 3, respectively, of this
appendix.
c. [Reserved]
End QPS Requirements
lllllllllllllllllllll
Begin Information
d. Other certificate holders or persons
desiring to use an FTD may contract with
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sroberts on PROD1PC70 with RULES
FTD sponsors to use FTDs previously
qualified at a particular level for an airplane
type and approved for use within an FAAapproved flight training program. Such FTDs
are not required to undergo an additional
qualification process, except as described in
§ 60.16.
e. Each FTD user must obtain approval
from the appropriate TPAA to use any FTD
in an FAA-approved flight training program.
f. The intent of the requirement listed in
§ 60.17(b), for each FTD to have a Statement
of Qualification within 6 years, is to have the
availability of that statement (including the
configuration list and the limitations to
authorizations) to provide a complete picture
of the FTD inventory regulated by the FAA.
The issuance of the statement will not
require any additional evaluation or require
any adjustment to the evaluation basis for the
FTD.
g. Downgrading of an FTD is a permanent
change in qualification level and will
necessitate the issuance of a revised
Statement of Qualification to reflect the
revised qualification level, as appropriate. If
a temporary restriction is placed on an FTD
because of a missing, malfunctioning, or
inoperative component or on-going repairs,
the restriction is not a permanent change in
qualification level. Instead, the restriction is
temporary and is removed when the reason
for the restriction has been resolved.
h. It is not the intent of the NSPM to
discourage the improvement of existing
simulation (e.g., the ‘‘updating’’ of a control
loading system, or the replacement of the IOS
with a more capable unit) by requiring the
‘‘updated’’ device to meet the qualification
standards current at the time of the update.
Depending on the extent of the update, the
NSPM may require that the updated device
be evaluated and may require that an
evaluation include all or a portion of the
elements of an initial evaluation. However,
the standards against which the device
would be evaluated are those that are found
in the MQTG for that device.
i. The NSPM will determine the evaluation
criteria for an FTD that has been removed
from active status for a prolonged period. The
criteria will be based on the number of
continuing qualification evaluations and
quarterly inspections missed during the
period of inactivity. For example, if the FTD
were out of service for a 1 year period, it
would be necessary to complete the entire
QTG, since all of the quarterly evaluations
would have been missed. The NSPM will
also consider how the FTD was stored,
whether parts were removed from the FTD
and whether the FTD was disassembled.
j. The FTD will normally be requalified
using the FAA-approved MQTG and the
criteria that was in effect prior to its removal
from qualification. However, inactive periods
of 2 years or more will require requalification under the standards in effect
and current at the time of requalification.
End Information
lllllllllllllllllllll
14. Inspection, Continuing Evaluation
Qualification Requirements (§ 60.19)
lllllllllllllllllllll
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Begin QPS Requirement
a. The sponsor must conduct a minimum
of four evenly spaced inspections throughout
the year. The objective test sequence and
content of each inspection in this sequence
must be developed by the sponsor and must
be acceptable to the NSPM.
b. The description of the functional
preflight inspection must be contained in the
sponsor’s QMS.
c. Record ‘‘functional preflight’’ in the FTD
discrepancy log book or other acceptable
location, including any item found to be
missing, malfunctioning, or inoperative.
End QPS Requirements
lllllllllllllllllllll
Begin Information
d. The sponsor’s test sequence and the
content of each quarterly inspection required
in § 60.19(a)(1) should include a balance and
a mix from the objective test requirement
areas listed as follows:
(1) Performance.
(2) Handling qualities.
(3) Motion system (where appropriate).
(4) Visual system (where appropriate).
(5) Sound system (where appropriate).
(6) Other FTD systems.
e. If the NSP evaluator plans to accomplish
specific tests during a normal continuing
qualification evaluation that requires the use
of special equipment or technicians, the
sponsor will be notified as far in advance of
the evaluation as practical; but not less than
72 hours. Examples of such tests include
latencies, control sweeps, or motion or visual
system tests.
f. The continuing qualification evaluations
described in § 60.19(b) will normally require
4 hours of FTD time. However, flexibility is
necessary to address abnormal situations or
situations involving aircraft with additional
levels of complexity (e.g., computer
controlled aircraft). The sponsor should
anticipate that some tests may require
additional time. The continuing qualification
evaluations will consist of the following:
(1) Review of the results of the quarterly
inspections conducted by the sponsor since
the last scheduled continuing qualification
evaluation.
(2) A selection of approximately 8 to 15
objective tests from the MQTG that provide
an adequate opportunity to evaluate the
performance of the FTD. The tests chosen
will be performed either automatically or
manually and should be able to be conducted
within approximately one-third (1⁄3) of the
allotted FTD time.
(3) A subjective evaluation of the FTD to
perform a representative sampling of the
tasks set out in attachment 3 of this
appendix. This portion of the evaluation
should take approximately two-thirds (2⁄3) of
the allotted FTD time.
(4) An examination of the functions of the
FTD may include the motion system, visual
system, sound system as applicable,
instructor operating station, and the normal
functions and simulated malfunctions of the
airplane systems. This examination is
normally accomplished simultaneously with
the subjective evaluation requirements.
g. The requirement established in
§ 60.19(b)(4) regarding the frequency of
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63503
NSPM-conducted continuing qualification
evaluations for each FTD is typically 12
months. However, the establishment and
satisfactory implementation of an approved
QMS for a sponsor will provide a basis for
adjusting the frequency of evaluations to
exceed 12-month intervals.
End Information
lllllllllllllllllllll
15. Logging FTD Discrepancies (§ 60.20)
There is no additional regulatory or
informational material that applies to § 60.20.
Logging FTD Discrepancies.
16. Interim Qualification of FTDs for New
Airplane Types or Models (§ 60.21)
lllllllllllllllllllll
Begin Information
There is no additional regulatory or
informational material that applies to § 60.21,
Interim Qualification of FTDs for New
Airplane Types or Models.
End Information
lllllllllllllllllllll
17. Modifications to FTDs (§ 60.23)
lllllllllllllllllllll
Begin QPS Requirements
a. The notification described in
§ 60.23(c)(2) must include a complete
description of the planned modification, with
a description of the operational and
engineering effect the proposed modification
will have on the operation of the FTD and
the results that are expected with the
modification incorporated.
b. Prior to using the modified FTD:
(1) All the applicable objective tests
completed with the modification
incorporated, including any necessary
updates to the MQTG (e.g., accomplishment
of FSTD Directives) must be acceptable to the
NSPM; and
(2) The sponsor must provide the NSPM
with a statement signed by the MR that the
factors listed in § 60.15(b) are addressed by
the appropriate personnel as described in
that section.
End QPS Requirements
lllllllllllllllllllll
Begin Information
c. FSTD Directives are considered
modification of an FTD. See Attachment 4 for
a sample index of effective FSTD Directives.
End Information
lllllllllllllllllllll
18. Operation With Missing, Malfunctioning,
or Inoperative Components (§ 60.25)
Begin Information
a. The sponsor’s responsibility with respect
to § 60.25(a) is satisfied when the sponsor
fairly and accurately advises the user of the
current status of an FTD, including any
missing, malfunctioning, or inoperative
(MMI) component(s).
b. If the 29th or 30th day of the 30-day
period described in § 60.25(b) is on a
Saturday, a Sunday, or a holiday, the FAA
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will extend the deadline until the next
business day.
c. In accordance with the authorization
described in § 60.25(b), the sponsor may
develop a discrepancy prioritizing system to
accomplish repairs based on the level of
impact on the capability of the FTD. Repairs
having a larger impact on the FTD’s ability
to provide the required training, evaluation,
or flight experience will have a higher
priority for repair or replacement.
the date of the change, a summary of the
change, and the reason for the change.
b. If a coded form for recordkeeping is
used, it must provide for the preservation
and retrieval of information with appropriate
security or controls to prevent the
inappropriate alteration of such records after
the fact.
§ 60.37, FSTD Qualification on the Basis of
a Bilateral Aviation Safety Agreement
(BASA).
End QPS Requirements
lllllllllllllllllllll
lllllllllllllllllllll
End Information
lllllllllllllllllllll
22. Applications, Logbooks, Reports, and
Records: Fraud, Falsification, or Incorrect
Statements (§ 60.33)
There are no additional QPS requirements
or informational material that apply to
§ 60.33, Applications, Logbooks, Reports, and
Records: Fraud, Falsification, or Incorrect
Statements.
19. Automatic Loss of Qualification and
Procedures for Restoration of Qualification
(§ 60.27)
Begin Information
If the sponsor provides a plan for how the
FTD will be maintained during its out-ofservice period (e.g., periodic exercise of
mechanical, hydraulic, and electrical
systems; routine replacement of hydraulic
fluid; control of the environmental factors in
which the FTD is to be maintained.) there is
a greater likelihood that the NSPM will be
able to determine the amount of testing that
required for requalification.
23. [Reserved]
24. Levels of FTD
lllllllllllllllllllll
End Information
lllllllllllllllllllll
20. Other Losses of Qualification and
Procedures for Restoration of Qualification
(§ 60.29)
lllllllllllllllllllll
Begin Information
If the sponsor provides a plan for how the
FTD will be maintained during its out-ofservice period (e.g., periodic exercise of
mechanical, hydraulic, and electrical
systems; routine replacement of hydraulic
fluid; control of the environmental factors in
which the FTD is to be maintained.) there is
a greater likelihood that the NSPM will be
able to determine the amount of testing that
required for requalification.
End Information
lllllllllllllllllllll
21. Recordkeeping and Reporting (§ 60.31)
lllllllllllllllllllll
Begin QPS Requirements
a. FTD modifications can include hardware
or software changes. For FTD modifications
involving software programming changes, the
record required by § 60.31(a)(2) must consist
of the name of the aircraft system software,
aerodynamic model, or engine model change,
Begin Information
a. The following is a general description of
each level of FTD. Detailed standards and
tests for the various levels of FTDs are fully
defined in Attachments 1 through 3 of this
appendix.
(1) Level 4. A device that may have an open
airplane-specific flight deck area, or an
enclosed airplane-specific cockpit and at
least one operating system with air/ground
logic (no aerodynamic programming
required).
(2) Level 5. A device that may have an open
airplane-specific flight deck area, or an
enclosed airplane-specific cockpit and a
generic aerodynamic program with at least
one operating system and control loading
that is representative of the simulated
airplane only at an approach speed and
configuration.
(3) Level 6. A device that has an enclosed
airplane-specific cockpit and aerodynamic
program with all applicable airplane systems
operating and control loading that is
representative of the simulated airplane
throughout its ground and flight envelope
and significant sound representation.
End Information
lllllllllllllllllllll
25. FSTD Qualification on the Basis of a
Bilateral Aviation Safety Agreement (BASA)
(§ 60.37)
lllllllllllllllllllll
Begin Information
There are no additional QPS requirements
or informational material that apply to
End Information
lllllllllllllllllllll
Attachment 1 to Appendix B to Part 60—
General FTD Requirements
Begin QPS Requirements
1. Requirements
a. Certain requirements included in this
appendix must be supported with a
Statement of Compliance and Capability
(SOC), which may include objective and
subjective tests. The SOC will confirm that
the requirement was satisfied, and describe
how the requirement was met. The
requirements for SOCs and tests are indicated
in the ‘‘General FTD Requirements’’ column
in Table B1A of this appendix.
b. Table B1A describes the requirements
for the indicated level of FTD. Many devices
include operational systems or functions that
exceed the requirements outlined in this
section. In any event, all systems will be
tested and evaluated in accordance with this
appendix to ensure proper operation.
End QPS Requirements
lllllllllllllllllllll
Begin Information
2. Discussion
a. This attachment describes the general
requirements for qualifying Level 4 through
Level 6 FTDs. The sponsor should also
consult the objectives tests in Attachment 2
and the examination of functions and
subjective tests listed in Attachment 3 to
determine the complete requirements for a
specific level FTD.
b. The material contained in this
attachment is divided into the following
categories:
(1) General Cockpit Configuration.
(2) Programming.
(3) Equipment Operation.
(4) Equipment and facilities for instructor/
evaluator functions.
(5) Motion System.
(6) Visual System.
(7) Sound System.
c. Table B1A provides the standards for the
General FTD Requirements.
End Information
lllllllllllllllllllll
TABLE B1A—MINIMUM FTD REQUIREMENTS
<<>>
sroberts on PROD1PC70 with RULES
No.
FTD level
General FTD requirements
4
5
6
<>
Notes
1. General Cockpit Configuration
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63505
TABLE B1A—MINIMUM FTD REQUIREMENTS—Continued
<<>>
FTD level
No.
General FTD requirements
4
1.a ........
The FTD must have a cockpit that is a replica of the airplane simulated with controls, equipment, observable
cockpit indicators, circuit breakers. and bulkheads
properly located, functionally accurate and replicating
the airplane. The direction of movement of controls
and switches must be identifical to that in the airplane. Pilot seat(s) must afford the capability for the
occupant to be able to achieve the design ‘‘eye position’’.
1.b ........
The FTS must have equipment (e.g., instruments, panels, systems, circuit breakers, and controls) simulated
sufficiently for the authorized training/checking events
to be accomplished. The installed equipment must be
located in a spatially correct location and may be in a
cockpit or an open flight deck area. Actuation of
equipment must replicate the appropriate function in
the airplane.
5
X
X
<>
Notes
6
For FTD purposes, the cockpit consists of all that space
forward of a cross section of the fuselage at the most
extreme aft setting of the pilots’ seats including additional, required flight crewmember duty stations and
those required bulkheads aft of the pilot seats. For
clarification, bulkheads containing only item such as
leanding gear pin storage compartments, fire axes or
extinguishers, spare light bulbs, aircraft documents
pouches are not considered essential and may be
omitted.
X
2. Programming
2.a ........
The FTD must provide the proper effect of aerodynamic
changes for the combinations of drag and thrust normally encountered in flight. This must include the effect of change in airplane attitude, thrust, drag, altitude, temperature, and configuration.
Level 6 additionally requires the effects of changes in
gross weight and center of gravity.
Level 5 requires only generic aerodynamic programming.
2.b ........
The FTD must have the computer (analog or digital) capability (i.e., capacity, accuracy, resolution, and dynamic response) needed to meet the qualification
level sought.
2.c ........
X
Relative responses of the cockpit instruments must be
measured by latency tests, or transport delay tests,
and may not exceed 300 milliseconds. The instruments must respond to abrupt input at the pilot’s position within the allotted time, but not before the time
when the airplane would respond under the same
conditions.
• Latency: The FTD instrument and, if applicable, the
motion system and the visual system response must
not be prior to that time when the airplane responds
and may respond up to 300 milliseconds after that
time under the same conditions.
• Transport Delay: As an alternative to the Latency requirement, a transport delay objective test may be
used to demonstrate that the FTD system does not
exceed the specified limit. The sponsor must measure
all the delay encountered by a step signal migrating
from the pilot’s control through all the simulation software modules in the correct order, using a handshaking protocol, finally through the normal output
interfaces to the instrument display and, if applicable,
the motion system, and the visual system.
X
X
X
X
X
X
X
X
The intent is to verify that the FTD provides instrument
cues that are, within the stated time delays, like the
airplane responses. For airplane response, acceleration in the appropriate, corresponding rotational axis
is preferred. Additional information regarding Latency
and Transport Delay testing may be found in appendix A, Attachment 2, paragraph 14.
3. Equipment Operations
sroberts on PROD1PC70 with RULES
3.a ........
All relevant instrument indications involved in the simulation of the airplane must automatically respond to
control movement or external disturbances to the simulated airplane; e.g., turbulence or winds.
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TABLE B1A—MINIMUM FTD REQUIREMENTS—Continued
<<>>
FTD level
No.
General FTD requirements
4
3.b ........
Navigation equipment must be installed and operate
within the tolerances applicable for the airplane.
Levels 6 must also include communication equipment
(inter-phone and air/ground) like that in the airplane
and, if appropriate to the operation being conducted,
an oxygen mask microphone system.
Level 5 need have only that navigation equipment necessary to fly an instrument approach.
3.c ........
Installed systems must simulate the applicable airplane
system operation, both on the ground and in flight. Installed systems must be operative to the extent that
applicable normal, abnormal, and emergency operating procedures included in the sponsor’s training
programs can be accomplished.
Level 6 must simulate all applicable airplane flight, navigation, and systems operation.
Level 5 must have at least functional flight and navigational controls, displays, and instrumentation.
Level 4 must have at least one airplane system installed
and functional.
X
X
3.d ........
The lighting environment for panels and instruments
must be sufficient for the operation being conducted.
3.e ........
The FTD must provide control forces and control travel
that correspond to the airplane being simulated. Control forces must react in the same manner as in the
airplane under the same flight conditions.
X
3.f .........
The FTD must provide control forces and control travel
of sufficient precision to manually fly an instrument
approach.
<>
Notes
6
X
X
X
5
X
X
4. Instructor or Evaluator Facilities
4.a ........
In addition to the flight crewmember stations, suitable
seating arrangements for an instructor/check airman
and FAA Inspector must be available. These seats
must provide adequate view of crewmember’s
panel(s).
X
X
X
4.b ........
The FTD must have instructor controls that permit activation of normal, abnormal, and emergency conditions as may be appropriate. Once activated, proper
system operation must result from system management by the crew and not require input from the instructor controls.
X
X
X
X
X
These seats need not be a replica of an aircraft seat
and may be as simple as an office chair placed in an
appropriate position.
5. Motion System (not required)
sroberts on PROD1PC70 with RULES
5.a. .......
The FTD may have a motion system, if desired, although it is not required. If a motion system is installed and additional training, testing, or checking
credits are being sought on the basis of having a motion system, the motion system operation must not be
distracting and must be coupled closely to provide integrated sensory cues. The motion system must also
respond to abrupt input at the pilot’s position within
the allotted time, but not before the time when the airplane would respond under the same conditions.
A Subjective Test is required.
The motion system standards set out in part 60, appendix A for at least Level A simulators is acceptable.
6. Visual System (not required)
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
63507
TABLE B1A—MINIMUM FTD REQUIREMENTS—Continued
<<>>
FTD level
<>
Notes
No.
General FTD requirements
4
5
6
6.a. .......
The FTD may have a visual system, if desired, although
it is not required. If a visual system is installed, it must
not be distracting.
X
X
X
6.b. .......
If a visual system is installed and additional training, testing, or checking credits are being sought on the basis of having a visual system, the visual system must meet the following criteria:
6.b.1 .....
The visual system must respond to abrupt input at the
pilot’s position.
An SOC is required.
A Subjective Test is required. ..........................................
X
X
X
6.b.2 .....
The visual system must be at least a single channel,
non-collimated display?.
An SOC is required.
A Subjective Test is required. ..........................................
X
X
X
6.b.3 .....
The visual system must provide at least a field of view
of 18° vertical/24° horizontal for the pilot flying..
An SOC is required.
X
X
X
6.b.4 .....
The visual system must provide for a maximum parallax
of 10° per pilot.
An SOC is required.
X
X
X
6.b.5 .....
The visual scene content may not be distracting ............
An SOC is required.
A Subjective Test is required.
X
X
X
6.b.6 .....
The minimum distance from the pilot’s eye position to
the surface of a direct view display may not be less
than the distance to any front panel instrument.
An SOC is required.
X
X
X
6.b.7 .....
The visual system must provide for a minimum resolution of 5 arc-minutes for both computed and displayed
pixel size.
An SOC is required.
X
X
X
7. Sound System
7.a ........
The FTD must simulate significant cockpit sounds resulting from pilot actions that correspond to those
heard in the airplane.
Attachment 2 to Appendix B to Part 60—
Flight Training Device (FTD) Objective Tests
lllllllllllllllllllll
sroberts on PROD1PC70 with RULES
Begin Information
1. For the purposes of this attachment, the
flight conditions specified in the Flight
Conditions Column of Table B2A, are defined
as follows:
(1) Ground—on ground, independent of
airplane configuration;
(2) Take-off—gear down with flaps/slats in
any certified takeoff position;
(3) First segment climb—gear down with
flaps/slats in any certified takeoff position
(normally not above 50 ft AGL);
(4) Second segment climb—gear up with
flaps/slats in any certified takeoff position
(normally between 50 ft and 400 ft AGL);
(5) Clean—flaps/slats retracted and gear
up;
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X
(6) Cruise—clean configuration at cruise
altitude and airspeed;
(7) Approach—gear up or down with flaps/
slats at any normal approach position as
recommended by the airplane manufacturer;
and
(8) Landing—gear down with flaps/slats in
any certified landing position.
2. The format for numbering the objective
tests in appendix A, Attachment 2, Table
A2A, and the objective tests in appendix B,
Attachment 2, Table B2A, is identical.
However, each test required for FFSs is not
necessarily required for FTDs. Also, each test
required for FTDs is not necessarily required
for FFSs. Therefore, when a test number (or
series of numbers) is not required, the term
‘‘Reserved’’ is used in the table at that
location. Following this numbering format
provides a degree of commonality between
the two tables and substantially reduces the
potential for confusion when referring to
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objective test numbers for either FFSs or
FTDs.
3. The QPS Requirements section imposes
a duty on the sponsor or other data provider
to ensure that a steady state condition exists
at the instant of time captured by the
‘‘snapshot’’ for cases where the objective test
results authorize a ‘‘snapshot test’’ or a
‘‘series of snapshot tests’’ results in lieu of a
time-history. This is often verified by
showing that a steady state condition existed
from some period prior to, through some
period following, the snap shot. The time
period most frequently used is from 5
seconds prior through 2 seconds following
the instant of time captured by the snap shot.
Other time periods may be acceptable as
authorized by the NSPM.
4. The reader is encouraged to review the
Airplane Flight Simulator Evaluation
Handbook, Volumes I and II, published by
the Royal Aeronautical Society, London, UK,
E:\FR\FM\30OCR2.SGM
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63508
Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
and FAA Advisory Circulars (AC) 25–7, as
may be amended, Flight Test Guide for
Certification of Transport Category Airplanes,
and (AC) 23–8, as may be amended, Flight
Test Guide for Certification of Part 23
Airplanes, for references and examples
regarding flight testing requirements and
techniques.
5. If relevant winds are present in the
objective data, the wind vector should be
clearly noted as part of the data presentation,
expressed in conventional terminology, and
related to the runway being used for the test.
6. A Level 4 FTD does not require objective
tests and therefore, Level 4 is not addressed
in the following table.
End Information
lllllllllllllllllllll
sroberts on PROD1PC70 with RULES
Begin QPS Requirements
1. Test Requirements
a. The ground and flight tests required for
qualification are listed in Table B2A
Objective Evaluation. Computer generated
FTD test results must be provided for each
test except where an alternate test is
specifically authorized by the NSPM. If a
flight condition or operating condition is
required for the test but does not apply to the
airplane being simulated or to the
qualification level sought, it may be
disregarded (e.g., an engine out missed
approach for a single-engine airplane; a
maneuver using reverse thrust for an airplane
without reverse thrust capability). Each test
result is compared against the validation data
described in § 60.13, and in appendix B. The
results must be produced on an appropriate
recording device acceptable to the NSPM and
must include FTD number, date, time,
conditions, tolerances, and appropriate
dependent variables portrayed in comparison
to the validation data. Time histories are
required unless otherwise indicated in Table
B2A. All results must be labeled using the
tolerances and units given.
b. Table B2A in this attachment sets out
the test results required, including the
parameters, tolerances, and flight conditions
for FTD validation. Tolerances are provided
for the listed tests because mathematical
modeling and acquisition and development
of reference data are often inexact. All
tolerances listed in the following tables are
applied to FTD performance. When two
tolerance values are given for a parameter,
the less restrictive may be used unless
otherwise indicated.
c. Certain tests included in this attachment
must be supported with a Statement of
Compliance and Capability (SOC). In Table
B2A, requirements for SOCs are indicated in
the ‘‘Test Details’’ column.
d. When operational or engineering
judgment is used in making assessments for
flight test data applications for FTD validity,
such judgment must not be limited to a single
parameter. For example, data that exhibit
rapid variations of the measured parameters
may require interpolations or a ‘‘best fit’’ data
section. All relevant parameters related to a
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given maneuver or flight condition must be
provided to allow overall interpretation.
When it is difficult or impossible to match
FTD to airplane data throughout a time
history, differences must be justified by
providing a comparison of other related
variables for the condition being assessed.
e. It is not acceptable to program the FTD
so that the mathematical modeling is correct
only at the validation test points. Unless
noted otherwise, tests must represent
airplane performance and handling qualities
at operating weights and centers of gravity
(CG) typical of normal operation. If a test is
supported by aircraft data at one extreme
weight or CG, another test supported by
aircraft data at mid-conditions or as close as
possible to the other extreme is necessary.
Certain tests that are relevant only at one
extreme CG or weight condition need not be
repeated at the other extreme. The results of
the tests for Level 6 are expected to be
indicative of the device’s performance and
handling qualities throughout all of the
following:
(1) The airplane weight and CG envelope;
(2) The operational envelope; and
(3) Varying atmospheric ambient and
environmental conditions—including the
extremes authorized for the respective
airplane or set of airplanes.
f. When comparing the parameters listed to
those of the airplane, sufficient data must
also be provided to verify the correct flight
condition and airplane configuration
changes. For example, to show that control
force is within the parameters for a static
stability test, data to show the correct
airspeed, power, thrust or torque, airplane
configuration, altitude, and other appropriate
datum identification parameters must also be
given. If comparing short period dynamics,
normal acceleration may be used to establish
a match to the airplane, but airspeed,
altitude, control input, airplane
configuration, and other appropriate data
must also be given. If comparing landing gear
change dynamics, pitch, airspeed, and
altitude may be used to establish a match to
the airplane, but landing gear position must
also be provided. All airspeed values must be
properly annotated (e.g., indicated versus
calibrated). In addition, the same variables
must be used for comparison (e.g., compare
inches to inches rather than inches to
centimeters).
g. The QTG provided by the sponsor must
clearly describe how the FTD will be set up
and operated for each test. Each FTD
subsystem may be tested independently, but
overall integrated testing of the FTD must be
accomplished to assure that the total FTD
system meets the prescribed standards. A
manual test procedure with explicit and
detailed steps for completing each test must
also be provided.
h. In those cases where the objective test
results authorize a ‘‘snapshot test’’ or a
‘‘series of snapshot test’’ results in lieu of a
time-history result, the sponsor or other data
provider must ensure that a steady state
condition exists at the instant of time
captured by the ‘‘snapshot.’’
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i. For previously qualified FTDs, the tests
and tolerances of this attachment may be
used in subsequent continuing qualification
evaluations for any given test if the sponsor
has submitted a proposed MQTG revision to
the NSPM and has received NSPM approval.
j. FTDs are evaluated and qualified with an
engine model simulating the airplane data
supplier’s flight test engine. For qualification
of alternative engine models (either
variations of the flight test engines or other
manufacturer’s engines) additional tests with
the alternative engine models may be
required. This Attachment contains
guidelines for alternative engines.
k. Testing Computer Controlled Airplane
(CCA) simulators, or other highly augmented
airplane simulators, flight test data is
required for the Normal (N) and/or Nonnormal (NN) control states, as indicated in
this Attachment. Where test results are
independent of control state, Normal or Nonnormal control data may be used. All tests in
Table A2A require test results in the Normal
control state unless specifically noted
otherwise in the Test Details section
following the CCA designation. The NSPM
will determine what tests are appropriate for
airplane simulation data. When making this
determination, the NSPM may require other
levels of control state degradation for specific
airplane tests. Where Non-normal control
states are required, test data must be
provided for one or more Non-normal control
states, and must include the least augmented
state. Where applicable, flight test data must
record Normal and Non-normal states for:
(1) Pilot controller deflections or
electronically generated inputs, including
location of input; and
(2) Flight control surface positions unless
test results are not affected by, or are
independent of, surface positions.
l. Tests of handling qualities must include
validation of augmentation devices. FTDs for
highly augmented airplanes will be validated
both in the unaugmented configuration (or
failure state with the maximum permitted
degradation in handling qualities) and the
augmented configuration. Where various
levels of handling qualities result from
failure states, validation of the effect of the
failure is necessary. Requirements for testing
will be mutually agreed to between the
sponsor and the NSPM on a case-by-case
basis.
m. Some tests will not be required for
airplanes using airplane hardware in the FTD
cockpit (e.g., ‘‘side stick controller’’). These
exceptions are noted in Section 2 ‘‘Handling
Qualities’’ in Table B2A of this attachment.
However, in these cases, the sponsor must
provide a statement that the airplane
hardware meets the appropriate
manufacturer’s specifications and the
sponsor must have supporting information to
that fact available for NSPM review.
End QPS Requirements
lllllllllllllllllllll
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
63509
TABLE B2A.—FLIGHT TRAINING DEVICE (FTD) OBJECTIVE TESTS
<<< QPS Requirements >>>
<< Information >>
Test
FTD level
Tolerances
Number
Flight conditions
Test details
Title
Notes
5
6
1. Performance
(Reserved).
1.b ..............
Takeoff.
1.b.1 ...........
Ground Acceleration
Time.
1.b.2.
through
1.b.6.
(Reserved)
1.b.7 ...........
Rejected Takeoff ........
1.b.8 ...........
(Reserved)
1.c ..............
Climb
1.c.1 ...........
Normal Climb all engines operating.
1.c.2.
through
1.c.4.
(Reserved)
1.d ..............
(Reserved)
1.e ..............
(Reserved)
1.f ...............
Engines
1.f.1 ............
sroberts on PROD1PC70 with RULES
1.a ..............
Acceleration ...............
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±5% time or ±1 sec .............
Takeoff .................
Record acceleration time for a
minimum of 80%
of the segment
from brake release to VR.
Preliminary aircraft certification
data may be
used.
X
±3% time or ±1 second .......
Dry Runway .........
Record time for at
least 80% of the
segment from
initiation of the
Rejected Takeoff to full stop.
X
±3 kt airspeed, ±5% or ±100
ft/min (0.5 m/sec) climb
rate.
Clean ....................
Flight test data or
airplane performance manual data may be
used. Record at
nominal climb
speed and at
nominal altitude.
May be a snapshot test result.
X
X
±10% Tt, ±1 sec for Level 5
Approach or Landing.
Record engine
power (N1, N2,
EPR, Torque,
Manifold Pressure) from idle
to maximum
takeoff power for
a rapid (slam)
throttle movement.
X
X
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This test is required only if
RTO training
credit is sought.
Tt is the total time
from initial throttle movement to
reaching 90% of
go around
power.
63510
Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
TABLE B2A.—FLIGHT TRAINING DEVICE (FTD) OBJECTIVE TESTS—Continued
<<< QPS Requirements >>>
<< Information >>
Test
FTD level
Tolerances
Number
Deceleration ...............
Test details
Title
1.f.2 ............
Flight conditions
Notes
5
±10% Tt, or ±1 sec for Level
5.
Ground .................
Record engine
power (N1, N2,
EPR, Torque,
Manifold Pressure) from maximum takeoff
power to idle for
a rapid (slam)
throttle movement.
6
X
X
Tt is the total time
from initial throttle movement to
reaching 90%
decay of maximum takeoff
power.
2. Handling Qualities
(3) For FTDs requiring Static tests at the controls (i.e., column, wheel, rudder pedal), special
test fixtures will not be required during initial or upgrade evaluations if the sponsor’s QTG/
MQTG shows both test fixture resultsand the results of an alternative approach, such as computer plots produced concurrently, that show satisfactory agreement. Repeat of the alternative
method during the initial or upgrade evaluation would then satisfy this test requirement
(3) Static Control Tests
2.a.1.a ........
Pitch Controller Position vs. Force and
Surface Position
Calibration.
±2 lb (0.9 daN) breakout,
±10% or ±5 lb (2.2 daN)
force, ±2° elevator.
Ground .................
Record results for
an uninterrupted
control sweep to
the stops.
2.a.1.b ........
Pitch Controller Position vs. Force.
±2 lb (0.9 daN) breakout,
±10% or ±5 lb (2.2 daN)
force.
Ground .................
Record results for
an uninterrupted
control sweep to
the stops.
2.a.2.a ........
Roll Controller Position vs. Force and
Surface Position
Calibration.
±2 lb (0.9 daN) breakout,
±10% or ±3 lb (1.3 daN)
force, ±2° aileron, ±3°
spoiler angle.
Ground .................
Record results for
an uninterrupted
control sweep to
the stops.
2.a.2.b ........
sroberts on PROD1PC70 with RULES
2.a ..............
Roll Controller Position vs. Force.
±2 lb (0.9 daN) breakout,
±10% or ±3 lb (1.3 daN)
force.
Ground .................
Record results for
an uninterrupted
control sweep to
the stops.
Testing of position
versus force is
not applicable if
forces are generated solely by
use of airplane
hardware in the
FTD.
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X
X
Applicable only on
continuing qualification evaluations. The intent
is to design the
control feel for
Level 5 to be
able to manually
fly an instrument
approach; and
not to compare
results to flight
test or other
such data.
X
X
Applicable only on
continuing qualification evaluations. The intent
is to design the
control feel for
Level 5 to be
able to manually
fly an instrument
approach; and
not to compare
results to flight
test or other
such data.
Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
63511
TABLE B2A.—FLIGHT TRAINING DEVICE (FTD) OBJECTIVE TESTS—Continued
<<< QPS Requirements >>>
<< Information >>
Test
FTD level
Tolerances
Flight conditions
Test details
Notes
Title
2.a.3.a ........
Rudder Pedal Position
vs. Force and Surface Position Calibration.
±5 lb (2.2 daN) breakout,
±10% or ±5 lb (2.2 daN)
force, ±2° rudder angle.
Ground .................
Record results for
an uninterrupted
control sweep to
the stops.
2.a.3.b ........
Rudder Pedal Position
vs. Force.
±5 lb (2.2 daN) breakout,
±10% or ±5 lb (2.2 daN)
force.
Ground .................
Record results for
an uninterrupted
control sweep to
the stops.
2.a.4 ...........
Nosewheel Steering
Controller Force.
±2 lb (0.9 daN) breakout,
±10% or ±3 lb (1.3 daN)
force.
Ground .................
..............................
X
2.a.5 ...........
Rudder Pedal Steering
Calibration.
±2° nosewheel angle ...........
Ground .................
..............................
X
2.a.6 ...........
Pitch Trim Indicator
vs. Surface Position
Calibration.
±0.5° of computed trim surface angle.
Ground .................
..............................
X
2.a.7 ...........
(Reserved).
2.a.8 ...........
Alignment of Cockpit
Throttle Lever vs.
Selected Engine Parameter.
±5° of throttle lever angle
±0.8 in (2 cm) for power
control without angular
travel.
Ground .................
Requires simultaneous recording
for all engines.
The tolerances
apply against
airplane data
and between engines. In the
case of propeller
powered airplanes, if a propeller lever is
present, it must
also be checked.
X
2.a.9 ...........
Brake Pedal Position
vs. Force.
±5 lb (2.2 daN) or 10%
force.
Ground .................
Two data points
are required:
zero and maximum deflection.
Computer output
results may be
used to show
compliance.
X
2.b ..............
sroberts on PROD1PC70 with RULES
Number
5
(Reserved)
2.c ..............
Longitudinal Control Tests
Power setting is that required for level flight unless otherwise specified
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6
X
X
Applicable only on
continuing qualification evaluations. The intent
is to design the
control feel for
Level 5 to be
able to manually
fly an instrument
approach; and
not to compare
results to flight
test or other
such data.
The purpose of the
test is to compare the FTD
against design
data or equivalent.
Test not required
unless RTO
credit is sought.
63512
Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
TABLE B2A.—FLIGHT TRAINING DEVICE (FTD) OBJECTIVE TESTS—Continued
<<< QPS Requirements >>>
<< Information >>
Test
FTD level
Tolerances
Flight conditions
Title
2.c.1 ...........
Power Change Force
±5 lb (2.2 daN) or, ±20%
force.
Cruise or Approach.
2.c.2 ...........
Flap/Slat Change
Force.
±5 lb (2.2 daN) or, ±20%
force.
2.c.3 ...........
Gear Change Force ...
2.c.5 ...........
Notes
(Reserved)
2.c.4 ...........
5
6
May be a series of
snapshot test results. Power
change dynamics test as described in test
2.c.1 of Table
A2A of this part
will be accepted.
X
X
Takeoff through
initial flap retraction, and approach to landing.
May be a series of
snapshot test results. Flap/Slat
change dynamics test as described in test
2.c.2 of Table
A2A of this part
will be accepted.
X
X
±5 lb (2.2 daN) or, ±20%
force.
Takeoff (retraction)
and Approach
(extension).
May be a series of
snapshot test results. Gear
change dynamics test as described in test
2.c.4 of Table
A2A of this part
will be accepted.
X
X
Longitudinal Trim .......
±0.5° trim surface angle ±1°
elevator ±1° pitch angle
±5% net thrust or equivalent.
Cruise, Approach,
and Landing.
May be a series of
snapshot tests.
Level 5 may use
equivalent stick
and trim controllers in lieu of elevator and trim
surface.
X
X
2.c.6 ...........
Longitudinal Maneuvering Stability
(Stick Force/g).
±5 lb (±2.2 daN) or ±10%
pitch controller force.
Cruise, Approach
and Landing.
May be a series of
snapshot test results.
2.c.7 ...........
Longitudinal Static
Stability.
±5 lb (±2.2 daN) or ±10%
pitch controller force.
Approach ..............
May be a series of
snapshot test results. Level 5
must exhibit
positive static
stability, but
need not comply
with the numerical tolerance.
X
X
2.c.8 ...........
sroberts on PROD1PC70 with RULES
Number
Test details
Stall Warning (actuation of stall warning device).
±3 kts. airspeed, ±2° bank ..
Second Segment
Climb, and Approach or Landing.
Record the stall
warning signal.
X
X
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X
The stall maneuver may be entered with thrust
at or near idle
power and
wings level (1g).
Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
63513
TABLE B2A.—FLIGHT TRAINING DEVICE (FTD) OBJECTIVE TESTS—Continued
<<< QPS Requirements >>>
<< Information >>
Test
FTD level
Tolerances
Flight conditions
Test details
Number
Title
2.c.9.a ........
Phugoid Dynamics .....
±10% period, ±10% of time
to 1⁄2 or double amplitude
or ±.02 of damping ratio.
Cruise ...................
The test must include whichever
is less of the following: Three
full cycles (six
overshoots after
the input is completed), or the
number of cycles sufficient to
determine time
to 1⁄2 or double
amplitude.
2.c.9.b ........
Phugoid Dynamics .....
±10% period, Representative damping.
Cruise ...................
The test must include whichever
is less of the following: Three
full cycles (six
overshoots after
the input is completed), or the
number of cycles sufficient to
determine representative
damping.
2.c.10 .........
Short Period Dynamics.
±1.5° pitch angle or ±2°/sec
pitch rate, ±0.10g acceleration.
Cruise ...................
..............................
2.d ..............
Notes
5
6
(3) Lateral Directional Tests
X
X
X
(3) Power setting is that required for level flight unless otherwise specified.
(Reserved). ................
..............................................
..............................
..............................
......
......
2.d.2 ...........
Roll Response (Rate)
±10% or ±2°/sec roll rate ....
Cruise, and Approach or Landing.
..............................
X
X
Results should be
recorded for normal roll controller deflection
(about one-third
of maximum roll
controller travel).
May be combined with step
input of flight
deck roll controller test
(2.d.3.).
2.d.3 ...........
Roll Response to
Cockpit Roll Controller Step Input.
±10% or ±2° bank angle .....
Approach or Landing.
..............................
X
May be combined
with roll response (rate)
test (2.d.2.).
2.d.4.a ........
sroberts on PROD1PC70 with RULES
2.d.1 ...........
Spiral Stability ............
Correct trend and ±3° or
±10% bank angle in 20
seconds.
Cruise ...................
..............................
X
Airplane data averaged from multiple tests in
same direction
may be used.
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63514
Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
TABLE B2A.—FLIGHT TRAINING DEVICE (FTD) OBJECTIVE TESTS—Continued
<<< QPS Requirements >>>
<< Information >>
Test
FTD level
Tolerances
Flight conditions
Test details
Notes
Number
Title
5
6
2.d.4.b ........
Spiral Stability ............
Correct trend .......................
Cruise ...................
..............................
X
2.d.5 ...........
(Reserved) .................
..............................................
..............................
..............................
......
2.d.6.a ........
Rudder Response ......
±2°/sec or ±10% yaw rate. ..
Approach or Landing.
Not required if rudder input and response is shown
in Dutch Roll
Test (test 2.d.7).
2.d.6.b ........
Rudder Response ......
Roll rate ±2°/sec, bank
angle ±3°.
Approach or Landing.
May be roll response to a
given rudder deflection.
2.d.7 ...........
Dutch, Roll, (Yaw
Damper OFF).
±0.5 sec or ±10% of period,
±10% of time to 1⁄2 or
double amplitude or ±.02
of damping ratio.
Cruise, and Approach or Landing.
Record results for
at least 6 complete cycles with
stability augmentation OFF,
or the number of
cycles sufficient
to determine
time to 1⁄2 or
double amplitude.
2.d.8 ...........
Steady State Sideslip
For given rudder position
Approach or Land±2° bank angle, ±1° sideing.
slip angle, ±10% or ±2°
aileron, ±10% or ±5°
spoiler or equivalent roll,
controller position or force.
May be a series of
snapshot test results. Propeller
driven airplanes
must test in
each direction.
X
X
2.e. through
2.h.
(Reserved) .................
..............................................
..............................
..............................
......
......
3 .................
(Reserved) .................
..............................................
..............................
..............................
......
......
4 .................
(Reserved) .................
..............................................
..............................
..............................
......
......
5 .................
(Reserved) .................
..............................................
..............................
..............................
......
......
300 ms (or less) after airplane response.
Take-off cruise,
and approach or
landing.
One test is required in each
axis (pitch, roll
and yaw) for
each of the
three conditions
(take-off, cruise,
and approach or
landing).
X
X
Airplane data averaged from multiple tests in
same direction
may be used.
......
X
X
X
6. FTD System Response Time
sroberts on PROD1PC70 with RULES
6a. ..............
Latency.
Transport Delay. If Transport Delay is chosen to demonstrate response time than Latency, it is
expected that when reviewing those existing tests where latency can be identified (e.g., short
period, roll response, rudder response) the sponsor and the NSPM will apply additional scrutiny
to ensure proper FTD response.
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A rudder step
input of 20%–
30% rudder
pedal throw may
be used.
Sideslip angle is
matched for repeatability on
continuing qualification evaluations.
Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
63515
TABLE B2A.—FLIGHT TRAINING DEVICE (FTD) OBJECTIVE TESTS—Continued
<<< QPS Requirements >>>
<< Information >>
Test
FTD level
Tolerances
Number
Flight conditions
Test details
Title
Notes
5
300 ms (or less) after controller movement.
3. For Additional Information on the
Following Topics, Please Refer to Appendix
A, Attachment 2, and the Indicated
Paragraph Within That Attachment
• Control Dynamics, paragraph 3.
• Motion System, paragraph 5.
• Sound System, paragraph 6.
• Engineering Simulator Validation Data,
paragraph 8.
• Approval Guidelines for Engineering
Simulator Validation Data, paragraph 9.
• Validation Test Tolerances, paragraph
10.
• Validation Data Road Map, paragraph 11.
• Acceptance Guidelines for Alternative
Engines Data, paragraph 12.
• Acceptance Guidelines for Alternative
Avionics, paragraph 13.
• Transport Delay Testing, paragraph 14.
• Continuing Qualification Evaluation
Validation Data Presentation, paragraph 15.
4. Alternative Objective Data for FTD Level
5.
lllllllllllllllllllll
N/A .......................
A separate test is
required in each
axis (pitch, roll,
and yaw).
Begin QPS Requirements
a. This paragraph (including the following
tables) is relevant only to FTD Level 5. It is
provided because this level is required to
simulate the performance and handling
characteristics of a set of airplanes with
similar characteristics, such as normal
airspeed/altitude operating envelope and the
same number and type of propulsion systems
(engines).
b. Tables B2B through B2E reflect FTD
performance standards that are acceptable to
the FAA. A sponsor must demonstrate that a
device performs within these parameters, as
applicable. If a device does not meet the
established performance parameters for some
or for all of the applicable tests listed in
Tables B2B through B2E, the sponsor may
use NSP accepted flight test data for
comparison purposes for those tests.
c. Sponsors using the data from Tables B2B
through B2E must comply with the
following:
(1) Submit a complete QTG, including
results from all of the objective tests
6
X
X
appropriate for the level of qualification
sought as set out in Table B2A. The QTG
must highlight those results that demonstrate
the performance of the FTD is within the
allowable performance ranges indicated in
Tables B2B through B2E, as appropriate.
(2) The QTG test results must include all
relevant information concerning the
conditions under which the test was
conducted; e.g., gross weight, center of
gravity, airspeed, power setting, altitude
(climbing, descending, or level), temperature,
configuration, and any other parameter that
impacts the conduct of the test.
(3) The test results become the validation
data against which the initial and all
subsequent recurrent evaluations are
compared. These subsequent evaluations will
use the tolerances listed in Table B2A.
(4) Subjective testing of the device must be
performed to determine that the device
performs and handles like an airplane within
the appropriate set of airplanes.
TABLE B2B. — ALTERNATIVE DATA SOURCE FOR FTD LEVEL 5 SMALL, SINGLE ENGINE (RECIPROCATING) AIRPLANE
<<< QPS requirement >>>
Applicable test
No.
Authorized
performance range
Title and procedure
1. Performance
1.c
Climb.
1.c.1 .....
Normal climb with nominal gross weight, at best rate-of-climb airspeed.
1.f .........
Engines.
1.f.1 ......
Acceleration; idle to takeoff power ..................................................
2–4 Seconds.
1.f.2 ......
Deceleration; takeoff power to idle .................................................
2–4 Seconds.
Climb rate = 500–1200 fpm (2.5–6 m/sec).
2. Handling Qualities
Longitudinal Tests.
2.c.1 .....
sroberts on PROD1PC70 with RULES
2.c ........
Power change force
(a) Trim for straight and level flight at 80% of normal cruise airspeed with necessary power. Reduce power to flight idle. Do
not change trim or configuration. After stabilization, record column force necessary to maintain original airspeed.
5–15 lbs (2.2–6.6 daN) of force (Pull).
OR
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
TABLE B2B. — ALTERNATIVE DATA SOURCE FOR FTD LEVEL 5 SMALL, SINGLE ENGINE (RECIPROCATING) AIRPLANE—
Continued
<<< QPS requirement >>>
Applicable test
No.
Authorized
performance range
Title and procedure
(b) Trim for straight and level flight at 80% of normal cruise airspeed with necessary power. Add power to maximum setting.
Do not change trim or configuration. After stabilized, record column force necessary to maintain original airspeed.
2.c.2 .....
5–15 lbs (2.2–6.6 daN) of force (Push).
Flap/slat change force.
(a) Trim for straight and level flight with flaps fully retracted at a
constant airspeed within the flaps- extended airspeed range.
Do not adjust trim or power. Extend the flaps to 50% of full flap
travel. After stabilized, record stick force necessary to maintain
original airspeed.
5–15 lbs (2.2–6.6 daN) of force (Pull).
OR
(b) Trim for straight and level flight with flaps extended to 50% of
full flap travel, at a constant airspeed within the flaps-extended
airspeed range. Do not adjust trim or power. Retract the flaps
to zero. After stabilized, record stick force necessary to maintain original airspeed.
2.c.4 .....
5–15 lbs (2.2–6.6 daN) of force (Push).
Gear change force
(a) Trim for straight and level flight with landing gear retracted at
a constant airspeed within the landing gear-extended airspeed
range. Do not adjust trim or power. Extend the landing gear.
After stabilized, record stick force necessary to maintain original airspeed.
2–12 lbs (0.88–5.3 daN) of force (Pull).
OR
(b) Trim for straight and level flight with landing gear extended, at
a constant airspeed within the landing gear-extended airspeed
range. Do not adjust trim or power. Retract the landing gear.
After stabilized, record stick force necessary to maintain original airspeed.
2–12 lbs (0.88–5.3 daN) of force (Push).
2.c.5 .....
Longitudinal trim ..............................................................................
Must be able to trim longitudinal stick force to ‘‘zero’’ in each of
the following configurations: cruise; approach; and landing.
2.c.7 .....
Longitudinal static stability ..............................................................
Must exhibit positive static stability.
2.c.8 .....
Stall warning (actuation of stall warning device) with nominal
gross weight; wings level; and a deceleration rate of approximately one (1) knot per second.
40–60 knots; ± 5° of bank.
(b) Clean configuration ....................................................................
Landing configuration speed + 10–20%.
2.c.9.b ..
Phugoid dynamics ...........................................................................
Must have a phugoid with a period of 30–60 seconds. May not
reach 1⁄2 or double amplitude in less than 2 cycles.
2.d ........
Lateral Directional Tests.
2.d.2 .....
sroberts on PROD1PC70 with RULES
(a) Landing configuration ................................................................
Roll response ..................................................................................
Roll rate must be measured through at least 30 degrees of roll.
Aileron control must be deflected 1⁄2 (50 percent) of maximum
travel.
Must have a roll rate of 6–40 degrees/second.
2.d.4.b ..
Spiral stability ..................................................................................
Cruise configuration and normal cruise airspeed. Establish a 20–
30 degree bank. When stabilized, neutralize the aileron control
and release. Must be completed in both directions of turn.
Initial bank angle (± 5 degrees) after 20 seconds.
2.d.6.b ..
Rudder response .............................................................................
6–12 degrees/second yaw rate.
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63517
TABLE B2B. — ALTERNATIVE DATA SOURCE FOR FTD LEVEL 5 SMALL, SINGLE ENGINE (RECIPROCATING) AIRPLANE—
Continued
<<< QPS requirement >>>
Applicable test
No.
Authorized
performance range
Title and procedure
Use 50 percent of maximum rudder deflection. (Applicable to approach or landing configuration.).
2.d.7 .....
Dutch roll, yaw damper off ..............................................................
(Applicable to cruise and approach configurations.).
A period of 2–5 seconds; and 1⁄2–2 cycles.
2.d.8 .....
Steady state sideslip .......................................................................
Use 50 percent rudder deflection. (Applicable to approach and
landing degrees of configurations.).
2–10 degrees of bank; 4–10 degrees of sideslip; and
2–10 degrees of aileron.
6 ...........
FTD System Response Time.
6.a ........
Cockpit instrument systems response to an abrupt pilot controller
input. One test is required in each axis (pitch, roll, yaw).
300 milliseconds or less.
TABLE B2C.—ALTERNATIVE DATA SOURCE FOR FTD LEVEL 5 SMALL, MULTI-ENGINE (RECIPROCATING) AIRPLANE
<<< QPS requirement >>>
Applicable test
Authorized performance range
Number
Title and procedure
1. Performance
1.c
Climb
1.c.1 .....
Normal climb with nominal gross weight, at best rate-of-climb airspeed.
1.f. ........
Engines
1.f.1 ......
Acceleration; idle to takeoff power ..................................................
2–5 Seconds
1.f.2 ......
Deceleration; takeoff power to idle .................................................
2–5 Seconds
Climb airspeed = 95–115 knots. Climb rate = 500–1500 fpm (2.5–
7.5 m/sec).
2. Handling Qualities
2.c Longitudinal Tests
2.c.1 .....
Power change force
a) Trim for straight and level flight at 80% of normal cruise airspeed with necessary power. Reduce power to flight idle. Do
not change trim or configuration. After stabilized, record column
force necessary to maintain original airspeed.
10–25 lbs (2.2–6.6 daN) of force (Pull).
OR
b) Trim for straight and level flight at 80% of normal cruise airspeed with necessary power. Add power to maximum setting.
Do not change trim or configuration. After stabilized, record column force necessary to maintain original airspeed.
sroberts on PROD1PC70 with RULES
2.c.2 .....
5–15 lbs (2.2–6.6 daN) of force (Push).
Flap/slat change force .....................................................................
a) Trim for straight and level flight with flaps fully retracted at a
constant airspeed within the flaps-extended airspeed range. Do
not adjust trim or power. Extend the flaps to 50% of full flap
travel. After stabilized, record stick force necessary to maintain
original airspeed.
5–15 lbs (2.2–6.6 daN) of force (Pull).
OR
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
TABLE B2C.—ALTERNATIVE DATA SOURCE FOR FTD LEVEL 5 SMALL, MULTI-ENGINE (RECIPROCATING) AIRPLANE—
Continued
<<< QPS requirement >>>
Applicable test
Authorized performance range
Number
Title and procedure
b) Trim for straight and level flight with flaps extended to 50% of
full flap travel, at a constant airspeed within the flaps-extended
airspeed range. Do not adjust trim or power. Retract the flaps
to zero. After stabilized, record stick force necessary to maintain original airspeed.
2.c.4 .....
5–15 lbs (2.2–6.6 daN) of force (Push).
Gear change force
a) Trim for straight and level flight with landing gear retracted at a
constant airspeed within the landing gear-extended airspeed
range. Do not adjust trim or power. Extend the landing gear.
After stabilized, record stick force necessary to maintain original airspeed.
2–12 lbs (0.88–5.3 daN) of force (Pull).
OR
b) Trim for straight and level flight with landing gear extended, at
a constant airspeed within the landing gear-extended airspeed
range. Do not adjust trim or power. Retract the landing gear.
After stabilized, record stick force necessary to maintain original airspeed.
2–12 lbs (0.88–5.3 daN) of force (Push).
2.c.4 .....
Longitudinal trim ..............................................................................
Must be able to trim longitudinal stick force to ‘‘zero’’ in each of
the following configurations: cruise; approach; and landing.
2.c.7 .....
Longitudinal static stability ..............................................................
Must exhibit positive static stability.
2.c.8 .....
Stall warning (actuation of stall warning device) with nominal
gross weight; wings level; and a deceleration rate of approximately one (1) knot per second.
a) Landing configuration: .................................................................
60–90 knots; ± 5° of bank.
b) Clean configuration: ....................................................................
Landing configuration speed + 10–20%.
2.c.9.b ..
Phugoid dynamics ...........................................................................
Must have a phugoid with a period of 30–60 seconds. May not
reach 1⁄2 or double amplitude in less than 2 cycles.
2.d ........
Lateral Directional Tests
2.d.2 .....
Roll response ..................................................................................
Roll rate must be measured through at least 30 degrees of roll. ...
Aileron control must be deflected 1⁄2 (50 percent) of maximum
travel.
Must have a roll rate of 6–40 degrees/second.
2.d.4.b ..
Spiral stability ..................................................................................
Cruise configuration and normal cruise airspeed. Establish a 20–
30 degree bank. When stabilized, neutralize the aileron control
and release. Must be completed in both directions of turn.
Initial bank angle (± 5 degrees) after 20 seconds.
2.d.6.b ..
Rudder response .............................................................................
Use 50 percent of maximum rudder deflection. (Applicable to approach or landing configuration.).
6–12 degrees/second yaw rate.
2.d.7 .....
Dutch roll, yaw damper off (Applicable to cruise and approach
configurations.).
A period of 2–5 seconds; and 1⁄2-2 cycles.
2.d.8 .....
Steady state sideslip .......................................................................
2–10 degrees of bank; 4–10 degrees of sideslip; and 2–10 degrees of aileron.
sroberts on PROD1PC70 with RULES
Use 50 percent rudder deflection. (Applicable to approach and
landing configurations.).
6. FTD System Response Time
6.a ........
Cockpit instrument systems response to an abrupt pilot controller
input. One test is required in each axis (pitch, roll, yaw).
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63519
TABLE B2D.—ALTERNATIVE DATA SOURCE FOR FTD LEVEL 5 SMALL, SINGLE ENGINE (TURBO-PROPELLER) AIRPLANE
<<< QPS requirement >>>
Applicable test
Title and procedure
Authorized
performance range
1.c ........
Climb
1.c.1 .....
Normal climb with nominal gross weight, at best rate-of-climb airspeed.
Climb airspeed = 95–115 knots, Climb rate = 800–1800 fpm (4–9
m/sec).
1.f .........
Engines
1.f.1 ......
Acceleration; idle to takeoff power ..................................................
4–8 Seconds
1.f.2 ......
Deceleration; takeoff power to idle .................................................
3–7 Seconds
Number
1. Performance
2. Handling Qualities
2.c Longitudinal Tests
2.c.1 .....
Power change force
a) Trim for straight and level flight at 80% of normal cruise airspeed with necessary power. Reduce power to flight idle. Do
not change trim or configuration. After stabilized, record column
force necessary to maintain original airspeed.
8 lbs (3.5 daN) of Push force—8 lbs (3.5 daN) of Pull force
OR
b) Trim for straight and level flight at 80% of normal cruise airspeed with necessary power. Add power to maximum setting.
Do not change trim or configuration. After stabilized, record column force necessary to maintain original airspeed.
2.c.2 .....
12–22 lbs (5.3–9.7 daN) of force (Push)
Flap/slat change force
a) Trim for straight and level flight with flaps fully retracted at a
constant airspeed within the flaps-extended airspeed range. Do
not adjust trim or power. Extend the flaps to 50% of full flap
travel. After stabilized, record stick force necessary to maintain
original airspeed.
5–15 lbs (2.2–6.6 daN) of force (Pull).
OR
b) Trim for straight and level flight with flaps extended to 50% of
full flap travel, at a constant airspeed within the flaps-extended
airspeed range. Do not adjust trim or power. Retract the flaps
to zero. After stabilized, record stick force necessary to maintain original airspeed.
2.c.4 .....
5–15 lbs (2.2–6.6 daN) of force (Push)
Gear change force
a) Trim for straight and level flight with landing gear retracted at a
constant airspeed within the landing gear-extended airspeed
range. Do not adjust trim or power. Extend the landing gear.
After stabilized, record stick force necessary to maintain original airspeed.
2–12 lbs (0.88–5.3 daN) of force (Pull)
OR
sroberts on PROD1PC70 with RULES
b) Trim for straight and level flight with landing gear extended, at
a constant airspeed within the landing gear-extended airspeed
range. Do not adjust trim or power. Retract the landing gear.
After stabilized, record stick force necessary to maintain original airspeed.
2–12 lbs (0.88– 5.3 daN) of force (Push)
2.b.5 .....
Longitudinal trim ..............................................................................
Must be able to trim longitudinal stick force to ‘‘zero’’ in each of
the following configurations: cruise; approach; and landing.
2.c.7 .....
Longitudinal static stability ..............................................................
Must exhibit positive static stability.
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
TABLE B2D.—ALTERNATIVE DATA SOURCE FOR FTD LEVEL 5 SMALL, SINGLE ENGINE (TURBO-PROPELLER) AIRPLANE—
Continued
<<< QPS requirement >>>
Applicable test
Authorized
performance range
Number
Title and procedure
2.c.8 .....
Stall warning (actuation of stall warning device) with nominal
gross weight; wings level; and a deceleration rate of approximately one (1) knot per second.
a) Landing configuration: .................................................................
60–90 knots; ± 5° of bank.
b) Clean configuration: ....................................................................
Landing configuration speed + 10–20%.
2.c.8.b ..
Phugoid dynamics ...........................................................................
Must have a phugoid with a period of 30–60 seconds. May not
reach 1⁄2 or double amplitude in less than 2 cycles.
2.d ........
Lateral Directional Tests
2.d.2 .....
Roll response ..................................................................................
Roll rate must be measured through at least 30 degrees of roll.
Aileron control must be deflected 1⁄2 (50 percent) of maximum
travel.
Must have a roll rate of 6–40 degrees/second.
2.d.4.b ..
Spiral stability ..................................................................................
Cruise configuration and normal cruise airspeed. Establish a 20–
30 degree bank. When stabilized, neutralize the aileron control
and release. Must be completed in both directions of turn.
Initial bank angle (± 5 degrees) after 20 seconds.
2.d.6.b ..
Rudder response .............................................................................
Use 50 percent of maximum rudder deflection. (Applicable to approach or landing configuration.).
6–12 degrees/second yaw rate.
2.d.7 .....
Dutch roll, yaw damper off ..............................................................
(Applicable to cruise and approach configurations.).
A period of 2–5 seconds; and 1.2–3 cycles.
2.d.8 .....
Steady state sideslip .......................................................................
2–10 degrees of bank; 4–10 degrees of sideslip; and 2–10 degrees of aileron.
Use 50 percent rudder deflection. (Applicable to approach and
landing degrees of configurations.).
6. FTD System Response Time
6.a ........
Cockpit instrument systems response to an abrupt pilot controller
input. One test is required in each axis (pitch, roll, yaw).
300 milliseconds or less.
TABLE B2E.—ALTERNATIVE DATA SOURCE FOR FTD LEVEL 5 MULTI-ENGINE (TURBO-PROPELLER) AIRPLANE
<<< QPS requirement >>>
Applicable test
Authorized performance range
No.
Title and procedure
1. Performance
Climb
1.b.1 .....
Normal climb with nominal gross weight, at best rate-of-climb airspeed
1.f .........
Engines
1.f.1 ......
Acceleration; idle to takeoff power ..................................................
2–6 Seconds.
1.f.2 ......
sroberts on PROD1PC70 with RULES
1.c ........
Deceleration; takeoff power to idle .................................................
1–5 Seconds.
Climb airspeed= 120–140 knots.
Climb rate= 1000–3000 fpm (5–15 m/sec).
2. Handling Qualities
2.c Longitudinal Tests
2.c.1 .....
Power change force
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63521
TABLE B2E.—ALTERNATIVE DATA SOURCE FOR FTD LEVEL 5 MULTI-ENGINE (TURBO-PROPELLER) AIRPLANE—Continued
<<< QPS requirement >>>
Applicable test
Authorized performance range
No.
Title and procedure
a) Trim for straight and level flight at 80% of normal cruise airspeed with necessary power. Reduce power to flight idle. Do
not change trim or configuration. After stabilized, record column
force necessary to maintain original airspeed
8 lbs (3.5 daN) of Push force to 8 lbs (3.5 daN) of Pull force.
OR
b) Trim for straight and level flight at 80% of normal cruise airspeed with necessary power. Add power to maximum setting.
Do not change trim or configuration. After stabilized, record column force necessary to maintain original airspeed
2.c.2 .....
12–22 lbs (5.3–9.7 daN) of force (Push).
Flap/slat change force
a) Trim for straight and level flight with flaps fully retracted at a
constant airspeed within the flaps-extended airspeed range. Do
not adjust trim or power. Extend the flaps to 50% of full flap
travel. After stabilized, record stick force necessary to maintain
original airspeed
5–15 lbs (2.2–6.6 daN) of force (Pull).
OR
b) Trim for straight and level flight with flaps extended to 50% of
full flap travel, at a constant airspeed within the flaps-extended
airspeed range. Do not adjust trim or power. Retract the flaps
to zero. After stabilized, record stick force necessary to maintain original airspeed
2.c.4 .....
5–15 lbs (2.2–6.6 daN) of force (Push).
Gear change force
a) Trim for straight and level flight with landing gear retracted at a
constant airspeed within the landing gear-extended airspeed
range. Do not adjust trim or power. Extend the landing gear.
After stabilized, record stick force necessary to maintain original airspeed
2–12 lbs (0.88–5.3 daN) of force (Pull).
OR
b) Trim for straight and level flight with landing gear extended, at
a constant airspeed within the landing gear-extended airspeed
range. Do not adjust trim or power. Retract the landing gear.
After stabilized, record stick force necessary to maintain original airspeed
2–12 lbs (0.88–5.3 daN) of force (Push).
2.b.5 .....
Longitudinal trim ..............................................................................
Must be able to trim longitudinal stick force to ‘‘zero’’ in each of
the following configurations; cruise; approach; and landing.
2.c.7 .....
Longitudinal static stability ..............................................................
Must exhibit positive static stability.
2.c.8 .....
Stall warning (actuation of stall warning device) with nominal
gross weight; wings level; and a deceleration rate of approximately one (1) knot per second
a) Landing configuration ..................................................................
b) Clean configuration .....................................................................
2.c.8.b ..
80–100 knots; ± 5° of bank.
Landing configuration speed + 10–20%
Phugoid dynamics ...........................................................................
Must have a phugoid with a period of 30–60 seconds. May not
reach 1⁄2 or double amplitude in less than 2 cycles.
sroberts on PROD1PC70 with RULES
2.d Lateral Directional Test
2.d.2 .....
Roll response ..................................................................................
Roll rate must be measured through at least 30 degrees of roll.
Aileron control must be deflected approximately 1⁄2 (50 percent)
of maximum travel
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Must have a roll rate of 6–40 degrees/second.
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TABLE B2E.—ALTERNATIVE DATA SOURCE FOR FTD LEVEL 5 MULTI-ENGINE (TURBO-PROPELLER) AIRPLANE—Continued
<<< QPS requirement >>>
Applicable test
Authorized performance range
No.
Title and procedure
2.d.4.b ..
Spiral stability ..................................................................................
Cruise configuration and normal cruise airspeed. Establish a 20–
30 degree bank. When stabilized, neutralize the aileron control
and release. Must be completed in both directions of turn
Initial bank angle (±5 degrees) after 20 seconds.
2.d.6.b ..
Rudder response .............................................................................
Use 50 percent of maximum rudder deflection
(Applicable to approach or landing configuration.)
6–12 degrees/second yaw rate.
2.d.7 .....
Dutch roll, yaw damper off
(Applicable to cruise and approach configurations.)
A period of 2–5 seconds; and 1⁄2–3 cycles.
2.d.8 .....
Steady state sideslip .......................................................................
Use 50 percent rudder deflection ....................................................
(Applicable to approach and landing configurations.)
2–10 degrees of bank;
4–10 degrees of sideslip; and
2–10 degrees of aileron.
6. FTD System Response Time
6.a ........
Cockpit instrument systems response to an abrupt pilot controller
input. One test is required in each axis (pitch, roll, yaw)
End QPS Requirements
5. Alternative Data Sources, Procedures, and
Instrumentation: Level 6 FTD Only.
lllllllllllllllllllll
sroberts on PROD1PC70 with RULES
Begin Information
a. In recent years, considerable progress
has been made by highly experienced aircraft
and FTD manufacturers in improvement of
aerodynamic modeling techniques. In
conjunction with increased accessibility to
very high powered computer technology,
these techniques have become quite
sophisticated. Additionally, those who have
demonstrated success in combining these
modeling techniques with minimal flight
testing have incorporated the use of highly
mature flight controls models and have had
extensive experience in comparing the
output of their effort with actual flight test
data—and they have been able to do so on
an iterative basis over a period of years.
b. It has become standard practice for
experienced FTD manufacturers to use such
techniques as a means of establishing data
bases for new FTD configurations while
awaiting the availability of actual flight test
data; and then comparing this new data with
the newly available flight test data. The
results of such comparisons have, as reported
by some recognized and experienced
simulation experts, become increasingly
consistent and indicate that these techniques,
applied with appropriate experience, are
becoming dependably accurate for the
development of aerodynamic models for use
in Level 6 FTDs.
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300 milliseconds or less.
c. In reviewing this history, the NSPM has
concluded that, with proper care, those who
are experienced in the development of
aerodynamic models for FTD application can
successfully use these modeling techniques
to acceptably alter the method by which
flight test data may be acquired and, when
applied to Level 6 FTDs, does not
compromise the quality of that simulation.
a. The information in the table that follows
(Table of Alternative Data Sources,
Procedures, and Information: Level 6 FTD
Only) is presented to describe an acceptable
alternative to data sources for Level 6 FTD
modeling and validation, and an acceptable
alternative to the procedures and
instrumentation found in the flight test
methods traditionally accepted for gathering
modeling and validation data.
(1) Alternative data sources that may be
used for part or all of a data requirement are
the Airplane Maintenance Manual, the
Airplane Flight Manual (AFM), Airplane
Design Data, the Type Inspection Report
(TIR), Certification Data or acceptable
supplemental flight test data.
(2) The NSPM recommends that use of the
alternative instrumentation noted in the
following Table be coordinated with the
NSPM prior to employment in a flight test or
data gathering effort.
b. The NSPM position regarding the use of
these alternative data sources, procedures,
and instrumentation is based on three
primary preconditions and presumptions
regarding the objective data and FTD
aerodynamic program modeling.
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(1) Data gathered through the alternative
means does not require angle of attack (AOA)
measurements or control surface position
measurements for any flight test. AOA can be
sufficiently derived if the flight test program
insures the collection of acceptable level,
unaccelerated, trimmed flight data. Angle of
attack may be validated by conducting the
three basic ‘‘fly-by’’ trim tests. The FTD time
history tests should begin in level,
unaccelerated, and trimmed flight, and the
results should be compared with the flight
test pitch angle.
(2) A simulation controls system model
should be rigorously defined and fully
mature. It should also include accurate
gearing and cable stretch characteristics
(where applicable) that are determined from
actual aircraft measurements. Such a model
does not require control surface position
measurements in the flight test objective data
for Level 6 FTD applications.
c. This table is not applicable to Computer
Controlled Aircraft FTDs.
d. Utilization of these alternate data
sources, procedures, and instrumentation
does not relieve the sponsor from compliance
with the balance of the information
contained in this document relative to Level
6 FTDs.
e. The term ‘‘inertial measurement system’’
allows the use of a functional global
positioning system (GPS).
End Information
lllllllllllllllllllll
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63523
TABLE B2F.—ALTERNATIVE DATA SOURCES, PROCEDURES, AND INSTRUMENTATION LEVEL 6 FTD INFORMATION
Alternative data sources, procedures,
and instrumentation
Notes and reminders
1.b.1 ................................................
Performance
Takeoff
Ground acceleration time.
Data may be acquired through a synchronized video recording of a
stop watch and the calibrated airplane airspeed indicator. Handrecord the flight conditions and airplane configuration.
This test is required only if RTO is
sought.
1.b.7 ................................................
Performance
Takeoff
Rejected takeoff.
Data may be acquired through a synchronized video recording of a
stop watch and the calibrated airplane airspeed indicator. Handrecord the flight conditions and airplane configuration.
This test is required only if RTO is
sought.
1.c.1 .................................................
Performance
Climb
Normal climb all engines operating.
Data may be acquired with a synchronized video of calibrated airplane instruments and engine power throughout the climb range.
1.f.1 .................................................
Performance
Engines
Acceleration.
Data may be acquired with a synchronized video recording of engine
instruments and throttle position.
1.f.2 .................................................
Performance
Engines
Deceleration.
Data may be acquired with a synchronized video recording of engine
instruments and throttle position.
2.a.1.a .............................................
Handling qualities
Static control tests
Pitch controller position vs. force
and surface position calibration.
Surface position data may be acquired from flight data recorder
(FDR) sensor or, if no FDR sensor, at selected, significant column
positions (encompassing significant column position data points),
acceptable to the NSPM, using a control surface protractor on the
ground (for airplanes with reversible control systems, this function
should be accomplished with winds less than 5 kt). Force data may
be acquired by using a hand held force gauge at the same column
position data points.
2.a.2.a .............................................
Handling qualities
Static control tests
Wheel position vs. force and surface position calibration.
Surface position data may be acquired from flight data recorder
(FDR) sensor or, if no FDR sensor, at selected, significant column
positions (encompassing significant column position data points),
acceptable to the NSPM, using a control surface protractor on the
ground (for airplanes with reversible control systems, this function
should be accomplished with winds less than 5 kt). Force data may
be acquired by using a hand held force gauge at the same column
position data points.
2.a.3.a .............................................
Handling qualities
Static control tests
Rudder pedal position vs. force and
surface position calibration.
Surface position data may be acquired from flight data recorder
(FDR) sensor or, if no FDR sensor, at selected, significant column
positions (encompassing significant column position data points),
acceptable to the NSPM, using a control surface protractor on the
ground (for airplanes with reversible control systems, this function
should be accomplished with winds less than 5 kt). Force data may
be acquired by using a hand held force gauge at the same column
position data points.
2.a.4 ................................................
Handling qualities
Static control tests
Nosewheel steering force.
Breakout data may be acquired with a hand held force gauge. The
remainder of the force to the stops may be calculated if the force
gauge and a protractor are used to measure force after breakout
for at least 25% of the total displacement capability.
2.a.5 ................................................
Handling qualities
Static control tests
Rudder pedal steering calibration.
sroberts on PROD1PC70 with RULES
Objective test
reference number
and title
Data may be acquired through the use of force pads on the rudder
pedals and a pedal position measurement device, together with design data for nose wheel position.
2.a.6 ................................................
Handling qualities
Static control tests
Pitch trim indicator vs. surface position calibration.
Data may be acquired through calculations. .........................................
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
TABLE B2F.—ALTERNATIVE DATA SOURCES, PROCEDURES, AND INSTRUMENTATION LEVEL 6 FTD INFORMATION—
Continued
Alternative data sources, procedures,
and instrumentation
2.a.8 ................................................
Handling qualities
Static control tests
Alignment of power lever angle vs.
selected engine parameter (e.g.,
EPR, N1, Torque).
Data may be acquired through the use of a temporary throttle quadrant scale to document throttle position. Use a synchronized video
to record steady state instrument readings or hand-record steady
state engine performance readings.
2.a.9 ................................................
Handling qualities
Static control tests
Brake pedal position vs. force.
Use of design or predicted data is acceptable. Data may be acquired
by measuring deflection at ‘‘zero’’ and at ‘‘maximum.’’.
2.c.1 .................................................
Handling qualities.
Longitudinal control tests
Power change force.
Data may be acquired by using an inertial measurement system and
a synchronized video of the calibrated airplane instruments, throttle
position, and the force/position measurements of cockpit controls.
Power change dynamics test is
acceptable using the same data
acquisition methodology.
2.c.2 .................................................
Handling qualities
Longitudinal control tests
Flap/slat change force.
Data may be acquired by using an inertial measurement system and
a synchronized video of calibrated airplane instruments, flap/slat
position, and the force/position measurements of cockpit controls.
Flap/slat change dynamics test is
acceptable using the same data
acquisition methodology.
2.c.4 .................................................
Handling qualities
Longitudinal control tests
Gear change force.
Data may be acquired by using an inertial measurement system and
a synchronized video of the calibrated airplane instruments, gear
position, and the force/position measurements of cockpit controls.
Gear change dynamics test is acceptable using the same data
acquisition methodology.
2.c.5 .................................................
Handling qualities
Longitudinal control tests
Longitudinal trim.
Data may be acquired through use of an inertial measurement system and a synchronized video of the cockpit controls position (previously calibrated to show related surface position) and the engine
instrument readings.
2.c.6 .................................................
Handling qualities
Longitudinal control tests
Longitudinal maneuvering stability
(stick force/g).
Data may be acquired through the use of an inertial measurement
system and a synchronized video of the calibrated airplane instruments; a temporary, high resolution bank angle scale affixed to the
attitude indicator; and a wheel and column force measurement indication.
2.c.7 .................................................
Handling qualities
Longitudinal control tests
Longitudinal static stability.
Data may be acquired through the use of a synchronized video of the
airplane flight instruments and a hand held force gauge.
2.c.8 .................................................
Handling qualities
Longitudinal control tests
Stall Warning (activation of stall
warning device).
Data may be acquired through a synchronized video recording of a
stop watch and the calibrated airplane airspeed indicator. Handrecord the flight conditions and airplane configuration.
2.c.9.a ..............................................
Handling qualities
Longitudinal control tests
Phugoid dynamics.
Data may be acquired by using an inertial measurement system and
a synchronized video of the calibrated airplane instruments and the
force/position measurements of cockpit controls.
2.c.10 ...............................................
Handling qualities
Longitudinal control tests
Short period dynamics.
Data may be acquired by using an inertial measurement system and
a synchronized video of the calibrated airplane instruments and the
force/position measurements of cockpit controls.
2.c.11 ...............................................
Handling qualities
Longitudinal control tests
Gear and flap/slat operating times.
sroberts on PROD1PC70 with RULES
Objective test
reference number
and title
May use design data, production flight test schedule, or maintenance
specification, together with an SOC.
2.d.2 ................................................
Handling qualities
Lateral directional tests
Roll response (rate).
Data may be acquired by using an inertial measurement system and
a synchronized video of the calibrated airplane instruments and the
force/position measurements of cockpit lateral controls.
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Notes and reminders
Airspeeds may be cross checked
with those in the TIR and AFM.
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63525
TABLE B2F.—ALTERNATIVE DATA SOURCES, PROCEDURES, AND INSTRUMENTATION LEVEL 6 FTD INFORMATION—
Continued
Objective test
reference number
and title
Alternative data sources, procedures,
and instrumentation
2.d.3 ................................................
Handling qualities
Lateral directional tests
(a) Roll overshoot
OR
(b) Roll response to cockpit roll
controller step input.
Data may be acquired by using an inertial measurement system and
a synchronized video of the calibrated airplane instruments and the
force/position measurements of cockpit lateral controls.
2.d.4 ................................................
Handling qualities
Lateral directional tests
Spiral stability.
Data may be acquired by using an inertial measurement system and
a synchronized video of the calibrated airplane instruments; the
force/position measurements of cockpit controls; and a stop watch.
2.d.6.a .............................................
Handling qualities
Lateral directional tests
Rudder response.
Data may be acquired by using an inertial measurement system and
a synchronized video of the calibrated airplane instruments; the
force/position measurements of rudder pedals.
2.d.7 ................................................
Handling qualities
Lateral directional tests
Dutch roll, (yaw damper OFF).
Data may be acquired by using an inertial measurement system and
a synchronized video of the calibrated airplane instruments and the
force/position measurements of cockpit controls.
2.d.8 ................................................
Handling qualities
Lateral directional tests
Steady state sideslip.
Data may be acquired by using an inertial measurement system and
a synchronized video of the calibrated airplane instruments and the
force/position measurements of cockpit controls.
Attachment 3 to Appendix B to Part 60—
Flight Training Device (FTD) Subjective
Evaluation
1. Discussion
lllllllllllllllllllll
Begin Information
a. The subjective tests provide a basis for
evaluating the capability of the FTD to
perform over a typical utilization period. The
items listed in the Table of Functions and
Subjective Tests are used to determine
whether the FTD competently simulates each
required maneuver, procedure, or task; and
verifying correct operation of the FTD
controls, instruments, and systems. The tasks
do not limit or exceed the authorizations for
use of a given level of FTD as described on
the Statement of Qualification or as may be
approved by the TPAA. All items in the
following paragraphs are subject to
examination.
b. All simulated airplane systems functions
will be assessed for normal and, where
appropriate, alternate operations. Simulated
airplane systems are listed separately under
‘‘Any Flight Phase’’ to ensure appropriate
attention to systems checks. Operational
navigation systems (including inertial
navigation systems, global positioning
systems, or other long-range systems) and the
associated electronic display systems will be
evaluated if installed. The NSP pilot will
include in his report to the TPAA, the effect
Notes and reminders
of the system operation and any system
limitation.
e. At the request of the TPAA, the NSP
Pilot may assess the FTD for a special aspect
of a sponsor’s training program during the
functions and subjective portion of an
evaluation. Such an assessment may include
a portion of a Line Oriented Flight Training
(LOFT) scenario or special emphasis items in
the sponsor’s training program. Unless
directly related to a requirement for the
qualification level, the results of such an
evaluation would not affect the qualification
of the FTD.
End Information
lllllllllllllllllllll
TABLE B3A.—TABLE OF FUNCTIONS AND SUBJECTIVE TESTS LEVEL 6 FTD
<<<
QPS requirement
>>>
No.
Tasks in this table are subject to evaluation if appropriate for the airplane system or systems simulated as indicated in the SOQ Configuration List as defined in appendix B, Attachment 2 of this part.
1. Preflight
sroberts on PROD1PC70 with RULES
Accomplish a functions check of all installed switches, indicators, systems, and equipment at all crewmembers’ and instructors’ stations, and determine that the cockpit (or flight deck area) design and functions replicate the appropriate airplane.
2. Surface Operations (pre-takeoff)
2.a ........
Engine start:
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
TABLE B3A.—TABLE OF FUNCTIONS AND SUBJECTIVE TESTS LEVEL 6 FTD—Continued
<<<
QPS requirement
>>>
No.
2.a.1 .....
Normal start.
2.a.2 .....
Alternative procedures start.
2.a.3 .....
Abnormal procedures start/shut down.
2.b ........
Pushback/Powerback (powerback requires visual system).
3. Takeoff (requires appropriate visual system as set out in Table B1A, item 6.b.; appendix B, Attachment 1.)
3.a ........
Instrument takeoff:
3.a.1 .....
Engine checks (e.g., engine parameter relationships, propeller/mixture controls).
3.a.2 .....
Acceleration characteristics.
3.a.3 .....
Nosewheel/rudder steering.
3.a.4 .....
Landing gear, wing flap, leading edge device operation.
3.b ........
Rejected takeoff:
3.b.1 .....
Deceleration characteristics.
3.b.2 .....
Brakes/engine reverser/ground spoiler operation.
3.b.3 .....
Nosewheel/rudder steering.
4. In-Flight Operations
4.a ........
Normal climb.
4.b ........
Cruise:
4.b.1 .....
Demonstration of performance characteristics (speed vs. power).
4.b.2 .....
Normal turns.
4.b.3 .....
Demonstration of high altitude handling.
4.b.4 .....
Demonstration of high airspeed handling/overspeed warning.
4.b.5 .....
Demonstration of Mach effects on control and trim.
4.b.6 .....
Steep turns.
4.b.10 ...
In-Flight engine shutdown (procedures only).
4.b.11 ...
In-Flight engine restart (procedures only).
4.b.13 ...
Specific flight characteristics.
4.b.14 ...
Response to loss of flight control power.
4.b.15 ...
Response to other flight control system failure modes.
4.b.19 ...
Operations during icing conditions.
4.b.20 ...
Effects of airframe/engine icing.
Other flight phase:
4.c.1 .....
sroberts on PROD1PC70 with RULES
4.c ........
Approach to stalls in the following configurations:
4.c.1.a ..
Cruise.
4.c.1.b ..
Takeoff or approach.
4.c.1.c ..
Landing.
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63527
TABLE B3A.—TABLE OF FUNCTIONS AND SUBJECTIVE TESTS LEVEL 6 FTD—Continued
<<<
QPS requirement
>>>
4.c.2 .....
No.
High angle of attack maneuvers in the following configurations:
4.c.2.a ..
Cruise.
4.c.2.b ..
Takeoff or approach.
4.c.2.c ..
Landing.
4.c.3 .....
Slow flight.
4.c.4 .....
Holding.
5.a.1 .....
Non-precision Instrument Approaches:
5.a.1.a.1
With use of autopilot and autothrottle, as applicable.
5.a.1.a.2
Without use of autopilot and autothrottle, as applicable.
5.a.1.b.1
With 10 knot tail wind.
5.a.1.b.2
With 10 knot crosswind.
5.a.2 .....
Precision Instrument Approaches:
5.a.2.a.1
With use of autopilot, autothrottle, and autoland, as applicable.
5.a.2.a.2
Without use of autopilot, autothrottle, and autoland, as applicable.
5.a.2.b.1
With 10 knot tail wind.
5.a.2.b.2
With 10 knot crosswind.
6. Missed Approach
6.a ........
Manually controlled.
6.b ........
Automatically controlled (if applicable).
7. Any Flight Phase, as appropriate
7.a ........
Normal system operation (installed systems).
7.b ........
Abnormal/Emergency system operation (installed systems).
7.c ........
Flap operation.
7.d ........
Landing gear operation.
7.e ........
Engine Shutdown and Parking.
7.e.1 .....
Systems operation.
7.e.2 .....
Parking brake operation.
8. Instructor Operating Station (IOS), as appropriate
8.a ........
Functions in this section are subject to evaluation only if appropriate for the airplane and/or installed on the specific FTD involved.
Power Switch(es).
8.b ........
Airplane conditions.
Gross weight, center of gravity, and fuel loading and allocation.
8.b.2 .....
sroberts on PROD1PC70 with RULES
8.b.1 .....
Airplane systems status.
8.b.3 .....
Ground crew functions (e.g., external power, push back).
8.c ........
Airports.
8.c.1 .....
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
TABLE B3A.—TABLE OF FUNCTIONS AND SUBJECTIVE TESTS LEVEL 6 FTD—Continued
<<<
QPS requirement
>>>
No.
8.c.2 .....
Runway selection.
8.c.3 .....
Preset positions (e.g., ramp, over FAF).
8.d ........
Environmental controls.
8.d.1 .....
Temperature.
8.d.2 .....
Climate conditions (e.g., ice, rain).
8.d.3 .....
Wind speed and direction.
8.e ........
Airplane system malfunctions.
8.e.1 .....
Insertion/deletion.
8.e.2 .....
Problem clear.
8.f .........
Locks, Freezes, and Repositioning.
8.f.1 ......
Problem (all) freeze/release.
8.f.2 ......
Position (geographic) freeze/release.
8.f.3 ......
Repositioning (locations, freezes, and releases).
8.f.4 ......
Ground speed control.
8.f.5 ......
Remote IOS, if installed.
9. Sound Controls. On/off/adjustment
10. Control Loading System (as applicable) On/off/emergency stop
11. Observer Stations
11.a ......
Position.
11.b ......
Adjustments.
End QPS Requirements
lllllllllllllllllllll
TABLE B3B.—TABLE OF FUNCTIONS AND SUBJECTIVE TESTS—LEVEL 5 FTD
<<< QPS Requirements >>>
No.
Operations tasks
Tasks in this table are subject to evaluation if appropriate for the airplane system or systems simulated as
indicated in the SOQ Configuration List as defined in appendix B, Attachment 2 of this part.
1. Preflight
Accomplish a functions check of all installed switches, indicators, systems, and equipment at all crewmembers’ and instructors’ stations, and determine that the cockpit (or flight deck area) design and functions replicate the appropriate airplane.
sroberts on PROD1PC70 with RULES
2. Surface Operations (pre-takeoff)
2.a ...................................................
2.a.1 ................................................
2.a.2 ................................................
2.a.3 ................................................
Engine start (if installed):
Normal start.
Alternative procedures start.
Abnormal/Emergency procedures start / shut down.
3. In-Flight Operations
3.a ...................................................
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TABLE B3B.—TABLE OF FUNCTIONS AND SUBJECTIVE TESTS—LEVEL 5 FTD—Continued
<<< QPS Requirements >>>
No.
Operations tasks
3.b ...................................................
3.b.1 ................................................
3.b.2 ................................................
3.c ...................................................
Cruise:
Performance characteristics (speed vs. power).
Normal turns.
Normal descent.
4. Approaches
4.a. ..................................................
Coupled instrument approach maneuvers (as applicable for the systems installed).
5. Any Flight Phase
5.a ...................................................
5.b ...................................................
5.c ...................................................
5.d ...................................................
5.e ...................................................
5.e.1 ................................................
5.e.2 ................................................
Normal system operation (Installed systems).
Abnormal/Emergency system operation (installed systems).
Flap operation.
Landing gear operation.
Engine Shutdown and Parking (if installed).
Systems operation.
Parking brake operation.
6. Instructor Operating Station (IOS)
6.a ...................................................
6.b ...................................................
6.c ...................................................
6.c.1 ................................................
6.c.2 ................................................
Power Switch(es).
Preset positions—ground, air.
Airplane system malfunctions (Installed systems).
Insertion/deletion.
Problem clear.
TABLE B3C.—TABLE OF FUNCTIONS AND SUBJECTIVE TESTS—LEVEL 4 FTD
<<< QPS Requirements >>>
No.
Operations tasks
Tasks in this table are subject to evaluation if appropriate for the airplane system or systems simulated as
indicated in the SOQ Configuration List as defined in appendix B, Attachment 2 of this part.
1 ......................................................
Level 4 FTDs are required to have at least one system. However, the NSP will accomplish a functions
check of all installed systems, switches, indicators, and equipment at all crewmembers’ and instructors’
stations, and determine that the cockpit (or flight deck area) design and functions replicate the appropriate airplane.
Attachment 4 to Appendix B to Part 60—
Sample Documents
lllllllllllllllllllll
Begin Information
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Table of Contents
Title of Sample
Figure B4A—Sample Letter, Request for
Initial, Upgrade, or Reinstatement
Evaluation
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Figure B4B—Attachment: FSTD Information
Form
Figure B4C—Sample Qualification Test
Guide Cover Page
Figure B4D—Sample Statement of
Qualification—Certificate
Figure B4E—Sample Statement of
Qualification—Configuration List
Figure B4F—Sample Statement of
Qualification—List of Qualified Tasks
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Figure B4G—Sample Continuing
Qualification Evaluation Requirements
Page
Figure B4H—Sample MQTG Index of
Effective FSTD Directives
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Appendix C to Part 60—Qualification
Performance Standards for Helicopter
Full Flight Simulators
lllllllllllllllllllll
Begin Information
This appendix establishes the standards for
Helicopter Full Flight Simulator (FFS)
evaluation and qualification. The Flight
Standards Service, National Simulator
Program Manager (NSPM), is responsible for
the development, application, and
implementation of the standards contained
within this appendix. The procedures and
criteria specified in this appendix will be
used by the NSPM, or a person assigned by
the NSPM, when conducting helicopter FFS
evaluations.
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Table of Contents
1. Introduction.
2. Applicability (§ 60.1) and (§ 60.2).
3. Definitions (§ 60.3).
4. Qualification Performance Standards
(§ 60.4).
5. Quality Management System (§ 60.5).
6. Sponsor Qualification Requirements
(§ 60.7).
7. Additional Responsibilities of the
Sponsor (§ 60.9).
8. FSTD Use (§ 60.11).
9. Simulator Objective Data Requirements
(§ 60.13).
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10. Special Equipment and Personnel
Requirements for Qualification of the
Simulator (§ 60.14).
11. Initial (and Upgrade) Qualification
Requirements (§ 60.15).
12. Additional Qualifications for a
Currently Qualified Simulator (§ 60.16).
13. Previously Qualified Simulators
(§ 60.17).
14. Inspection, Continuing Qualification
Evaluation, and Maintenance Requirements
(§ 60.19).
15. Logging Simulator Discrepancies
(§ 60.20).
16. Interim Qualification of Simulators for
New Helicopter Types or Models (§ 60.21).
17. Modifications to Simulators (§ 60.23).
18. Operations with Missing,
Malfunctioning, or Inoperative Components
(§ 60.25).
19. Automatic Loss of Qualification and
Procedures for Restoration of Qualification
(§ 60.27).
20. Other Losses of Qualification and
Procedures for Restoration of Qualification
(§ 60.29).
21. Record Keeping and Reporting
(§ 60.31).
22. Applications, Logbooks, Reports, and
Records: Fraud, Falsification, or Incorrect
Statements (§ 60.33).
23. [Reserved]
24. [Reserved]
25. FSTD Qualification on the Basis of a
Bilateral Aviation Safety Agreement (BASA)
(§ 60.37).
Attachment 1 to Appendix C to Part 60—
General Simulator Requirements.
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Attachment 2 to Appendix C to Part 60—
Simulator Objective Tests.
Attachment 3 to Appendix C to Part 60—
Simulator Subjective Evaluation.
Attachment 4 to Appendix C to Part 60—
Sample Documents.
End Information
lllllllllllllllllllll
1. Introduction
lllllllllllllllllllll
Begin Information
a. This appendix contains background
information as well as regulatory and
informative material as described later in this
section. To assist the reader in determining
what areas are required and what areas are
permissive, the text in this appendix is
divided into two sections: ‘‘QPS
Requirements’’ and ‘‘Information.’’ The QPS
Requirements sections contain details
regarding compliance with the part 60 rule
language. These details are regulatory, but are
found only in this appendix. The Information
sections contain material that is advisory in
nature, and designed to give the user general
information about the regulation.
b. Related Reading References.
(1) 14 CFR part 60.
(2) 14 CFR part 61.
(3) 14 CFR part 63.
(4) 14 CFR part 119.
(5) 14 CFR part 121.
(6) 14 CFR part 125.
(7) 14 CFR part 135.
(8) 14 CFR part 141.
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(9) 14 CFR part 142.
(10) AC 120–35B, Line Operational
Simulations: Line-Oriented Flight Training,
Special Purpose Operational Training, Line
Operational Evaluation.
(11) AC 120–57A, Surface Movement
Guidance and Control System (SMGS).
(12) AC 150/5300–13, Airport Design.
(13) AC 150/5340–1G, Standards for
Airport Markings.
(14) AC 150/5340–4C, Installation Details
for Runway Centerline Touchdown Zone
Lighting Systems.
(15) AC 150/5340–19, Taxiway Centerline
Lighting System.
(16) AC 150/5340–24, Runway and
Taxiway Edge Lighting System.
(17) AC 150/5345–28D, Precision
Approach Path Indicator (PAPI) Systems.
(18) AC 150/5390–2B, Heliport Design.
(19) International Air Transport
Association document, ‘‘Flight Simulator
Design and Performance Data Requirements,’’
as amended.
(20) AC 29–2B, Flight Test Guide for
Certification of Transport Category
Rotorcraft.
(21) AC 27–1A, Flight Test Guide for
Certification of Normal Category Rotorcraft.
(22) International Civil Aviation
Organization (ICAO) Manual of Criteria for
the Qualification of Flight Simulators, as
amended.
(23) Airplane Flight Simulator Evaluation
Handbook, Volume I, as amended and
Volume II, as amended, The Royal
Aeronautical Society, London, UK.
(24) FAA Publication FAA–S–8081 series
(Practical Test Standards for Airline
Transport Pilot Certificate, Type Ratings,
Commercial Pilot, and Instrument Ratings).
(25) The FAA Aeronautical Information
Manual (AIM). An electronic version of the
AIM is on the internet at https://www.faa.gov/
atpubs.
End Information
lllllllllllllllllllll
2. Applicability (§§ 60.1 & 60.2)
lllllllllllllllllllll
Begin Information
There is no additional regulatory or
informational material that applies to § 60.1,
Applicability, or to § 60.2, Applicability of
sponsor rules to person who are not sponsors
and who are engaged in certain unauthorized
activities.
End Information
lllllllllllllllllllll
3. Definitions (§ 60.3)
lllllllllllllllllllll
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Begin Information
See appendix F for a list of definitions and
abbreviations from part 1 and part 60,
including the appropriate appendices of part
60.
End Information
lllllllllllllllllllll
4. Qualification Performance Standards
(§ 60.4)
lllllllllllllllllllll
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Begin Information
There is no additional regulatory or
informational material that applies to § 60.4,
Qualification Performance Standards.
End Information
lllllllllllllllllllll
5. Quality Management System (§ 60.5)
lllllllllllllllllllll
Begin Information
See appendix E for additional regulatory
and informational material regarding Quality
Management Systems.
End Information
lllllllllllllllllllll
6. Sponsor Qualification Requirements
(§ 60.7)
lllllllllllllllllllll
Begin Information
a. The intent of the language in § 60.7(b) is
to have a specific FFS, identified by the
sponsor, used at least once in an FAAapproved flight training program for the
helicopter simulated during the 12-month
period described. The identification of the
specific FFS may change from one 12-month
period to the next 12-month period as long
as that sponsor sponsors and uses at least one
FFS at least once during the prescribed
period. There is no minimum number of
hours or minimum FFS periods required.
b. The following examples describe
acceptable operational practices:
(1) Example One.
(a) A sponsor is sponsoring a single,
specific FFS for its own use, in its own
facility or elsewhere—this single FFS forms
the basis for the sponsorship. The sponsor
uses that FFS at least once in each 12-month
period in that sponsor’s FAA-approved flight
training program for the helicopter
simulated. This 12-month period is
established according to the following
schedule:
(i) If the FFS was qualified prior to October
30, 2007 the 12-month period begins on the
date of the first continuing qualification
evaluation conducted in accordance with
§ 60.19 after October 30, 2007 and continues
for each subsequent 12-month period;
(ii) A device qualified on or after October
30, 2007 will be required to undergo an
initial or upgrade evaluation in accordance
with § 60.15. Once the initial or upgrade
evaluation is complete, the first continuing
qualification evaluation will be conducted
within 6 months. The 12 month continuing
qualification evaluation cycle begins on that
date and continues for each subsequent 12month period.
(b) There is no minimum number of hours
of FFS use required.
(c) The identification of the specific FFS
may change from one 12-month period to the
next 12-month period as long as that sponsor
sponsors and uses at least one FFS at least
once during the prescribed period.
(2) Example Two.
(a) A sponsor sponsors an additional
number of FFSs, in its facility or elsewhere.
Each additionally sponsored FFS must be—
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(i) Used by the sponsor in the sponsor’s
FAA-approved flight training program for the
helicopter simulated (as described in
§ 60.7(d)(1));
OR
(ii) Used by another FAA certificate holder
in that other certificate holder’s FAAapproved flight training program for the
helicopter simulated (as described in
§ 60.7(d)(1)). This 12-month period is
established in the same manner as in
example one.
OR
(iii) Provided a statement each year from a
qualified pilot (after having flown the
helicopter, not the subject FFS or another
FFS, during the preceding 12-month period)
stating that the subject FFS’s performance
and handling qualities represent the
helicopter (as described in § 60.7(d)(2)). This
statement is provided at least once in each
12-month period established in the same
manner as in example one.
(b) There is no minimum number of hours
of FFS use required.
(3) Example Three.
(a) A sponsor in New York (in this
example, a Part 142 certificate holder)
establishes ‘‘satellite’’ training centers in
Chicago and Moscow.
(b) The satellite function means that the
Chicago and Moscow centers must operate
under the New York center’s certificate (in
accordance with all of the New York center’s
practices, procedures, and policies; e.g.,
instructor and/or technician training/
checking requirements, record keeping, QMS
program).
(c) All of the FFSs in the Chicago and
Moscow centers could be dry-leased (i.e., the
certificate holder does not have and use
FAA-approved flight training programs for
the FFSs in the Chicago and Moscow centers)
because —
(i) Each FFS in the Chicago center and each
FFS in the Moscow center is used at least
once each 12-month period by another FAA
certificate holder in that other certificate
holder’s FAA-approved flight training
program for the helicopter (as described in
§ 60.7(d)(1));
OR
(ii) A statement is obtained from a
qualified pilot (having flown the helicopter,
not the subject FFS or another FFS during the
preceding 12-month period) stating that the
performance and handling qualities of each
FFS in the Chicago and Moscow centers
represents the helicopter (as described in
§ 60.7(d)(2)).
End Information
lllllllllllllllllllll
7. Additional Responsibilities of the Sponsor
(§ 60.9)
lllllllllllllllllllll
Begin Information
The phrase ‘‘as soon as practicable’’ in
§ 60.9(a) means without unnecessarily
disrupting or delaying beyond a reasonable
time the training, evaluation, or experience
being conducted in the FSTD.
End Information
lllllllllllllllllllll
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8. FSTD Use (§ 60.11)
lllllllllllllllllllll
Begin Information
There is no additional regulatory or
informational material that applies to § 60.11,
FSTD Use.
End Information
lllllllllllllllllllll
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9. Simulator Objective Data Requirements
(§ 60.13)
lllllllllllllllllllll
Begin QPS Requirements
a. Flight test data used to validate FFS
performance and handling qualities must
have been gathered in accordance with a
flight test program containing the following:
(1) A flight test plan consisting of:
(a) The maneuvers and procedures
required for aircraft certification and
simulation programming and validation.
(b) For each maneuver or procedure—
(i) The procedures and control input the
flight test pilot and/or engineer used.
(ii) The atmospheric and environmental
conditions.
(iii) The initial flight conditions.
(iv) The helicopter configuration, including
weight and center of gravity.
(v) The data to be gathered.
(vi) All other information necessary to
recreate the flight test conditions in the FFS.
(2) Appropriately qualified flight test
personnel.
(3) An understanding of the accuracy of the
data to be gathered using appropriate
alternative data sources, procedures, and
instrumentation that is traceable to a
recognized standard as described in
Attachment 2, Table C2D.
(4) Appropriate and sufficient data
acquisition equipment or system(s),
including appropriate data reduction and
analysis methods and techniques, as would
be acceptable to the FAA’s Aircraft
Certification Service.
b. The data, regardless of source, must be
presented:
(1) in a format that supports the FFS
validation process;
(2) in a manner that is clearly readable and
annotated correctly and completely;
(3) with resolution sufficient to determine
compliance with the tolerances set forth in
Attachment 2, Table C2A of this appendix.
(4) with any necessary instructions or other
details provided, such as yaw damper or
throttle position; and
(5) without alteration, adjustments, or bias;
however the data may be re-scaled, digitized,
or otherwise manipulated to fit the desired
presentation.
c. After completion of any additional flight
test, a flight test report must be submitted in
support of the validation data. The report
must contain sufficient data and rationale to
support qualification of the FFS at the level
requested.
d. As required by § 60.13(f), the sponsor
must notify the NSPM when it becomes
aware that an addition to, an amendment to,
or a revision of data that may relate to FFS
performance or handling characteristics is
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available. The data referred to in this
paragraph are those data that are used to
validate the performance, handling qualities,
or other characteristics of the aircraft,
including data related to any relevant
changes occurring after the type certificate
was issued. This notification must be made
within 10 working days.
End QPS Requirements
lllllllllllllllllllll
Begin Information
e. The FFS sponsor is encouraged to
maintain a liaison with the manufacturer of
the aircraft being simulated (or with the
holder of the aircraft type certificate for the
aircraft being simulated if the manufacturer
is no longer in business), and, if appropriate,
with the person having supplied the aircraft
data package for the FFS in order to facilitate
the notification required by § 60.13(f).
f. It is the intent of the NSPM that for new
aircraft entering service, at a point well in
advance of preparation of the Qualification
Test Guide (QTG), the sponsor should submit
to the NSPM for approval, a descriptive
document (a validation data roadmap)
containing the plan for acquiring the
validation data, including data sources. This
document should clearly identify sources of
data for all required tests, a description of the
validity of these data for a specific engine
type and thrust rating configuration, and the
revision levels of all avionics affecting the
performance or flying qualities of the aircraft.
Additionally, this document should provide
other information, such as the rationale or
explanation for cases where data or data
parameters are missing, instances where
engineering simulation data are used or
where flight test methods require further
explanations. It should also provide a brief
narrative describing the cause and effect of
any deviation from data requirements. The
aircraft manufacturer may provide this
document.
g. There is no requirement for any flight
test data supplier to submit a flight test plan
or program prior to gathering flight test data.
However, the NSPM notes that inexperienced
data gatherers often provide data that is
irrelevant, improperly marked, or lacking
adequate justification for selection. Other
problems include inadequate information
regarding initial conditions or test
maneuvers. The NSPM has been forced to
refuse these data submissions as validation
data for an FFS evaluation. It is for this
reason that the NSPM recommends that any
data supplier not previously experienced in
this area review the data necessary for
programming and for validating the
performance of the FFS, and discuss the
flight test plan anticipated for acquiring such
data with the NSPM well in advance of
commencing the flight tests.
h. In those cases where the objective test
results authorize a ‘‘snapshot test’’ or a
‘‘series of snapshot test’’ results in lieu of a
time-history result, Attachment 2 requires the
sponsor or other data provider to ensure that
a steady state condition exists at the instant
of time captured by the ‘‘snapshot.’’ This is
often verified by showing that a steady state
condition existed from some period of time
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during which the snapshot is taken. The time
period most frequently used is 5 seconds
prior through 2 seconds following the instant
of time captured by the snapshot. This
paragraph is primarily addressing the source
data and the method by which the data
provider ensures that the steady state
condition for the snapshot is representative.
i. The NSPM will consider, on a case-bycase basis, whether or not to approve
supplemental validation data derived from
flight data recording systems such as a Quick
Access Recorder or Flight Data Recorder.
End Information
lllllllllllllllllllll
10. Special Equipment and Personnel
Requirements for Qualification of the
Simulator (§ 60.14)
lllllllllllllllllllll
Begin Information
a. In the event that the NSPM determines
that special equipment or specifically
qualified persons will be required to conduct
an evaluation, the NSPM will make every
attempt to notify the sponsor at least one (1)
week, but in no case less than 72 hours, in
advance of the evaluation. Examples of
special equipment include spot photometers,
flight control measurement devices, and
sound analyzers. Examples of specially
qualified personnel include individuals
specifically qualified to install or use any
special equipment when its use is required.
b. Examples of a special evaluation include
an evaluation conducted after an FFS is
moved, at the request of the TPAA, or as a
result of comments received from FFS that
raise questions regarding the continued
qualification or use of the FFS.
End Information
lllllllllllllllllllll
11. Initial (and Upgrade) Qualification
Requirements (§ 60.15)
lllllllllllllllllllll
Begin QPS Requirements
a. In order to be qualified at a particular
qualification level, the FFS must:
(1) Meet the general requirements listed in
Attachment 1;
(2) Meet the objective testing requirements
listed in Attachment 2; and
(3) Satisfactorily accomplish the subjective
tests listed in Attachment 3.
b. The request described in § 60.15(a) must
include all of the following:
(1) A statement that the FFS meets all of
the applicable provisions of this part and all
applicable provisions of the QPS.
(2) A confirmation that the sponsor will
forward to the NSPM the statement described
in § 60.15(b) in such time as to be received
no later than 5 business days prior to the
scheduled evaluation and may be forwarded
to the NSPM via traditional or electronic
means.
(3) A qualification test guide (QTG),
acceptable to the NSPM, that includes all of
the following:
(i) Objective data obtained from aircraft
testing or another approved source.
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(ii) Correlating objective test results
obtained from the performance of the FFS as
prescribed in the applicable QPS.
(iii) The result of FFS subjective tests
prescribed in the applicable QPS.
(iv) A description of the equipment
necessary to perform the evaluation for initial
qualification and the continuing qualification
evaluations.
c. The QTG described in paragraph (a)(3)
of this section, must provide the documented
proof of compliance with the simulator
objective tests in Attachment 2, Table C2A of
this appendix.
d. The QTG is prepared and submitted by
the sponsor, or the sponsor’s agent on behalf
of the sponsor, to the NSPM for review and
approval, and must include, for each
objective test:
(1) Parameters, tolerances, and flight
conditions;
(2) Pertinent and complete instructions for
the conduct of automatic and manual tests;
(3) A means of comparing the FFS test
results to the objective data;
(4) Any other information as necessary, to
assist in the evaluation of the test results;
(5) Other information appropriate to the
qualification level of the FFS.
e. The QTG described in paragraphs (a)(3)
and (b) of this section, must include the
following:
(1) A QTG cover page with sponsor and
FAA approval signature blocks (see
Attachment 4, Figure C4C, for a sample QTG
cover page).
(2) A continuing qualification evaluation
schedule requirements page. This page will
be used by the NSPM to establish and record
the frequency with which continuing
qualification evaluations must be conducted
and any subsequent changes that may be
determined by the NSPM in accordance with
§ 60.19. See Attachment 4, Figure C4G, for a
sample Continuing Qualification Evaluation
Requirements page.
(3) An FFS information page that provides
the information listed in this paragraph (see
Attachment 4, Figure C4B, for a sample FFS
information page). For convertible FFSs, the
sponsor must submit a separate page for each
configuration of the FFS.
(a) The sponsor’s FFS identification
number or code.
(b) The helicopter model and series being
simulated.
(c) The aerodynamic data revision number
or reference.
(d) The engine model(s) and its data
revision number or reference.
(e) The flight control data revision number
or reference.
(f) The flight management system
identification and revision level.
(g) The FFS model and manufacturer.
(h) The date of FFS manufacture.
(i) The FFS computer identification.
(j) The visual system model and
manufacturer, including display type.
(k) The motion system type and
manufacturer, including degrees of freedom.
(4) A Table of Contents.
(5) A log of revisions and a list of effective
pages.
(6) List of all relevant data references.
(7) A glossary of terms and symbols used
(including sign conventions and units).
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(8) Statements of compliance and
capability (SOCs) with certain requirements.
SOCs must provide references to the sources
of information that show the capability of the
FFS to comply with the requirements. SOCs
must also provide a rationale explaining how
the referenced material is used, the
mathematical equations and parameter
values used, and the conclusions reached.
Refer to the ‘‘Additional Details’’ column in
Attachment 1, Table C1A, ‘‘Simulator
Standards,’’ or in the ‘‘Test Details’’ column
in Attachment 2, Table C2A, ‘‘Simulator
Objective Tests,’’ to see when SOCs are
required.
(9) Recording procedures or equipment
required to accomplish the objective tests.
(10) The following information for each
objective test designated in Attachment 2,
Table C2A, as applicable to the qualification
level sought:
(a) Name of the test.
(b) Objective of the test.
(c) Initial conditions.
(d) Manual test procedures.
(e) Automatic test procedures (if
applicable).
(f) Method for evaluating FFS objective test
results.
(g) List of all relevant parameters driven or
constrained during the automatically
conducted test(s).
(h) List of all relevant parameters driven or
constrained during the manually conducted
test(s).
(i) Tolerances for relevant parameters.
(j) Source of Validation Data (document
and page number).
(k) Copy of the Validation Data (if located
in a separate binder, a cross reference for the
identification and page number for pertinent
data location must be provided).
(l) Simulator Objective Test Results as
obtained by the sponsor. Each test result
must reflect the date completed and must be
clearly labeled as a product of the device
being tested.
f. A convertible FFS is addressed as a
separate FFS for each model and series
helicopter to which it will be converted and
for the FAA qualification level sought. If a
sponsor seeks qualification for two or more
models of a helicopter type using a
convertible FFS, the sponsor must submit a
QTG for each helicopter model, or a
supplemented QTG for each helicopter
model. The NSPM will conduct evaluations
for each helicopter model.
g. Form and manner of presentation of
objective test results in the QTG:
(1) The sponsor’s FFS test results must be
recorded in a manner acceptable to the
NSPM, that allows easy comparison of the
FFS test results to the validation data (e.g.,
use of a multi-channel recorder, line printer,
cross plotting, overlays, transparencies).
(2) FFS results must be labeled using
terminology common to helicopter
parameters as opposed to computer software
identifications.
(3) Validation data documents included in
a QTG may be photographically reduced only
if such reduction will not alter the graphic
scaling or cause difficulties in scale
interpretation or resolution.
(4) Scaling on graphical presentations must
provide the resolution necessary to evaluate
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the parameters shown in Attachment 2, Table
C2A of this appendix.
(5) Tests involving time histories, data
sheets (or transparencies thereof) and FFS
test results must be clearly marked with
appropriate reference points to ensure an
accurate comparison between the FFS and
the helicopter with respect to time. Time
histories recorded via a line printer are to be
clearly identified for cross plotting on the
helicopter data. Over-plots must not obscure
the reference data.
h. The sponsor may elect to complete the
QTG objective and subjective tests at the
manufacturer’s facility or at the sponsor’s
training facility. If the tests are conducted at
the manufacturer’s facility, the sponsor must
repeat at least one-third of the tests at the
sponsor’s training facility in order to
substantiate FFS performance. The QTG must
be clearly annotated to indicate when and
where each test was accomplished. Tests
conducted at the manufacturer’s facility and
at the sponsor’s training facility must be
conducted after the FFS is assembled with
systems and sub-systems functional and
operating in an interactive manner. The test
results must be submitted to the NSPM.
i. The sponsor must maintain a copy of the
MQTG at the FFS location.
j. All FFSs for which the initial
qualification is conducted after October 30,
2013 must have an electronic MQTG
(eMQTG) including all objective data
obtained from helicopter testing, or another
approved source (reformatted or digitized),
together with correlating objective test results
obtained from the performance of the FFS
(reformatted or digitized) as prescribed in
this appendix. The eMQTG must also contain
the general FFS performance or
demonstration results (reformatted or
digitized) prescribed in this appendix, and a
description of the equipment necessary to
perform the initial qualification evaluation
and the continuing qualification evaluations.
The eMQTG must include the original
validation data used to validate FFS
performance and handling qualities in either
the original digitized format from the data
supplier or an electronic scan of the original
time-history plots that were provided by the
data supplier. A copy of the eMQTG must be
provided to the NSPM.
k. All other FFSs not covered in
subparagraph ‘‘j’’ must have an electronic
copy of the MQTG by October 30, 2013. A
copy of the eMQTG must be provided to the
NSPM. This may be provided by an
electronic scan presented in a Portable
Document File (PDF), or similar format
acceptable to the NSPM.
End QPS Requirements
lllllllllllllllllllll
Begin Information
l. Only those FFSs that are sponsored by
a certificate holder as defined in appendix F
will be evaluated by the NSPM. However,
other FFS evaluations may be conducted on
a case-by-case basis as the Administrator
deems appropriate, but only in accordance
with applicable agreements.
m. The NSPM will conduct an evaluation
for each configuration, and each FFS must be
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evaluated as completely as possible. To
ensure a thorough and uniform evaluation,
each FFS is subjected to the general
simulator requirements in Attachment 1, the
objective tests listed in Attachment 2, and the
subjective tests listed in Attachment 3 of this
appendix. The evaluations described herein
will include, but not necessarily be limited
to the following:
(1) Helicopter responses, including
longitudinal and lateral-directional control
responses (see Attachment 2 of this
appendix);
(2) Performance in authorized portions of
the simulated helicopter’s operating
envelope, to include tasks evaluated by the
NSPM in the areas of surface operations,
takeoff, climb, cruise, descent, approach, and
landing as well as abnormal and emergency
operations (see Attachment 2 of this
appendix);
(3) Control checks (see Attachment 1 and
Attachment 2 of this appendix);
(4) Cockpit configuration (see Attachment
1 of this appendix);
(5) Pilot, flight engineer, and instructor
station functions checks (see Attachment 1
and Attachment 3 of this appendix);
(6) Helicopter systems and sub-systems (as
appropriate) as compared to the helicopter
simulated (see Attachment 1 and Attachment
3 of this appendix);
(7) FFS systems and sub-systems,
including force cueing (motion), visual, and
aural (sound) systems, as appropriate (see
Attachment 1 and Attachment 2 of this
appendix); and
(8) Certain additional requirements,
depending upon the qualification level
sought, including equipment or
circumstances that may become hazardous to
the occupants. The sponsor may be subject to
Occupational Safety and Health
Administration requirements.
n. The NSPM administers the objective and
subjective tests, which includes an
examination of functions. The tests include
a qualitative assessment of the FFS by an
NSP pilot. The NSP evaluation team leader
may assign other qualified personnel to assist
in accomplishing the functions examination
and/or the objective and subjective tests
performed during an evaluation when
required.
(1) Objective tests provide a basis for
measuring and evaluating FFS performance
and determining compliance with the
requirements of this part.
(2) Subjective tests provide a basis for:
(a) Evaluating the capability of the FFS to
perform over a typical utilization period;
(b) Determining that the FFS satisfactorily
simulates each required task;
(c) Verifying correct operation of the FFS
controls, instruments, and systems; and
(d) Demonstrating compliance with the
requirements of this part.
o. The tolerances for the test parameters
listed in Attachment 2 of this appendix
reflect the range of tolerances acceptable to
the NSPM for FFS validation and are not to
be confused with design tolerances specified
for FFS manufacture. In making decisions
regarding tests and test results, the NSPM
relies on the use of operational and
engineering judgment in the application of
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data (including consideration of the way in
which the flight test was flown and way the
data was gathered and applied) data
presentations, and the applicable tolerances
for each test.
p. In addition to the scheduled continuing
qualification evaluation, each FFS is subject
to evaluations conducted by the NSPM at any
time without prior notification to the
sponsor. Such evaluations would be
accomplished in a normal manner (i.e.,
requiring exclusive use of the FFS for the
conduct of objective and subjective tests and
an examination of functions) if the FFS is not
being used for flight crewmember training,
testing, or checking. However, if the FFS
were being used, the evaluation would be
conducted in a non-exclusive manner. This
non-exclusive evaluation will be conducted
by the FFS evaluator accompanying the
check airman, instructor, Aircrew Program
Designee (APD), or FAA inspector aboard the
FFS along with the student(s) and observing
the operation of the FFS during the training,
testing, or checking activities.
q. Problems with objective test results are
handled as follows:
(1) If a problem with an objective test result
is detected by the NSP evaluation team
during an evaluation, the test may be
repeated or the QTG may be amended.
(2) If it is determined that the results of an
objective test do not support the level
requested but do support a lower level, the
NSPM may qualify the FFS at that lower
level. For example, if a Level D evaluation is
requested and the FFS fails to meet sound
test tolerances, it could be qualified at Level
C.
r. After an FFS is successfully evaluated,
the NSPM issues a statement of qualification
(SOQ) to the sponsor. The NSPM
recommends the FFS to the TPAA, who will
approve the FFS for use in a flight training
program. The SOQ will be issued at the
satisfactory conclusion of the initial or
continuing qualification. However, it is the
sponsor’s responsibility to obtain TPAA
approval prior to using the FSTD in an FAAapproved flight training program.
s. Under normal circumstances, the NSPM
establishes a date for the initial or upgrade
evaluation within ten (10) working days after
determining that a complete QTG is
acceptable. Unusual circumstances may
warrant establishing an evaluation date
before this determination is made. A sponsor
may schedule an evaluation date as early as
6 months in advance. However, there may be
a delay of 45 days or more in rescheduling
and completing the evaluation if the sponsor
is unable to meet the scheduled date. See
Attachment 4, Figure C4A, Sample Request
for Initial, Upgrade, or Reinstatement
Evaluation.
t. The numbering system used for objective
test results in the QTG should closely follow
the numbering system set out in Attachment
2, FFS Objective Tests, Table C2A.
u. Contact the NSPM or visit the NSPM
Web site for additional information regarding
the preferred qualifications of pilots used to
meet the requirements of § 60.15(d).
v. Examples of the exclusions for which
the FFS might not have been subjectively
tested by the sponsor or the NSPM and for
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63545
which qualification might not be sought or
granted, as described in § 60.15(g)(6), include
takeoffs and landing from slopes and
pinnacles.
End Information
lllllllllllllllllllll
12. Additional Qualifications for a Currently
Qualified Simulator (§ 60.16)
There is no additional regulatory or
informational material that applies to § 60.16,
Additional Qualifications for a Currently
Qualified FFS.
13. Previously Qualified Simulators (§ 60.17)
lllllllllllllllllllll
Begin QPS Requirements
a. In instances where a sponsor plans to
remove a FFS from active status for a period
of less than two years, the following
procedures apply:
(1) The NSPM must be notified in writing
and the notification must include an estimate
of the period that the FFS will be inactive;
(2) Continuing Qualification evaluations
will not be scheduled during the inactive
period;
(3) The NSPM will remove the FFS from
the list of qualified FSTDs on a mutually
established date not later than the date on
which the first missed continuing
qualification evaluation would have been
scheduled;
(4) Before the FFS is restored to qualified
status, it must be evaluated by the NSPM.
The evaluation content and the time required
to accomplish the evaluation is based on the
number of continuing qualification
evaluations and sponsor-conducted quarterly
inspections missed during the period of
inactivity.
(5) The sponsor must notify the NSPM of
any changes to the original scheduled time
out of service;
b. Simulators qualified prior to October 30,
2007, are not required to meet the general
simulation requirements, the objective test
requirements, and the subjective test
requirements of attachments 1, 2, and 3,
respectively, of this appendix.
c. [Reserved]
End QPS Requirements
lllllllllllllllllllll
Begin Information
d. Other certificate holders or persons
desiring to use an FFS may contract with FFS
sponsors to use FFSs previously qualified at
a particular level for a helicopter type and
approved for use within an FAA-approved
flight training program. Such FFSs are not
required to undergo an additional
qualification process, except as described in
§ 60.16.
e. Each FFS user must obtain approval
from the appropriate TPAA to use any FFS
in an FAA-approved flight training program.
f. The intent of the requirement listed in
§ 60.17(b), for each FFS to have a Statement
of Qualification within 6 years, is to have the
availability of that statement (including the
configuration list and the limitations to
authorizations) to provide a complete picture
of the FFS inventory regulated by the FAA.
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The issuance of the statement will not
require any additional evaluation or require
any adjustment to the evaluation basis for the
FFS.
g. Downgrading of an FFS is a permanent
change in qualification level and will
necessitate the issuance of a revised
Statement of Qualification to reflect the
revised qualification level, as appropriate. If
a temporary restriction is placed on an FFS
because of a missing, malfunctioning, or
inoperative component or on-going repairs,
the restriction is not a permanent change in
qualification level. Instead, the restriction is
temporary and is removed when the reason
for the restriction has been resolved.
h. It is not the intent of the NSPM to
discourage the improvement of existing
simulation (e.g., the ‘‘updating’’ of a visual
system to a newer model, or the replacement
of the IOS with a more capable unit) by
requiring the ‘‘updated’’ device to meet the
qualification standards current at the time of
the update. Depending on the extent of the
update, the NSPM may require that the
updated device be evaluated and may require
that an evaluation include all or a portion of
the elements of an initial evaluation.
However, the standards against which the
device would be evaluated are those that are
found in the MQTG for that device.
i. The NSPM will determine the evaluation
criteria for an FSTD that has been removed
from active status. The criteria will be based
on the number of continuing qualification
evaluations and quarterly inspections missed
during the period of inactivity. For example,
if the FFS were out of service for a 1 year
period, it would be necessary to complete the
entire QTG, since all of the quarterly
evaluations would have been missed. The
NSPM will also consider how the FFS was
stored, whether parts were removed from the
FFS and whether the FFS was disassembled.
j. The FFS will normally be requalified
using the FAA-approved MQTG and the
criteria that was in effect prior to its removal
from qualification. However, inactive periods
of 2 years or more will require requalification
under the standards in effect and current at
the time of requalification.
End Information
lllllllllllllllllllll
sroberts on PROD1PC70 with RULES
14. Inspection, Continuing Qualification
Evaluation, and Maintenance Requirements
(§ 60.19)
lllllllllllllllllllll
Begin QPS Requirements
a. The sponsor must conduct a minimum
of four evenly spaced inspections throughout
the year. The objective test sequence and
content of each inspection must be
developed by the sponsor and must be
acceptable to the NSPM.
b. The description of the functional
preflight inspection must be contained in the
sponsor’s QMS.
c. Record ‘‘functional preflight’’ in the FFS
discrepancy log book or other acceptable
location, including any item found to be
missing, malfunctioning, or inoperative.
End QPS Requirements
lllllllllllllllllllll
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Begin Information
d. The sponsor’s test sequence and the
content of each quarterly inspection required
in § 60.19(a)(1) should include a balance and
a mix from the objective test requirement
areas listed as follows:
(1) Performance.
(2) Handling qualities.
(3) Motion system (where appropriate).
(4) Visual system (where appropriate).
(5) Sound system (where appropriate).
(6) Other FFS systems.
e. If the NSP evaluator plans to accomplish
specific tests during a normal continuing
qualification evaluation that requires the use
of special equipment or technicians, the
sponsor will be notified as far in advance of
the evaluation as practical; but not less than
72 hours. Examples of such tests include
latencies, control dynamics, sounds and
vibrations, motion, and/or some visual
system tests.
f. The continuing qualification evaluations,
described in § 60.19(b), will normally require
4 hours of FFS time. However, flexibility is
necessary to address abnormal situations or
situations involving aircraft with additional
levels of complexity (e.g., computer
controlled aircraft). The sponsor should
anticipate that some tests may require
additional time. The continuing qualification
evaluations will consist of the following:
(1) Review of the results of the quarterly
inspections conducted by the sponsor since
the last scheduled continuing qualification
evaluation.
(2) A selection of approximately 8 to 15
objective tests from the MQTG that provide
an adequate opportunity to evaluate the
performance of the FFS. The tests chosen
will be performed either automatically or
manually and should be able to be conducted
within approximately one-third (1/3) of the
allotted FFS time.
(3) A subjective evaluation of the FFS to
perform a representative sampling of the
tasks set out in attachment 3 of this
appendix. This portion of the evaluation
should take approximately two-thirds (2/3) of
the allotted FFS time.
(4) An examination of the functions of the
FFS may include the motion system, visual
system, sound system, instructor operating
station, and the normal functions and
simulated malfunctions of the simulated
helicopter systems. This examination is
normally accomplished simultaneously with
the subjective evaluation requirements.
g. The requirement established in
§ 60.19(b)(4) regarding the frequency of
NSPM-conducted continuing qualification
evaluations for each FFS is typically 12
months. However, the establishment and
satisfactory implementation of an approved
QMS for a sponsor will provide a basis for
adjusting the frequency of evaluations to
exceed 12-month intervals.
End Information
lllllllllllllllllllll
15. Logging Simulator Discrepancies
(§ 60.20)
There is no additional regulatory or
informational material that applies to § 60.20.
Logging FFS Discrepancies.
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16. Interim Qualification of Simulators for
New Helicopter Types or Models (§ 60.21)
There is no additional regulatory or
informational material that applies to § 60.21,
Interim Qualification of FFSs for New
Helicopter Types or Models.
17. Modifications to Simulators (§ 60.23)
lllllllllllllllllllll
Begin QPS Requirements
a. The notification described in
§ 60.23(c)(2) must include a complete
description of the planned modification, with
a description of the operational and
engineering effect the proposed modification
will have on the operation of the FFS and the
results that are expected with the
modification incorporated.
b. Prior to using the modified FFS:
(1) All the applicable objective tests
completed with the modification
incorporated, including any necessary
updates to the MQTG (e.g., accomplishment
of FSTD Directives) must be acceptable to the
NSPM; and
(2) The sponsor must provide the NSPM
with a statement signed by the MR that the
factors listed in § 60.15(b) are addressed by
the appropriate personnel as described in
that section.
End QPS Requirements
lllllllllllllllllllll
Begin Information
FSTD Directives are considered
modifications of an FFS. See Attachment 4
for a sample index of effective FSTD
Directives.
End Information
lllllllllllllllllllll
18. Operation with Missing, Malfunctioning,
or Inoperative Components (§ 60.25)
lllllllllllllllllllll
Begin Information
a. The sponsor’s responsibility with respect
to § 60.25(a) is satisfied when the sponsor
fairly and accurately advises the user of the
current status of an FFS, including any
missing, malfunctioning, or inoperative
(MMI) component(s).
b. If the 29th or 30th day of the 30-day
period described in § 60.25(b) is on a
Saturday, a Sunday, or a holiday, the FAA
will extend the deadline until the next
business day.
c. In accordance with the authorization
described in § 60.25(b), the sponsor may
develop a discrepancy prioritizing system to
accomplish repairs based on the level of
impact on the capability of the FFS. Repairs
having a larger impact on FFS capability to
provide the required training, evaluation, or
flight experience will have a higher priority
for repair or replacement.
End Information
lllllllllllllllllllll
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19. Automatic Loss of Qualification and
Procedures for Restoration of Qualification
(§ 60.27)
Begin Information
If the sponsor provides a plan for how the
FFS will be maintained during its out-ofservice period (e.g., periodic exercise of
mechanical, hydraulic, and electrical
systems; routine replacement of hydraulic
fluid; control of the environmental factors in
which the FFS is to be maintained) there is
a greater likelihood that the NSPM will be
able to determine the amount of testing
required for requalification.
End Information
lllllllllllllllllllll
20. Other Losses of Qualification and
Procedures for Restoration of Qualification
(§ 60.29)
lllllllllllllllllllll
§ 60.31(a)(2) must consist of the name of the
aircraft system software, aerodynamic model,
or engine model change, the date of the
change, a summary of the change, and the
reason for the change.
b. If a coded form for record keeping is
used, it must provide for the preservation
and retrieval of information with appropriate
security or controls to prevent the
inappropriate alteration of such records after
the fact.
End QPS Requirements
lllllllllllllllllllll
22. Applications, Logbooks, Reports, and
Records: Fraud, Falsification, or Incorrect
Statements (§ 60.33)
There are no additional QPS requirements
or informational material that apply to
§ 60.33, Applications, Logbooks, Reports, and
Records: Fraud, Falsification, or Incorrect
Statements.
Begin Information
If the sponsor provides a plan for how the
FFS will be maintained during its out-ofservice period (e.g., periodic exercise of
mechanical, hydraulic, and electrical
systems; routine replacement of hydraulic
fluid; control of the environmental factors in
which the FFS is to be maintained) there is
a greater likelihood that the NSPM will be
able to determine the amount of testing
required for requalification.
23. [Reserved]
End Information
lllllllllllllllllllll
Attachment 1 to Appendix C to Part 60—
General Simulator Requirements
lllllllllllllllllllll
21. Recordkeeping and Reporting (§ 60.31)
lllllllllllllllllllll
Begin QPS Requirements
a. FSTD modifications can include
hardware or software changes. For FSTD
modifications involving software
programming changes, the record required by
24. [Reserved]
25. FSTD Qualification on the Basis of a
Bilateral Aviation Safety Agreement (BASA)
(§ 60.37)
There are no additional QPS requirements
or informational material that apply to
§ 60.37, FSTD Qualification on the Basis of
a Bilateral Aviation Safety Agreement
(BASA).
Begin QPS Requirements
1. Requirements.
a. Certain requirements included in this
appendix must be supported with a
Statement of Compliance and Capability
(SOC), which may include objective and
63547
subjective tests. The SOC will confirm that
the requirement was satisfied, and describe
how the requirement was met, such as gear
modeling approach or coefficient of friction
sources. The requirements for SOCs and tests
are indicated in the ‘‘General Simulator
Requirements’’ column in Table C1A of this
appendix.
b. Table C1A describes the requirements
for the indicated level of FFS. Many devices
include operational systems or functions that
exceed the requirements outlined in this
section. However, all systems will be tested
and evaluated in accordance with this
appendix to ensure proper operation.
End QPS Requirements
lllllllllllllllllllll
Begin Information
2. Discussion.
a. This attachment describes the general
simulator requirements for qualifying a
helicopter FFS. The sponsor should also
consult the objective tests in Attachment 2
and the examination of functions and
subjective tests listed in Attachment 3 to
determine the complete requirements for a
specific level simulator.
b. The material contained in this
attachment is divided into the following
categories:
(1) General cockpit configuration.
(2) Simulator programming.
(3) Equipment operation.
(4) Equipment and facilities for instructor/
evaluator functions.
(5) Motion system.
(6) Visual system.
(7) Sound system.
c. Table C1A provides the standards for the
General Simulator Requirements.
End Information
lllllllllllllllllllll
TABLE C1A.— MINIMUM SIMULATOR REQUIREMENTS
QPS requirements
No.
Simulator levels
General simulator requirements
A
B
C
Information
Notes
D
1. General Cockpit Configuration
sroberts on PROD1PC70 with RULES
1.a ..
The simulator must have a cockpit that is a replica of the helicopter simulated with controls, equipment, observable
cockpit indicators, circuit breakers, and bulkheads properly
located, functionally accurate and replicating the helicopter.
The direction of movement of controls and switches must
be identical to that in the helicopter. Pilot seats must afford
the capability for the occupant to be able to achieve the
design ‘‘eye position’’ established for the helicopter being
simulated. Equipment for the operation of the cockpit windows must be included, but the actual windows need not
be operable. Fire axes, extinguishers, spare light bulbs,
etc., must be available in the FFS but may be relocated to
a suitable location as near as practical to the original position. Fire axes, landing gear pins, and any similar purpose
instruments need only be represented in silhouette.
An SOC is required.
X
X
X
1.b.
Those circuit breakers that affect procedures and/or result in
observable cockpit indications must be properly located
and functionally accurate.
X
X
X
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For simulator purposes, the cockpit consists of
all that space forward of a cross section of the
fuselage at the most extreme aft setting of the
pilots’ seats including addiitonal, required flight
crewmember duty stations and those required
bulkheads aft of the pilot seats. For clarification, bulkheads containing only items such as
landing gear pin storage compartments, fire
axes or extinguishers, spare light bulbs, aircraft documents pouches etc., are not considered essential and may be omitted.
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
TABLE C1A.— MINIMUM SIMULATOR REQUIREMENTS—Continued
QPS requirements
No.
Simulator levels
General simulator requirements
A
B
C
Information
Notes
D
An SOC is required.
2. Programming
2.a.
A flight dynamics model that accounts for various combinations of drag and thrust normally encountered in flight must
correspond to actual flight conditions, including the effect
of change in helicopter attitude, thrust, drag, altitude, temperature, gross weight, moments of inertia, center of gravity location, and configuration.
An SOC is required.
X
X
X
2.b.
The simulator must have the computer capacity, accuracy,
resolution, and dynamic response needed to meet the
qualification level sought.
An SOC is required.
X
X
X
2.c ..
Ground handling and aerodynamic programming must include the following:
2.c.1
Ground effect ...........................................................................
X
X
X
Applicable areas include flare and touchdown
from a running landing as well as for inground-effect (IGE) hover. A reasonable simulation of ground effect includes modeling of
lift, drag, pitching moment, trim, and power
while in ground effect.
X
X
X
Reaction of the helicopter upon contact with the
landing surface during landing, (e.g., strut deflection, tire or skid friction, side forces) and
may differ with changes in gross weight, airspeed, rate of descent on touchdown, and
slide slip.
X
X
X
X
X
Level B does not require hover programming.
An SOC is required.
2.c.2
Ground reaction .......................................................................
Level B does not require hover programming.
An SOC is required.
Ground handling characteristics. Control inputs required during operations in crosswind, during braking and deceleration, and for turning radius.
2.d ..
The simulator must provide for manual and automatic testing
of simulator hardware and software programming to determine compliance with simulator objective tests as prescribed in Attachment 2.
An SOC is required. .................................................................
2.e ..
Relative responses of the motion system, visual system, and
cockpit instruments, measured by latency tests or transport
delay tests. Motion onset should occur before the start of
the visual scene change (the start of the scan of the first
video field containing different information) but must occur
before the end of the scan of that video field. Instrument
response may not occur prior to motion onset. Test results
must be within the following limits:
2.e.1
Response must be within 150 milliseconds of the helicopter
response.
Objective Tests are required. See Attachment 2 for Transport
Delay and Latency Tests.
2.e.2
sroberts on PROD1PC70 with RULES
2.c.3
Response must be within 100 milliseconds of the helicopter
response.
Objective Tests are required. See Attachment 2 for Transport
Delay and Latency Tests.
X
X
2.f ...
The simulator must accurately reproduce the following runway conditions:
(1) Dry;
X
X
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This may include an automated system, which
could be used for conducting at least a portion
of the QTG tests. Automatic ‘‘flagging’’ of outof-tolerance situations is encouraged.
The intent is to verify that the simulator provides
instrument, motion, and visual cues that are
like the helicopter responses within the stated
time delays. For helicopter response, acceleration in the appropriate corresponding rotational
axis is preferred.
X
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63549
TABLE C1A.— MINIMUM SIMULATOR REQUIREMENTS—Continued
QPS requirements
No.
Simulator levels
General simulator requirements
A
B
C
Information
Notes
D
(2) Wet;
(3) Icy;
(4) Patchy Wet
(5) Patchy Icy
An SOC is required.
Objective tests are required for dry, wet, and icy runway conditions.
Subjective tests are required for patchy wet, patchy icy, and
wet on rubber residue in touchdown zone conditions.
2.g.
The simulator must simulate:
(1) Brake and tire failure dynamics (including antiskid
failure).
(2) Decreased brake efficiency due to high brake temperatures, if applicable.
An SOC is required.
X
X
Simulator pitch, side loading, and directional
control characteristics should be representative of the helicopter.
2.h ..
The modeling in the simulator must include:
(1) Ground effect,
(2) Effects of airframe icing (if applicable),
(3) Aerodynamic interference effects between the rotor
wake and fuselage,
(4) Influence of the rotor on control and stabilization systems, and
(5) Representations of nonlinearities due to sideslip.
An SOC is required and must include references to computations of aeroelastic representations and of nonlinearities
due to sideslip.
An SOC and a demonstration of icing effects (if applicable)
are required.
X
X
See Attachment 2 for further information on
ground effect.
2.i ...
The simulator must provide for realistic mass properties, including gross weight, center of gravity, and moments of inertia as a function of payload and fuel loading.
An SOC is required and must include a range of tabulated
target values to enable a subjective test of the mass properties model to be conducted from the instructor’s station.
X
X
X
3. Equipment Operation
All relevant instrument indications involved in the simulation
of the helicopter must automatically respond to control
movement or external disturbances to the simulated helicopter; e.g., turbulence or windshear. Numerical values
must be presented in the appropriate units.
A subjective test is required.
X
X
X
3.b ..
Communications, navigation, caution, and warning equipment
must be installed and operate within the tolerances applicable for the helicopter being simulated.
A subjective test is required.
X
X
X
3.c ..
Simulated airplane systems must operate as the helicopter
systems would operate under normal, abnormal, and
emergency operating conditions on the ground and in flight.
A subjective test is required.
X
X
X
3.d ..
sroberts on PROD1PC70 with RULES
3.a.
The simulator must provide pilot controls with control forces
and control travel that correspond to the simulated helicopter. The simulator must also react in the same manner
as in the helicopter under the same flight conditions.
An objective test is required.
X
X
X
See Attachment 3 for further information regarding long-range navigation equipment.
4. Instructor / Evaluator Facilities
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
TABLE C1A.— MINIMUM SIMULATOR REQUIREMENTS—Continued
QPS requirements
Simulator levels
No.
General simulator requirements
4.a ..
A
Information
Notes
B
C
D
In addition to the flight crewmember stations, the simulator
must have at least two suitable seats for the instructor/
check airman and FAA inspector. These seats must provide adequate vision to the pilot’s panel and forward windows. All seats other than flight crew seats need not represent those found in the helicopter but must be adequately secured to the floor and equipped with similar positive restraint devices.
A subjective test is required.
X
X
X
4.b ..
The simulator must have controls that enable the instructor/
evaluator to control all required system variables and insert
all abnormal or emergency conditions into the simulated
helicopter systems as described in the sponsor’s FAA-approved training program, or as described in the relevant
operating manual as appropriate.
A subjective test is required.
X
X
X
4.c ..
The simulator must have instructor controls for environmental
conditions including wind speed and direction.
A subjective test is required.
X
X
X
4.d ..
The simulator must provide the instructor or evaluator the the
ability to present ground and air hazards.
X
X
For example, another aircraft crossing the active
runway and converging airborne traffic.
X
X
For example, touchdown cues should be a function of the rate of descent (RoD) of the simulated helicopter.
X
X
X
X
X
X
X
X
X
X
The NSPM will consider alternatives to this
standard for additional seats based on unique
cockpit configurations.
A subjective test is required.
5. Motion System
The simulator must have motion (force) cues perceptible to
the pilot that are representative of the motion in a helicopter.
A subjective test is required.
X
5.b ..
The simulator must have a motion (force cueing) system with
a minimum of three degrees of freedom (at least pitch, roll,
and heave).
An SOC is required.
X
5.c ..
The simulator must have a motion (force cueing) system that
produces cues at least equivalent to those of a six-degrees-of-freedom, synergistic platform motion system (i.e.,
pitch, roll, yaw, heave, sway, and surge).
An SOC is required.
5.d ..
The simulator must provide for the recording of the motion
system response time.
An SOC is required.
5.e ..
sroberts on PROD1PC70 with RULES
5.a ..
The simulator must provide motion effects programming to
include the following:
(1) Runway rumble, oleo deflections, effects of ground
speed, uneven runway, characteristics.
(2) Buffets due to transverse flow effects.
(3) Buffet during extension and retraction of landing
gear.
(4) Buffet due to retreating blade stall.
(5) Buffet due to settling with power.
(6) Representative cues resulting from touchdown.
(7) Rotor vibrations.
A subjective test is required for each.
(8) Tire failure dynamics.
(9) Engine malfunction and engine damage.
(10) Airframe ground strike.
A subjective test is required for each.
(11) Motion vibrations that result from atmospheric disturbances.
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X
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For air turbulence, general purpose disturbance
models that approximate demonstrable flight
test data are acceptable.
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
63551
TABLE C1A.— MINIMUM SIMULATOR REQUIREMENTS—Continued
QPS requirements
Simulator levels
No.
General simulator requirements
A
5.f ...
B
C
The simulator must provide characteristic motion vibrations
that result from operation of the helicopter, (for example,
retreating blade stall, extended landing gear, settling with
power) in so far as vibration marks an event or helicopter
state, which can be sensed in the cockpit.
A subjective test is required.
An objective test is required.
Information
Notes
D
X
The simulator should be programmed and instrumented in such a manner that the characteristic buffet modes can be measured and
compared to helicopter data.
6. Visual System
6.a ..
The simulator must have a visual system providing an out-ofthe-cockpit view.
A subjective test is required.
X
6.b ..
The simulator must provide a continuous minimum collimated
field of view of 75° horizontally and 30° vertically per pilot
seat. Both pilot seat visual systems must be operable simultaneously.
An SOC is required.
X
6.c ..
The simulator must provide a continuous minimum collimated
visual field of view of 150° horizontally and 40° vertically
per pilot seat. Both pilot seat visual systems must be operable simultaneously. Horizontal field of view is centered on
the zero degree azimuth line relative to the aircraft
fuselange.
An SOC is required.
6.d ..
The simulator must provide a continuous minimum collimated
visual field of view of 180° horizontally and 60° vertically
per pilot seat. Both pilot seat visual systems must be operable simultaneously. Horizontal field of view is centered on
the zero degree azimuth line relative to the aircraft fuselage.
An SOC is required.
An objective test is required.
6.e ..
The visual system must be free from optical discontinuities
and artifacts that create non-realistic cues.
X
X
X
Optimization of the visual field of view may be
considered with respect to the specific helicopter cockpit cut-off angle.
X
Optimization of the visual field of view may be
considered with respect to the specific airplane
cockpit cut-off angle.
Non-realistic cues might include image ‘‘swimming’’ and image ‘‘roll-off,’’ that may lead a
pilot to make incorrect assessments of speed,
acceleration and/or situational awareness.
X
X
X
A subjective test is required.
The simulator must have operational landing lights for night
scenes. Where used, dusk (or twilight) scenes require
operational landing lights.
A subjective test is required.
X
X
X
6.g ..
The simulator must have instructor controls for the following:
(1) Cloudbase.
(2) Visibility in statute miles (kilometers) and runway visual range (RVR) in ft. (meters).
(3) Airport or landing area selection.
(4) Airport or landing area lighting.
A subjective test is required.
X
X
X
6.h ..
sroberts on PROD1PC70 with RULES
6.f ...
Each airport scene displayed must include the following:
1. Airport runways and taxiways.
2. Runway definition:
a. Runway surface and markings.
b. Lighting for the runway in use, including runway
threshold, edge, centerline, touchdown zone,
VASI (or PAPI), and approach lighting of appropriate colors, as appropriate.
c. Taxiway lights.
A subjective test is required.
X
X
X
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
TABLE C1A.— MINIMUM SIMULATOR REQUIREMENTS—Continued
QPS requirements
Simulator levels
General simulator requirements
6.i ...
B
C
The distances at which runway features are visible, as measured from runway threshold to a helicopter aligned with the
runway on an extended 3° glide slope must not be less
than listed below:
1. Runway definition, strobe lights, approach lights, runway edge white lights and VASI or PAPI system lights
from 5 statute miles (8 km) of the runway threshold.
2. Runway centerline lights and taxiway definition from 3
statute miles (4.8 km).
3. Threshold lights and touchdown zone lights from 2
statute miles (3.2 km).
4. Runway markings within range of landing lights for
night scenes and as required by three (3) arc-minutes
resolution on day scenes.
A subjective test is required.
X
X
X
The simulator must provide visual system compatibility with
dynamic response programming.
A subjective test is required.
X
X
X
6.k ..
The simulator must show that the segment of the ground
visible from the simulator cockpit is the same as from the
airplane cockpit (within established tolerances) when at the
correct airspeed, in the landing configuration, at a main
wheel height of 100 feet (30 meters) above the touchdown
zone. Data submitted must include at least the following:
(1) Static helicopter dimensions as follows:
(i) Horizontal and vertical distance from main landing gear (MLG) or landing skids to glideslope reception antenna.
(ii) Horizontal and vertical distance from MLG or
skids to pilot’s eyepoint.
(iii) Static cockpit cutoff angle.
(2) Approach data as follows:
(i) Identification of runway.
(ii) Horizontal distance from runway threshold to
glideslope intercept with runway.
(iii) Glideslope angle.
(iv) Helicopter pitch angle on approach.
(3) Helicopter data for manual testing:
(i) Gross weight.
(ii) Helicopter configuration.
(iii) Approach airspeed.
The QTG must contain appropriate calculations and a drawing showing the pertinent data used to establish the helicopter location and the segment of the ground that is visible considering the helicopter attitude (cockpit cut-off
angle) and a runway visual range of 1,200 feet or 350 meters. Simulator performance must be measured against the
QTG calculations. Sponsors must provide this data for
each simulator (regardless of previous qualification standards) to qualify the simulator for all precision instrument
approaches.
At the near end of the visual ground segment, lights and
ground objects computed to be visible from the helicopter
cockpit must be visible in the FFS. The far end of the visual ground segment must be at the computed end of the
segment ±20% of the computed visible segment distance.
An SOC is required.
An objective test is required.
X
X
X
6.1 ..
The simulator must provide visual cues necessary to assess
rate of change of height, height AGL, as well as
translational displacement and rates during takeoffs and
landings.
A subjective test is required.
X
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A
Information
Notes
D
6.j ...
sroberts on PROD1PC70 with RULES
No.
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The test should be conducted in the landing configuration, trimmed for appropriate airspeed, at
100 ft (30m) above the touchdown zone, on
glide slope with an RVR value set at 1,200 ft
(350m). This will show the modeling accuracy
of RVR, glideslope, and localizer for a given
weight, configuration and speed within the helicopter’s operational envelope for a normal
appraoch and landing. If non-homogenous fog
is used, the vertical variation in horizontal visibility should be described and be included in
the slant range visibility calculation used in the
computations.
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
63553
TABLE C1A.— MINIMUM SIMULATOR REQUIREMENTS—Continued
QPS requirements
Simulator levels
No.
General simulator requirements
6.m
A
B
C
The simulator must have night and dusk (or twilight) visual
scene capability, including general terrain characteristics
and significant landmarks, free from apparent quantization.
Dusk (or twilight) scene must enable identification of a visible
horizon and general terrain characteristics.
A subjective test is required.
X
X
6.n ..
The simulator must provide visual cues necessary to assess
rate of change of height, height AGL, as well as
translational displacement and rates during takeoff, low altitude/low airspeed maneuvering, hover, and landing.
A subjective test is required.
X
X
6.o.
The simulator must provide for accurate portrayal of the visual environment relating to the simulator attitude.
X
X
Information
Notes
D
X
Examples of general terrain characteristics are
fields, roads, and bodies of water.
Visual attitude vs. simulator attitude is a comparison of pitch and roll of the horizon as displayed in the visual scene compared to the
display on the attitude indicator.
A subjective test is required.
The simulator must provide for quick confirmation of visual
system color, RVR, focus, and intensity.
An SOC is required.
A subjective test is required.
X
X
6.q ..
The simulator must provide a minimum of three airport
scenes including the following:
1. Surfaces on runways, taxiways, and ramps.
2. Lighting of approriate color for all runways, including
runway threshold, edge, centerline, VASI (or PAPI),
and approach lighting for the runway in use.
3. Airport taxiway lighting.
4. Ramps and buildings that correspond to the sponsor’s
Line Oriented scenarios, as appropriate.
A subjective test is required.
X
X
6.r ...
The simulator must be capable of producing at least 10 levels of occulting..
A subjective test is required.
X
X
6.s ..
The fog simulator must be able to provide weather representations including the following:
(1) Variable cloud density.
(2) Partial obscuration of ground scenes; i.e., the effect
of a scattered to broken cloud deck.
(3) Gradual breakout.
(4) Patchy fog.
(5) The effect of fog on airport lighting
The weather representations must be provided at and below
an altitude of 2,000 ft (610 m) height above the airport and
within a radius of 10 miles (16 km) from the airport.
A subjective test is required.
X
X
6.t ...
sroberts on PROD1PC70 with RULES
6.p ..
Night Visual Scenes. The simulator must provide night visual
scenes with sufficient scene content to recognize the airport, the terrain, and major landmarks around the airport.
The scene content must allow a pilot to successfully accomplish a visual landing. Night scenes, as a minimum,
must provide presentations of sufficient surfaces with appropriate textural cues that include self-illuminated objects
such as road networks, ramp lighting, and airport signage,
to conduct a visual approach, a landing, and airport movement (taxi). Scenes must include a definable horizon and
typical terrain characteristics such as fields, roads and
bodies of water and surfaces illuminated by airplane landing lights.
X
X
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63554
Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
TABLE C1A.— MINIMUM SIMULATOR REQUIREMENTS—Continued
QPS requirements
Simulator levels
No.
General simulator requirements
A
B
C
6.u ..
Dusk (Twilight) Visual Scenes. The simulator must provide
dusk (or twilight) visual scenes with sufficient scene content to recognize the airport, the terrain, and major landmarks around the airport. The scene content must allow a
pilot to successfully accomplish a visual landing. Dusk (or
twilight) scenes, as a minimum, must provide full color
presentations of reduced ambient intensity, sufficient surfaces with appropriate textural cues that include self-illuminated objects such as road networks, ramp lighting and
airport signage, to conduct a visual approach, landing and
airport movement (taxi). Scenes must include a definable
horizon and typical terrain characteristics such as fields,
roads and bodies of water and surfaces illuminated by representative aircraft lighting (e.g., landing lights). If provided,
directional horizon lighting must have correct orientation
and be consistent with surface shading effects. Total
scene content must be comparable in detail to that produced by 10,000 visible textured surfaces and 15,000 visible lights with sufficient system capacity to display 16 simultaneously moving objects.
An SOC is required.
X
6.v ..
Night, Dusk (Twilight), and Daylight Visual Scenes. The simulator must have night, dusk (twilight), and daylight visual
scenes with sufficient scene content to recognize the airport, the terrain, and major landmarks around the airport.
The scene content must allow a pilot to successfully accomplish a visual landing. Any ambient lighting must not
‘‘washout’’ the displayed visual scene. Total scene content
must be comparable in detail to that produced by 10,000
visible textured surfaces and 6,000 visible lights with sufficient system capacity to display 16 simultaneously moving
objects. The visual display must be free of apparent quantization and other distracting visual effects while the simulator is in motion.
Note: These requirements are applicable to any level of simulator equipped with a daylight visual system.
An SOC is required.
A subjective test is required.
Objective tests are required.
X
6.w
The simulator must provide operational visual scenes that
portray physical relationships known to cause landing illusions to pilots.
X
Information
Notes
D
X
For example: short runways, landing approaches
over water, uphill or downhill runways, rising
terrain on the approach path, unique topographic features.
A subjective test is required.
The simulator must provide special weather representations
of light, medium, and heavy precipitation near a thunderstorm on takeoff and during approach and landing. Representations need only be presented at and below an altitude of 2,000 ft. (610 m) above the airport surface and
within 10 miles (16 km) of the airport.
A subjective test is required.
X
6.y.
The simulator must present visual scenes of wet and snowcovered runways, including runway lighting reflections for
wet conditions, partially obsecured lights for snow conditions.
A subjective test is required.
X
6.z ..
sroberts on PROD1PC70 with RULES
6.x ..
The simulator must present realistic color and directionality of
all airport lighting.
A subjective test is required.
X
The NSPM will consider suitable alternative effects.
7. Sound System
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
63555
TABLE C1A.— MINIMUM SIMULATOR REQUIREMENTS—Continued
QPS requirements
Simulator levels
No.
General simulator requirements
7.a ..
B
C
The simulator must provide cockpit sounds that result from
pilot actions that correspond to those that occur in the helicopter.
X
X
X
7.b ..
Volume control, if installed, must have an indication of the
sound level setting.
X
X
X
7.c ..
The simulator must accurately simulate the sound of precipitation, windshield wipers, and other significant helicopter
noises perceptible to the pilot during normal and abnormal
operations, and include the sound of a crash (when the
simulator is landed in an unusual attitude or in excess of
the structural gear limitations); normal engine sounds; and
the sounds of gear extension and retraction.
An SOC is required.
A subjective test is required.
X
X
7.d ..
The simulator must provide realistic amplitude and frequency
of cockpit noises and sounds. Simulator performance must
be recorded, compared to amplitude and frequency of the
same sounds recorded in the helicopter, and made a part
of the QTG.
Begin Information
1. Discussion.
(a) If relevant winds are present in the
objective data, the wind vector (magnitude
and direction) should be clearly noted as part
of the data presentation, expressed in
conventional terminology, and related to the
runway being used for the test.
(b) The NSPM will not evaluate any
simulator unless the required SOC indicates
that the motion system is designed and
manufactured to safely operate within the
simulator’s maximum excursion,
acceleration, and velocity capabilities (see
Motion System in the following table).
End Information
lllllllllllllllllllll
Begin QPS Requirements
sroberts on PROD1PC70 with RULES
Information
Notes
D
Attachment 2 to Appendix C to Part 60—
Simulator Objective Tests
lllllllllllllllllllll
1. Test requirements.
a. The ground and flight tests required for
qualification are listed in Table of C2A, FFS
Objective Tests. Computer generated
simulator test results must be provided for
each test except where an alternative test is
specifically authorized by the NSPM. If a
flight condition or operating condition is
required for the test but does not apply to the
helicopter being simulated or to the
qualification level sought, it may be
disregarded (e.g., an engine out missed
approach for a single-engine helicopter, or a
hover test for a Level B simulator). Each test
result is compared against the validation data
described in § 60.13 and in this appendix.
Although use of a driver program designed to
automatically accomplish the tests is
encouraged for all simulators and required
for Level C and Level D simulators, each test
must be able to be accomplished manually
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A
X
while recording all appropriate parameters.
The results must be produced on an
appropriate recording device acceptable to
the NSPM and must include simulator
number, date, time, conditions, tolerances,
and appropriate dependent variables
portrayed in comparison to the validation
data. Time histories are required unless
otherwise indicated in Table C2A. All results
must be labeled using the tolerances and
units given.
b. Table C2A sets out the test results
required, including the parameters,
tolerances, and flight conditions for
simulator validation. Tolerances are provided
for the listed tests because mathematical
modeling and acquisition/development of
reference data are often inexact. All
tolerances listed in the following tables are
applied to simulator performance. When two
tolerance values are given for a parameter,
the less restrictive may be used unless
otherwise indicated.
c. Certain tests included in this attachment
must be supported with a Statement of
Compliance and Capability (SOC). In Table
C2A, requirements for SOCs are indicated in
the ‘‘Test Details’’ column.
d. When operational or engineering
judgment is used in making assessments for
flight test data applications for simulator
validity, such judgment must not be limited
to a single parameter. For example, data that
exhibit rapid variations of the measured
parameters may require interpolations or a
‘‘best fit’’ data selection. All relevant
parameters related to a given maneuver or
flight condition must be provided to allow
overall interpretation. When it is difficult or
impossible to match simulator to helicopter
data throughout a time history, differences
must be justified by providing a comparison
of other related variables for the condition
being assessed.
e. It is not acceptable to program the FFS
so that the mathematical modeling is correct
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only at the validation test points. Unless
noted otherwise, simulator tests must
represent helicopter performance and
handling qualities at operating weights and
centers of gravity (CG) typical of normal
operation. If a test is supported by helicopter
data at one extreme weight or CG, another
test supported by helicopter data at midconditions or as close as possible to the other
extreme must be included, except as may be
authorized by the NSPM. Certain tests that
are relevant only at one extreme CG or weight
condition need not be repeated at the other
extreme. Tests of handling qualities must
include validation of augmentation devices.
f. When comparing the parameters listed to
those of the helicopter, sufficient data must
also be provided to verify the correct flight
condition and helicopter configuration
changes. For example, to show that control
force is within ±0.5 pound (0.22 daN) in a
static stability test, data to show the correct
airspeed, power, thrust or torque, helicopter
configuration, altitude, and other appropriate
datum identification parameters must also be
given. If comparing short period dynamics,
normal acceleration may be used to establish
a match to the helicopter, but airspeed,
altitude, control input, helicopter
configuration, and other appropriate data
must also be given. All airspeed values must
be properly annotated (e.g., indicated versus
calibrated). In addition, the same variables
must be used for comparison (e.g., compare
inches to inches rather than inches to
centimeters).
g. The QTG provided by the sponsor must
clearly describe how the simulator will be set
up and operated for each test. Each simulator
subsystem may be tested independently, but
overall integrated testing of the simulator
must be accomplished to assure that the total
simulator system meets the prescribed
standards. A manual test procedure with
explicit and detailed steps for completing
each test must also be provided.
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h. In those cases where the objective test
results authorize a ‘‘snapshot test’’ or ‘‘a
series of snapshot test’’ results in lieu of a
time-history result, the sponsor or other data
provider must ensure that a steady state
condition exists at the instant of time
captured by the ‘‘snapshot.’’
i. For previously qualified simulators, the
tests and tolerances of this attachment may
be used in subsequent continuing
qualification evaluations for any given test if
the sponsor has submitted a proposed MQTG
revision to the NSPM and has received
NSPM approval.
j. Motion System Tests:
(a) The minimum excursions,
accelerations, and velocities for pitch, roll,
and yaw must be measurable about a single,
common reference point and must be
achieved by driving one degree of freedom at
a time.
(b) The minimum excursions,
accelerations, and velocities for heave, sway,
and surge may be measured about different
but identifiable reference points and must
also be achieved by driving one degree of
freedom at a time.
k. Tests of handling qualities must include
validation of augmentation devices. FFSs for
highly augmented helicopters will be
validated both in the unaugmented
configuration (or failure state with the
maximum permitted degradation in handling
qualities) and the augmented configuration.
Where various levels of handling qualities
result from failure states, validation of the
effect of the failure is necessary. For those
performance and static handling qualities
tests where the primary concern is control
position in the unaugmented configuration,
unaugmented data are not required if the
design of the system precludes any affect on
control position. In those instances where the
unaugmented helicopter response is
divergent and non-repeatable, it may not be
feasible to meet the specified tolerances.
Alternative requirements for testing will be
mutually agreed upon by the sponsor and the
NSPM on a case-by-case basis.
l. Some tests will not be required for
helicopters using helicopter hardware in the
simulator cockpit (e.g., ‘‘helicopter modular
controller’’). These exceptions are noted in
Table C2A of this attachment. However, in
these cases, the sponsor must provide a
statement that the helicopter hardware meets
the appropriate manufacturer’s specifications
and the sponsor must have supporting
information to that fact available for NSPM
review.
m. For objective test purposes, ‘‘Near
maximum’’ gross weight is a weight chosen
by the sponsor or data provider that is not
less than the basic operating weight (BOW)
of the helicopter being simulated plus 80%
of the difference between the maximum
certificated gross weight (either takeoff
weight or landing weight, as appropriate for
the test) and the BOW. ‘‘Light’’ gross weight
is a weight chosen by the sponsor or data
provider that is not more than 120% of the
BOW of the helicopter being simulated or as
limited by the minimum practical operating
weight of the test helicopter. ‘‘Medium’’ gross
weight is a weight chosen by the sponsor or
data provider that is approximately ±10% of
the average of the numerical values of the
BOW and the maximum certificated gross
weight. (Note: BOW is the empty weight of
the aircraft plus the weight of the following:
normal oil quantity; lavatory servicing fluid;
potable water; required crewmembers and
their baggage; and emergency equipment.
(References: Advisory Circular 120–27,
‘‘Aircraft Weight and Balance;’’ and FAA–H–
8083–1, ‘‘Aircraft Weight and Balance
Handbook.’’).
End QPS Requirements
lllllllllllllllllllll
Begin QPS Requirements
TABLE C2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS
<<>>
<>
Test
Simulator level
Tolerance(s)
No.
Flight condition
Test details
Title
Notes
A
B
C
D
1. Performance
Engine Assessment.
1.a.1 ........
Start Operations..
1.a.1.a .....
Engine start and acceleration (transient).
Light Off Time — ±10% or ±1
sec., Torque — ±5%, Rotor
Speed — ±3%, Fuel Flow —
±10%,
Gas
Generator
Speed — ±5%, Power Turbine Speed — ±5%, Gas
Turbine Temp. — ±30°C.
Ground with the
Rotor Brake Used
and Not Used.
Record each engine
start from the initiation of the start
sequence to
steady state idle
and from steady
state idle to operating RPM.
X
X
X
1.a.1.b .....
Steady State Idle and
Operating RPM conditions.
Torque — ±3%, Rotor Speed
— ±1.5%, Fuel Flow —
±5%, Gas Generator Speed
— ±2%, Power Turbine
Speed — ±2%, Turbine Gas
Temp. — ±20°C.
Ground ....................
Record both steady
state idle and operating RPM conditions..
May be a series of
snapshot tests..
X
X
X
1.a.2 ........
Power Turbine Speed
Trim.
±10% of total change of power
turbine speed.
Ground ....................
Record engine response to trim
system actuation
in both directions.
X
X
X
1.a.3 ........
Engine and Rotor Speed
Governing.
Torque — ±5%, Rotor Speed
— 1.5%.
Climb, descent ........
Record results using
a step input to the
collective. May be
conducted concurrently with climb
and descent performance tests.
X
X
X
1.b ...........
sroberts on PROD1PC70 with RULES
1.a ...........
Surface Operations.
1.b.1 ........
Minimum Radius Turn ...
±3 ft. (0.9m) or 20% of helicopter turn radius.
Ground ....................
If brakes are used,
brake force must
be matched to the
helicopter flight
test value.
X
X
X
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63557
TABLE C2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
<>
Test
Simulator level
Tolerance(s)
No.
Flight condition
Test details
Title
Notes
A
B
C
D
1.b.2 ........
Rate of Turn vs. Pedal
Deflection or
Nosewheel Angle.
±10% or ±2°/sec. Turn Rate ...
Ground Takeoff .......
.................................
X
X
X
1.b.3 ........
Taxi ................................
Pitch Angle — ±1.5°, Torque
— ±3%, Longitudinal Control
Position — ±5%, Lateral
Control Position — ±5%,
Dirrectional Control Position.
Ground ....................
Record results for
control position
and pitch attitude
during ground taxi
for a specific
ground speed,
wind speed and
direction, and
density altitude.
X
X
X
±5%, Collective Control Position — ±5%.
.................................
.................................
X
X
X
±10% of time and distance ......
Ground ....................
.................................
X
X
X
1.b.4 ........
Brake Effectiveness .......
1.c ...........
Takeoff .
1.c.1 ........
All Engines ....................
Airspeed — ±3 kt, Altitude —
±20 ft (6.1m), Torque —
±3%, Rotor Speed —
±1.5%, Vertical Velocity —
±100 fpm (0.50m/sec) or
10%, Pitch Attitude — ±1.5°,
Bank Attitude — ±2°, Heading — ±2°, Longitudinal Control Position — ±10%, Lateral Control Position —
±10%, Directional Control
Position — ±10%, Collective
Control Position — ±10%.
Ground/Takeoff and
Initial Segment of
Climb.
Record results of
takeoff flight path
as appropriate to
helicopter model
simulated (running
takeoff for Level
B, takeoff from a
hover for Level C
and D). For Level
B, the criteria
apply only to
those segments at
airspeeds above
effective
translational lift.
Results must be
recorded from the
initiation of the
takeoff to at least
200 ft (61m) AGL.
X
X
X
1.c.2 ........
One Engine Inoperative
Airspeed — ±3 kt, Altitude —
±20 ft (6.1m), Torque —
±3%, Rotor Speed —
±1.5%, Vertical Velocity —
±100 fpm (0.50m/sec) or
10%, Pitch Attitude — ±1.5°,
Bank Attitude — ±2°, Heading — ±2°, Longitudinal Control Position — ±10%, Lateral Control Position —
±10%, Directional Control
Position — ±10%, Collective
Control Position — ±10%.
Ground/Takeoff; and
Initial Segment of
Climb.
Record takeoff flight
path as appropriate to helicopter
model simulated.
Results must be
recorded from the
initiation of the
takeoff to at least
200 ft (61m) AGL.
X
X
X
1.d ...........
Hover.
Torque — ±3%, Pitch Attitude
— ±1.5°, Bank Attitude —
±1.5°, Longitudinal Control
Position — ±5%, Lateral
Control Position — ±5%, Directional Control Position —
±5%, Collective Control Position — ±5%,.
In Ground Effect
(IGE); and Out of
Ground Effect
(OGE).
Record results for
light and heavy
gross weights.
May be a series
of snapshot tests.
X
X
X
Vertical Velocity — ±100 fpm
(0.50 m/sec) or ±10%, Directional Control Position —
±5%, Collective Control Position — ±5%.
From OGE Hover ....
Record results for
light and heavy
gross weights.
May be a series
of snapshot tests.
X
X
Performance ..................
1.e ...........
Vertical Climb.
sroberts on PROD1PC70 with RULES
Performance ..................
1.f ............
Level Flight.
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TABLE C2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
<>
Test
Simulator level
Tolerance(s)
No.
Test details
Notes
A
B
C
D
Torque — ±3%, Pitch Attitude
— ±1.5°, Sideslip Angle —
±2°, Longitudinal Control Position — ±5%, Lateral Control Position — ±5%, Directional Control Position —
±5%, Collective Control Position — ±5%.
Cruise (Augmentation On and Off).
Record results for
two gross weight
and CG combinations with varying
trim speeds
throughout the airspeed envelope.
May be a series
of snapshot tests.
X
X
X
Vertical Velocity — ±100 fpm
(6.1m/sec) or ±10%, Pitch
Attitude — ±1.5°, Sideslip
Angle — ±2°, Longitudinal
Control Position — ±5%,
Lateral Control Position —
±5%, Directional Control Position — ±5%, Collective
Control Position — ±5%.
Performance and
Trimmed Flight Control Positions.
1.g ...........
Flight condition
Title
All engines operRecord results for
ating; One engine
two gross weight
inoperative; Augand CG combinamentation Systions. The data
tem(s) On and Off.
presented must
be for normal
climb power conditions. May be a
series of snapshot
tests.
X
X
X
Climb.
Performance and
Trimmed Flight Control Positions.
1.h ...........
Descent.
1.h.1 ........
Descent Performance
and Trimmed Flight
Control Positions.
Torque — ±3%, Pitch Attitude
— ±1.5°, Sideslip Angle —
±2°, Longitudinal Control Position — ±5%, Lateral Control Position — ±5%, Directional Control Position —
±5%, Collective Control Position — ±5%.
At or near 1,000 fpm
rate of descent
(RoD) at normal
approach speed.
Augmentation
System(s) On and
Off.
Results must be recorded for two
gross weight and
CG combinations.
May be a series
of snapshot tests.
X
X
X
1.h.2 ........
Autorotation Performance and Trimmed
Flight Control Positions.
Torque — ±3%, Pitch Attitude
— ±1.5°, Sideslip Angle —
±2°, Longitudinal Control Position — ±5%, Lateral Control Position — ±5%, Directional Control Position —
±5%, Collective Control Position — ±5% Vertical Velocity ±100 fpm or 19%, Rotor
Speed ±1.5%.
Steady descents.
Augmentation
System(s) On and
Off.
Record results for
two gross weight
conditions. Data
must be recorded
for normal operating RPM. (Rotor
speed tolerance
applies only if collective control position is full down.)
May be a series
of snapshot tests.
X
X
X
1.i ............
Autorotation.
Rotor Speed—±3% Pitch Attitude ±2°Roll Attitude—±3°
Yaw
Attitude—±5°
Airspeed—±5 kts. Vertical Velocity—±200 fpm (1.00 m/
sec) or 10%.
Cruise or Climb .......
Record results of a
rapid throttle reduction to idle. If
the cruise condition is selected,
comparison must
be made for the
maximum range
airspeed. If the
climb condition is
selected, comparison must be
made for the maximum rate of climb
airspeed at or
near maximum
continuous power.
......
X
X
Entry ..............................
sroberts on PROD1PC70 with RULES
1.j ............
Landing.
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63559
TABLE C2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
<>
Test
Simulator level
Tolerance(s)
Flight condition
No.
1.j.1 .........
All Engines ....................
Airspeed—±3 kts., Altitude—
±20 ft. (6.1m), Torque—
±3%, Rotor Speed—±1.5%,
Pitch Attitude—±1.5°, Bank
Attitude—±1.5°, Heading—
±2°, Longitudinal Control Position—±10%, Lateral Control Position—±10%, Directional Control Position—
±10%, Collective Control Position—±10%.
Approach .................
1.j.2 .........
One Engine Inoperative
Airspeed—±3 kts., Altitude—
±20 ft. (6.1m), Torque—
±3%, Rotor Speed—±1.5%,
Pitch Attitude—±1.5°, Bank
Attitude—±1.5°, Heading—
±2°, Longitudinal Control Position—±10%, Lateral Control Position—±10%, Directional Control Position—
±10%, Collective Control Position—±10%.
1.j.3 .........
Balked Landing ..............
1.j.4 .........
Autorotational Landing ..
Test details
Title
Notes
A
B
C
D
Record results of
the approach and
landing profile as
appropriate to the
helicopter model
simulated (running
landing for Level
B, or approach to
a hover for Level
C and D). For
Level B, the criteria apply only to
those segments at
airspeeds above
effective
translational lift.
X
X
X
Approach .................
Record results for
both Category A
and Category B
approaches and
landing as appropriate to helicopter
model simulated.
For Level B, the
criteria apply only
to those segments
at airspeeds
above effective
translational lift.
X
X
X
Airspeed—±3 kts., Altitude—
±20 ft. (6.1 m), Torque—
±3%, Rotor Speed—±1.5%,
Pitch Attitude—±1.5°, Bank
Attitude—±1.5°, Heading—
±2°, Longitudinal Control Position—±10%, Lateral Control Position—±10%, Directional Control Position—
±10%, Collective Control Position—±10%.
Approach .................
Record the results
for the maneuver
initiated from a
stabilized approach at the
landing decision
point (LDP).
X
X
X
Torque—±3%, Rotor Speed—
±3%, Vertical Velocity—±100
fpm (0.50 m/sec) or 10%,
Pitch Attitude—±2°, Bank Attitude—±2°, Heading—±5°,
Longitudinal Control Position—±10%, Lateral Control
Position—±10%, Directional
Control
Position—±10%,
Collective Control Position—
±10%.
Landing ...................
Record the results
of an
autorotational deceleration and
landing from a
stabilized
autorotational descent, to touch
down.
X
X
2. Handling Qualities.
2.a ...........
Control System Mechanical Characteristic(s).
For simulators requiring Static or Dynamic tests at the controls (i.e., cyclic, collective, and pedal), special
test fixtures will not be required during initial or upgrade evaluations if the sponsor’s QTG/MQTG shows
both test fixture results and the results of an alternative approach, such as computer plots produced
concurrently showing satisfactory agreement. Repeat of the alternative method during the initial or upgrade evaluation would then satisfy this test requirement. For initial and upgrade evaluations, the control
dynamic characteristics must be measured at and recorded directly from the cockpit controls, and must
be accomplished in hover, climb, cruise, and autorotation.
sroberts on PROD1PC70 with RULES
2.a.1 ........
Cyclic .............................
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Breakout—±0.25 lbs. (0.112
daN) or 25%; Force—±1.0
lb. (0.224 daN) or 10%.
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and Off. Friction
Off Augmentation
On and Off.
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Record results for
an uninterrupted
control sweep to
the stops. (This
test does not
apply if aircraft
hardware modular
controllers are
used.).
E:\FR\FM\30OCR2.SGM
Contact the NSPM
for clarification of
any issue regarding helicopters
with reversible
controls.
X
30OCR2
X
X
63560
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TABLE C2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
<>
Test
Simulator level
Tolerance(s)
Flight condition
Collective/Pedals ...........
Breakout—±0.5 lb. (0.224 daN)
or 25%; Force—±1.0 lb.
(0.224 daN) or 10%..
Ground; Static conditions. Trim On
and Off. Friction
Off. Augmentation
On and Off.
2.a.3 ........
Brake Pedal Force vs.
Position.
±5 lbs. (2.224 daN) or 10% .....
2.a.4 ........
Trim System Rate (all
applicable systems).
2.a.5 ........
Test details
Title
2.a.2 ........
Notes
B
C
D
Record results for
an uninterrupted
control sweep to
the stops.
X
X
X
Ground; Static conditions.
.................................
X
X
X
Rate—±10% ............................
Ground; Static conditions. Trim On,
Friction Off.
The tolerance applies to the recorded value of
the trim rate.
X
X
X
Control Dynamics (all
axes).
±10% of time for first zero
crossing and ±10 (N+1)% of
period thereafter, ±10% of
amplitude of first overshoot,
20% of amplitude of 2nd and
subsequent
overshoots
greater than 5% of initial displacement, ±1 overshoot.
Hover/Cruise, Trim
On, Friction Off.
Results must be recorded for a normal control displacement in both
directions in each
axis.
......
X
X
2.a.6 ........
Freeplay .........................
±0.10 in ....................................
Ground; Static conditions.
Record and compare results for all
controls.
X
X
X
2.b ...........
Low Airspeed Handling Qualities.
2.b.1 ........
Trimmed Flight Control
Positions.
Torque—±3% Pitch Attitude—
±1.5° Bank Attitude—±2°
Longitudinal Control Position—±5% Lateral Control
Position—±5%
Directional
Control Position—±5% Collective Control Position—
±5%.
Translational Flight
IGE—Sideward,
rearward, and forward flight. Augmentation On and
Off.
X
Critical Azimuth .............
Torque—±3% Pitch Hover—
Bank Attitude—±2°, Longitudinal Control Position—±5%,
Lateral Control Position—
±5%, Directional Control Position—±5%, Collective Control Position—±5%.
Stationary Hover.
Augmentation On
and Off.
Record results for
several airspeed
increments to the
translational airspeed limits and
for 45 kts. forward
airspeed..
May be a series of
snapshot tests.
Record results for
three relative wind
directions (including the most critical case) in the
critical quadrant.
May be a series
of snapshot tests.
X
2.b.2 ........
X
X
2.b.3 ........
Control Response.
2.b.3.a .....
Longitudinal ...................
Pitch Rate—±10% or ±2% sec.
Pitch Attitude Change—
±10% or 1.5°.
Hover.
Agumentation On
and Off.
Record results for a
step control input.
The Off-axis response must
show correct trend
for unaugmented
cases.
X
X
2.b.3.b .....
sroberts on PROD1PC70 with RULES
No.
Lateral ............................
Roll Rate—±10% or ±2% sec.
Pitch Attitude Change—
±10% or 1.5°.
Hover. Augmentation On and Off.
Record results for a
step control input.
The Off-axis response must
show correct trend
for unaugmented
cases.
X
X
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Typically, control
displacement of
25% to 50% is
necessary for
proper excitation.
Control Dynamics
for irreversible
control systems
may be evaluated
in a ground/static
condition. Additional information
on control dynamics is found later
in this attachment.
‘‘N’’ is the sequential period of a full
cycle of oscillation.
Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
63561
TABLE C2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
<>
Test
Simulator level
Tolerance(s)
Flight condition
Directional ......................
Yaw Rate—±10% or ±2% sec.
Heading Change—±10% or
2°.
Hover. Augmentation On and Off.
2.b.3.d .....
Vertical ...........................
Normal Acceleration—±0.1 g ..
2.c ...........
2.c.1 ........
Longitudinal Handling Qualities.
Control Response .......... Pitch Rate—±10% or ±2°/sec.,
Pitch Attitude Change—
±10% or ±1.5°.
2.c.2 ........
Static Stability ................
2.c.3 ........
Notes
Dynamic Stability.
2.c.3.a .....
Test details
Title
2.b.3.c .....
C
D
Record results for a
step control input.
The Off-axis response must
show correct trend
for unaugmented
cases.
X
X
Hover control input.
The Off-axis response must
show correct trend
for unaugmented
cases.
Record results for a
step.
X
X
Cruise Augmentation On and Off.
Results must be recorded for two
cruise airspeeds
to include minimum power required speed.
Record data for a
step control input.
The Off-axis response must
show correct trend
for unaugmented
cases.
X
X
X
Longitudinal Control Position:
±10% of change from trim or
±0.25 in. (6.3 mm) or Longitudinal Control Force: ±0.5
lb. (0.223 daN) or ±10%.
Cruise or Climb.
Autorotation. Augmentation On and
Off.
Record results for a
minimum of two
speeds on each
side of the trim
speed. May be a
series of snapshot
tests.
X
X
X
Long Term Response ....
±10% of calculated period,
±10% of time to 1⁄2 or double amplitude, or ±0.02 of
damping ratio.
Cruise Augmentation On and Off.
Record results for
three full cycles (6
overshoots after
input completed)
or that sufficient to
determine time to
1⁄2 or double amplitude, whichever
is less. For nonperiod responses,
the time history
must be matched.
X
X
X
2.c.3.b .....
Short Term Response ...
±1.5° Pitch or ±2°/sec. Pitch
Rate. ±0.1 g Normal Acceleration.
Cruise or Climb.
Augmentation On
and Off.
Record results for at
least two airspeeds.
X
X
X
2.c.4 ........
Maneuvering Stability ....
Longitudinal Control Position—
±10% of change from trim or
±0.25 in. (6.3mm) or Longitudinal Control Forces—±0.5
lb. (0.223 daN) or ±10%.
Cruise or Climb.
Augmentation On
and Off.
Record results for at
least two airspeeds. The force
may be shown as
a cross plot for irreversible systems. May be a
series of snapshot
tests.
X
X
X
2.c.5 ........
sroberts on PROD1PC70 with RULES
No.
Landing Gear Operating
Times.
±1 sec ......................................
Takeoff (Retraction)
Approach (Extension).
X
X
xl
2.d ...........
Lateral and Directional Handling Qualities.
2.d.1 ........
Control Response.
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A
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B
30OCR2
Typically, 30°–45°
bank angle is necessary for adequate stability
measurement.
63562
Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
TABLE C2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
<>
Test
Simulator level
Tolerance(s)
Flight condition
Lateral ............................
Roll Rate—±10% or ±3°/sec.,
Roll Attitude Change—±10%
or ±3°.
Cruise Augmentation On and Off.
2.d.1.b .....
Directional ......................
Yaw Rate—±10% or ±2°/sec.,
Yaw
Attitude
Change—
±10% or ±2°.
2.d.2 ........
Directional Static Stability.
Lateral
Control
Position—
±10% of change from trim or
±0.25 in. (6.3mm) or Lateral
Control
Force—±0.5
lb.
(0.223 daN) or 10%, Roll Attitude—±1.5,
Directional
Control Position—±10% of
change from trim or ±0.25
in. (6.3mm) or Directional
Control Force—±1 lb. (0.448
daN) or 10%., Longitudinal
Control Position—±10% of
change from trim or ±0.25
in. (6.3mm), Vertical Velocity—±100 fpm (0.50m/sec)
or 10%.
2.d.3 ........
Lateral-Directional Oscillations.
2.d.3.b .....
Spiral Stability ................
Notes
Dynamic Lateral and Directional Stability.
2.d.3.a .....
Test details
Title
2.d.1.a .....
sroberts on PROD1PC70 with RULES
No.
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A
B
C
D
Record results for
least two airspeeds, including
the speed at or
near the minimum
power required
airspeed. Record
results for a step
control input. The
Off-axis response
must show correct
trend for unaugmented cases.
X
X
X
Cruise Augmentation On and Off.
Record data for at
least two airspeeds, including
the speed at or
near the minimum
power required
airspeed. Record
results for a step
control input. The
Off-axis response
must show correct
trend for unaugmented cases.
X
X
X
Cruise; or Climb
(may use Descent
instead of Climb if
desired), Augmentation On and
Off.
Record results for at
least two sideslip
angles on either
side of the trim
point. The force
may be shown as
a cross plot for irreversible systems. May be a
series of snapshot
tests.
X
X
X
±0.5 sec. or ±10% of period,
±10% of time to 1⁄2 or double amplitude or ±0.02 of
damping ratio, ±20% of ±1
sec. of time difference between peaks of bank and
sideslip.
Cruise or Climb.
Augmentation On/
Off.
Record results for at
least two airspeeds. The test
must be initiated
with a cyclic or a
pedal doublet
input. Record results for six full
cycles (12 overshoots after input
completed) or that
sufficient to determine time to 1⁄2 or
double amplitude,
whichever is less.
For non-periodic
response, the time
history must be
matched.
X
X
X
Correct Trend, ±2° bank or
±10% in 20 sec.
Cruise or Climb.
Augmentation On
and Off.
Record the results
of a release from
pedal only or cyclic only turns.
Results must be
recorded from
turns in both directions.
X
X
X
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This is a steady
heading sideslip
test.
Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
63563
TABLE C2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
<>
Test
Simulator level
Tolerance(s)
No.
2.d.3.c .....
Adverse/Proverse Yaw ..
Flight condition
Test details
Title
Notes
A
Correct Trend, ±2° transient
sideslip angle.
Cruise or Climb.
Augmentation On
and Off.
C
D
X
X
X
X
X
X
Record the time history of initial entry
into cyclic only
turns, using only a
moderate rate for
cyclic input. Results must be recorded for turns in
both directions.
B
X
2. Handling Qualities.
2.a ........... Control System
3. Motion System.
3.a ...........
Motion Envelope.
3.a.1
Pitch.
3.a.1.a .....
Displacement—TBD° .....
..................................................
.................................
.................................
±25° ...............................
..................................................
.................................
.................................
Velocity—TBD°/sec .......
..................................................
.................................
.................................
±20°/sec .........................
..................................................
.................................
.................................
Acceleration—TBD°/sec2
..................................................
.................................
.................................
X
±100°/sec2
.....................
..................................................
.................................
.................................
X
Displacement—TBD° .....
..................................................
.................................
.................................
X
±25° ...............................
..................................................
.................................
.................................
Velocity—TBD°/sec .......
..................................................
.................................
.................................
±20°/sec .........................
..................................................
.................................
.................................
Acceleration—TBD°/sec2
..................................................
.................................
.................................
±100°/sec2
3.a.1.b .....
3.a.1.c .....
3.a.2
3.a.2.a .....
3.a.2.b .....
3.a.2.c .....
......
X
X
X
X
X
X
X
X
X
......
.....................
..................................................
.................................
.................................
X
X
3.a.3 ........
Yaw
3.a.3.a .....
Displacement ¥±25° .....
..................................................
.................................
.................................
X
X
3.a.3.b .....
Velocity—±20°/sec ........
..................................................
.................................
.................................
X
X
3.a.3.c .....
Acceleration—±100°/
sec2.
..................................................
.................................
.................................
X
X
3.a.4 ........
Vertical ...........................
..................................................
.................................
.................................
3.a.4.a .....
Displacement—TBD in ..
..................................................
.................................
.................................
±34 in. ............................
..................................................
.................................
.................................
X
X
Velocity—TBD in ...........
..................................................
.................................
.................................
±24 in .............................
..................................................
.................................
.................................
X
X
3.a.4.c .....
Acceleration—TBD g .....
..................................................
.................................
.................................
±0.8 g ............................
..................................................
.................................
.................................
X
X
3.A.5 ........
Lateral
Displacement: ±45 in .....
..................................................
.................................
.................................
X
X
Velocity: ±28 in/sec .......
..................................................
.................................
.................................
X
X
Acceleration: ±0.6 g ......
..................................................
.................................
.................................
X
X
..................................................
.................................
.................................
X
X
sroberts on PROD1PC70 with RULES
3.a.4.b .....
3.a.6 ........
X
X
X
......
Longitudinal.
Displacement: ±34 in .....
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63564
Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
TABLE C2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
<>
Test
Simulator level
Tolerance(s)
No.
Flight condition
Test details
Title
Notes
A
B
C
D
Velocity: ±28 in/sec .......
.................................
.................................
X
X
Acceleration: ±0.6 g ......
3.a.7 ........
..................................................
..................................................
.................................
.................................
X
X
X
X
Initial Rotational Acceleration Ratio
All axes: TBD°/sec2/sec
.................................
.................................
All axes: 300°/ sec2/sec
3.a.8 ........
..................................................
..................................................
.................................
X
.................................
Initial Linear Acceleration Ratio.
Vertical: ±TBD g/sec .....
.................................
..................................................
.................................
.................................
X
X
Lateral: ±3g/sec .............
..................................................
.................................
.................................
X
X
Longitudinal: ±3g/sec ....
..................................................
.................................
.................................
X
X
Band, Hz Phase, deg. ...
Amplitude, Ratio, db, ...............
.................................
.................................
......
X
X
X
0.10 to 0.5 ¥15 to ¥20
±2 .............................................
±2 .............................................
.................................
.................................
......
0.51 to 1.0 ¥15 to ¥20
3.c ...........
.................................
±6g/sec ..........................
3.b ...........
..................................................
±4, ............................................
±4 .............................................
.................................
.................................
......
1.5° ..........................................
.................................
The phase shift between a datum
jack and any other
jack must be
measured using a
heave (vertical)
signal of 0.5 Hz.
at ±0.25 g.
......
X
X
X
0.05 g ......................................
.................................
The motion base
must be driven
sinusoidally in
heave through a
displacement of 6
inches (150mm)
peak to peak at a
frequency of 0.5
Hz. Deviation from
the desired sinusoidal acceleration
must be measured.
X
X
X
Frequency Response
Leg Balance.
Leg Balance ..................
3.d ...........
Turn Around.
Turn Around ..................
4 ..............
Visual System Display Tests.
4.a ...........
sroberts on PROD1PC70 with RULES
X
Field of View.
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63565
TABLE C2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
<>
Test
Simulator level
Tolerance(s)
No.
Flight condition
Test details
Title
Notes
A
B
C
D
Continuous collimated
visual field of view.
Minimum
continuous
collimated field of view providing 75° horizontal and 30°
vertical field of view for each
pilot simultaneously.
N/A ..........................
An SOC is required.
Horizontal field of
view is centered
on the zero degree azimuth line
relative to the aircraft fuselage.
4.a.2 ........
Continuous collimated
visual field of view.
Minimum
continuous
collimated field of view providing 150° horizontal and
40° vertical field of view for
each pilot simultaneously.
N/A/ .........................
An SOC is required.
Horizontal field of
view is centered
on the zero degree azimuth line
relative to the aircraft fuselage.
4.a.3 ........
Continuous collimated
visual field of view.
Minimum
continuous
collimated field of view providing 180° horizontal and
60° vertical field of view for
each pilot simultaneously.
N/A ..........................
An SOC is required.
Horizontal field of
view is centered
on the zero degree azimuth line
relative to the aircraft fuselage.
X
Field of view may be
measured using a
visual test pattern
filling the entire
visual scene (all
channels) with a
matrix of black
and white 5°
squares. The installed alignment
should be addressed in the
SOC.
4.c ...........
sroberts on PROD1PC70 with RULES
4.a.1 ........
Surface contrast ratio ....
Not less than 5:1 .....................
N/A ..........................
The ratio is calculated by dividing
the brightness
level of the center,
bright square (providing at least 2
foot-lamberts or 7
cd/ms2) by the
brightness level of
any adjacent dark
square.
X
Measurements may
be made using a
1° spot photometer and a raster
drawn test pattern
filling the entire
visual scene (all
channels) with a
test pattern of
black and white
squares, 5 per
square, with a
white square in
the center of each
channel. During
contrast ratio testing, simulator aftcab and flight
deck ambient light
levels should be
zero.
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X
A vertical field of
view of 30° may
be insufficient to
meet visual
ground segment
requirements.
Field of view may
be measured
using a visual test
pattern filling the
entire visual
scene (all channels) with a matrix
of black and white
5° squares. The
installed alignment
should be addressed in the
SOC.
X
30OCR2
Field of view may be
measured using a
visual test pattern
filling the entire
visual scene (all
channels) with a
matrix of black
and white 5°
squares. The installed alignment
should be addressed in the
SOC.
63566
Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
TABLE C2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
<>
Test
Simulator level
Tolerance(s)
Flight condition
Test details
Notes
No.
Title
A
4.d ...........
Highlight brightness .......
Not less than six (6) foot-lamberts (20 cd/m 2).
N/A ..........................
Measure the brightness of the center, white square
while superimposing a highlight on that white
square. The use
of calligraphic capabilities to enhance the raster
brightness is acceptable; however, measuring
light points is not
acceptable.
4.e ...........
Vernier resolution (surface resolution).
Not greater than 3 arc minutes
N/A ..........................
An SOC is required
and must include
the appropriate
calculations and
an explanation of
those calculations.
X
X
4.f ............
Light point size ..............
Not greater than six (6) arcminutes..
N/A ..........................
An SOC is required
and must include
the relevant calculations and an
explanation of
those calculations.
X
X
Light point size may
be measured
using a test pattern consisting of
a centrally located
single row of light
points reduced in
length until modulation is just discernible in each
visual channel. A
row of 48 lights
will form a 4°
angle or less.
4.g ...........
Light point contrast ratio
Not less than 25:1 ...................
N/A ..........................
An SOC is required
and must include
the relevant calculations..
X
X
A 1° spot photometer may be used
to measure a
square of at least
1° filled with light
points (where light
point modulation
is just discernible)
and compare the
results to the
measured adjacent background.
During contrast
ratio testing, simulator aft-cab and
flight deck ambient light levels
should be zero.
lllllllllllllllllllll
Begin Information
sroberts on PROD1PC70 with RULES
2. Control Dynamics.
a. General. The characteristics of a
helicopter flight control system have a major
effect on the handling qualities. A significant
consideration in pilot acceptability of a
helicopter is the ‘‘feel’’ provided through the
flight controls. Considerable effort is
expended on helicopter feel system design so
that pilots will be comfortable and will
consider the helicopter desirable to fly. In
order for a FFS to be representative, it should
‘‘feel’’ like the helicopter being simulated.
Compliance with this requirement is
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determined by comparing a recording of the
control feel dynamics of the FFS to actual
helicopter measurements in the takeoff,
cruise and landing configurations.
b. Recordings such as free response to an
impulse or step function are classically used
to estimate the dynamic properties of
electromechanical systems. In any case, it is
only possible to estimate the dynamic
properties as a result of only being able to
estimate true inputs and responses.
Therefore, it is imperative that the best
possible data be collected since close
matching of the FFS control loading system
to the helicopter system is essential. The
required dynamic control tests are described
in Table C2A of this attachment.
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B
C
D
X
Measurements may
be made using a
1° spot photometer and a raster
drawn test pattern
filling the entire
visual scene (all
channels) with a
test pattern of
black and white
squares, 5 per
square, with a
white square in
the center of each
channel.
c. For initial and upgrade evaluations, the
QPS requires that control dynamics
characteristics be measured and recorded
directly from the flight controls (Handling
Qualities—Table C2A). This procedure is
usually accomplished by measuring the free
response of the controls using a step or
impulse input to excite the system. The
procedure should be accomplished in the
takeoff, cruise and landing flight conditions
and configurations.
d. For helicopters with irreversible control
systems, measurements may be obtained on
the ground if proper pitot-static inputs are
provided to represent airspeeds typical of
those encountered in flight. Likewise, it may
be shown that for some helicopters, hover,
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
sroberts on PROD1PC70 with RULES
climb, cruise, and autorotation have like
effects. Thus, one may suffice for another. If
either or both considerations apply,
engineering validation or helicopter
manufacturer rationale should be submitted
as justification for ground tests or for
eliminating a configuration. For FFSs
requiring static and dynamic tests at the
controls, special test fixtures will not be
required during initial and upgrade
evaluations if the QTG shows both test
fixture results and the results of an alternate
approach (e.g., computer plots that were
produced concurrently and show satisfactory
agreement). Repeat of the alternate method
during the initial evaluation would satisfy
this test requirement.
(1) Control Dynamics Evaluations. The
dynamic properties of control systems are
often stated in terms of frequency, damping,
and a number of other classical
measurements. In order to establish a
consistent means of validating test results for
FFS control loading, criteria are needed that
will clearly define the measurement
interpretation and the applied tolerances.
Criteria are needed for underdamped,
critically damped and overdamped systems.
In the case of an underdamped system with
very light damping, the system may be
quantified in terms of frequency and
damping. In critically damped or
overdamped systems, the frequency and
damping are not readily measured from a
response time history. Therefore, the
following suggested measurements may be
used:
(2) For Levels C and D simulators. Tests to
verify that control feel dynamics represent
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the helicopter should show that the dynamic
damping cycles (free response of the
controls) match those of the helicopter
within specified tolerances. The NSPM
recognizes that several different testing
methods may be used to verify the control
feel dynamic response. The NSPM will
consider the merits of testing methods based
on reliability and consistency. One
acceptable method of evaluating the response
and the tolerance to be applied is described
below for the underdamped and critically
damped cases. A sponsor using this method
to comply with the QPS requirements should
perform the tests as follows:
e. Tolerances.
(1) Underdamped Response.
(a) Two measurements are required for the
period, the time to first zero crossing (in case
a rate limit is present) and the subsequent
frequency of oscillation. It is necessary to
measure cycles on an individual basis in case
there are non-uniform periods in the
response. Each period will be independently
compared to the respective period of the
helicopter control system and, consequently,
will enjoy the full tolerance specified for that
period.
(b) The damping tolerance will be applied
to overshoots on an individual basis. Care
should be taken when applying the tolerance
to small overshoots since the significance of
such overshoots becomes questionable. Only
those overshoots larger than 5 percent of the
total initial displacement should be
considered significant. The residual band,
labeled T(Ad) on Figure C2A is ±5 percent of
the initial displacement amplitude Ad from
the steady state value of the oscillation. Only
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63567
oscillations outside the residual band are
considered significant. When comparing FFS
data to helicopter data, the process should
begin by overlaying or aligning the FFS and
airplane steady state values and then
comparing amplitudes of oscillation peaks,
the time of the first zero crossing, and
individual periods of oscillation. The FFS
should show the same number of significant
overshoots to within one when compared
against the helicopter airplane data. The
procedure for evaluating the response is
illustrated in Figure C2A.
(2) Critically damped and Overdamped
Response. overdamped response. Due to the
nature of critically damped and overdamped
responses (no overshoots), the time to reach
90 percent of the steady state (neutral point)
value should be the same as the helicopter
within ±10 percent. The simulator response
must be critically damped also. Figure C2B
illustrates the procedure.
(3) The following summarizes the
tolerances:
T(P0) ±10% of P0
T(P1) ±20% of P1
T(A) ±10% of A1, ±20% of Subsequent Peaks
T(Ad) ±10% of Ad = Residual Band
Overshoots ±1
(4) In the event the number of cycles
completed outside of the residual band, and
thereby significant, exceeds the number
depicted in figure 1 of this attachment, the
following tolerances (T) will apply:
T(Pn) ±10%(n+1)% of Pn, where ‘‘n’’ is the
next in sequence.
BILLING CODE 491073–P
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
3. Motion Cue Repeatability Testing.
a. The motion system characteristics in the
Table C2A address basic system capability,
but not pilot cueing capability. Motion
systems will continue to be ‘‘tuned’’
subjectively until there is an objective
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procedure for determining the motion cues
necessary to support pilot tasks and stimulate
the pilot response that occurs in a helicopter
for the same tasks. When a motion system is
tuned, it is important to test the system to
ensure that it continues to perform as
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originally qualified. Any motion performance
change from the initially qualified baseline
can be measured objectively.
b. Motion performance change should be
assessed at least annually. An assessment
may be conducted as follows:
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
sroberts on PROD1PC70 with RULES
(1) Compare the current performance of the
motion system to the initial recorded test
data.
(2) Record the parameters of the motion
drive algorithms and the jack position
transducers.
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(3) Insert the test input signals at an
appropriate point prior to the integrations in
the equations of motion (see Figure C2C of
this attachment).
(4) Adjust the characteristics of the test
signal (see Figure C2D of this attachment) to
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63569
ensure that the motion is exercised properly.
Motion system manufactures suggest a range
of approximately 2⁄3 of the maximum
displacement capability in each axis with a
time segment (T0–T1) of sufficient duration to
ensure steady initial conditions.
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
BILLING CODE 491073–C
Attachment 3 to Appendix C to Part 60—
Simulator Subjective Evaluation
1. Discussion
lllllllllllllllllllll
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Begin Information
a. The subjective tests provide a basis for
evaluating the capability of the simulator to
perform over a typical utilization period;
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
determining that the simulator competently
simulates each required maneuver,
procedure, or task; and verifying correct
operation of the simulator controls,
instruments, and systems. The items listed in
the following Tables are for simulator
evaluation purposes only. They must not be
used to limit or exceed the authorizations for
use of a given level of simulator as described
on the Statement of Qualification or as may
be approved by the TPAA. All items in the
following paragraphs are subject to an
examination.
b. The tests in Table A3A, Operations
Tasks, in this attachment address pilot
functions, including maneuvers and
procedures (called flight tasks), and is
divided by flight phases. The performance of
these tasks by the NSPM includes an
operational examination of the visual system
and special effects. There are flight tasks
included to address some features of
advanced technology helicopters and
innovative training programs.
c. The tests in Table A3A, Operations
Tasks, and Table A3G, Instructor Operating
Station, in this attachment addresses the
overall function and control of the simulator
including the various simulated
environmental conditions; simulated
helicopter system operation (normal,
abnormal, and emergency); visual system
displays; and special effects necessary to
meet flight crew training, evaluation, or flight
experience requirements.
d. All simulated helicopter systems
functions will be assessed for normal and,
where appropriate, alternate operations.
Normal, abnormal, and emergency operations
associated with a flight phase will be
assessed during the evaluation of flight tasks
or events within that flight phase. Simulated
helicopter systems are listed separately under
‘‘Any Flight Phase’’ to ensure appropriate
attention to systems checks. Operational
navigation systems (including inertial
navigation systems, global positioning
systems, or other long-range systems) and the
associated electronic display systems will be
evaluated if installed. The NSP pilot will
include in his report to the TPAA, the effect
of the system operation and any system
limitation.
e. Simulators demonstrating a satisfactory
circling approach will be qualified for the
circling approach maneuver and may be
approved for such use by the TPAA in the
sponsor’s FAA-approved flight training
program. To be considered satisfactory, the
circling approach will be flown at maximum
gross weight for landing, with minimum
visibility for the helicopter approach
category, and must allow proper alignment
with a landing runway at least 90° different
from the instrument approach course while
allowing the pilot to keep an identifiable
portion of the airport in sight throughout the
maneuver (reference—14 CFR 91.175(e)).
f. At the request of the TPAA, the NSP
Pilot may assess the simulator for a special
aspect of a sponsor’s training program during
the functions and subjective portion of an
evaluation. Such an assessment may include
a portion of a Line Oriented Flight Training
(LOFT) scenario or special emphasis items in
the sponsor’s training program. Unless
directly related to a requirement for the
qualification level, the results of such an
evaluation would not affect the qualification
of the simulator.
g. The NSPM acknowledges that there are
previously qualified simulators with certain,
early generation Computer Generated Image
(CGI) visual systems, that are limited by
either the capability of the Imgage Generator
or the display system used. As a result, the
NSPM has agreed to discuss the specific
circumstances that may be determined to
exist and has agreed to reach a mutually
acceptable course of action to address these
limitations beyond those that are listed in the
QPS requirements of this table. The following
are examples:
(1) Early CGI visual systems that are
exempt from the necessity of including
runway numbers as a part of the specific
runway marking requirements are:
(a) Link NVS and DNVS.
(b) Novoview 2500 and 6000.
(c) FlightSafety VITAL series up to, and
including, VITAL III, but not beyond.
(d) Redifusion SP1, SP1T, and SP2.
(2) Early CGI visual systems that are
exempt from the necessity of including
runway numbers except for those runways
used for LOFT training sessions. These LOFT
airport models require runway numbers but
only for the specific runway end (one
direction) used in the LOFT session. The
systems required to display runway numbers
only for LOFT scenes are:
(a) FlightSafety VITAL IV.
(b) Redifusion SP3 and SP3T.
(c) Link-Miles Image II.
(3) Previously qualified CGI and/or display
systems that are incapable of generating blue
lights, and therefore will not be required to
have accurate taxi-way edge lighting are:
(a) Redifusion SP1 and SP1T.
(b) FlightSafety Vital IV.
(c) Link-Miles Image II and Image IIT
(d) XKD displays (even though the XKD
image generator is capable of generating blue
colored lights, the display cannot
accommodate that color).
End Information
lllllllllllllllllllll
TABLE C3A.—FUNCTIONS AND SUBJECTIVE TESTS
<<< QPS requirements >>>
Simulator level
No.
Operations tasks
A
B
C
D
Tasks in this table are subject to evaluation if appropriate for the helicopter simulated as indicated in the SOQ Configuration List and/or the
level of simulator qualification involved. Items not installed or not functional on the simulator and, therefore, not appearing on the SOQ Configuration List, are not required to be listed as exceptions on the SOQ.
1. Preparation For Flight
1.a ..........................
Cockpit check: switches, indicators, systems, and equipment ...................................................................
X
X
X
2. APU/Engine start and run-up
Normal start procedures ..............................................................................................................................
X
X
X
2.b ..........................
Alternate start procedures ...........................................................................................................................
X
X
X
2.c ..........................
Abnormal starts and shutdowns (e.g., hot start, hung start) .......................................................................
X
X
X
2.d ..........................
sroberts on PROD1PC70 with RULES
2.a ..........................
Rotor engagement .......................................................................................................................................
X
X
X
2.e ..........................
System checks .............................................................................................................................................
X
X
X
3. (Reserved)
4. (Reserved)
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TABLE C3A.—FUNCTIONS AND SUBJECTIVE TESTS—Continued
<<< QPS requirements >>>
Simulator level
No.
Operations tasks
A
B
C
D
5. (Reserved)
6. Take-off
6.a ..........................
Normal .........................................................................................................................................................
X
X
X
6.a.1 .......................
From ground ............................................................................................................................................
X
X
X
6.a.2 .......................
From hover ...............................................................................................................................................
X
X
X
6.a.2.a ....................
Cat A ....................................................................................................................................................
X
X
X
6.a.2.b ....................
Cat B ....................................................................................................................................................
X
X
X
6.a.3 .......................
Running ....................................................................................................................................................
X
X
X
6.a.4 .......................
Crosswind/tailwind ...................................................................................................................................
X
X
X
6.a.5 .......................
Maximum performance ............................................................................................................................
X
X
X
6.a.6 .......................
Instrument ................................................................................................................................................
X
X
X
6.a.7 .......................
(Reserved).
6.a.8 .......................
(Reserved).
6.a.9 .......................
(Reserved).
6.a.10 .....................
(Reserved).
6.b ..........................
Abnormal/emergency procedures ................................................................................................................
X
X
X
6.b.1 .......................
Takeoff with engine failure after critical decision point (CDP) ................................................................
X
X
X
6.b.1.a ....................
Cat A ....................................................................................................................................................
X
X
X
6.b.1.b ....................
Cat B ....................................................................................................................................................
X
X
X
X
X
X
6.c ..........................
(Reserved).
7. Climb
7.a ..........................
Normal .........................................................................................................................................................
7.b ..........................
(Reserved).
7.c ..........................
(Reserved).
7.d ..........................
One engine inoperative ...............................................................................................................................
X
X
X
8.a ..........................
Performance ................................................................................................................................................
X
X
X
8.b ..........................
Flying qualities .............................................................................................................................................
X
X
X
8.c ..........................
Turns ............................................................................................................................................................
X
X
X
8.c.1 .......................
Timed .......................................................................................................................................................
X
X
X
8.c.2 .......................
Normal ......................................................................................................................................................
X
X
X
8.c.3 .......................
Steep ........................................................................................................................................................
X
X
X
8.d ..........................
Accelerations and decelerations ..................................................................................................................
X
X
X
8.e ..........................
High speed vibrations ..................................................................................................................................
X
X
X
8.f ...........................
(Reserved).
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TABLE C3A.—FUNCTIONS AND SUBJECTIVE TESTS—Continued
<<< QPS requirements >>>
Simulator level
No.
Operations tasks
A
B
C
D
8.g ..........................
Abnormal/emergency procedures ................................................................................................................
X
X
X
8.g.1 .......................
Engine fire ................................................................................................................................................
X
X
X
8.g.2 .......................
Engine failure ...........................................................................................................................................
X
X
X
8.g.3 .......................
Inflight engine shutdown and restart ........................................................................................................
X
X
X
8.g.4 .......................
Fuel governing system failures ................................................................................................................
X
X
X
8.g.5 .......................
Directional control malfunction .................................................................................................................
X
X
X
8.g.6 .......................
Hydraulic failure .......................................................................................................................................
X
X
X
8.g.7 .......................
Stability system failure .............................................................................................................................
X
X
X
8.g.8 .......................
Rotor vibrations ........................................................................................................................................
X
X
X
9.a ..........................
Normal .........................................................................................................................................................
X
X
X
9.b ..........................
Maximum rate ..............................................................................................................................................
X
X
X
9.c ..........................
(Reserved).
9. Descent
10. Approach
Non-precision ...............................................................................................................................................
X
X
X
10.a.1 .....................
All engines operating ...............................................................................................................................
X
X
X
10.a.2 .....................
One or more engines inoperative ............................................................................................................
X
X
X
10.a.3 .....................
Approach procedures ...............................................................................................................................
X
X
X
10.a.3.a ..................
NDB ......................................................................................................................................................
X
X
X
10.a.3.b ..................
VOR, RNAV, TACAN ...........................................................................................................................
X
X
X
10.a.3.c ..................
ASR ......................................................................................................................................................
X
X
X
10.a.3.d ..................
(Reserved).
10.a.3.e ..................
Helicopter only ......................................................................................................................................
X
X
X
10.a.4 .....................
Missed approach ......................................................................................................................................
X
X
X
10.a.4.a ..................
All engines operating ............................................................................................................................
X
X
X
10.a.4.b ..................
One or more engines inoperative .........................................................................................................
X
X
X
10.b ........................
Precision ......................................................................................................................................................
X
X
X
10.b.1 .....................
All engines operating ...............................................................................................................................
X
X
X
10.b.2 .....................
One or more engines inoperative ............................................................................................................
X
X
X
10.b.3 .....................
Approach procedures ...............................................................................................................................
X
X
X
10.b.3.a ..................
PAR ......................................................................................................................................................
X
X
X
10.b.3.b ..................
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10.a ........................
MLS ......................................................................................................................................................
X
X
X
10.b.3.c ..................
ILS ........................................................................................................................................................
X
X
X
10.b.3.c ..................
(1) Manual (raw data) .......................................................................................................................
X
X
X
10.b.3.c ..................
(2) Flight director only .......................................................................................................................
X
X
X
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TABLE C3A.—FUNCTIONS AND SUBJECTIVE TESTS—Continued
<<< QPS requirements >>>
Simulator level
No.
Operations tasks
A
B
C
D
10.b.3.c ..................
(3) Autopilot coupled .........................................................................................................................
X
X
X
10.b.3.c ..................
—Cat I ...........................................................................................................................................
X
X
X
10.b.3.c ..................
—Cat II ..........................................................................................................................................
X
X
X
10.b.4 .....................
Missed approach.
10.b.4.a ..................
All engines operating ............................................................................................................................
X
X
X
10.b.4.b ..................
One or more engines inoperative .........................................................................................................
X
X
X
10.b.4.c ..................
Stability system failure .............................................................................................................................
X
X
X
10.c ........................
(Reserved).
11. (Reserved)
12. Any Flight Phase
12.a ........................
Helicopter and powerplant systems operation.
12.a.1 .....................
Air conditioning ........................................................................................................................................
X
X
X
12.a.2 .....................
Anti-icing/deicing ......................................................................................................................................
X
X
X
12.a.3 .....................
Auxiliary power-plant ................................................................................................................................
X
X
X
12.a.4 .....................
Communications .......................................................................................................................................
X
X
X
12.a.5 .....................
Electrical ...................................................................................................................................................
X
X
X
12.a.6 .....................
Fire detection and suppression ................................................................................................................
X
X
X
12.a.7 .....................
Stabilizer ..................................................................................................................................................
X
X
X
12.a.8 .....................
Flight controls ...........................................................................................................................................
X
X
X
12.a.9 .....................
Fuel and oil ..............................................................................................................................................
X
X
X
12.a.10 ...................
Hydraulic ..................................................................................................................................................
X
X
X
12.a.11 ...................
Landing gear ............................................................................................................................................
X
X
X
12.a.12 ...................
Oxygen .....................................................................................................................................................
X
X
X
12.a.13 ...................
Pneumatic ................................................................................................................................................
X
X
X
12.a.14 ...................
Powerplant ...............................................................................................................................................
X
X
X
12.a.15 ...................
Flight control computers ...........................................................................................................................
X
X
X
12.a.16 ...................
Stability and control augmentation ...........................................................................................................
X
X
X
12.b ........................
Flight management and guidance system.
Airborne radar ..........................................................................................................................................
X
X
X
12.b.2 .....................
Automatic landing aids .............................................................................................................................
X
X
X
12.b.3 .....................
Autopilot ...................................................................................................................................................
X
X
X
12.b.4 .....................
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12.b.1 .....................
Collision avoidance system ......................................................................................................................
X
X
X
12.b.5 .....................
Flight data displays ..................................................................................................................................
X
X
X
12.b.6 .....................
Flight management computers ................................................................................................................
X
X
X
12.b.7 .....................
Heads-up displays ...................................................................................................................................
X
X
X
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TABLE C3A.—FUNCTIONS AND SUBJECTIVE TESTS—Continued
<<< QPS requirements >>>
Simulator level
No.
Operations tasks
A
12.b.8 .....................
12.c ........................
C
D
X
Navigation systems ..................................................................................................................................
B
X
X
Airborne procedures.
12.c.1 .....................
Holding .....................................................................................................................................................
X
X
X
12.c.2 .....................
Air hazard avoidance ...............................................................................................................................
X
X
X
12.c.3 .....................
Retreating blade stall recovery ................................................................................................................
X
X
X
12.c.4 .....................
Mast bumping ..........................................................................................................................................
X
X
X
13. Engine Shutdown and Parking
13.a ........................
Engine and systems operation ....................................................................................................................
X
X
X
13.b ........................
Parking brake operation ..............................................................................................................................
X
X
X
13.c ........................
Rotor brake operation ..................................................................................................................................
X
X
X
13.d ........................
Abnormal/emergency procedures ................................................................................................................
X
X
X
Table C3B [Reserved]
Table C3C [Reserved]
TABLE C3D.—FUNCTIONS AND SUBJECTIVE TESTS
<<< QPS requirements >>>
Simulator level
Number
Instructor Operating Station (IOS) (As appropriate)
A
B
C
D
Functions in this table are subject to evaluation only if appropriate for the helicopter and/or the system is installed on the specific simulator.
1. Simulator
Power
Switch(es)
.................................................................................................................................................................
X
X
X
2. Helicopter conditions
2.a ..........................
2.b ..........................
2.c. .........................
Gross weight, center of gravity, fuel loading and allocation ....................................................................
Helicopter systems status ........................................................................................................................
Ground crew functions .............................................................................................................................
....
....
....
X
X
X
X
X
X
X
X
X
Number and selection ..............................................................................................................................
Runway or landing area selection ...........................................................................................................
Landing surface conditions (rough, smooth, icy, wet, dry, snow) ...........................................................
Preset positions ........................................................................................................................................
Lighting controls .......................................................................................................................................
....
....
....
....
....
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
....
....
....
....
X
X
X
....
X
X
X
....
X
X
X
3. Airports/Heliports
3.a
3.b
3.c
3.d
3.e
..........................
..........................
..........................
..........................
..........................
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4. Environmental controls
4.a ..........................
4.b ..........................
4.c ..........................
4.d ..........................
4.e ..........................
4.f ...........................
VerDate Aug<31>2005
(Reserved).
(Reserved).
Temperature .............................................................................................................................................
Climate conditions ....................................................................................................................................
Wind speed and direction ........................................................................................................................
(Reserved) ...............................................................................................................................................
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TABLE C3D.—FUNCTIONS AND SUBJECTIVE TESTS—Continued
<<< QPS requirements >>>
Simulator level
Number
Instructor Operating Station (IOS) (As appropriate)
A
B
C
X
X
X
Problem (all) freeze/release .....................................................................................................................
Position (geographic) freeze/release .......................................................................................................
Repositioning (locations, freezes, and releases) .....................................................................................
Ground speed control ..............................................................................................................................
....
....
....
....
X
X
X
X
X
X
X
X
7. Remote IOS.
......................................................................................................................................................................
X
X
X
8. Sound Controls.
On/off/adjustment
......................................................................................................................................................................
X
X
X
5. Helicopter system malfunctions (Insertion/
deletion)
......................................................................................................................................................................
D
6. Locks, Freezes, and Repositioning
6.a
6.b
6.c
6.d
..........................
..........................
..........................
..........................
X
X
X
X
9. Motion/Control Loading System
9.a ..........................
On/off/emergency stop .............................................................................................................................
....
X
X
10. Observer
Seats/Stations.
Position/Adjustment/Positive
restraint system
......................................................................................................................................................................
X
X
X
Attachment 4 to Appendix C to Part 60—
Sample Documents
sroberts on PROD1PC70 with RULES
Table of Contents
Title of Sample
Figure C4A—Sample Letter, Request for
Initial, Upgrade, or Reinstatement
Evaluation
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Figure C4B—Attachment: FSTD Information
Form
Figure C4C—Sample Qualification Test
Guide Cover Page
Figure C4D—Sample Statement of
Qualification—Certificate
Figure C4E—Sample Statement of
Qualification—Configuration List
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Figure C4F—Sample Statement of
Qualification—List of Qualified Tasks
Figure C4G—Sample Continuing
Qualification Evaluation Requirements
Page
Figure C4H—Sample MQTG Index of
Effective FSTD Directives
BILLING CODE 491073–P
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BILLING CODE 491073–C
Appendix D to Part 60—Qualification
Performance Standards for Helicopter
Flight Training Devices
lllllllllllllllllllll
sroberts on PROD1PC70 with RULES
Begin Information
This appendix establishes the standards for
Helicopter Flight Training Device (FTD)
evaluation and qualification at Level 4, Level
5, or Level 6. The Flight Standards Service,
National Simulator Program Manager
(NSPM), is responsible for the development,
application, and implementation of the
standards contained within this appendix.
The procedures and criteria specified in this
appendix will be used by the NSPM, or a
person or persons assigned by the NSPM
when conducting helicopter FTD
evaluations.
Table of Contents
1. Introduction.
2. Applicability (§ 60.1) and Applicability of
sponsor rules to persons who are not
sponsors and who are engaged in certain
unauthorized activities (§ 60.2).
3. Definitions (60.3).
4. Qualification Performance Standards
(§ 60.4).
5. Quality Management System (§ 60.5).
6. Sponsor Qualification Requirements
(§ 60.7).
7. Additional Responsibilities of the Sponsor
(§ 60.9).
8. FTD Use (§ 60.11).
9. FTD Objective Data Requirements
(§ 60.13).
10. Special Equipment and Personnel
Requirements for Qualification of the
FTD (§ 60.14).
11. Initial (and Upgrade) Qualification
Requirements (§ 60.15).
12. Additional Qualifications for Currently
Qualified FTDs (§ 60.16).
13. Previously Qualified FTDs (§ 60.17).
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14. Inspection, Continuing Qualification
Evaluation, and Maintenance
Requirements (§ 60.19).
15. Logging FTD Discrepancies (§ 60.20).
16. Interim Qualification of FTDs for New
Helicopter Types or Models (§ 60.21).
17. Modifications to FTDs (§ 60.23).
18. Operations with Missing, Malfunctioning,
or Inoperative Components (§ 60.25).
19. Automatic Loss of Qualification and
Procedures for Restoration of
Qualification (§ 60.27).
20. Other Losses of Qualification and
Procedures for Restoration of
Qualification (§ 60.29).
21. Record Keeping and Reporting (§ 60.31).
22. Applications, Logbooks, Reports, and
Records: Fraud, Falsification, or
Incorrect Statements (§ 60.33).
23. [Reserved]
24. Levels of FTD.
25. FSTD Qualification on the Basis of a
Bilateral Aviation Safety Agreement
(BASA) (§ 60.37).
Attachment 1 to Appendix D to Part 60—
General FTD Requirements.
Attachment 2 to Appendix D to Part 60—
Flight Training Device (FTD) Objective
Tests.
Attachment 3 to Appendix D to Part 60—
Flight Training Device (FTD) Subjective
Evaluation.
Attachment 4 to Appendix D to Part 60—
Sample Documents.
End Information
lllllllllllllllllllll
1. Introduction
lllllllllllllllllllll
Begin Information
a. This appendix contains background
information as well as regulatory and
informative material as described later in this
section. To assist the reader in determining
what areas are required and what areas are
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permissive, the text in this appendix is
divided into two sections: ‘‘QPS
Requirements’’ and ‘‘Information.’’ The QPS
Requirements sections contain details
regarding compliance with the part 60 rule
language. These details are regulatory, but are
found only in this appendix. The Information
sections contain material that is advisory in
nature, and designed to give the user general
information about the regulation.
b. Related Reading References.
(1) 14 CFR part 60
(2) 14 CFR part 61.
(3) 14 CFR part 63.
(4) 14 CFR part 119.
(5) 14 CFR part 121.
(6) 14 CFR part 125
(7) 14 CFR part 135.
(8) 14 CFR part 141
(9) 14 CFR part 142
(10) Advisory Circular (AC) 120–28C,
Criteria for Approval of Category III Landing
Weather Minima.
(11) AC 120–29, Criteria for Approving
Category I and Category II Landing Minima
for part 121 operators.
(12) AC 120–35B, Line Operational
Simulations: Line-Oriented Flight Training,
Special Purpose Operational Training, Line
Operational Evaluation.
(13) AC 120–41, Criteria for Operational
Approval of Airborne Wind Shear Alerting
and Flight Guidance Systems.
(14) AC 120–57A, Surface Movement
Guidance and Control System (SMGS).
(15) AC 150/5300–13, Airport Design.
(16) AC 150/5340–1G, Standards for
Airport Markings.
(17) AC 150/5340–4C, Installation Details
for Runway Centerline Touchdown Zone
Lighting Systems.
(18) AC 150/5390—2B, Heliport Design.
(19) AC 150/5340–19, Taxiway Centerline
Lighting System.
(20) AC 150/5340–24, Runway and
Taxiway Edge Lighting System.
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(21) AC 150/5345–28D, Precision
Approach Path Indicator (PAPI) Systems.
(22) International Air Transport
Association document, ‘‘Flight Simulator
Design and Performance Data Requirements,’’
as amended.
(23) AC 29–2B, Flight Test Guide for
Certification of Transport Category
Rotorcraft.
(24) AC 27–1A, Flight Test Guide for
Certification of Normal Category Rotorcraft.
(25) International Civil Aviation
Organization (ICAO) Manual of Criteria for
the Qualification of Flight Simulators, as
amended.
(26) Airplane Flight Simulator Evaluation
Handbook, Volume I, as amended and
Volume II, as amended, The Royal
Aeronautical Society, London, UK.
(27) FAA Publication FAA–S–8081 series
(Practical Test Standards for Airline
Transport Pilot Certificate, Type Ratings,
Commercial Pilot, and Instrument Ratings).
(28) The FAA Aeronautical Information
Manual (AIM). An electronic version of the
AIM is on the internet at https://www.faa.gov/
atpubs.
End Information
lllllllllllllllllllll
2. Applicability (§§ 60.1 & 60.2)
There is no additional regulatory or
informational material that applies to § 60.1,
Applicability, or to § 60.2, Applicability of
sponsor rules to person who are not sponsors
and who are engaged in certain unauthorized
activities.
3. Definitions (§ 60.3)
lllllllllllllllllllll
Begin Information
See appendix F for a list of definitions and
abbreviations from part 1, part 60, and the
QPS appendices of part 60.
End Information
lllllllllllllllllllll
4. Qualification Performance Standards
(§ 60.4)
There is no additional regulatory or
informational material that applies to § 60.4,
Qualification Performance Standards.
5. Quality Management System (§ 60.5)
lllllllllllllllllllll
Begin Information
Additional regulatory material and
informational material regarding Quality
Management Systems for FTDs may be found
in appendix E of this part.
End Information
lllllllllllllllllllll
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6. Sponsor Qualification Requirements
(§ 60.7)
lllllllllllllllllllll
Begin Information
a. The intent of the language in § 60.7(b) is
to have a specific FTD, identified by the
sponsor, used at least once in an FAAapproved flight training program for the
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helicopter simulated during the 12-month
period described. The identification of the
specific FTD may change from one 12-month
period to the next 12-month period as long
as that sponsor sponsors and uses at least one
FTD at least once during the prescribed
period. There is no minimum number of
hours or minimum FTD periods required.
b. The following examples describe
acceptable operational practices:
(1) Example One.
(a) A sponsor is sponsoring a single,
specific FTD for its own use, in its own
facility or elsewhere —this single FTD forms
the basis for the sponsorship. The sponsor
uses that FTD at least once in each 12-month
period in that sponsor’s FAA-approved flight
training program for the helicopter
simulated. This 12-month period is
established according to the following
schedule:
(i) If the FTD was qualified prior to October
30, 2007 the 12-month period begins on the
date of the first continuing qualification
evaluation conducted in accordance with
§ 60.19 after October 30, 2007 and continues
for each subsequent 12-month period;
(ii) A device qualified on or after October
30, 2007 will be required to undergo an
initial or upgrade evaluation in accordance
with § 60.15. Once the initial or upgrade
evaluation is complete, the first continuing
qualification evaluation will be conducted
within 6 months. The 12 month continuing
qualification evaluation cycle begins on that
date and continues for each subsequent 12month period.
(b) There is no minimum number of hours
of FTD use required.
(c) The identification of the specific FTD
may change from one 12-month period to the
next 12-month period as long as that sponsor
sponsors and uses at least one FTD at least
once during the prescribed period.
(2) Example Two.
(a) A sponsor sponsors an additional
number of FTDs, in its facility or elsewhere.
Each additionally sponsored FTD must be—
(i) Used by the sponsor in the sponsor’s
FAA-approved flight training program for the
helicopter simulated (as described in
§ 60.7(d)(1));
OR
(ii) Used by another FAA certificate holder
in that other certificate holder’s FAAapproved flight training program for the
helicopter simulated (as described in
§ 60.7(d)(1)). This 12-month period is
established in the same manner as in
example one.
OR
(iii) Provided a statement each year from a
qualified pilot, (after having flown the
helicopter not the subject FTD or another
FTD, during the preceding 12-month period)
stating that the subject FTD’s performance
and handling qualities represent the
helicopter (as described in § 60.7(d)(2)). This
statement is provided at least once in each
12-month period established in the same
manner as in example one.
(b) There is no minimum number of hours
of FTD use required.
(3) Example Three.
(a) A sponsor in New York (in this
example, a Part 142 certificate holder)
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63589
establishes ‘‘satellite’’ training centers in
Chicago and Moscow.
(b) The satellite function means that the
Chicago and Moscow centers must operate
under the New York center’s certificate (in
accordance with all of the New York center’s
practices, procedures, and policies; e.g.,
instructor and/or technician training/
checking requirements, record keeping, QMS
program).
(c) All of the FTDs in the Chicago and
Moscow centers could be dry-leased (i.e., the
certificate holder does not have and use
FAA-approved flight training programs for
the FTDs in the Chicago and Moscow
centers) because—
(i) Each FTD in the Chicago center and
each FTD in the Moscow center is used at
least once each 12-month period by another
FAA certificate holder in that other
certificate holder’s FAA-approved flight
training program for the helicopter (as
described in § 60.7(d)(1));
OR
(ii) A statement is obtained from a
qualified pilot (having flown the helicopter,
not the subject FTD or another FTD during
the preceding 12-month period) stating that
the performance and handling qualities of
each FTD in the Chicago and Moscow centers
represents the helicopter (as described in
§ 60.7(d)(2)).
End Information
lllllllllllllllllllll
7. Additional Responsibilities of the Sponsor
(§ 60.9)
lllllllllllllllllllll
Begin Information
The phrase ‘‘as soon as practicable’’ in
§ 60.9(a) means without unnecessarily
disrupting or delaying beyond a reasonable
time the training, evaluation, or experience
being conducted in the FSTD.
End Information
lllllllllllllllllllll
8. FTD Use (§ 60.11)
There is no additional regulatory or
informational material that applies to § 60.11,
FTD Use.
9. FTD Objective Data Requirements
(§ 60.13)
lllllllllllllllllllll
Begin QPS Requirements
a. Flight test data used to validate FTD
performance and handling qualities must
have been gathered in accordance with a
flight test program containing the following:
(1) A flight test plan consisting of:
(a) The maneuvers and procedures
required for aircraft certification and
simulation programming and validation.
(b) For each maneuver or procedure—
(i) The procedures and control input the
flight test pilot and/or engineer used.
(ii) The atmospheric and environmental
conditions.
(iii) The initial flight conditions.
(iv) The helicopter configuration, including
weight and center of gravity.
(v) The data to be gathered.
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(vi) All other information necessary to
recreate the flight test conditions in the FTD.
(2) Appropriately qualified flight test
personnel.
(3) An understanding of the accuracy of the
data to be gathered using appropriate
alternative data sources, procedures, and
instrumentation that is traceable to a
recognized standard as described in
Attachment 2, Table D2F.
(4) Appropriate and sufficient data
acquisition equipment or system(s),
including appropriate data reduction and
analysis methods and techniques, as would
be acceptable to the FAA’s Aircraft
Certification Service.
b. The data, regardless of source, must be
presented:
(1) In a format that supports the FTD
validation process;
(2) In a manner that is clearly readable and
annotated correctly and completely;
(3) With resolution sufficient to determine
compliance with the tolerances set forth in
Attachment 2, Table D2A appendix.
(4) With any necessary guidance
information provided; and
(5) Without alteration, adjustments, or bias;
however the data may be re-scaled, digitized,
or otherwise manipulated to fit the desired
presentation.
c. After completion of any additional flight
test, a flight test report must be submitted in
support of the validation data. The report
must contain sufficient data and rationale to
support qualification of the FTD at the level
requested.
d. As required by § 60.13(f), the sponsor
must notify the NSPM when it becomes
aware that an addition to or a revision of the
flight related data or helicopter systems
related data is available if this data is used
to program and operate a qualified FTD. The
data referred to in this sub-section are those
data that are used to validate the
performance, handling qualities, or other
characteristics of the aircraft, including data
related to any relevant changes occurring
after the type certification is issued. This
notification must be made within 10 working
days.
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End QPS Requirements
lllllllllllllllllllll
Begin Information
e. The FTD sponsor is encouraged to
maintain a liaison with the manufacturer of
the aircraft being simulated (or with the
holder of the aircraft type certificate for the
aircraft being simulated if the manufacturer
is no longer in business), and if appropriate,
with the person having supplied the aircraft
data package for the FTD in order to facilitate
the notification described in this paragraph.
f. It is the intent of the NSPM that for new
aircraft entering service, at a point well in
advance of preparation of the Qualification
Test Guide (QTG), the sponsor should submit
to the NSPM for approval, a descriptive
document (a validation data roadmap)
containing the plan for acquiring the
validation data, including data sources. This
document should clearly identify sources of
data for all required tests, a description of the
validity of these data for a specific engine
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type and thrust rating configuration, and the
revision levels of all avionics affecting the
performance or flying qualities of the aircraft.
Additionally, this document should provide
other information such as the rationale or
explanation for cases where data or data
parameters are missing, instances where
engineering simulation data are used, or
where flight test methods require further
explanations. It should also provide a brief
narrative describing the cause and effect of
any deviation from data requirements. The
aircraft manufacturer may provide this
document.
g. There is no requirement for any flight
test data supplier to submit a flight test plan
or program prior to gathering flight test data.
However, the NSPM notes that inexperienced
data gatherers often provide data that is
irrelevant, improperly marked, lacking
adequate justification for selection. Other
problems include inadequate information
regarding initial conditions or test
maneuvers. The NSPM has been forced to
refuse these data submissions as validation
data for an FTD evaluation. It is for this
reason that the NSPM recommends that any
data supplier not previously experienced in
this area review the data necessary for
programming and for validating the
performance of the FTD and discuss the
flight test plan anticipated for acquiring such
data with the NSPM well in advance of
commencing the flight tests.
h. In those cases where the objective test
results authorize a ‘‘snapshot test’’ or a
‘‘series of snapshot tests’’ results in lieu of a
time-history result, Attachment 2 requires the
sponsor or other data provider to ensure that
a steady state condition exists at the instant
of time captured by the ‘‘snapshot.’’ This is
often verified by showing that a steady state
condition existed from some period of time
during which the snap shot is taken. The
time period most frequently used is 5
seconds prior through 2 seconds following
the instant of time captured by the snap shot.
This paragraph is primarily addressing the
source data and the method by which the
data provider ensures that the steady state
condition for the snap shot is representative.
i. The NSPM will consider, on a case-bycase basis, whether or not to approve
supplemental validation data derived from
flight data recording systems such as a Quick
Access Recorder or Flight Data Recorder.
End Information
10. Special Equipment and Personnel
Requirements for Qualification of the FTD
(§ 60.14)
Begin Information
a. In the event that the NSPM determines
that special equipment or specifically
qualified persons will be required to conduct
an evaluation, the NSPM will make every
attempt to notify the sponsor at least one (1)
week, but in no case less than 72 hours, in
advance of the evaluation. Examples of
special equipment include flight control
measurement devices, accelerometers, or
oscilloscopes. Examples of specially
qualified personnel include individuals
specifically qualified to install or use any
special equipment when its use is required.
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b. Examples of a special evaluation include
an evaluation conducted after an FTD is
moved; at the request of the TPAA; or as a
result of comments received from FTD users
that raise questions regarding the continued
qualification or use of the FTD.
End Information
11. Initial (and Upgrade) Qualification
Requirements (§ 60.15)
Begin QPS Requirement
a. In order to be qualified at a particular
qualification level, the FTD must:
(1) Meet the general requirements listed in
Attachment 1;
(2) Meet the objective testing requirements
listed in Attachment 2 (Level 4 FTDs do not
require objective tests); and
(3) Satisfactorily accomplish the subjective
tests listed in Attachment 3.
b. The request described in § 60.15(a) must
include all of the following:
(1) A statement that the FTD meets all of
the applicable provisions of this part and all
applicable provisions of the QPS.
(2) A confirmation that the sponsor will
forward to the NSPM the statement described
in § 60.15(b) in such time as to be received
no later than 5 business days prior to the
scheduled evaluation and may be forwarded
to the NSPM via traditional or electronic
means.
(3) Except for a Level 4 FTD, a qualification
test guide (QTG), acceptable to the NSPM,
that includes all of the following:
(a) Objective data obtained from aircraft
testing or another approved source.
(b) Correlating objective test results
obtained from the performance of the FTD as
prescribed in the applicable QPS.
(c) The result of FTD subjective tests
prescribed in the applicable QPS.
(d) A description of the equipment
necessary to perform the evaluation for initial
qualification and the continuing qualification
evaluations.
c. The QTG described in paragraph a(3) of
this section, must provide the documented
proof of compliance with the FTD objective
tests in Attachment 2,Table D2A of this
appendix.
d. The QTG is prepared and submitted by
the sponsor, or the sponsor’s agent on behalf
of the sponsor, to the NSPM for review and
approval, and must include, for each
objective test:
(1) Parameters, tolerances, and flight
conditions;
(2) Pertinent and complete instructions for
conducting automatic and manual tests;
(3) A means of comparing the FTD test
results to the objective data;
(4) Any other information as necessary to
assist in the evaluation of the test results;
(5) Other information appropriate to the
qualification level of the FTD.
e. The QTG described in paragraphs (a)(3)
and (b) of this section, must include the
following:
(1) A QTG cover page with sponsor and
FAA approval signature blocks (see
Attachment 4, Figure D4C, for a sample QTG
cover page).
(2) A continuing qualification evaluation
requirements page. This page will be used by
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the NSPM to establish and record the
frequency with which continuing
qualification evaluations must be conducted
and any subsequent changes that may be
determined by the NSPM in accordance with
§ 60.19. See Attachment 4, Figure D4G, for a
sample Continuing Qualification Evaluation
Requirements page.
(3) An FTD information page that provides
the information listed in this paragraph, if
applicable (see Attachment 4, Figure D4B, for
a sample FTD information page). For
convertible FTDs, the sponsor must submit a
separate page for each configuration of the
FTD.
(a) The sponsor’s FTD identification
number or code.
(b) The helicopter model and series being
simulated.
(c) The aerodynamic data revision number
or reference.
(d) The engine model(s) and its data
revision number or reference.
(e) The flight control data revision number
or reference.
(f) The flight management system
identification and revision level.
(g) The FTD model and manufacturer.
(h) The date of FTD manufacture.
(i) The FTD computer identification.
(j) The visual system model and
manufacturer, including display type.
(k) The motion system type and
manufacturer, including degrees of freedom.
(4) A Table of Contents.
(5) A log of revisions and a list of effective
pages.
(6) List of all relevant data references.
(7) A glossary of terms and symbols used
(including sign conventions and units).
(8) Statements of compliance and
capability (SOCs) with certain requirements.
SOCs must provide references to the sources
of information that show the capability of the
FTD to comply with the requirement, a
rationale explaining how the referenced
material is used, mathematical equations and
parameter values used, and the conclusions
reached; i.e., that the FTD complies with the
requirement. Refer to the ‘‘General FTD
Requirements’’ column, Table D1A, in
Attachment 1, or in the ‘‘Alternative Data
Sources, Procedures, and Instrumentation’’
column, Table D2F, in Attachment 2, to see
when SOCs are required.
(9) Recording procedures or equipment
required to accomplish the objective tests.
(10) The following information for each
objective test designated in Attachment 2, as
applicable to the qualification level sought:
(a) Name of the test.
(b) Objective of the test.
(c) Initial conditions.
(d) Manual test procedures.
(e) Automatic test procedures (if
applicable).
(f) Method for evaluating FTD objective test
results.
(g) List of all relevant parameters driven or
constrained during the automatic test(s).
(h) List of all relevant parameters driven or
constrained during the manual test(s).
(i) Tolerances for relevant parameters.
(j) Source of Validation Data (document
and page number).
(k) Copy of the Validation Data (if located
in a separate binder, a cross reference for the
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identification and page number for pertinent
data location must be provided).
(l) FTD Objective Test Results as obtained
by the sponsor. Each test result must reflect
the date completed and must be clearly
labeled as a product of the device being
tested.
f. A convertible FTD is addressed as a
separate FTD for each model and series
helicopter to which it will be converted and
for the FAA qualification level sought. The
NSPM will conduct an evaluation for each
configuration. If a sponsor seeks qualification
for two or more models of a helicopter type
using a convertible FTD, the sponsor must
provide a QTG for each helicopter model, or
a supplemented QTG for each helicopter
model. The NSPM will conduct evaluations
for each helicopter model.
g. The form and manner of presentation of
objective test results in the QTG must
include the following:
(1) The sponsor’s FTD test results must be
recorded in a manner acceptable to the
NSPM, that allows easy comparison of the
FTD test results to the validation data (e.g.,
use of a multi-channel recorder, line printer,
cross plotting, overlays, transparencies).
(2) FTD results must be labeled using
terminology common to helicopter
parameters as opposed to computer software
identifications.
(3) Validation data documents included in
a QTG may be photographically reduced only
if such reduction will not alter the graphic
scaling or cause difficulties in scale
interpretation or resolution.
(4) Scaling on graphical presentations must
provide the resolution necessary to evaluate
the parameters shown in Attachment 2, Table
D2A of this appendix.
(5) Tests involving time histories, data
sheets (or transparencies thereof) and FTD
test results must be clearly marked with
appropriate reference points to ensure an
accurate comparison between FTD and
helicopter with respect to time. Time
histories recorded via a line printer are to be
clearly identified for cross-plotting on the
helicopter data. Over-plots must not obscure
the reference data.
h. The sponsor may elect to complete the
QTG objective and subjective tests at the
manufacturer’s facility or at the sponsor’s
training facility. If the tests are conducted at
the manufacturer’s facility, the sponsor must
repeat at least one-third of the tests at the
sponsor’s training facility in order to
substantiate FTD performance. The QTG
must be clearly annotated to indicate when
and where each test was accomplished. Tests
conducted at the manufacturer’s facility and
at the sponsor’s training facility must be
conducted after the FTD is assembled with
systems and sub-systems functional and
operating in an interactive manner. The test
results must be submitted to the NSPM.
i. The sponsor must maintain a copy of the
MQTG at the FTD location.
j. All FTDs for which the initial
qualification is conducted after October 30,
2013 must have an electronic MQTG
(eMQTG) including all objective data
obtained from helicopter testing, or another
approved source (reformatted or digitized),
together with correlating objective test results
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obtained from the performance of the FTD
(reformatted or digitized) as prescribed in
this appendix. The eMQTG must also contain
the general FTD performance or
demonstration results (reformatted or
digitized) prescribed in this appendix, and a
description of the equipment necessary to
perform the initial qualification evaluation
and the continuing qualification evaluations.
The eMQTG must include the original
validation data used to validate FTD
performance and handling qualities in either
the original digitized format from the data
supplier or an electronic scan of the original
time-history plots that were provided by the
data supplier. A copy of the eMQTG must be
provided to the NSPM.
k. All other FTDs (not covered in
subparagraph ‘‘j’’) must have an electronic
copy of the MQTG by and after October 30,
2013. A copy of the eMQTG must be
provided to the NSPM. This may be provided
by an electronic scan presented in a Portable
Document File (PDF), or similar format
acceptable to the NSPM.
End QPS Requirements
lllllllllllllllllllll
Begin Information
l. Only those FTDs that are sponsored by
a certificate holder as defined in appendix F
will be evaluated by the NSPM. However,
other FTD evaluations may be conducted on
a case-by-case basis as the Administrator
deems appropriate, but only in accordance
with applicable agreements.
m. The NSPM will conduct an evaluation
for each configuration, and each FTD must be
evaluated as completely as possible. To
ensure a thorough and uniform evaluation,
each FTD is subjected to the general FTD
requirements in Attachment 1, the objective
tests listed in Attachment 2, and the
subjective tests listed in Attachment 3 of this
appendix. The evaluations described herein
will include, but not necessarily be limited
to the following:
(1) Helicopter responses, including
longitudinal and lateral-directional control
responses (see Attachment 2 of this
appendix);
(2) Performance in authorized portions of
the simulated helicopter’s operating
envelope, to include tasks evaluated by the
NSPM in the areas of surface operations,
takeoff, climb, cruise, descent, approach and
landing, as well as abnormal and emergency
operations (see Attachment 2 of this
appendix);
(3) Control checks (see Attachment 1 and
Attachment 2 of this appendix);
(4) Cockpit configuration (see Attachment
1 of this appendix);
(5) Pilot, flight engineer, and instructor
station functions checks (see Attachment 1
and Attachment 3 of this appendix);
(6) Helicopter systems and sub-systems (as
appropriate) as compared to the helicopter
simulated (see attachment 1 and attachment
3 of this appendix);
(7) FTD systems and sub-systems,
including force cueing (motion), visual, and
aural (sound) systems, as appropriate (see
Attachment 1 and Attachment 2 of this
appendix); and
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(8) Certain additional requirements,
depending upon the qualification level
sought, including equipment or
circumstances that may become hazardous to
the occupants. The sponsor may be subject to
Occupational Safety and Health
Administration requirements.
n. The NSPM administers the objective and
subjective tests, which includes an
examination of functions. The tests include
a qualitative assessment of the FTD by an
NSP pilot. The NSP evaluation team leader
may assign other qualified personnel to assist
in accomplishing the functions examination
and/or the objective and subjective tests
performed during an evaluation when
required.
(1) Objective tests provide a basis for
measuring and evaluating FTD performance
and determining compliance with the
requirements of this part.
(2) Subjective tests provide a basis for:
(a) Evaluating the capability of the FTD to
perform over a typical utilization period;
(b) Determining that the FTD satisfactorily
simulates each required task;
(c) Verifying correct operation of the FTD
controls, instruments, and systems; and
(d) Demonstrating compliance with the
requirements of this part.
o. The tolerances for the test parameters
listed in Attachment 2 of this appendix
reflect the range of tolerances acceptable to
the NSPM for FTD validation and are not to
be confused with design tolerances specified
for FTD manufacture. In making decisions
regarding tests and test results, the NSPM
relies on the use of operational and
engineering judgment in the application of
data (including consideration of the way in
which the flight test was flown and way the
data was gathered and applied) data
presentations, and the applicable tolerances
for each test.
p. In addition to the scheduled continuing
qualification evaluation, each FTD is subject
to evaluations conducted by the NSPM at any
time without prior notification to the
sponsor. Such evaluations would be
accomplished in a normal manner (i.e.,
requiring exclusive use of the FTD for the
conduct of objective and subjective tests and
an examination of functions) if the FTD is not
being used for flight crewmember training,
testing, or checking. However, if the FTD
were being used, the evaluation would be
conducted in a non-exclusive manner. This
non-exclusive evaluation will be conducted
by the FTD evaluator accompanying the
check airman, instructor, Aircrew Program
Designee (APD), or FAA inspector aboard the
FTD along with the student(s) and observing
the operation of the FTD during the training,
testing, or checking activities.
q. Problems with objective test results are
handled as follows:
(1) If a problem with an objective test result
is detected by the NSP evaluation team
during an evaluation, the test may be
repeated or the QTG may be amended.
(2) If it is determined that the results of an
objective test do not support the qualification
level requested but do support a lower level,
the NSPM may qualify the FTD at a lower
level.
r. After an FTD is successfully evaluated,
the NSPM issues a statement of qualification
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(SOQ) to the sponsor, The NSPM
recommends the FTD to the TPAA, who will
approve the FTD for use in a flight training
program. The SOQ will be issued at the
satisfactory conclusion of the initial or
continuing qualification. However, it is the
sponsor’s responsibility to obtain TPAA
approval prior to using the FTD in an FAAapproved flight training program.
s. Under normal circumstances, the NSPM
establishes a date for the initial or upgrade
evaluation within ten (10) working days after
determining that a complete QTG is
acceptable. Unusual circumstances may
warrant establishing an evaluation date
before this determination is made. A sponsor
may schedule an evaluation date as early as
6 months in advance. However, there may be
a delay of 45 days or more in rescheduling
and completing the evaluation if the sponsor
is unable to meet the scheduled date. See
Attachment 4, Figure D4A, Sample Request
for Initial, Upgrade, or Reinstatement
Evaluation.
t. The numbering system used for objective
test results in the QTG should closely follow
the numbering system set out in Attachment
2, FTD Objective Tests, Table D2A.
u. Contact the NSPM or visit the NSPM
Web site for additional information regarding
the preferred qualifications of pilots used to
meet the requirements of § 60.15(d).
v. Examples of the exclusions for which
the FTD might not have been subjectively
tested by the sponsor or the NSPM and for
which qualification might not be sought or
granted, as described in § 60.15(g)(6), include
approaches to and departures from slopes
and pinnacles.
End Information
lllllllllllllllllllll
12. Additional Qualifications for Currently
Qualified FTDs (§ 60.16)
There is no additional regulatory or
informational material that applies to § 60.16,
Additional Qualifications for a Currently
Qualified FTD.
13. Previously Qualified FTDs (§ 60.17)
lllllllllllllllllllll
Begin QPS Requirements
a. In instances where a sponsor plans to
remove an FTD from active status for a
period of less than two years, the following
procedures apply:
(1) The NSPM must be notified in writing
and the notification must include an estimate
of the period that the FTD will be inactive;
(2) Continuing Qualification evaluations
will not be scheduled during the inactive
period;
(3) The NSPM will remove the FTD from
the list of qualified FSTDs on a mutually
established date not later than the date on
which the first missed continuing
qualification evaluation would have been
scheduled;
(4) Before the FTD is restored to qualified
status, it must be evaluated by the NSPM.
The evaluation content and the time required
to accomplish the evaluation is based on the
number of continuing qualification
evaluations and sponsor-conducted quarterly
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inspections missed during the period of
inactivity.
(5) The sponsor must notify the NSPM of
any changes to the original scheduled time
out of service;
b. FTDs qualified prior to October 30, 2007,
are not required to meet the general FTD
requirements, the objective test requirements,
and the subjective test requirements of
Attachments 1, 2, and 3, respectively, of this
appendix.
c. [Reserved]
End QPS Requirements
lllllllllllllllllllll
Begin Information
d. Other certificate holders or persons
desiring to use an FTD may contract with
FTD sponsors to use FTDs previously
qualified at a particular level for a helicopter
type and approved for use within an FAAapproved flight training program. Such FTDs
are not required to undergo an additional
qualification process, except as described in
§ 60.16.
e. Each FTD user must obtain approval
from the appropriate TPAA to use any FTD
in an FAA-approved flight training program.
f. The intent of the requirement listed in
§ 60.17(b), for each FTD to have a Statement
of Qualification within 6 years, is to have the
availability of that statement (including the
configuration list and the limitations to
authorizations) to provide a complete picture
of the FTD inventory regulated by the FAA.
The issuance of the statement will not
require any additional evaluation or require
any adjustment to the evaluation basis for the
FTD.
g. Downgrading of an FTD is a permanent
change in qualification level and will
necessitate the issuance of a revised
Statement of Qualification to reflect the
revised qualification level, as appropriate. If
a temporary restriction is placed on an FTD
because of a missing, malfunctioning, or
inoperative component or on-going repairs,
the restriction is not a permanent change in
qualification level. Instead, the restriction is
temporary and is removed when the reason
for the restriction has been resolved.
h. It is not the intent of the NSPM to
discourage the improvement of existing
simulation (e.g., the ‘‘updating’’ of a control
loading system, or the replacement of the IOS
with a more capable unit) by requiring the
‘‘updated’’ device to meet the qualification
standards current at the time of the update.
Depending on the extent of the update, the
NSPM may require that the updated device
be evaluated and may require that an
evaluation include all or a portion of the
elements of an initial evaluation. However,
the standards against which the device
would be evaluated are those that are found
in the MQTG for that device.
i. The NSPM will determine the evaluation
criteria for an FTD that has been removed
from active status for a prolonged period. The
criteria will be based on the number of
continuing qualification evaluations and
quarterly inspections missed during the
period of inactivity. For example, if the FTD
were out of service for a 1 year period, it
would be necessary to complete the entire
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QTG, since all of the quarterly evaluations
would have been missed. The NSPM will
also consider how the FTD was stored,
whether parts were removed from the FTD
and whether the FTD was disassembled.
j. The FTD will normally be requalified
using the FAA-approved MQTG and the
criteria that was in effect prior to its removal
from qualification. However, inactive periods
of 2 years or more will require requalification under the standards in effect
and current at the time of requalification.
End Information
14. Inspection, Continuing Qualification
Evaluation, and Maintenance Requirements
(§ 60.19).
Begin QPS Requirement
a. The sponsor must conduct a minimum
of four evenly spaced inspections throughout
the year. The objective test sequence and
content of each inspection in this sequence
must be developed by the sponsor and must
be acceptable to the NSPM.
b. The description of the functional
preflight inspection must be contained in the
sponsor’s QMS.
c. Record ‘‘functional preflight’’ in the FTD
discrepancy log book or other acceptable
location, including any item found to be
missing, malfunctioning, or inoperative.
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End QPS Requirements
lllllllllllllllllllll
Begin Information
d. The sponsor’s test sequence and the
content of each quarterly inspection required
in § 60.19(a)(1) should include a balance and
a mix from the objective test requirement
areas listed as follows:
(1) Performance.
(2) Handling qualities.
(3) Motion system (where appropriate).
(4) Visual system (where appropriate).
(5) Sound system (where appropriate).
(6) Other FTD systems.
e. If the NSP evaluator plans to accomplish
specific tests during a normal continuing
qualification evaluation that requires the use
of special equipment or technicians, the
sponsor will be notified as far in advance of
the evaluation as practical; but not less than
72 hours. Examples of such tests include
latencies and control sweeps.
f. The continuing qualification evaluations
described in § 60.19(b) will normally require
4 hours of FTD time. However, flexibility is
necessary to address abnormal situations or
situations involving aircraft with additional
levels of complexity (e.g., computer
controlled aircraft). The sponsor should
anticipate that some tests may require
additional time. The continuing qualification
evaluations will consist of the following:
(1) Review of the results of the quarterly
inspections conducted by the sponsor since
the last scheduled continuing qualification
evaluation.
(2) A selection of approximately 8 to 15
objective tests from the MQTG that provide
an adequate opportunity to evaluate the
performance of the FTD. The tests chosen
will be performed either automatically or
manually and should be able to be conducted
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within approximately one-third (1⁄3) of the
allotted FTD time.
(3) A subjective evaluation of the FTD to
perform a representative sampling of the
tasks set out in attachment 3 of this
appendix. This portion of the evaluation
should take approximately two-thirds (2⁄3) of
the allotted FTD time.
(4) An examination of the functions of the
FTD may include the motion system, visual
system, sound system as applicable,
instructor operating station, and the normal
functions and simulated malfunctions of the
simulated helicopter systems. This
examination is normally accomplished
simultaneously with the subjective
evaluation requirements.
g. The requirement established in
§ 60.19(b)(4) regarding the frequency of
NSPM-conducted continuing qualification
evaluations for each FTD is typically 12
months. However, the establishment and
satisfactory implementation of an approved
QMS for a sponsor will provide a basis for
adjusting the frequency of evaluations to
exceed 12-month intervals.
End Information
lllllllllllllllllllll
15. Logging FTD Discrepancies (§ 60.20).
There is no additional regulatory or
informational material that applies to § 60.20.
Logging FTD Discrepancies.
16. Interim Qualification of FTDs for New
Helicopter Types or Models (§ 60.21).
There is no additional regulatory or
informational material that applies to § 60.21,
Interim Qualification of FTDs for New
Helicopter Types or Models.
17. Modifications to FTDs (§ 60.23).
lllllllllllllllllllll
Begin QPS Requirements
a. The notification described in
§ 60.23(c)(2) must include a complete
description of the planned modification, with
a description of the operational and
engineering effect the proposed modification
will have on the operation of the FTD and
the results that are expected with the
modification incorporated.
b. Prior to using the modified FTD:
(1) All the applicable objective tests
completed with the modification
incorporated, including any necessary
updates to the MQTG (e.g., accomplishment
of FSTD Directives) must be acceptable to the
NSPM; and
(2) The sponsor must provide the NSPM
with a statement signed by the MR that the
factors listed in § 60.15(b) are addressed by
the appropriate personnel as described in
that section.
End QPS Requirements
lllllllllllllllllllll
Begin Information
c. FSTD Directives are considered
modification of an FTD. See Attachment 4,
Figure D4H for a sample index of effective
FSTD Directives.
End Information
lllllllllllllllllllll
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18. Operation With Missing, Malfunctioning,
or Inoperative Components (§ 60.25).
lllllllllllllllllllll
Begin Information
a. The sponsor’s responsibility with respect
to § 60.25(a) is satisfied when the sponsor
fairly and accurately advises the user of the
current status of an FTD, including any
missing, malfunctioning, or inoperative
(MMI) component(s).
b. If the 29th or 30th day of the 30-day
period described in § 60.25(b) is on a
Saturday, a Sunday, or a holiday, the FAA
will extend the deadline until the next
business day.
c. In accordance with the authorization
described in § 60.25(b), the sponsor may
develop a discrepancy prioritizing system to
accomplish repairs based on the level of
impact on the capability of the FTD. Repairs
having a larger impact on the FTD’s ability
to provide the required training, evaluation,
or flight experience will have a higher
priority for repair or replacement.
End Information
lllllllllllllllllllll
19. Automatic Loss of Qualification and
Procedures for Restoration of Qualification
(§ 60.27).
lllllllllllllllllllll
Begin Information
If the sponsor provides a plan for how the
FTD will be maintained during its out-ofservice period (e.g., periodic exercise of
mechanical, hydraulic, and electrical
systems; routine replacement of hydraulic
fluid; control of the environmental factors in
which the FTD is to be maintained.) there is
a greater likelihood that the NSPM will be
able to determine the amount of testing that
is required for requalification.
End Information
lllllllllllllllllllll
20. Other Losses of Qualification and
Procedures for Restoration of Qualification
(§ 60.29).
lllllllllllllllllllll
Begin Information
If the sponsor provides a plan for how the
FTD will be maintained during its out-ofservice period (e.g., periodic exercise of
mechanical, hydraulic, and electrical
systems; routine replacement of hydraulic
fluid; control of the environmental factors in
which the FTD is to be maintained.) there is
a greater likelihood that the NSPM will be
able to determine the amount of testing that
is required for requalification.
lllllllllllllllllllll
End Information
21. Recordkeeping and Reporting (§ 60.31).
lllllllllllllllllllll
Begin QPS Requirements
a. FTD modifications can include hardware
or software changes. For FTD modifications
involving software programming changes, the
record required by § 60.31(a)(2) must consist
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of the name of the aircraft system software,
aerodynamic model, or engine model change,
the date of the change, a summary of the
change, and the reason for the change.
b. If a coded form for record keeping is
used, it must provide for the preservation
and retrieval of information with appropriate
security or controls to prevent the
inappropriate alteration of such records after
the fact.
End QPS Requirements
lllllllllllllllllllll
22. Applications, Logbooks, Reports, and
Records: Fraud, Falsification, or Incorrect
Statements (§ 60.33).
There are no additional QPS requirements
or informational material that apply to
§ 60.33, Applications, Logbooks, Reports, and
Records: Fraud, Falsification, or Incorrect
Statements.
23. [Reserved].
24. Levels of FTD.
lllllllllllllllllllll
Begin Information
a. The following is a general description of
each level of FTD. Detailed standards and
tests for the various levels of FTDs are fully
defined in Attachments 1 through 3 of this
appendix.
(1) Level 4. A device that may have an open
helicopter-specific flight deck area, or an
enclosed helicopter-specific cockpit and at
least one operating system with air/ground
logic (no aerodynamic programming
required).
(2) Level 5. A device that may have an open
helicopter-specific flight deck area, or an
enclosed helicopter-specific cockpit and a
generic aerodynamic program with at least
one operating system and control loading
that is representative of the simulated
helicopter only at an approach speed and
configuration.
(3) Level 6. A device that has an enclosed
helicopter-specific cockpit and aerodynamic
program with all applicable helicopter
systems operating and control loading that is
representative of the simulated helicopter
throughout its ground and flight envelope
and significant sound representation.
how the requirement was met. The
requirements for SOCs and tests are indicated
in the ‘‘General FTD Requirements’’ column
in Table D1A of this appendix.
b. Table D1A describes the requirements
for the indicated level of FTD. Many devices
include operational systems or functions that
exceed the requirements outlined in this
section. In any event, all systems will be
tested and evaluated in accordance with this
appendix to ensure proper operation.
End Information
lllllllllllllllllllll
End QPS Requirements
25. FSTD Qualification on the Basis of a
Bilateral Aviation Safety Agreement (BASA)
(§ 60.37).
lllllllllllllllllllll
Begin Information
Begin Information
There are no additional QPS requirements
or informational material that apply to
§ 60.37, FSTD Qualification on the Basis of
a Bilateral Aviation Safety Agreement
(BASA).
End Information
lllllllllllllllllllll
Attachment 1 to Appendix D to Part 60—
General FTD Requirements
lllllllllllllllllllll
Begin QPS Requirements
1. Requirements
a. Certain requirements included in this
appendix must be supported with a
Statement of Compliance and Capability
(SOC), which may include objective and
subjective tests. The SOC will confirm that
the requirement was satisfied, and describe
lllllllllllllllllllll
2. Discussion
a. This attachment describes the general
requirements for qualifying Level 4 through
Level 6 FTDs. The sponsor should also
consult the objectives tests in Attachment 2
and the examination of functions and
subjective tests listed in Attachment 3 to
determine the complete requirements for a
specific level FTD.
b. The material contained in this
attachment is divided into the following
categories:
(1) General Cockpit Configuration.
(2) Programming.
(3) Equipment Operation.
(4) Equipment and facilities for instructor/
evaluator functions.
(5) Motion System.
(6) Visual System.
(7) Sound System.
c. Table D1A provides the standards for the
General FTD Requirements.
End Information
lllllllllllllllllllll
TABLE D1A.—MINIMUM FTD REQUIREMENTS
<<>>
<>
Notes
FTD Level
No.
General FTD requirements
4
5
6
1. General Cockpit Configuration
TABLE D1A.—MINIMUM FTD REQUIREMENTS
<<>>
<>
Notes
FTD Level
No.
General FTD requirements
4
sroberts on PROD1PC70 with RULES
1.a ........
5
The FTD must have a cockpit that is a replica of the
helicopter, or set purposes, the of helicopters simulated with controls, equipment, observable cockpit indicators, circuit breakers, and bulkheads properly located, functionally accurate and replicating the helicopter or set of helicopters. The direction of movement of controls and switches must be identical to
that in the helicopters or set of helicopters. Crewmember seats must afford the capability for the occupant to be able to achieve the design ‘‘eye position’’
for specific helicopters, or to approximate such a position for a generic set of helicopters.
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6
X
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For FTD purposes, the cockpit consists of all that space
forward of a cross section of the fuselage at the most
extreme aft setting of the pilots’ seats including additional, required crewmember duty stations and those
required bulkheads aft of the pilot seats.
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TABLE D1A.—MINIMUM FTD REQUIREMENTS—Continued
<<>>
<>
Notes
FTD Level
No.
General FTD requirements
4
2.b ........
The FTD must have equipment (i.e., instruments, panels, systems, and controls) simulated sufficiently for
the authorized training/checking events to be accomplished. The installed equipment, must be locted in a
spatially correct configuration, and may be in a cockpit or an open flight deck area. Actuation of this
equipment must replicate the appropriate function in
the helicopter.
3.c .........
5
X
X
Circuit breakers must function accurately when they are
involved in operating procedures or malfunctions requiring or involving flight crew response.
Level 6 devices must have installed circuit breakers
properly located in the FTD cockpit.
6
X
X
X
X
4. Programming
The FTD must provide the proper effect of aerodynamic
changes for the combinations of drag and thrust normally encountered in flight. This must include the effect of change in helicopter attitude, thrust, drag, altitude, temperature, and configuration.
Level 6 additionally requires the effects of changes in
gross weight and center of gravity.
Level 5 requires only generic aerodynamic programming.
4.b ........
The FTD must have computer (analog or digital) capability (i.e., capacity, accuracy, resolution, and dynamic
response) needed to meet the qualification level
sought.
X
X
X
4.c .........
sroberts on PROD1PC70 with RULES
4.a ........
The FTD hardware and programming must be updated
within 6 months of any helicopter modifications or
data releases (or any such modification or data releases applicable to the set of helicopters) unless,
with prior coordination, the NSPM authorizes otherwise.
X
X
X
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TABLE D1A.—MINIMUM FTD REQUIREMENTS—Continued
<<>>
<>
Notes
FTD Level
No.
General FTD requirements
4
4.d ........
Related responses of the cockpit instruments (and the
visual and motion systems, if installed and training,
testing, or checking credits are being sought) must be
coupled closely to provide integrated sensory cues.
The instruments (and the visual and motion systems, if
installed, and training, testing, or checking credits are
being sought) must respond to abrupt input at the pilot’s position within the allotted time, but not before
the time, when the helicopter or set of helicopters
would respond under the same conditions. (If a visual
system is installed and training, testing, or checking
credits are sought, the visual scene changes from
steady state disturbance must occur within the appropriate system dynamic response limt but not before
the instrument response (and not before the motion
system onset if a motion system is installed)).
A demonstration is required and must simultaneously
record: The analog out put from the pilot’s control column, wheel, and pedals; and the output signal to the
pilot’s attitude indicator. These recordings must be
compared to helicopter response data in the following
configurations: Takeoff, cruise, and approach or landing. The results must be recorded in the QTG. Additionally, if a visual system is installed and training,
testing, or checking credit are sought, the output signal to the visual system disply (including visual system analog delays must be recorded); and if a motion
system is installed and training, testing, or checking
credits are sought, the output from an accelerometer
attached to the motion system platform located at an
acceptable location near the pilots’ seates is also required.
5
6
......
X
X
5. Equipment Operation
All relevant instrument indications involved in the simulation of the helicopter (or set of helicopters) must
automatically respond to control movement or external disturbances to the simulated helicopter or set of
helicopters; e.g., turbulence or winds.
X
X
5.b ........
Navigation equipment must be installed and operate
within the tolerances applicable for the helicopter or
set of helicopters.
Level 5 only needs that navigation equipment necesary
to fly an instrument approach. Level 6 must also include communication equipment (inter-phone and air/
ground) like that in the helicopter, or set of helicopters, and, if appropriate to the operation being
conducted, an oxygen mask microphone system.
X
X
5.c .........
sroberts on PROD1PC70 with RULES
5.a ........
Installed systems must simulate the applicable helicopter (or set of helicopters) system operation both
on the ground and in flight. At least one helicopter
system must be represented. Systems must be operative to the extent that applicable normal, abnormal,
and emergency operating procedures included in the
sponor’s training programs can be accomplished.
Level 6 must simulate all applicable helicopter flight,
navigation, and systems operation. Level 5 must have
functional flight and navigational controls, displays,
and instrumentation.
X
X
X
5.d ........
The lighting environment for panels and instruments
must be sufficient for the operation being conducted.
X
X
X
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63597
TABLE D1A.—MINIMUM FTD REQUIREMENTS—Continued
<<>>
<>
Notes
FTD Level
No.
General FTD requirements
4
5.e ........
The FTD must provide control forces and control travel
that correspond to the replicated helicopter or set of
helicopters. Control forces must react in the same
manner as in the helicopter or set of helicopters
under the same flight conditions.
5.f .........
The FTD must provide control forces and control travel
of sufficient precision to manually fly an instrument
approach. The control forces must react in the same
manner as in the helicopter or set of helicopters
under the same flight conditions.
5
6
X
X
6. Instructor or Evaluator Facilities
6.a ........
In addition to the flight crewmember stations, suitable
seating arrangements for an instructor/check airman
and FAA Inspector must be available. These seats
must provide adequate view of crewmember’s
panel(s).
X
X
X
6.b ........
The FTD must have instructor controls that permit activation of norma, abnormal, and emergency conditions, as may be appropriate. Once activated, proper
system operation must result from system management by the crew and not require input from the instructor controls.
X
X
X
X
X
X
X
X
These seats need not be a replica of an aircraft seat
and may be as simple as an office chair placed in an
appropriate position.
X
7. Motion System
7.a ........
The FTD may have a motion system; if desired, although it is not required.
If installed, the motion system operation may not be distracting. The motion system standards set out in QPS
FAA–S–120–40C for at least Level A simulators is acceptable.
8. Visual System
sroberts on PROD1PC70 with RULES
8.a ........
The FTD may have a visual system; if desired, although
it is not required. If a visual system is installed, it
must meet the following criteria:
(1) Sinle channel, uncollimated display is acceptable.
(2) Minimum field of view: 18° vertical/24° horizontal for
the pilot flying.
(3) Maximum paralax error: 10° per pilot.
(4) Scene content may not be distracting.
(5) Minimum distance from the pilot’s eye position to the
surface of a direct view display may not be less than
the distance to any front panel instrument.
(6) Minimum resolution of 5 arc-min. for both computed
and displayed pixel size.
(7) Maximum latency or through-put must not exceed
300 milliseconds.
A statement of capability is required.
A demonstration of latency or through-put is required.
Visual system standards set out in QPS FAA–S–120–
40C, for at least Level A simulators is acceptable.
However, if additional authorizations (training, testing,
or checking credits) are sought that require the use of
a visual systems, the Level A simulator visual system
standards apply.
9. Sound System
9.a ........
The FTD must simulate significant cockpit sounds resulting from pilot actions that correspond to those
heard in the helicopter.
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63598
Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
Attachment 2 to Appendix D to Part 60—
Flight Training Device (FTD) Objective Tests
lllllllllllllllllllll
Begin QPS Requirements
sroberts on PROD1PC70 with RULES
1. Test Requirements
a. The ground and flight tests required for
qualification are listed in Table D2A
Objective Evaluation. Computer generated
FTD test results must be provided for each
test except where an alternate test is
specifically authorized by the NSPM. If a
flight condition or operating condition is
required for the test but does not apply to the
helicopter being simulated or to the
qualification level sought, it may be
disregarded (e.g., engine out climb capability
for a single-engine helicopter). Each test
result is compared against the validation data
described in § 60.13, and in appendix B. The
results must be produced on an appropriate
recording device acceptable to the NSPM and
must include FTD number, date, time,
conditions, tolerances, and appropriate
dependent variables portrayed in comparison
to the validation data. Time histories are
required unless otherwise indicated in Table
D2A. All results must be labeled using the
tolerances and units given.
b. Table D2A in this attachment sets out
the test results required, including the
parameters, tolerances, and flight conditions
for FTD validation. Tolerances are provided
for the listed tests because mathematical
modeling and acquisition and development
of reference data are often inexact. All
tolerances listed in the following tables are
applied to FTD performance. When two
tolerance values are given for a parameter,
the less restrictive may be used unless
otherwise indicated.
c. Certain tests included in this attachment
must be supported with a Statement of
Compliance and Capability (SOC). In Table
D2A, requirements for SOCs are indicated in
the ‘‘Test Details’’ column.
d. When operational or engineering
judgment is used in making assessments for
flight test data applications for FTD validity,
such judgment must not be limited to a single
parameter. For example, data that exhibit
rapid variations of the measured parameters
may require interpolations or a ‘‘best fit’’ data
section. All relevant parameters related to a
given maneuver or flight condition must be
provided to allow overall interpretation.
When it is difficult or impossible to match
FTD to helicopter data throughout a time
history, differences must be justified by
providing a comparison of other related
variables for the condition being assessed.
e. It is not acceptable to program the FTD
so that the mathematical modeling is correct
only at the validation test points. Unless
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Jkt 211001
noted otherwise, tests must represent
helicopter performance and handling
qualities at operating weights and centers of
gravity (CG) typical of normal operation. If a
test is supported by aircraft data at one
extreme weight or CG, another test supported
by aircraft data at mid-conditions or as close
as possible to the other extreme is necessary.
Certain tests that are relevant only at one
extreme CG or weight condition need not be
repeated at the other extreme. The results of
the tests for Level 6 are expected to be
indicative of the device’s performance and
handling qualities throughout all of the
following:
(1) The helicopter weight and CG envelope;
(2) The operational envelope; and
(3) Varying atmospheric ambient and
environmental conditions—including the
extremes authorized for the respective
helicopter or set of helicopters.
f. When comparing the parameters listed to
those of the helicopter, sufficient data must
also be provided to verify the correct flight
condition and helicopter configuration
changes. For example, to show that control
force is within the parameters for a static
stability test, data to show the correct
airspeed, power, thrust or torque, helicopter
configuration, altitude, and other appropriate
datum identification parameters must also be
given. If comparing short period dynamics,
normal acceleration may be used to establish
a match to the helicopter, but airspeed,
altitude, control input, helicopter
configuration, and other appropriate data
must also be given. If comparing landing gear
change dynamics, pitch, airspeed, and
altitude may be used to establish a match to
the helicopter, but landing gear position must
also be provided. All airspeed values must be
properly annotated (e.g., indicated versus
calibrated). In addition, the same variables
must be used for comparison (e.g., compare
inches to inches rather than inches to
centimeters).
g. The QTG provided by the sponsor must
clearly describe how the FTD will be set up
and operated for each test. Each FTD
subsystem may be tested independently, but
overall integrated testing of the FTD must be
accomplished to assure that the total FTD
system meets the prescribed standards. A
manual test procedure with explicit and
detailed steps for completing each test must
also be provided.
h. In those cases where the objective test
results authorize a ‘‘snapshot test’’ or a
‘‘series of snapshot test’’ results in lieu of a
time-history result, the sponsor or other data
provider must ensure that a steady state
condition exists at the instant of time
captured by the ‘‘snapshot.’’
i. For previously qualified FTDs, the tests
and tolerances of this attachment may be
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used in subsequent continuing qualification
evaluations for any given test if the sponsor
has submitted a proposed MQTG revision to
the NSPM and has received NSPM approval.
j. Tests of handling qualities must include
validation of augmentation devices. FTDs for
highly augmented helicopters will be
validated both in the unaugmented
configuration (or failure state with the
maximum permitted degradation in handling
qualities) and the augmented configuration.
Where various levels of handling qualities
result from failure states, validation of the
effect of the failure is necessary. For those
performance and static handling qualities
tests where the primary concern is control
position in the unaugmented configuration,
unaugmented data are not required if the
design of the system precludes any affect on
control position. In those instances where the
unaugmented helicopter response is
divergent and non-repeatable, it may not be
feasible to meet the specified tolerances.
Alternative requirements for testing will be
mutually agreed upon by the sponsor and the
NSPM on a case-by-case basis.
k. Some tests will not be required for
helicopters using helicopter hardware in the
FTD cockpit (e.g., ‘‘helicopter modular
controller’’). These exceptions are noted in
Section 2 ‘‘Handling Qualities’’ in Table D2A
of this attachment. However, in these cases,
the sponsor must provide a statement that the
helicopter hardware meets the appropriate
manufacturer’s specifications and the
sponsor must have supporting information to
that fact available for NSPM review.
l. For objective test purposes, ‘‘Near
maximum’’ gross weight is a weight chosen
by the sponsor or data provider that is not
less than the basic operating weight (BOW)
of the helicopter being simulated plus 80%
of the difference between the maximum
certificated gross weight (either takeoff
weight or landing weight, as appropriate for
the test) and the BOW. ‘‘Light’’ gross weight
is a weight chosen by the sponsor or data
provider that is not more than 120% of the
BOW of the helicopter being simulated or as
limited by the minimum practical operating
weight of the test helicopter. ‘‘Medium’’ gross
weight is a weight chosen by the sponsor or
data provider that is approximately ±10% of
the average of the numerical values of the
BOW and the maximum certificated gross
weight. (Note: BOW is the empty weight of
the aircraft plus the weight of the following:
Normal oil quantity; lavatory servicing fluid;
potable water; required crewmembers and
their baggage; and emergency equipment.
(References: Advisory Circular 120–27,
‘‘Aircraft Weight and Balance;’’ and FAA–H–
8083–1, ‘‘Aircraft Weight and Balance
Handbook.’’).
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
63599
TABLE D2A.—FLIGHT TRAINING DEVICE (FTD) OBJECTIVE TESTS
<<< QPS Requirements >>>
FTD
Level
Test
No.
Tolerances
Flight conditions
Test details
5
Title
6
1. Performance
1.a Engine Assessment
1.a.1 ......
1.a.1.a ...
Start Operations ..........
Engine start and acceleration (transient).
1.a.1.b ...
Steady State Idle and
Operating RPM conditions.
1.a.2 ......
1.a.3 ......
Light Off Time—±10% or ±1
sec.Torque—±5%Rotor
Speed—±3% Fuel Flow—
±10% Gas Generator
Speed—±5% Power
TurbineSpeed—±5% Gas
TurbineTemp.—±30°C.
Ground with the
Rotor Brake
Used and Not
Used.
Ground ..................
Power Turbine Speed
Trim.
Torque—±3% Rotor Speed—
±1.5% Fuel Flow—±5%
Gas Generator Speed—
±2% Power Turbine
Speed—±2% Turbine Gas
Temp.—±20°C.
±10% of total change of
power turbine speed.
Engine and Rotor
Speed Governing.
Torque—±5% Rotor Speed—
±1.5%.
1) Climb ................
2) Descent ............
Performance and
Trimmed Flight Control Positions.
Torque—±3% Pitch Attitude—±1.5° Sideslip
Angle—±2° Longitudinal
Control Position—±5% Lateral Control Position—±5%
Directional Control Position—±5% Collective Control Position—±5%.
Cruise (Augmentation On and Off).
Record results for
two gross weight
CG combinations
with varying trim
speeds throughout the airspeed
envelope. May
be a series of
snapshot tests.
X
X
Performance and
Trimmed Flight Control Positions.
Verticle Velocity—±100 fpm
(61m/sec) or ±10% Pitch
Attitude—±1.5° Sideslip
Angle—±2° Longitudinal
Control Position—±5% Lateral Control Position—±5%
Directional Control Position—±5% Collective Control Position—±5%.
All engines operating. One engine inoperative.
Augmentation
System(s) On
and Off.
Record results for
two gross weight
and CG combinations. The
data presented
must be for normal climb power
conditions. May
be a series of
snapshot tests.
X
X
Torque—±3% Pitch Attitude—±1.5° Sideslip
Angle—±2° Longitudinal
Control Position—±5%.
At or near 1,000
fpm rate of descent (RoD) at
normal approach
speed.
Record results for
two gross weight
and CG combinations. May
be a series of
snapshot tests.
X
X
Ground ..................
Record each engine start from
the initiation of
the start sequence to steady
state idle and
from steady state
idle to operating
RPM.
Record both steady
state idle and
operating RPM
conditions. May
be a series of
snapshot tests.
Record engine response to trim
system actuation
in both directions.
Record results
using a step
input to the collective. May be
conducted concurrently with
climb and descent performance tests.
X
X
X
X
X
1.b. In Flight
1.c. Climb
1.d Descent
sroberts on PROD1PC70 with RULES
1.d.1 ......
Descent Performance
and Trimmed Flight
Control Positions.
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63600
Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
TABLE D2A.—FLIGHT TRAINING DEVICE (FTD) OBJECTIVE TESTS—Continued
<<< QPS Requirements >>>
FTD
Level
Test
No.
1.d.2 ......
Tolerances
Flight conditions
Test details
5
Title
Autorotation Performance and Trimmed
Flight Control Positions.
Lateral Control Position—
±5% Directional Control
Position—±5% Collective
Control Position—±5%.
Torque—±3% Pitch Attitude—±1.5° Sideslip
Angle—±2° Longitudinal
Control Position—±5% Lateral Control Position—±5%
Directional Control Position—±5% Collective Control Position—±5%.
Augmentati on
System(s) On
and Off.
Steady descents.
Augmentation
System(s) On
and Off.
Record results for
two gross weight
conditions. Data
must be recorded for normal operating
RPM. (Rotor
speed tolerance
applies only if
collective control
position is full
down.) Data
must be recorded for
speeds from approximately 50
kts. through at
least maximum
glide distance
airspeed. May be
a series of snapshot tests.
Rotor Speed—±3% Pitch Attitude±2° Roll Attitude—
±3° Yaw Attitude—±5° Airspeed—±5 kts. Vertical
Velocity—±200 fpm (1.00
m/sec) or 10%.
1) Cruise; or 2)
Climb.
6
X
X
..........................
1.e. Autorotation
Entry ............................
...............................................
..........................
Record results of a
rapid throttle reduction to idle. If
accomplished in
cruise, results
must be for the
maximum range
airspeed. If accomplished in
climb, results
must be for the
maximum rate of
climb airspeed at
or near maximum continuous
power..
..........................
Contact the NSPM for clarification of any issue regarding helicopters with reversible controls.
Breakout—±0.25lbs. (0.112
daN) or 25%. Force—±1.0
lb. (0.224 daN) or 10%.
...............................
...............................
Ground; Static conditions. Trim On
and Off. Friction
Off Augmentation On and off.
Record results for
an uninterrupted
control sweep to
the stops. (This
test does not
apply if aircraft
hardware modular controllers
are used.).
Record results for
an uninterrupted
control sweep to
the stops.
X
2. Handling Qualities.
Start [here] Contro 1
System Mechanical
Characteristics.
2.a.1. .....
sroberts on PROD1PC70 with RULES
2.a. ........
Cyclic ...........................
2.a.2. .....
Collective and Pedals
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Breakout—±0.5 lb. (0.224
daN) or 25%. Force —±1.0
lb. (0.224 daN) or 10%.
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Ground; Static conditions. Trim On
and Off. Friction
Off Augmentation and On and
Off.
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<< Information >>
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X
X
X
X
Notes
Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
63601
TABLE D2A.—FLIGHT TRAINING DEVICE (FTD) OBJECTIVE TESTS—Continued
<<< QPS Requirements >>>
FTD
Level
Test
No.
Tolerances
Flight conditions
Test details
5
6
X
The tolerance applies to the recorded value of
the trim rate.
Results must be
recorded for a
normal control
displacement in
both directions in
each axis (approximately 255
to 50% of full
throw).
X
X
..........................................
±5 lbs. (2.224 daN) or 10% ..
2.a.5. .....
Control Dynamics (all
axes).
±10% of time for first zero
crossing and ±10 (N+1)%
of period thereafter. ±10%
of amplitude of first overshoot. ±20% of amplitude
of 2nd and subsequent
overshoots greater than
5% of initial displacement
±1 overshoot.
Hover/Cruise Trim
On Friction Off.
2.a.6 ......
Freeplay ......................
±0.10 in .................................
Ground; Static conditions.
Record and compare results for
all controls.
X
X
2.a.4. .....
Rate—±10% .........................
..........................
Ground; Static conditions..
Ground; Static conditions. Trim On
Friction Off.
..........................
..........................
X
2.b. Longitudinal Handling Qualities.
Control Response .......
Pitch Rate—±10% or ±2/sec.
Pitch Attitude Change—
±10% or ±1.5°.
Cruise Augmentation On and Off.
Results must be
recorded for two
cruise airspeeds
to include minimum power required speed
Record data for
a step control
input. The Offaxis response
must show correct trend for unaugmented
cases.
X
X
2.b.2 ......
Static Stability .............
Longitudinal Control Position:
±10% of change from trim
or ±0.25 in. (6.3 mm) or
Longitudinal Control Force:
±0.5 lb. (0.223 daN) or
±10%.
Cruise or Climb.
Autorotation.
Augmentation
On and Off.
Record results for
a minimum of
two speeds on
each side of the
trim speed. May
be a series of
snapshot tests.
X
X
2.b.3 ......
Dynamic Stability .........
2.b.3.a. ..
sroberts on PROD1PC70 with RULES
2.b.1 ......
Long Term Response
±10% of calculated period.
±10% of time to 1⁄2 or double amplitude, or ±0.02 of
damping ratio.
Cruise Augmentation On and Off.
Record results for
three full cycles
(6 overshoots
after input completed) or that
sufficient to determine time to
1⁄2 double or amplitude, whichever is less. For
non-periodic responses, the
time history must
be matched.
X
X
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Notes
X
Title
.................................
Brake Pedal Force vs.
Position..
Trim System Rate (all
applicable systems).
2.a.3. .....
<< Information >>
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Control Dynamics
for irreversible
control systems
may be evaluated in a ground/
static condtion.
Refer to paragraph 3 of this
attachment for
additional information. ‘‘N’’ is
the sequential
period of a full
cycle of oscillation.
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
TABLE D2A.—FLIGHT TRAINING DEVICE (FTD) OBJECTIVE TESTS—Continued
<<< QPS Requirements >>>
FTD
Level
Test
Tolerances
Flight conditions
Test details
5
6
No.
Title
2.b.3.b ...
Short Term Response
±1.5° Pitch or ±2/sec. Pitch
Rate. ±0.1 g Normal Acceleration.
Cruise or Climb.
Augmentation
On and Off.
Record results for
at least two airspeeds.
X
2.b.4 ......
Maneuvering Stability ..
Longitudinal Control Position—±10% of change
from trim or ±0.25 in.
(6.3mm) or Longitudinal
Control Forces—±0.5 lb.
(0.223 daN) or ±10%.
Cruise or Climb.
Augmentation
On and Off.
X
2.b.5 ......
Landing Gear Operating Times.
±1 sec ...................................
Takeoff (Retraction) Approach
(Extension).
Record results for
at least two airspeeds. Record
results for Approximately 30°–
45° bank angle.
The force may
be shown as a
cross plot for irreversible systems. May be a
series of snapshot tests.
..........................
X
X
X
X
X
X
2.c. Lateral and Directional Handling Qualities.
Control Response .......
Lateral .........................
2.c.1.b ...
sroberts on PROD1PC70 with RULES
2.c.1 ......
2.c.1.a ...
(b) Directional ..............
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Roll Rate—±10% or ±3°/sec.
Roll Attitude Change—
±10% or ±3°.
Cruise Augmentation On and Off.
Yaw Rate—±10% or ±2°/sec.
Yaw Attitude Change—
±10% or ±2°.
Cruise Augmentation On and Off.
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<< Information >>
Record results for
at least two airspeeds, including
the speed at or
near the minimum power required airspeed.
Record results
for a step control
input. The Offaxis response
must show correct trend for unaugmented
cases.
Record data for at
least two Airspeeds, including
the speed at or
near the minimum power required airspeed
Record results
for a step control
input. The Offaxis response
must show correct trend for unaugmented
cases.
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63603
TABLE D2A.—FLIGHT TRAINING DEVICE (FTD) OBJECTIVE TESTS—Continued
<<< QPS Requirements >>>
FTD
Level
Test
No.
Tolerances
Test details
5
Title
2.c.2. .....
Directional Static Stability.
2.c.3. .....
2.c.3.a. ..
Dynamic Lateral and
Directional Stability.
Lateral-Directional Oscillations.
2.c.3.b. ..
2.c.3.c. ..
Lateral Control Position—
1) Cruise; ..............
±10% of change from trim
or 2) Climb (may
or ±0.25 in. (6.3mm) or
use Descent inLateral Control Force—
stead of Climb if
±0.5 lb. (0.223 daN) or
desired).
10%. Roll Attitude—±1.5..
Augmentation On
Directional Control Position—
and Off..
±10% of change from trim
or ±0.25 in. (6.3mm) or Directional Control Force—
±1 lb. (0.448 daN) or 10%..
Longitudinal Control Position—±10% of change
from trim or ±0.25 in.
(6.3mm).
Vertical Velocity—±100 fpm
(0.50m/sec) or 10%.
...............................................
..........................
Record results for
at least two sideslip angles on either side of the
trim point..
The force may be
shown as a
cross plot for irreversible systems..
May be a series of
snapshot test..
±0.5 sec. or ±10% of period.
±10% of time to 1⁄2 or double amplitude or ±0.02 of
damping ratio. ±20% or ±1
sec of time difference between peaks of bank and
sideslip.
Cruise or Climb.
Augmentation
On/Off.
Spiral Stability .............
Correct Trend, ±2 bank or
±10% in 20 sec.
Cruise or Climb.
Augmentation
On and Off.
Adverse/Proverse Yaw
Correct Trend, ±2 transient
sideslip angle.
Cruise or Climb.
Augmentation
On and Off.
Record results for
at least two airspeeds..
The test must be
initiated with a
cyclic or a pedal
doublet input.
Record results
for six full cycles
(12 overshoots
after input completed) or that
sufficient to determine time to
1⁄2 or double amplitude, whichever is less. For
non-periodic response, the time
history must be
matched.
Record the results
of a release from
pedal only or cyclic only turns.
Results must be
recorded from
turns in both directions.
Record the time
history of initial
entry into cyclic
only turns, using
only a moderate
rate for cyclic
input. Results
must be recorded for turns
in both directions.
3. Control Dynamics
sroberts on PROD1PC70 with RULES
Flight conditions
Begin Information
a. The characteristics of a helicopter flight
control system have a major effect on the
handling qualities. A significant
consideration in pilot acceptability of a
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Notes
X
X
This is a steady
heading sideslip
test.
X
X
X
X
X
X
..........................
helicopter is the ‘‘feel’’ provided through the
cockpit controls. Considerable effort is
expended on helicopter feel system design in
order to deliver a system with which pilots
will be comfortable and consider the
helicopter desirable to fly. In order for an
FTD to be representative, it too must present
PO 00000
6
the pilot with the proper feel; that of the
respective helicopter.
b. Recordings such as free response to an
impulse or step function are classically used
to estimate the dynamic properties of
electromechanical systems. In any case, it is
only possible to estimate the dynamic
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
sroberts on PROD1PC70 with RULES
properties as a result of only being able to
estimate true inputs and responses.
Therefore, it is imperative that the best
possible data be collected since close
matching of the FTD control loading system
to the helicopter systems is essential. Control
feel dynamic tests are described in the Table
of Objective Tests in this appendix. Where
accomplished, the free response is measured
after a step or pulse input is used to excite
the system.
c. For initial and upgrade evaluations, it is
required that control dynamic characteristics
be measured at and recorded directly from
the cockpit controls. This procedure is
usually accomplished by measuring the free
response of the controls using a step or pulse
input to excite the system. The procedure
must be accomplished in hover, climb,
cruise, and autorotation. For helicopters with
irreversible control systems, measurements
may be obtained on the ground. Proper pitotstatic inputs (if appropriate) must be
provided to represent airspeeds typical of
those encountered in flight.
d. It may be shown that for some
helicopters, climb, cruise, and autorotation
have like effects. Thus, some tests for one
may suffice for some tests for another. If
either or both considerations apply,
engineering validation or helicopter
manufacturer rationale must be submitted as
justification for ground tests or for
eliminating a configuration. For FTDs
requiring static and dynamic tests at the
controls, special test fixtures will not be
required during initial and upgrade
evaluations if the sponsor’s QTG shows both
test fixture results and the results of an
alternative approach, such as computer plots
which were produced concurrently and show
satisfactory agreement. Repeat of the
alternative method during the initial
evaluation would then satisfy this test
requirement.
e. Control Dynamics Evaluations. The
dynamic properties of control systems are
often stated in terms of frequency, damping,
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Jkt 211001
and a number of other classical
measurements which can be found in texts
on control systems. In order to establish a
consistent means of validating test results for
FTD control loading, criteria are needed that
will clearly define the interpretation of the
measurements and the tolerances to be
applied. Criteria are needed for both the
underdamped system and the overdamped
system, including the critically damped case.
In the case of an underdamped system with
very light damping, the system may be
quantified in terms of frequency and
damping. In critically damped or
overdamped systems, the frequency and
damping is not readily measured from a
response time history. Therefore, some other
measurement must be used.
f. Tests to verify that control feel dynamics
represent the helicopter must show that the
dynamic damping cycles (free response of the
control) match that of the helicopter within
specified tolerances. The method of
evaluating the response and the tolerance to
be applied are described below for the
underdamped and critically damped cases.
g. Tolerances.
(1) Underdamped Response.
(a) Two measurements are required for the
period, the time to first zero crossing (in case
a rate limit is present) and the subsequent
frequency of oscillation. It is necessary to
measure cycles on an individual basis in case
there are nonuniform periods in the
response. Each period will be independently
compared to the respective period of the
helicopter control system and, consequently,
will enjoy the full tolerance specified for that
period.
(b) The damping tolerance will be applied
to overshoots on an individual basis. Care
must be taken when applying the tolerance
to small overshoots since the significance of
such overshoots becomes questionable. Only
those overshoots larger than 5 percent of the
total initial displacement will be considered
significant. The residual band, labeled T(Ad)
on Figure 1 of this attachment is ±5 percent
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of the initial displacement amplitude, Ad,
from the steady state value of the oscillation.
Oscillations within the residual band are
considered insignificant. When comparing
simulator data to helicopter data, the process
would begin by overlaying or aligning the
simulator and helicopter steady state values
and then comparing amplitudes of oscillation
peaks, the time of the first zero crossing, and
individual periods of oscillation. To be
satisfactory, the simulator must show the
same number of significant overshoots to
within one when compared against the
helicopter data. The procedure for evaluating
the response is illustrated in Figure 1 of this
attachment.
(2) Critically Damped and Overdamped
Response. Due to the nature of critically
damped responses (no overshoots), the time
to reach 90 percent of the steady state
(neutral point) value must be the same as the
helicopter within ±10 percent. The simulator
response must be critically damped also.
Figure 2 of this attachment illustrates the
procedure.
(3)(a) The following summarizes the
tolerances, T, for an illustration of the
referenced measurements. (See Figures 1 and
2, above)
T(P0) ±10% of P0
T(P1) ±20% of P1
T(A) ±10% of A1, ±20% of Subsequent Peaks
T(Ad) ±10% of Ad = Residual Band
Overshoots ±1
(b) In the event the number of cycles
completed outside of the residual band, and
thereby significant, exceeds the number
depicted in figure 1, the following tolerances
(T) will apply:
T(Pn) ±10%(n+1)% of Pn, where ‘‘n’’ is the
next in sequence.
End Information
✖
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Attachment 3 to Appendix D to Part 60—
Flight Training Device (FTD) Subjective
Evaluation
1. Discussion
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Begin Information
a. The subjective tests and the examination
of functions provide a basis for evaluating the
capability of the FTD to perform over a
typical utilization period; determining that
the FTD satisfactorily meets the appropriate
training/testing/checking objectives and
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competently simulates each required
maneuver, procedure, or task; and verifying
correct operation of the FTD controls,
instruments, and systems. The items in the
list of operations tasks are for FTD evaluation
purposes only. They must not be used to
limit or exceed the authorizations for use of
a given level of FTD as found in the Practical
Test Standards or as may be approved by the
TPAA. All items in the following paragraphs
are subject to an examination of function.
b. The List of Operations Tasks addressing
pilot functions and maneuvers is divided by
flight phases. All simulated helicopter
systems functions will be assessed for normal
and, where appropriate, alternate operations.
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Normal, abnormal, and emergency operations
associated with a flight phase will be
assessed during the evaluation of maneuvers
or events within that flight phase.
c. Systems to be evaluated are listed
separately under ‘‘Any Flight Phase’’ to
ensure appropriate attention to systems
checks. Operational navigation systems
(including inertial navigation systems, global
positioning systems, or other long-range
systems) and the associated electronic
display systems will be evaluated if installed.
The NSP pilot will include in his report to
the TPAA, the effect of the system operation
and any system limitation.
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d. At the request of the TPAA, the NSP
Pilot may assess the FTD for a special aspect
of a sponsor’s training program during the
functions and subjective portion of an
evaluation. Such an assessment may include
a portion of a Line Oriented Flight Training
(LOFT) scenario or special emphasis items in
the sponsor’s training program. Unless
directly related to a requirement for the
qualification level, the results of such an
evaluation would not necessarily affect the
qualification of the FTD.
End Information
lllllllllllllllllllll
TABLE D3A.—TABLE OF FUNCTIONS AND SUBJECTIVE TESTS LEVEL 6 FTD
<<< QPS Requirements >>>
No.
Operations tasks
Tasks in this table are subject to evaluation if appropriate for the helicopter simulated as indicated in the SOQ Configuration List and/or for a
Level 6 FTD. Items not installed or not functional on the FTD and, therefore, not appearing on the SOQ Configuration List, are not required
to be listed as exceptions on the SOQ.
1. Preflight Procedures
1.a .................
1.b .................
1.b.1 ..............
1.b.2 ..............
1.b.3 ..............
1.b.4 ..............
1.b.5 ..............
Preflight Inspection (Cockpit Only) switches, indicators, systems, and equipment.
APU/Engine start and run-up.
Normal start procedures.
Alternate start procedures.
Abnormal starts and shutdowns.
Rotor engagement.
System checks.
2. Takeoff and Departure Phase
2.a .................
2.b .................
instrument
Takeoff with engine failure after critical decision point (CDP).
3. Climb
3.a .................
3.b .................
Normal.
One engine inoperative.
4. Inflight Maneuvers
4. ...................
4.b .................
4.c .................
4.c.1 ..............
4.c.2 ..............
4.c.3 ..............
4.d .................
4.e .................
4.e.1 ..............
4.e.2 ..............
4.e.3 ..............
4.e.4 ..............
4.e.5 ..............
4.e.6 ..............
4.e.7 ..............
Performance.
Flying qualities.
Turns.
Timed.
Normal.
Steep.
Accelerations and decelerations.
Abnormal/emergency procedures.
Engine fire.
Engine failure.
In-flight engine shutdown (and restart, if applicable).
Fuel governing system failures (e.g., FADEC malfunction).
Directional control malfunction (restricted to the extent that the maneuver may not terminate in a landing).
Hydraulic failure.
Stability augmentation system failure.
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5. Instrument Procedures
5.a .................
5.b .................
5.b.1 ..............
5.b.2 ..............
5.b.3 ..............
5.b.4 ..............
5.b.5 ..............
5.b.6 ..............
5.b.7 ..............
5.b.8 ..............
5.c .................
5.c .................
5.c .................
5.c .................
5.c.1 ..............
5.c.2 ..............
5.c.3 ..............
5.c.4 ..............
5.d .................
5.d.1 ..............
5.d.2 ..............
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Holding.
Precision Instrument Approach.
All engines operating.
One or more engines inoperative.
Approach procedures:
PAR.
ILS.
Manual (raw data).
Flight director only.
Autopilot* and flight director (if appropriate) coupled.
Non-precision Instrument Approach.
Normal—All engines operating.
One or more engines inoperative.
Approach procedures:
NDB.
VOR, RNAV, TACAN, GPS.
ASR.
Helicopter only.
Missed Approach.
All engines operating.
One or more engines inoperative.
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TABLE D3A.—TABLE OF FUNCTIONS AND SUBJECTIVE TESTS LEVEL 6 FTD—Continued
<<< QPS Requirements >>>
No.
5.d.3 ..............
Operations tasks
Stability augmentation system failure.
6. Normal and Abnormal Procedures (any phase of flight)
6.a .................
6.a.1 ..............
6.a.2 ..............
6.a.3 ..............
6.a.4 ..............
6.a.5 ..............
6.a.6 ..............
6.a.7 ..............
6.a.8 ..............
6.a.9 ..............
6.a.10 ............
6.a.11 ............
6.a.12 ............
6.a.13 ............
6.a.14 ............
6.a.15 ............
6.a.16 ............
6.b .................
6.b.1 ..............
6.b.2 ..............
6.b.3 ..............
6.b.4 ..............
6.b.5 ..............
6.b.6 ..............
6.b.7 ..............
Helicopter and powerplant systems operation (as applicable).
Anti-icing/deicing systems.
Auxiliary power-plant.
Communications.
Electrical system.
Environmental system.
Fire detection and suppression.
Flight control system.
Fuel system.
Engine oil system.
Hydraulic system.
Landing gear.
Oxygen.
Pneumatic.
Powerplant.
Flight control computers.
Stability augmentation and control augmentation system(s).
Flight management and guidance system (as applicable).
Airborne radar.
Automatic landing aids.
Autopilot*.
Collision avoidance system.
Flight data displays.
Flight management computers.
Navigation systems.
7. Postflight Procedures
7.a
7.b
7.c
7.d
7.e
.................
.................
.................
.................
.................
Parking and Securing.
Engine and systems operation.
Parking brake operation.
Rotor brake operation.
Abnormal/emergency procedures.
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8. Instructor Operating Station (IOS), as appropriate
8.a .................
8.b.1 ..............
8.b.2 ..............
8.b.3 ..............
8.b.4 ..............
8.c .................
8.c.1 ..............
8.c.2 ..............
8.c.3 ..............
8.c.4 ..............
8.d .................
8.d.1 ..............
8.d.2 ..............
8.d.3 ..............
8.e .................
8.e.1 ..............
8.e.2 ..............
8.f ..................
8.f.1 ...............
8.f.2 ...............
8.f.3 ...............
8.f.4 ...............
8.g .................
8.h .................
8.i ..................
8.i.1 ...............
8.i.2 ...............
Power Switch(es).
Helicopter conditions.
Gross weight, center of gravity, fuel loading and allocation, etc.
Helicopter system status.
Ground crew functions (e.g., ext. power).
Airports and landing areas.
Number and selection.
Runway or landing area selection.
Preset positions (e.g., ramp, over FAF).
Lighting controls.
Environmental controls.
Temperature.
Climate conditions (e.g., ice, rain).
Wind speed and direction.
Helicopter system malfunctions.
Insertion/deletion.
Problem clear.
Locks, Freezes, and Repositioning.
Problem (all) freeze/release.
Position (geographic) freeze/release.
Repositioning (locations, freezes, and releases).
Ground speed control.
Sound Controls. On/off / adjustment.
Control Loading System (as applicable On/off/emergency stop.)
Observer Stations.
Position.
Adjustments.
* ‘‘Autopilot’’ means attitude retention mode of operation.
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TABLE D3B—TABLE OF FUNCTIONS
AND SUBJECTIVE TESTS
Level 5 FTD
TABLE D3B—TABLE OF FUNCTIONS
AND SUBJECTIVE TESTS—Continued
Level 5 FTD
TABLE D3C.—TABLE OF FUNCTIONS
AND SUBJECTIVE TESTS—Continued
Level 4 FTD
<<< QPS Requirements >>>
<<< QPS Requirements >>>
<<< QPS Requirements >>>
Item No.
Item No.
Operations tasks
Operations tasks
Tasks in this table are subject to evaluation if
appropriate for the helicopter simulated as
indicated in the SOQ Configuration List
and/or for a Level 5 FTD. Items not installed or not functional on the FTD and,
therefore, not appearing on the SOQ Configuration List, are not required to be listed
as exceptions on the SOQ.
7.b. Preset positions (ground; air)
Operations tasks
6.d. Rotor brake operation.
1. Preflight Procedures
Item
number
1.a. Preflight Inspection (Cockpit Only)
switches, indicators, systems, and equipment.
1.b.
APU/Engine start and run-up.
1.b.1. ...
1.b.2. ...
1.b.3. ...
Normal start procedures.
Alternate start procedures.
Abnormal starts and shutdowns.
6.e. Abnormal/emergency procedures.
2. Normal and Abnormal Procedures (any
phase of flight).
7. Instructor Operating Station (IOS), as appropriate
2.a. Normal system operation (Installed
systems).
7.a. Power Switch(es).
2.b. Abnormal/Emergency system operation (installed systems).
7.c. Helicopter system malfunctions.
7.c.1. ...
7.c.2. ...
3. Postflight Procedures.
3.a. Parking and Securing.
Insertion / deletion.
Problem clear.
3.b. Engine and systems operation.
7.d. Control Loading System (as applicable
On / off / emergency stop.
7.e. ......
Observer Stations.
4. Instructor Operating Station (IOS), as
appropriate.
7.e1. ....
7.e.2. ...
2. Climb
3.c. Parking brake operation.
Position.
Adjustments.
4.a. Power Switch(es).
4.b. Preset positions (ground; air)
2.a. Normal.
TABLE D3C.—TABLE OF FUNCTIONS
AND SUBJECTIVE TESTS
3. Inflight Maneuvers
Level 4 FTD
3.a. Performance.
4.c. Helicopter system malfunctions.
4.c.1. ...
4.c.2. ...
Insertion / deletion.
Problem clear.
<<< QPS Requirements >>>
3.b. Turns, Normal.
Item
number
4. Instrument Procedures
4.a. Coupled instrument approach maneuvers (as applicable for the systems installed).
5. Normal and Abnormal Procedures (any
phase of flight)
5.a. Normal system operation (Installed systems).
5.b. Abnormal/Emergency system operation
(installed systems).
Operations tasks
Tasks in this table are subject to evaluation if
appropriate for the helicopter simulated as
indicated in the SOQ Configuration List
and/or for a Level 4 FTD. Items not installed or not functional on the FTD and,
therefore, not appearing on the SOQ Configuration List, are not required to be listed
as exceptions on the SOQ.
1. Preflight Procedures.
6. Postflight Procedures
1.a. Preflight Inspection (Cockpit Only)
switches, indicators, systems, and equipment.
6.a. Parking and Securing.
1.b. APU/Engine start and run-up.
6.b. Engine and systems operation.
1.b.1. ...
1.b.2. ...
1.b.3. ...
6.c. Parking brake operation.
Normal start procedures.
Alternate start procedures.
Abnormal starts and shutdowns.
Attachment 4 to Appendix D to Part 60—
Sample Documents
Table of Contents
Figure D4A—Sample Letter, Request for
Initial, Upgrade, or Reinstatement
Evaluation
Figure D4B—Attachment: FSTD Information
Form
Figure D4C—Sample Qualification Test
Guide Cover Page
Figure D4D—Sample Statement of
Qualification—Certificate
Figure D4E—Sample Statement of
Qualification—Configuration List
Figure D4F—Sample Statement of
Qualification—List of Qualified Tasks
Figure D4G—Sample Continuing
Qualification Evaluation Requirements
Page
Figure D4H—Sample MQTG Index of
Effective FSTD Directives
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Appendix E to Part 60—Qualification
Performance Standards for Quality
Management Systems for Flight
Simulation Training Devices
lllllllllllllllllllll
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Begin QPS Requirements
a. Not later than October 30, 2008 each
current sponsor of an FSTD must submit to
the NSPM a proposed Quality Management
System (QMS) program as described in this
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QPS appendix. The NSPM will review the
program in order of receipt and notify the
sponsor within 90 days of beginning the
review regarding the acceptability of the
program including any required adjustments.
Within 6 months of the notification of
acceptability, the sponsor must implement
the program, conduct internal audit(s), make
any required program adjustments as a result
of any internal audit, and have the NSPM
initial audit scheduled.
b. For first-time FSTD sponsors, not later
than 120 days prior to the date scheduled for
the initial FSTD evaluation, the sponsor must
submit to the NSPM the proposed QMS
program as described in this QPS appendix.
The NSPM will review the program and
notify the sponsor within 90 days of
beginning the review regarding the
acceptability of the program including any
required adjustments. Within 6 months of the
notification of acceptability, the sponsor
must implement the program, conduct
internal audit(s), make any required program
adjustments as a result of any internal audit,
and have the NSPM initial audit scheduled.
c. The Director of Operations for a Part 119
certificate holder, the Chief Instructor for a
Part 141 certificate holder, or the equivalent
for a Part 142 or Flight Engineer School
sponsor must designate a management
representative who has the responsibility and
authority to establish and modify the
sponsor’s policies, practices, and procedures
regarding the QMS program for the recurring
qualification and the day-to-day use of each
FSTD.
d. The minimum content required for an
acceptable QMS is found in Table E1. The
policies, processes, and/or procedures
described in this table must be maintained in
a Quality Manual and will serve as the basis
for the following:
(1) The sponsor-conducted initial and ongoing periodic assessments;
(2) The NSPM-conducted initial and ongoing periodic assessments; and
(3) The continuing surveillance and
analysis by the NSPM of the sponsor’s
performance and effectiveness in providing a
satisfactory FSTD for use on a regular basis.
End QPS Requirements
Begin Information
e. When a person sponsors an FSTD
maintained by a person other than a U.S.
certificate holder, the sponsor remains
responsible for the QMS program for that
FSTD; however—
(1) If that FSTD is maintained under a
qualification by a non-FAA regulatory
authority and that authority and the NSPM
have agreed to accept each other’s simulator
evaluations (e.g., under a Bilateral Aviation
Safety Agreement (BASA) and associated
Simulator Implementation Procedures (SIP),
such as the JAA of Europe), no additional
requirements are necessary for QMS
programs.
(2) If that FSTD is maintained under
qualification of a regulatory authority where
there is no BASA/SIP or that authority and
the NSPM have not agreed to accept each
other’s qualification programs, the NSPM
request additional information regarding
those aspects of the sponsor’s QMS program
for maintaining the qualification standards
for the FSTD.
End Information
lllllllllllllllllllll
Begin QPS Requirements
TABLE E1.—MINIMUM REQUIREMENTS FOR SATISFACTORY FSTD QUALITY MANAGEMENT SYSTEM
Information
(Reference)
Number
QPS requirement
E1.1. ............
E1.2. ............
A QMS manual that sets out the policies, processes, and/or procedures outlined in this table. ..
A policy, process, and/or procedure specifying how the sponsor will identify deficiencies in the
QMS.
A policy, process, and/or procedure specifying how the sponsor will document how the QMS
program will be changed to address deficiencies when found.
A policy, process, and/or procedure specifying how the sponsor will address proposed program
changes (for programs that do not meet the minimum requirements as notified by the NSPM)
to the NSPM and receive approval prior to their implementation.
A policy, process, and/or procedure specifying how the sponsor will document that at least one
FSTD is used within the sponsor’s FAA-approved flight training program for the aircraft or set
of aircraft at least once within the 12-month period following the initial/upgrade evaluation
conducted by the NSP and at least once within each subsequent 12-month period thereafter.
A policy, process, and/or procedure specifying how the sponsor will document that at least one
FSTD is used within the sponsor’s FAA-approved flight training program for the aircraft or set
of aircraft at least once within the 12-month period following the first continuing qualification
evaluation conducted by the NSP and at least once within each subsequent 12-month period
thereafter.
A policy, process, and/or procedure specifying how the sponsor will obtain an annual written
statement from a qualified pilot (after having flown the subject aircraft or set of aircraft during
the preceding 12-month period) that the performance and handling qualities of the subject
FSTD represents the subject aircraft or set of aircraft (within the normal operating envelope).
Required only if the subject FSTD is not used in the sponsor’s FAA-approved flight training
program for the aircraft or set of aircraft at least once within the preceding 12-month period.
A policy, process, and/or procedure specifying how independent feedback(from persons recently completing training, evaluation, or obtaining flight experience; instructors and check
airmen using the FSTD for training, evaluation or flight experience sessions; and FSTD technicians and maintenance personnel) will be received and addressed by the sponsor regarding the FSTD and its operation.
A policy, process, and/or procedure specifying how and where the FSTDStatement of Qualification will be posted, or accessed by an appropriate terminal or display, in or adjacent to
the FSTD.
A policy, process, and/or procedure specifying how the sponsor’s management representative
(MR) is selected and identified by name to the NSPM.
A policy, process, and/or procedure specifying the MR authority and responsibility for the following:
Monitoring the on-going qualification of assigned FSTDs to ensure all matters regarding FSTD
qualification are being carried out as provided for in 14 CFR part 60.
Ensuring that the QMS is properly established, implemented, and maintained by overseeing
the QMS policies, practices, and/or procedures and by and modifying when and where necessary.
Regularly briefing sponsor’s management on the status of the on-going FSTD qualification program and the effectiveness and efficiency of the QMS.
E1.3. ............
E1.4. ............
E1.5. ............
E1.6. ............
E1.7. ............
E1.8. ............
E1.9. ............
E1.10. ..........
E1.11. ..........
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E1.11.a. .......
E1.11.b. .......
E1.11.c. .......
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§ 60.5(a).
§ 60.5(b).
§ 60.5(b).
§ 60.5(c).
§ 60.7(b)(5).
§ 60.7(b)(6).
§ 60.5(b)(7) and § 60.7(d)(2).
§ 60.9(b)(1).
§ 60.9(b)(2).
§ 60.9(c) and appendix E, paragraph(d).
§ 60.9(c)(2), (3), and (4).
Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
63621
TABLE E1.—MINIMUM REQUIREMENTS FOR SATISFACTORY FSTD QUALITY MANAGEMENT SYSTEM—Continued
Information
(Reference)
Number
QPS requirement
E1.11.d. .......
Serving as the primary contact point for all matters between the sponsor and the NSPM regarding the qualification of assigned FSTDs.
Delegating the MR assigned duties to an individual at each of the sponsor’s locations, when/if/
where appropriate.
A policy, process, and/or procedure specifying how the sponsor will:.
Ensure that the data made available to the NSPM (the validation data package) includes the
aircraft manufacturer’s flight test data (or other data approved by the NSPM) and all relevant
data developed after the type certificate was issued (e.g., data developed in response to an
airworthiness directive) if such data results from a change in performance, handling qualities,
functions, or other characteristics of the aircraft that must be considered for flight crewmember training, evaluation, or for meeting experience requirements of this chapter;
Notify the NSPM within 10 working days of becoming aware that an addition to or a revision of
the flight related data or airplane systems related data is available if this data is used to program and/or operate a qualified FSTD; and
Maintain a liaison with the manufacturer of the aircraft being simulated (or with the holder of
the aircraft type certificate for the aircraft being simulated if the manufacturer is no longer in
business), and if appropriate, with the person having supplied the aircraft data package for
the FFS for the purposes of receiving notification of data package changes.
A policy, process, and/or procedure specifying how the sponsor will make available all special
equipment and qualified personnel needed to accomplish or assist in the accomplishment of
tests during initial, continuing qualification, or special evaluations.
A policy, process, and/or procedure specifying how the sponsor will submit to the NSPM a request to evaluate the FSTD for initial qualification at a specific level and simultaneously request the TPAA forward a concurring letter to the NSPM; including how the MR will use
qualified personnel to confirm the following:
That the performance and handling qualities of the FSTD represents those of the aircraft or set
of aircraft within the normal operating envelope;
E1.11.e. .......
E1.12. ..........
E1.12.a. .......
E1.12.b. .......
E1.12.c. .......
E1.13. ..........
E1.14. ..........
E1.14.a. .......
E1.14.b. .......
E1.14.c. .......
E1.15. ..........
E1.16. ..........
E1.17. ..........
E1.18. ..........
E1.19. ..........
E1.20. ..........
E1.21. ..........
E1.22. ..........
E1.23. ..........
E1.23.a. .......
E1.23.b. .......
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E1.24. ..........
E1.25. ..........
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The FSTD systems and sub-systems(including the simulated aircraft systems) functionally represent those in the aircraft or set of aircraft; and
The cockpit represents the configuration of the specific type or aircraft make, model, and series
aircraft being simulated, as appropriate.
A policy, process, and/or procedure specifying how, for an initial evaluation, all of the subjective tests and all of the objective tests are accomplished at the sponsor’s training facility, except as provided for in the applicable QPS.
A policy, process, and/or procedure specifying how, after the NSPM completes the evaluation
for initial qualification, the sponsor will update the QTG with the results of the FAA-witnessed
tests and demonstrations together with the results of all the objective tests and demonstrations described in the applicable QPS.
A policy, process, and/or procedure specifying how the sponsor will make the MQTG available
to the NSPM upon request.
A policy, process, and/or procedure specifying how the sponsor will and apply to the NSPM for
additional qualification(s) to the Statement of Qualification.
A policy, process, and/or procedure specifying how the sponsor accomplishes all applicable
QPS Attachment 2 objective tests each year in a minimum of four evenly spaced inspections
as specified in the applicable QPS.
A policy, process, and/or procedure specifying how the sponsor completes and records a functional preflight check of the FSTD within the preceding 24 hours of FSTD use, including a
description of the functional preflight.
A policy, process, and/or procedure specifying how the sponsor schedules with the NSPM continuing qualification evaluations not later than 60 days before the evaluation is due.
A policy, process, and/or procedure specifying how the sponsor ensures that the FSTD has received a continuing qualification evaluation at the interval as described in the respective
MQTG, allowing for the 1-month grace period before or after the calendar month required.
A policy, process, and/or procedure describing that when a discrepancy is discovered the following is recorded in the FSTD discrepancy log:
A description of each discrepancy is entered and remains in the log until the discrepancy is
corrected; and
A description of the corrective action taken for each discrepancy, the identity of the individual
taking the action, and the date that action is taken.
A policy, process, and/or procedure specifying how the discrepancy log is kept in a form and
manner acceptable to the Administrator and is kept in or adjacent to the FSTD. (An electronic log that may be accessed by an appropriate terminal or display in or adjacent to the
FSTD is satisfactory.)
A policy, process, and/or procedure that requires each instructor, check airman, or representative of the Administrator conducting training, evaluation, or flight experience, and each person conducting the preflight inspection, who discovers a discrepancy, including any missing,
malfunctioning, or inoperative components in the FSTD, to write or cause to be written a description of that discrepancy into the discrepancy log at the end of the FSTD preflight or
FSTD use session.
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§ 60.13; QPS appendices A, B,
C, and D.
§ 60.14.
§ 60.15(a)–(d); § 60.15(b);
§ 60.15(b)(i); § 60.15(b)(ii);
§ 60.15(b)(iii).
§ 60.15(e).
§ 60.15(h).
§ 60.15(i).
§ 60.16(a); § 60.16(a)(1)(i);
§ 60.16(a)(1)(ii).
§ 60.19(a)(1) QPS appendices
A, B, C, or D.
§ 60.19(a)(2) QPS appendices
A, B, C, or D.
§ 60.19(b)(2).
§ 60.19(b)(5)–(6).
§ 60.19(c); § 60.19(c)(2)(i);
§ 60.19(c)(2)(ii).
§ 60.19(c)(2)(iii).
§ 60.20.
63622
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TABLE E1.—MINIMUM REQUIREMENTS FOR SATISFACTORY FSTD QUALITY MANAGEMENT SYSTEM—Continued
Information
(Reference)
Number
QPS requirement
E1.26. ..........
A policy, process, and/or procedure specifying how the sponsor will (if operating an FSTD
based on an interim qualification), within twelve months of the release of the final aircraft
data package by the aircraft manufacturer (but no later than two years after the issuance of
the interim qualification status the sponsor) apply for initial qualification based on the final
aircraft data package approved by the aircraft manufacturer.
A policy, process, and/or procedure specifying how the sponsor determines whether an FSTD
change qualifies as a modification as described in 14 CFR part 60.
A policy, process, and/or procedure specifying how the sponsor will ensure the FSTD is modified in accordance with any FSTD Directive regardless of the original qualification basis.
A policy, process, and/or procedure specifying how, if an FSTD change is determined to be a
modification as defined in 14 CFR part 60, the sponsor will notify the NSPM and TPAA of
their intent to use the modified FSTD and to ensure that the modified FSTD will not be used
prior to:
Twenty-one days since the sponsor notified the NSPM and the TPAA of the proposed modification and the sponsor has not received any response from either the NSPM or the TPAA;
or
Twenty-one days since the sponsor notified the NSPM and the TPAA of the proposed modification and one has approved the proposed modification and the other has not responded;
or
The FSTD successfully completing any evaluation the NSPM may require in accordance with
the standards for an evaluation for initial qualification or any part thereof before the modified
FSTD is placed in service.
A policy, process, and/or procedure specifying how, after an FSTD modification is approved by
the NSPM, the sponsor will:
Post an addendum to the Statement of Qualification until such time as a permanent, updated
statement is received from the NSPM and posted;
Update the MQTG with current objective test results and appropriate objective data for each affected objective test or other MQTG section that is affected by the modification; and
File in the MQTG the direction to make the modification and the record of the modification
completion.
A policy, process, and/or procedure specifying how the sponsor will track the length of time a
component has been missing, malfunctioning, or inoperative (MMI), including:
How the sponsor will post a list of MMI components in or adjacent to the FSTD; and
E1.27. ..........
E1.28. ..........
E1.29. ..........
E1.29.a. .......
E1.29.b. .......
E1.29.c. .......
E1.30 ...........
E1.30.a. .......
E1.30.b. .......
E1.30.c. .......
E1.31. ..........
E1.31.a. .......
E1.31.b. .......
E1.32. ..........
E1.33. ..........
E1.33.a. .......
E1.33.b. .......
E1.33.c. .......
E1.33.d. .......
E1.33.e. .......
E1.33.f. ........
E1.33.g. .......
E1.33.g.1.
E1.33.g.2.
E1.33.g.3.
E1.33.g.4.
....
....
....
....
How the sponsor will notify the NSPM if the MMI has not been repaired or replaced within 30
days.*
A policy, process, and/or procedure specifying how the sponsor will notify the NSPM and how
the sponsor will seek requalification of the FSTD if the FSTD is moved and reinstalled in a
different location.
A policy, process, and/or procedure specifying how the sponsor will maintain control of the following: (The sponsor must specify how these records are maintained in plain language form
or in coded form; but if the coded form is used, the sponsor must specify how the preservation and retrieval of information will be conducted.)
The MQTG and each amendment thereto;
A record of all FSTD modifications required by this part since the issuance of the original
Statement of Qualification;
Results of the qualification evaluations (initial and each upgrade) since the issuance of the
original Statement of Qualification;
Results of the objective tests conducted in accordance with this part for a period of 2 years;
Results of the previous three continuing qualification evaluations, or the continuing qualification
evaluations from the previous 2 years, whichever covers a longer period;
Comments obtained in accordance with Section 60.9(b);
A record of all discrepancies entered in the discrepancy log over the previous 2 years, including the following:
A list of the components or equipment that were or are missing, malfunctioning, or inoperative;
The action taken to correct the discrepancy;
The date the corrective action was taken; and
The identity of the person determining that the discrepancy has been corrected.
§ 60.21(c).
§ 60.23(a)(1)–(2).
§ 60.23(b).
§ 60.23(c)(1)(i),(ii), and (iv).
§ 60.23(d)–(e).
§ 60.25(b)–(c), and QPS appendices A, B, C, or D.
§ 60.27(a)(3).
§ 60.31.
*Note 1.—If the sponsor has an approved discrepancy prioritization system, this item is satisfied by describing how discrepancies are
prioritized, what actions are taken, and how the sponsor will notify the NSPM if the MMI has not been repaired or replaced within the specified
timeframe.
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End QPS Requirements
lllllllllllllllllllll
Begin Information
f. Table E2 contains a sample Assessment
Tool that the NSPM will use when
conducting the desk assessment of a
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sponsor’s request for initial evaluation of the
required elements of a QMS program.
g. Table E3 contains a sample Assessment
Tool that the NSPM will use when
conducting the on-site practical evaluation of
a sponsor’s request for initial and continuing
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evaluation of the required elements of a QMS
program.
h. Table E4 contains a sample Assessment
Tool that the NSPM will use when
conducting the desk assessment of a
sponsor’s request for initial evaluation of the
voluntary elements of a QMS program.
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i. Table E5 contains a sample Assessment
Tool that will be used by the NSPM when
conducting the on-site practical evaluation of
a sponsor’s request for initial and continuing
evaluation of the voluntary elements of a
QMS program.
j. Additional Information.
(1) In addition to specifically designated
QMS evaluations, the NSPM will evaluate
the sponsor’s QMS program as part of
regularly scheduled FSTD continuing
qualification evaluations and no-notice FSTD
evaluations, focusing in part on the
effectiveness and viability of the QMS
program and its contribution to the overall
capability of the FSTD to meet the
requirements of this part.
(2) The sponsor, through the MR, may
delegate duties associated with maintaining
the qualification of the FSTD (e.g., corrective
and preventive maintenance, scheduling for
and the conducting of tests and/or
inspections, functional preflight checks) but
retains the responsibility and authority for
the day-to-day qualification of the FSTD. One
person may serve in this capacity for more
than one FSTD, but one FSTD would not
have more than one person serving in this
capacity.
(3) The QMS requirements should not be
interpreted to preclude a given QMS program
from being applicable to more than one
certificate holder (e.g., part 119 and part 142
or two part 119 certificate holders) and
should not be interpreted to preclude an
individual from being a Management
Representative (MR) for more than one
certificate holder (e.g., part 119 and part 142
or two part 119 certificate holders) as long as
the other QMS program requirements and the
other MR requirements are respectively met
for each such certificate holder.
(4) Standard Measurements for Flight
Simulator Quality: A quality system tied to
measurement of FSTD performance will
improve and maintain training quality. One
acceptable means of measuring FSTD
performance is ARINC report 433 (as
amended), entitled ‘‘Standard Measurements
for Flight Simulator Quality. ARINC report
433 is a widely accepted industry standard.
(6) The NSPM will use the results of the
assessment(s) of the voluntary portions of the
QMS program (as described in Tables E4 and
E5) to determine whether or not a sponsor or
a FSTD may have the interval between
NSPM-conducted evaluations extended and
what the extension might be.
k. While the FAA does not mandate any
specific QMS program format, the following
subparagraphs outline those factors that
would be typically found in an acceptable
QMS program.
(1) Establishment of a Quality Policy. This
is a formal written Quality Policy Statement
that is a commitment by the sponsor
outlining what the Quality System will
achieve.
(2) The selected MR should be someone
who has overall authority and responsibility
for monitoring the on-going qualification of
assigned FSTDs to ensure that all matters
regarding FSTD qualification are being
carried out as required by this part and
ensuring that the QMS program is properly
established, implemented, and maintained.
The MR should regularly:
63623
(i) Brief the sponsor’s management
regarding the status of on-going qualification
processes; and
(ii) Serve as the primary contact point for
all matters between the sponsor and the
NSPM regarding the qualification of the
assigned FSTDs.
(iii) Oversee the day-to-day quality control.
(3) The system and processes outlined in
the QMS should enable the sponsor to
monitor compliance with all applicable
regulations and ensure correct maintenance
and performance of the FSTD.
(4) A QMS program, together with a
statement acknowledging completion of a
periodic review by the MR, should include
the following:
(i) A maintenance facility that provides
suitable FSTD hardware and software tests
and maintenance capability.
(ii) A recording system in the form of a
technical log in which defects, deferred
defects, and development projects are listed,
assigned and reviewed within a specified
time period.
(iii) Routine maintenance of the FSTD and
performance of the QTG tests with adequate
staffing to cover FSTD operating periods.
(iv) A planned internal assessment
schedule and a periodic review should be
used to verify that corrective action was
complete and effective. The assessor should
have adequate knowledge of FSTDs and
should be acceptable to the NSPM.
(5) The MR should receive appropriate
Quality System training and brief other
personnel on the procedures.
TABLE E2.—INFORMATION SIMULATION QUALITY MANAGEMENT SYSTEM (SQMS) ASSESSMENT TOOL—INITIAL (DESK)
Basic (Part 60 required) elements
Rating
see element assessment table
Element No.
Does the sponsor have . . .
N
E.2.1 ..................................................
E.2.2 ..................................................
E.2.3 ..................................................
E.2.4 ..................................................
E.2.5 ..................................................
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E.2.6 ..................................................
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A QMS program approved by the NSPM including a Quality Management System Manual that sets out the policies, processes, and/or procedures required by 14 CFR part 60 and part 60, appendix E.
A policy, process, and/or procedure specifying how the sponsor will
identify deficiencies in the QMS.
A policy, process, and/or procedure specifying how the sponsor will document how the QMS program will be changed to address deficiencies
when found.
A policy, process, and/or procedure specifying how the sponsor will propose program changes to the NSPM and receive approval prior to
their implementation.
A policy, process, and/or procedure specifying how the sponsor will document that at least one FSTD is used within the sponsor’s FAA-approved flight training program for the aircraft or set of aircraft at least
once within the 12-month period following the initial/upgrade evaluation conducted by the NSP and at least once within each subsequent
12-month period thereafter.
A policy, process, and/or procedure specifying how the sponsor will document that at least one FSTD is used within the sponsor’s FAA-approved flight training program for the aircraft or set of aircraft at least
once within the 12-month period following the first continuing qualification evaluation conducted by the NSP and at least once within each
subsequent 12-month period thereafter.
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63624
Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
TABLE E2.—INFORMATION SIMULATION QUALITY MANAGEMENT SYSTEM (SQMS) ASSESSMENT TOOL—INITIAL (DESK)—
Continued
Basic (Part 60 required) elements
Rating
see element assessment table
Element No.
Does the sponsor have . . .
N
E.2.7 ..................................................
E.2.8 ..................................................
E.2.9 ..................................................
E.2.10 ................................................
E.2.11 ................................................
E.2.11.a .............................................
E.2.11.b .............................................
E.2.11.c .............................................
E.2.11.d .............................................
E.2.11.e .............................................
E.2.12 ................................................
E.2.12.a .............................................
E.2.12.b .............................................
E.2.12.c .............................................
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E.2.13. ...............................................
E.2.14 ................................................
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A policy, process, and/or procedure specifying how the sponsor will obtain an annual written statement from a qualified pilot (after having
flown the subject aircraft or set of aircraft during the preceding 12month period) that the performance and handling qualities of the subject FSTD represents the subject aircraft or set of aircraft (within the
normal operating envelope). Required only if the subject FSTD is not
used in the sponsor’s FAA-approved flight training program for the aircraft or set of aircraft at least once within the preceding 12-month period.
A policy, process, and/or procedure specifying how independent feedback (from persons recently completing training, evaluation, or obtaining flight experience; instructors and check airmen using the FSTD for
training, evaluation or flight experience sessions; and FSTD technicians and maintenance personnel) will be received and addressed by
the sponsor regarding the FSTD and its operation.
A policy, process, and/or procedure specifying how and where the
FSTD Statement of Qualification will be posted, or accessed by an
appropriate terminal or display, in or adjacent to the FSTD.
A policy, process, and/or procedure specifying how the sponsor’s management representative (MR) is selected and identified by name to
the NSPM.
A policy, process, and/or procedure specifying the MR’s authority and
responsibility for the following:
Monitoring the on-going qualification of assigned FSTDs to ensure all
matters regarding FSTD qualification are being carried out as provided for in 14 CFR part 60.
Ensuring that the QMS is properly established, implemented, and maintained by overseeing the QMS policies, practices, and/or procedures
and by and modifying when and where necessary.
Regularly briefing sponsor’s management on the status of the on-going
FSTD qualification program and the effectiveness and efficiency of the
QMS. (designate maximum interval).
Serving as the primary contact point for all matters between the sponsor
and the NSPM regarding the qualification of assigned FSTDs.
Delegating the MR assigned duties to an individual at each of the sponsor’s locations, when/if/where appropriate.
A policy, process, and/or procedure specifying how the sponsor will:
Ensure that the data made available to the NSPM (the validation data
package) includes the aircraft manufacturer’s flight test data (or other
data approved by the NSPM) and all relevant data developed after
the type certificate was issued (e.g., data developed in response to an
airworthiness directive) if such data results from a change in performance, handling qualities, functions, or other characteristics of the aircraft that must be considered for flight crew member training, evaluation, or for meeting experience requirements of this chapter.
Immediately notify the NSPM when an addition to or a revision of the
flight related data or airplane systems related data is available if this
data is used to program and/or operate a qualified FFS, including
technical information about this data to the NSPM relative to the
data’s significance for training, evaluation, or flight experience activities in the FFS.
Maintain a liaison with the manufacturer of the aircraft being simulated
(or with the holder of the aircraft type certificate for the aircraft being
simulated if the manufacturer is no longer in business), and/or, if appropriate, with the person having supplied the aircraft data package
for the FFS for the purposes of receiving notification of data package
changes..
A policy, process, and/or procedure specifying how the sponsor will
make available all special equipment and qualified personnel needed
to accomplish or assist in the accomplishment of tests during initial,
continuing qualification, or special evaluations.
A policy, process, and/or procedure specifying how the sponsor will submit to the NSPM a request to evaluate the FSTD for initial qualification at a specific level and simultaneously request the TPAA forward a
concurring letter to the NSPM; including how the MR will use qualified
personnel to confirm the following:
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63625
TABLE E2.—INFORMATION SIMULATION QUALITY MANAGEMENT SYSTEM (SQMS) ASSESSMENT TOOL—INITIAL (DESK)—
Continued
Basic (Part 60 required) elements
Rating
see element assessment table
Element No.
Does the sponsor have . . .
N
E.2.14.a .............................................
E.2.14.b .............................................
E.2.14.c .............................................
E.2.15 ................................................
E.2.16 ................................................
E.2.17 ................................................
E.2.18 ................................................
E.2.19 ................................................
E.2.20 ................................................
E.2.21 ................................................
E.2.22 ................................................
E.2.23 ................................................
E.2.23.a .............................................
E.2.23.b .............................................
E.2.24 ................................................
E.2.25 ................................................
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E.2.26 ................................................
E.2.27 ................................................
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That the performance and handling qualities of the FSTD represents
those of the aircraft or set of aircraft within the normal operating envelope.
The FSTD systems and sub-systems (including the simulated aircraft
systems) functionally represent those in the aircraft or set of aircraft.
The cockpit represents the configuration of the specific type; or aircraft
make, model, and series aircraft being simulated, as appropriate.
A policy, process, and/or procedure specifying how, for an initial evaluation, all of the subjective tests and all of the objective tests are accomplished at the sponsor’s training facility, except as provided for in
the applicable QPS.
A policy, process, and/or procedure specifying how, after the NSPM
completes the evaluation for initial qualification, the sponsor will update the QTG with the results of the FAA-witnessed tests and demonstrations together with the results of all the objective tests and demonstrations described in the applicable QPS.
A policy, process, and/or procedure specifying how the sponsor will
make the MQTG available to the NSPM upon request.
A policy, process, and/or procedure specifying how the sponsor will
apply to the NSPM to add (an) additional qualification(s) to the Statement of Qualification.
A policy, process, and/or procedure specifying how the sponsor accomplishes all applicable QPS Attachment 2 objective tests each year in a
minimum of four evenly spaced inspections as specified in the applicable QPS.
A policy, process, and/or procedure specifying how the sponsor completes a functional preflight check of the FSTD within the preceding
24 hours of FSTD use.
A policy, process, and/or procedure specifying how the sponsor schedules with the NSPM continuing qualification evaluations not later than
60 days before the evaluation is due.
A policy, process, and/or procedure specifying how the sponsor ensures
that the FSTD has received a continuing qualification evaluation at the
interval as described in the respective MQTG, allowing for the 1month grace period before or after the calendar month required.
A policy, process, and/or procedure describing that when a discrepancy
is discovered the following is recorded in the FSTD discrepancy log:
A description of each discrepancy is entered and remains in the log until
the discrepancy is corrected.
A description of the corrective action taken for each discrepancy, the
identity of the individual taking the action, and the date that action is
taken.
A policy, process, and/or procedure specifying how the discrepancy log
is kept in a form and manner acceptable to the Administrator and is
kept in or adjacent to the FSTD. (An electronic log that may be
accessed by an appropriate terminal or display in or adjacent to the
FSTD is satisfactory.)
A policy, process, and/or procedure that requires each instructor, check
airman, or representative of the Administrator conducting training,
evaluation, or flight experience for flight crew members, and each person conducting the preflight inspection, who discovers a discrepancy,
including any missing, malfunctioning, or inoperative components in
the FSTD, to write or cause to be written a description of that discrepancy into the discrepancy log at the end of the FSTD preflight or
FSTD use session.
A policy, process, and/or procedure specifying how the sponsor will (if
operating an FSTD based on an interim qualification), within twelve
months of the release of the final aircraft data package by the aircraft
manufacturer (but no later than two years after the issuance of the interim qualification status the sponsor) apply for initial qualification
based on the final aircraft data package approved by the aircraft manufacturer.
A policy, process, and/or procedure specifying how the sponsor determines whether an FSTD change qualifies as a modification as described in 14 CFR part 60.
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TABLE E2.—INFORMATION SIMULATION QUALITY MANAGEMENT SYSTEM (SQMS) ASSESSMENT TOOL—INITIAL (DESK)—
Continued
Basic (Part 60 required) elements
Rating
see element assessment table
Element No.
Does the sponsor have . . .
N
E.2.28 ................................................
E.2.29 ................................................
E.2.29.a .............................................
E.2.29.b .............................................
E.2.29.c .............................................
E.2.30 ................................................
E.2.30.a .............................................
E.2.30.b .............................................
E.2.30.c .............................................
E.2.31 ................................................
E.2.31.a .............................................
E.2.31.b .............................................
E.2.32 ................................................
E.2.33 ................................................
E.2.33.a .............................................
E.2.33.b .............................................
E.2.33.c .............................................
E.2.33.d. ............................................
E.2.33.e .............................................
E.2.33.f ..............................................
E.2.33.g .............................................
sroberts on PROD1PC70 with RULES
E.2.33.g.1 ..........................................
E.2.33.g.2 ..........................................
E.2.33.g.3 ..........................................
E.2.33.g.4 ..........................................
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A policy, process, and/or procedure specifying how the sponsor will ensure the FSTD is modified in accordance with any FSTD Directive regardless of the original qualification basis.
A policy, process, and/or procedure specifying how, if an FSTD change
is determined to be a modification as defined in 14 CFR part 60, the
sponsor will notify the NSPM and TPAA of their intent to use the
modified FSTD and to ensure that the modified FSTD will not be used
prior to:
Twenty-one days since the sponsor notified the NSPM and the TPAA of
the proposed modification and the sponsor has not received any response from either the NSPM or the TPAA.
Twenty-one days since the sponsor notified the NSPM and the TPAA of
the proposed modification and one has approved the proposed modification and the other has not responded.
The FSTD successfully completing any evaluation the NSPM may require in accordance with the standards for an evaluation for initial
qualification or any part thereof before the modified FSTD is placed in
service.
A policy, process, and/or procedure specifying how, after a FSTD modification is approved by the NSPM, the sponsor will:
Post an addendum to the Statement of Qualification until such time as a
permanent, updated statement is received from the NSPM and posted.
Update the MQTG with current objective test results and appropriate objective data for each affected objective test or other MQTG section
that is affected by the modification.
File in the MQTG the direction to make the modification and the record
of the modification completion.
A policy, process, and/or procedure specifying how the sponsor will
track the length of time a component has been missing, malfunctioning, or inoperative (MMI), including:
How the sponsor will post a list of MMI components in or adjacent to the
FSTD.
How the sponsor will notify the NSPM if the MMI has not been repaired
or replaced within 30 days; or if the sponsor has a discrepancy
prioritization system, describe how discrepancies are prioritized and
how the sponsor will notify the NSPM if the MMI has not been repaired or replaced within the specified timeframe.
A policy, process, and/or procedure specifying how the sponsor will notify the NSPM and how the sponsor will seek re-qualification of the
FSTD if the FSTD is moved and reinstalled in a different location.
A policy, process, and/or procedure specifying how the sponsor will
maintain control of the following documents: [The sponsor must specify how these records are maintained in plain language form or in
coded form; but if the coded form is used, the sponsor must specify
how the preservation and retrieval of information will be conducted.]
The MQTG and each amendment thereto.
A record of all FSTD modifications required by this part since the
issuance of the original Statement of Qualification.
Results of the qualification evaluations (initial and each upgrade) since
the issuance of the original Statement of Qualification..
Results of the objective tests conducted in accordance with this part for
a period of 2 years.
Results of the previous three continuing qualification evaluations, or the
continuing qualification evaluations from the previous 2 years, whichever covers a longer period.
Comments obtained in accordance with this part for a period of at least
90 days.
A record of all discrepancies entered in the discrepancy log over the
previous 2 years, including the following:
A list of the components or equipment that were or are missing, malfunctioning, or inoperative.
The action taken to correct the discrepancy.
The date the corrective action was taken.
The identity of the person determining that the discrepancy has been
corrected.
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
TABLE E.3.—INFORMATION (SQMS) ASSESSMENT TOOL—ON-SITE
Element
number
Rating
See Element
Assessment
Table
Basic (Part 60 Required) Elements
N
There is evidence that the element is: (1) Being utilized/applied as is appropriate/necessary;
(2) Being utilized/applied as stated/specified/defined in the QMS;
(3) Achieving/producing effective results.
E.3.1. .........
The Quality Management System Manual sets our current QMS policies, processes and/or procedures.
E.3.2. .........
The policy, process, and/or procedure specifying how the sponsor will identify deficiencies in the
QMS.
The policy, process, and/or procedure specifying how the sponsor will document how the QMS
program will be changed to address deficiencies when found.
The policy, process, and/or procedure specifying how the sponsor will propose program changes to
the NSPM and receive approval prior to their implementation.
The policy, process, and/or procedure specifying how the sponsor will document that at least one
FSTD is used within the sponsor’s FAA-approved flight training program for the aircraft or set of
aircraft at least once within the 12-month period following the initial/upgrade evaluation conducted by the NSP and at least once within each subsequent 12-month period thereafter.
The policy, process, and/or procedure specifying how the sponsor will document that at least one
FSTD is used within the sponsor’s FAA-approved flight training program for the aircraft or set of
aircraft at least once within the 12-month period following the first continuing qualification evaluation conducted by the NSP and at least once within each subsequent 12-month period thereafter.
The policy, process, and/or procedure specifying how the sponsor will obtain an annual written
statement from a qualified pilot (after having flown the subject aircraft or set of aircraft during the
preceding 12-month period) that the performance and handling qualities of the subject FSTD
represents the subject aircraft or set of aircraft (within the normal operating envelope). Required
only if the subject FSTD is not used in the sponsor’s FAA-approved flight training program for
the aircraft or set of aircraft at least once within the preceding 12-month period.
A policy, process, and/or procedure specifying how independent feedback (from persons recently
completing training, evaluation, or obtaining flight experience; instructors and check airmen using
the FSTD for training, evaluation or flight experience sessions; and FSTD technicians and maintenance personnel) will be received and addressed by the sponsor regarding the FSTD and its
operation.
The policy, process, and/or procedure specifying how and where the FSTD Statement of Qualification will be posted, or accessed by an appropriate terminal or display, in or adjacent to the FSTD.
The policy, process, and/or procedure specifying how the sponsor’s management representative
(MR) is selected and identified by name to the NSPM.
The policy, process, and/or procedure specifying the MR’s authority and responsibility for the following:
Monitoring the on-going qualification of assigned FSTDs to ensure all matters regarding FSTD
qualification are being carried out as provided for in 14 CFR part 60.
Ensuring that the QMS is properly established, implemented, and maintained by overseeing the
QMS policies, practices, and/or procedures and by and modifying when and where necessary.
Regularly briefing sponsor’s management on the status of the on-going FSTD qualification program
and the effectiveness and efficiency of the QMS. (designate maximum interval).
Serving as the primary contact point for all matters between the sponsor and the NSPM regarding
the qualification of assigned FSTDs.
Delegating the MR assigned duties to an individual at each of the sponsor’s locations, when/if/
where appropriate.
A policy, process, and/or procedure specifying how the sponsor will:
Ensure that the data made available to the NSPM (the validation data package) includes the aircraft manufacturer’s flight test data (or other data approved by the NSPM) and all relevant data
developed after the type certificate was issued (e.g., data developed in response to an airworthiness directive) if such data results from a change in performance, handling qualities, functions,
or other characteristics of the aircraft that must be considered for flight crew member training,
evaluation, or for meeting experience requirements of this chapter.
Immediately notify the NSPM when an addition to or a revision of the flight related data or airplane
systems related data is available if this data is used to program and/or operate a qualified FFS,
including technical information about this data to the NSPM relative to the data’s significance for
training, evaluation, or flight experience activities in the FFS.
Maintain a liaison with the manufacturer of the aircraft being simulated (or with the holder of the
aircraft type certificate for the aircraft being simulated if the manufacturer is no longer in business), and/or, if appropriate, with the person having supplied the aircraft data package for the
FFS for the purposes of receiving notification of data package changes.
A policy, process, and/or procedure specifying how the sponsor will make available all special
equipment and qualified personnel needed to accomplish or assist in the accomplishment of
tests during initial, continuing qualification, or special evaluations.
E.3.3. .........
E.3.4. .........
E.3.5. .........
E.3.6. .........
E.3.7. .........
E.3.8. .........
E.3.9. .........
E.3.10. .......
E.3.11. .......
E.3.11.a. ....
E.3.11.b. ....
E.3.11.c. .....
E.3.11.d. ....
E.3.11.e. ....
E.3.12. .......
E.3.12.a. ....
E.3.12.b. ....
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E.3.12.c. .....
E.3.13. .......
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TABLE E.3.—INFORMATION (SQMS) ASSESSMENT TOOL—ON-SITE—Continued
Element
number
Rating
See Element
Assessment
Table
Basic (Part 60 Required) Elements
N
E.3.14. .......
E.3.14.a. ....
E.3.14.b. ....
E.3.14.c. .....
E.3.15. .......
E.3.16. .......
E.3.17. .......
E.3.18. .......
E.3.19. .......
E.3.20. .......
E.3.21. .......
E.3.22. .......
E.3.23. .......
E.3.23.a. ....
E.3.23.b. ....
E.3.24 ........
E.3.25. .......
E.3.26. .......
E.3.27. .......
E.3.28. .......
E.3.29. .......
sroberts on PROD1PC70 with RULES
E.3.29.a. ....
E.3.29.b. ....
E.3.29.c. .....
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A policy, process, and/or procedure specifying how the sponsor will submit to the NSPM a request
to evaluate the FSTD for initial qualification at a specific level and simultaneously request the
TPAA forward a concurring letter to the NSPM; including how the MR will use qualified personnel to confirm the following:
That the performance and handling qualities of the FSTD represent those of the aircraft or set of
aircraft within the normal operating envelope.
The FSTD systems and sub-systems (including the simulated aircraft systems) functionally represent those in the aircraft or set of aircraft.
The cockpit represents the configuration of the specific type; or aircraft make, model, and series
aircraft being simulated, as appropriate.
A policy, process, and/or procedure specifying how, for an initial evaluation, all of the subjective
tests and all of the objective tests are accomplished at the sponsor’s training facility, except as
provided for in the applicable QPS.
A policy, process, and/or procedure specifying how, after the NSPM completes the evaluation for
initial qualification, the sponsor will update the QTG with the results of the FAA-witnessed tests
and demonstrations together with the results of all the objective tests and demonstrations described in the applicable QPS.
A policy, process, and/or procedure specifying how the sponsor will make the MQTG available to
the NSPM upon request.
A policy, process, and/or procedure specifying how the sponsor will apply to the NSPM to add (an)
additional qualification(s) to the Statement of Qualification.
A policy, process, and/or procedure specifying how the sponsor accomplishes all applicable QPS
Attachment 2 objective tests each year in a minimum of four evenly spaced inspections as specified in the applicable QPS.
A policy, process, and/or procedure specifying how the sponsor completes a functional preflight
check of the FSTD within the preceding 24 hours of FSTD use.
A policy, process, and/or procedure specifying how the sponsor schedules with the NSPM continuing qualification evaluations not later than 60 days before the evaluation is due.
A policy, process, and/or procedure specifying how the sponsor ensures that the FSTD has received a continuing qualification evaluation at the interval as described in the respective MQTG,
allowing for the 1-month grace period before or after the calendar month required.
A policy, process, and/or procedure describing that when a discrepancy is discovered the following
is recorded in the FSTD discrepancy log:
A description of each discrepancy is entered and remains in the log until the discrepancy is corrected.
A description of the corrective action taken for each discrepancy, the identity of the individual taking the action, and the date that action is taken.
A policy, process, and/or procedure specifying how the discrepancy log is kept in a form and manner acceptable to the Administrator and is kept in or adjacent to the FSTD. (An electronic log
that may be accessed by an appropriate terminal or display in or adjacent to the FSTD is satisfactory.).
A policy, process, and/or procedure that requires each instructor, check airman, or representative
of the Administrator conducting training, evaluation, or flight experience for flight crew members,
and each person conducting the preflight inspection, who discovers a discrepancy, including any
missing, malfunctioning, or inoperative components in the FSTD, to write or cause to be written
a description of that discrepancy into the discrepancy log at the end of the FSTD preflight or
FSTD use session.
A policy, process, and/or procedure specifying how the sponsor will (if operating an FSTD based
on an interim qualification), within twelve months of the release of the final aircraft data package
by the aircraft manufacturer (but no later than two years after the issuance of the interim qualification status the sponsor) apply for initial qualification based on the final aircraft data package
approved by the aircraft manufacturer.
A policy, process, and/or procedure specifying how the sponsor determines whether an FSTD
change qualifies as a modification as described in 14 CFR part 60..
A policy, process, and/or procedure specifying how the sponsor will ensure the FSTD is modified in
accordance with any FSTD Directive regardless of the original qualification basis.
A policy, process, and/or procedure specifying how, if an FSTD change is determined to be a
modification as defined in 14 CFR part 60, the sponsor will notify the NSPM and TPAA of their
intent to use the modified FSTD and to ensure that the modified FSTD will not be used prior to:
Twenty-one days since the sponsor notified the NSPM and the TPAA of the proposed modification
and the sponsor has not received any response from either the NSPM or the TPAA.
Twenty-one days since the sponsor notified the NSPM and the TPAA of the proposed modification,
and one has approved the proposed modification and the other has not responded.
The FSTD successfully completing any evaluation the NSPM may require in accordance with the
standards for an evaluation for initial qualification or any part thereof before the modified FSTD
is placed in service.
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
TABLE E.3.—INFORMATION (SQMS) ASSESSMENT TOOL—ON-SITE—Continued
Element
number
Rating
See Element
Assessment
Table
Basic (Part 60 Required) Elements
N
E.3.30. .......
E.3.30.a. ....
E.3.30.b. ....
E.3.30.c. .....
E.3.31. .......
E.3.31.a. ....
E.3.31.b. ....
E.3.32. .......
E.3.33. .......
E.3.33.a. ....
E.3.33.b. ....
E.3.33.c. .....
E.3.33.d. ....
E.3.33.e. ....
E.3.33.f. .....
E.3.33.g. ....
E.3.33.g.1.
E.3.33.g.2.
E.3.33.g.3.
E.3.33.g.4.
P
Comments
Y
A policy, process, and/or procedure specifying how, after a FSTD modification is approved by the
NSPM, the sponsor will:
Post an addendum to the Statement of Qualification until such time as a permanent, updated statement is received from the NSPM and posted.
Update the MQTG with current objective test results and appropriate objective data for each affected objective test or other MQTG section that is affected by the modification.
File in the MQTG the direction to make the modification and the record of the modification completion.
A policy, process, and/or procedure specifying how the sponsor will track the length of time a component has been missing, malfunctioning, or inoperative (MMI), including:
How the sponsor will post a list of MMI components in or adjacent to the FSTD.
How the sponsor will notify the NSPM if the MMI has not been repaired or replaced within 30 days;
or if the sponsor has a discrepancy prioritization system, describe how discrepancies are
prioritized and how the sponsor will notify the NSPM if the MMI has not been repaired or replaced within the specified timeframe.
A policy, process, and/or procedure specifying how the sponsor will notify the NSPM and how the
sponsor will seek re-qualification of the FSTD if the FSTD is moved and reinstalled in a different
location.
A policy, process, and/or procedure specifying how the sponsor will maintain control of the following documents: The sponsor must specify how these records are maintained in plain language form or in coded form; but if the coded form is used, the sponsor must specify how the
preservation and retrieval of information will be conducted.].
The MQTG and each amendment thereto.
A record of all FSTD modifications required by this part since the issuance of the original Statement of Qualification.
Results of the qualification evaluations (initial and each upgrade) since the issuance of the original
Statement of Qualification.
Results of the objective tests conducted in accordance with this part for a period of 2 years.
Results of the previous three continuing qualification evaluations, or the continuing qualification
evaluations from the previous 2 years, whichever covers a longer period.
Comments obtained in accordance with this part for a period of at least 90 days.
A record of all discrepancies entered in the discrepancy log over the previous 2 years, including
the following:
A list of the components or equipment that were or are missing, malfunctioning, or inoperative.
The action taken to correct the discrepancy.
The date the corrective action was taken.
The identity of the person determining that the discrepancy has been corrected.
TABLE E.4.—INFORMATION SQMS ASSESSMENT TOOL—INITIAL (DESK)
EXPANDED (voluntary) elements
Element
number
Rating
see element assessment table
Does the sponsor have . . .
N
QUALITY MANAGEMENT SYSTEM MANUAL:
V.4.1. .....
V.4.1.a. ..
V.4.1.a.1.
V.4.1.a.2.
V.4.1.a.3.
V.4.2. .....
Quality Management System Manual documentation includes:
The scope of the SQMS, including:
Responsibilities Matrix, or the equivalent, designating responsibility, by position, name or title, for approval and control of SQMS functions/elements.
Documented SQMS policies, processes and procedures listed in V.4.10, or reference to them.
A description of the sequence and interaction of the documented SQMS processes.
Quality Management System Manual established as a controlled document that includes provision for
identification of current revision status and the date of last revision imprinted on each page concerned.
sroberts on PROD1PC70 with RULES
QUALITY POLICY AND QUALITY OBJECTIVES:
V.4.3. .....
V.4.3.a. ..
V.4.3.b. ..
V.4.3.c. ..
V.4.4. .....
V.4.4.a. ..
A quality policy that:
Is appropriate to the purpose of the organization.
Includes the concept of continual SQMS improvement.
Provides a framework for establishing and reviewing quality objectives.
Quality objectives that:
Have been established for relevant SQMS functions at relevant levels within the organization.
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
TABLE E.4.—INFORMATION SQMS ASSESSMENT TOOL—INITIAL (DESK)—Continued
EXPANDED (voluntary) elements
Element
number
Rating
see element assessment table
Does the sponsor have . . .
N
V.4.4.b. ..
V.4.4.c. ..
Include the ultimate objective of providing the continuous presentation of a qualified FSTD, or FSTDs,
for credible flight training, evaluation and/or meeting experience requirements.
Are measurable and consistent with the Quality Policy.
MANAGEMENT COMMITMENT:
V.4.5. .....
V.4.5.a. ..
V.4.5.b. ..
V.4.5.c. ..
V.4.5.d. ..
V.4.5.e. ..
V.4.5.e.1.
V.4.5.e.2.
V.4.5.f. ...
V.4.5.g. ..
A policy, process, and/or procedure that specifies how management will:
Ensure that the quality policy is communicated and understood at appropriate levels of the organization.
Ensure that employees are aware of the relevance and importance of their activities and how they
contribute to the achievement of the quality objectives.
Ensure that the resources (human and financial) necessary to achieve the quality objectives are identified, planned and available.
Document management resource planning output.
Conduct and record periodic management reviews (stated minimum interval required) to:
(1) Evaluate planned resource allocation and ...........................................................................................
(2) Take action to ensure continuing suitability and effectiveness of the:.
Quality policy.
Quality objectives.
Verify implementation of proper corrective action/managed change on assessment deficiencies.
Record the results of corrective action/managed change on assessment deficiencies and report the
results to the NSPM.
DOCUMENT/RECORD CONTROL
V.4.6. .....
V.4.7. .....
V.4.7.a. ..
V.4.7.b. ..
V.4.7.c. ..
V.4.7.d. ..
V.4.7.e. ..
V.4.7.f. ...
V.4.7.g. ..
V.4.7.h. ..
V.4.8. .....
V.4.8.a.
V.4.8.b.
V.4.8.c.
V.4.8.d.
..
..
..
..
A Master List of internal and external documents that are actively utilized in the SQMS to ensure effective operation and control of the processes (identified, as applicable, by publisher/originator, title/
description, volume no./form no., revision no./version, effective date)..
Note: By implementing a policy, process or procedure that categorizes inactive/unused documents as
‘‘archived,’’ these documents: (1) May be left off of the Master List, (2) Must be controlled and (3)
Must be added to the Master List if/when they are subsequently activated [re: V.4.7.h.]..
A policy, process, and/or procedure that specifies how the sponsor will provide for:
Approval of documents for adequacy prior to use.
Periodic review, updating, re-approval of documents (where necessary).
Identification of current document revision status including the date of last revision on each page concerned.
Ensuring that current relevant versions of applicable documents are available at point-of-use.
Suitable identification of obsolete documents if they are retained for any purpose.
Preventing the unintended use of obsolete documents.
Ensuring that external-origin documents are identified & their distribution/accessibility controlled.
Protection and storage/archiving of records/documents.
A policy, process, and/or procedure specifying how the sponsor will retain the following for a period of
two years (The sponsor must specify whether these records are maintained in plain language form
or in coded form. If the coded form is used, the sponsor must specify how the preservation retrieval
of information will be conducted.):
A record of training time lost due to FSTD discrepancies.
A record of the two most recent NSPM assessments.
A record of the two most recent Sponsor assessments.
SQMS Corrective Action records and/or Managed Change documentation (Including change pertaining to assessment findings)
ASSIGNMENT of PERSONNEL/TRAINING
V.4.9. .....
V.4.9.a. ..
V.4.9.b. ..
V.4.9.c. ..
sroberts on PROD1PC70 with RULES
V.4.9.d. ..
A policy, process or procedure specifying how the sponsor will, for those performing inspection, testing, engineering and normal, preventative and corrective maintenance on FSTDs:
Identify the necessary skill requirements.
Assign personnel that satisfy the identified skill requirements based upon experience, skills, education
or training
Maintain appropriate ongoing records of skill, experience, education and/or training qualifications for
assigned personnel.
Evaluate the adequacy/appropriateness of the skill requirements and the effectiveness of sponsorprovided training, referencing, in part, the criteria for workmanship specified in V.4.11.d.
POLICY, PROCESS and/or PROCEDURE CONTROL
V.4.10. ...
Documented policies, processes and/or procedures for essential QMS functions that directly affect
quality, including the relevant/essential sequence and interaction of these processes (Supported by
diagrams/flow charts/maps at sponsor’s discretion) to include:
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Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 / Rules and Regulations
TABLE E.4.—INFORMATION SQMS ASSESSMENT TOOL—INITIAL (DESK)—Continued
EXPANDED (voluntary) elements
Element
number
Rating
see element assessment table
Does the sponsor have . . .
N
V.4.10.a.
V.4.10.b.
V.4.11. ...
V.4.11.a.
V.4.11.b.
V.4.11.c.
V.4.11.d.
V.4.11.e.
V.4.12. ...
V.4.12.a.
V.4.12.b.
V.4.13. ...
P
Comments
Y
Scheduling and tracking inspection, testing, engineering and normal and preventative maintenance on
FSTDs to verify that the specified qualification requirements for the FSTD are met.
A policy, process, and/or procedure specifying how the sponsor will determine FSTD training, evaluation, and/or flight experience restrictions, including: (1) Implementation, status notification and coordination with the sponsor’s training organization, other users and TPAA and (2) Removal of the
restrictions.
A policy, process, and/or procedure specifying how the sponsor will implement controlled conditions
to provide:
A suitable work environment.
Approval of equipment.
Availability of suitable equipment and suitable equipment maintenance.
Compliance with documented procedures and/or reference standards/codes set out in the Quality
Management System Manual.
Criteria for workmanship (e.g., written standards, representative samples or illustrations).
A policy, process, and/or procedure specifying how the sponsor will ensure use of current, valid
measuring and monitoring devices, including:
Recording the basis for their periodic, or prior to use, calibration.
Protecting them from damage and safeguarding them from adjustments that would invalidate their
calibration.
A policy, process, and/or procedure that specifies how the sponsor will record NSPM assessments.
INTERNAL ASSESSMENT
V.4.14. ...
V.4.14.a.
V.4.14.b.
V.4.14.c.
V.4.14.d.
V.4.14.e.
V.4.14.f.
A policy, process, and/or procedure that specifies how the sponsor will conduct internal assessments
to determine that the SQMS: (1) Has been effectively implemented and maintained, (2) Conforms
to regulatory standards and (3) Conforms to SQMS requirements in accordance with documented
procedures, as follows:
Responsibilities and requirements for conducting assessments.]
Assessment frequency (at least annually).
Assessment scope.
How assessments are conducted and recorded.
Personnel other than those who control/perform the activity, process, procedure or practice being assessed conduct the assessment (Authorization to deviate from this standard may be approved by
the NSPM for those sponsors that have limited personnel resources).
When, how and by whom the results of such assessments and the associated corrective action/managed change are reported to Responsible Management and the NSPM.
CORRECTIVE ACTION/MANAGED CHANGE (For Other Than FSTD Operational Discrepancies)
V.4.15. ...
V.4.15.a.
V.4.15.b.
V.4.15.c.
V.4.15.d.
V.4.15.e.
V.4.15.f.
V.4.15.g.
V.4.15.h.
V.4.15.i.
V.4.15.j.
V.4.15.k.
V.4.15.l.
V.4.15.m.
V.4.15.n.
A policy, process, and/or procedure that specifies how a perceived need for change will:
Be validated (determined), and if valid, be activated as a Change Initiative.
If processed as a Corrective Action:
Determine the cause.
Determine and implement corrective action.
Record the action taken.
Evaluate the effectiveness of the action taken.
Record the results of this evaluation.
Evaluate the need for further action to prevent recurrence.
If processed as a Managed Change:
Analyze and determine action on the Change Initiative.
Establish the Scope of Change.
Develop a Change Plan.
Review the Change Plan.
Implement the Approved Change Plan.
Evaluate the implemented change.
Review the evaluation.
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TABLE E.5.—INFORMATION—SQMS ASSESSMENT TOOL—ON-SITE
Element number
Rating—
See Element
Assessment
Table
EXPANDED (Voluntary) Elements
N
There is evidence that the element is:
(4) (1) Being utilized/applied as is appropriate/necessary;
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TABLE E.5.—INFORMATION—SQMS ASSESSMENT TOOL—ON-SITE—Continued
Element number
Rating—
See Element
Assessment
Table
EXPANDED (Voluntary) Elements
N
(4)
(4)
(2) Being utilized/applied as stated/specified/defined in the QMS;
(3) Achieving/producing effective results.
QUALITY MANAGEMENT SYSTEM MANUAL:
V.5.1. .............................................
V.5.1.a. ..........................................
V.5.1.b. ..........................................
V.5.1.c. ...........................................
V.5.2. .............................................
Quality Management System Manual containscurrent:
Responsibilities Matrix, or the equivalent, designating responsibility by position, name or title for approval and/or control of essential QMS functions/
elements.
Documented SQMS processes and procedures listed in V.5.10, or reference
to them.
Descriptions of the sequence and interaction of the documented SQMS
processes.
The Quality Management System Manual is being properly controlled and includes identification of current revision status and the date of last revision
imprinted on each page concerned.
QUALITY POLICY AND QUALITY OBJECTIVES:
V.5.3. .............................................
V.5.3.a. ..........................................
V.5.3.b. ..........................................
V.5.4. .............................................
V.5.4.a. ..........................................
V.5.4.b. ..........................................
V.5.4.c. ...........................................
MANAGEMENT COMMITMENT:
V.5.5. .............................................
V.5.5.a. ..........................................
V.5.5.b. ..........................................
V.5.5.c. ...........................................
V.5.5.d. ..........................................
V.5.5.e. ..........................................
v.5.5.e.1. ........................................
v.5.5.e.2. ........................................
V.5.5.f. ...........................................
V.5.5.g. ..........................................
Currently stated quality policy:
Is appropriate for the organization.
Includes the concept of continual SQMS improvement.
Current written quality objectives:
Exist for relevant QMS functions at relevant levels within the organization.
Include the ‘‘ultimate objective’’ of providing continuous presentation of a
qualified FSTD, or FSTDs, for credible flight training, evaluation and/or
meeting experience requirements.
Are measurable and consistent with the Quality Policy.
Management is using their stated SQMS method(s) to:
Communicate and ensure that the quality policy is understood at appropriate
levels of the organization.
Ensure that employees are aware of the relevance and importance of their
activities and how they contribute to the achievement of the quality objectives.
Allocate resources (human and financial), using documented resource planning output, and implement action necessary to achieve planned operational results/quality objectives.
Document resource planning output.
Conduct periodic recorded management reviews (in compliance with stated
minimum interval) to evaluate and take action (corrective action/managed
change) to ensure continuing suitability and effectiveness of the:
Quality policy.
Quality objectives.
Verify implementation of proper corrective action/managed change on assessment deficiencies.
Record the results of corrective action/managed change on assessment deficiencies and report the results to the NSPM.
DOCUMENT/RECORD CONTROL
V.5.6. .............................................
V.5.6.a. ..........................................
v.5.6.a.1. ........................................
V.5.6.a.2. .......................................
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V.5.6.b. ..........................................
V.5.7. .............................................
V.5.7.a. ..........................................
V.5.7.b. ..........................................
V.5.7.c. ...........................................
V.5.7.d. ..........................................
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Internal and external documents:
That are actively utilized in the SQMS to ensure effective operation and control of the processes are:
On the Master List of Documents, including documents originally categorized
as ‘‘archived’’ that have been activated.
Adequately identified by publisher/originator, title/description, volume no./
form no., revision no./version, or effective date..
That are inactive/unused are being controlled according to the approved
‘‘archiving’’ policy [re: V.5.7.h.].
Stated SQMS method(s) for:
Approval of documents for adequacy prior to issue.
Periodically (where necessary) reviewing documents and records and updating/re-approving them.
Maintaining current revision(s) and entering revision status and the date of
last revision on each page concerned.
Maintaining current relevant versions of applicable documents at point-of-use.
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TABLE E.5.—INFORMATION—SQMS ASSESSMENT TOOL—ON-SITE—Continued
Element number
Rating—
See Element
Assessment
Table
EXPANDED (Voluntary) Elements
N
V.5.7.e. ..........................................
V.5.7.f. ...........................................
V.5.7.g. ..........................................
V.5.7.h. ..........................................
V.5.8. .............................................
V.5.8.a.
V.5.8.b.
V.5.8.c.
V.5.8.d.
..........................................
..........................................
...........................................
..........................................
V.5.8.e. ..........................................
Suitably identifying and designating obsolete documents if they are retained
for any purpose.
Preventing unintended use of obsolete documents.
Identifying and controlling distribution/accessibility of documents of external
origin.
Adequately protecting and storing/archiving records/documents.
Documents/records have been retained for two years, in plain language form
or in coded form, as follows:
Training time lost due to FSTD discrepancies.
Two most recent NSPM assessments.
Two most recent Sponsor assessments.
SQMS Corrective Action records and/or Managed Change documentation
(Including change pertaining to assessment findings).
Documented Management Resource Planning output and review.
ASSIGNMENT of PERSONNEL/TRAINING
V.5.9. .............................................
V.5.9.a. ..........................................
V.5.9.b. ..........................................
V.5.9.c. ...........................................
Stated SQMS method(s) for:
Assignment of personnel to perform inspection, testing, engineering and normal, preventative and corrective maintenance on FSTDs based upon experience, skills, education or training that satisfies the identified skill requirements.
Maintaining appropriate records of experience, skills, education or training to
indicate that the qualifications of the assigned personnel satisfy the stated
skill requirements.
Evaluating the: (1) Adequacy/appropriateness of the identified skill requirements and (2) Effectiveness of sponsor-provided training, utilizing, in part,
the criteria for workmanship specified in V.5.11.d.
POLICY, PROCESS and/or PROCEDURE CONTROL
V.5.10. ...........................................
V.5.10.a. ........................................
V.5.10.b. ........................................
V.5.11. ...........................................
V.5.11.a. ........................................
V.5.11.b. ........................................
V.5.11.c. .........................................
V.5.11.d. ........................................
V.5.11.e. ........................................
V.5.12. ...........................................
V.5.12.a. ........................................
V.5.12.b. ........................................
V.5.13. ...........................................
Documented policies, processes and/or procedures for essential SQMS
functions, including the relevant/essential sequence and interaction of
these processes (Supported by diagrams/flow charts/maps at sponsor’s
discretion) to include:
Scheduling and tracking inspection, testing, engineering and normal and preventative maintenance on FSTDs to verify that the specified qualification
requirements for the FSTD are met.
Determination of FSTD training, evaluation, and/or flight experience restrictions, including their implementation, status notification and coordination
with the sponsor’s training organization, other users and TPAA and removal of the restrictions.
Implementation of controlled conditions that provide:
A suitable work environment.
Approval of equipment.
Availability of suitable equipment and suitable equipment maintenance.
Compliance with documented procedures and/or reference standards/codes
as set out in the Quality Management System Manual.
Utilization of criteria for workmanship (e.g., written standards, representative
samples/illustrations).
Implementation of controlled conditions that provide availability of current,
valid measuring/monitoring devices that are consistent with measurement
requirements, including:
Recording the basis for the periodic, or prior to use, calibration of measurement devices.
Protection of measurement devices from damage and safeguarding them
from adjustments that would invalidate their calibration.
The method used to record NSPM assessments, including all recommendations and corrective action/managed change taken.
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INTERNAL ASSESSMENT
V.5.14. ...........................................
V.5.14.a. ........................................
V.514.b. .........................................
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Internal assessments have been conducted to determine that: (1) The
SQMS has been effectively implemented and maintained, (2) Conforms to
regulatory standards and (3) Conforms to SQMS requirements in accordance with documented procedures, including:.
Assignment of responsibilities and requirements for conducting assessments.
Assessment frequency.
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TABLE E.5.—INFORMATION—SQMS ASSESSMENT TOOL—ON-SITE—Continued
Element number
Rating—
See Element
Assessment
Table
EXPANDED (Voluntary) Elements
N
V.5.14.c. .........................................
V.5.14.d. ........................................
V.5.14.e. ........................................
V.5.14.f. .........................................
Adequate assessment scope.
Assessment methodology and recording.
Personnel, other than those who control/perform the activity, process, procedure or practice being assessed, conducted the assessment (Note any
NSPM approved authorization to deviate from this requirement for sponsors that have limited personnel resources).
Reporting assessment results to Responsible Management and the NSPM.
CORRECTIVE ACTION/MANAGED CHANGE (For Other Than FSTD Operational Discrepancies)
V.5.15. ...........................................
V.5.15.a. ........................................
V.5.15.b.
V.5.15.c.
V.5.15.d.
V.5.15.e.
V.5.15.f.
V.5.15.g.
—.
........................................
.........................................
........................................
........................................
.........................................
........................................
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V.5.15.h. ........................................
V.5.15.i. ..........................................
V.5.15.j. ..........................................
V.5.15.k. .........................................
V.5.15.l. ..........................................
V.5.15.m. .......................................
V.5.15.n. ........................................
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The policy, process, and/or procedure that specifies how a perceived need
for change will:
Be validated (determined), and if valid, be activated as a Change Initiative.
If processed as a Corrective Action:
Determine the cause.
Determine and implement corrective action.
Record the action taken.
Evaluate the effectiveness of the action taken.
Record the results of this evaluation.
Evaluate the need for further action to prevent recurrence.
If processed as a Managed Change:.
Analyze and determine action on the Change Initiative.
Establish the Scope of Change.
Develop a Change Plan.
Review the Change Plan.
Implement the Approved Change Plan.
Evaluate the implemented change.
Review the evaluation.
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BILLING CODE 4910–73–C
Appendix F to Part 60—Definitions and
Abbreviations for Flight Simulation
Training Devices
lllllllllllllllllllll
Begin Information
1. The definitions presented below in Italic
type face are repeated from the regulatory
definitions found in part 1 or part 60, as
indicated. In the event that a discrepancy
exists between a definition found here, and
one found in part 1 or part 60, the part 1 or
part 60 definition prevails.
End Information
lllllllllllllllllllll
lllllllllllllllllllll
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Begin QPS Requirements
2. Definitions.
1st Segment—is that portion of the takeoff
profile from liftoff to gear retraction.
2nd Segment—is that portion of the takeoff
profile from after gear retraction to initial
flap/slat retraction.
3rd Segment—is that portion of the takeoff
profile after flap/slat retraction is complete.
Aircraft data package—is a combination of
the various types of data used to design,
program, manufacture, modify, and test the
FSTD.
Airspeed—is calibrated airspeed unless
otherwise specified and is expressed in terms
of nautical miles per hour (knots).
Altitude—is pressure altitude (meters or
feet) unless specified otherwise.
Angle of attack—is the angle between the
airplane longitudinal axis and the relative
wind vector projected onto the airplane plane
of symmetry.
Automatic Testing—is FSTD testing
wherein all stimuli are under computer
control.
Bank—is the airplane attitude with respect
to or around the longitudinal axis, or roll
angle (degrees).
Breakout—is the force required at the
pilot’s primary controls to achieve initial
movement of the control position.
Certificate holder—A person issued a
certificate under parts 119, 141, or 142 of this
chapter or a person holding an approved
course of training for flight engineers in
accordance with part 63 of this chapter. (Part
60)
Closed Loop Testing—is a test method for
which the input stimuli are generated by
controllers, which drive the FSTD to follow
a pre-defined target response.
Computer Controlled Airplane—is an
airplane where all pilot inputs to the control
surfaces are transferred and augmented by
computers.
Control Sweep—is movement of the
appropriate pilot controller from neutral to
an extreme limit in one direction (Forward,
Aft, Right, or Left), a continuous movement
back through neutral to the opposite extreme
position, and then a return to the neutral
position.
Convertible FSTD—is an FSTD in which
hardware and software can be changed so
that the FSTD becomes a replica of a different
model, usually of the same type aircraft. The
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same FSTD platform, cockpit shell, motion
system, visual system, computers, and
necessary peripheral equipment can thus be
used in more than one simulation.
Critical Engine Parameter—is the
parameter, which is the most accurate
measure of propulsive force.
Deadband—is the amount of movement of
the input for a system for which there is no
reaction in the output or state of the system
observed.
Distance—is the length of space between
two points and is expressed in terms of
nautical miles unless specified otherwise.
Discrepancy—as used in this part, means
an aspect of the FSTD that is not correct with
respect to the aircraft being simulated. This
includes missing, malfunctioning, and/or
inoperative components that are required to
be present and operate correctly for training,
evaluation, and experience functions to be
creditable. It also includes errors in the
documentation used to support the FSTD
(e.g., errors in, or information missing from,
the MQTG, required statements from
appropriately qualified personnel).
Downgrade—is a permanent change in the
qualification level of an FSTD to a lower
level.
Driven—is a test method where the input
stimulus or variable is positioned by
automatic means, generally a computer
input.
Electronic Copy of the MQTG—an
electronic copy of the MQTG provided by an
electronic scan presented in a Portable
Document File (PDF), or similar format,
acceptable to the NSPM.
Electronic Master Qualification Test
Guide—is an electronic version of the MQTG
(eMQTG), where all objective data obtained
from airplane testing, or another approved
source, together with correlating objective
test results obtained from the performance of
the FSTD and a description of the equipment
necessary to perform the evaluation for the
initial and the continuing qualification
evaluations is stored, archived, or presented
in either reformatted or digitized electronic
format.
Engine—as used in this part, means the
appliance or structure that supplies
propulsive force for movement of the aircraft:
i.e., the turbine engine for turbine powered
aircraft; the turbine engine and propeller
assembly for turbo-propeller powered
aircraft; and the reciprocating engine and
propeller assembly for reciprocating engine
powered aircraft. For purposes of this part,
engine failure is the failure of either the
engine, or propeller assembly, to provide
thrust higher than idle power thrust due to
a failure of either the engine or the propeller
assembly.
Evaluation—With respect to an individual,
the checking, testing, or review associated
with flight crewmember qualification,
training, and certification under parts 61, 63,
121, or 135 of this chapter. With respect to
an FSTD, the qualification activities (e.g., the
objective and subjective tests, the
inspections, or the continuing qualification
evaluations) associated with the
requirements of this part. (Part 60)
Fictional Airport—is a visual model of an
airport that is a collection of non-‘‘real
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world’’ terrain, instrument approach
procedures, navigation aids, maps, and visual
modeling detail sufficient to enable
completion of an Airline Transport Pilot
Certificate or Type Rating.
Flight experience—Flight experience
means recency of flight experience for
landing credit purposes. (Part 60)
Flight simulation training device (FSTD)
means a full flight simulator (FFS) or a flight
training device (FTD). (Part 1)
Flight test data—(a subset of Objective
data) Aircraft data collected by the aircraft
manufacturer (or other supplier of data that
are acceptable to the NSPM) during an
aircraft flight test program. (Part 60)
Flight training device (FTD) means a
replica of aircraft instruments, equipment,
panels, and controls in an open flight deck
area or an enclosed aircraft cockpit replica.
It includes the equipment and computer
programs necessary to represent aircraft (or
set of aircraft) operations in ground and flight
conditions having the full range of
capabilities of the systems installed in the
device as described in part 60 of this chapter
and the qualification performance standard
(QPS) for a specific FTD qualification level.
(Part 1)
Free Response—is the response of the
FSTD after completion of a control input or
disturbance.
Frozen—is a test condition where one or
more variables are held constant with time.
FSTD Approval—is the extent to which an
FSTD may be used by a certificate holder as
authorized by the FAA. It takes into account
aircraft to FSTD differences and the training
ability of the organization.
FSTD Directive—A document issued by the
FAA to an FSTD sponsor, requiring a
modification to the FSTD due to a recognized
safety-of-flight issue and amending the
qualification basis for the FSTD. (Part 60)
FSTD Latency—is the additional time
beyond that of the response time of the
aircraft due to the response of the FSTD.
FSTD Performance—The overall
performance of the FSTD includes aircraft
performance (e.g., thrust/drag relationships,
climb, range) as well as flight and ground
handling. (Part 60)
Full flight simulator (FFS) means a replica
of a specific type; or make, model, and series
aircraft cockpit. It includes the assemblage of
equipment and computer programs necessary
to represent aircraft operations in ground and
flight conditions, a visual system providing
an out-of-the-cockpit view, a system that
provides cues at least equivalent to those of
a three-degree-of-freedom motion system,
and has the full range of capabilities of the
systems installed in the device as described
in part 60 of this chapter and the
qualification performance standards (QPS)
for a specific FFS qualification level. (Part 1)
Generic Airport—is a Class III visual model
that combines correct navigation aids for a
real world airport with a visual model which
does not correctly depict that same airport.
Grandfathering—as used in this part,
means the practice of assigning a
qualification basis for an FSTD, based on the
period of time during which a published set
of standards governed the requirements for
the initial and continuing qualification of
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FSTDs. Each FSTD manufactured during this
specified period of time is ‘‘grandfathered,’’
or is ‘‘held to the standards’’ that are, or
were, in effect during that time period. The
grandfathered standards remain applicable to
each FSTD manufactured during the stated
time period, regardless of any subsequent
modification to those standards and
regardless of the sponsor, as long as the FSTD
remains continuously qualified or is
maintained in a non-qualified status in
accordance with the specific requirements
and time periods set out in this part. Each
FSTD manufactured prior to the beginning
date (or manufactured after the ending date)
of a designated grandfather time period
would have as its qualification basis, the
standards in effect during the time period
prior to, or subsequent to, the designated
period.
Gross Weight—For objective test purposes:
Basic Operating Weight—(BOW) is the
empty weight of the aircraft plus the weight
of the following: normal oil quantity; lavatory
servicing fluid; potable water; required
crewmembers and their baggage; and
emergency equipment.
Near Maximum Gross Weight—is a weight
chosen by the sponsor or data provider that
is not less than the basic operating weight
(BOW) of the airplane being simulated plus
80% of the difference between the maximum
certificated gross weight (either takeoff
weight or landing weight, as appropriate for
the test) and the BOW.
Light Gross Weight—is a weight chosen by
the sponsor or data provider that is not more
than 120% of the BOW of the airplane being
simulated or as limited by the minimum
practical operating weight of the test
airplane.
Medium Gross Weight—is a weight chosen
by the sponsor or data provider that is
approximately ±10% of the average of the
numerical values of the BOW and the
maximum certificated gross weight.
Ground Effect—is the change in
aerodynamic characteristics due to
modification of the airflow past the aircraft
caused by the proximity of the Earth’s surface
to the airplane.
Hands Off—is a test maneuver conducted
without pilot control inputs.
Hands On—is a test maneuver conducted
with pilot control inputs as required.
Heave—is FSTD movement with respect to
or along the vertical axis.
Height—is the height above ground level
(or AGL) expressed in meters or feet.
‘‘In Use’’ Runway—as used in this part,
means the runway that is ‘‘active,’’ (is
currently ‘‘selected’’ and able to be used for
takeoffs and landings) and has the surface
lighting and markings required by this part.
Integrated Testing—is testing of the FSTD
such that all aircraft system models are active
and contribute appropriately to the results
where none of the models used are
substituted with models or other algorithms
intended for testing only.
Irreversible Control System—is a control
system in which movement of the control
surface will not backdrive the pilot’s control
in the cockpit.
Locked—is a test condition where one or
more variables are held constant with time.
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Manual Testing—is FSTD testing
conducted without computer inputs except
for initial setup and all modules of the
simulation are active.
Master Qualification Test Guide (MQTG)—
The FAA-approved Qualification Test Guide
with the addition of the FAA-witnessed test
results, applicable to each individual FSTD.
(Part 60)
Medium—is the normal operational weight
for a given flight segment.
National Simulator Program Manager
(NSPM)—The FAA manager responsible for
the overall administration and direction of
the National Simulator Program (NSP), or a
person approved by that FAA manager. (Part
60)
Nominal—is the normal operating
configuration, atmospheric conditions, and
flight parameters for the flight segment
specified.
Non-Normal Control—is a term used in
reference to Computer Controlled Airplanes
and is the state where one or more of the
intended control, augmentation, or protection
functions are not fully working. NOTE:
Specific terms such as ALTERNATE,
DIRECT, SECONDARY, or BACKUP may be
used to define an actual level of degradation.
Normal Control—is a term used in
reference to Computer Controlled Airplanes
and is the state where the intended control,
augmentation, and protection functions are
fully working.
Objective data—Quantitative data,
acceptable to the NSPM, used to evaluate the
FSTD.
Objective test—A quantitative
measurement and evaluation of FSTD
performance. (Part 60)
Pitch—is the airplane attitude with respect
to, or around, the lateral axis expressed in
degrees.
Power Lever Angle (PLA)—is the angle of
the pilot’s primary engine control lever(s) in
the cockpit. This may also be referred to as
THROTTLE or POWER LEVER.
Predicted data—Estimations or
extrapolations of either existing flight test
data or data from other simulation models
using engineering analyses, engineering
simulations, design data, and/or wind tunnel
data. (Part 60)
Protection Functions—are systems
functions designed to protect an airplane
from exceeding its flight maneuver
limitations.
Pulse Input—is a step input to a control
followed by an immediate return to the
initial position.
Qualification level—The categorization of
an FSTD established by the NSPM, based on
the FSTDs demonstrated technical and
operational capabilities as set out in this part.
(Part 60)
Qualification Performance Standard
(QPS)—The collection of procedures and
criteria published by the FAA to be used
when conducting objective tests and
subjective tests, including general FSTD
requirements, for establishing FSTD
qualification levels. The QPS are published
in the appendices to this part, as follows:
Appendix A, for Airplane Simulators;
Appendix B, for Airplane Flight Training
Devices; Appendix C, for Helicopter
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Simulators; Appendix D, for Helicopter
Flight Training Devices; Appendix E, for
Quality Management Systems for Flight
Simulation Training Devices; and Appendix
F, for Definitions and Abbreviations for
Flight Simulation Training Devices. (Part 60)
Qualification Test Guide (QTG)—The
primary reference document used for
evaluating an aircraft FSTD. It contains test
results, statements of compliance and
capability, the configuration of the aircraft
simulated, and other information for the
evaluator to assess the FSTD against the
applicable regulatory criteria. (Part 60)
Quality Management System (QMS)—the
aviation standard for flight simulation
quality-systems that can be used for external
quality-assurance purposes. It is a collection
of generic and independent requirements
unrelated to any specific industry or
economic sector. It is not designed to enforce
uniformity of quality systems, but to identify
the processes needed, determine the
sequence and interaction of these processes,
determine criteria and methods required to
ensure the effective operation and control of
these processes, ensure the availability of
information necessary to support the
operation and monitoring of these processes,
measure, monitor and analyze these
processes, and implement the actions
necessary to achieve planned results. The
design and implementation of a specific
quality management system is influenced by
the varying needs of the individual sponsor,
their particular objectives, the flight
simulation products and services supplied,
and the processes and specific practices
employed.
Real-World Airport—as used in this part in
reference to airport visual models, means a
computer generated visual depiction of an
airport that exists in reality.
Representative—When used as an adjective
in this part, means typical, demonstrative, or
characteristic of, or with respect to, the
feature being described. For example:
1. ‘‘Representative sampling of tests’’
means a sub-set of the complete set of all
tests such that the sample includes one or
more of the tests in each of the major
categories, the results of which would
provide the evaluator a typical, or overall,
understanding of the performance and/or
handling characteristics of the FSTD.
2. ‘‘Representative airport model’’ (or
‘‘ground/airborne traffic,’’ ‘‘lights,’’ ‘‘runway/
taxiway markings,’’ ‘‘terrain,’’ ‘‘weather
phenomena’’) means a computer generated
visual depiction of a real-world or fictional
airport (or traffic, lights, markings, terrain,
weather phenomena.) that is typical or
characteristic of an airport (or traffic, lights,
markings, terrain, weather phenomena)
regularly used or seen by the sponsor, or the
sponsor’s client using the FSTD, in normal
operations.
Reversible Control System—is a control
system in which movement of the control
surface will backdrive the pilot’s control in
the cockpit.
Roll—is the airplane attitude with respect
to, or around, the longitudinal axis expressed
in degrees.
Set of aircraft—Aircraft that share similar
handling and operating characteristics and
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similar operating envelopes and have the
same number and type of engines or power
plants. (Part 60)
Sideslip Angle—is the angle between the
relative wind vector and the airplane plane
of symmetry. (note: this definition replaces
the current definition of ‘‘sideslip.’’)
Simulation Quality Management System
(SQMS)—consists of the required and
voluntary elements of a quality management
system for FSTD continuing qualification.
Snapshot—is a presentation of one or more
variables at a given instant of time.
Special Evaluation—is an evaluation of the
FSTD for purposes other than initial,
upgrade, or continuing qualification.
Circumstances that might indicate the need
for a special evaluation would include, but
not necessarily be limited to, the following:
after the FSTD is moved and reinstalled at
another location; after an update to FSTD
software or hardware that might affect
performance or flying qualities; after a
substantial update to FSTD avionics packages
(e.g., autopilot, flight management systems);
after substantial modifications to FSTD
configuration; after a complaint is received
from a credible source indicating that the
FSTD does not perform or handle like the
aircraft it simulates.
Sponsor—A certificate holder who seeks or
maintains FSTD qualification and is
responsible for the prescribed actions as set
out in this part and the QPS for the
appropriate FSTD and qualification level.
(Part 60)
Statement of Compliance and Capability
(SOC)—is a declaration that specific
requirements have been met. It must declare
that compliance with the requirement is
achieved and explain how the requirement is
met (e.g., gear modeling approach, coefficient
of friction sources). It must also describe the
capability of the FSTD to meet the
requirement (e.g., computer speed, visual
system refresh rate). In doing this, the
statement must provide references to needed
sources of information for showing
compliance, rationale to explain how the
referenced material is used, mathematical
equations and parameter values used, and
conclusions reached.
Step Input—is an abrupt control input held
at a constant value.
Subjective test—A qualitative assessment
of the performance and operation of the
FSTD. (Part 60)
Surge—is FSTD movement with respect to
or along the longitudinal axis.
Sway—is FSTD movement with respect to
or along the lateral axis.
Time History—is a presentation of the
change of a variable with respect to time.
Training Program Approval Authority
(TPAA)—A person authorized by the
Administrator to approve the aircraft flight
training program in which the FSTD will be
used. (Part 60)
Training Restriction—is a temporary
condition where, due to a Missing,
Malfunctioning, or Inoperative (MMI)
Component condition, the FSTD may
continue to be used at the qualification level
indicated on its SOQ but restricted from
accomplishing the task for which the correct
function of the MMI component is required.
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Transport Delay or ‘‘Throughput’’—is the
total FSTD system processing time required
for an input signal from a pilot primary flight
control until motion system, visual system,
or instrument response. It is the overall time
delay incurred from signal input until output
response. It does not include the
characteristic delay of the airplane simulated.
Upgrade—The improvement or
enhancement of an FSTD for the purpose of
achieving a higher qualification level. (Part
60)
Validation Data—Objective data used to
determine if the FSTD performance is within
the tolerances prescribed in the QPS.
Validation Test—An objective test whereby
FSTD parameters are compared to the
relevant validation data to ensure that the
FSTD performance is within the tolerances
prescribed in the QPS.
Visual Data Base—is a display that may
include one or more visual models.
Visual Model—is a collection of one or
more visual scenes of an airport or portion(s)
of an airport.
Visual System Response Time—is the
interval from a control input to the
completion of the visual display scan of the
first video field containing the resulting
different information.
Yaw—is airplane attitude with respect to,
or around, the vertical axis expressed in
degrees.
3. Abbreviations.
AFM Approved Flight Manual.
AlL Above Ground Level (meters or feet).
AOA Angle of Attack (degrees).
APD Aircrew Program Designee.
CCA Computer Controlled Airplane.
cd/m2 candela/meter2, 3.4263 candela/m2 =
1 ft-Lambert.
CFR Code of Federal Regulations.
cm(s) centimeter, centimeters.
daN decaNewtons, one (1) decaNewton =
2.27 pounds.
deg(s) degree, degrees.
DOF Degrees-of-freedom.
eMQTG Electronic Master Qualification
Test Guide.
EPR Engine Pressure Ratio.
FAA Federal Aviation Administration
(U.S.).
fpm feet per minute.
ft foot/feet, 1 foot = 0.304801 meters.
ft-Lambert foot-Lambert, 1 ft-Lambert =
3.4263 candela/m2.
g Acceleration due to Gravity (meters or
feet/sec2); 1 g = 9.81 m/sec2 or 32.2 feet/
sec2.
G/S Glideslope.
IATA International Airline Transport
Association.
ICAO International Civil Aviation
Organization.
IGE In ground effect.
ILS Instrument Landing System.
IQTG International Qualification Test
Guide.
km Kilometers 1 km = 0.62137 Statute
Miles.
kPa KiloPascal (Kilo Newton/Meters2). 1
psi = 6.89476 kPa.
kts Knots calibrated airspeed unless
otherwise specified, 1 knot = 0.5148 m/sec
or 1.689 ft/sec.
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63639
lb(s) pound(s), one (1) pound = 0.44
decaNewton.
LDP Landing decision point.
M,m Meters, 1 Meter = 3.28083 feet.
Min(s) Minute, minutes.
MLG Main Landing Gear.
Mpa MegaPascals (1 psi = 6894.76 pascals).
ms millisecond(s).
N NORMAL CONTROL Used in reference
to Computer Controlled Airplanes.
nm Nautical Mile(s) 1 Nautical Mile = 6,080
feet.
NN NON-NORMAL CONTROL Used in
reference to Computer Controlled
Airplanes.
N1 Low Pressure Rotor revolutions per
minute, expressed in percent of maximum.
N2 High Pressure Rotor revolutions per
minute, expressed in percent of maximum.
N3 High Pressure Rotor revolutions per
minute, expressed in percent of maximum.
NWA Nosewheel Angle (degrees).
OGE Out of ground effect.
PAPI Precision Approach Path Indicator
System.
Pf Impact or Feel Pressure, often expressed
as ‘‘q.’’
PLA Power Lever Angle.
PLF Power for Level Flight.
psi pounds per square inch.
QPS Qualification Performance Standard.
RAE Royal Aerospace Establishment.
R/C Rate of Climb (meters/sec or feet/min).
R/D Rate of Descent (meters/sec or feet/
min).
REIL Runway End Identifier Lights.
RVR Runway Visual Range (meters or feet).
s second(s).
sec(s) second, seconds.
sm Statute Mile(s) 1 Statute Mile = 5,280
feet.
SOC Statement of Compliance and
Capability.
Tf Total time of the flare maneuver
duration.
Ti Total time from initial throttle movement
until a 10% response of a critical engine
parameter.
TIR Type Inspection Report.
T/O Takeoff.
Tt Total time from Ti to a 90% increase or
decrease in the power level specified.
VASI Visual Approach Slope Indicator
System.
VGS Visual Ground Segment.
V1 Decision speed.
V2 Takeoff safety speed.
Vmc Minimum Control Speed.
Vmca Minimum Control Speed in the air.
Vmcg Minimum Control Speed on the
ground.
Vmcl Minimum Control Speed—Landing.
Vmu The speed at which the last main
landing gear leaves the ground.
VR Rotate Speed.
Vs Stall Speed or minimum speed in the
stall.
WAT Weight, Altitude, Temperature.
End QPS Requirements
PART 121—OPERATING
REQUIREMENTS: DOMESTIC, FLAG,
AND SUPPLEMENTAL OPERATIONS
7. The authority citation for part 121
continues to read as follows:
I
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Authority: 49 U.S.C. 106(g), 1153, 40101,
40102, 40103, 40113, 41721, 44105, 44106,
44111, 44701–44717, 44722, 44901, 44903,
44904, 44906, 44912, 44914, 44936, 44938,
46103, 46105.
8. Revise Appendix H to part 121 to
read as follows:
I
Appendix H to Part 121—Advanced
Simulation
This appendix provides guidelines and a
means for achieving flightcrew training in
advanced airplane simulators. The
requirements in this appendix are in addition
to the simulator approval requirements in
§ 121.407. Each simulator used under this
appendix must be approved as a Level B, C,
or D simulator, as appropriate.
Advanced Simulation Training Program
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For an operator to conduct Level C or D
training under this appendix all required
simulator instruction and checks must be
conducted under an advanced simulation
training program approved by the
Administrator for the operator. This program
must also ensure that all instructors and
check airmen used in appendix H training
and checking are highly qualified to provide
the training required in the training program.
The advanced simulation training program
must include the following:
1. The operator’s initial, transition,
upgrade, and recurrent simulator training
programs and its procedures for reestablishing recency of experience in the
simulator.
2. How the training program will integrate
Level B, C, and D simulators with other
simulators and training devices to maximize
the total training, checking, and certification
functions.
3. Documentation that each instructor and
check airman has served for at least 1 year
in that capacity in a certificate holder’s
approved program or has served for at least
1 year as a pilot in command or second in
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02:00 Oct 28, 2006
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command in an airplane of the group in
which that pilot is instructing or checking.
4. A procedure to ensure that each
instructor and check airman actively
participates in either an approved regularly
scheduled line flying program as a flight
crewmember or an approved line observation
program in the same airplane type for which
that person is instructing or checking.
5. A procedure to ensure that each
instructor and check airman is given a
minimum of 4 hours of training each year to
become familiar with the operator’s advanced
simulation training program, or changes to it,
and to emphasize their respective roles in the
program. Training for simulator instructors
and check airmen must include training
policies and procedures, instruction methods
and techniques, operation of simulator
controls (including environmental and
trouble panels), limitations of the simulator,
and minimum equipment required for each
course of training.
6. A special Line Oriented Flight Training
(LOFT) program to facilitate the transition
from the simulator to line flying. This LOFT
program must consist of at least a 4-hour
course of training for each flightcrew. It also
must contain at least two representative flight
segments of the operator’s route. One of the
flight segments must contain strictly normal
operating procedures from push back at one
airport to arrival at another. Another flight
segment must contain training in appropriate
abnormal and emergency flight operations.
Level B
Training and Checking Permitted
1. Recency of experience (§ 121.439).
2. Night takeoffs and landings (Part 121,
Appendix E).
3. Landings in a proficiency check without
the landing on the line requirements
(§ 121.441).
Level C
Training and Checking Permitted
1. For all pilots, transition training between
airplanes in the same group, and for a pilot
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in command the certification check required
by § 61.153 of this chapter.
2. Upgrade to pilot-in-command training
and the certification check when the pilot—
a. Has previously qualified as second in
command in the equipment to which the
pilot is upgrading;
b. Has at least 500 hours of actual flight
time while serving as second in command in
an airplane of the same group; and
c. Is currently serving as second in
command in an airplane in this same group.
3. Initial pilot-in-command training and
the certification check when the pilot—
a. Is currently serving as second in
command in an airplane of the same group;
b. Has a minimum of 2,500 flight hours as
second in command in an airplane of the
same group; and
c. Has served as second in command on at
least two airplanes of the same group.
4. For all second-in-command pilot
applicants who meet the aeronautical
experience requirements of § 61.159 of this
chapter in the airplane, the initial and
upgrade training and checking required by
this part, and the certification check
requirements of § 61.153 of this chapter.
Level D
Training and Checking Permitted
Except for the requirements listed in the
next sentence, all pilot flight training and
checking required by this part and the
certification check requirements of
§ 61.153(g) of this chapter. The line check
required by § 121.440, the static airplane
requirements of appendix E of this part, and
the operating experience requirements of
§ 121.434 must still be performed in the
airplane.
Issued in Washington, DC, on August 28,
2006.
Marion C. Blakey,
Administrator.
[FR Doc. 06–8677 Filed 10–27–06; 8:45 am]
BILLING CODE 4910–13–P
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[Federal Register Volume 71, Number 209 (Monday, October 30, 2006)]
[Rules and Regulations]
[Pages 63392-63640]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-8677]
[[Page 63391]]
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Part II
Department of Transportation
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Federal Aviation Administration
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14 CFR Parts 1, 11, 60, and 121
Flight Simulation Training Device Initial and Continuing Qualification
and Use; Final Rule
Federal Register / Vol. 71, No. 209 / Monday, October 30, 2006 /
Rules and Regulations
[[Page 63392]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Parts 1, 11, 60, and 121
[Docket No. FAA-2002-12461; Amendment Nos. 1-54, 11-52, 60-1, 121-327]
RIN 2120-AH07
Flight Simulation Training Device Initial and Continuing
Qualification and Use
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final Rule.
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SUMMARY: The FAA is amending the regulations to establish a new part to
set forth qualification requirements for flight simulation training
devices (FSTD). The new part consolidates and updates FSTD requirements
that currently exist in different parts of the FAA's regulations and in
advisory circulars. In addition, the FAA is requiring that sponsors of
FSTDs have a Quality Management System. These changes are necessary to
promote standardization and accountability for FSTD qualification,
maintenance, and evaluation. The intended effect of the new part is to
ensure that users of FSTDs receive training in devices that closely
match the performance and handling characteristics of the aircraft
being simulated.
EFFECTIVE DATE: These amendments become effective October 30, 2007.
FOR FURTHER INFORMATION CONTACT: Ed Cook, Air Transportation Division
(AFS-200), Flight Standards Service, Federal Aviation Administration,
100 Hartsfield Centre Parkway, Suite 400, Atlanta, GA 30354; telephone:
404-832-4700.
SUPPLEMENTARY INFORMATION:
Availability of Rulemaking Documents
You can get an electronic copy using the Internet by:
(1) Searching the Department of Transportation's electronic Docket
Management System (DMS) Web page (https://dms.dot.gov/search);
(2) Visiting the FAA's Regulations and Policies Web page at https://
www.faa.gov/regulations_policies/; or
(3) Accessing the Government Printing Office's Web page at https://
www.gpoaccess.gov/fr/.
You can also get a copy by sending a request to the Federal
Aviation Administration, Office of Rulemaking, ARM-1, 800 Independence
Avenue SW., Washington, DC 20591, or by calling (202) 267-9680. Make
sure to identify the amendment number or docket number of this
rulemaking.
Anyone is able to search the electronic form of all comments
received into any of our dockets by the name of the individual
submitting the comment (or signing the comment, if submitted on behalf
of an association, business, labor union, etc.). You may review DOT's
complete Privacy Act statement in the Federal Register published on
April 11, 2000 (Volume 65, Number 70; Pages 19477-78) or you may visit
https://dms.dot.gov.
Small Business Regulatory Enforcement Fairness Act
The Small Business Regulatory Enforcement Fairness Act (SBREFA) of
1996 requires FAA to comply with small entity requests for information
or advice about compliance with statutes and regulations within its
jurisdiction. If you are a small entity and you have a question
regarding this document, you may contact its local FAA official, or the
person listed under FOR FURTHER INFORMATION CONTACT. You can find out
more about SBREFA on the Internet at https://www.faa.gov/regulations_
policies/rulemaking/sbre_act/.
Authority for This Rulemaking
The FAA's authority to issue rules regarding aviation safety is
found in Title 49 of the United States Code. Subtitle I, Section 106
describes the authority of the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more detail the scope of the agency's
authority.
This rulemaking is promulgated under the authority described in
Subtitle VII, Part A, subpart I, 49 U.S.C. 44701. Under that section,
the FAA is charged with regulating air commerce in a way that best
promotes safety.
Background
For many years the flightcrew training regulations in 14 CFR part
121 subparts N and O allowed simulator training as an enhancement to
training and testing in the aircraft, but not as a complete replacement
for training in the aircraft. Due to improvements in flight simulator
performance, appendix H was added to part 121 in 1980. Appendix H
permitted and expanded use of simulators by air carriers that took
advantage of the new simulator performance through an ``Advanced
Simulation Training Program.'' Appendix H permits simulators to be used
for varying amounts (up to 100%) of the training, testing, and checking
required by the FAA. The amount of training permitted depends on the
simulator's qualification level.
As the state-of-the-art in simulator technology has advanced, more
effective use has been made of the aircraft simulator in training,
checking, and certification of flight crewmembers. Using flight
simulators rather than aircraft in training allows for more in-depth
training, including the practice of critical emergency procedures, in a
safer environment. Not only do simulators provide improvements in
safety and in safer training operations, they also provide such
benefits as reducing noise, air pollution and air traffic congestion,
and conserving petroleum resources.
Since 1980 appendix H of 14 CFR part 121 has provided an Advanced
Simulation plan outlining the steps toward optimum use of flight
simulators. Most major air carriers have taken advantage of appendix H
and conduct most or all of their training and checking in simulators.
The FAA originally placed simulator technical requirements in
appendix H because part 121 air carriers were the primary users of
aircraft simulators. As the larger aviation community became interested
in using simulators, the FAA in 1980 provided guidance in an advisory
circular AC 121-14C, Aircraft Simulator and Visual System Evaluation
and Approval. The AC more fully described what the technical
capabilities of simulators should be, how those capabilities might be
verified, and how all these capabilities might be incorporated into
training programs.
Over the next several years following publication of AC 121-14C,
the FAA, in consultation with the aviation industry, refined and
republished its guidance material several times. Because the
regulations regarding advanced simulators remained in part 121,
appendix H, certificate holders who operated under parts other than 121
(such as parts 125 and 135) had to obtain exemptions in order to use
simulators as provided in part 121, appendix H. The number of these
operators has continued to grow.
The ability to manage the increasing number of exemptions, each one
with slightly different provisions, conditions and limitations, became
increasingly difficult. The development of 14 CFR part 142,
Certification of Training Centers, was seen to be a logical and
necessary way to deal with those operators who wished to conduct
training for flight crewmembers but who did not operate under any of
the part 121, 125 or 135 rules. However, the regulatory requirements
for the technical criteria for a majority of the simulators coming into
the U.S. aviation inventory has remained in the part 121 operating
rule.
[[Page 63393]]
Notice of Proposed Rulemaking
The FAA published a Notice of Proposed Rulemaking (NPRM) for part
60 and related amendments on September 25, 2002, (67 FR 60284) and
published a correction to the NPRM on October 25, 2002 (67 FR 65524).
From December 2 until December 13, 2002, the FAA hosted an on-line
public forum, which provided an opportunity for the public to answer
specific questions posed by the FAA and allowed the FAA to respond with
clarifying information. After an extension requested by commenters, the
comment period closed on February 24, 2003.
In the NPRM the FAA proposed to remove the technical requirements
for flight simulation devices (FSD) (flight simulators and flight
training devices) from part 121 and place them in a new part 60, titled
``Flight Simulation Device Initial and Continuing Qualification and
Use.'' The NPRM proposed to establish FSTD requirements for anyone
conducting flight crewmember training, evaluation, and flight
experience under any of the Federal Aviation Regulations.
Flight Simulation Device Aviation Rulemaking Committee (ARC)
In order to resolve comments and provide a forum for the FAA and
the aviation community to discuss issues regarding Flight Simulation
Training Devices (FSTDs), the FAA established the Flight Simulation
Device Aviation Rulemaking Committee (ARC) on July 2, 2003. The ARC
included participants from: Air Line Pilots Association, Aircraft
Owners and Pilots Association, American Airlines, Alteon, Atlas Air,
Boeing, CAE Electronics, Continental Airlines, Delta Air Lines, Federal
Express, FlightSafety International, Northwest Airlines, Pan Am Flight
Academy, Thales Training and Simulation, United Airlines, U.S. Airways,
and FAA.
The general goal of the ARC was to provide advice, guidance, and
recommendations on FSTD issues including, but not limited to, safety of
flight; the suitability and the application of the simulation to flight
crewmember training, testing, or checking activities; and
implementation of technical changes or scientific advancements in
simulation. The ARC provided a forum for the FAA and affected members
of the aviation community to discuss issues. The ARC also allowed
members of the aviation community to reach consensus on certain
recommendations that would be submitted to the FAA and to develop
resolutions to facilitate the evolution of FSTDs. The ARC's initial
task was to review the FAA's September 25, 2002, proposed rule. On
November 24, 2003, the ARC submitted to the FAA its recommendations on
how the proposed rule language should be clarified and reorganized.
After the FAA received recommendations from the ARC the comment period
was reopened on February 10, 2004, to permit interested persons to
review these recommendations and submit additional comments. The
recommendations from the ARC are available online at https://dms.dot.gov
by searching for entry 84 in docket number FAA-2002-12461. The comment
period closed on March 11, 2004. The overwhelming majority of the
clarifications and revisions contained in the final rule are consistent
with the ARC recommendations.
Summary of the Final Rule
New part 60 contains the requirements for the evaluation,
qualification, and maintenance of FSTDs. These requirements are based
on the current guidance regarding the capability and performance of
simulators in appendix H of part 121 and Sec. 121.407. As part of this
rulemaking project, the FAA has amended appendix H of part 121 and
removed the Simulator Requirements and the Visual Requirements for
Level B, C and D devices. These requirements are now outlined in the
appropriate Qualification Performance Standards (QPS) appendices. In a
separate rulemaking project that will follow this final rule, the FAA
will propose to move Training and Checking Requirements of appendix H
to a new subpart of part 121, and to delete appendix H.
Part 60 also contains items (such as frequency, content, and method
of evaluation) previously found in the advisory material in AC 120-40B,
Airplane Flight Simulator Qualification, in AC 120-45A, Airplane Flight
Training Device Qualification, and in AC 120-63, Helicopter Simulator
Qualification. Standards from this advisory material and specific items
that are subject to change through technological advancements are being
placed into one of the first four appendices to part 60:
Appendix A, ``Qualification Performance Standards for
Airplane Full Flight Simulators.''
Appendix B, ``Qualification Performance Standards for
Airplane Flight Training Devices.''
Appendix C, ``Qualification Performance Standards for
Helicopter Full Flight Simulators.''
Appendix D, ``Qualification Performance Standards for
Helicopter Flight Training Devices.''
In addition, the FAA has reorganized and clarified some material
from the original NPRM into two appendices, Appendix E, ``Qualification
Performance Standards for Quality Management Systems for Flight
Simulation Training Devices,'' and Appendix F, ``Definitions and
Abbreviations.'' Appendix E will become the single appendix for
reference to Quality Management System (QMS) programs for FSTDs under
this part. Appendix F will become the single appendix for definitions
and abbreviations for terms used throughout part 60 and the QPS
appendices.
Some of the terms and abbreviations listed in the new appendix F
and added to part 1 are clarifications of terms that appeared in the
September 25, 2002, NPRM. For example, FSD has been replaced with the
more internationally compatible term--FSTD. The term FSTD more
accurately addresses the full range of uses for these devices as
addressed in part 60 and also harmonizes with the Joint Aviation
Authorities (JAA) of Europe. In addition, to more appropriately
describe the devices, the term Flight Simulator has been changed to
Full Flight Simulator (FFS). Another clarification the FAA has made
with respect to terms and definitions is that the Quality Assurance
Program (QAP) is now called a QMS.
The QPS requirements in appendices A through E are regulatory.
Future changes and additions to these standards are subject to notice
and comment rulemaking procedures under the Administrative Procedure
Act, unless ``good cause'' (see 5 U.S.C. 553(b)(B)) exists to justify
proceeding without notice and comment. In addition, the FAA has issued
FAA Order 1110.136, ``Flight Simulation Device Aviation Rulemaking
Committee.''
What Action Is the Agency Taking?
The FAA is adding part 60 to Title 14 of the Code of Federal
Regulations to establish qualification requirements for flight
simulation training devices (FSTD). These requirements are based on the
current requirements found in appendix H of part 121 and Sec. 121.407
for the capability and performance of aircraft simulators. The new rule
also incorporates certain existing practices that were previously
described in the following Advisory Circulars: AC 120-40B, Airplane
Flight Simulator Qualification, AC 120-45A, Airplane Flight Training
Device Qualification, and AC 120-63, Helicopter Simulator
Qualification.
[[Page 63394]]
Why Is the Rule Necessary?
The rule is necessary to promote standardization and accountability
for FSTD maintenance, qualification and evaluation for use in an FAA
approved flight training program. FSTDs are often used in lieu of
aircraft to train and check individuals for purposes of issuing airmen
certificates and ratings. FSTDs are also used to meet FAA air carrier
training requirements for flight crewmembers. In fact, depending on the
status of the airman and the sophistication of the device, an FSTD may
be used for 100% of the training, testing, and checking required by the
FAA. Training in an FSTD is most effective when the FSTD closely
matches the performance and handling characteristics of the aircraft
being simulated. This rule sets forth the regulatory process for
establishing the qualification level of the FSTD and for the continuous
review and inspection of FSTD performance to identify potential
problems with FSTD maintenance and operation. The new rule will improve
flight crewmember training, reduce operational errors and increase
safety. It will also provide the standards that must be reached in
order for a device to be qualified at a certain level (i.e., Level A,
B, C, or D Simulators and Level 4, 5, or 6 Training Devices).
Generally speaking, the amount of training and testing that can be
conducted in an FSTD for the purpose of meeting FAA airmen
certification or training requirements is directly proportional to the
qualification level of the device. Thus, a device with a higher
qualification level (e.g., Level D) will be eligible for more
certification and training credits than a device with a lower
qualification level (e.g., Level A).
Qualification Performance Standards (QPS)
One of the unique features of the part 60 rule is the incorporation
of QPS. The QPS is an appendix to the regulation and outlines
requirements and other information regarding the qualification,
performance, evaluation and maintenance of FSTDs. The QPS contains
several charts. Some of the charts prescribe regulatory requirements,
while others outline general information and examples to assist the
user in meeting the regulatory requirements.
The charts containing regulatory material are labeled ``QPS
Requirements.'' Compliance with the criteria in these charts is
mandatory in order to receive and maintain approval from the FAA for
the qualification level and use of an FSTD. Changes to a QPS
Requirement are subject to notice and comment rulemaking procedures
under the Administrative Procedure Act, unless ``good cause'' (see 5
U.S.C. 553(b)(B)) exists to justify proceeding without notice and
comment. The charts containing general information and examples are
labeled ``Information.'' Compliance with the material contained in
these charts is not mandatory, and changes to an Information section
are generally not subject to notice and comment rulemaking procedures.
The Information charts are included simply to provide additional
guidance to the user.
Incorporating both the regulatory and advisory material into the
QPS consolidates all of the relevant information and makes it available
in one location. This promotes ease of use and greater uniformity among
those involved in every aspect of FSTD performance, including
manufacturers, airmen, training providers and regulators. Moreover, it
gives greater insight to the regulated community regarding the FAA's
intent behind the regulation, and the required and approved methods of
compliance.
Comments
The FAA received 54 comments in response to the NPRM. Commenters
included industry associations, airlines, training centers and schools,
aircraft manufacturers, simulator and flight training device
manufacturers, pilot associations, governmental organizations, and
individuals. The major concerns of the commenters were harmonization of
FAA standards with those of International Civil Aviation Organization
(ICAO) and the JAA, the cost of complying with the new requirements,
grandfathering existing simulators and other flight training devices,
the requirement for a Quality Assurance Program (QAP), and the proposed
requirements to be approved by the FAA as an FSTD ``sponsor.''
The FAA reviewed all comments. They are more fully explained in the
Discussion section to follow. With respect to the major concerns raised
by commenters, the FAA took the following actions:
Revised certain sections of the QPS Requirements to
incorporate ICAO/JAA standards that were within the scope of the
original NPRM. Changes that are beyond the scope will be incorporated
in future revisions to the QPS Requirements.
Revised certain requirements where appropriate in order to
reduce costs. The FAA notes, however, that part 60 is largely a
codification of existing practices, and therefore, the agency does not
anticipate that sponsors will incur many new or additional costs. The
FAA's cost projection is outlined in the Regulatory Evaluation.
Excluded Levels 2 and -3 Flight Training Devices from this
rulemaking effort. The FAA will review its existing advisory material
and determine the best method to continue to evaluate and qualify these
devices.
Replaced the QAP proposal with a Quality Management System
(QMS). The QMS is significantly less costly than the proposed QAP.
Eliminated the 600-hour annual use requirement for
sponsorship eligibility. Persons are now permitted to sponsor an FSTD
as long as the device is used at least once per year in an FAA approved
training program, or at least once per year a pilot, appropriately
qualified on the aircraft being simulated, flies the FSTD and confirms
that the performance and handling qualities are like the aircraft.
Many other detailed comments of an editorial nature were also
provided. These are not included in the summary, but have been
carefully reviewed by the FAA in preparing the Final Rule. In addition,
the specific comments on the QPS appendices are not summarized in the
Final Rule summary, but have been carefully reviewed and incorporated,
where appropriate, into the Final Rule. The FAA made certain changes to
the QPS appendices from the proposed language to include technical
corrections and clarifications that did not adversely affect safety and
were within the scope of the NPRM. There were other technical changes
that the FAA did not incorporate into this final rule because they were
beyond the scope of the NPRM. The FAA will issue another NPRM to
incorporate the changes that were beyond the scope of the original
NPRM, and will incorporate these changes before the rule becomes
effective. All of the comments are available for review at https://
dms.dot.gov. The Docket Number is 12461.
Abbreviations Used in this Preamble
AC Advisory Circular
ALPA Airline Pilots Association
AOPA Aircraft Owners and Pilots Association
ARC Aviation Rulemaking Committee
ATA Air Transport Association
ATOS Air Transportation Oversight System
CBT Computer Based Training
DPE Designated Pilot Examiner
EASA European Aviation Safety Authority (formerly Joint Aviation
Authorities (JAA)
FFS Full Flight Simulator
FOQA Flight Operations Quality Assurance
FSB Flight Safety Boeing
FSD Flight Simulation Device
[[Page 63395]]
FSDO Flight Standards District Office
FSI FlightSafety International
FSTD Flight Simulation Training Device
FTD Flight Training Device
ICAO International Civil Aviation Organization
MQTG Master Qualification Test Guide
MR Management Representative
NAFI National Association of Flight Instructors
NATA National Air Transport Association
NBAA National Business Aviation Association
NDB Non-Directional Beacon
NPRM Notice of Proposed Rulemaking
NSP National Simulator Program
NSPM National Simulator Program Manager
POI Principal Operations Inspector
QPS Qualification Performance Standards
QAP Quality Assurance Program
QMS Quality Management System
QS Quality System
QTG Qualification Test Guide
RAA Regional Airline Association
SITC Simulation and Instrument Training Center, Inc.
SOQ Statement of Qualification
TCPM Training Center Program Managers
Thales Thales Training & Simulation
TPAA Training Program Approval Authority
UA United Airlines
UAA University Aviation Association
UPS United Parcel Service
General Issues
General Comments
Eclipse, NLX Corporation, JAA, and an individual, applaud and
appreciate the FAA's attempt to amend the regulations for FSTDs. JAA
writes that the ``proposal takes care of the legal concern that
regulations in this area have to have a mandatory basis * * * and it
concentrates all related material in one document.'' This commenter
states that this proposal did not address the latest modifications
applied to the ICAO Manual and questions if using an FSTD instead of an
aircraft would be made mandatory. An individual writes that
simplification and consolidation of these regulations are appropriate
and more detailed regulations and device inspection will force flight
training schools to improve and that ``somewhat of a loophole'' in
flight training in flight simulators and flight training devices would
be closed. NLX indicates that these new regulations are a step forward
in the overall process of FSTD qualifications. An individual believes
that statistics proving that the use of simulator training has reduced
aviation accidents or incidents are needed.
FAA Response: This final rule does not mandate the use of FSTDs
instead of aircraft for training. This rule simply establishes FSTD
qualification requirements. The FAA is developing an NPRM that proposes
to revise the QPS appendices to achieve the desired level of
harmonization.
Disposition of Level 7 Flight Training Devices
Regional Airline Association states that the preamble should
discuss the disposition of Level 7 FTDs.
FAA Response: The original premise for the Level 7 FTD was that
there was to be an aircraft entering service that would not have an
``on-set motion cue'' with the failure of an engine, and that the
pilots training in an FSTD for that airplane type could be trained and
checked on such an engine failure without requiring a force (motion)
cueing system. The FAA determined that a Level C simulator aerodynamic
data package would be required for the level 7 FTD to accurately
simulate such an aircraft. However, the airplane never entered service
and the requirements for the Level 7 FTD quickly became superfluous.
Level 6 and Level 7 FTDs had the same authorizations (except for one
area involving ``icing accountability''), but the Level 7 FTD continued
to require significantly more aerodynamic data for no more value than
the Level 6 FTD. The elimination of the Level 7 FTD does not preclude
any Level 6 FTD from incorporating a Level C data package and having
essentially the same kind of device as the originally described Level 7
device. However, there has been essentially no difference between the
two levels in authorized use, and it made little sense to continue with
a Level 7 FTD when there was little difference between a Level 6 and
Level 7 FTD.
The FAA is considering future rulemaking to develop standards for
Level 7 FTDs for helicopters. Any new requirements would be subject to
notice and comment.
Rule vs. QPS
Continental asserts that there is a conflict between the rule and
the Qualification Performance Standards (QPS). Continental states that
the rule addresses a number of technical issues that would be best
delegated to the QPS, and also notes that parts of the rule and its
application have different definitions than the QPS.
FAA Response: In the final rule, we eliminated the repetition of
the rule language in the QPS appendices because it was never the FAA's
intent to have different definitions for terms in the rule and the QPS
appendices. The FAA has also revised the rule language and the QPS
appendices so that technical information is presented in the most
appropriate sections and formats.
Codified Design Criteria
Northwest writes, ``The proposed regulation should be streamlined
to centrally codify simulator design and qualification criteria.''
FAA Response: The FAA deems it appropriate to stop short of
establishing a regulation mandating the design and construction
criteria for these devices. While the FAA has type certificate
requirements for aircraft instead of individual qualification
requirements like we have for FSTDs, the FAA is not including such
requirements in this final rule. We believe requiring a type
certificate process would create the potential for enormous cost
increases with virtually no gain in the quality of the devices.
Clarification of Requirements and Oversight Responsibilities
TWA and CAE were concerned with the lack of clarity in the rule
language. Specifically, TWA wants the rule rewritten clearly stating
FAA's intentions and adding that the National Simulator Program Manager
(NSPM) has full authority over FSTDs and all results of other
inspections must go through the NSPM before action can be taken. CAE
expressed a similar concern.
FAA Response: The FAA revised the part 60 rule language and QPS
appendices to ensure the requirements are clear. The QPS appendices
provide examples and additional information and criteria outlining the
method of compliance with the regulations. In addition, the FAA has
clarified the NSPM will exercise oversight responsibility for the
evaluation and qualification of all FSTDs included in part 60.
Use of FSTDs in the Course of Training
FlightSafety Boeing (FSB) believes part 60 ``should be limited to
the definition, design criteria, required documentation and record-
keeping of Flight Simulation Devices, and the evaluation process to
assure continued functionality as designed, for the respective level of
device.'' In FSB's opinion the authority on planned or actual use of
FSTDs in the course of training should remain with the respective
sponsor of the device and the Training Program Approval Authority
(TPAA) as presently required in existing regulations. Also, FSB writes
that all proposed wording addressing the continued use of a device be
eliminated, including the words ``and use'' in the title of the
proposal.
FAA Response: The final rule addresses the definition, required
documentation and record keeping for
[[Page 63396]]
FSTDs. It also outlines the evaluation process to assure continued
functionality of FSTDs, including the objective and subjective
requirements. However, as stated earlier, the FAA has determined it is
not appropriate to include FSTD ``design criteria'' in the final rule.
Also, the phrase ``and use'' in the title of the part 60 rule does not
apply to the actual ``use'' of an FSTD in the course of training
approved by the TPAA. Rather, the term refers to those uses of the FSTD
for which representatives of the NSPM have qualified a specific FSTD.
NSP Office
TechniFlite states, ``There should be an official (rather than
implied or assumed) FAA office established at the Washington level to
be responsible for the oversight of the National Simulation Program.
This office could be responsible for reviewing appeals when disputes
with the NSP arise.''
FAA Response: The NSP is part of the Flight Standards Service.
Specifically, it is part of the Air Transportation Division, AFS-200,
and answers directly to the AFS-200 manager in Washington, DC. An
appeals process is outlined in Sec. Sec. 60.5(d) and 60.29(b). In both
cases, the Director of the Flight Standards Service, AFS-1, is the
person/office to whom appeals should be made.
Level of Detail in Regulations
Thales Training & Simulation (Thales) ``objects to the way that our
regulations are becoming so overly prescriptive.''
FAA Response: The part 60 rule is, for the most part, a
codification of existing practices. However, there are new requirements
such as the QMS requirement in Sec. 60.5. The FAA, working with the
ARC, including Thales, developed requirements that balance safety
concerns without being overly burdensome.
Necessity of the Rule
Several commenters question whether this rule is needed. American
Airlines states that it has worked closely with the NSPM to develop its
simulator program and it believes it has the highest quality simulator
program in the world. American sees ``nothing in the NPRM that will
result in an increase in the quality or effectiveness of the American
Airlines training program.'' Similarly the National Business Aviation
Association (NBAA) does not think the rule will result in a safety
enhancement, stating that, ``there has been no evidence that the
current system of certifying and maintaining flight simulator devices
has compromised safety in any way.'' The Aircraft Owners and Pilots
Association (AOPA) states that the proposed rule ``places an
unnecessary regulatory burden on the aviation industry, and it does not
address a safety problem or provide a net safety benefit.'' Storm Haven
Aviation and a flight instructor make similar comments.
FAA Response: Codifying simulation qualification standards provides
for a ``level playing field'' among FSTD manufacturers and sponsors in
the United States and a harmonization of interests internationally.
Further, these provisions, together with the provision for a QMS, will
provide each sponsor a clear understanding of what is required of them
for a satisfactory FSTD. The FAA also notes that part 60 is largely a
codification of existing practices, and does not impose significantly
new burdens. The FAA recognizes the close working relationship that
exists between the NSPM and a large portion of the aviation training
community. That close working relationship continues with this
rulemaking effort and should continue after the rule becomes effective.
The FAA believes that the rule will result in an increase in the
quality and effectiveness of flight training programs without an undue
burden on the industry.
Withdraw NPRM
Air Transport Association (ATA) requests the immediate withdrawal
of the NPRM and the formation of an industry-government advisory
committee to develop a new proposed rule. In support of this request,
ATA states five general concerns with the NPRM:
1. If published as currently written, the NPRM would eliminate
the use of a significant number of simulators until they could be
qualified or replaced.
2. The proposed rule ignores harmonization efforts between the
FAA, the JAA, and the simulator industry.
3. The FAA currently is revising Subparts N & O of FAR Part 121,
which deal directly with crew training and the practical use of
FSTD. However, the NPRM overlaps and implicates training
requirements, and thus it is impossible to determine the overall
impacts of the NPRM until the training requirements of Subparts N &
O are revised or clarified.
4. The NSP, or each responsible TPAA, would have to be manned on
a 24 hour/7 days per week basis to administer the proposed FAR Part
60 requirements in order to prevent unnecessary FSTD downtime.
5. The NPRM places a severe financial burden on U.S. airlines.
The cost of the NPRM is not justified by its benefits.
Several other commenters, including Bombardier, FedEx, American
Trans Air, TWA, Continental, and DHL agree with ATA's position that the
NPRM should be immediately withdrawn and that an industry-government
advisory committee should be convened to develop a new proposed rule.
Other commenters did not specifically cite the ATA position, but did
suggest that a more effective rule would be achieved through government
and industry collaboration.
FAA Response: Rather than withdraw the NPRM, the FAA established
the ARC. The overwhelming majority of the ARC members, including ATA
members and an ATA representative, participated in the development of
recommendations to the FAA. As proposed in the NPRM, each currently
qualified FSTD will continue to be evaluated against the criteria
current at the time of that FSTDs original evaluation (67 FR 60291). No
currently qualified FSTDs will be disqualified because of the new part
60 evaluation requirements. Therefore, the FAA does not expect that
anyone will be ``driven back into the airplane'' for training, testing,
or checking because of the part 60 final rule.
In addition, the standards contained in the final rule have been
modified so they are more in line with ICAO and JAA standards. Also, as
mentioned previously, the FAA is continuing its efforts to achieve the
desired level of harmonization. The FAA would like to note that part 60
is not interdependent with and does not overlap the rulemaking effort
to revise 14 CFR part 121, Subparts N and O. The part 121, Subparts N
and O rulemaking deals directly with flight crewmember training and the
practical use of FSTDs, while part 60 deals with the standards for FSTD
qualification and evaluation.
Cost of the Proposed Rule
A group of commenters cite cost as the reason the NPRM should be
withdrawn. AOPA states that the proposed rule places an unnecessary
regulatory burden by imposing a large cost without properly identifying
the cost impact. TechniFlite explains that with the cooperation of the
FAA and industry, initiatives can be taken to make significant
reductions in the cost of simulators thereby making simulators more
available to the broader needs of the industry. Professional Instrument
Courses believes that the proposed rule would add needless expense to
their company with no gain in the quality of safety of their program
and would put their successful 22-year-old instrument flight training
company out of business.
FAA Response: The FAA continues to believe that training in an FSTD
is most effective when the FSTD closely
[[Page 63397]]
matches the performance and handling characteristics of the aircraft
being simulated. Accordingly, training and checking activities should
be accomplished only in those devices that are objectively and
subjectively evaluated. The rule creates no new technical requirements
for qualification of the basic levels of FTDs. The NSPM has maintained
an open and continuous dialogue with aircraft simulator manufacturers
and users. This dialogue continues to enhance the quality of
simulation, improve the evaluation of simulation devices, and reduce
the costs of acquiring, evaluating, and using these devices for flight
crewmember training and checking. It is the FAA's intent to maintain
this on-going effort.
Advisory Circulars vs. Regulations (Appendices A-D)
Three commenters disagree with including the advisory language that
currently exists in the Advisory Circulars (ACs) for airplane
simulators and flight training devices in the proposed rule. Delta
states that the advisory language is very lengthy and detailed and that
after incorporating this language into the rule, the FAA and users will
need to strictly abide by it and any changes would need to go through a
lengthy revision process. Regional Airline Association (RAA) says the
proposed QPS appendices are written as ``engineering standards,'' as
opposed to performance standards. RAA believes the FAA should adopt
performance based regulations whenever possible because they allow for
flexibility and freedom for innovation. RAA states its concern that
even seemingly minor requests for deviations from the QPS appendices
content will require that operators/owners petition the FAA for
deviation approval, a process it says takes weeks and most often months
for approval. In addition, RAA notes, ``no specific instances of the
proposal were mentioned as to industry's failure to constructively use
and follow the content of the AC's.'' FSI says the NPRM preamble
incorrectly explains that the FAA is proposing to remove the technical
requirements from part 121 and place them in the new part 60. FSI
maintains that these requirements have always been advisory and not
regulatory, and recommends that the FAA clearly acknowledge that a
major purpose of this rulemaking is to make previously advisory
material mandatory.
The National Association of Flight Instructors (NAFI) agrees
completely with moving the requirements into the proposed rule. It
applauds and unequivocally supports the FAA's efforts to make these
requirements regulatory rather than advisory.
FAA Response: The FAA disagrees that the QPS appendices are written
as an engineering standard, rather than as a performance standard. The
QPS appendices are a codification of existing advisory material that
was used to determine whether or not a specific FSTD met FAA
requirements. These standards have always been ``performance
standards,'' involving an objective and subjective evaluation of the
device in comparison to the aircraft. There has never been a
requirement for an ``engineering standard'' in simulation beyond that
which is necessary to meet the stated performance objectives. Part 60
does not change these requirements.
The decision to codify FSTD qualification requirements was made
after careful consideration of facts and circumstances. This decision
is not a result of ``industry's failure to constructively use and
follow the content of the AC's.'' Rather, the FAA has determined that
continued oversight through the issuance and application of ACs is not
appropriate. Executive Order 12866 states ``(e)ach agency shall draft
its regulations to be simple and easy to understand, with the goal of
minimizing the potential for uncertainty and litigation arising from
such uncertainty'' [section 1(b)(12)]. Additionally, Section 5-1 of FAA
Order 1320.46A, ``Advisory Circular System,'' states that
AC's are not regulations and may not impose or lessen a burden
on anyone, nor have a mandatory effect. AC's may not be used to add
to, interpret, or relieve a duty imposed by a Federal Aviation
Regulation (FAR). Advisory circulars may set forth `acceptable
means' or `methods of compliance' with a particular FAR. However,
the language used to explain the compliance methods in the AC must
not imply that it is the only or minimum acceptable means, nor
require other methods of compliance to be `equivalent' to the one
described in the AC.
In order to be legally valid, a regulation must establish a
requirement or standard that is sufficiently clear to persons required
to comply with it so that they can have a reasonable understanding of
what is expected of them, without having to resort to material not
published in the rule. In other words, the regulation must be able to
stand on its own. The regulations that support the current set of ACs
describing simulation standards are found in 14 CFR part 121, Subpart N
and, since 1980, part 121, appendix H. However, in neither of these
rule sections is the regulatory language sufficient to meet the
requirement that persons would not have to resort to additional
material not published in the rule. Additionally, while FSTD
qualification standards have been contained in ACs, they have been
treated as though they were regulatory. Clearly, this practice is not
in compliance with either the EO or the FAA Order. Therefore, the
development of a rule for the qualification of FSTDs was imperative.
Due to a comment, the FAA recognized that it did not have rule
language in the part 60 NPRM that proposed to remove technical FSTD
requirements from part 121. In the final rule, we have removed from
part 121 those technical FSTD requirements that are in part 60. It was
an administrative oversight that we neglected to propose removing
technical FSTD requirements from part 121, but we were clear in the
NPRM that part 60 would serve as the regulatory part for FSTD
qualification and evaluation.
The FAA is aware that there are differences in the application of
what may be authorized under an advisory circular concept and what may
be required or authorized under a regulatory concept. However, the
language of this final rule has been carefully constructed to
accommodate ``operations and engineering judgment'' when applying
flight test data to objective test requirements and tolerances. The
goal was to allow the logical application of this judgment while, at
the same time, not allow complete ``free play'' with FAA standards.
QPS Document
FSI states ``The Qualification Performance Standard (QPS) contains
regulatory language that appears only in the QPS. The combination of
information, data, and regulatory language will create misunderstanding
between FAA and the industry.'' In addition, FSI believes that the
``tabular technical requirements in the QPS are also confusing due to
the outdated condition of the tolerances and test descriptions.'' FSI
further states, ``The most glaring of the unrealistic requirements in
the QPS is the motion system `specifications.' In the past when rules
have attempted to define hardware and software simulator system
`specifications,' the rules became obsolete before they were
published.'' Therefore, FSI recommends the QPS define tolerances, not
design specifications.
TWA states that the ``direct quote or a paraphrasing of the Part 60
rule'' in the QPS documents is sometimes very confusing and sometimes
they are in disagreement with the rule. TWA recommends removing them to
make the QPS smaller and easier to use.
[[Page 63398]]
FAA Response: The FAA has revised the final rule to eliminate the
motion system standards published in the NPRM. Additionally, the FAA
has removed the part 60 rule language from the QPS appendices to avoid
confusion and repetition. The FAA recognizes the necessity of
additional modifications to certain sections of the QPS appendices that
are beyond the scope of the NPRM. The FAA is continuing to revise the
QPS, and any recommendations for changes to part 60 will be available
for public review and comment as an NPRM prior to being adopted. It is
the FAA's intent the part 60 final rule not be effective until the
first revision of the QPS appendices have been published in the Federal
Register as a final rule.
Related to N&O Rulemaking
FSI notes that the preamble states ``In a separate rulemaking
project that will follow this proposal, other portions of appendix H
would be moved to a new subpart of part 121, and appendix H would be
deleted.'' Concerned that timely action may not be taken and
considering the length of time for rulemakings, FSI requests that the
FAA make the necessary and proper conforming changes now and amend
Sec. 121.407 and delete appendix H.
Air Transport Association (ATA) states that this NPRM and subparts
N and O of part 121 are very closely linked, and ``recommends that any
proposed changes to Subparts N and O be coordinated with this
rulemaking and, in particular, that any changes to Subparts N and O
precede this rulemaking.''
FAA Response: The FAA recognizes 14 CFR part 121, appendix H has
both technical requirements and operational authorizations. By
``removing and reserving'' certain sections in the current part 121,
appendix H, (i.e., those sections dealing with technical requirements
of FFSs) without canceling the entire appendix, the remaining sections
of appendix H will continue to serve operational necessities until such
time as appendix H is cancelled. The requirements contained in 14 CFR
121.407 are not contrary to the requirements contained in part 60.
Changes to 14 CFR part 121, Subparts N and O will include
references to FSTDs, but only to the extent of defining what tasks may
be authorized for part 121 flight crewmembers in a given level of FSTD.
Part 60, including all of the evaluation and qualification
requirements, is not dependent upon or interdependent with, any future
Subparts N and O changes that may be proposed or adopted.
Harmonization and ICAO
Many commenters address the issue of harmonization of FAA's FSD
qualification standards with those of ICAO and the JAA. Boeing, United,
Continental, American, FSI, FSB, NLX, CAE, and Eclipse are concerned
that the NPRM does not include recent industry efforts to harmonize the
latest regulatory standards for the qualification of FSDs. Delta
commented that an opportunity to revise the rule would provide a chance
to define an improved revision process for the advisory material and to
incorporate harmonization with the ICAO Manual of Criteria for the
Qualification of Flight Simulators. Eclipse states that the ICAO Manual
of the Criteria for the Qualification of Flight Simulators, 2nd
edition, which was endorsed by the FAA, should be incorporated into the
QPS appendices. Continental states that a lack of harmonization will
impose a financial burden on the carriers when they sponsor or use FSDs
that are currently approved under the ICAO standard. American states
that, instead of matching the ICAO criteria, the NPRM appendices
contain a version of the criteria contained in the Draft AC 120-40C,
modified with additional requirements. American states that since the
FAA is on record as planning to eventually adopt the ICAO criteria,
there is no reason not to do it in this rule.
NLX comments that although updating the QPS should not require the
lengthy time frames experienced with changes like AC 120-40C, the
industry has no assurance this will occur. NLX is concerned that after
the rule is in place, updating the QPS will result in an extended time
frame of possibly several years during which the industry must comply
with the obsolete requirements. NLX states that, without some guarantee
that this will not be the case, it recommends that the QPS be updated
to reflect the latest JAR/ICAO material before the rule is put into
effect.
FSB states that the proposed FAA standards are significantly
different from the JAR STD 1A requirements, which are stricter. FSB
urges the FAA to reconsider the timetable so as to include the recent
updates to the ICAO 9625, JAR STD 1A and to remove changes to the
motion standards in appendix A, which were vigorously disapproved by
industry when added to the AC 120-40C. If the plan is to go forth with
the rulemaking process with the existing differences, FSB strongly
suggests that the FAA comment on an implementation plan and timetable
for complete harmonization to take place.
United comments that the proposed standards decouple the functional
and subjective test requirements from the FSD qualification level and
require an FSD qualification task list without offering any criteria
against which such tasks would be approved. United states that this is
a break from past FAA practice, from the current JAA practice, and from
the recommendations in the ICAO Manual.
Boeing comments that considerable industry time and expense has
been expended over the past years to harmonize the standards. The
results of these efforts have been incorporated into the ICAO Manual
and are in the process of being incorporated into the JAA's JAR-STD 1A
document, Aeroplane Flight Simulators. In addition, Boeing states, a
set of ``best practices'' advisory material has been developed and is
being included in both JAR-STD 1A and ICAO Document 9625. According to
Boeing,
The latest standards and best practices material has not been
included in the FAA's proposed Part 60. If the NPRM were to go
forward as proposed, there would be two different sets of standards
for the regulated public to comply with. This would impose an
unnecessary adverse economic impact on the industry, including the
data provider. We consider that the proposed Part 60, as currently
structured, would be unacceptable to the industry, and both
difficult and costly for the FAA to administer. We strongly
recommend that the FAA revise the NPRM prior to any further action.
Boeing includes in its comments an extensive history of the
harmonization efforts and detailed suggestions on how to harmonize the
NPRM with the JAA and ICAO material.
CAE comments that ``The United States has been a leading voice in
encouraging other countries to adopt and maintain international
standards; implementation of Part 60 regulations that are inconsistent
with ICAO standards would undermine the U.S. Government's credibility
in making these arguments to other countries.''
Several commenters disagreed with the statement in the NPRM
paragraph on ``International Compatibility'' that the FAA had
identified ``no differences'' between the proposal and the ICAO
Standards and Recommended Practices. Thales Training and Simulation
states ``where there are major deviations between the proposed Part 60
standards and the latest agreed ICAO standards, the motion requirements
being a good example, industry needs to be aware of how the Part 60
standards will evolve towards the ICAO standards. It is
[[Page 63399]]
unreasonable for industry to be expected to expend major investment to
meet a standard that may only be in existence for a few months.'' CAE
states there are several instances in which the proposed rule
significantly differs from ICAO standards, including areas such as
latency, tolerances, organization of validation test cases, numbering,
and definitions. CAE recommends that the FAA identify and clarify the
differences between the two standards and confirm whether the ICAO
standards could be used as an acceptable alternative for obtaining FAA
qualification of an FSD. ATA states that the rule should not be
published until the QPS documents are updated to reflect the ICAO
guidance.
FAA Response: The FAA recognizes it is necessary for simulator
qualification technical requirements to reflect international standards
as appropriate. The FAA plans to harmonize the simulator qualification
technical requirements as part of the first revision of the QPS
appendices.
Impacts on General Aviation
Several commenters are concerned about the impact of the proposed
rule on the use of FSDs by general aviation, particularly with respect
to Level 1-3 FTDs.
FSI states that the NPRM preamble language stating that ``other
certificate holders may seek approval to use the same FSD'' seems to
eliminate non-certificate holders, such as corporate or private
operators under part 91, from doing the same thing. FSI comments that
fractional ownership operators would be precluded from being sponsors
by the same wording.
Fidelity comments that due to the recent advent of affordable,
significant computing power, general aviation is able to use advanced
simulation and that part 61 allows for a significant usage of FSDs.
Fidelity comments that the proposed rule is unclear as to whether a
sponsor must be a certificate holder in order to use the FSD for part
61 training.
NAFI is also concerned about the potential impact of the proposed
rule on general aviation flight instruction. NAFI states that the
required level of actual aircraft emulation for high-end, full motion
simulation should be vastly different from general aviation flight
training devices, and this proposed rule appears to lump them together.
Specifically, NAFI states, smaller operators with less sophisticated
FTDs will be unnecessarily burdened by the required establishment of
the QAP and daily inspections.
National Air Transportation Association (NATA) comments that the
proposal seems to give consideration only to training that targets
commercial and high-end corporate aircraft operators and makes no
attempt to provide a framework that enables the greater deployment of
these devices for light general aviation and corporate aircraft.
Furthermore, NATA states that placing the responsibility for
qualification of FSDs and FTDs with the National Simulator Program
Office will limit the ability of the aviation industry to use such
devices.
FAA Response: Only those persons required to have an FAA approved
flight training program or otherwise authorized under Sec. 60.7 are
eligible to sponsor an FSTD. The FAA acknowledges that Fractional
Ownership Program Managers are required by Sec. 91.1073 to have an FAA
approved flight training program. However, this requirement did not
exist when the proposed part 60 was being drafted because the
fractional program regulations had not been finalized. It is beyond the
scope of this rulemaking project to include Fractional Ownership
Program Managers as eligible FSTD sponsors. Therefore, the FAA will
initiate a separate rulemaking project to incorporate Fractional
Ownership Program Managers into the class of persons eligible to
sponsor FSTDs. The FAA does not intend to allow other part 91 operators
to be FSTD sponsors because they are not required to have an FAA
approved flight training program.
The FAA has not included the qualification requirements for Level 2
and 3 FTDs in this final rule. The FAA has determined that these
devices should continue to be monitored and qualified under advisory
material. The FAA has posted, for comment, an Advisory Circular
providing guidance about the evaluation and approval of Basic Aircraft
Training Devices and Advanced Aircraft Training Devices. To view and
comment on the Advisory Circular go to the following Web address:
https://www.faa.gov/aircraft/draft_docs
Conforming Changes (Parts 61, 63, 125, 137, 141, and 142)
FSI states that training, testing, and checking requirements of
parts 125 and 137 may be accomplished in FSDs, but there is no
reference to these parts. FSI suggests that the FAA clearly state the
permitted uses of FSDs.
FSI, NATA, University Aviation Association (UAA), and Purdue
University comment that the NPRM states that the devices described in
Sec. 61.4 may be used only for private pilot certification and
instrument ratings. These commenters state that training for a
commercial pilot certificate and training under part 141, Pilot
Schools, can also be done in an approved training device; they ask the
FAA to verify the uses permitted for approved training devices under
parts 61 and 141.
FSI states that it is mandatory to withdraw appendix H of part 121
in order for part 60 to be possible. FSI also cites other sections that
should be changed (e.g., Sec. Sec. 121.407, 135.335, 142.59, 141.41,
135.324, 135.321, and 121.402). FSI suggests that the FAA conduct a
comprehensive review of all rules that may be in contradiction to part
60 and make the appropriate changes.
FAA Response: The permitted uses of FSTDs for credit purposes
(i.e., to meet airmen certification standards or certain commercial
operator training requirements) are a topic for a different rule. Part
60 addresses only the requirements for the evaluation and qualification
of FSTDs. Section 61.4 does not state that FSTDs may only be used for
private pilot certification and the instrument rating. Rather, Sec.
61.4(a) specifically refers to ``any training, testing, or checking
requirement under this chapter.'' ``This chapter'' refers to Chapter I,
Subchapter D (Airmen), and specifically, all airmen, certificates, and
ratings falling under the purview of part 61, Certification of pilots,
flight instructors, and ground instructors.
It is not necessary to withdraw all of 14 CFR part 121, appendix H
because of part 60. As stated earlier, the FAA is ``removing and
reserving'' appropriate sections of appendix H to eliminate those
technical requirements that have been moved into part 60 and is
retaining those operational requirements in appendix H until such time
as those sections are combined in a subsequent rulemaking effort and
appendix H is cancelled. Additionally, the requirements contained in
Sec. Sec. 121.407, 135.335, 141.41, and 142.59 are not contrary to the
requirements contained in part 60. The FAA has reviewed all other
sections to see if any additional conforming changes need to be made
because of part 60.
In addition, the FAA has determined that the conforming changes to
parts 61, 141, and 142 proposed in the NPRM are no longer necessary
since Level 2 and 3 FTDs are not included in this final rule.
Impact on Part 142
FSI states that when part 142 was issued, training centers were
given regulatory assurance that if they did certain things, the
Administrator was obligated to issue a certificate under that part. FSI
believes that for the FAA to propose now that another step is
[[Page 63400]]
required, i.e., gaining approval as a sponsor, is improper. Also, FSI
states training centers were told they would not be required to have
any specific relationship with an air carrier, yet under this proposal
a training center may have to have an air carrier client as the sponsor
of the FSD, for example, to meet the minimum annual usage requirement.
FAA Response: The FAA eliminated the hourly usage requirements for
sponsor qualification. The FAA eliminated the proposed requirement for
sponsor utilization of additional simulators, except for the initial
FSTD to qualify an applicant for a part 142 Training Certificate or the
initial FSTD as part of a part 119 FAA-approved flight training
program. The FAA has determined that these proposed requirements are
not necessary because the requirements for an FAA approved training
program are sufficiently robust to ensure safety.
Elimination of Exemptions
AOPA states that the proposal places additional regulatory burdens
on the entire aviation industry, including small pilot training
centers, simply to allow the FAA to rid itself of the burden of issuing
exemptions to part 125 and 135 operators who wish to use Level A-D
flight simulators under part 121, appendix H. Instead, AOPA suggests
making the appropriate changes in parts 125, 135, and 142 by cross
referencing part 121, appendix H. According to AOPA, the proposal
should then be modified to address only part 125 and 135 operators and
Level A-D flight simulators.
FAA Response: The purpose of this final rule is not to relieve the
FAA of the task of issuing exemptions. The requirements set out under
part 60 are for the evaluation and qualification of FSTDs, a task that
the FAA has to perform regardless of whether the device will be used in
air carrier operations or not. This final rule codifies existing
practices and provides uniform standards for all FSTDs regardless of
where they will be used. Authorized uses under any individual part of
14 CFR are contained in the respective part. Therefore, even if a
device is evaluated and qualified for certain tasks and maneuvers, the
FAA, independent of part 60, will still need to determine whether the
device is suitable for use in a particular FAA approved training
program.
Comments Regarding Definitions
ATA states that the definition of flight simulator uses the term
``series'' of aircraft, while the definition of flight training device
uses ``set'' of aircraft. Since proposed Sec. 60.3 does not define
``series'' of aircraft and since an aircraft series meets the proposed
definition for ``set of aircraft'' and a definition for ``set of
aircraft'' is already proposed, ATA recommends that the term ``series''
should be deleted and replaced with the term ``set of aircraft''
throughout the document. In addition, the term ``ground operation''
should be replaced with the term ``surface operation,'' since surface
operation is utilized in Attachment 3 to appendix A as operational task
b. ``Surface Operations.'' Also, ATA notes that the definition of
flight training device uses the term ``full size replica,'' while
appendix B does not use this term in describing the FTD requirements.
ATA recommends using the language in appendix B, while Delta suggests
using ``realistic replica'' instead of ``full size replica.''
CAE states that in the definition of ``evaluation'' in the use of
``etc.'' is open to interpretation and should be removed. Likewise, CAE
claims that the word ``performance'' is used in a very general sense in
the definition of ``flight test data'' and in many other places. CAE
states, ``Performance in simulators has traditionally meant airplane
performance with regard to thrust/drag relationships, climb, range,
etc.'' CAE recommends defining ``Approved data supplier'' as ``the
aircraft manufacturer or other supplier of data acceptable to the
NSPM.'' CAE also recommends defining ``Performance'' as ``the overall
performance of the FSD to include aerodynamic performance as well as
flight and ground handling.'' Additionally, CAE recommends changing the
definition for ``flight test data'' to ``Actual aircraft performance
data collected by an approved data supplier during an aircraft flight
test program. This includes the aircraft on the ground test data as
well as in the air.''
FSI states that the definition of ``flight experience'' is at odds
with Sec. 61.1 and other parts of 14 CFR. FSI recommends deleting this
definition or more accurately defining it.
Boeing recommends changing the phrase ``actual or predicted
aircraft performance data'' in the definition of ``objective test'' to
``final test or approved aircraft data'' because it is not clear what
is meant by ``actual'' or ``predicted'' data. Boeing states that
``predicted data'' should apply to data that are truly predicted, i.e.,
data that are estimated for regions of the flight envelope where there
are no relevant flight test data (for example, for very high angle of
attack), or for a new airplane configuration that has not yet been
flight-tested. Boeing believes the