Flight Simulation Training Device Initial and Continuing Qualification and Use, 59600-59903 [07-4884]
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 60
[Docket No. FAA–2002–12461; Notice No.
07–14]
RIN 2120–AJ12
Flight Simulation Training Device
Initial and Continuing Qualification and
Use
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of Proposed Rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to amend
the Qualification Performance
Standards (QPS) for flight simulation
training devices (FSTD) and add a new
level of simulation for helicopter flight
training devices (FTD). The FAA
proposes to codify existing practice by
requiring all existing FSTD visual
scenes that are beyond the number
required for qualification to meet
specified requirements. The proposal
also reorganizes certain sections of the
QPS appendices and provides
additional information on validation
tests, established parameters for
tolerances, acceptable data formats, and
the use of alternative data sources. The
proposed changes would ensure that the
training and testing environment is
accurate and realistic, would codify
existing practice, and would provide
greater harmonization with the
international standards document for
simulation. None of these proposed
technical requirements would apply to
simulators qualified before May 30,
2008, except for the proposal to codify
existing practice regarding certain visual
scene requirements. The over-all impact
of this proposal would result in minimal
to no cost increases for manufacturers
and sponsors.
DATES: Send your comments on or
before December 21, 2007.
ADDRESSES: You may send comments
identified by Docket Number FAA–
2002–12461 using any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov and follow
the online instructions for sending your
comments electronically.
• Mail: Send comments to the Docket
Management Facility; U.S. Department
of Transportation, 1200 New Jersey
Avenue, SE., West Building Ground
Floor, Room W12–140, Washington, DC
20590–0001.
• Hand Delivery or Courier: Bring
comments to the Docket Management
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Facility in Room W12–140 of the West
Building Ground Floor at 1200 New
Jersey Avenue, SE., Washington, DC,
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
• Fax: Fax comments to the Docket
Management Facility at 202–493–2251.
Privacy Act: We will post all
comments we receive, without change,
to https://www.regulations.gov, including
any personal information you provide.
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 (65 FR 19477–78) or you may visit
https://DocketInfo.dot.gov.
Docket: To read background
documents or comments received, go to
https://www.regulations.gov at any time
and follow the online instructions for
accessing the docket. Or, go to the
Docket Management Facility in Room
W12–140 of the West Building Ground
Floor at 1200 New Jersey Avenue, SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
FOR FURTHER INFORMATION CONTACT:
Edward 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: Part 60
was originally added to Title 14 of the
Code of Federal Regulations on October
30, 2006, with an effective date of
October 30, 2007. In a document
published in the Rules and Regulations
section of this issue of the Federal
Register, the effective date was delayed
until May 30, 2008. This proposed rule
would change the appendices of Part 60
originally published on October 30,
2006.
Later in this preamble under the
Additional Information section, we
discuss how you can comment on this
proposal and how we will handle your
comments. Included in this discussion
is related information about the docket,
privacy, and the handling of proprietary
or confidential business information.
We also discuss how you can get a copy
of this proposal and related rulemaking
documents.
Authority for This Rulemaking
The FAA’s authority to issue rules
regarding aviation safety is found in
Title 49 of the United States Code.
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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.
Table of Contents
I. Summary of the Proposal
II. Qualification Performance Standards
(QPS) Amendment Process
III. Background
A. Current Qualification Requirements
B. Harmonization with International
Standards
C. Compliance
IV. The Proposal
A. Visual Scenes and Airport Models; Class
I, Class II, and Class III Airports; and the
FSTD Directive for Class II Visual Scenes
and Airport Models
B. New Requirements for Objective Testing
Standards
C. New Requirements for Motion Systems
for Full Flight Simulators and Level 7
Helicopter Flight Training Devices
D. New Requirements for Visual Systems
for Level C and D Full Flight Simulators
E. New Requirements for Sound Systems
for Level D Simulators
F. New Requirements for Subjective
Testing Standards for Visual Scenes and
Airport Models
G. New Level 7 Helicopter FSTD
Requirements
H. Quality Management Systems
I. New Information on Operation and
Testing Requirements for FSTDs
V. Regulatory Notices and Analyses
I. Summary of the Proposal
The primary purpose of this NPRM is
to ensure that the training and testing
environment is accurate and realistic
and provide greater harmonization with
the international standards document
for simulation. The proposed
requirements are expected to reduce
expenses and workload for simulator
sponsors by avoiding conflicting
compliance standards. These
modifications incorporate technological
advances in, encourage innovation of,
and standardize the initial and
continuing qualification requirements
for FSTDs that are consistent with the
requirements recently established by the
international flight simulation
community.
The secondary purpose of this
rulemaking project is to reorganize,
simplify, and improve the readability of
the QPS appendices. This proposal also
clarifies and codifies certain standards
presently contained in advisory
circulars. In addition, the FAA proposes
to amend the Qualification Performance
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Standards (QPS) for flight simulation
training devices (FSTD) and add a new
level of simulation for helicopter flight
training devices (FTD).
The FAA is proposing the following
improvements to its FSTD qualification
requirements:
• Provide a listing of the tasks for
which a simulator may be qualified.
• Require the collection of objective
test data during currently required
aircraft certification testing for specific
FSTD functions, including: Idle and
emergency descents, and pitch trim
rates for use in airplane simulators;
engine inoperative rejected takeoffs for
use in helicopter simulators; and
takeoffs, hover, vertical climbs, and
normal landings for use in helicopter
flight training devices.
• Provide in the QPS additional
information for sponsors on the testing
requirements for FSTDs, including the
use of alternative data sources when
complete flight test data are not
available or lesser technically complex
levels of simulation are being
developed.
• Clarify and standardize existing
requirements for motion, visual, and
sound systems, including subjective
buffeting motions, visual scene content,
and sound replication.
• By FSTD Directive require each
Class II visual scene or airport model
available in any FFS, regardless of the
original qualification date, to meet the
requirements described in Table A3C
(Appendix A, Attachment 3) or Table
C3C (Appendix C, Attachment 3), as
appropriate.
• Clarify existing Quality
Management System (QMS)
requirements by removing nonregulatory information.
Except for the FSTD Directive,
manufacturers and sponsors would not
be required to incorporate any of the
changes listed above for existing FSTDs.
The appendices and attachments to part
60 affected by this proposal would only
apply to FSTDs that come into service
after part 60 is effective (currently May
30, 2008). The proposed changes to the
QMS program would eliminate
potentially confusing information that
addresses the voluntary portions of a
QMS program. The FAA anticipates that
this proposal would result in minimal to
no cost increases for manufacturers and
sponsors.
II. Qualification Performance
Standards (QPS) Amendment Process
The part 60 Final Rule contains six
QPS appendices: Appendix A—
Airplane Full Flight Simulators;
Appendix B—Airplane Flight Training
Devices; Appendix C—Helicopter Full
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Flight Simulators; Appendix D—
Helicopter Flight Training Devices;
Appendix E—Quality Management
Systems for Flight Simulation Training
Devices; and Appendix F—Definitions
and Abbreviations for Flight Simulation
Training Devices.
The QPS amendment process is faster
than the traditional rulemaking process.
It is designed to allow modifications to
be implemented in a substantially
shortened timeframe. In the part 60
Final Rule published October 30, 2006,
(71 FR 63392), the FAA explained that
the ‘‘fast track’’ QPS amendment
process would be used to incorporate
technical changes to flight simulation
standards. The FAA anticipated QPS
amendments based on several factors
such as analysis of incident and
accident data or changes in aircraft or
simulation technology. Changes to the
QPS documents are published in the
Federal Register as an NPRM 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.
Although proposed QPS amendments
are published in the Federal Register for
public comment, the authority for final
review and issuance of the NPRM has
been delegated from the Administrator
to the Director of Flight Standards
Service. The delegation of authority
facilitates timely implementation of
improved technological advances. This
delegation of authority is exercised in
conjunction with the Office of the Chief
Counsel. If at any time during the
amendment process the Administrator,
Chief Counsel, or the Director of Flight
Standards Service determines that a
proposed amendment is not appropriate
for the streamlined process, the
rulemaking project would proceed in
accordance with the agency’s normal
rulemaking procedures.
III. Background
A. Current Qualification Requirements
The FAA issued Part 60 to promote
standardization and accountability for
FSTD maintenance, qualification, and
evaluation. The regulation codified the
standards contained in advisory
circulars and implemented the QPS
format. The QPS appendices allow
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regulatory requirements and
information to be presented in one
location. This promotes ease of use and
greater insight about the FAA’s intent
behind the regulation and the required
and approved methods of compliance.
B. Harmonization With International
Standards
During the development of the part 60
Final Rule, the international community
also began updating flight simulation
standards.1 However, many of the
changes recommended by the
international community were beyond
the scope of the part 60 NPRM and
could not be included in the final rule.
Rather than delay its efforts or issue a
supplemental notice of proposed
rulemaking, the FAA determined that
the fastest approach would be to publish
the part 60 Final Rule, delay the
effective date, and amend the technical
requirements under the expedited QPS
amendment process. This approach
avoided increased expenses, greater
workload, and conflicting compliance
requirements for sponsors who would
be required to comply with part 60.
The majority of the proposed
additions to the QPS provide
information to the sponsors on objective
tests. The information included explains
why the tests are necessary, how to
stage the simulator, and how to arrange
other equipment to conduct the tests
efficiently and produce optimum
results. This information would be
beneficial for simulator manufacturers
and users.
The proposal clarifies and codifies the
standards for motion, and visual and
sound systems. The proposal also
permits a new higher level of simulation
for helicopter FTDs. The proposal adds
2 tables of material for operations tasks
and system tasks, which are used as a
reference when developing the
statement of qualification for the FSTD.
The proposal also includes a set of
tables describing visual scene and
airport model requirements for FSTD
qualification.
Some of the proposed changes are
marginally more stringent than the
requirements in the October 30, 2006,
1 The international community began releasing its
recommendations with the publication of the
International Civil Aviation Organization’s Manual
of Criteria for the Qualification of Flight Simulators
(Document 9625) in 1994. The Joint Aviation
Authorities of Europe issued JAA–STD–1A
(Synthetic Training Device—document for airplane
flight simulators) in 1998, followed by updates in
1999, 2001, and 2003. The first ICAO update of
Document 9625 was in January of 2004 and the
most recent consideration for update is the release
of JAR–FSTD–A and JAR–FSTD–H documents in
the late spring of 2005 for European national
regulatory authorities to begin their review and
consideration.
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Final Rule. For example, a simulator
qualified at Level C or Level D after May
30, 2008, would have the field of view
and system capacity requirements for
the visual system increased by 20
percent over the present requirement.
The proposed requirements are
consistent with international standards,
which simulator manufacturers are
currently following. This change
improves the quality of simulation
necessary to train and evaluate flight
crewmembers. Other proposed changes
are more flexible than the requirements
prescribed in the October 30, 2006,
Final Rule. For example, the tolerance
for displacement in the control system
‘‘freeplay’’ test in helicopter simulators
was increased from 0.10 inches to 0.15
inches, allowing additional space to
adapt aircraft and non-aircraft hardware
for use in the simulator.2 This change
was based on the FAA’s belief that a
0.10 inch tolerance would create an
undue hardship on sponsors because it
would require constant adjustment of
the controls to maintain the close
tolerance. The change from 0.10 inches
to 0.15 inches is large enough to
minimize the hardship on sponsors, and
small enough to continue providing
pilots with an accurate controller feel.
Other than this change to the visual
scene requirement, the requirements of
this proposal would not apply to current
simulators. In all instances the overall
costs applicable to new simulators are
minimal to none. The most expensive
change being proposed is the increase in
horizontal field of view for some visual
system applications.
C. Compliance
With the exception of QMS
requirements and any FSTD Directives,
simulators qualified prior to May 30,
2008, are not required to meet QPS
requirements as long as the simulator
continues to meet the requirements
contained in the Master Qualification
Test Guide that was developed when
the simulator was originally qualified.
IV. The Proposal
A. Visual Scenes and Airport Models;
Class I, Class II, and Class III Airports;
and the FSTD Directive for Class II
Visual Scenes and Airport Models
Current part 60 contains requirements
for the number of visual scenes or
airport models that must be included for
full flight simulator (FFS) qualification
and a description of what the visual
scenes or airport models must contain.
Included in this proposal is a
codification of existing practice for
2 See Appendix C of this part, Table C2A, item
2.a.6.
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visual scene quality, environmental
effects, visual feature recognition, and
scene control and management
capability. Also included is the
codification of existing practice for
updating visual scenes and airport
visual models, including the
identification of other aspects of the
airport environment that would have to
correspond with the visual scene or
model.
The proposal establishes the
requirements for Class I, Class II, and
Class III visual scenes and airport
models already covered by ACs issued
by the FAA. For circling approaches, all
of the proposed requirements would
apply to the runway used for the initial
approach and to the runway of intended
landing. Additional proposed
requirements include an accurate visual
relationship between the scenes or
airport models and other aspects of the
airport environment, an accurate visual
relationship of the aircraft and
associated equipment, scene quality
assessment features, and control of these
scenes or models that the instructor is
able to exercise. The FAA believes these
requirements are necessary to ensure
realistic and accurate depiction of
airports and visual scenes incorporated
in simulators for FAA-approved training
programs.
Additional visual scenes or airport
models beyond those necessary for
simulator qualification may be used for
various training program applications,
including Line Oriented Flight Training,
and are important for flight training and
testing. Historically, these additional
visual scenes or airport models were not
routinely evaluated or required to meet
any standardized criteria. This led to
qualified simulators containing visual
scenes or airport models that may have
been incorrect or may have contained
inappropriate visual references. To
prevent this from occurring in the
future, the FAA proposes to issue FSTD
Directive (FD) Number 1. All FDs issued
would be found in the FSTD Directive
Attachments: Appendix A, Attachment
6; Appendix B, Attachment 5, Appendix
C, Attachment 5, and Appendix D,
Attachment 5. FD Number 1 is not
contained in Appendix B or in
Appendix D because no existing level of
FSTD in Appendix B or Appendix D
requires a visual system. Proposed FD
Number 1 would require each simulator
sponsor to verify that each Class II
visual scene or airport model available
in the FFS, regardless of the original
qualification basis and regardless of the
initial qualification date, meets the
requirements in 14 CFR part 60,
Appendix A, Attachment 3, Table A3C
or Appendix C, Attachment 3, Table
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C3C, as applicable. FD Number 1 would
apply to all FSTDs with visual systems
containing visual scenes or airport
models used as part of an FAAapproved curriculum that are available
for use and are beyond the minimum
number of required visual scenes or
airport models required for qualification
at the stated level. This FSTD Directive
would not require visual scenes or
airport models to contain details beyond
the design capability of the existing
qualified visual system. The availability
of the scene or model in the FFS would
serve as the sponsor’s verification that
the requirements were met. Therefore, a
reporting requirement for these scenes
or models would not be necessary.
Currently, visual scenes and airport
models available in any FFS that would
be classified as Class II are likely to
already meet the requirements being
proposed. Additionally, each visual
scene or airport model classified as
Class II would be beyond the number of
visual scenes or airport models required
for qualification. In the event any Class
II visual scene or airport model is found
by the sponsor to be deficient in some
way, the sponsor could remove that
scene or model from the FFS library
without jeopardizing the qualification
status of the FFS. Alternately, the
sponsor, at his or her option, may elect
to bring the deficient aspect into
compliance and retain the availability of
that scene or model. Each sponsor has
a full year to review each FFS during
normal training, checking, or testing
activities and determine the preferred
course of action. For these reasons, the
FAA has determined that in a few cases
the cost for complying with this
proposal would be minimal and in
many cases there would be no cost to
the sponsor.
In addition to the proposed
requirements for Class II visual scenes
and models, the FAA also proposes to
allow the continuation of the use of
visual scenes or airport models that
have been approved by the Training
Program Approval Authority (TPAA) for
specific purposes. Examples of
approved activities include specific
airport or runway qualification, very
low visibility operations training,
including Surface Movement Guidance
System (SMGS) operations, or use of a
specific airport visual model aligned
with an instrument procedure for
another airport for instrument training.
At the end of the interim period, all
Class III visual scenes and airport
models must be classified as either a
Class I or a Class II visual scene or
airport model or be removed from
availability at the simulator Instructor
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Operating Stations (IOS). Class III visual
scenes and airport models may continue
to be used after the end of the interim
period if they are part of a training
program specifically approved by the
TPAA or other regulatory authority that
uses a task and capability analysis as the
basis for approval of this specific media
element, (i.e., the specific scene or
model selected for use in that program).
Because any visual scene or airport
model that may be classified as Class III
is likely to already have some form of
a task and capability analysis completed
and is already specifically approved by
the TPAA, the FAA has determined that
in many cases there would be no cost
for complying with this proposal.
However, if a task and capability
analysis is required or if modification to
the visual scene is necessary, then the
cost would be minimal.
B. New Requirements for Objective
Testing Standards
The FAA proposes to revise the
objective testing requirements for
certain simulation performance areas.
These revisions are necessary to clarify
the instructions and requirements for
certain tests contained in the final rule.
In addition to changing the
requirements for certain tests, the FAA
also proposes several new tests that
were not included in the final rule. The
revised tests impact the following
simulation performance areas:
1. Idle and emergency descents for
airplane simulators.
2. Pitch trim rates for airplane
simulators.
3. Landing test requirements:
autopilot landings and ground effect
demonstration for airplane simulators.
4. Takeoffs, hover, vertical climbs,
and normal landings in helicopter flight
training devices.
5. Spiral stability tests for both
airplane and helicopter simulators.
6. Engine inoperative rejected takeoffs
for helicopter simulators.
7. Motion System tests for airplane
and helicopter simulators and for
helicopter flight training devices.
8. Visual System tests for airplane and
helicopter simulators and for helicopter
flight training devices.
9. Sound System tests for airplane and
helicopter simulators.
An example of a revised requirement
is the spiral stability test for airplane
and helicopter simulators. Under the
proposal, an additional parameter must
be measured to achieve the required
results. For airplanes, the spiral stability
test must be conducted in an additional
flight configuration (approach or
landing) instead of being conducted in
cruise configuration only. For
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helicopters, the final rule required the
helicopter to maintain the correct trend
during the spiral stability test, whereas
this proposal would require the
helicopter to meet a specific roll or bank
angle during the test. These additional
parameters provide a more complete
and accurate evaluation of the
simulator, and ensure better replication
of aircraft performance. The data that
would be used to validate simulator
performance and handling in these areas
is obtained from lateral-directional
stability tests conducted during normal
aircraft certification flight testing. The
data for these additional parameters are
either regularly available or can be made
available simply by activating the
recording equipment when the test is
begun.
Another example of the revised
requirements is the inclusion of an
alternative method for validating control
dynamics for the pitch, roll, and yaw
control tests for airplane simulators.3
The alternative method would not
change the requirements that the
simulator must meet for qualification,
but would allow the validation tests for
control dynamics to be conducted on
the ground rather than in-flight. The
FAA believes this change would
provide an equivalent level of safety,
while conserving resources and
providing greater flexibility for
manufacturers and sponsors.
These proposed requirements affect
only those FSTDs that will be coming
into service after May 30, 2008, and
some proposed changes may be
marginally more stringent than the
requirements in the October 30, 2006,
Final Rule, while some are less
stringent. Where the proposed
requirements are marginally more
stringent than the current requirements
the cost would be minimal.
C. New Requirements for Motion
Systems for Full Flight Simulators and
Level 7 Helicopter Flight Training
Devices
This proposal adds tables describing
the motion vibration that must be
displayed by the FSTD. The FAA
proposes on-set motion cueing
capability for airplane and helicopter
FFSs and Level 7 helicopter FTDs. For
the FFSs, the proposal includes a
requirement that the motion cueing
must be provided by a platform motion
system. For the Level 7 helicopter FTDs,
the proposal would allow a method
other than a platform motion system to
be used, such as the use of a large, bass
speaker located beneath the pilot’s seat
3 See
Appendix A of this part, Attachment 2, para.
4.
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with sufficient response to provide
vibration cues to the pilot. The proposal
also eliminates certain requirements for
ranges and rates of motion system
response for helicopter simulators.
However, the proposal would require
additional tests that capture the motion
system ‘‘signature.’’ The signature is a
simultaneous recording of motion
system responses captured while
conducting required objective tests. The
signature is recorded and may be
compared to signatures captured in
subsequent evaluations to determine if
any differences exist. Any differences
would be corrected to return the motion
system back to its original system
operation. Signature testing would
apply to airplane and helicopter
simulators.
The October 30, 2006, Final Rule does
not contain motion system testing
requirements for airplane flight
simulators. However, current practice
(under the Advisory Circular) includes
motion system testing that consists of
‘‘frequency response,’’ ‘‘leg balance,’’
and ‘‘turn around check.’’ This proposal
codifies that current practice and adds
the motion system benchmarking of a
‘‘motion cueing performance signature’’
and ‘‘characteristic motion vibrations,’’
both of which are also proposed for
helicopter simulators. Motion cueing
performance signature and
characteristic motion vibrations for
airplane flight simulators and helicopter
simulators are already recorded during
the conduct of other required objective
and subjective testing for these
simulators, thereby eliminating any
cost.
The proposal also requires the
recording of motion cueing performance
signature and characteristic motion
vibrations for simulators and Level 7
helicopter FTDs. The proposal only
requires that the motion cueing
performance signature and the
characteristic motion vibrations be
recorded while currently required tests
are being conducted. The motion cueing
performance signature is the motion
system response recorded during certain
objective tests. The characteristic
motion vibrations are the motion system
response recorded during certain
subjective tests.
These proposed requirements would
provide for more comprehensive
simulator assessments. The additional
cost for implementation would be either
negligible or no cost. These
requirements would also harmonize
with the international standards
document.
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D. New Requirements for Visual
Systems for Level C and D Full Flight
Simulators
F. New Requirements for Subjective
Testing Standards for Visual Scenes and
Airport Models
The FAA proposes technical changes
for visual systems on Level C and Level
D simulators. For example, the FAA
proposes that the surface resolution of
objects in the visual scene must be able
to be visually ‘‘resolved’’ at 2 arc
minutes rather than 3 arc minutes. Also,
the horizontal field of view
requirements would be increased from
150° to 180°. The FAA believes these
requirements would provide better
training to pilots by improving visual
cues and better replicating the outside
views. These changes would also be
consistent with the current international
standards. The requirements of this
proposal would not apply to current
simulators and the overall costs
applicable to new simulators are
minimal to none.
The proposed requirements for visual
scene and airport models for FFSs
would codify existing advisory material,
and include the following:
1. Scene content—1 airport scene
required for Level A and B; 3 airport
scenes required for Level C and D. The
scenes must contain specific details,
both on-airport and off-airport.
2. Visual scene management.
3. Visual scene recognition.
4. Airport model content.
5. Surrounding visual features
consistent with the airport environment.
6. The quality of visual scene,
including correct color and realistic
textural cues.
7. Instructor control of environment,
airport selection, and lighting.
These requirements would be
necessary to ensure a training
environment that provides accurate
simulation and allows pilots to practice
skills using visual scenes and models
encountered in actual operations. These
requirements would be particularly
helpful for pilots with lower flight
experience levels.
In addition to codifying standards for
the required visual scenes and airport
models, the FAA also proposes
requirements for visual scenes and
airport models that are included in the
device by the sponsor, but are not
required for the qualification level. In
the past, there were no established
standards for optional scenes or airport
models that a sponsor may have
incorporated in an FSTD. This created
inconsistencies in approval methods
and in the training credits issued for
tasks completed in a device that had
capability beyond what was required for
the stated qualification level. By
establishing minimum requirements for
these optional scenes and models, the
FAA would be requiring the sponsor of
each FSTD to meet at least the
minimum content, and the device may
be eligible for additional training credits
for pilots.
The visual scenes and airport models
currently available in any FFS that
would be classified as Class II are
beyond the number of visual scenes or
airport models required for qualification
and are likely to already meet the
requirements being proposed. As
previously described, in the event any
Class II visual scene or airport model is
found by the sponsor to be deficient in
some way, the sponsor could remove
that scene or model from the FFS library
without jeopardizing the qualification
status of the FFS. However, the sponsor,
E. New Requirements for Sound Systems
for Level D Simulators
The FAA proposes new sound testing
requirements for new Level D
simulators. These requirements would
specify basic and special case sound
tests, and would be consistent with
existing FAA advisory material, FAA
regulations, and the standards
developed by the international
simulation working group. The proposal
contains a standardized list of sounds
that would be recorded and compared
during initial and subsequent
qualification evaluations. All new level
D simulators would be tested for
frequency response and background
noise. There would also be specific tests
based on whether the simulator is
replicating a jet powered aircraft or a
propeller powered aircraft. These tests
would ensure accuracy in the overall
sound quality of the device. This
proposal codifies existing practice of
measuring sounds and will result in no
additional cost to the sponsor. These
changes would also be consistent with
the current international standards. The
FAA has always required Level D
simulators to have sounds recorded.
These sounds are then measured and
compared between the aircraft and the
simulator and adjusted until they match
to within stated tolerances. However,
under current requirements there are
inconsistencies with what sounds are to
be recorded and what tolerances should
be applied. The proposal specifies the
portions of the flight envelope that must
be recorded, therefore eliminating the
previous inconsistencies.
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at his option, may elect to bring the
deficient aspect into compliance and
retain the availability of that scene or
model. Each sponsor has a full year to
review each FFS during normal training,
checking, or testing activities and
determine the preferred course of
action. For these reasons, the FAA has
determined that in a few cases the cost
for complying with this proposal would
be minimal and in many cases there
would be no cost to the sponsor.
G. New Level 7 Helicopter FSTD
Requirements
The FAA is proposing a Level 7
Helicopter FTD QPS. There are
currently no Level 7 helicopter FTDs.
The standards proposed for this device
would insure the quality of simulation
necessary for the training and
evaluation of flight crewmembers. The
Level 7 FTD QPS would contain specific
requirements for visual and motion
systems. For example, the device would
have to provide a visual system with a
field of view of 150° x 40° for both pilots
simultaneously and a motion cueing
system that may consist of a platform
motion system, a seat shaker system, or
a strategically located bass speaker of
sufficient response to provide an
indication of rotor vibration and
vibration changes with changes in RPM
or collective input. The Level 7 device
would expand the training capability for
helicopter students. Because the Level 7
FTD is a new voluntary training option
and would not be required for
compliance with any training, testing or
checking requirements, the proposal
would not impose any additional cost
on sponsors or manufacturers.
H. Quality Management Systems
The October 30, 2006, Final Rule
established a Quality Management
System (QMS) for FSTDs. The QMS is
divided into two separate categories—a
mandatory program and a voluntary
program. This proposal would remove
the details regarding the voluntary
program from Appendix E. The proposal
also clarifies the obligation of sponsors
to be consistent in their conduct of
internal assessments and clarifies the
potential for increase in internal audit
intervals.
Under the proposal, the National
Simulator Program Manager (NSPM)
would conduct continuing qualification
evaluations of each FSTD every 12
months unless the NSPM becomes
aware of discrepancies or performance
problems with the device that warrants
more frequent evaluations. The
continuing qualification evaluations
frequency could be extended beyond the
12-month interval if: (1) The sponsor
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implements a voluntary QMS program;
and (2) the NSPM determines that the
administration of the QMS program and
the FSTD performance justifies less
frequent evaluations. However, in no
case would the frequency of continuing
qualification evaluations exceed 36
months.
I. New Information on Operation and
Testing Requirements for FSTDs
The QPS material attached to this
proposed rule adds 11 paragraphs of
information to better explain the
operation and testing requirements for
FSTDs. The paragraphs provide
information on the use of alternative
data sources, alternative engines data,
alternative avionics data, and
engineering simulators to provide
validation data. There are also
information paragraphs on motion
systems, sound systems, simulator
qualifications for new or derivative
airplanes, validation test tolerances,
validation data roadmap, transport
delay testing, and validation test data
presentation.
V. Regulatory Notices and Analyses
Privacy Impact Statement for Proposed
14 CFR Part 60, Appendices A Through
F
Legal Requirements
Section 522 of the Consolidated
Appropriations Act of 2005 instructs
DOT to conduct a privacy impact
assessment (PIA) of proposed rules that
will affect the privacy of individuals.
The PIA should identify potential
threats relating to the collection,
handling, use, sharing and security of
the data, the measures identified to
mitigate these threats, and the rationale
for the final decisions made for the
rulemaking as a result of conducting the
PIA.
Definitions
Sponsor means a certificate holder
who seeks or maintains FSTD
qualification and is responsible for the
prescribed actions as prescribed in this
part and the QPS for the appropriate
FSTD and qualification level.
Certificate holder means 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.
Individual means a living human
being, specifically including a citizen of
the United States or an alien lawfully
admitted for permanent residence.
Personally Identifiable Information
(PII) is any information that permits the
identity of an individual to whom the
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information applies to be reasonably
inferred by either direct or indirect
means, singly or in combination with
other data. Examples of PII include but
are not limited to physical and online
contact information, Social Security
number or driver’s license number.
Privacy Impact Assessment is an
analysis of how a rulemaking would
impact the way information is handled
in order to ensure data handling
conforms to applicable legal, regulatory,
and policy requirements regarding
privacy, determine the risks and effects
the rulemaking will have on collecting,
maintaining and sharing PII, and
examine and evaluate protections and
alternative processes for handling
information to mitigate potential
privacy risks.
Requirements for the Submission and
Retention of PII as Part of Compliance
With Proposed 14 CFR part 60, Flight
Simulation Training Device Initial and
Continuing Qualification and Use
The FAA proposes to amend the QPS
requirements for FSTDs. Compliance
with the QPS requirements is the
responsibility of the FSTD sponsor.
There are approximately 60 FSTD
sponsors.
The proposed rule does not require
sponsors to submit PII to the FAA or to
maintain PII in their own records.
However, the FAA recognizes that
certain PII may be contained in a
sponsor’s records, including
information about individuals who have
used a particular FSTD. This
information may include the person’s
name, employer, duty position, and type
ratings. The FAA may request a sponsor
to disclose this PII for investigation,
compliance, or enforcement purposes.
For example, the FAA may request the
sponsor to provide the names of all
individuals trained on a specific device
if the FAA discovered that the device
was not adequately simulating the
aircraft and determined that those
individuals needed to be retrained or
reevaluated.
The FAA protects PII in accordance
with ‘‘Privacy Act Notice DOT/FAA
847—Aviation Records on Individuals
(formerly General Air Transportation
Records on Individuals).’’ The Privacy
Act Notice is available at https://
cio.ost.dot.gov/DOT/OST/Documents/
files/records.html.
The FAA did not conduct a PIA for
this rulemaking because there are no
new requirements for PII as part of these
QPS amendments. In August 2004, the
FAA released a PIA for airmen
certification records. The PIA addresses
the methodology the agency uses to
collect, store, distribute, and protect PII
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59605
for certificated airmen, including pilots.
The PIA is available at https://
www.dot.gov/pia/faa_rms.htm. This PIA
would apply to any PII the FAA may
receive from a sponsor in the course of
exercising its oversight authority.
For more information or for comments
and concerns on our privacy practices,
please contact our Privacy Officer, Carla
Mauney at carla.mauney@faa.gov, or by
phone at (202) 267–9895.
Paperwork Reduction Act
Information collection requirements
associated with this NPRM 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.
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 identified no differences with
these proposed regulations.
Economic Assessment, Initial
Regulatory Flexibility Determination,
Trade Impact Assessment, and
Unfunded Mandates Assessment
Changes to Federal regulations must
undergo several economic analyses.
First, Executive Order 12866 directs that
each Federal agency shall propose or
adopt a regulation only upon a reasoned
determination that the benefits of the
intended regulation justify its costs.
Second, the Regulatory Flexibility Act
of 1980 (Pub. L. 96–354) requires
agencies to analyze the economic
impact of regulatory changes on small
entities. Third, the Trade Agreements
Act (Pub. L. 96–39) prohibits agencies
from setting standards that create
unnecessary obstacles to the foreign
commerce of the United States. In
developing U.S. standards, the Trade
Act requires agencies to consider
international standards and, where
appropriate, that they be the basis of
U.S. standards. Fourth, the Unfunded
Mandates Reform Act of 1995 (Pub. L.
104–4) requires agencies to prepare a
written assessment of the costs, benefits,
and other effects of proposed or final
rules that include a Federal mandate
likely to result in the expenditure by
State, local, or tribal governments, in the
aggregate, or by the private sector, of
$100 million or more annually (adjusted
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for inflation with base year of 1995).
This portion of the preamble
summarizes the FAA’s analysis of the
economic impacts of this proposed rule.
Department of Transportation Order
DOT 2100.5 prescribes policies and
procedures for simplification, analysis,
and review of regulations. If the
expected cost impact is so minimal that
a proposed or final rule does not
warrant a full evaluation, this order
permits that a statement to that effect
and the basis for it to be included in the
preamble if a full regulatory evaluation
of the cost and benefits is not prepared.
Such a determination has been made for
this proposed rule. The reasoning for
this determination follows:
The FAA proposes to codify existing
practice by requiring all existing FSTD
visual scenes beyond the number
required for qualification to meet
specified requirements. The proposal
also reorganizes certain sections of the
QPS appendices and provides
additional information on validation
tests, established parameters for
tolerances, acceptable data formats, and
the use of alternative data sources. The
proposed changes would ensure that the
training and testing environment is
accurate and realistic, would codify
existing practice, and would provide
greater harmonization with the
international standards document for
simulation. None of these proposed
technical requirements would apply to
simulators qualified before May 30,
2008, except for the proposal to codify
existing practice regarding certain visual
scene requirements. The overall impact
of this proposal would result in minimal
to no cost increases for manufacturers
and sponsors.
The FAA has, therefore, determined
that this proposed rule is not a
‘‘significant regulatory action’’ as
defined in section 3(f) of Executive
Order 12866, and is not ‘‘significant’’ as
defined in DOT’s Regulatory Policies
and Procedures.
Regulatory Flexibility Determination
The Regulatory Flexibility Act of 1980
(Pub. L. 96–354) (RFA) establishes ‘‘as a
principle of regulatory issuance that
agencies shall endeavor, consistent with
the objectives of the rule and of
applicable statutes, to fit regulatory and
informational requirements to the scale
of the businesses, organizations, and
governmental jurisdictions subject to
regulation. To achieve this principle,
agencies are required to solicit and
consider flexible regulatory proposals
and to explain the rationale for their
actions to assure that such proposals are
given serious consideration.’’ The RFA
covers a wide-range of small entities,
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including small businesses, not-forprofit organizations, and small
governmental jurisdictions.
Agencies must perform a review to
determine whether a rule will have a
significant economic impact on a
substantial number of small entities. If
the agency determines that it will, the
agency must prepare a regulatory
flexibility analysis as described in the
RFA.
However, if an agency determines that
a rule is not expected to have a
significant economic impact on a
substantial number of small entities,
section 605(b) of the RFA 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 FAA proposes to codify existing
practice by requiring all existing FSTD
visual scenes beyond the number
required for qualification to meet
specified requirements. The proposal
also reorganizes certain sections of the
QPS appendices and provides
additional information on validation
tests, established parameters for
tolerances, acceptable data formats, and
the use of alternative data sources. The
proposed changes would ensure that the
training and testing environment is
accurate and more realistic, would
codify existing practice, and would
provide greater harmonization with the
international standards document for
simulation. None of these proposed
technical requirements would apply to
simulators qualified before May 30,
2008, except for the proposal to codify
existing practice regarding certain visual
scene requirements. The overall impact
of this proposal would result in minimal
to no cost increases for manufacturers
and sponsors. Therefore the FAA
certifies that this proposed rule would
not have a significant economic impact
on a substantial number of small
entities. The FAA solicits comments
regarding this determination.
and has determined that it would
impose the same costs on domestic and
international entities and thus has a
neutral trade impact.
International Trade Impact Assessment
The Trade Agreements Act of 1979
(Pub. L. 96–39) prohibits Federal
agencies from establishing any
standards or engaging in 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. The FAA has assessed
the potential effect of this proposed rule
Regulations That Significantly Affect
Energy Supply, Distribution, or Use
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Unfunded Mandates Assessment
Title II of the Unfunded Mandates
Reform Act of 1995 (Pub. L. 104–4)
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 with the
base year 1995) 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-adjusted value of
$128.1 million in lieu of $100 million.
This proposed rule does not contain
such a mandate.
Executive Order 13132, Federalism
The FAA has analyzed this notice of
proposed rulemaking under the
principles and criteria of Executive
Order 13132, Federalism. We
determined that this proposal 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 proposed 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 proposed
rule action qualifies for the categorical
exclusion identified in paragraph 312f
and involves no extraordinary
circumstances.
The FAA has analyzed this proposed
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.
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Additional Information
Availability of Rulemaking Documents
Comments Invited
You can get an electronic copy of
rulemaking documents using the
Internet by—
1. Searching the Federal eRulemaking
Portal (https://www.regulations.gov);
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 docket number, notice
number, or amendment number of this
rulemaking.
The FAA invites interested persons to
participate in this rulemaking by
submitting written comments, data, or
views. We also invite comments relating
to the economic, environmental, energy,
or federalism impacts that might result
from adopting the proposals in this
document. The most helpful comments
reference a specific portion of the
proposal, explain the reason for any
recommended change, and include
supporting data. To ensure the docket
does not contain duplicate comments,
please send only one copy of written
comments, or if you are filing comments
electronically, please submit your
comments only one time.
We will file in the docket all
comments we receive, as well as a
report summarizing each substantive
public contact with FAA personnel
concerning this proposed rulemaking.
Before acting on this proposal, we will
consider all comments we receive on or
before the closing date for comments.
We will consider comments filed after
the comment period has closed if it is
possible to do so without incurring
expense or delay. We may change this
proposal in light of the comments we
receive.
Proprietary or Confidential Business
Information
Do not file in the docket information
that you consider to be proprietary or
confidential business information. Send
or deliver this information directly to
the person identified in the FOR FURTHER
INFORMATION CONTACT section of this
document. You must mark the
information that you consider
proprietary or confidential. If you send
the information on a disk or CD–ROM,
mark the outside of the disk or CD–ROM
and also identify electronically within
the disk or CD–ROM the specific
information that is proprietary or
confidential.
Under 14 CFR 11.35(b), when we are
aware of proprietary information filed
with a comment, we do not place it in
the docket. We hold it in a separate file
to which the public does not have
access, and we place a note in the
docket that we have received it. If we
receive a request to examine or copy
this information, we treat it as any other
request under the Freedom of
Information Act (5 U.S.C. 552). We
process such a request under the DOT
procedures found in 49 CFR part 7.
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List of Subjects in 14 CFR Part 60
Airmen, Aviation safety, Reporting
and recordkeeping requirements.
The Proposed Amendment
In consideration of the foregoing, the
Federal Aviation Administration
proposes to further amend the final rule
amending part 60 of Title 14 of the Code
of Federal Regulations, as published at
71 FR 63392 on October 30, 2006, as
follows:
PART 60—FLIGHT SIMULATION
TRAINING DEVICE INITIAL AND
CONTINUING QUALIFICATION AND
USE
1. The authority citation for part 60
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, and
44701.
2. Part 60, published at 71 FR 63392
on October 30, 2006 is amended by
revising appendices A–F to read as
follows:
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
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59607
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. FSTD Objective Data Requirements
(§ 60.13)
10. Special Equipment and Personnel
Requirements for Qualification of the
FSTD (§ 60.14)
11. Initial (and Upgrade) Qualification
Requirements (§ 60.15)
12. Additional Qualifications for a Currently
Qualified FSTD (§ 60.16)
13. Previously Qualified FSTDs (§ 60.17)
14. Inspection, Continuing Qualification
Evaluation, and Maintenance
Requirements (§ 60.19)
15. Logging FSTD Discrepancies (§ 60.20)
16. Interim Qualification of FSTDs for New
Airplane Types or Models (§ 60.21)
17. Modifications to FSTDs (§ 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. Recordkeeping 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 Objective Tests
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
Attachment 6 to Appendix A to Part 60—
FSTD Directives Applicable to Airplane
Flight Simulators
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
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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. Questions regarding the contents of this
publication should be sent to the U.S.
Department of Transportation, Federal
Aviation Administration, Flight Standards
Service, National Simulator Program Staff,
AFS–205, 100 Hartsfield Centre Parkway,
Suite 400, Atlanta, Georgia, 30354.
Telephone contact numbers for the NSP are:
phone, 404–832–4700; fax, 404–761–8906.
The general email address for the NSP office
is: 9-aso-avr-sim-team@faa.gov. The NSP
Internet Web Site address is: https://
www.faa.gov/safety/programs_initiatives/
aircraft_aviation/nsp/. On this Web Site you
will find an NSP personnel list with
telephone and email contact information for
each NSP staff member, a list of qualified
flight simulation devices, advisory circulars,
a description of the qualification process,
NSP policy, and an NSP ‘‘In-Works’’ section.
Also linked from this site are additional
information sources, handbook bulletins,
frequently asked questions, a listing and text
of the Federal Aviation Regulations, Flight
Standards Inspector’s handbooks, and other
FAA links.
c. The NSPM encourages the use of
electronic media for all communication,
including any record, report, request, test, or
statement required by this appendix. The
electronic media used must have adequate
security provisions and be acceptable to the
NSPM. The NSPM recommends inquiries on
system compatibility, and minimum system
requirements are also included on the NSP
Web site.
d. 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.
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(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 and 60.2)
lllllllllllllllllllll
Begin Information
No additional regulatory or informational
material 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 of this part 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
No additional regulatory or informational
material applies to § 60.4, Qualification
Performance Standards.
End Information
lllllllllllllllllllll
5. Quality Management System (§ 60.5)
lllllllllllllllllllll
Begin Information
See Appendix E of this part for additional
regulatory and informational material
regarding Quality Management Systems.
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 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 the sponsor sponsors and uses at least one
FFS at least once during the prescribed
period. No minimum number of hours or
minimum FFS periods are 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 the 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 May 30,
2008, the 12-month period begins on the date
of the first continuing qualification
evaluation conducted in accordance with
§ 60.19 after May 30, 2008, and continues for
each subsequent 12-month period;
(ii) A device qualified on or after May 30,
2008, 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 the 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 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 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.
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(b) No minimum number of hours of FFS
use is 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.
End Information
lllllllllllllllllllll
8. FSTD Use (§ 60.11)
lllllllllllllllllllll
Begin Information
No additional regulatory or informational
material applies to § 60.11, Simulator Use.
End Information
lllllllllllllllllllll
9. FSTD Objective Data Requirements
(§ 60.13)
lllllllllllllllllllll
Begin QPS Requirements
lllllllllllllllllllll
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.
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(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 A2E.
(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. The sponsor must—
(1) Within 10 calendar days, notify the
NSPM of the existence of this data; and
(2) Within 45 calendar days, notify the
NSPM of—
(a) The schedule to incorporate this data
into the FFS; or
(b) The reason for not incorporating this
data into the FFS.
e. 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, the sponsor or other data
provider must ensure that a steady state
condition exists at the instant of time
captured by the ‘‘snapshot.’’ The steady state
condition must exist from 4 seconds prior to,
through 1 second following, the instant of
time captured by the snapshot.
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59609
End QPS Requirements
lllllllllllllllllllll
Begin Information
f. 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).
g. 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.
h. 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.
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 FSTDs
(§ 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
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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 users of the
FFS that raise questions about 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:
(a) Objective data obtained from aircraft
testing or another approved source.
(bi) Correlating objective test results
obtained from the performance of the FFS as
prescribed in the appropriate QPS.
(c) The result of FFS subjective tests
prescribed in the appropriate 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 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;
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(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) An 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 source of the basic aerodynamic
model and the aerodynamic coefficient data
used to modify the basic model.
(e) The engine model(s) and its data
revision number or reference.
(f) The flight control data revision number
or reference.
(g) The flight management system
identification and revision level.
(h) The FFS model and manufacturer.
(i) The date of FFS manufacture.
(j) The FFS computer identification.
(k) The visual system model and
manufacturer, including display type.
(l) 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) A 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 requirement, a
rationale explaining how the referenced
material is used, mathematical equations and
parameter values used, and the conclusions
reached; i.e., that the FFS complies with the
requirement.
(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.
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(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 QTG for
the first airplane model and a supplement to
that QTG for each additional 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
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.
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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 May 30,
2014, 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 May 30, 2014. 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.
l. During the initial (or upgrade)
qualification evaluation conducted by the
NSPM, the sponsor must also provide a
person who is a user of the device (e.g., a
qualified pilot or instructor pilot with flight
time experience in that aircraft) and
knowledgeable about the operation of the
aircraft and the operation of the FFS.
End QPS Requirements
lllllllllllllllllllll
Begin Information
m. 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.
n. 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:
(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);
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(3) Control checks (see Attachment 1 and
Attachment 2 of this appendix);
(4) Flight deck 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.
o. 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.
p. 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.
q. 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
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59611
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.
r. 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.
s. 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 evaluation and will
list the tasks for which the FSTD is qualified,
referencing the tasks described in Table A1B
in attachment 1. However, it is the sponsor’s
responsibility to obtain TPAA approval prior
to using the FSTD in an FAA-approved flight
training program.
t. 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.
u. 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.
v. 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).
w. 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 FSTD (§ 60.16)
lllllllllllllllllllll
Begin Information
No additional regulatory or informational
material applies to § 60.16, Additional
Qualifications for a Currently Qualified FFS.
End Information
lllllllllllllllllllll
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13. Previously Qualified FSTDs (§ 60.17)
lllllllllllllllllllll
Begin QPS Requirements
a. In instances where a sponsor plans to
remove an 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 May 30,
2008, are not required to meet the general
simulation requirements, the objective test
requirements or the subjective test
requirements of attachments 1, 2, and 3 of
this appendix as long as the simulator
continues to meet the test requirements
contained in the MQTG developed under the
original qualification basis.
c. After [date 1 year after effective date of
the final rule] each visual scene or airport
model beyond the minimum required for the
FSTD qualification level that is installed in
and available for use in a qualified FSTD
must meet the requirements described in
attachment 3 of this appendix.
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
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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
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.
d. During the continuing qualification
evaluation conducted by the NSPM, the
sponsor must also provide a person
knowledgeable about the operation of the
aircraft and the operation of the FFS.
e. The NSPM will conduct continuing
qualification evaluations every 12 months
unless:
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(1) The NSPM becomes aware of
discrepancies or performance problems with
the device that warrants more frequent
evaluations; or
(2) The sponsor implements a QMS that
justifies less frequent evaluations. However,
in no case shall the frequency of a continuing
qualification evaluation exceed 36 months.
End QPS Requirements
lllllllllllllllllllll
Begin Information
f. 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.
g. 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.
h. 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.
End Information
lllllllllllllllllllll
15. Logging FSTDs Discrepancies (§ 60.20)
lllllllllllllllllllll
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Begin Information
No additional regulatory or informational
material applies to § 60.20. Logging FFS
Discrepancies.
End Information
lllllllllllllllllllll
16. Interim Qualification of FSTDs for New
Airplane Types or Models (§ 60.21)
lllllllllllllllllllll
Begin Information
No additional regulatory or informational
material applies to § 60.21, Interim
Qualification of FFSs for New Airplane
Types or Models.
End Information
lllllllllllllllllllll
17. Modifications to FSTDs (§ 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. See Attachment 6 for a list of all
effective FSTD Directives applicable to
Airplane FFSs.
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
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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)
lllllllllllllllllllll
59613
Begin Information
No additional regulatory or informational
material applies to § 60.33, Applications,
Logbooks, Reports, and Records: Fraud,
Falsification, or Incorrect Statements.
lllllllllllllllllllll
23. Specific Full Flight Simulator
Compliance Requirements (§ 60.35)
lllllllllllllllllllll
No additional regulatory or informational
material applies to § 60.35, Specific FFS
Compliance Requirements.
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.
24. [Reserved]
lllllllllllllllllllll
End Information
lllllllllllllllllllll
End Information
lllllllllllllllllllll
20. Other Losses of Qualification and
Procedures for Restoration of Qualification
(§ 60.29)
lllllllllllllllllllll
Attachment 1 to Appendix A to Part 60—
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 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.
End QPS Requirements
lllllllllllllllllllll
22. Applications, Logbooks, Reports, and
Records: Fraud, Falsification, or Incorrect
Statements (§ 60.33)
lllllllllllllllllllll
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25. FSTD Qualification on the Basis of a
Bilateral Aviation Safety Agreement (BASA)
(§ 60.37)
lllllllllllllllllllll
No additional regulatory or informational
material applies to § 60.37, FSTD
Qualification on the Basis of a Bilateral
Aviation Safety Agreement (BASA).
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 flight deck configuration.
(2) Simulator programming.
(3) Equipment operation.
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(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.
d. Table A1B provides the tasks that the
sponsor will examine to determine whether
the FSTD satisfactorily meets the
requirements for flight crew training, testing,
and experience, and provides the tasks for
which the simulator may be qualified.
e. Table A1C provides the functions that an
instructor/check airman must be able to
control in the simulator.
f. It is not required that all of the tasks that
appear on the List of Qualified Tasks (part of
the SOQ) be accomplished during the initial
or continuing qualification evaluation.
End Information
lllllllllllllllllllll
TABLE A1A.—MINIMUM SIMULATOR REQUIREMENTS
<<>>
Simulator levels
General simulator
requirements
Number
Information
A
B
C
D
Notes
For simulator purposes, the flight deck 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 Flight Deck Configuration
1.a. ......
The simulator must have a flight deck that is a replica
of the airplane simulated with controls, equipment,
observable flight deck 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
flight deck 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 flight deck 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.
An SOC is required.
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.
A subjective test is required.
X
2.d. ......
Ground handling and aerodynamic programming must
include the following:
A subjective test is required for each.
2.d.1. ...
Ground effect ...................................................................
X
X
X
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Ground effect includes modeling that accounts for
roundout, flare, touchdown, lift, drag, pitching moment, trim, and power while in ground effect.
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59615
TABLE A1A.—MINIMUM SIMULATOR REQUIREMENTS—Continued
<<>>
Number
General simulator
requirements
2.d.2. ...
Simulator levels
B
C
D
Notes
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
2.e. ......
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
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.
A subjective test is required.
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 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.
X
X
Automatic ‘‘flagging’’ of out-of-tolerance situations is encouraged.
2.g. ......
Relative responses of the motion system, visual system, and flight deck 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. ...
A
Information
300 milliseconds of the airplane response.
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
X
Objective Tests are required.
2.g.2. ...
150 milliseconds of the airplane response.
Objective Tests are required.
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X
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TABLE A1A.—MINIMUM SIMULATOR REQUIREMENTS—Continued
<<>>
Simulator levels
Number
General simulator
requirements
2.h. ......
Information
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.
A
B
C
D
Subjective tests are required for patchy wet, patchy icy,
and wet on rubber residue in touchdown zone conditions; see Attachment 3.
X
X
2.i. ........
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 and
engine icing.
A Subjective Test is required.
X
X
2.k. .......
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.
Notes
An SOC is required.
Objective tests are required only for dry, wet, and icy
runway conditions; see Attachment 2.
2.l. ........
in-
X
Simulator pitch, side loading, and directional control
characteristics should be representative of the airplane.
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. .......
Simulated airplane 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
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See Attachment 3 for further information regarding longrange navigation equipment.
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59617
TABLE A1A.—MINIMUM SIMULATOR REQUIREMENTS—Continued
<<>>
Simulator levels
Number
General simulator
requirements
A
B
C
D
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
3.e. ......
Simulator control feel dynamics must replicate the airplane. This must be determined by comparing a recording of the control feel dynamics of the simulator
to airplane measurements. For initial and upgrade
qualification evaluations, the control dynamic characteristics must be measured and recorded directly
from the flight deck controls, and must be accomplished in takeoff, cruise, and landing flight conditions
and configurations.
Objective tests are required.
X
Information
X
Notes
4. Instructor or Evaluator Facilities
4.a. ......
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
The NSPM will consider alternatives to this standard for
additional seats based on unique flight deck configurations.
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 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
4.d. ......
The simulator must provide the instructor or evaluator
the ability to present ground and air hazards.
A subjective test is required.
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
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.
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TABLE A1A.—MINIMUM SIMULATOR REQUIREMENTS—Continued
<<>>
Simulator levels
Number
General simulator
requirements
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
B
C
D
X
X
Information
Notes
X
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 flight deck.
An objective test is required.
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
6.a. ......
The simulator must have a visual system providing an
out-of-the-flight deck view.
A subjective test is required.
X
X
6.b. ......
The simulator must provide a continuous collimated
field of view of at least 45° horizontally and 30°
vertically per pilot seat or the number of degrees necessary to meet the visual ground segment requirement, whichever is greater. Both pilot seat visual systems must be operable simultaneously. The minimum
horizontal field of view coverage must be plus and
minus one-half (1⁄2) of the minimum continuous field
of view requirement, centered on the zero degree azimuth line relative to the aircraft fuselage. Additional
field of view capability may be added at the sponsor’s
discretion provided the minimum fields of view are retained.
An SOC must explain the geometry of the installation.
An SOC is required.
X
X
6.c. .......
(Reserved)
6.d. ......
The simulator must provide a continuous collimated visual field of view of at least 176° horizontally and 36°
vertically or the number of degrees necessary to
meet the visual ground segment requirement, whichever is greater. The minimum horizontal field of view
coverage must be plus and minus one-half (1⁄2) of the
minimum continuous field of view requirement, centered on the zero degree azimuth line relative to the
aircraft fuselage. Additional field of view capability
may be added at the sponsor’s discretion provided
the minimum fields of view are retained.
An SOC must explain the geometry of the installation.
An SOC is required.
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The horizontal field of view is traditionally described as
a 180° field of view. However, the field of view is
technically no less than 176°.
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TABLE A1A.—MINIMUM SIMULATOR REQUIREMENTS—Continued
<<>>
Simulator levels
Information
Number
General simulator
requirements
A
B
C
D
Notes
6.e. ......
The visual system must be free from optical discontinuities and artifacts that create non-realistic cues.
A subjective test is required.
X
X
X
X
Non-realistic cues might include image ‘‘swimming’’ and
image ‘‘roll-off,’’ that may lead a pilot to make incorrect assessments of speed, acceleration, or situational awareness.
6.f. .......
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.g. ......
The simulator must have instructor controls for the following:
(1) Visibility in statute miles (km) and runway visual
range (RVR) in ft.(m).
(2) Airport selection.
(3) Airport lighting.
A subjective test is required.
X
X
X
X
6.h. ......
The simulator must provide visual system compatibility
with dynamic response programming.
A subjective test is required.
X
X
X
X
6.i. ........
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.j. ........
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.k. .......
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.l. ........
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.m. .....
The simulator must be capable of producing at least 10
levels of occulting.
A subjective test is required.
X
X
6.n. ......
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.
A subjective test is required.
X
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
<<>>
Simulator levels
Number
General simulator
requirements
6.o. ......
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. 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 airplane landing lights. If provided, directional horizon lighting must have correct
orientation and be consistent with surface shading effects. Total night or dusk (twilight) 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.
A subjective test is required.
6.p. ......
Daylight Visual Scenes. The simulator must provide
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 daylight 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.
A
B
C
D
X
Information
Notes
X
X
Brightness capability may be demonstrated with a test
pattern of white light using a spot photometer.
X
For example: short runways, landing approaches over
water, uphill or downhill runways, rising terrain on the
approach path, unique topographic features.
Note: These requirements are mandatory for level D,
and applicable to any level of simulator equipped with
a ‘‘daylight’’ visual system.
An SOC is required.
A subjective test is required.
6.q. ......
The simulator must provide operational visual scenes
that portray physical relationships known to cause
landing illusions to pilots.
A subjective test is required.
6.r. .......
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.
X
A subjective test is required.
6.s. .......
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.
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE A1A.—MINIMUM SIMULATOR REQUIREMENTS—Continued
<<>>
Simulator levels
General simulator
requirements
Number
A
B
C
Information
D
Notes
A subjective test is required.
6.t. .......
The simulator must present realistic
directionality of all airport lighting.
color
and
X
A subjective test is required.
7. Sound System
7.a. ......
The simulator must provide flight deck sounds that result from pilot actions that correspond to those that
occur in the airplane.
X
X
X
X
7.b. ......
Volume control, if installed, must have an indication of
the sound level setting.
X
X
X
X
7.c. .......
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.
X
X
An SOC is required.
A subjective test is required.
7.d. ......
The simulator must provide realistic amplitude and frequency of flight deck 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.
X
Objective tests are required.
TABLE A1B.—TABLE OF TASKS VS. SIMULATOR LEVEL
<<>>
Number
<>
Subjective requirements
In order to be qualified at the simulator qualification level indicated, the
simulator must be able to perform at least the tasks associated with that
level of qualification.
Simulator levels
Notes
A
B
C
D
1. Preflight Procedures
1.a. ......
Preflight Inspection (flight deck only) ............................................................
X
X
X
X
1.b. ......
Engine Start ...................................................................................................
X
X
X
X
1.c. .......
Taxiing ...........................................................................................................
X
X
1.d. ......
Pre-takeoff Checks ........................................................................................
X
X
X
X
X
X
2. Takeoff and Departure Phase
2.a. ......
Normal and Crosswind Takeoff .....................................................................
2.b. ......
Instrument Takeoff .........................................................................................
X
X
X
X
2.c. .......
Engine Failure During Takeoff .......................................................................
A
X
X
X
2.d. ......
Rejected Takeoff ............................................................................................
X
X
X
X
2.e. ......
Departure Procedure .....................................................................................
X
X
X
X
3. Inflight Maneuvers
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE A1B.—TABLE OF TASKS VS. SIMULATOR LEVEL—Continued
<<>>
<>
Subjective requirements
In order to be qualified at the simulator qualification level indicated, the
simulator must be able to perform at least the tasks associated with that
level of qualification.
A
B
C
D
3.a. ......
Steep Turns ...................................................................................................
X
X
X
X
3.b. ......
Approaches to Stalls ......................................................................................
X
X
X
X
3.c. .......
Engine Failure—Multiengine Airplane ...........................................................
X
X
X
X
3.d. ......
Engine Failure—Single-Engine Airplane .......................................................
X
X
X
X
3.e. ......
Specific Flight Characteristics incorporated into the user’s FAA approved
flight training program.
A
A
A
A
3.f. .......
Recovery From Unusual Attitudes .................................................................
X
X
X
X
Number
Simulator levels
Notes
Within the normal flight envelope
supported by applicable simulation
validation data.
4. Instrument Procedures
4.a. ......
Standard Terminal Arrival/Flight Management System Arrivals Procedures
X
X
X
X
4.b. ......
Holding ...........................................................................................................
X
X
X
X
4.c. .......
Precision Instrument.
4.c.1. ....
All engines operating .....................................................................................
X
X
X
X
e.g., Autopilot, Manual (Flt. Dir. Assisted), Manual (Raw Data).
4.c.2. ....
One engine inoperative .................................................................................
X
X
X
X
e.g., Manual (Flt. Dir. Assisted),
Manual (Raw Data).
4.d. ......
d. Non-precision Instrument Approach ..........................................................
X
X
X
X
e.g., NDB, VOR, VOR/DME, VOR/
TAC, RNAV, LOC, LOC/BC, ADF,
and SDF.
4.e. ......
e. Circling Approach ......................................................................................
X
X
X
X
Specific authorization required.
4.f. .......
Missed Approach.
4.f.1. ....
Normal ...........................................................................................................
X
X
X
X
4.f.2. ....
One engine Inoperative .................................................................................
X
X
X
X
5. Landings and Approaches to Landings
5.a. ......
Normal and Crosswind Approaches and Landings .......................................
R
X
X
5.b. ......
Landing From a Precision/Non-Precision Approach .....................................
R
X
X
5.c. .......
Approach and Landing with (Simulated) Engine Failure—Multiengine Airplane.
R
X
X
5.d. ......
Landing From Circling Approach ...................................................................
R
X
X
5.e. ......
Rejected Landing ...........................................................................................
X
X
X
5.f. .......
Landing From a No Flap or a Nonstandard Flap Configuration Approach ...
R
X
X
X
6. Normal and Abnormal Procedures
6.a. ......
Engine (including shutdown and restart) .......................................................
X
X
X
X
6.b. ......
Fuel System ...................................................................................................
X
X
X
X
6.c. .......
Electrical System ...........................................................................................
X
X
X
X
6.d. ......
Hydraulic System ...........................................................................................
X
X
X
X
6.e. ......
Environmental and Pressurization Systems ..................................................
X
X
X
X
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
59623
TABLE A1B.—TABLE OF TASKS VS. SIMULATOR LEVEL—Continued
<<>>
<>
Subjective requirements
In order to be qualified at the simulator qualification level indicated, the
simulator must be able to perform at least the tasks associated with that
level of qualification.
A
B
C
D
6.f. .......
Fire Detection and Extinguisher Systems .....................................................
X
X
X
X
6.g. ......
Navigation and Avionics Systems .................................................................
X
X
X
X
6.h. ......
Automatic Flight Control System, Electronic Flight Instrument System, and
Related Subsystems.
X
X
X
X
6.i. ........
Flight Control Systems ..................................................................................
X
X
X
X
6.j. ........
Anti-ice and Deice Systems ..........................................................................
X
X
X
X
6.k. .......
Aircraft and Personal Emergency Equipment ...............................................
X
X
X
X
Number
Simulator levels
Notes
7. Emergency Procedures
7.a. ......
Emergency Descent (Max. Rate) ..................................................................
X
X
X
X
7.b. ......
Inflight Fire and Smoke Removal ..................................................................
X
X
X
X
7.c. .......
Rapid Decompression ...................................................................................
X
X
X
X
7.d. ......
Emergency Evacuation ..................................................................................
X
X
X
X
8. Postflight Procedures
8.a. ......
After-Landing Procedures ..............................................................................
X
X
X
X
8.b. ......
Parking and Securing ....................................................................................
X
X
X
X
‘‘A’’—indicates that the system, task, or procedure may be examined if the appropriate aircraft system or control is simulated in the FSTD and
is working properly.
‘‘R’’—indicates that the simulator may be qualified for this task for recurrent training.
‘‘X’’—indicates that the simulator must be able to perform this task for this level of qualification.
TABLE A1C.—TABLE OF SIMULATOR SYSTEM TASKS
<<>>
<<>>
Subjective requirements
In order to be qualified at the simulator qualification
level indicated, the simulator must be able to perform at least the tasks associated with that level of
qualification.
Number
Simulator levels
Notes
A
B
C
D
1. Instructor Operating Station (IOS), as appropriate
1.a. ....................
Power switch(es) .......................................................
X
X
X
X
1.b. ....................
Airplane conditions ....................................................
X
X
X
X
e.g., GW, CG, Fuel loading and Systems.
1.c. ....................
Airports / Runways ....................................................
X
X
X
X
e.g., Selection, Surface, Presets, Lighting controls.
1.d. ....................
Environmental controls .............................................
X
X
X
X
e.g., Clouds, Visibility, RVR, Temp, Wind, Ice,
Snow, Rain, and Windshear.
1.e. ....................
Airplane system malfunctions (Insertion/deletion) ....
X
X
X
X
1.f. .....................
Locks, Freezes, and Repositioning ..........................
X
X
X
X
X
X
X
X
X
X
X
X
2. Sound Controls
2.a. ....................
On/off/adjustment ......................................................
3. Motion/Control Loading System
3.a. ....................
On /off/emergency stop ............................................
4. Observer Seats/Stations
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE A1C.—TABLE OF SIMULATOR SYSTEM TASKS—Continued
<<>>
<<>>
Subjective requirements
In order to be qualified at the simulator qualification
level indicated, the simulator must be able to perform at least the tasks associated with that level of
qualification.
Number
4.a. ....................
A
B
C
D
Position/Adjustment/Positive restraint system ..........
X
X
X
X
Attachment 2 to Appendix A to Part 60—
Full Flight Simulator Objective Tests
Simulator levels
Notes
3. ..............
General.
4. ..............
Control Dynamics.
5. ..............
Ground Effect.
6. ..............
Motion System.
7. ..............
Sound System.
8. ..............
Additional Information About
Flight Simulator Qualification
for New or Derivative Airplanes.
9. ..............
Engineering
tion Data.
10. ............
[Reserved].
11. ............
Validation Test Tolerances.
12. ............
Validation Data Roadmap.
13. ............
Acceptance Guidelines for Alternative Engines Data.
14. ............
Acceptance Guidelines for Alternative Avionics (Flight-Related
Computers and Controllers).
15. ............
Transport Delay Testing.
16. ............
Continuing Qualification Evaluations—Validation Test Data
Presentation.
17. ............
Alternative Data Sources, Procedures, and Instrumentation:
Level A and Level B Simulators Only.
Conditions Column of Table A2A, 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;
(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.
b. 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
objective test numbers for either FFSs or
FTDs.
c. 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.
d. 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.
lllllllllllllllllllll
End Information
lllllllllllllllllllll
Begin Information
Begin QPS Requirements
1. Introduction
2. Test Requirements
a. The ground and flight tests required for
qualification are listed in Table of A2A, FFS
TABLE OF CONTENTS
Paragraph
No.
Title
1. ..............
Introduction.
2. ..............
Test Requirements.
Table A2A, Objective Tests.
Simulator—Valida-
a. For the purposes of this attachment, the
flight conditions specified in the Flight
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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
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
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.
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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. 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. 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.
i. 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 manufacturers’ engines) additional tests
with the alternative engine models may be
required. This Attachment contains
guidelines for alternative engines.
j. 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.
k. 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
59625
sponsor and the NSPM on a case-by-case
basis.
l. Some tests will not be required for
airplanes using airplane hardware in the
simulator flight deck (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.
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 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 within 10 percent 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.’’)
n. 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, the sponsor or other data
provider must ensure that a steady state
condition exists at the instant of time
captured by the ‘‘snapshot.’’ The steady state
condition must exist from 4 seconds prior to,
through 1 second following, the instant of
time captured by the snapshot.
End QPS Requirements
lllllllllllllllllllll
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS
<<>>
Test
Tolerance
Number
Title
Simulator level
Flight
conditions
Test details
Ground ........................
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.
A
B
C
D
X
X
X
1. Performance
1.a. .....................
Taxi
1.a.1. ..................
Minimum Radius Turn
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59626
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Tolerance
Simulator level
Flight
conditions
Test details
Ground ........................
Record a minimum of
two speeds, greater
than minimum turning radius speed,
with a spread of at
least 5 knots groundspeed.
Number
Title
1.a.2. ..................
Rate of Turn vs.
Nosewheel Steering
Angle (NWA).
1.b. .....................
Takeoff
1.b.1. ..................
Ground Acceleration
Time and Distance.
±5% time and distance
or ±5% time and
±200 ft (61 m) of distance.
Takeoff ........................
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..
1.b.2. ..................
Minimum Control
Speed—ground
(Vmcg) using aerodynamic controls
only (per applicable
airworthiness standard) or alternative
low speed 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 ........................
1.b.3. ..................
Minimum Unstick
Speed (Vmu) or
equivalent test to
demonstrate early
rotation takeoff characteristics.
±3 kts airspeed ±1.5°
pitch angle.
Takeoff ........................
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±10% or ±2°/sec. turn
rate.
A
Information
notes
B
C
D
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.
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.
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 V1 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.
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 or
an early rotation
take-off.
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.).
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
59627
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Tolerance
Test details
Number
Title
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).
Takeoff ........................
1.b.5. ..................
Critical Engine Failure
on Takeoff.
±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).
1.b.6. ..................
Crosswind Takeoff ......
±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.
Correct trend at
groundspeeds below
40 kts. for rudder/
pedal and heading.
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 (1.3daN)
wheel force, ±10%
or ±5 lb (2.2 daN)
rudder pedal force.
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Simulator level
Flight
conditions
A
B
C
D
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 configurations, 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
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
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 wind
measured at 33 ft
(10 m) above the
runway.
X
X
X
X
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notes
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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.
In those situations
where a maximum
crosswind or a maximum demonstrated
crosswind is not
known, contact the
NSPM.
59628
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Tolerance
Simulator level
Flight
conditions
Test details
Number
Title
1.b.7. ..................
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. .....................
Climb
1.c.1. ..................
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. (300
m).
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
climb gradient requirements of 14
CFR part 23 or part
25, as appropriate.
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. (300 m).
X
1.c.3. ..................
One Engine Inoperative En route Climb.
±10% time, ±10% distance, ±10% fuel
used.
Clean ...........................
Record results for at
least a 5,000 ft
(1550 m) climb segment. Flight test data
or airplane performance manual data
may be used.
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A
E:\FR\FM\22OCP2.SGM
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.
X
X
X
X
X
X
X
X
22OCP2
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
59629
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Simulator level
Flight
conditions
Test details
±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.
Approach .....................
Tolerance
Number
Title
A
B
C
1.c.4. ..................
One Engine Inoperative Approach
Climb (if operations
in icing conditions
are authorized).
D
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. (300
m).
X
X
X
X
1.d. .....................
Cruise/Descent
1.d.1. ..................
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
1.d.2. ..................
Level flight deceleration.
X
±5% Time ....................
Cruise ..........................
Record results for a
minimum of 50 kts.
speed decrease
using idle power.
X
X
X
1.d.3. ..................
X
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.d.4. ..................
Idle descent ................
±3 kt airspeed, ±5% or
±200 ft/min (1.0m/
sec) descent rate.
Clean ...........................
Record a stabilized,
idle power descent
at normal descent
speed at mid-altitude. Flight simulator
performance must
be recorded over an
interval of at least
1,000 ft. (300 m).
X
X
X
X
1.d.5. ..................
Emergency descent ....
±5 kt airspeed, ±5% or
±300 ft/min (1.5m/s)
descent rate.
N/A ..............................
Performance must be
recorded over an interval of at least
3,000 ft (900 m).
X
X
X
X
1.e. .....................
Stopping
Information
notes
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The airplane should be
configured with all
anti-ice and de-ice
systems operating
normally, with the
gear up and goaround flaps set. All
icing accountability
considerations
should be applied in
accordance with the
aircraft certification
or authorization for
an approach in icing
conditions.
The stabilized descent
should be conducted
with speed brakes
extended, if applicable, at mid-altitude
and near Vmo speed
or in accordance
with emergency descent procedures.
59630
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Tolerance
Simulator level
Flight
conditions
Test details
Number
Title
1.e.1. ..................
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 .......................
1.e.2. ..................
Stopping time and distance, using reverse
thrust and no wheel
brakes on a dry runway.
±5% time and the
smaller of ±10% or
±200 ft (61 m) of distance.
1.e.3. ..................
Stopping distance,
using wheel brakes
and no reverse
thrust on a wet runway.
1.e.4. ..................
Stopping distance,
using wheel brakes
and no reverse
thrust on an icy runway.
1.f. ......................
Engines
VerDate Aug<31>2005
17:31 Oct 19, 2007
A
B
C
D
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
X
X
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.
X
X
X
X
±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
±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
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notes
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
59631
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Tolerance
Simulator level
Flight
conditions
Test details
Number
Title
1.f.1. ...................
Acceleration ................
±10% Tt and ±10% Ti,
or ±0.25 sec.
Approach or landing ...
1.f.2. ...................
Deceleration ................
±10% Tt and ±10% Ti,
or ±0.25 sec.
Ground ........................
Information
notes
A
B
C
D
Record engine power
(N1, N2, EPR,
Torque) from flight
idle to go-around
power for a rapid
(slam) throttle movement.
X
X
X
X
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% of go
around power.
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.
X
X
X
X
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.
2. Handling Qualities
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 test 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 flight deck 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
2.a. .....................
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 and Surface Position Calibration.
2.a.2.b. ...............
(Reserved)
2.a.3.a. ...............
Rudder Pedal Position
vs. Force and Surface Position Calibration.
Contact the NSPM for
clarification of any
issue regarding airplanes with reversible controls.
VerDate Aug<31>2005
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±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 inflight 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 inflight 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, ±2°
rudder angle.
Ground ........................
Record results for an
uninterrupted control
sweep to the stops.
X
X
X
X
Test results should be
validated with inflight 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.
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59632
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Tolerance
Number
Title
Simulator level
Flight
conditions
Test details
A
B
C
Information
notes
D
2.a.3.b. ...............
(Reserved)
2.a.4. ..................
Nosewheel Steering
Controller Force and
Position Calibration.
±2 lb (0.9 daN) breakout, ±10% or ±3 lb
(1.3 daN) force, ±2°
nosewheel angle.
Ground ........................
Record results of an
uninterrupted control
sweep to the stops.
X
X
X
X
2.a.5. ..................
Rudder Pedal Steering
Calibration.
±2° nosewheel angle ..
Ground ........................
Record results of 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. ..................
Pitch Trim Rate ...........
±10% trim rate (°/sec)
Ground and approach
The trim rate must be
checked using the
pilot primary trim
(ground) and using
the autopilot or pilot
primary trim in flight
at go-around flight
conditions.
X
X
X
X
2.a.8. ..................
Alignment of Flight
Deck Throttle Lever
vs. Selected Engine
Parameter.
±5° of throttle lever
angle, or ±3% N1, or
±.03 EPR, or ±3%
maximum rated
manifold pressure, or
±3% 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
Calibration.
±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
2.b. .....................
Dynamic Control Tests
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.
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The purpose of the test
is to compare full
flight simulator
against design data
or equivalent.
Full flight simulator
computer output results may be used to
show compliance.
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
59633
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Tolerance
Flight
conditions
Number
Title
2.b.1. ..................
Pitch 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).
For the alternate method see paragraph 4
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.
Takeoff, Cruise, and
Landing.
2.b.2. ..................
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
(0.1Ad).
For the alternate method see paragraph 4
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.
Takeoff, Cruise, and
Landing.
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Simulator level
Test details
A
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 full throw or 25%
to 50% of the maximum allowable pitch
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 4 of
this attachment for
more information.
Static and dynamic
flight control tests
should be accomplished at the same
feel or impact pressures.
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 or 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 4 of
this attachment for
more information.
Static and dynamic
flight control tests
should be accomplished at the same
feel or impact pressures.
E:\FR\FM\22OCP2.SGM
B
Information
notes
22OCP2
59634
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Tolerance
Flight
conditions
Number
Title
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
(0.1Ad).
For the alternate method (see paragraph 4
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.
Takeoff, Cruise, and
Landing.
2.b.4. ..................
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 ..
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Test details
A
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 full throw.
X
X
Control inputs must be
typical of minor corrections made while
established on an
ILS approach
course, using from
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
E:\FR\FM\22OCP2.SGM
B
Information
notes
22OCP2
‘‘n’’ is the sequential
period of a full cycle
of oscillation. Refer
to paragraph 4 of
this attachment for
more information.
Static and dynamic
flight control tests
should be accomplished at the same
feel or impact pressures.
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
59635
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Tolerance
Simulator level
Flight
conditions
Test details
Number
Title
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. .....................
A
B
C
D
Control inputs must be
typical of minor corrections made while
established on an
ILS approach
course, using from
0.5°/sec to 2°/sec
roll rate. The test
may be run in only
one direction; however, for airplanes
that exhibit non-symmetrical 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, using from
0.5°/sec to 2°/sec
yaw rate. The test
may be run in only
one direction; however, for airplanes
that exhibit non-symmetrical 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
Longitudinal Control Tests
X
X
Power setting is that required for level flight unless otherwise specified.
2.c.1. ..................
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Power Change Dynamics.
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±3 kt airspeed, ±100 ft
(30 m) altitude,
±20% or ±1.5° pitch
angle.
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Approach .....................
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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.
E:\FR\FM\22OCP2.SGM
X
X
22OCP2
Information
notes
59636
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Tolerance
Test details
Number
Title
2.c.2. ..................
Flap/Slat Change Dynamics.
±3 kt airspeed, ±100 ft
(30 m) altitude,
±20% or ±1.5° pitch
angle.
Takeoff through initial
flap retraction, and
approach to landing.
2.c.3. ..................
Spoiler/Speedbrake
Change Dynamics.
±3 kt airspeed, ±100 ft
(30 m) altitude,
±20% or ±1.5° pitch
angle.
2.c.4. ..................
Gear Change Dynamics.
2.c.5. ..................
Longitudinal Trim ........
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Simulator level
Flight
conditions
A
B
C
D
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
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
±0.5° trim surface
angle ±1° elevator
±1° pitch angle ±5%
net thrust or equivalent.
Cruise, Approach, and
Landing.
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
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Information
notes
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
59637
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Tolerance
Test details
Number
Title
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.
Cruise, Approach, and
Landing.
2.c.7. ..................
Longitudinal Static Stability.
±5 lb (±2.2 daN) or
±10% pitch controller
force.
Alternative method: ±1°
or ±10% change of
elevator.
2.c.8. ..................
Stall Characteristics ....
±3 kt airspeed for initial
buffet, stall warning,
and stall speeds. ±2°
bank for speeds
greater than stick
shaker or initial buffet.
Additionally, for those
simulators with reversible flight control
systems: ±10% or ±5
lb (2.2 daN)) Stick/
Column force (prior
to ‘‘g break’’ only).
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Simulator level
Flight
conditions
A
B
C
D
Continuous time history data or a series
of snapshot tests
may be used.
Record results up to
30° of bank for approach and landing
configurations.
Record results for up
to 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-force-per-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
or Non-normal control states.
X
X
X
X
Second Segment
Climb, and Approach
or Landing.
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 stall
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
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Information
notes
59638
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Tolerance
Simulator level
Flight
conditions
Test details
Number
Title
A
2.c.9. ..................
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.
CCA: Test in Non-normal control states.
2.c.10. ................
Short Period Dynamics
±1.5° pitch angle or
±2°/sec pitch rate,
±0.10g acceleration.
Cruise ..........................
CCA: Test in Normal
and Non-normal control states.
2.c.11. ................
(Reserved)
2.d. .....................
B
C
D
X
X
X
X
X
X
Information
notes
X
Lateral Directional Tests
Power setting is that required for level flight unless otherwise specified.
2.d.1. ..................
Minimum Control
Speed, Air (Vmca or
Vmcl), per Applicable
Airworthiness Standard or Low Speed
Engine Inoperative
Handling Characteristics in the Air.
±3 kt airspeed .............
Takeoff or Landing
(whichever is most
critical in the airplane).
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.
X
X
X
X
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.
Record results for normal roll controller deflection (about onethird of maximum roll
controller travel).
May be combined
with step input of
flight deck roll controller test (2.d.3.).
X
X
X
X
2.d.3. ..................
Roll Response to Flight
deck Roll Controller
Step Input.
±10% or ±2° bank
angle.
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
2.d.4. ..................
Spiral Stability .............
Correct trend and ±2°
or ±10% bank angle
in 20 seconds.
Alternate test requires
correct trend and ±2°
aileron.
Cruise, and Approach
or Landing.
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 28° to 32°.
CCA: Test in Normal
and Non-normal control states.
X
X
X
X
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Low Speed Engine Inoperative Handling
may be governed by
a performance or
control limit that prevents demonstration
of Vmca in the conventional manner.
With wings level, apply
a step roll control
input using approximately one-third 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.
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
59639
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Tolerance
Number
Title
Flight
conditions
Simulator level
Test details
A
B
C
Information
notes
D
2.d.5. ..................
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
2.d.6. ..................
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
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 Non-normal control states.
X
X
X
X
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.
X
X
X
X
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 nosewheel touchdown.
CCA: Test in Normal
and Non-normal control states.
X
X
X
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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.
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.
59640
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Tolerance
Flight
conditions
Simulator level
Test details
Number
Title
2.e.2. ..................
Minimum 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 or 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 lb
(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. Test data
must include information on wind profile, for a crosswind
component of 60%
of the maximum
wind measured at 33
ft (10 m) above the
runway.
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. ..................
Autopilot landing (if applicable).
±5 ft (1.5 m) flare
height, ±0.5 sec Tf,
or ±10%Tf, ±140 ft/
min (0.7 m/sec) rate
of descent at touchdown.
±10 ft (3 m) lateral deviation during rollout.
2.e.6. ..................
All engines operating,
autopilot, go around.
±3 kt airspeed, ±1.5°
pitch angle, ±1.5°
angle of attack.
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C
D
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
Landing .......................
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
.....................................
Normal, all-engines-operating, Go Around
with the autopilot engaged (if applicable)
at medium landing
weight.
CCA: Test in Normal
and Non-normal control states.
X
X
X
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Information
notes
22OCP2
In those situations
where a maximum
crosswind or a maximum demonstrated
crosswind is not
known, contact the
NSPM.
Tf = duration of flare.
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
59641
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Flight
conditions
Tolerance
Number
Title
Simulator level
Test details
A
B
C
D
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
Information
notes
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.
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 asymmetric 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. ......................
Ground Effect
±1° elevator
±0.5°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.
Landing .......................
The Ground Effect
model must be validated by the test selected and a rationale must be provided
for selecting the particular test.
X
X
X
See paragraph on
Ground Effect in this
attachment for additional information.
See Attachment 5 .......
Takeoff and Landing ...
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.
X
X
See Attachment 5 for
information related to
Level A and B simulators.
Test to demonstrate
Ground Effect.
2.g. .....................
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. .....................
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.....................................
Flight Maneuver and Envelope Protection Functions
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59642
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Tolerance
Number
Title
Flight
conditions
Simulator level
Test details
A
B
C
Information
notes
D
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. Set 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
X
Based on Simulator
Capability.
N/A ..............................
Required as part of
MQTG but not required to be scheduled as part of continuing qualification
evaluations.
The test must demonstrate motion system leg balance as
specified by the applicant for flight simulator qualification.
X
X
X
X
Based on Simulator
Capability.
N/A ..............................
Required as part of
MQTG but not required to be scheduled as part of continuing qualification
evaluations.
The test must demonstrate a smooth
turn-around (shift to
opposite direction of
movement) of the
motion system as
specified by the applicant for flight simulator qualification.
X
X
X
X
3. Motion System
3.a. .....................
3.b. .....................
3.c. .....................
3.d. .....................
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Leg balance
Turn-around check
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. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
59643
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Tolerance
Number
Title
With the same input
signal, the test results must be repeatable to within ±0.05g
actual platform linear
acceleration.
3.e. .....................
Simulator level
Flight
conditions
Test details
Accomplished in both
the ‘‘ground’’ mode
and in the ‘‘flight’’
mode of the motion
system operation.
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.
A
B
C
D
X
X
X
X
Information
notes
This test ensures that
motion system hardware and software
(in normal flight simulator operating
mode) continue to
perform as originally
qualified. Performance changes from
the original baseline
can be readily identified with this information.
Motion cueing performance signature.
Required as part of MQTG but not required as part of continuing evaluations.
These tests should be
run with the motion
buffet mode disabled. See paragraph 5.d., of this attachment, Motion
cueing performance
signature.
3.e.1. ..................
Takeoff rotation (VR to
V2).
As specified by the
sponsor for flight
simulator qualification.
Ground ........................
Pitch attitude due to
initial climb must
dominate over cab
tilt due to longitudinal acceleration.
X
X
X
X
Associated with test
1.b.4.
3.e.2. ..................
Engine failure between
V1 and VR.
As specified by the
sponsor for flight
simulator qualification.
Ground ........................
.....................................
X
X
X
X
Associated with test
1.b.5.
3.e.3. ..................
Pitch change during
go-around.
As specified by the
sponsor for flight
simulator qualification.
Flight ...........................
.....................................
X
X
X
Associated with test
2.e.6.
3.e.4. ..................
Configuration changes
As specified by the
sponsor for flight
simulator qualification.
Flight ...........................
.....................................
X
X
X
X
Associated with tests
2.c.2. and 2.c.4.
3.e.5. ..................
Power change dynamics.
As specified by the
sponsor for flight
simulator qualification.
Flight ...........................
.....................................
X
X
X
X
Associated with test
2.c.1.
3.e.6. ..................
Landing flare ...............
As specified by the
sponsor for flight
simulator qualification.
Flight ...........................
.....................................
X
X
X
Associated with test
2.e.1.
3.e.7. ..................
Touchdown bump .......
As specified by the
sponsor for flight
simulator qualification.
Ground ........................
.....................................
X
X
Associated with test
2.e.1.
3.f. ......................
Characteristic motion vibrations
The recorded test results for characteristic buffets must allow the comparison of relative amplitude
versus frequency.
3.f.1. ...................
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Simulator test results
must exhibit the
overall appearance
and trends of the airplane data, with at
least three (3) of the
predominant frequency ‘‘spikes’’
being present within
±2 Hz.
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the maximum possible thrust with
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59644
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Tolerance
Number
Title
Simulator level
Flight
conditions
Test details
A
B
C
Information
notes
D
3.f.2. ...................
Buffet with landing
gear extended.
Simulator test results
must exhibit the
overall appearance
and trends of the airplane data, with at
least three (3) of the
predominant frequency ‘‘spikes’’
being present within
±2 Hz.
Flight ...........................
The test must be conducted at a nominal,
mid-range airspeed;
i.e., sufficiently
below landing gear
limiting airspeed to
avoid inadvertently
exceeding this limitation.
X
3.f.3. ...................
Buffet with flaps extended.
Simulator test results
must exhibit the
overall appearance
and trends of the airplane data, with at
least three (3) of the
predominant frequency ‘‘spikes’’
being present within
±2 Hz.
Flight ...........................
The test must be conducted at a nominal,
mid-range airspeed;
i.e., sufficiently
below flap extension
limiting airspeed to
avoid inadvertently
exceeding this limitation.
X
3.f.4. ...................
Buffet with
speedbrakes deployed.
Simulator test results
must exhibit the
overall appearance
and trends of the airplane data, with at
least three (3) of the
predominant frequency ‘‘spikes’’
being present within
±2 Hz.
Flight ...........................
.....................................
X
3.f.5. ...................
Buffet at approach-tostall.
Simulator test results
must exhibit the
overall appearance
and trends of the airplane data, with at
least three (3) of the
predominant frequency ‘‘spikes’’
being present within
±2 Hz.
Flight ...........................
The test must be conducted for approach
to stall. Post stall
characteristics are
not required.
X
3.f.6. ...................
Buffet at high airSimulator test results
speeds or high Mach.
must exhibit the
overall appearance
and trends of the airplane data, with at
least three (3) of the
predominant frequency ‘‘spikes’’
being present within
±2 Hz.
Flight ...........................
.....................................
X
3.f.7. ...................
In-flight vibrations for
propeller driven airplanes.
Flight (clean configuration).
.....................................
X
Simulator test results
must exhibit the
overall appearance
and trends of the airplane data, with at
least three (3) of the
predominant frequency ‘‘spikes’’
being present within
±2 Hz.
The test may be conducted during either
a high speed maneuver (e.g., ‘‘windup’’ turn) or at high
Mach.
4. Visual System
4.a. .....................
Visual System Response Time: (Choose either test 4.a.1. or 4.a.2. to satisfy test 4.a., Visual System
Response Time Test. This test also suffices for motion system response timing and flight deck instrument response timing.)
4.a.1. ..................
Latency
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See additional information in this attachment.
22OCP2
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
59645
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Simulator level
Flight
conditions
Test details
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).
150 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).
300 ms (or less) after
controller movement.
N/A ..............................
A separate test is required in each axis
(pitch, roll, and yaw).
150 ms (or less) after
controller movement.
N/A ..............................
A separate test is required in each axis
(pitch, roll, and yaw).
Continuous collimated
field of view providing at least 45°
horizontal and 30°
vertical field of view
for each pilot seat.
Both pilot seat visual
systems must be operable simultaneously.
N/A ..............................
Required as part of
MQTG but not required as part of
continuing evaluations.
Tolerance
Number
Title
4.a.2. ..................
A
B
X
C
X
Information
notes
D
The visual scene or
test pattern used
during the response
testing should be
representative of the
system capacities required to meet the
daylight, twilight
(dusk/dawn) and/or
night visual capability as appropriate.
X
X
Transport Delay
4.b. .....................
Continuous collimated
visual field of view.
4.b.2. ..................
X
If Transport Delay is
the chosen method
to demonstrate relative responses, the
sponsor and the
NSPM will use the
latency values to ensure proper simulator response when
reviewing those existing tests where latency can be identified (e.g., short period, roll response,
rudder response).
X
(Reserved)
X
Field of View
4.b.1. ..................
X
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X
X
22OCP2
A vertical field of view
of 30° may be insufficient to meet visual
ground segment requirements.
59646
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Simulator level
Flight
conditions
Test details
Continuous field of
view of at least 176°
horizontally and 36
vertically.
N/A ..............................
An SOC is required
and must explain the
geometry of the installation. Horizontal
field of view must be
at least 176° (including not less than 88°
either side of the
center line of the design eye point). Additional horizontal
field of view capability may be added
at the sponsor’s discretion provided the
minimum field of
view is retained.
Vertical field of view
must be at least 36°
from each pilot’s eye
point. Required as
part of MQTG but
not required as part
of continuing qualification evaluations.
5° even angular spacing within ±1° as
measured from either pilot eye point
and within 1.5° for
adjacent squares.
N/A ..............................
The angular spacing of
any chosen 5°
square and the relative spacing of adjacent squares must
be within the stated
tolerances.
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/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.
Tolerance
Number
Title
4.b.3. ..................
Continuous, collimated,
field of view.
4.c. .....................
(System geometry)
4.d. .....................
4.e. .....................
VerDate Aug<31>2005
A
D
X
The horizontal field of
view is traditionally
described as a 180°
field of view. However, the field of
view is technically no
less than 176°. Field
of view should 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
X
The purpose of this
test is to evaluate
local linearity of the
displayed image at
either pilot eye point.
System geometry
should be measured
using a visual test
pattern filling the entire visual scene (all
channels) with a matrix of black and
white 5° squares
with light points at
the intersections.
X
X
C
X
X
B
Information
notes
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 aft-cab and
flight deck ambient
light levels should be
zero.
Surface contrast ratio
Highlight brightness
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
59647
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Simulator level
Flight
conditions
Test details
Not less than six (6)
foot-lamberts (20 cd/
m2).
N/A ..............................
Not greater than two
(2) arc minutes.
Tolerance
Number
Title
4.g. .....................
C
D
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.
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.
Not greater than five
(5) arc-minutes.
4.f. ......................
A
B
Information
notes
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 10:1 ......
N/A ..............................
An SOC is required
and must include the
relevant calculations.
Surface resolution
Light point size
4.h. .....................
Light point contrast ratio
4.h.1. ..................
For Level A and B simulators.
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X
X
22OCP2
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.
59648
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Simulator level
Flight
conditions
Test details
Not less than 25:1 ......
N/A ..............................
An SOC is required
and must include the
relevant calculations.
The visible segment in
the simulator must
be within 20% of the
segment computed
to be visible from the
airplane flight deck.
The tolerance(s)
may be applied at either or both ends of
the displayed segment. However,
lights and ground
objects computed to
be visible from the
airplane flight deck
at the near end of
the visible segment
must be visible in
the simulator.
Landing configuration,
trimmed for appropriate airspeed, at
100 ft (30 m) above
the touchdown zone,
on glide slope with
an RVR value set at
1,200 ft (350 m).
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, flight
deck cut-off angle,
and a visibility of
1,200 ft (350 m)
RVR. Simulator performance must be
measured against
the QTG calculations.
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 flight
deck cutoff
angle.
Tolerance
Number
Title
4.h.2. ..................
For Level C and D
simulators.
4.i. ......................
A
B
Information
notes
C
D
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.
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
X
X
(2) Approach data as
follows:
(i) Identification of
runway.
(ii) Horizontal distance from runway threshold to
glideslope intercept with runway.
(iii) Glideslope
angle.
(iv) Airplane pitch
angle on approach.
(3) Airplane data for
manual testing:
(i) Gross weight.
(ii) Airplane configuration.
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
59649
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Tolerance
Number
Title
Flight
conditions
Simulator level
Test details
A
B
C
D
(iii) Approach airspeed.
If non-homogenous fog
is used to obscure
visibility, the vertical
variation in horizontal visibility must
be described and be
included in the slant
range visibility calculation used in the
computations.
5. Sound System
The sponsor will not be required to repeat the airplane tests (i.e., tests 5.a.1. through 5.a.8. (or 5.b.1. through 5.b.9.)
and 5.c., as appropriate) during continuing qualification evaluations if frequency response and background noise test
results are within tolerance when compared to the initial qualification evaluation results, and the sponsor shows that
no software changes have occurred that will affect the airplane test results. If the frequency response test method is
chosen and fails, the sponsor may elect to fix the frequency response problem and repeat the test or the sponsor may
elect to repeat the airplane tests. If the airplane tests are repeated during continuing qualification evaluations, the results may be compared against initial qualification evaluation results or airplane master data.
5.a. .....................
Turbo-jet airplanes
5.a.1. ..................
Ready for engine start
±5 dB per 1⁄3 octave
band.
Ground ........................
Normal conditions prior
to engine start with
the Auxiliary Power
Unit operating, if appropriate.
X
5.a.2. ..................
All engines at idle .......
±5 dB per 1⁄3 octave
band.
Ground ........................
Normal condition prior
to takeoff.
X
5.a.3. ..................
All engines at maximum allowable
thrust with brakes
set.
±5 dB per 1⁄3 octave
band.
Ground ........................
Normal condition prior
to takeoff.
X
5.a.4. ..................
Climb ...........................
±5 dB per 1⁄3 octave
band.
En-route climb .............
Medium altitude ..........
X
5.a.5. ..................
Cruise ..........................
±5 dB per 1⁄3 octave
band.
Cruise ..........................
Normal cruise configuration.
X
5.a.6. ..................
Speedbrake/spoilers
extended (as appropriate).
±5 dB per 1⁄3 octave
band.
Cruise ..........................
Normal and constant
speedbrake deflection for descent at a
constant airspeed
and power setting.
X
5.a.7. ..................
Initial approach ...........
±5 dB per 1⁄3 octave
band.
Approach .....................
Constant airspeed,
gear up, flaps and
slats, as appropriate.
X
5.a.8. ..................
Final approach ............
±5 dB per 1⁄3 octave
band.
Landing .......................
Constant airspeed,
gear down, full flaps.
X
5.b. .....................
Propeller airplanes
5.b.1. ..................
Ready for engine start
±5 dB per 1⁄3 octave
band.
Ground ........................
Normal conditions prior
to engine start with
the Auxiliary Power
Unit operating, if appropriate.
X
5.b.2. ..................
All propellers feathered
±5 dB per 1⁄3 octave
band.
Ground ........................
Normal condition prior
to takeoff.
X
5.b.3. ..................
Ground idle or equivalent.
±5 dB per 1⁄3 octave
band.
Ground ........................
Normal condition prior
to takeoff.
X
5.b.4. ..................
Flight idle or equivalent
±5 dB per 1⁄3 octave
band.
Ground ........................
Normal condition prior
to takeoff.
X
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Information
notes
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TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Tolerance
Number
Title
Simulator level
Flight
conditions
Test details
A
B
C
Information
notes
D
5.b.5. ..................
All engines at maximum allowable
power with brakes
set.
±5 dB per ⁄ octave
band.
Ground ........................
Normal condition prior
to takeoff.
X
5.b.6. ..................
Climb ...........................
±5 dB per 1⁄3 octave
band.
En-route climb .............
Medium altitude ..........
X
5.b.7. ..................
Cruise ..........................
±5 dB per 1⁄3 octave
band.
Cruise ..........................
Normal cruise configuration.
X
5.b.8. ..................
Initial approach ...........
±5 dB per 1⁄3 octave
band.
Approach .....................
Constant airspeed,
gear up, flaps extended as appropriate, RPM as per
operating manual.
X
5.b.9. ..................
Final Approach ............
±5 dB per 1⁄3 octave
band.
Landing .......................
Constant airspeed,
gear down, full flaps,
RPM as per operating manual.
X
5.c. .....................
Special cases
±5 dB per 1⁄3 octave
band.
As appropriate ............
.....................................
X
These special cases
are identified as particularly significant
during critical phases
of flight and ground
operations for a specific airplane type or
model.
±3 dB per 1⁄3 octave
band.
.....................................
Results of the background noise at initial qualification must
be included in the
MQTG.
Measurements must
be made with the
simulation running,
the sound muted
and a ‘‘dead’’ flight
deck.
X
The simulated sound
will be evaluated to
ensure that the
background noise
does not interfere
with training, testing,
or checking.
5.d. .....................
5.e. .....................
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Frequency response
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
59651
TABLE A2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
Test
Tolerance
Number
Title
±5 dB on three (3)
consecutive bands
when compared to
initial evaluation; and
±2 dB when comparing the average
of the absolute differences between
initial and continuing
qualification evaluation.
lllllllllllllllllllll
Begin Information
3. 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.
4. 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 an FFS to be representative, it
should ‘‘feel’’ like the airplane being
simulated. Compliance with this requirement
is determined by comparing a recording of
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Simulator level
Flight
conditions
Test details
.....................................
Applicable only to Continuing Qualification
Evaluations. If frequency response
plots are provided
for each channel at
the initial qualification evaluation,
these plots may be
repeated at the continuing qualification
evaluation with the
following tolerances
applied:
(a) The continuing
qualification 1⁄3
octave band
amplitudes must
not exceed ±5
dB for three
consecutive
bands when
compared to initial results.
(b) The average of
the sum of the
absolute differences between initial and
continuing qualification results
must not exceed
2 dB (refer to
table A.2.B. in
this attachment).
A
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 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.
(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
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B
C
Information
notes
D
X
Measurements are
compared to those
taken during initial
qualification evaluation.
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
controls) match those of the airplane within
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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
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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
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
First overshoot and ±1 subovershoots.
sequent 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
End Information
lllllllllllllllllllll
Begin QPS Requirement
c. Alternative method for control dynamics
evaluation.
(1) An alternative means for validating
control dynamics for aircraft with
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hydraulically powered flight controls and
artificial feel systems is by the measurement
of control force and rate of movement. For
each axis of pitch, roll, and yaw, the control
must be forced to its maximum extreme
position for the following distinct rates.
These tests are conducted under normal
flight and ground conditions.
(a) Static test—Slowly move the control so
that a full sweep is achieved within 95 to 105
seconds. 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 within 8–12 seconds.
(c) Fast dynamic test—Achieve a full
sweep within 3–5 seconds.
Note: Dynamic sweeps may be limited to
forces not exceeding 100 lbs. (44.5 daN).
(d) Tolerances
(i) Static test; see Table A2A, Full Flight
Simulator (FFS) Objective Tests, Items 2.a.1.,
2.a.2., and 2.a.3.
(ii) Dynamic test ±2 lbs (0.9 daN) or ±10%
on dynamic increment above static test.
End QPS Requirement
lllllllllllllllllllll
Begin Information
d. The FAA is open to alternative means
such as the one described above. The
alternatives should be justified and
appropriate to the application. For example,
the method described here may not apply to
all manufacturers’’ systems and certainly not
to aircraft with reversible control systems.
Each case is considered on its own merit on
an ad hoc basis. If the FAA finds that
alternative methods do not result in
satisfactory performance, more
conventionally accepted methods will have
to be used.
BILLING CODE 4910–13–P
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
BILLING CODE 4910–13–C
5. Ground Effect
a. For an FFS to be used for take-off and
landing (not applicable to Level A simulators
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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
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chosen for FFS validation should indicate
these changes.
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(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.
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.
6. Motion System
a. General.
(1) Pilots use continuous information
signals to regulate the state of the airplane.
In concert with the instruments and outsideworld visual information, whole-body
motion feedback is essential in assisting the
pilot to control the airplane dynamics,
particularly in the presence of external
disturbances. The motion system should
meet basic objective performance criteria,
and should be subjectively tuned at the
pilot’s seat position to represent the linear
and angular accelerations of the airplane
during a prescribed minimum set of
maneuvers and conditions. The response of
the motion cueing system should also be
repeatable.
(2) The Motion System tests in Section 3
of Table A2A are intended to qualify the FFS
motion cueing system from a mechanical
performance standpoint. Additionally, the
list of motion effects provides a
representative sample of dynamic conditions
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that should be present in the flight simulator.
An additional list of representative, trainingcritical maneuvers, selected from Section 1
(Performance tests), and Section 2 (Handling
Qualities tests), in Table A2A, that should be
recorded during initial qualification (but
without tolerance) to indicate the flight
simulator motion cueing performance
signature have been identified (reference
Section 3.e). These tests are intended to help
improve the overall standard of FFS motion
cueing.
b. Motion System Checks. The intent of test
3a, Frequency Response, test 3b, Leg Balance,
and test 3c, Turn-Around Check, as described
in the Table of Objective Tests, is to
demonstrate the performance of the motion
system hardware, and to check the integrity
of the motion set-up with regard to
calibration and wear. These tests are
independent of the motion cueing software
and should be considered robotic tests.
c. Motion System Repeatability. The intent
of this test is to ensure that the motion
system software and motion system hardware
have not degraded or changed over time. This
diagnostic test should be completed during
continuing qualification checks in lieu of the
robotic tests. This will allow an improved
ability to determine changes in the software
or determine degradation in the hardware.
The following information delineates the
methodology that should be used for this test.
(1) Input: The inputs should be such that
rotational accelerations, rotational rates, and
linear accelerations are inserted before the
transfer from airplane center of gravity to
pilot reference point with a minimum
amplitude of 5 deg/sec/sec, 10 deg/sec and
0.3 g, respectively, to provide adequate
analysis of the output.
(2) Recommended output:
(a) Actual platform linear accelerations; the
output will comprise accelerations due to
both the linear and rotational motion
acceleration;
(b) Motion actuators position.
d. Motion Cueing Performance Signature.
(1) Background. The intent of this test is to
provide quantitative time history records of
motion system response to a selected set of
automated QTG maneuvers during initial
qualification. This is not intended to be a
comparison of the motion platform
accelerations against the flight test recorded
accelerations (i.e., not to be compared against
airplane cueing). If there is a modification to
the initially qualified motion software or
motion hardware (e.g., motion washout filter,
simulator payload change greater than 10%)
then a new baseline may need to be
established.
(2) Test Selection. The conditions
identified in Section 3.e. in Table A2A are
those maneuvers where motion cueing is the
most discernible. They are general tests
applicable to all types of airplanes and
should be completed for motion cueing
performance signature at any time acceptable
to the NSPM prior to or during the initial
qualification evaluation, and the results
included in the MQTG.
(3) Priority. Motion system should be
designed with the intent of placing greater
importance on those maneuvers that directly
influence pilot perception and control of the
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59655
airplane motions. For the maneuvers
identified in section 3.e. in Table A2A, the
flight simulator motion cueing system should
have a high tilt co-ordination gain, high
rotational gain, and high correlation with
respect to the airplane simulation model.
(4) Data Recording. The minimum list of
parameters provided should allow for the
determination of the flight simulator’s
motion cueing performance signature for the
initial qualification evaluation. The following
parameters are recommended as being
acceptable to perform such a function:
(a) Flight model acceleration and rotational
rate commands at the pilot reference point;
(b) Motion actuators position;
(c) Actual platform position;
(d) Actual platform acceleration at pilot
reference point.
e. Motion Vibrations.
(1) Presentation of results. The
characteristic motion vibrations may be used
to verify that the flight simulator can
reproduce the frequency content of the
airplane when flown in specific conditions.
The test results should be presented as a
Power Spectral Density (PSD) plot with
frequencies on the horizontal axis and
amplitude on the vertical axis. The airplane
data and flight simulator data should be
presented in the same format with the same
scaling. The algorithms used for generating
the flight simulator data should be the same
as those used for the airplane data. If they are
not the same then the algorithms used for the
flight simulator data should be proven to be
sufficiently comparable. As a minimum, the
results along the dominant axes should be
presented and a rationale for not presenting
the other axes should be provided.
(2) Interpretation of results. The overall
trend of the PSD plot should be considered
while focusing on the dominant frequencies.
Less emphasis should be placed on the
differences at the high frequency and low
amplitude portions of the PSD plot. During
the analysis, certain structural components of
the flight simulator have resonant
frequencies that are filtered and may not
appear in the PSD plot. If filtering is
required, the notch filter bandwidth should
be limited to 1 Hz to ensure that the buffet
feel is not adversely affected. In addition, a
rationale should be provided to explain that
the characteristic motion vibration is not
being adversely affected by the filtering. The
amplitude should match airplane data as
described below. However, if the PSD plot
was altered for subjective reasons, a rationale
should be provided to justify the change. If
the plot is on a logarithmic scale, it may be
difficult to interpret the amplitude of the
buffet in terms of acceleration. For example,
a 1×10¥3 grams2/Hz would describe a heavy
buffet and may be seen in the deep stall
regime. Alternatively, a 1×10¥6 grams2/Hz
buffet is almost not perceivable; but may
represent a flap buffet at low speed. The
previous two examples differ in magnitude
by 1000. On a PSD plot this represents three
decades (one decade is a change in order of
magnitude of 10; and two decades is a change
in order of magnitude of 100).
7. Sound System
a. General. The total sound environment in
the airplane is very complex, and changes
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with atmospheric conditions, airplane
configuration, airspeed, altitude, and power
settings. Flight deck sounds are an important
component of the flight deck operational
environment and provide valuable
information to the flight crew. These aural
cues can either assist the crew (as an
indication of an abnormal situation), or
hinder the crew (as a distraction or
nuisance). For effective training, the flight
simulator should provide flight deck sounds
that are perceptible to the pilot during
normal and abnormal operations, and
comparable to those of the airplane. The
flight simulator operator should carefully
evaluate background noises in the location
where the device will be installed. To
demonstrate compliance with the sound
requirements, the objective or validation tests
in this attachment were selected to provide
a representative sample of normal static
conditions typically experienced by a pilot.
b. Alternate propulsion. For FFS with
multiple propulsion configurations, any
condition listed in Table A2A of this
attachment should be presented for
evaluation as part of the QTG if identified by
the airplane manufacturer or other data
supplier as significantly different due to a
change in propulsion system (engine or
propeller).
c. Data and Data Collection System.
(1) Information provided to the flight
simulator manufacturer should be presented
in the format suggested by the International
Air Transport Association (IATA) ‘‘Flight
Simulator Design and Performance Data
Requirements,’’ as amended. This
information should contain calibration and
frequency response data.
(2) The system used to perform the tests
listed in Table A2A should comply with the
following standards:
(a) The specifications for octave, half
octave, and third octave band filter sets may
be found in American National Standards
Institute (ANSI) S1.11–1986;
(b) Measurement microphones should be
type WS2 or better, as described in
International Electrotechnical Commission
(IEC) 1094–4–1995.
(3) Headsets. If headsets are used during
normal operation of the airplane they should
also be used during the flight simulator
evaluation.
(4) Playback equipment. Playback
equipment and recordings of the QTG
conditions should be provided during initial
evaluations.
(5) Background noise.
(a) Background noise is the noise in the
flight simulator that is not associated with
the airplane, but is caused by the flight
simulator’s cooling and hydraulic systems
and extraneous noise from other locations in
the building. Background noise can seriously
impact the correct simulation of airplane
sounds and should be kept below the
airplane sounds. In some cases, the sound
level of the simulation can be increased to
compensate for the background noise.
However, this approach is limited by the
specified tolerances and by the subjective
acceptability of the sound environment to the
evaluation pilot.
(b) The acceptability of the background
noise levels is dependent upon the normal
sound levels in the airplane being
represented. Background noise levels that fall
below the lines defined by the following
points, may be acceptable:
(i) 70 dB @ 50 Hz;
(ii) 55 dB @ 1000 Hz;
(iii) 30 dB @ 16 kHz
(Note: These limits are for unweighted 1/
3 octave band sound levels. Meeting these
limits for background noise does not ensure
an acceptable flight simulator. Airplane
sounds that fall below this limit require
careful review and may require lower limits
on background noise.)
(6) Validation testing. Deficiencies in
airplane recordings should be considered
when applying the specified tolerances to
ensure that the simulation is representative
of the airplane. Examples of typical
deficiencies are:
(a) Variation of data between tail numbers;
(b) Frequency response of microphones;
(c) Repeatability of the measurements.
TABLE A2B.—EXAMPLE OF RECURRENT FREQUENCY RESPONSE TEST TOLERANCE
Initial results
(dBSPL)
Band center frequency
Recurrent
results
(dBSPL)
50 .................................................................................................................................................
63 .................................................................................................................................................
80 .................................................................................................................................................
100 ...............................................................................................................................................
125 ...............................................................................................................................................
160 ...............................................................................................................................................
200 ...............................................................................................................................................
250 ...............................................................................................................................................
315 ...............................................................................................................................................
400 ...............................................................................................................................................
500 ...............................................................................................................................................
630 ...............................................................................................................................................
800 ...............................................................................................................................................
1000 .............................................................................................................................................
1250 .............................................................................................................................................
1600 .............................................................................................................................................
2000 .............................................................................................................................................
2500 .............................................................................................................................................
3150 .............................................................................................................................................
4000 .............................................................................................................................................
5000 .............................................................................................................................................
6300 .............................................................................................................................................
8000 .............................................................................................................................................
10000 ...........................................................................................................................................
12500 ...........................................................................................................................................
16000 ...........................................................................................................................................
75.0
75.9
77.1
78.0
81.9
79.8
83.1
78.6
79.5
80.1
80.7
81.9
73.2
79.2
80.7
81.6
76.2
79.5
80.1
78.9
80.1
80.7
84.3
81.3
80.7
71.1
73.8
75.6
76.5
78.3
81.3
80.1
84.9
78.9
78.3
79.5
79.8
80.4
74.1
80.1
82.8
78.6
74.4
80.7
77.1
78.6
77.1
80.4
85.5
79.8
80.1
71.1
Average ................................................................................................................................
........................
1.1
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1.2
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0.6
0.3
0.6
0.3
1.8
0.3
1.2
0.9
0.9
1.5
0.9
0.9
2.1
3.0
1.8
1.2
3.0
0.3
3.0
0.3
1.2
1.5
0.6
0.0
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
End Information
lllllllllllllllllllll
8. Additional Information About Flight
Simulator Qualification for New or
Derivative Airplanes
a. Typically, an airplane manufacturer’s
approved final data for performance,
handling qualities, systems or avionics is not
available until well after a new or derivative
airplane has entered service. However, flight
crew training and certification often begins
several months prior to the entry of the first
airplane into service. Consequently, it may be
necessary to use preliminary data provided
by the airplane manufacturer for interim
qualification of flight simulators.
b. In these cases, the NSPM may accept
certain partially validated preliminary
airplane and systems data, and early release
(‘‘red label’’) avionics data in order to permit
the necessary program schedule for training,
certification, and service introduction.
c. Simulator sponsors seeking qualification
based on preliminary data should consult the
NSPM to make special arrangements for
using preliminary data for flight simulator
qualification. The sponsor should also
consult the airplane and flight simulator
manufacturers to develop a data plan and
flight simulator qualification plan.
d. The procedure to be followed to gain
NSPM acceptance of preliminary data will
vary from case to case and between airplane
manufacturers. Each airplane manufacturer’s
new airplane development and test program
is designed to suit the needs of the particular
project and may not contain the same events
or sequence of events as another
manufacturer’s program, or even the same
manufacturer’s program for a different
airplane. Therefore, there cannot be a
prescribed invariable procedure for
acceptance of preliminary data, but instead
there should be a statement describing the
final sequence of events, data sources, and
validation procedures agreed by the
simulator sponsor, the airplane
manufacturer, the flight simulator
manufacturer, and the NSPM.
Note: A description of airplane
manufacturer-provided data needed for flight
simulator modeling and validation is to be
found in the IATA Document ‘‘Flight
Simulator Design and Performance Data
Requirements,’’ as amended.
e. The preliminary data should be the
manufacturer’s best representation of the
airplane, with assurance that the final data
will not significantly deviate from the
preliminary estimates. Data derived from
these predictive or preliminary techniques
should be validated available sources
including, at least, the following:
(1) Manufacturer’s engineering report. The
report should explain the predictive method
used and illustrate past success of the
method on similar projects. For example, the
manufacturer could show the application of
the method to an earlier airplane model or
predict the characteristics of an earlier model
and compare the results to final data for that
model.
(2) Early flight test results. This data is
often derived from airplane certification
tests, and should be used to maximum
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advantage for early flight simulator
validation. Certain critical tests that would
normally be done early in the airplane
certification program should be included to
validate essential pilot training and
certification maneuvers. These include cases
where a pilot is expected to cope with an
airplane failure mode or an engine failure.
Flight test data that will be available early in
the flight test program will depend on the
airplane manufacturer’s flight test program
design and may not be the same in each case.
The flight test program of the airplane
manufacturer should include provisions for
generation of very early flight test results for
flight simulator validation.
f. The use of preliminary data is not
indefinite. The airplane manufacturer’s final
data should be available within 12 months
after the airplane’s first entry into service or
as agreed by the NSPM, the simulator
sponsor, and the airplane manufacturer.
When applying for interim qualification
using preliminary data, the simulator sponsor
and the NSPM should agree on the update
program. This includes specifying that the
final data update will be installed in the
flight simulator within a period of 12 months
following the final data release, unless
special conditions exist and a different
schedule is acceptable. The flight simulator
performance and handling validation would
then be based on data derived from flight
tests. Initial airplane systems data should be
updated after engineering tests. Final
airplane systems data should also be used for
flight simulator programming and validation.
g. Flight simulator avionics should stay
essentially in step with airplane avionics
(hardware and software) updates. The
permitted time lapse between airplane and
flight simulator updates should be minimal.
It may depend on the magnitude of the
update and whether the QTG and pilot
training and certification are affected.
Differences in airplane and flight simulator
avionics versions and the resulting effects on
flight simulator qualification should be
agreed between the simulator sponsor and
the NSPM. Consultation with the flight
simulator manufacturer is desirable
throughout the qualification process.
h. The following describes an example of
the design data and sources that might be
used in the development of an interim
qualification plan.
(1) The plan should consist of the
development of a QTG based upon a mix of
flight test and engineering simulation data.
For data collected from specific airplane
flight tests or other flights, the required
design model or data changes necessary to
support an acceptable Proof of Match (POM)
should be generated by the airplane
manufacturer.
(2) For proper validation of the two sets of
data, the airplane manufacturer should
compare their simulation model responses
against the flight test data, when driven by
the same control inputs and subjected to the
same atmospheric conditions as recorded in
the flight test. The model responses should
result from a simulation where the following
systems are run in an integrated fashion and
are consistent with the design data released
to the flight simulator manufacturer:
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(a) Propulsion
(b) Aerodynamics;
(c) Mass properties;
(d) Flight controls;
(e) Stability augmentation; and
(f) Brakes/landing gear.
i. A qualified test pilot should be used to
assess handling qualities and performance
evaluations for the qualification of flight
simulators of new airplane types.
End Information
lllllllllllllllllllll
Begin QPS Requirement
9. Engineering Simulator—Validation Data
a. When a fully validated simulation (i.e.,
validated with flight test results) is modified
due to changes to the simulated airplane
configuration, the airplane manufacturer or
other acceptable data supplier must
coordinate with the NSPM to supply
validation data from an ‘‘audited’’
engineering simulator/simulation to
selectively supplement flight test data. The
NSPM must be provided an opportunity to
audit the use of the engineering simulation
or the engineering simulator during the
acquisition of the data that will be used as
validation data. Audited data may be used for
changes that are incremental in nature.
Manufacturers or other data suppliers should
be able to demonstrate that the predicted
changes in aircraft performance are based on
acceptable aeronautical principles with
proven success history and valid outcomes.
This should include comparisons of
predicted and flight test validated data.
b. Airplane manufacturers or other
acceptable data suppliers seeking to use an
engineering simulator for simulation
validation data as an alternative to flight-test
derived validation data, must contact the
NSPM and provide the following:
(1) A description of the proposed aircraft
changes, a description of the proposed
simulation model changes, and the use of an
integral configuration management process,
including an audit of the actual simulation
model modifications that includes a step-bystep description leading from the original
model(s) to the current model(s).
(2) A schedule for review by the NSPM of
the proposed plan and the subsequent
validation data to establish acceptability of
the proposal.
(3) Information that demonstrates an ability
to qualify the FFS in which this data is to be
used in accordance with the criteria
contained in § 60.15.
c. To be qualified to supply engineering
simulator validation data, for aerodynamic,
engine, flight control, or ground handling
models, an airplane manufacturer or other
acceptable data supplier must:
(1) Be able to verify their ability to:
(a) Develop and implement high fidelity
simulation models; and
(b) Predict the handling and performance
characteristics of an airplane with sufficient
accuracy to avoid additional flight test
activities for those handling and performance
characteristics.
(2) Have an engineering simulator that:
(a) Is a physical entity, complete with a
flight deck representative of the simulated
class of airplane;
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(b) Has controls sufficient for manual
flight;
(c) Has models that run in an integrated
manner;
(d) Has fully flight-test validated
simulation models as the original or baseline
simulation models;
(e) Has an out-of-the-flight deck visual
system;
(f) Has actual avionics boxes
interchangeable with the equivalent software
simulations to support validation of released
software;
(g) Uses the same models as released to the
training community (which are also used to
produce stand-alone proof-of-match and
checkout documents);
(h) Is used to support airplane
development and certification; and
(i) Has been found to be a high fidelity
representation of the airplane by the
manufacturer’s pilots (or other acceptable
data supplier), certificate holders, and the
NSPM.
(3) Use the engineering simulator to
produce a representative set of integrated
proof-of-match cases.
(4) Use a configuration control system
covering hardware and software for the
operating components of the engineering
simulator.
(5) Demonstrate that the predicted effects
of the change(s) are within the provisions of
subparagraph ‘‘a’’ of this section, and confirm
that additional flight test data are not
required.
d. Additional Requirements for Validation
Data
(1) When used to provide validation data,
an engineering simulator must meet the
simulator standards currently applicable to
training simulators except for the data
package.
(2) The data package used should be:
(a) Comprised of the engineering
predictions derived from the airplane design,
development, or certification process;
(b) Based on acceptable aeronautical
principles with proven success history and
valid outcomes for aerodynamics, engine
operations, avionics operations, flight control
applications, or ground handling;
(c) Verified with existing flight-test data;
and
(d) Applicable to the configuration of a
production airplane, as opposed to a flighttest airplane.
(3) Where engineering simulator data are
used as part of a QTG, an essential match
must exist between the training simulator
and the validation data.
(4) Training flight simulator(s) using these
baseline and modified simulation models
must be qualified to at least internationally
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recognized standards, such as contained in
the ICAO Document 9625, the ‘‘Manual of
Criteria for the Qualification of Flight
Simulators.’’
End QPS Requirement
lllllllllllllllllllll
10. [Reserved]
lllllllllllllllllllll
Begin QPS Requirement
11. Validation Test Tolerances
a. Non-Flight-Test Tolerances
(1) If engineering simulator data or other
non-flight-test data are used as an allowable
form of reference validation data for the
objective tests listed in Table A2A of this
attachment, the data provider must supply a
well-documented mathematical model and
testing procedure that enables a replication of
the engineering simulation results within
20% of the corresponding flight test
tolerances.
End QPS Requirement
lllllllllllllllllllll
Begin Information
b. Background
(1) The tolerances listed in Table A2A of
this attachment are designed to measure the
quality of the match using flight-test data as
a reference.
(2) Good engineering judgment should be
applied to all tolerances in any test. A test
is failed when the results fall outside of the
prescribed tolerance(s).
(3) Engineering simulator data are
acceptable because the same simulation
models used to produce the reference data
are also used to test the flight training
simulator (i.e., the two sets of results should
be ‘‘essentially’’ similar).
(4) The results from the two sources may
differ for the following reasons:
(a) Hardware (avionics units and flight
controls);
(b) Iteration rates;
(c) Execution order;
(d) Integration methods;
(e) Processor architecture;
(f) Digital drift, including:
(i) Interpolation methods;
(ii) Data handling differences; and
(iii) Auto-test trim tolerances.
(5) Any differences must be within 20% of
the flight test tolerances. The reasons for any
differences, other than those listed above,
should be explained.
(6) Guidelines are needed for the
application of tolerances to engineeringsimulator-generated validation data because:
(a) Flight-test data are often not available
due to sound technical reasons;
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(b) Alternative technical solutions are
being advanced; and
(c) High costs.
12. Validation Data Roadmap.
a. Airplane manufacturers or other data
suppliers should supply a validation data
roadmap (VDR) document as part of the data
package. A VDR document contains guidance
material from the airplane validation data
supplier recommending the best possible
sources of data to be used as validation data
in the QTG. A VDR is of special value when
requesting interim qualification, qualification
of simulators for airplanes certificated prior
to 1992, and qualification of alternate engine
or avionics fits. A sponsor seeking to have a
device qualified in accordance with the
standards contained in this QPS appendix
should submit a VDR to the NSPM as early
as possible in the planning stages. The NSPM
is the final authority to approve the data to
be used as validation material for the QTG.
The NSPM and the Joint Aviation
Authorities’ Synthetic Training Devices
Advisory Board have committed to maintain
a list of agreed VDRs.
b. The VDR should identify (in matrix
format) sources of data for all required tests.
It should also provide guidance regarding the
validity of these data for a specific engine
type, thrust rating configuration, and the
revision levels of all avionics affecting
airplane handling qualities and performance.
The VDR should include rationale or
explanation in cases where data or
parameters are missing, engineering
simulation data are to be used, flight test
methods require explanation, or there is any
deviation from data requirements.
Additionally, the document should refer to
other appropriate sources of validation data
(e.g., sound and vibration data documents).
c. The VDR table shown in Table A2C
depicts a generic roadmap matrix identifying
sources of validation data for an abbreviated
list of tests. A complete matrix should
address all test conditions.
d. Two examples of rationale pages are
presented in Appendix F of the IATA ‘‘Flight
Simulator Design and Performance Data
Requirements.’’ These illustrate the type of
airplane and avionics configuration
information and descriptive engineering
rationale used to describe data anomalies,
provide alternative data, or provide an
acceptable basis for obtaining deviations
from QTG validation requirements.
End Information
lllllllllllllllllllll
BILLING CODE 4910–13–P
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lllllllllllllllllllll
Begin Information
13. Acceptance Guidelines for Alternative
Engines Data
a. Background
(1) For a new airplane type, the majority
of flight validation data are collected on the
first airplane configuration with a ‘‘baseline’’
engine type. These data are then used to
validate all flight simulators representing that
airplane type.
(2) Additional flight test validation data
may be needed for flight simulators
representing an airplane with engines of a
different type than the baseline, or for
engines with thrust rating that is different
from previously validated configurations.
(3) When a flight simulator with alternate
engines is to be qualified, the QTG should
contain tests against flight test validation
data for selected cases where engine
differences are expected to be significant.
b. Approval Guidelines for Validating
Alternate Engine Applications.
(1) The following guidelines apply to flight
simulators representing airplanes with
alternate engine applications or with more
than one engine type or thrust rating.
(2) Validation tests can be segmented into
two groups, those that are dependent on
engine type or thrust rating and those that are
not.
(3) For tests that are independent of engine
type or thrust rating, the QTG can be based
on validation data from any engine
application. Tests in this category should be
designated as independent of engine type or
thrust rating.
(4) For tests that are affected by engine
type, the QTG should contain selected
engine-specific flight test data sufficient to
validate that particular airplane-engine
configuration. These effects may be due to
engine dynamic characteristics, thrust levels
or engine-related airplane configuration
changes. This category is primarily
characterized by variations between different
engine manufacturers’ products, but also
includes differences due to significant engine
design changes from a previously flightvalidated configuration within a single
engine type. See Table A2D, Alternate Engine
Validation Flight Tests in this section for a
list of acceptable tests.
(5) The validation data should be based on
flight test data, except where other data are
specifically allowed. If certification of the
flight characteristics of the airplane with a
new thrust rating (regardless of percentage
change) does require certification flight
testing with a comprehensive stability and
control flight instrumentation package, then
the conditions described in Table A2D in this
section should be obtained from flight testing
and presented in the QTG. Flight test data,
other than throttle calibration data, are not
required if the new thrust rating is certified
on the airplane without need for a
comprehensive stability and control flight
instrumentation package.
(6) As a supplement to the engine-specific
flight tests listed in Table A2D and baseline
engine-independent tests, additional enginespecific engineering validation data should
be provided in the QTG, as appropriate, to
facilitate running the entire QTG with the
alternate engine configuration. The sponsor
and the NSPM should agree in advance on
the specific validation tests to be supported
by engineering simulation data.
(7) A matrix or VDR should be provided
with the QTG indicating the appropriate
validation data source for each test.
(8) The flight test conditions in Table A2D
are appropriate and should be sufficient to
validate implementation of alternate engines
in a flight simulator.
End Information
lllllllllllllllllllll
Begin QPS Requirement
c. Test Requirements
(1) The QTG must contain selected enginespecific flight test data sufficient to validate
the alternative thrust level when:
(a) the engine type is the same, but the
thrust rating exceeds that of a previously
flight-test validated configuration by five
percent (5%) or more; or
(b) the engine type is the same, but the
thrust rating is less than the lowest
previously flight-test validated rating by
fifteen percent (15%) or more.
(2) Flight test data is not required if the
thrust increase is greater than 5%, but flight
tests have confirmed that the thrust increase
does not change the airplane’s flight
characteristics.
(3) Throttle calibration data (i.e.,
commanded power setting parameter versus
throttle position) must be provided to
validate all alternate engine types and engine
thrust ratings that are higher or lower than
a previously validated engine. Data from a
test airplane or engineering test bench with
the correct engine controller (both hardware
and software) are required.
End QPS Requirement
lllllllllllllllllllll
Begin QPS Requirement
TABLE A2D.—ALTERNATIVE ENGINE VALIDATION FLIGHT TESTS
Test Number
Test description
Alternative
engine type
Alternative
thrust rating 2
1.b.1., 1.b.4. ...........
1.b.2. ......................
1.b.5. ......................
1.b.8. ......................
Normal take-off/ground acceleration time and distance .....................................................
Vmcg, if performed for airplane certification .........................................................................
Engine-out take-off.
Dynamic engine failure after take-off.
Either test may be performed .............................................................................................
Rejected take-off if performed for airplane certification ......................................................
Cruise performance .............................................................................................................
Engine acceleration and deceleration .................................................................................
Throttle calibration 1 .............................................................................................................
Power change dynamics (acceleration) ..............................................................................
Vmca if performed for airplane certification ..........................................................................
Engine inoperative trim .......................................................................................................
Normal landing ....................................................................................................................
X
X
X
X
1.b.7.
1.d.1.
1.f.1.,
2.a.7.
2.c.1.
2.d.1.
2.d.5.
2.e.1.
......................
......................
1.f.2. .............
......................
......................
......................
......................
......................
X
X
X
X
X
X
X
X
X
X
X
X
X
X
1 Must
2 See
be provided for all changes in engine type or thrust rating; see paragraph 12.b.(7).
paragraphs 12.b.(5) through 12.b.(8), for a definition of applicable thrust ratings.
End QPS Requirement
lllllllllllllllllllll
Begin Information
14. Acceptance Guidelines for Alternative
Avionics (Flight-Related Computers and
Controllers)
a. Background
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(1) For a new airplane type, the majority
of flight validation data are collected on the
first airplane configuration with a ‘‘baseline’’
flight-related avionics ship-set; (see
subparagraph b.(2) in this paragraph). These
data are then used to validate all flight
simulators representing that airplane type.
(2) Additional validation data may be
required for flight simulators representing an
airplane with avionics of a different
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hardware design than the baseline, or a
different software revision than previously
validated configurations.
(3) When a flight simulator with additional
or alternate avionics configurations is to be
qualified, the QTG should contain tests
against validation data for selected cases
where avionics differences are expected to be
significant.
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b. Approval Guidelines for Validating
Alternate Avionics
(1) The following guidelines apply to flight
simulators representing airplanes with a
revised avionics configuration, or more than
one avionics configuration.
(2) The baseline validation data should be
based on flight test data, except where other
data are specifically allowed (e.g.,
engineering flight simulator data).
(3) The airplane avionics can be segmented
into two groups, systems or components
whose functional behavior contributes to the
aircraft response presented in the QTG
results, and systems that do not. The
following avionics are examples of
contributory systems for which hardware
design changes or software revisions may
lead to significant differences in the aircraft
response relative to the baseline avionics
configuration: flight control computers and
controllers for engines, autopilot, braking
system, nose wheel steering system, and high
lift system. Related avionics such as stall
warning and augmentation systems should
also be considered.
(4) The acceptability of validation data
used in the QTG for an alternative avionics
fit should be determined as follows:
(a) For changes to an avionics system or
component that do not affect QTG validation
test response, the QTG test can be based on
validation data from the previously validated
avionics configuration.
(b) For an avionics change to a contributory
system, where a specific test is not affected
by the change (e.g., the avionics change is a
Built In Test Equipment (BITE) update or a
modification in a different flight phase), the
QTG test can be based on validation data
from the previously-validated avionics
configuration. The QTG should include
authoritative justification (e.g., from the
airplane manufacturer or system supplier)
that this avionics change does not affect the
test.
(c) For an avionics change to a contributory
system, the QTG may be based on validation
data from the previously-validated avionics
configuration if no new functionality is
added and the impact of the avionics change
on the airplane response is based on
acceptable aeronautical principles with
proven success history and valid outcomes.
This should be supplemented with avionicsspecific validation data from the airplane
manufacturer’s engineering simulation,
generated with the revised avionics
configuration. The QTG should also include
an explanation of the nature of the change
and its effect on the airplane response.
(d) For an avionics change to a
contributory system that significantly affects
some tests in the QTG or where new
functionality is added, the QTG should be
based on validation data from the previously
validated avionics configuration and
supplemental avionics-specific flight test
data sufficient to validate the alternate
avionics revision. Additional flight test
validation data may not be needed if the
avionics changes were certified without the
need for testing with a comprehensive flight
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instrumentation package. The airplane
manufacturer should coordinate flight
simulator data requirements, in advance with
the NSPM.
(5) A matrix or ‘‘roadmap’’ should be
provided with the QTG indicating the
appropriate validation data source for each
test. The roadmap should include
identification of the revision state of those
contributory avionics systems that could
affect specific test responses if changed.
15. Transport Delay Testing
a. This paragraph explains how to
determine the introduced transport delay
through the flight simulator system so that it
does not exceed a specific time delay. The
transport delay should be measured from
control inputs through the interface, through
each of the host computer modules and back
through the interface to motion, flight
instrument, and visual systems. The
transport delay should not exceed the
maximum allowable interval.
b. Four specific examples of transport
delay are:
(1) Simulation of classic non-computer
controlled airplanes;
(2) Simulation of computer controlled
airplanes using real airplane black boxes;
(3) Simulation of computer controlled
airplanes using software emulation of
airplane boxes;
(4) Simulation using software avionics or
re-hosted instruments.
c. Figure A2C illustrates the total transport
delay for a non-computer-controlled airplane
or the classic transport delay test. Since there
are no airplane-induced delays for this case,
the total transport delay is equivalent to the
introduced delay.
d. Figure A2D illustrates the transport
delay testing method using the real airplane
controller system.
e. To obtain the induced transport delay for
the motion, instrument and visual signal, the
delay induced by the airplane controller
should be subtracted from the total transport
delay. This difference represents the
introduced delay and should not exceed the
standards prescribed in Table A1A.
f. Introduced transport delay is measured
from the flight deck control input to the
reaction of the instruments and motion and
visual systems (See Figure A2C).
g. The control input may also be
introduced after the airplane controller
system and the introduced transport delay
measured directly from the control input to
the reaction of the instruments, and
simulator motion and visual systems (See
Figure A2D).
h. Figure A2E illustrates the transport
delay testing method used on a flight
simulator that uses a software emulated
airplane controller system.
i. It is not possible to measure the
introduced transport delay using the
simulated airplane controller system
architecture for the pitch, roll and yaw axes.
Therefore, the signal should be measured
directly from the pilot controller. The flight
simulator manufacturer should measure the
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total transport delay and subtract the
inherent delay of the actual airplane
components because the real airplane
controller system has an inherent delay
provided by the airplane manufacturer. The
flight simulator manufacturer should ensure
that the introduced delay does not exceed the
standards prescribed in Table A1A.
j. Special measurements for instrument
signals for flight simulators using a real
airplane instrument display system instead of
a simulated or re-hosted display. For flight
instrument systems, the total transport delay
should be measured and the inherent delay
of the actual airplane components subtracted
to ensure that the introduced delay does not
exceed the standards prescribed in Table
A1A.
(1) Figure A2FA illustrates the transport
delay procedure without airplane display
simulation. The introduced delay consists of
the delay between the control movement and
the instrument change on the data bus.
(2) Figure A2FB illustrates the modified
testing method required to measure
introduced delay due to software avionics or
re-hosted instruments. The total simulated
instrument transport delay is measured and
the airplane delay should be subtracted from
this total. This difference represents the
introduced delay and should not exceed the
standards prescribed in Table A1A. The
inherent delay of the airplane between the
data bus and the displays is indicated in
figure A2FA. The display manufacturer
should provide this delay time.
k. Recorded signals. The signals recorded
to conduct the transport delay calculations
should be explained on a schematic block
diagram. The flight simulator manufacturer
should also provide an explanation of why
each signal was selected and how they relate
to the above descriptions.
l. Interpretation of results. Flight simulator
results vary over time from test to test due
to ‘‘sampling uncertainty.’’ All flight
simulators run at a specific rate where all
modules are executed sequentially in the
host computer. The flight controls input can
occur at any time in the iteration, but these
data will not be processed before the start of
the new iteration. For example, a flight
simulator running at 60 Hz may have a
difference of as much as 16.67 msec between
test results. This does not mean that the test
has failed. Instead, the difference is
attributed to variations in input processing.
In some conditions, the host simulator and
the visual system do not run at the same
iteration rate, so the output of the host
computer to the visual system will not
always be synchronized.
m. The transport delay test should account
for both daylight and night modes of
operation of the visual system. In both cases,
the tolerances prescribed in Table A1A must
be met and the motion response should occur
before the end of the first video scan
containing new information.
BILLING CODE 4910–13–P
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BILLING CODE 4910–13–C
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Begin Information
16. Continuing Qualification Evaluations—
Validation Test Data Presentation
a. Background
(1) The MQTG is created during the initial
evaluation of a flight simulator. This is the
master document, as amended, to which
flight simulator continuing qualification
evaluation test results are compared.
(2) The currently accepted method of
presenting continuing qualification
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evaluation test results is to provide flight
simulator results over-plotted with reference
data. Test results are carefully reviewed to
determine if the test is within the specified
tolerances. This can be a time consuming
process, particularly when reference data
exhibits rapid variations or an apparent
anomaly requiring engineering judgment in
the application of the tolerances. In these
cases, the solution is to compare the results
to the MQTG. The ontinuing qualification
results are compared to the results in the
MQTG for acceptance. The flight simulator
operator and the NSPM should look for any
change in the flight simulator performance
since initial qualification.
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b. Continuing Qualification Evaluation
Test Results Presentation
(1) Flight simulator operators are
encouraged to over-plot continuing
qualification validation test results with
MQTG flight simulator results recorded
during the initial evaluation and as amended.
Any change in a validation test will be
readily apparent. In addition to plotting
continuing qualification validation test and
MQTG results, operators may elect to plot
reference data as well.
(2) There are no suggested tolerances
between flight simulator continuing
qualification and MQTG validation test
results. Investigation of any discrepancy
between the MQTG and continuing
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qualification flight simulator performance is
left to the discretion of the flight simulator
operator and the NSPM.
(3) Differences between the two sets of
results, other than variations attributable to
repeatability issues that cannot be explained,
should be investigated.
(4) The flight simulator should retain the
ability to over-plot both automatic and
manual validation test results with reference
data.
End Information
lllllllllllllllllllll
Begin QPS Requirements
17. Alternative Data Sources, Procedures,
and Instrumentation: Level A and Level B
Simulators Only
a. Sponsors are not required to use the
alternative data sources, procedures, and
instrumentation. However, any sponsor
choosing to use alternative sources must
comply with the requirements in Table A2E.
End QPS Requirements
lllllllllllllllllllll
Begin Information
b. It has become standard practice for
experienced simulator manufacturers to use
modeling techniques to establish data bases
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.
(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.
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
(Table A2E) 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).
i. Synchronized video for the use of
alternative data sources, procedures, and
instrumentation should have:
(1) Sufficient resolution to allow
magnification of the display to make
appropriate measurement and comparisons;
and
(2) Sufficient size and incremental marking
to allow similar measurement and
comparison. The detail provided by the video
should provide sufficient clarity and
accuracy to measure the necessary
parameter(s) to at least 1⁄2 of the tolerance
authorized for the specific test being
conducted and allow an integration of the
parameter(s) in question to obtain a rate of
change.
End Information
lllllllllllllllllllll
TABLE A2E.—ALTERNATIVE DATA SOURCES, PROCEDURES, AND INSTRUMENTATION
<<>>
Table of objective tests
Sim level
Test reference number and title
A
B
Alternative data sources, procedures, and instrumentation
Notes and reminders
The standards in this table are required if the data gathering methods described in paragraph 9 of Appendix A are not used.
1.a.1. Performance. Taxi. Minimum
Radius turn.
X
1.b.1. Performance. Takeoff. Ground
Acceleration Time and Distance.
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X
TIR, AFM, or Design data may be used ..............
X
1.a.2. Performance. Taxi Rate of
Turn vs. Nosewheel Steering
Angle.
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.
Preliminary certification data may be used. Data
may be acquired by using a stop watch, 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.
X
PO 00000
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A single procedure may not be adequate for all airplane steering systems, therefore appropriate measurement procedures must be devised and proposed for NSPM
concurrence.
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59665
TABLE A2E.—ALTERNATIVE DATA SOURCES, PROCEDURES, AND INSTRUMENTATION—Continued
<<>>
Table of objective tests
Sim level
Alternative data sources, procedures, and instrumentation
Notes and reminders
X
Data may be acquired by using an inertial measurement system and a synchronized video of
calibrated airplane instruments and force/position measurements of flight deck controls.
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.
X
X
Data may be acquired by using an inertial measurement system and a synchronized video of
calibrated airplane instruments and the force/
position measurements of flight deck controls.
X
X
1.b.5. Performance. Takeoff. Critical
Engine Failure during Takeoff.
X
X
1.b.6. Performance. Takeoff. Crosswind Takeoff.
X
X
1.b.7. Performance.
jected Takeoff.
Re-
X
X
1.c.1. Performance. Climb. Normal
Climb all engines operating.
X
X
1.c.2. Performance. Climb. One Engine Inoperative Climb.
X
X
1.c.4. Performance. Climb. One Engine Inoperative Approach Climb
(if operations in icing conditions
are authorized).
1.d.1. Cruise/Descent. Level flight
acceleration.
X
X
Data may be acquired by using an inertial measurement system and a synchronized video of
calibrated airplane instruments and force/position measurements of flight deck controls.
AOA can be calculated from pitch attitude and
flight path.
Data may be acquired by using an inertial measurement system and a synchronized video of
calibrated airplane instruments and force/position measurements of flight deck controls.
Data may be acquired by using an inertial measurement system and a synchronized video of
calibrated airplane instruments and force/position measurements of flight deck controls.
Data may be acquired with a synchronized video
of calibrated airplane instruments, thrust lever
position, engine parameters, and distance
(e.g., runway markers). A stop watch is required.
Data may be acquired with a synchronized video
of calibrated airplane instruments and engine
power throughout the climb range.
Data may be acquired with a synchronized video
of calibrated airplane instruments and engine
power throughout the climb range.
Data may be acquired with a synchronized video
of calibrated airplane instruments and engine
power throughout the climb range.
X
X
1.d.2. Cruise/Descent. Level flight
deceleration.
X
X
1.d.4. Cruise/Descent. Idle descent ..
X
X
1.d.5. Cruise/Descent.
Descent.
Emergency
X
X
1.e.1. Performance. Stopping. Deceleration time and distance, using
manual application of wheel
brakes and no reverse thrust on a
dry runway.
1.e.2. Performance. Ground. Deceleration Time and Distance, using
reverse thrust and no wheel
brakes.
X
X
X
X
1.f.1. Performance. Engines. Acceleration.
X
X
Test reference number and title
A
B
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.
1.b.3. Performance. Takeoff. Minimum Unstick Speed (Vmu) or
equivalent test to demonstrate
early rotation takeoff characteristics.
1.b.4. Performance. Takeoff. Normal
Takeoff.
X
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Record airplane dynamic response
to engine failure and control inputs
required to correct flight path.
The ‘‘1:7 law’’ to 100 feet (30 meters) is an acceptable wind profile.
Data may be acquired with a synchronized video
of calibrated airplane instruments, thrust lever
position, engine parameters, and elapsed time.
Data may be acquired with a synchronized video
of calibrated airplane instruments, thrust lever
position, engine parameters, and elapsed time.
Data may be acquired with a synchronized video
of calibrated airplane instruments, thrust lever
position, engine parameters, and elapsed time.
Data may be acquired with a synchronized video
of calibrated airplane instruments, thrust lever
position, engine parameters, and elapsed time.
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.
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 pertinent parameters of engine power.
Data may be acquired with a synchronized video
recording of engine instruments and throttle
position.
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TABLE A2E.—ALTERNATIVE DATA SOURCES, PROCEDURES, AND INSTRUMENTATION—Continued
<<>>
Table of objective tests
Sim level
Test reference number and title
A
B
1.f.2. Performance. Engines. Deceleration.
X
X
2.a.1.a. Handling Qualities. Static
Control Checks. Pitch Controller
Position vs. Force and Surface Position Calibration.
X
X
2.a.2.a. Handling Qualities. Static
Control Checks. Roll Controller
Position vs. Force and Surface Position Calibration.
X
X
2.a.3.a. Handling Qualities. Static
Control Checks. Rudder Pedal Position vs. Force and Surface Position Calibration.
X
X
2.a.4. Handling Qualities. Static Control Checks. Nosewheel Steering
Controller Force and Position.
X
X
2.a.5. Handling Qualities. Static Control Checks. Rudder Pedal Steering Calibration.
X
X
2.a.6. Handling Qualities. Static Control Checks. Pitch Trim Indicator
vs. Surface Position Calibration.
2.a.7. Handling qualities. Static control tests. Pitch trim rate.
X
X
X
X
2.a.8. Handling Qualities. Static Control tests. Alignment of Flight deck
Throttle Lever Angle vs. Selected
engine parameter.
X
X
2.a.9. Handling qualities. Static control tests. Brake pedal position vs.
force and brake system pressure
calibration.
X
X
2.c.1. Handling qualities. Longitudinal
control tests. Power change dynamics.
X
X
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Alternative data sources, procedures, and instrumentation
Data may be acquired with a synchronized video
recording of engine instruments and throttle
position.
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.
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.
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.
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.
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.
Data may be acquired through calculations.
Data may be acquired by using a synchronized
video of pitch trim indication and elapsed time
through range of trim indication.
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.
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.
Data may be acquired by using an inertial measurement system and a synchronized video of
calibrated airplane instruments and throttle position.
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Notes and reminders
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
59667
TABLE A2E.—ALTERNATIVE DATA SOURCES, PROCEDURES, AND INSTRUMENTATION—Continued
<<>>
Table of objective tests
Sim level
Test reference number and title
A
B
2.c.2. Handling qualities. Longitudinal
control tests. Flap/slat change dynamics.
X
X
2.c.3. Handling qualities. Longitudinal
control tests. Spoiler/speedbrake
change dynamics.
X
X
2.c.4. Handling qualities. Longitudinal
control tests. Gear change dynamics.
X
X
2.c.5. Handling qualities. Longitudinal
control tests. Longitudinal trim.
X
X
2.c.6. Handling qualities. Longitudinal
control tests. Longitudinal maneuvering stability (stick force/g).
X
X
2.c.7. Handling qualities. Longitudinal
control tests. Longitudinal static
stability.
2.c.8. Handling qualities. Longitudinal
control tests. Stall characteristics.
X
X
X
X
2.c.9. Handling qualities. Longitudinal
control tests. Phugoid dynamics.
X
X
2.c.10. Handling qualities. Longitudinal control tests. Short period dynamics.
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.
2.d.2. Handling qualities. Lateral directional tests. Roll response (rate).
X
X
X
X
X
2.d.3. Handling qualities. Lateral directional tests. Roll response to
flight deck roll controller step input.
X
X
2.d.4. Handling qualities. Lateral directional tests. Spiral stability.
X
X
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Alternative data sources, procedures, and instrumentation
Data may be acquired by using an inertial measurement system and a synchronized video of
calibrated airplane instruments and flap/slat
position.
Data may be acquired by using an inertial measurement system and a synchronized video of
calibrated airplane instruments and spoiler/
speedbrake position.
Data may be acquired by using an inertial measurement system and a synchronized video of
calibrated airplane instruments and gear position.
Data may be acquired through use of an inertial
measurement system and a synchronized
video of flight deck controls position (previously calibrated to show related surface position) and the engine instrument readings.
Data may be acquired through the use of an inertial measurement system and a synchronized video of calibrated airplane instruments; a temporary, high resolution bank
angle scale affixed to the attitude indicator;
and a wheel and column force measurement
indication.
Data may be acquired through the use of a synchronized video of airplane flight instruments
and a hand held force gauge.
Data may be acquired through a synchronized
video recording of a stop watch and calibrated
airplane airspeed indicator. Hand-record the
flight conditions and airplane configuration.
Data may be acquired by using an inertial measurement system and a synchronized video of
calibrated airplane instruments and force/position measurements of flight deck controls.
Data may be acquired by using an inertial measurement system and a synchronized video of
calibrated airplane instruments and force/position measurements of flight deck controls.
Data may be acquired by using an inertial measurement system and a synchronized video of
calibrated airplane instruments and force/position measurements of flight deck controls.
Data may be acquired by using an inertial measurement system and a synchronized video of
calibrated airplane instruments and force/position measurements of flight deck lateral controls.
Data may be acquired by using an inertial measurement system and a synchronized video of
calibrated airplane instruments and force/position measurements of flight deck lateral controls.
Data may be acquired by using an inertial measurement system and a synchronized video of
calibrated airplane instruments; force/position
measurements of flight deck controls; and a
stop watch.
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Notes and reminders
Airspeeds may be cross checked
with those in the TIR and AFM.
May be combined with step input of
flight deck roll controller test,
2.d.3.
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TABLE A2E.—ALTERNATIVE DATA SOURCES, PROCEDURES, AND INSTRUMENTATION—Continued
<<>>
Table of objective tests
Sim level
Test reference number and title
A
B
2.d.5. Handling qualities. Lateral directional tests. Engine inoperative
trim.
X
X
2.d.6. Handling qualities. Lateral directional tests. Rudder response.
X
X
2.d.7. Handling qualities. Lateral directional tests. Dutch roll (yaw
damper OFF).
X
X
2.d.8. Handling qualities. Lateral directional tests. Steady state sideslip.
X
X
2.e.1. Handling qualities. Landings.
Normal landing.
X
2.e.3. Handling qualities. Landings.
Crosswind landing.
X
2.e.4. Handling qualities. Landings.
One engine inoperative landing.
X
2.e.5. Handling qualities. Landings.
Autopilot landing (if applicable).
X
2.e.6. Handling qualities. Landings.
All engines operating, autopilot, go
around.
X
2.e.7. Handling qualities. Landings.
One engine inoperative go around.
X
2.e.8. Handling qualities. Landings.
Directional control (rudder effectiveness with symmetric thrust).
X
2.e.9. Handling qualities. Landings.
Directional control (rudder effectiveness with asymmetric reverse
thrust).
X
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Alternative data sources, procedures, and instrumentation
Notes and reminders
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 calibrated airplane instruments and force/position measurements of flight deck controls.
Data may be acquired by using an inertial measurement system and a synchronized video of
calibrated airplane instruments and force/position measurements of rudder pedals.
Data may be acquired by using an inertial measurement system and a synchronized video of
calibrated airplane instruments and force/position measurements of flight deck controls.
Data may be acquired by using an inertial measurement system and a synchronized video of
calibrated airplane instruments and force/position measurements of flight deck controls.
Ground track and wind corrected heading may
be used for sideslip angle.
Data may be acquired by using an inertial measurement system and a synchronized video of
calibrated airplane instruments and force/position measurements of flight deck controls.
Data may be acquired by using an inertial measurement system and a synchronized video of
calibrated airplane instruments and force/position measurements of flight deck controls.
Data may be acquired by using an inertial measurement system and a synchronized video of
calibrated airplane instruments and the force/
position measurements of flight deck controls.
Normal and lateral accelerations may be recorded in lieu of AOA and sideslip.
Data may be acquired by using an inertial measurement system and a synchronized video of
calibrated airplane instruments and force/position measurements of flight deck controls. Normal and lateral accelerations may be recorded
in lieu of AOA and sideslip.
Data may be acquired by using an inertial measurement system and a synchronized video of
calibrated airplane instruments and force/position measurements of flight deck controls. Normal and lateral accelerations may be recorded
in lieu of AOA and sideslip.
Data may be acquired by using an inertial measurement system and a synchronized video of
calibrated airplane instruments and force/position measurements of flight deck controls. Normal and lateral accelerations may be recorded
in lieu of AOA and sideslip.
Data may be acquired by using an inertial measurement system and a synchronized video of
calibrated airplane instruments and force/position measurements of flight deck controls. Normal and lateral accelerations may be recorded
in lieu of AOA and sideslip.
Data may be acquired by using an inertial measurement system and a synchronized video of
calibrated airplane instruments and force/position measurements of flight deck controls. Normal and lateral accelerations may be recorded
in lieu of AOA and sideslip.
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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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
59669
TABLE A2E.—ALTERNATIVE DATA SOURCES, PROCEDURES, AND INSTRUMENTATION—Continued
<<>>
Table of objective tests
Sim level
Test reference number and title
A
2.f. Handling qualities. Ground effect.
Test to demonstrate ground effect.
X
End Information
Attachment 3 to Appendix A to Part 60—
Simulator Subjective Evaluation
lllllllllllllllllllll
Begin QPS Requirements
1. Requirements
a. Except for special use visual scenes and
airport models described below, all visual
scenes and airport models required by this
part must be representations of real-world,
operational airports or representations of
fictional airports and must meet the
requirements set out in Tables A3B and A3C
of this attachment, as appropriate.
b. If fictional airports are used, the sponsor
must ensure that navigational aids and all
appropriate maps, charts, and other
navigational reference material for the
fictional airports (and surrounding areas as
necessary) are compatible, complete, and
accurate with respect to the visual
presentation and scene content of the visual
model of this fictional airport. An SOC must
be submitted that addresses navigation aid
installation and performance and other
criteria (including obstruction clearance
protection) for all instrument approaches to
the fictional airports that are available in the
simulator. The SOC must reference and
account for information in the terminal
instrument procedures manual and the
construction and availability of the required
maps, charts, and other navigational material.
This material must be clearly marked ‘‘for
training purposes only.’’
c. When the simulator is being used by an
instructor or evaluator for purposes of
training, checking, or testing under this
chapter, only visual scenes and airport
models classified as Class I, Class II, or Class
III may be available to the instructor or
evaluator. The classifications are as follows:
(1) Class I (whether modeling real world
airports or fictional airports), for those visual
scenes and airport models used for simulator
qualification at a specified level. These visual
scenes and airport models must meet the
minimum requirements in Table A3B of this
attachment, be evaluated by the NSPM, be
listed on the Statement of Qualification
(SOQ), and be available for use at the
simulator IOS.
(2) Class II (whether modeling real world
airports or fictional airports), for those visual
scenes and airport models that are in excess
of those used for simulator qualification at a
specified level. These visual scenes and
airport models must meet the minimum
requirements set out in Table A3C of this
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B
Alternative data sources, procedures, and instrumentation
Data may be acquired by using calibrated airplane instruments, an inertial measurement
system, and a synchronized video of calibrated airplane instruments and force/position
measurements of flight deck controls.
attachment. These visual scenes and airport
models may be made available on the
simulator IOS without further involvement of
the NSPM or the TPAA.
(3) For an interim period ending [date 2
years after the effective date of the final rule],
Class III visual scenes and airport models
(whether modeling real world airports,
generic airports, or fictional airports) may be
approved for specific purposes by the TPAA
or a foreign regulatory authority for a foreign
user of the device. Examples of approved
activities include specific airport or runway
qualification, very low visibility operations
training, including Surface Movement
Guidance System (SMGS) operations, or use
of a specific airport visual model aligned
with an instrument procedure for another
airport for instrument training. At the end of
the interim period, all Class III visual scenes
and airport models must be classified as
either a Class I or a Class II visual scene or
airport model or be removed from availability
at the simulator IOS. However, Class III
visual scenes and airport models may
continue to be used after the end of the
interim period if they are part of a training
program specifically approved by the TPAA
or other regulatory authority that uses a task
and capability analysis as the basis for
approval of this specific media element, (i.e.,
the specific scene or model selected for use
in that program).
d. When a person sponsors an FSTD
maintained by a person other than a U.S.
certificate holder, the sponsor is accountable
for that FSTD originally meeting, and
continuing to meet, the criteria under which
it was originally qualified and the
appropriate Part 60 criteria, including the
visual scenes and airport models that may be
used by instructors or evaluators for purposes
of training, checking, or testing under this
chapter.
e. Neither Class II nor Class III airport
visual models are required to appear on the
SOQ. However, the sponsor is responsible for
ensuring the FSTD originally meets, and
continues to meet, the visual scene and
airport model requirements for Class II or
Class III visual scenes and airport models
that may be used by instructors or evaluators
for training, checking, or testing under this
chapter.
f. When the visual scenes and airport
models represent real world airports and a
permanent change is made to that real world
airport (e.g., a new runway, an extended
taxiway, a new lighting system, a runway
closure) without a written extension grant
from the NSPM (described below), an update
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Frm 00070
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to that visual scene or airport model must be
made in accordance with the following time
limits:
(1) For a new airport runway, a runway
extension, a new airport taxiway, a taxiway
extension, or a runway/taxiway closure—
within 60 days of the opening for use of the
new airport runway, runway extension, new
airport taxiway, or taxiway extension; or
within 60 days of the closure of the runway
or taxiway.
(2) For a new or modified approach light
system—within 30 days of the activation of
the new or modified approach light system.
(3) For other facility or structural changes
on the airport (e.g., new terminal, relocation
of Air Traffic Control Tower)—within 6
months of the opening of the new or changed
facility or structure.
g. If a sponsor desires an extension to the
time limit for an update to a visual scene or
airport model, the sponsor must provide a
written extension request to the POI/TCPM
stating the reason for the update delay and
a proposed completion date. A copy of this
request must also be sent to the NSPM. The
sponsor will forward a copy of the POI/
TCPM’s response to the NSPM. If the POI/
TCPM has granted an extension, the NSPM
will issue an extension authorization, not to
exceed an additional 12 months.
End QPS Requirements
lllllllllllllllllllll
Begin Information
2. Discussion
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
operation of the simulator controls,
instruments, and systems. The items listed in
the following Tables are for simulator
evaluation purposes only. They may 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.
b. The tests in Table A3A, Operations
Tasks, in this attachment, address pilot
functions, including maneuvers and
procedures (called flight tasks), and are
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
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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. The FAA intends to allow the use of
Class III visual scenes and airport models on
a limited basis when the sponsor provides
the TPAA (or other regulatory authority) an
appropriate analysis of the skills, knowledge,
and abilities (SKAs) necessary for competent
performance of the tasks in which this
particular media element is used. The
analysis should describe the ability of the
FSTD/visual media to provide an adequate
environment in which the required SKAs
may be satisfactorily performed and learned.
The analysis should also include the specific
media element, such as the visual scene or
airport model. Additional sources of
information on the conduct of task and
capability analysis may be found on the
FAA’s Advanced Qualification Program
(AQP) Web site at: https://www.faa.gov/
education_research/training/aqp/.
h. Previously qualified simulators with
certain early generation Computer Generated
Image (CGI) visual systems, are limited by 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) 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).
End Information
lllllllllllllllllllll
TABLE A3A.—FUNCTIONS AND SUBJECTIVE TESTS
<<>>
Simulator level
Number
Operation tasks
A
B
C
D
Tasks in this table are subject to evaluation if appropriate for the airplane simulated as indicated in the SOQ Configuration List 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. ..............................
Surface Operations (Pre-Take-Off)
2.a. ...................
X
X
X
X
Engine Start
2.a.1. .........
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
X
X
X
X
2.b. ...................
Pushback/Powerback
2.c. ....................
Taxi
2.c.1. .........
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TABLE A3A.—FUNCTIONS AND SUBJECTIVE TESTS—Continued
<<>>
Simulator level
Number
Operation tasks
A
B
C
D
2.c.2. .........
Power lever friction ....................................................................................................................................
X
X
X
X
2.c.3. .........
Ground handling ........................................................................................................................................
X
X
X
X
2.c.4. .........
Nose wheel scuffing ...................................................................................................................................
X
X
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
3.b.8. .........
Propulsion System Malfunction: ................................................................................................................
(i) Prior to V1 decision speed
(ii) Between V1 and Vr (rotation speed)
(iii) Between Vr and 500 feet above ground level
X
X
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
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TABLE A3A.—FUNCTIONS AND SUBJECTIVE TESTS—Continued
<<>>
Simulator level
Number
Operation tasks
A
6. ..............................
B
C
D
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
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. ..............................
8.a. ...................
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.
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 ...
X
X
X
X
A. With cross-wind (maximum demonstrated) ...................................................................................
X
X
X
X
B. With windshear ...............................................................................................................................
X
X
X
X
(vi) Autopilot/autothrottle coupled 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
8.a.3. .........
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TABLE A3A.—FUNCTIONS AND SUBJECTIVE TESTS—Continued
<<>>
Simulator level
Number
Operation tasks
A
D
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
(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) ......................................................
X
X
X
X
A. With generator failure ............................................................................................................................
X
X
X
X
B. With 10 knot tail wind ............................................................................................................................
X
X
X
X
C. With 10 knot crosswind .........................................................................................................................
8.b. ...................
C
(iv) Category II published approach (auto-coupled, autothrottle) ..............................................................
8.a.4. .........
B
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.
9.a. ...................
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
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TABLE A3A.—FUNCTIONS AND SUBJECTIVE TESTS—Continued
<<>>
Simulator level
Number
Operation tasks
A
9.m. ..................
10. ............................
Approach procedures with vertical guidance (APV), e.g., SBAS ..............................................................
B
C
D
X
X
X
X
Missed Approach
10.a. .................
All engines .................................................................................................................................................
X
X
X
X
10.b. .................
One or more engine(s) out ........................................................................................................................
X
X
X
X
10.c. ..................
With flight control system failures, reconfiguration modes, manual reversion and associated handling
X
X
X
X
11. ............................
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, patchy wet, wet on rubber residue, and patchy 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.
12.a.1. .......
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
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE A3A.—FUNCTIONS AND SUBJECTIVE TESTS—Continued
<<>>
Simulator level
Number
Operation tasks
A
12.a.22. .....
12.b. .................
Automatic landing aids ..............................................................................................................................
B
C
D
X
X
X
X
X
X
X
X
Airborne procedures
12.b.1. .......
Holding .......................................................................................................................................................
12.b.2. .......
Air hazard avoidance. (Traffic, Weather) ...................................................................................................
X
X
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.—FUNCTIONS AND SUBJECTIVE TESTS—VISUAL SCENE CONTENT FOR QUALIFICATION AT THE STATED LEVEL
Simulator level
Number
Class I visual scenes/visual models
A
B
C
D
This table specifies the minimum airport visual model content and functionality to qualify a simulator at the indicated level. This table applies
only to the airport scenes required for simulator qualification; i.e., one airport scene for Level A and Level B simulators; three airport scenes
for Level C and Level D simulators.
Begin QPS Requirements
1. ...................
Functional test content requirements for Level A and Level B simulators. The following is the minimum airport model content requirement to satisfy visual capability tests, and provides suitable visual cues to allow completion of all functions and subjective tests described in this attachment for simulators at Levels A and B.
1.a. .........
A minimum of one (1) representative airport model. This model identification must be acceptable to the
sponsor’s TPAA, selectable from the IOS, and listed on the Statement of Qualification.
X
X
1.b. .........
The fidelity of the visual scene must be sufficient for the aircrew to visually identify the airport; determine the
position of the simulated airplane within a night visual scene; successfully accomplish take-offs, approaches, and landings; and maneuver around the airport on the ground as necessary.
X
X
1.c. .........
Runways: ..............................................................................................................................................................
X
X
1.c.1.
Visible runway number .........................................................................................................................................
X
X
1.c.2.
Runway threshold elevations and locations must be modeled to provide sufficient correlation with airplane
systems (e.g., altimeter).
X
X
1.c.3.
Runway surface and markings .............................................................................................................................
X
X
1.c.4.
Lighting for the runway in use including runway edge and centerline .................................................................
X
X
1.c.5.
Lighting, visual approach aid and approach lighting of appropriate colors .........................................................
X
X
1.c.6.
Representative taxiway lights ...............................................................................................................................
X
X
2. ...................
Functional test content requirements for Level C and Level D simulators. The following is the minimum airport model content requirement to satisfy visual capability tests, and provide suitable visual cues to allow completion of all functions and subjective tests described in this attachment for simulators at Levels C and D. Not all of the elements described in this section
must be found in a single airport scene. However, all of the elements described in this section must be found throughout a
combination of the three (3) airport models described in item 2.a.
2.a. .........
A minimum of three (3) representative airport models. The model identifications must be acceptable to the
sponsor’s TPAA, selectable from the IOS, and listed on the Statement of Qualification.
X
X
2.a.1.
Night and Twilight (Dusk) scenes required ..........................................................................................................
X
X
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE A3B.—FUNCTIONS AND SUBJECTIVE TESTS—VISUAL SCENE CONTENT FOR QUALIFICATION AT THE STATED
LEVEL—Continued
Simulator level
Number
Class I visual scenes/visual models
A
B
C
D
2.a.2.
Daylight scenes required ......................................................................................................................................
2.b. .........
Two parallel runways and one crossing runway, displayed simultaneously; at least two of the runways must
be able to be lighted fully and simultaneously.
NOTE: This requirement may be demonstrated at either a fictional airport or a real-world airport. However, if a fictional airport is used, this airport must be listed on the Statement of Qualification.
X
X
2.c. .........
Runway threshold elevations and locations must be modeled to provide sufficient correlation with airplane
systems (e.g., HGS, GPS, altimeter); slopes in runways, taxiways, and ramp areas must not cause distracting or unrealistic effects, including pilot eye-point height variation.
X
X
2.d. .........
Representative airport buildings, structures and lighting .....................................................................................
X
X
2.e. .........
At least one useable gate, at the appropriate height (required only for those airplanes that typically operate
from terminal gates).
X
X
2.f. ..........
Representative moving and static gate clutter (e.g., other airplane, power carts, tugs, fuel trucks, and additional gates).
X
X
2.g. .........
Representative gate/apron markings (e.g., hazard markings, lead-in lines, gate numbering) and lighting ........
X
X
2.h. .........
Representative runway markings, lighting, and signage, including a windsock that gives appropriate wind
cues.
X
X
2.i. ..........
Representative taxiway markings, lighting, and signage necessary for position identification, and to taxi from
parking to a designated runway and return to parking.
X
X
2.j. ..........
A low visibility taxi route (e.g., Surface Movement Guidance Control System, follow-me truck, daylight taxi
lights) must also be demonstrated.
2.k. .........
Representative moving and static ground traffic (e.g., vehicular and airplane), including the capability to
present ground hazards (e.g., another airplane crossing the active runway).
X
X
2.l. ..........
Representative moving airborne traffic, including the capability to present air hazards (e.g., airborne traffic
on a possible collision course).
X
X
2.m. ........
Representative depiction of terrain and obstacles as well as significant and identifiable natural and cultural
features, within 25 NM of the reference airport.
X
X
2.n. .........
Appropriate approach lighting systems and airfield lighting for a VFR circuit and landing, non-precision approaches and landings, and Category I, II and III precision approaches and landings.
X
X
2.o. .........
Representative gate docking aids or a marshaller ...............................................................................................
X
X
2.p. .........
Portrayal of physical relationships known to cause landing illusions (e.g., short runways, landing approaches
over water, uphill or downhill runways, rising terrain on the approach path).This requirement may be met
by a Statement of Compliance and Capability (SOC) and a demonstration of two landing illusions. The illusions are not required to be beyond the normal operational capabilities of the airplane being simulated.
The demonstrated illusions must be available to the instructor or check airman at the IOS for training, testing, checking, or experience activities.
X
2.q. .........
Portrayal of runway surface contaminants, including runway lighting reflections when wet and partially obscured lights when snow is present, or suitable alternative effects.
X
3. ...................
X
X
Visual scene management. The following are the minimum visual scene management requirements for simulators at Levels A,
B, C, and D.
3.a. .........
Runway and approach lighting must fade into view in accordance with the environmental conditions set in
the simulator, and the distance from the object.
X
X
X
X
3.b. .........
The direction of strobe lights, approach lights, runway edge lights, visual landing aids, runway centerline
lights, threshold lights, and touchdown zone lights must be replicated.
X
X
X
X
4. ...................
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Visual feature recognition. The following are the minimum distances at which runway features must be visible for simulators at
Levels A, B, C, and D. Distances are measured from runway threshold to an airplane aligned with the runway on an extended 3° glide-slope in simulated meteorological conditions that recreate the minimum distances for visibility. For circling
approaches, all tests apply to the runway used for the initial approach and to the runway of intended landing.
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE A3B.—FUNCTIONS AND SUBJECTIVE TESTS—VISUAL SCENE CONTENT FOR QUALIFICATION AT THE STATED
LEVEL—Continued
Simulator level
Number
Class I visual scenes/visual models
A
B
C
D
X
X
X
X
X
X
4.a. .........
Runway definition, strobe lights, approach lights, and runway edge white lights from 5 sm (8 km) of the runway threshold.
4.b. .........
Visual Approach Aid lights (VASI or PAPI) from 5 sm (8 km) of the runway threshold ......................................
4.c. .........
Visual Approach Aid lights (VASI or PAPI) from 3 sm (5 km) of the runway threshold ......................................
X
X
4.d. .........
Runway centerline lights and taxiway definition from 3 sm (5 km) .....................................................................
X
X
X
X
4.e. .........
Threshold lights and touchdown zone lights from 2 sm (3 km) ...........................................................................
X
X
X
X
4.f. ..........
Runway markings within range of landing lights for night scenes as required by the surface resolution test
on day scenes.
X
X
X
X
4.g. .........
For circling approaches, the runway of intended landing and associated lighting should fade into view in a
non-distracting manner.
X
X
X
X
5. ...................
5.a. .........
Airport model content. The following sets out the minimum requirements for what must be provided in an airport visual model
and also identifies the other aspects of the airport environment that must correspond with that model for simulators at Levels A, B, C, and D. For circling approaches, all tests apply to the runway used for the initial approach and to the runway of
intended landing. If all runways in an airport model used to meet the requirements of this attachment are not designated as
‘‘in use,’’ then the ‘‘in use’’ runways must be listed on the Statement of Qualification (e.g., KORD, Rwys 9R, 14L, 22R).
Models of airports with more than one runway must have all significant runways not ‘‘in-use’’ visually depicted for airport
and runway recognition purposes. The use of white or off white light strings that identify the runway threshold, edges, and
ends for twilight and night scenes are acceptable for this requirement. Rectangular surface depictions are acceptable for
daylight scenes. A visual system’s capabilities must be balanced between providing airport models with an accurate representation of the airport and a realistic representation of the surrounding environment.
The surface and markings for each ‘‘in-use’’ runway must include the following:
5.a.1.
Threshold markings ..............................................................................................................................................
X
X
X
X
5.a.2.
Runway numbers ..................................................................................................................................................
X
X
X
X
5.a.3.
Touchdown zone markings ..................................................................................................................................
X
X
X
X
5.a.4.
Fixed distance markings .......................................................................................................................................
X
X
X
X
5.a.5.
Edge markings ......................................................................................................................................................
X
X
X
X
5.a.6.
Centerline stripes ..................................................................................................................................................
X
X
X
X
5.b. .........
5.b.1.
Each runway designated as an ‘‘in-use’’ runway must include the following detail that is either modeled using airport pictures,
construction drawings and maps, U.S. National Imagery and Mapping Agency, or other data, or modeled in accordance with
published regulatory material. Sponsors are not required to provide every detail of a runway, but the detail that is provided
should be correct within reasonable limits
The lighting for each ‘‘in-use’’ runway must include the following:
(i) Threshold lights ................................................................................................................................................
X
X
X
(ii) Edge lights .......................................................................................................................................................
X
X
X
X
(iii) End lights ........................................................................................................................................................
X
X
X
X
(iv) Centerline lights, if appropriate ......................................................................................................................
X
X
X
X
(v) Touchdown zone lights, if appropriate ............................................................................................................
X
X
X
X
(vi) Leadoff lights, if appropriate ...........................................................................................................................
X
X
X
X
(vii) Appropriate visual landing aid(s) for that runway ..........................................................................................
X
X
X
X
(viii) Appropriate approach lighting system for that runway .................................................................................
5.b.2.
X
X
X
X
X
X
X
X
X
The taxiway surface and markings associated with each ‘‘in-use’’ runway must include the following:
(i) Edge .................................................................................................................................................................
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE A3B.—FUNCTIONS AND SUBJECTIVE TESTS—VISUAL SCENE CONTENT FOR QUALIFICATION AT THE STATED
LEVEL—Continued
Simulator level
Number
Class I visual scenes/visual models
A
C
D
(ii) Centerline ........................................................................................................................................................
X
X
X
X
(iii) Runway hold lines ..........................................................................................................................................
X
X
X
X
(iv) ILS critical area marking .................................................................................................................................
X
X
X
X
(i) Edge .................................................................................................................................................................
X
X
X
(ii) Centerline, if appropriate .................................................................................................................................
X
X
X
X
(iii) Runway hold and ILS critical area lights ........................................................................................................
5.b.3.
B
X
X
X
X
The taxiway lighting associated with each ‘‘in-use’’ runway must include the following:
(iv) Edge lights of correct color ............................................................................................................................
5.b.4.
X
Airport signage associated with each ‘‘in-use’’ runway must include the following:
(i) Distance remaining signs, if appropriate ..........................................................................................................
X
X
X
(ii) Signs at intersecting runways and taxiways ...................................................................................................
X
X
X
X
(iii) Signs described in items ‘‘2h’’ and ‘‘2i’’ of this table ......................................................................................
5.b.5.
X
X
X
X
X
X
X
X
X
Required visual model correlation with other aspects of the airport environment simulation:
(i) The airport model must be properly aligned with the navigational aids that are associated with operations
at the runway ‘‘in-use’’.
(ii) The simulation of runway contaminants must be correlated with the displayed runway surface and lighting
where applicable.
6. ...................
X
Correlation with airplane and associated equipment.The following are the minimum correlation comparisons that must be made
for simulators at Levels A, B, C, and D.
6.a. .........
Visual system compatibility with aerodynamic programming ...............................................................................
X
X
X
X
6.b. .........
Visual cues to assess sink rate and depth perception during landings ...............................................................
X
X
X
X
6.c. .........
Accurate portrayal of environment relating to flight simulator attitudes ...............................................................
X
X
X
X
6.d. .........
The visual scene must correlate with integrated airplane systems, where fitted (e.g. terrain, traffic and
weather avoidance systems and Head-up Guidance System (HGS)).
X
X
X
X
6.e. .........
Representative visual effects for each visible, own-ship, airplane external light(s) ............................................
X
X
X
X
6.f. ..........
The effect of rain removal devices .......................................................................................................................
7. ...................
X
Scene quality. The following are the minimum scene quality tests that must be conducted for simulators at Levels A, B, C, and
D.
7.a. .........
Surfaces and textural cues must be free from apparent quantization (aliasing) .................................................
X
X
7.b. .........
System capable of portraying full color realistic textural cues .............................................................................
X
X
7.c. .........
The system light points must be free from distracting jitter, smearing or streaking ............................................
X
X
X
X
7.d. .........
Demonstration of occulting through each channel of the system in an operational scene .................................
X
X
7.e. .........
Demonstration of a minimum of ten levels of occulting through each channel of the system in an operational
scene.
X
X
7.f. ..........
System capable of providing focus effects that simulate rain ..............................................................................
7.g. .........
System capable of providing focus effects that simulate light point perspective growth ....................................
7.h. .........
System capable of six discrete light step controls (0–5) .....................................................................................
8. ...................
VerDate Aug<31>2005
X
X
X
X
X
X
X
Environmental effects. The following are the minimum environmental effects that must be available in simulators at Levels A, B,
C, and D.
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE A3B.—FUNCTIONS AND SUBJECTIVE TESTS—VISUAL SCENE CONTENT FOR QUALIFICATION AT THE STATED
LEVEL—Continued
Simulator level
Number
Class I visual scenes/visual models
A
8.a. .........
8.a.1.
B
C
The displayed scene corresponding to the appropriate surface contaminants and including runway lighting
reflections for wet, partially obscured lights for snow, or alternative effects.
D
X
Special weather representations which include:
(i) The sound, motion and visual effects of light, medium and heavy precipitation near a thunderstorm on
take-off, approach, and landings at and below an altitude of 2,000 ft (600 m) above the airport surface
and within a radius of 10 sm (16 km) from the airport.
X
(ii) One airport with a snow scene to include terrain snow and snow-covered taxiways and runways ..............
X
8.b. .........
In-cloud effects such as variable cloud density, speed cues and ambient changes ...........................................
X
X
8.c. .........
The effect of multiple cloud layers representing few, scattered, broken and overcast conditions giving partial
or complete obstruction of the ground scene.
X
X
8.d. .........
Visibility and RVR measured in terms of distance. Visibility/RVR checked at 2,000 ft (600 m) above the airport and at two heights below 2000ft with at least 500 ft. of separation between the measurements. The
measurements must be taken within a radius of 10 sm (16 km) from the airport.
X
X
8.e. .........
Patchy fog giving the effect of variable RVR .......................................................................................................
8.f. ..........
Effects of fog on airport lighting such as halos and defocus ...............................................................................
X
X
8.g. .........
Effect of own-ship lighting in reduced visibility, such as reflected glare, including landing lights, strobes, and
beacons.
X
X
8.h. .........
Wind cues to provide the effect of blowing snow or sand across a dry runway or taxiway selectable from the
instructor station.
9. ...................
X
X
X
X
Instructor control of the following: The following are the minimum instructor controls that must be available in simulators at Levels A, B, C, and D.
9.a. .........
Environmental effects, e.g., cloud base, cloud effects, cloud density, visibility in statute miles/ kilometers and
RVR in feet/meters.
X
X
X
X
9.b. .........
Airport selection ....................................................................................................................................................
X
X
X
X
9.c. .........
Airport lighting, including variable intensity ..........................................................................................................
X
X
X
X
9.d. .........
Dynamic effects including ground and flight traffic ..............................................................................................
X
X
End QPS Requirement
Begin Information
10. .................
An example of being able to ‘‘combine two airport models to achieve two ‘‘in-use’’ runways: One runway designated as the ‘‘in
use’’ runway in the first model of the airport, and the second runway designated as the ‘‘in use’’ runway in the second model of
the same airport. For example, the clearance is for the ILS approach to Runway 27, Circle to Land on Runway 18 right. Two airport visual models might be used: the first with Runway 27 designated as the ‘‘in use’’ runway for the approach to runway 27,
and the second with Runway 18 Right designated as the ‘‘in use’’ runway. When the pilot breaks off the ILS approach to runway
27, the instructor may change to the second airport visual model in which runway 18 Right is designated as the ‘‘in use’’ runway, and the pilot would make a visual approach and landing. This process is acceptable to the FAA as long as the temporary
interruption due to the visual model change is not distracting to the pilot.
11. .................
Sponsors are not required to provide every detail of a runway, but the detail that is provided should be correct within reasonable
limits.
End Information
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE A3C.—FUNCTIONS AND SUBJECTIVE TESTS
Visual Scene Content; Additional Visual Models Beyond Minimum Required for Qualification
Simulator level
Number
Class II visual scenes/visual models
A
B
C
D
This table specifies the minimum airport visual model content and functionality necessary to add airport visual models to a simulator’s visual
model library, beyond those necessary for qualification at the stated level, without the necessity of further involvement of the NSPM or TPAA.
Begin QPS Requirements
1. .........
1.a.
2. .........
Visual scene management. The following is the minimum visual scene management requirements for simulators at Levels A, B, C,
and D.
The direction of strobe lights, approach lights, runway edge lights, visual landing aids, runway centerline lights,
threshold lights, and touchdown zone lights on the ‘‘in-use’’ runway must be replicated.
X
X
X
X
Visual feature recognition. The following are the minimum distances at which runway features must be visible for simulators at Levels
A, B, C, and D. Distances are measured from runway threshold to an airplane aligned with the runway on an extended 3° glide-slope
in simulated meteorological conditions that recreate the minimum distances for visibility. For circling approaches, all requirements of
this section apply to the runway used for the initial approach and to the runway of intended landing.
2.a.
Runway definition, strobe lights, approach lights, and runway edge white lights from 5 sm (8 km) from the runway
threshold.
2.b.
Visual Approach Aid lights (VASI or PAPI) from 5 sm (8 km) from the runway threshold ...........................................
2.c.
Visual Approach Aid lights (VASI or PAPI) from 3 sm (5 km) from the runway threshold ...........................................
X
X
2.d.
Runway centerline lights and taxiway definition from 3 sm (5 km) from the runway threshold ...................................
X
2.e.
Threshold lights and touchdown zone lights from 2 sm (3 km) from the runway threshold .........................................
2.f.
2.g.
3. .........
3.a.
X
X
X
X
X
X
X
X
X
X
X
X
X
Runway markings within range of landing lights for night scenes and as required by the surface resolution requirements on day scenes.
X
X
X
X
For circling approaches, the runway of intended landing and associated lighting must fade into view in a non-distracting manner.
X
X
X
X
Airport model content. The following prescribes the minimum requirements for what must be provided in an airport visual model and
identifies other aspects of the airport environment that must correspond with that model for simulators at Levels A, B, C, and D. The
detail must be modeled using airport pictures, construction drawings and maps, or other data, or modeled in accordance with published regulatory material; however, this does not require that airport models contain details that are beyond the designed capability of
the currently qualified visual system. For circling approaches, all requirements of this section apply to the runway used for the initial
approach and to the runway of intended landing.
The surface and markings for each ‘‘in-use’’ runway:
3.a.1. ...
Threshold markings ........................................................................................................................................................
X
X
X
X
3.a.2. ...
Runway numbers ...........................................................................................................................................................
X
X
X
X
3.a.3. ...
Touchdown zone markings ............................................................................................................................................
X
X
X
X
3.a.4. ...
Fixed distance markings ................................................................................................................................................
X
X
X
X
3.a.5. ...
Edge markings ...............................................................................................................................................................
X
X
X
X
3.a.6. ...
Centerline stripes ...........................................................................................................................................................
X
X
X
X
3.b
The lighting for each ‘‘in-use’’ runway:
3.b.1. ...
Threshold lights ..............................................................................................................................................................
X
X
X
X
3.b.2. ...
Edge lights .....................................................................................................................................................................
X
X
X
X
3.b.3. ...
End lights .......................................................................................................................................................................
X
X
X
X
3.b.4. ...
Centerline lights .............................................................................................................................................................
X
X
X
X
3.b.5. ...
Touchdown zone lights, if appropriate ...........................................................................................................................
X
X
X
X
3.b.6. ...
Leadoff lights, if appropriate ..........................................................................................................................................
X
X
X
X
3.b.7. ...
Appropriate visual landing aid(s) for that runway ..........................................................................................................
X
X
X
X
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TABLE A3C.—FUNCTIONS AND SUBJECTIVE TESTS—Continued
Visual Scene Content; Additional Visual Models Beyond Minimum Required for Qualification
Simulator level
Number
Class II visual scenes/visual models
A
3.b.8. ...
3.c.
Appropriate approach lighting system for that runway ..................................................................................................
B
C
D
X
X
X
X
The taxiway surface and markings associated with each ‘‘in-use’’ runway:
3.c.1. ....
Edge ...............................................................................................................................................................................
X
X
X
X
3.c.2. ....
Centerline .......................................................................................................................................................................
X
X
X
X
3.c.3. ....
Runway hold lines ..........................................................................................................................................................
X
X
X
X
3.c.4. ....
ILS critical area markings ..............................................................................................................................................
X
X
X
X
X
X
3.d.
The taxiway lighting associated with each ‘‘in-use’’ runway:
3.d.1. ...
Edge ...............................................................................................................................................................................
3.d.2. ...
Centerline .......................................................................................................................................................................
X
X
X
X
3.d.3. ...
Runway hold and ILS critical area lights .......................................................................................................................
X
X
X
X
4. .........
Required visual model correlation with other aspects of the airport environment simulation. The following are the minimum visual
model correlation tests that must be conducted for simulators at Levels A, B, C, and D.
4.a.
The airport model must be properly aligned with the navigational aids that are associated with operations at the
‘‘in-use’’ runway.
X
X
X
X
4.b.
Slopes in runways, taxiways, and ramp areas must not cause distracting or unrealistic effects .................................
X
X
X
X
5. .........
Correlation with airplane and associated equipment. The following are the minimum correlation comparisons that must be made for
simulators at Levels A, B, C, and D.
5.a.
Visual system compatibility with aerodynamic programming ........................................................................................
X
X
X
X
5.b.
Accurate portrayal of environment relating to flight simulator attitudes ........................................................................
X
X
X
X
5.c.
Visual cues to assess sink rate and depth perception during landings ........................................................................
X
X
X
5.d.
Visual effects for each visible, own-ship, airplane external light(s) ...............................................................................
X
X
X
6. .........
Scene quality. The following are the minimum scene quality tests that must be conducted for simulators at Levels A, B, C, and D.
6.a.
Surfaces and textural cues should be free from apparent quantization (aliasing) ........................................................
6.b.
Correct color and realistic textural cues ........................................................................................................................
6.c.
Light points free from distracting jitter, smearing or streaking ......................................................................................
7. .........
X
X
X
X
X
X
X
Instructor controls of the following: The following are the minimum instructor controls that must be available in simulators at Levels A,
B, C, and D.
7.a.
Environmental effects, e.g., cloud base (if used), cloud effects, cloud density, visibility in statute miles/kilometers
and RVR in feet/meters.
X
X
X
X
7.b.
Airport selection .............................................................................................................................................................
X
X
X
X
7.c.
Airport lighting including variable intensity .....................................................................................................................
X
X
X
X
7.d.
Dynamic effects including ground and flight traffic ........................................................................................................
X
X
X
X
End QPS Requirements
Begin Information
8. .........
Sponsors are not required to provide every detail of a runway, but the detail that is provided must be correct within the capabilities of the system.
End Information
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE A3D.—FUNCTIONS AND SUBJECTIVE TESTS
<<>>
Simulator level
Number
Motion system effects
Information
A
B
C
D
This table specifies motion effects that are required to indicate when a flight crewmember must be able to recognize an event or situation.
Where applicable, flight simulator pitch, side loading and directional control characteristics must be representative of the airplane
1.
Runway rumble, oleo deflection, ground speed, uneven
runway, runway and taxiway centerline light characteristics:
Procedure: After the airplane has been pre-set to the
takeoff position and then released, taxi at various
speeds with a smooth runway and note the general
characteristics of the simulated runway rumble effects
of oleo deflections. Repeat the maneuver with a runway roughness of 50%, then with maximum roughness. The associated motion vibrations should be affected by ground speed and runway roughness.
X
X
X
2. .........
Buffets on the ground due to spoiler/speedbrake extension and reverse thrust:
Procedure: Perform a normal landing and use ground
spoilers and reverse thrust—either individually or in
combination—to decelerate the simulated airplane.
Do not use wheel braking so that only the buffet due
to the ground spoilers and thrust reversers is felt.
X
X
X
3. .........
Bumps associated with the landing gear:
Procedure: Perform a normal take-off paying special attention to the bumps that could be perceptible due to
maximum oleo extension after lift-off. When the landing gear is extended or retracted, motion bumps can
be felt when the gear locks into position.
X
X
X
4. .........
Buffet during extension and retraction of landing gear:
Procedure: Operate the landing gear. Check that the
motion cues of the buffet experienced represent the
actual airplane.
X
X
X
5. .........
Buffet in the air due to flap and spoiler/speedbrake extension and approach to stall buffet:
Procedure: Perform an approach and extend the flaps
and slats with airspeeds deliberately in excess of the
normal approach speeds. In cruise configuration,
verify the buffets associated with the spoiler/
speedbrake extension. The above effects can also be
verified with different combinations of spoiler/
speedbrake, flap, and landing gear settings to assess
the interaction effects.
X
X
X
6. .........
Approach to stall buffet:
Procedure: Conduct an approach-to-stall with engines
at idle and a deceleration of 1 knot/second. Check
that the motion cues of the buffet, including the level
of buffet increase with decreasing speed, are representative of the actual airplane.
X
X
X
7. .........
Touchdown cues for main and nose gear:
Procedure: Conduct several normal approaches with
various rates of descent. Check that the motion cues
for the touchdown bumps for each descent rate are
representative of the actual airplane.
X
X
X
8. .........
Nose wheel scuffing:
Procedure: Taxi at various ground speeds and manipulate the nose wheel steering to cause yaw rates to
develop that cause the nose wheel to vibrate against
the ground (‘‘scuffing’’). Evaluate the speed/nose
wheel combination needed to produce scuffing and
check that the resultant vibrations are representative
of the actual airplane.
X
X
X
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If time permits, different gross weights can also be selected, which may also affect the associated vibrations depending on airplane type. The associated motion effects for the above tests should also include an
assessment of the effects of rolling over centerline
lights, surface discontinuities of uneven runways, and
various taxiway characteristics.
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TABLE A3D.—FUNCTIONS AND SUBJECTIVE TESTS—Continued
<<>>
Simulator level
Number
Motion system effects
Information
A
B
C
D
9. .........
Thrust effect with brakes set:
Procedure: Set the brakes on at the take-off point and
increase the engine power until buffet is experienced.
Evaluate its characteristics. Confirm that the buffet increases appropriately with increasing engine thrust.
X
X
X
10. .......
Mach and maneuver buffet:
Procedure: With the simulated airplane trimmed in 1 g
flight while at high altitude, increase the engine power
so that the Mach number exceeds the documented
value at which Mach buffet is experienced. Check
that the buffet begins at the same Mach number as it
does in the airplane (for the same configuration) and
that buffet levels are representative of the actual airplane. For certain airplanes, maneuver buffet can
also be verified for the same effects. Maneuver buffet
can occur during turning flight at conditions greater
than 1 g, particularly at higher altitudes.
X
X
X
11. .......
Tire failure dynamics:
Procedure: Simulate a single tire failure and a multiple
tire failure.
X
X
12. .......
Engine malfunction and engine damage:
Procedure: The characteristics of an engine malfunction
as stipulated in the malfunction definition document
for the particular flight simulator must describe the
special motion effects felt by the pilot. The associated
engine instruments should vary according to the nature of the malfunction and replicate the effects of the
airframe vibration.
X
X
X
13. .......
Tail strikes and engine pod strikes:
Procedure: Tail-strikes can be checked by over-rotation
of the airplane at a speed below Vr while performing
a takeoff. The effects can also be verified during a
landing. The motion effect should be felt as a noticeable bump. If the tail strike affects the airplane angular rates, the cueing provided by the motion system
should have an associated effect.
Excessive banking of the airplane during its take-off/
landing roll can cause a pod strike. The motion effect
should be felt as a noticeable bump. If the pod strike
affects the airplane angular rates, the cueing provided by the motion system should have an associated effect.
X
X
This effect is most discernible with wing-mounted engines.
X
The pilot may notice some yawing with a multiple tire
failure selected on the same side. This should require
the use of the rudder to maintain control of the airplane. Dependent on airplane type, a single tire failure may not be noticed by the pilot and should not
have any special motion effect. Sound or vibration
may be associated with the actual tire losing pressure.
TABLE A3E.—FUNCTIONS AND SUBJECTIVE TESTS
<<>>
Simulator level
Number
Sound system
A
B
C
D
The following checks are performed during a normal flight profile with motion system ON.
1. .........
Precipitation ....................................................................................................................................................................
X
X
2. .........
Rain removal equipment ................................................................................................................................................
X
X
3. .........
Significant airplane noises perceptible to the pilot during normal operations ...............................................................
X
X
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TABLE A3E.—FUNCTIONS AND SUBJECTIVE TESTS—Continued
<<>>
Simulator level
Number
Sound system
A
B
C
D
4. .........
Abnormal operations for which there are associated sound cues including, engine malfunctions, landing gear/tire
malfunctions, tail and engine pod strike and pressurization malfunction.
X
X
5. .........
Sound of a crash when the flight simulator is landed in excess of limitations .............................................................
X
X
TABLE A3F.—FUNCTIONS AND SUBJECTIVE TESTS
<<>>
Simulator level
Number
Sound effects
A
B
C
D
This table specifies the minimum special effects necessary for the specified simulator level.
1. .........
Braking Dynamics:
Representations of the dynamics of brake failure (flight simulator pitch, side-loading, and directional control characteristics representative of the airplane), including antiskid and decreased brake efficiency due to high brake
temperatures (based on airplane related data), sufficient to enable pilot identification of the problem and implementation of appropriate procedures.
X
X
2. .........
Effects of Airframe and Engine Icing:
Required only for those airplanes authorized for operations in known icing conditions ...............................................
Procedure: With the simulator airborne, in a clean configuration, nominal altitude and cruise airspeed, autopilot on
and auto-throttles off, engine and airfoil anti-ice/de-ice systems deactivated; activate icing conditions at a rate
that allows monitoring of simulator and systems response. Icing recognition will include an increase in gross
weight, airspeed decay, change in simulator pitch attitude, change in engine performance indications (other than
due to airspeed changes), and change in data from pitot/static system. Activate heating, anti-ice, or de-ice systems independently. Recognition will include proper effects of these systems, eventually returning the simulated
airplane to normal flight.
X
X
TABLE A3G.—FUNCTIONS AND SUBJECTIVE TESTS
<<>>
Simulator level
Instructor operating station (IOS)
(as appropriate)
Number
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 simulator
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
X
X
X
X
4. .........
4.a
Environmental controls
Visibility (statute miles (kilometers)) ..............................................................................................................................
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TABLE A3G.—FUNCTIONS AND SUBJECTIVE TESTS—Continued
<<>>
Simulator level
Instructor operating station (IOS)
(as appropriate)
A
B
C
D
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.
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
Number
6.a.
Problem (all) freeze/release ...........................................................................................................................................
X
X
X
X
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
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 his
or her 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
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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.
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.
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(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) Flight deck Layout (compare with
difference list).
(5) Equipment.
(a) Quick Donning Oxygen Masks.
(b) Head Sets.
(c) Smoke Goggles.
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(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.
(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. Flight deck Checks.
(1) Flight deck 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) Flight deck ‘‘Daylight’’ ambient
lighting.
(c) Environment Light Controls.
(d) Runway Light Controls.
(e) Taxiway Light Controls.
(2) Scene Content.
(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 and 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:
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(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/
300m.
(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 increase
(7) Windshear during Takeoff (check the
following):
(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
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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.
(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:
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(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.
(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.
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(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.
(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 Ill Approach and Landing—
System Malfunctions.
(15) CAT Ill 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) Flight deck ambient lighting during
‘‘daylight’’ conditions.
(c) Environment Light Controls.
(d) Runway Light Controls.
(e) Taxiway Light Controls.
(f) Approach Light Controls.
(2) Scene Content.
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(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
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.
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End Information
Attachment 4 to Appendix A to Part 60—
Sample Documents
Table of Contents
Title of Sample
Figure A4A—Sample Letter, Request for
Initial, Upgrade, or Reinstatement
Evaluation.
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(a) Visual model satisfactory.
(b) Parking brake operation satisfactory.
(3) Shutdown Checks.
q. Crash Function.
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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(1) Gear-up Crash.
(2) Excessive rate of descent Crash.
(3) Excessive bank angle Crash.
lllllllllllllllllllll
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
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(c) Flight deck height above ground.
p. After Landing Operations.
(1) After Landing Checks.
(2) Taxi back to gate. Check the following:
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Attachment 5 to Appendix A to Part 60—
Simulator Qualification Requirements for
Windshear Training Program Use
lllllllllllllllllllll
Begin QPS Requirements
1. Applicability
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.
2. Statement of Compliance and Capability
(SOC)
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
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simulator (such as crosswind takeoffs,
crosswind approaches, and crosswind
landings).
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 flight deck 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.
3. Models
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.
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(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
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.
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4. Demonstrations
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,
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.
5. Recording Parameters
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.
6. Equipment Installation and Operation
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.
7. Qualification Test Guide
a. All QTG material must be forwarded to
the NSPM.
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
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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
Begin Information
8. Subjective Evaluation
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.
9. Qualification Basis
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.
10. Demonstration Repeatability
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
Attachment 6 to Appendix A to Part 60—
FSTD Directives Applicable To Airplane
Flight Simulators
Flight Simulation Training Device (FSTD)
Directive (FD)
FSTD Directive Number 1. Applicable to
all Full Flight Simulators (FFS), regardless of
the original qualification basis and
qualification date (original or upgrade),
having Class–II visual scenes or airport
models available.
Agency: Federal Aviation Administration
(FAA), DOT
Action: This is a retroactive requirement to
have all Class II visual scenes or airport
models meet current requirements.
lllllllllllllllllllll
Summary: Notwithstanding the
authorization listed in paragraph 13b in
Appendices A and C, this FSTD Directive
(FD) requires each sponsor to ensure that, by
[date 1 year after effective date of the final
rule], each Class II visual scene or airport
model available in an FFS, meets the
requirements of 14 CFR part 60, Appendix A,
Attachment 3, Table A3C, or Appendix C,
Attachment 3, Table C3C, as applicable. The
completion of this requirement will not
require a report. The fact that the scene or
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model is available in the FFS is the sponsor’s
testament that the requirements are met.
Dates: This FD becomes effective on
[effective date of the final rule].
For Further Information Contact: Ed Cook,
Senior Advisor to the Division Manager, Air
Transportation Division, AFS–200, 800
Independence Ave, SW., Washington, DC,
20591: telephone: (404) 832–4701; fax: (404)
761–8906.
Specific Requirements:
1. Part 60 requires that each FSTD be:
a. Sponsored by a person holding or
applying for an FAA operating certificate
under Part 119, Part 141, or Part 142, or
holding or applying for an FAA-approved
training program under Part 63, Appendix C,
for flight engineers, and
b. Evaluated and issued a Statement of
Qualification for a specific FSTD level.
2. Full flight simulators (FFS) also require
the installation of a visual system that is
capable of providing an out-of-the-flight-deck
view of visual scenes or airport models. To
be qualified, each FFS must have available
for use a minimum number of visual scenes
or airport models that have certain features.
These are called Class I visual scenes or
airport models, the required features of
which are listed in Part 60. Additional scenes
or models that are beyond those necessary for
qualification may also be used for various
additional training program applications,
including Line Oriented Flight Training, are
classified as Class II. However, historically
these visual scenes or airport models were
not routinely evaluated or required to meet
any standardized criteria. This has led to
qualified simulators containing visual scenes
or airport models being used to meet FAAapproved training, testing, or checking
requirements with potentially incorrect or
inappropriate visual references.
3. To prevent this from occurring in the
future, by [date 1 year after effective date of
the final rule], each FSTD sponsor must
assure that each Class II visual scene or
airport model available in a qualified FFS
meets the requirements found in 14 CFR part
60, Appendix A, Attachment 3, Table A3C or
Appendix C, Attachment 3, Table C3C, as
applicable. These references describe the
requirements for visual scene management
and the minimum distances from which
runway or landing area features must be
visible for all levels of simulator. The visual
scene or airport model must provide, for each
‘‘in-use runway’’ or ‘‘in-use landing area,’’
runway or landing area surface and markings,
runway or landing area lighting, taxiway
surface and markings, and taxiway lighting.
Additional requirements include correlation
of the visual scenes or airport models with
other aspects of the airport environment,
correlation of the aircraft and associated
equipment, scene quality assessment
features, and the control of these scenes or
models the instructor must be able to
exercise.
4. For circling approaches, all requirements
of this section apply to the runway used for
the initial approach and to the runway of
intended landing.
5. The details in these scenes or models
must be developed using airport pictures,
construction drawings and maps, or other
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similar data, or developed in accordance
with published regulatory material. However,
this FD does not require that visual scenes or
airport models contain details that are
beyond the initially designed capability of
the visual system, as currently qualified. The
recognized limitations to visual systems are
as follows:
a. Visual systems not required to have
runway numbers as a part of the specific
runway marking requirements are:
(1) Link NVS and DNVS.
(2) Novoview 2500 and 6000.
(3) FlightSafety VITAL series up to, and
including, VITAL III, but not beyond.
(4) Redifusion SP1, SP1T, and SP2.
b. Visual systems required to display
runway numbers only for LOFT scenes are:
(1) FlightSafety VITAL IV.
(2) Redifusion SP3 and SP3T.
(3) Link-Miles Image II.
c. Visual systems not required to have
accurate taxiway edge lighting are:
(1) Redifusion SP1.
(2) FlightSafety Vital IV.
(3) Link-Miles Image II and Image IIT.
(4) XKD displays (even though the XKD
image generator is capable of generating blue
colored lights, the display cannot
accommodate that color).
6. A copy of this Directive must be filed
in the Master Qualification Test Guide in the
designated FSTD Directive Section, and its
inclusion must be annotated on the Index of
Effective FSTD Directives chart. See
Attachment 4, Appendices A through D for
a sample MQTG Index of Effective FSTD
Directives chart.
Appendix B to Part 60—Qualification
Performance Standards for Airplane Flight
Training Devices
lllllllllllllllllllll
12. Additional Qualifications for Currently
Qualified FSTDs (§ 60.16).
13. Previously Qualified FSTDs (§ 60.17).
14. Inspection, Continuing Qualification
Evaluation, and Maintenance
Requirements (§ 60.19).
15. Logging FSTD Discrepancies (§ 60.20).
16. Interim Qualification of FSTDs for New
Airplane Types or Models (§ 60.21).
17. Modifications to FSTDs (§ 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.
Attachment 5 to Appendix B to Part 60—
FSTD Directives.
End Information
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
(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 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
FSTD (§ 60.14).
11. Initial (and Upgrade) Qualification
Requirements (§ 60.15).
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1. Introduction
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. Questions regarding the contents of this
publication should be sent to the U.S.
Department of Transportation, Federal
Aviation Administration, Flight Standards
Service, National Simulator Program Staff,
AFS–205, 100 Hartsfield Centre Parkway,
Suite 400, Atlanta, Georgia, 30354.
Telephone contact numbers for the NSP are:
phone, 404–832–4700; fax, 404–761–8906.
The general email address for the NSP office
is: 9-aso-avr-sim-team@faa.gov. The NSP
Internet Web Site address is: https://
www.faa.gov/safety/programs_initiatives/
aircraft_aviation/nsp/. On this Web Site you
will find an NSP personnel list with
telephone and email contact information for
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each NSP staff member, a list of qualified
flight simulation devices, advisory circulars,
a description of the qualification process,
NSP policy, and an NSP ‘‘In-Works’’ section.
Also linked from this site are additional
information sources, handbook bulletins,
frequently asked questions, a listing and text
of the Federal Aviation Regulations, Flight
Standards Inspector’s handbooks, and other
FAA links.
c. The NSPM encourages the use of
electronic media for all communication,
including any record, report, request, test, or
statement required by this appendix. The
electronic media used must have adequate
security provisions and be acceptable to the
NSPM. The NSPM recommends inquiries on
system compatibility, and minimum system
requirements are also included on the NSP
Web site.
d. 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
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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 and 60.2)
lllllllllllllllllllll
Begin Information
No additional regulatory or informational
material 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)
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.
4. Qualification Performance Standards
(§ 60.4)
No additional regulatory or informational
material applies to § 60.4, Qualification
Performance Standards.
5. Quality Management System (§ 60.5)
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 May
30, 2008, the 12-month period begins on the
date of the first continuing qualification
evaluation conducted in accordance with
§ 60.19 after (60 days after date of publication
of the final rule in the Federal Register) and
continues for each subsequent 12-month
period;
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(ii) A device qualified on or after May 30,
2008, 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, 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 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
the preceding 12-month period) stating that
the performance and handling qualities of
each FTD in the Chicago and Moscow centers
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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.
8. FSTD Use (§ 60.11)
No additional regulatory or informational
material applies to § 60.11, FSTD use.
End Information
lllllllllllllllllllll
9. FSTD 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
(5) Without alteration, adjustments, or bias;
however the data may be re-scaled, digitized,
or otherwise manipulated to fit the desired
presentation.
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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. The
sponsor must—
(1) Within 10 calendar days, notify the
NSPM of the existence of this data; and
(2) Within 45 calendar days, notify the
NSPM of—
(i) The schedule to incorporate this data
into the FTD; or
(ii) The reason for not incorporating this
data into the FTD.
e. 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.’’ The steady state
condition must exist from 4 seconds prior to,
through 1 second following, the instant of
time captured by the snap shot.
End QPS Requirements
lllllllllllllllllllll
Begin Information
f. 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.
g. 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.
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h. 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 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.
i. The NSPM will consider, on a case-bycase basis, whether 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 FSTD
(§ 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 users of the
FTD that raise questions about 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.
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.
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(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 appropriate QPS.
(c) The result of FTD subjective tests
prescribed in the appropriate 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.
(d) The source of the basic aerodynamic
model and the aerodynamic coefficient data
used to modify the basic model.
(e) The engine model(s) and its data
revision number or reference.
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(f) The flight control data revision number
or reference.
(g) The flight management system
identification and revision level.
(h) The FTD model and manufacturer.
(i) The date of FTD manufacture.
(j) The FTD computer identification.
(k) The visual system model and
manufacturer, including display type.
(l) 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.
(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
QTG for the first airplane model and a
supplement to that QTG for each additional
airplane model. The NSPM will conduct
evaluations for each airplane 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.,
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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 may 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 May 30,
2014, 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
copy of the MQTG by and after May 30, 2014.
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.
l. During the initial (or upgrade)
qualification evaluation conducted by the
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NSPM, the sponsor must also provide a
person knowledgeable about the operation of
the aircraft and the operation of the FTD.
End QPS Requirements
lllllllllllllllllllll
Begin Information
m. 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.
n. 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) Flight deck 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.
o. 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;
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(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.
p. 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.
q. 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.
r. 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.
s. 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 evaluation and will
list the tasks for which the FTD is qualified,
referencing the tasks described in Table B1B
in attachment 1. However, it is the sponsor’s
responsibility to obtain TPAA approval prior
to using the FTD in an FAA-approved flight
training program.
t. 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.
u. 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.
v. 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).
w. 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.
59707
Begin Information
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 May 30, 2008,
and replacement FTD systems, are not
required to meet the general FTD
requirements, the objective test requirements,
and the subjective test requirements of
Attachments 1, 2, and 3 of this appendix as
long as the FTD continues to meet the test
requirements contained in the MQTG
developed under the original qualification
basis.
c. [Reserved]
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 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 QPS Requirements
lllllllllllllllllllll
End Information
lllllllllllllllllllll
12. Additional Qualifications for Currently
Qualified FSTDs (§ 60.16)
No additional regulatory or informational
material applies to § 60.16, Additional
Qualifications for a Currently Qualified FTD.
End Information
lllllllllllllllllllll
13. Previously Qualified FSTDs (§ 60.17)
lllllllllllllllllllll
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
14. Inspection, Continuing Qualification,
Evaluation, and Maintenance Requirements
(§ 60.19)
lllllllllllllllllllll
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.
d. During the continuing qualification
evaluation conducted by the NSPM, the
sponsor must also provide a person
knowledgeable about the operation of the
aircraft and the operation of the FTD.
End QPS Requirements
lllllllllllllllllllll
Begin Information
e. 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.
f. 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.
g. 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.
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(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.
h. 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.
15. Logging FSTD Discrepancies (§ 60.20)
No additional regulatory or informational
material applies to § 60.20. Logging FTD
Discrepancies.
16. Interim Qualification of FSTDs for New
Airplane Types or Models (§ 60.21)
No additional regulatory or informational
material applies to § 60.21, Interim
Qualification of FTDs for New Airplane
Types or Models.
End Information
lllllllllllllllllllll
17. Modifications to FSTDs (§ 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.
See Attachment 6 for a list of all effective
FSTD Directives applicable to Airplane
FTDs.
End Information
lllllllllllllllllllll
18. Operation with Missing, Malfunctioning,
or Inoperative Components (§ 60.25)
lllllllllllllllllllll
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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
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
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,
the date of the change, a summary of the
change, and the reason for the change.
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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)
lllllllllllllllllllll
Begin Information
No additional regulatory or informational
material applies to § 60.33, Applications,
Logbooks, Reports, and Records: Fraud,
Falsification, or Incorrect Statements.
End Information
lllllllllllllllllllll
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
airplane-specific flight deck area, or an
enclosed airplane-specific flight deck and at
least one operating system. Air/ground logic
is required (no aerodynamic programming
required). All displays may be flat/LCD panel
representations or actual representations of
displays in the aircraft. All controls,
switches, and knobs may be touch sensitive
activation (not capable of manual
manipulation of the flight controls) or may
physically replicate the aircraft in control
operation.
(2) Level 5. A device that may have an open
airplane-specific flight deck area, or an
enclosed airplane-specific flight deck 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. All displays may be flat/LCD
panel representations or actual
representations of displays in the aircraft.
Primary and secondary flight controls (e.g.,
rudder, aileron, elevator, flaps, spoilers/
speed brakes, engine controls, landing gear,
nose wheel steering, trim, brakes) must be
physical controls. All other controls,
switches, and knobs may be touch sensitive
activation.
(3) Level 6. A device that has an enclosed
airplane-specific flight deck 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. All displays may be flat/LCD
panel representations or actual
representations of displays in the aircraft, but
all controls, switches, and knobs must
physically replicate the aircraft in control
operation.
End Information
lllllllllllllllllllll
25. FSTD Qualification on the Basis of a
Bilateral Aviation Safety Agreement (BASA)
(§ 60.37)
lllllllllllllllllllll
Begin Information
No additional regulatory or informational
material applies to § 60.37, FSTD
Qualification on the Basis of a Bilateral
Aviation Safety Agreement (BASA).
End Information
lllllllllllllllllllll
Attachment 1 to Appendix B 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
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 flight deck 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.
d. Table B1B provides the tasks that the
sponsor will examine to determine whether
the FSTD satisfactorily meets the
requirements for flight crew training, testing,
and experience, and provides the tasks for
which the simulator may be qualified.
e. Table B1C provides the functions that an
instructor/check airman must be able to
control in the simulator.
f. It is not required that all of the tasks that
appear on the List of Qualified Tasks (part of
the SOQ) be accomplished during the initial
or continuing qualification evaluation.
End Information
lllllllllllllllllllll
TABLE B1A.—MINIMUM FTD REQUIREMENTS
<<>>
<>
FTD level
Number
General FTD requirements
Notes
4
5
6
1. General Flight Deck Configuration
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TABLE B1A.—MINIMUM FTD REQUIREMENTS—Continued
<<>>
<>
FTD level
Number
General FTD requirements
Notes
4
1.a. ......
The FTD must have a flight deck that is a replica of the
airplane simulated with controls, equipment, observable
flight deck 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 that in the airplane. Pilot
seat(s) must afford the capability for the occupant to be
able to achieve the design ‘‘eye position.’’ Equipment
for the operation of the flight deck windows must be included, but the actual windows need not be operable.
Fire axes, extinguishers, and spare light bulbs must be
available in the flight simulator, 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.
1.b. ......
The FTD 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 flight
deck or an open flight deck area. Additional equipment
required for the authorized training/checking events
must be available in the FTD, but may be located in a
suitable location as near as practical to the spatially correct position. Actuation of equipment must replicate the
appropriate function in the airplane. Fire axes, landing
gear pins, and any similar purpose instruments need
only be represented in silhouette.
An SOC is required.
5
6
X
X
For FTD purposes, the flight deck 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 items such as landing 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.
An SOC is required.
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.
An SOC is required.
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X
X
X
X
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59711
TABLE B1A.—MINIMUM FTD REQUIREMENTS—Continued
<<>>
<>
FTD level
Number
General FTD requirements
Notes
4
2.c. ......
5
X
Relative responses of the flight deck 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.
An objective test is required.
6
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 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 winds.
A subjective test is required.
X
X
3.b. ......
Navigation equipment must be installed and operate within
the tolerances applicable for the airplane.
Level 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.
A subjective test is required.
X
X
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.
A subjective test is required.
X
X
X
3.d. ......
The lighting environment for panels and instruments must
be sufficient for the operation being conducted.
A subjective test is required.
X
X
X
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.
An objective test is required.
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Back-lighted panels and instruments may be installed but
are not required.
X
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TABLE B1A.—MINIMUM FTD REQUIREMENTS—Continued
<<>>
<>
FTD level
Number
General FTD requirements
Notes
4
3.f. .......
5
The FTD must provide control forces and control travel of
sufficient precision to manually fly an instrument approach.
A subjective test is required.
6
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).
A subjective test is required.
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.
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.
A subjective test is required.
X
X
X
X
X
The motion system standards set out in part 60, Appendix
A for at least Level A simulators are acceptable.
X
The motion system standards set out in part 60, Appendix
A for at least Level A simulators are acceptable.
5. Motion System (not required)
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 may 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.
5.b. ......
If a motion system is installed, it must be measured by latency tests or transport delay tests and may not exceed
300 milliseconds. Instrument response may not occur
prior to motion onset.
An objective test is required.
6. Visual System
6.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:
6.a.1. ...
The visual system must respond to abrupt input at the pilot’s position.
An SOC is required.
A subjective test is required.
6.a.2. ...
The visual system must be at least a single channel, noncollimated display.
An SOC is required.
A subjective test is required.
6.a.3. ...
X
X
X
X
X
X
X
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.a.4. ...
The visual system must provide for a maximum parallax of
10° per pilot.
An SOC is required.
X
X
X
6.a.5. ...
The visual scene content may not be distracting ................
An SOC is required.
A subjective test is required.
X
X
X
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
59713
TABLE B1A.—MINIMUM FTD REQUIREMENTS—Continued
<<>>
<>
FTD level
Number
General FTD requirements
Notes
4
5
6
6.a.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.a.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
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, a visual system meeting the
standards set out for at least a Level A FFS (see Appendix A of this part) will be required. A ‘‘direct-view,’’
non-collimated visual system (with the other requirements for a Level A visual system met) may be considered satisfactory for those installations where the visual
system design ‘‘eye point’’ is appropriately adjusted for
each pilot’s position such that the parallax error is at or
less than 10° simultaneously for each pilot.
An SOC is required.
An objective test is required.
X
Directly projected, non-collimated visual displays may
prove to be unacceptable for dual pilot applications.
7. Sound System
7.a. ......
The FTD must simulate significant flight deck sounds resulting from pilot actions that correspond to those heard
in the airplane.
X
TABLE B1B.—TABLE OF TASKS VS. FTD LEVEL
<<>>
Number
<>
Subjective requirements
In order to be qualified at the FTD qualification level indicated, the FTD must be able to perform at least the tasks
associated with that level of qualification.
See Notes 1 and 2 at the end of the Table
FTD level
Notes
4
5
6
1. Preflight Procedures
1.a. ......
Preflight Inspection (flight deck only) ..................................
A
A
X
1.b. ......
Engine Start .........................................................................
A
A
X
1.c. ......
Pre-takeoff Checks ..............................................................
A
A
X
2. Takeoff and Departure Phase
2.a. ......
Rejected Takeoff (requires visual system) ..........................
2.b. ......
A
Departure Procedure ...........................................................
X
X
3. In-flight Maneuvers
3.a. ......
a. Steep Turns .....................................................................
X
X
3.b. ......
b. Approaches to Stalls .......................................................
A
X
3.c. ......
c. Engine Failure (procedures only)—Multiengine Airplane
A
X
3.d. ......
d. Engine Failure (procedures only)—Single-Engine Airplane.
A
X
3.e. ......
e. Specific Flight Characteristics incorporated into the
user’s FAA approved flight training program.
A
A
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59714
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE B1B.—TABLE OF TASKS VS. FTD LEVEL—Continued
<<>>
Number
<>
Subjective requirements
In order to be qualified at the FTD qualification level indicated, the FTD must be able to perform at least the tasks
associated with that level of qualification.
See Notes 1 and 2 at the end of the Table
FTD level
Notes
4
5
6
4. Instrument Procedures
4.a. ......
Standard Terminal Arrival/Flight Management System Arrival.
A
X
4.b. ......
Holding .................................................................................
A
X
4.c. ......
Precision Instrument, all engines operating ........................
A
X
e.g., Autopilot, Manual (Flt. Dir. Assisted), Manual (Raw
Data).
4.d. ......
Non-precision Instrument, all engines operating .................
A
X
e.g., NDB, VOR, VOR/DME, VOR/TAC, RNAV, LOC,
LOC/BC, ADF, and SDF.
4.e. ......
Circling Approach (requires visual system) .........................
4.f. .......
Missed Approach .................................................................
A
A
X
5. Normal and Abnormal Procedures
5.a. ......
Engine (including shutdown and restart procedures only) ..
A
A
X
5.b. ......
Fuel System .........................................................................
A
A
X
5.c. ......
Electrical System .................................................................
A
A
X
5.d. ......
Hydraulic System .................................................................
A
A
X
5.e. ......
Environmental and Pressurization Systems ........................
A
A
X
5.f. .......
Fire Detection and Extinguisher Systems ...........................
A
A
X
5.g. ......
Navigation and Avionics Systems .......................................
A
A
X
5.h. ......
Automatic Flight Control System, Electronic Flight Instrument System, and Related Subsystems.
A
A
X
5.i. .......
Flight Control Systems ........................................................
A
A
X
5.j. .......
Anti-ice and Deice Systems ................................................
A
A
X
5.k. ......
Aircraft and Personal Emergency Equipment
A
A
X
6. Emergency Procedures
6.a. ......
Emergency Descent (maximum rate) ..................................
A
X
6.b. ......
Inflight Fire and Smoke Removal ........................................
A
X
6.c. ......
Rapid Decompression .........................................................
A
X
6.d. ......
Emergency Evacuation ........................................................
A
A
X
7. Postflight Procedures
7.a. ......
After-Landing Procedures ....................................................
A
A
X
7.b. ......
Parking and Securing ..........................................................
A
A
X
Note 1: An ‘‘A’’ in the table indicates that the system, task, or procedure, although not required to be present, may be examined if the appropriate airplane system is simulated in the FTD and is working properly.
Note 2: Items not installed or not functional on the FTD and not appearing on the SOQ Configuration List, are not required to be listed as exceptions on the SOQ.
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
59715
TABLE B1C.—TABLE OF TASKS VS. FTD LEVEL
<<>>
Number
<>
Subject requirements
In order to be qualified at the FTD qualification level indicated, the
FTD must be able to perform at least the tasks associated with
that level of qualification.
FTD level
Notes
4
5
6
1. Instructor Operating Station (IOS)
1.a. ......
Power switch(es) ...............................................................................
X
X
X
1.b. ......
Airplane conditions ............................................................................
A
X
X
e.g., GW, CG, Fuel loading, Systems, Ground.
Crew.
1.c. ......
Airports/Runways ..............................................................................
X
X
X
e.g., Selection, Surface, Presets, Lighting controls.
1.d. ......
Environmental controls ......................................................................
X
X
X
e.g., Temp, Wind.
1.e. ......
Airplane system malfunctions (Insertion/deletion) ............................
A
X
X
1.f. .......
Locks, Freezes, and Repositioning ...................................................
X
X
X
1.g. ......
Sound Controls. (On/off/adjustment) ................................................
X
X
X
1.h. ......
Motion/Control Loading System, as appropriate. On/off/emergency
stop.
A
X
X
X
X
X
2. Observer Seats/Stations
2.a. ......
Position/Adjustment/Positive restraint system ..................................
Attachment 2 to Appendix B to Part 60—
Flight Training Device (FTD) Objective Tests
lllllllllllllllllllll
Begin Information
1. Discussion
a. 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;
(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.
b. 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
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provides a degree of commonality between
the two tables and substantially reduces the
potential for confusion when referring to
objective test numbers for either FFSs or
FTDs.
c. 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.
d. 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.
e. A Level 4 FTD does not require objective
tests and therefore, Level 4 is not addressed
in the following table.
End Information
lllllllllllllllllllll
Begin QPS Requirements
2. Test Requirements
a. The ground and flight tests required for
qualification are listed in Table B2A
Objective Tests. 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
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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 may 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.
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
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.’’ The steady state
condition must exist from 4 seconds prior to,
through 1 second following, the instant of
time captured by the snapshot.
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 Non-
normal 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
flight deck (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
TABLE B2A.—FLIGHT TRAINING DEVICE (FTD) OBJECTIVE TESTS
<<>>
FTD
level
Test
Tolerances
Number
Flight conditions
Test details
Title
5
<>
6
Notes
X
This test is required
only if RTO training credit is
sought.
1. Performance
1.a. ........
(Reserved)
1.b. ........
Takeoff
1.b.1. .....
Ground Acceleration
Time.
1.b.2.
through
1.b.6.
(Reserved)
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Record acceleration time for a
minimum of 80% of the segment from brake release to
VR.
Preliminary aircraft certification
data may be used.
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59717
TABLE B2A.—FLIGHT TRAINING DEVICE (FTD) OBJECTIVE TESTS—Continued
<<>>
FTD
level
Test
Tolerances
Number
Rejected Takeoff ....
1.b.8. .....
5
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. ......
1.f.2. ......
6
<>
(Reserved)
1.c. ........
Test details
Title
1.b.7. .....
Flight conditions
Notes
±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.
±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. FTD performance
must be recorded over an
interval of at least 1,000 ft
(300 m).
X
X
Acceleration ............
Level 6: ±10% Tt, or
±0.25 sec.
Level 5: ±1 sec .......
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
Tt is the total time
from initial throttle
movement to
reaching 90% of
go around power.
Deceleration ............
Level 6: ±10% Tt, or
±0.25 sec.
Level 5: ±1 sec .......
Ground ....................
Record engine power (N1, N2,
EPR, Torque, Manifold
Pressure) from maximum
takeoff power to idle for a
rapid (slam) throttle movement.
X
X
Tt is the total time
from initial throttle
movement to
reaching 90%
decay of maximum takeoff
power.
X
2. Handling Qualities
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 results and 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
2.a. ........
Static Control Tests
2.a.1.a. ..
Pitch Controller Position vs. Force
and Surface Position Calibration.
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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±2 lb (0.9 daN)
Ground ....................
breakout, ±10% or
±5 lb (2.2 daN)
force, ±2° elevator.
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Record results for an uninterrupted control sweep to the
stops.
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59718
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE B2A.—FLIGHT TRAINING DEVICE (FTD) OBJECTIVE TESTS—Continued
<<>>
FTD
level
Test
Tolerances
Flight conditions
Test details
Number
Title
2.a.1.b. ..
Pitch Controller Position vs. Force.
±2 lb (0.9 daN)
breakout, ±10% or
±5 lb (2.2 daN)
force.
As determined by
sponsor.
Record results during initial
qualification evaluation for
an uninterrupted control
sweep to the stops. The recorded tolerances apply to
subsequent comparisons on
continuing qualification evaluations.
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. ..
Roll Controller Position vs. Force.
±2 lb (0.9 daN)
breakout, ±10% or
±3 lb (1.3 daN)
force.
As determined by
sponsor.
Record results during initial
qualification evaluation for
an uninterrupted control
sweep to the stops. The recorded tolerances apply to
subsequent comparisons on
continuing qualification evaluations.
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, ±27° 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.
As determined by
sponsor.
Record results during initial
qualification evaluation for
an uninterrupted control
sweep to the stops. The recorded tolerances apply to
subsequent comparisons on
continuing qualification evaluations.
2.a.4. .....
Nosewheel Steering
Controller Force.
±2 lb (0.9 daN)
breakout, ±10% or
±3 lb (1.3 daN)
force.
Ground ....................
Record results of an uninterrupted control sweep to the
stops.
X
2.a.5. .....
Rudder Pedal Steering Calibration.
±2° nosewheel
angle.
Ground ....................
Record results of an uninterrupted control sweep to the
stops.
X
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6
X
<>
Notes
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.
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. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
59719
TABLE B2A.—FLIGHT TRAINING DEVICE (FTD) OBJECTIVE TESTS—Continued
<<>>
FTD
level
Test
Tolerances
Number
Pitch Trim Indicator
vs. Surface Position Calibration.
2.a.7. .....
5
<>
(Reserved)
2.a.8. .....
Test details
Title
2.a.6. .....
Flight conditions
6
Notes
X
The purpose of the
test is to compare
the FTD against
design data or
equivalent.
±0.5° of computed
trim surface angle.
Ground ....................
Alignment of Flight
deck Throttle
Lever vs. Selected Engine Parameter.
±5° of throttle lever
angle or ±0.8 in (2
cm) for power
control without angular travel, or
±3% N1, or ±0.03
EPR, or ±3%
maximum rated
manifold pressure,
or ±3% torque.
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
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. ........
(Reserved)
2.c. ........
Longitudinal Control Tests
Power setting is that required for level flight unless otherwise specified.
2.c.1. .....
Power Change
Force.
±5 lb (2.2 daN) or,
±20% force.
Approach ................
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
2.c.2. .....
Flap/Slat Change
Force.
±5 lb (2.2 daN) or,
±20% force.
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
2.c.3. .....
(Reserved)
2.c.4. .....
Gear Change Force
±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
2.c.5. .....
Longitudinal Trim ....
±0.5° trim surface
angle ±1° elevator
±1° pitch angle
±5% net thrust or
equivalent.
Cruise, Approach,
and Landing.
Record steady-state condition
with wings level and thrust
set for level flight. 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
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Test not required
unless RTO credit
is sought.
59720
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE B2A.—FLIGHT TRAINING DEVICE (FTD) OBJECTIVE TESTS—Continued
<<>>
FTD
level
Test
Tolerances
Flight conditions
Test details
Number
Title
5
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.
Cruise, Approach,
and Landing.
Continuous time history data
or a series of snapshot tests
may be used. Record results up to 30° of bank for
approach and landing configurations. Record results
for up to 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 FTD. The
alternative method applies
to airplanes that do not exhibit ‘‘stick-force-per-g’’ characteristics.
2.c.7. .....
Longitudinal Static
Stability.
±5 lb (±2.2 daN) or
±10% pitch controller force.
Alternative method:
±1° or ±10%
change of elevator.
Approach ................
May be a series of snapshot
test results. Record results
for at least 2 speeds above
and 2 speeds below trim
speed. The force tolerance
is not applicable if forces
are generated solely by the
use of airplane hardware in
the FTD. The alternative
method applies to airplanes
that do not exhibit speed
stability characteristics.
Level 5 must exhibit positive
static stability, but need not
comply with the numerical
tolerance.
2.c.8. .....
Stall Warning (actuation of stall warning device.).
±3 kts. airspeed, ±2°
bank for speeds
greater than actuation of stall warning device or initial buffet.
2.c.9.a. ..
Phugoid Dynamics ..
2.c.9.b. ..
6
X
X
X
Second Segment
The stall maneuver must be
Climb, and Apentered with thrust at or
proach or Landing.
near idle power and wings
level (1g). Record the stall
warning signal and initial
buffet if applicable.
X
X
±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.
X
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.
X
2.c.10. ...
Short Period Dynamics.
±1.5° pitch angle or
±2°/sec pitch rate,
±0.10g acceleration..
Cruise .....................
2.d. ........
Lateral Directional Tests
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Notes
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
59721
TABLE B2A.—FLIGHT TRAINING DEVICE (FTD) OBJECTIVE TESTS—Continued
<<>>
FTD
level
Test
Tolerances
Number
Flight conditions
Test details
Title
5
6
X
<>
Notes
X
Power setting is that required for level flight unless otherwise specified.
2.d.1. .....
(Reserved)
2.d.2. .....
Roll Response
(Rate).
±10% or ±2°/sec roll
rate.
Cruise, and ApRecord results for normal roll
proach or Landing.
controller deflection (onethird of maximum roll controller travel). May be combined with step input of flight
deck roll controller test (see
2.d.3.).
2.d.3. .....
Roll Response to
Flight deck Roll
Controller Step
Input.
±10% or ±2° bank
angle.
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 (see 2.d.2.).
X
2.d.4.a. ..
Spiral Stability .........
Correct trend and
±3° or ±10% bank
angle in 30 seconds.
Cruise .....................
Record results for both directions. As an alternate test,
demonstrate the lateral control required to maintain a
steady turn with a bank
angle of 30°.
X
2.d.4.b. ..
Spiral Stability .........
Correct trend ...........
Cruise .....................
2.d.5. .....
(Reserved)
2.d.6.a. ..
Rudder Response ...
±2°/sec or ±10%
yaw rate.
Approach or Landing.
A rudder step input of 20%–
30% rudder pedal throw
must be used. 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 ApRecord results for at least 6
proach or Landing.
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 ±2° bank
angle, ±1° sideslip
angle, ±10% or
±2° aileron, ±10%
or ±5° spoiler or
equivalent roll,
controller position
or force.
Approach or Landing.
2.e.
through
2.h.
(Reserved)
X
May be a series of snapshot
test results. Propeller driven
airplanes must test in each
direction. Sideslip angle is
matched only for repeatability and only on continuing qualification evaluations.
3. (Reserved)
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Airplane data averaged from multiple tests in same
direction may be
used.
X
X
X
X
Airplane data averaged from multiple tests in same
direction may be
used.
X
59722
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE B2A.—FLIGHT TRAINING DEVICE (FTD) OBJECTIVE TESTS—Continued
<<>>
FTD
level
Test
Tolerances
Number
Flight conditions
Test details
Title
5
6
X
<>
Notes
X
4. (Reserved)
5. (Reserved)
6. FTD System Response Time
6.a. ........
Latency
............................
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).
.................................
.................................
..................................................
300 ms (or less)
after controller
movement.
Transport Delay ......
300 ms (or less)
after airplane response.
N/A ..........................
A separate test is required in
each axis (pitch, roll, and
yaw).
lllllllllllllllllllll
Begin Information
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.
End Information
lllllllllllllllllllll
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4. Alternative Objective Data for FTD Level 5
lllllllllllllllllllll
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
appropriate for the level of qualification
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If Transport Delay is
the chosen method to demonstrate
relative responses, the
sponsor and the
NSPM will use the
latency values to
ensure proper
simulator response when reviewing those existing tests where
latency can be
identified (e.g.,
short period, roll
response, rudder
response).
X
X
sought as set out in Table B2A. The QTG
must highlight those results that demonstrate
that 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.
End QPS Requirements
lllllllllllllllllllll
Begin Information
d. The reader is encouraged to consult the
Airplane Flight Simulator Evaluation
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
Handbook, Volumes I and II, published by
the Royal Aeronautical Society, London, UK,
and FAA Advisory Circulars (AC) 25–7,
Flight Test Guide for Certification of
Transport Category Airplanes, and (AC) 23–
8A, Flight Test Guide for Certification of Part
23 Airplanes, as amended, for references and
examples regarding flight testing
requirements and techniques.
59723
End Information
lllllllllllllllllllll
TABLE B2B.—ALTERNATIVE DATA SOURCE FOR FTD LEVEL 5 SMALL, SINGLE ENGINE (RECIPROCATING) AIRPLANE
<<>>
The performance parameters in this table must be used to program the FTD if flight test data is not used to program the FTD.
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 ..................................................
2–4 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
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.
5–15 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.
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.
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2–12 lbs (0.88–5.3 daN) of force (Push).
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59724
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE B2B.—ALTERNATIVE DATA SOURCE FOR FTD LEVEL 5 SMALL, SINGLE ENGINE (RECIPROCATING) AIRPLANE—
Continued
<<>>
The performance parameters in this table must be used to program the FTD if flight test data is not used to program the FTD.
Applicable test
Authorized performance range
Number
Title and procedure
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 not more than three
(3) knots per second
(a) Landing configuration ................................................................
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. ....
Roll response (rate) .........................................................................
Roll rate must be measured through at least 30° of roll.
Aileron control must be deflected 1⁄3 (33.3 percent) of maximum
travel.
Must have a roll rate of 4°–25°/second.
2.d.4.b.
Spiral stability ..................................................................................
Cruise configuration and normal cruise airspeed. Establish a 20°–
30° bank. When stabilized, neutralize the aileron control and
release. Must be completed in both directions of turn.
Initial bank angle (±5°) after 20 seconds.
2.d.6.b.
Rudder response .............................................................................
Use 25 percent of maximum rudder deflection. (Applicable to approach or landing configuration.).
2°–6°/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 .......................................................................
Use 50 percent rudder deflection. (Applicable to approach and
landing configurations.)
2°–10° of bank; 4°–10° of sideslip; and
2°–10° of aileron.
6. FTD System Response Time
6.a. .......
Latency ............................................................................................
Flight deck 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
<<>>
The performance parameters in this table must be used to program the FTD if flight test data is not used to program the FTD.
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.
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Climb rate = 500–1500 fpm (2.5–7.5 m/sec).
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
59725
TABLE B2C.—ALTERNATIVE DATA SOURCE FOR FTD LEVEL 5 SMALL, MULTI-ENGINE (RECIPROCATING) AIRPLANE—
Continued
<<>>
The performance parameters in this table must be used to program the FTD if flight test data is not used to program the FTD.
Applicable test
Authorized performance range
Number
Title and procedure
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.
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.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 not more than three
(3) knots 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
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59726
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE B2C.—ALTERNATIVE DATA SOURCE FOR FTD LEVEL 5 SMALL, MULTI-ENGINE (RECIPROCATING) AIRPLANE—
Continued
<<>>
The performance parameters in this table must be used to program the FTD if flight test data is not used to program the FTD.
Applicable test
Authorized performance range
Number
Title and procedure
2.d.2. ....
Roll response ..................................................................................
Roll rate must be measured through at least 30° of roll. Aileron
control must be deflected 1⁄3 (33.3 percent) of maximum travel.
Must have a roll rate of 4°–25°/second.
2.d.4.b.
Spiral stability ..................................................................................
Cruise configuration and normal cruise airspeed. Establish a 20°–
30° bank. When stabilized, neutralize the aileron control and
release. Must be completed in both directions of turn.
Initial bank angle (±5°) after 20 seconds.
2.d.6.b.
Rudder response .............................................................................
Use 25 percent of maximum rudder deflection. (Applicable to approach or landing configuration.).
3°–6°/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 .......................................................................
Use 50 percent rudder deflection. (Applicable to approach and
landing configurations.)
2°–10° of bank; 4–10 degrees of sideslip; and 2°–10° of aileron.
6. FTD System Response Time
6.a. .......
Flight deck instrument systems response to an abrupt pilot controller input. One test is required in each axis (pitch, roll, yaw).
300 milliseconds or less.
TABLE B2D.—ALTERNATIVE DATA SOURCE FOR FTD LEVEL 5 SMALL, SINGLE ENGINE (TURBO-PROPELLER) AIRPLANE
<<>>
The performance parameters in this table must be used to program the FTD in flight test data is not used to program the FTD.
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 ..................................................
4–8 Seconds.
1.f.2. .....
Deceleration; takeoff power to idle .................................................
3–7 Seconds.
Climb airspeed = 95–115 knots.
Climb rate = 800–1800 fpm (4–9 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.
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
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59727
TABLE B2D.—ALTERNATIVE DATA SOURCE FOR FTD LEVEL 5 SMALL, SINGLE ENGINE (TURBO-PROPELLER) AIRPLANE—
Continued
<<>>
The performance parameters in this table must be used to program the FTD in flight test data is not used to program the FTD.
Applicable test
Authorized performance range
Number
Title and procedure
(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 not more than three
(3) knots 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° of roll. Aileron
control must be deflected 1⁄3 (33.3 percent) of maximum travel.
Must have a roll rate of 4°–25°/second.
2.d.4.b.
Spiral stability ..................................................................................
Cruise configuration and normal cruise airspeed. Establish a 20°–
30° bank. When stabilized, neutralize the aileron control and
release. Must be completed in both directions of turn.
Initial bank angle (±5°) after 20 seconds.
2.d.6.b.
Rudder response .............................................................................
Use 25 percent of maximum rudder deflection. (Applicable to approach or landing configuration.)
3°–6°/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° of bank; 4°–10° of sideslip; and 2°–10° of aileron.
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59728
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE B2D.—ALTERNATIVE DATA SOURCE FOR FTD LEVEL 5 SMALL, SINGLE ENGINE (TURBO-PROPELLER) AIRPLANE—
Continued
<<>>
The performance parameters in this table must be used to program the FTD in flight test data is not used to program the FTD.
Applicable test
Authorized performance range
Number
Title and procedure
6. FTD System Response Time
6.a. .......
Flight deck 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
<<>>
The performance parameters in this table must be used to program the FTD in flight test data is not used to program the FTD.
Applicable test
Authorized performance range
Number
Title and procedure
1. Performance
1.c. .......
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. .....
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
(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
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
59729
TABLE B2E.—ALTERNATIVE DATA SOURCE FOR FTD LEVEL 5 MULTI-ENGINE (TURBO-PROPELLER) AIRPLANE—Continued
<<>>
The performance parameters in this table must be used to program the FTD in flight test data is not used to program the FTD.
Applicable test
Authorized performance range
Number
Title and procedure
(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 not more
than three (3) knots per second.
(a) Landing configuration ................................................................
(b) Clean configuration ....................................................................
80–100 knots; ±5° of bank.
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° of roll. Aileron
control must be deflected 1⁄3 (33.3 percent) of maximum travel.
Must have a roll rate of 4–25 degrees/second.
2.d.4.b.
Spiral stability ..................................................................................
Cruise configuration and normal cruise airspeed. Establish a 20°–
30° bank. When stabilized, neutralize the aileron control and
release. Must be completed in both directions of turn.
Initial bank angle (±5°) after 20 seconds.
2.d.6.b.
Rudder response .............................................................................
Use 25 percent of maximum rudder deflection. (Applicable to approach or landing configuration.)
3°–6°/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 .......................................................................
Use 50 percent rudder deflection. (Applicable to approach and
landing configurations.)
2°–10° of bank;
4°–10° of sideslip; and
2°–10° of aileron.
6. FTD System Response Time
6.a. .......
Flight deck instrument systems response to an abrupt pilot controller input. One test is required in each axis (pitch, roll, yaw).
End QPS Requirements
300 milliseconds or less.
lllllllllllllllllllll
choosing to use alternative sources must
comply with the requirements in Table B2F.
Begin QPS Requirements
End QPS Requirements
5. Alternative Data Sources, Procedures, and
Instrumentation: Level 6 FTD Only
a. Sponsors are not required to use the
alternative data sources, procedures, and
instrumentation. However, any sponsor
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lllllllllllllllllllll
Begin Information
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
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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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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
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.
d. 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 Table
B2F be coordinated with the NSPM prior to
employment 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 three
primary preconditions and presumptions
regarding the objective data and FTD
aerodynamic program modeling.
(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.
f. Table B2F is not applicable to Computer
Controlled Aircraft FTDs.
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
6 FTDs.
h. The term ‘‘inertial measurement system’’
allows the use of a functional global
positioning system (GPS).
End Information
lllllllllllllllllllll
TABLE B2F.—ALTERNATIVE DATA SOURCES, PROCEDURES, AND INSTRUMENTATION LEVEL 6 FTD
<<>>
The standards in this table are required if the data gathering methods described in paragraph 9 of Appendix B are not used.
Objective test reference number and title
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. Hand-record 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. Hand-record 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.
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
59731
TABLE B2F.—ALTERNATIVE DATA SOURCES, PROCEDURES, AND INSTRUMENTATION LEVEL 6 FTD—Continued
<<>>
The standards in this table are required if the data gathering methods described in paragraph 9 of Appendix B are not used.
Objective test reference number and title
Alternative data sources, procedures,
and instrumentation
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.
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.
2.a.8. ...........................................................
Handling qualities
Static control tests
Alignment of power lever angle vs. selected engine parameter (e.g., EPR, N1,
Torque, Manifold pressure).
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 flight deck 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 flight deck 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 flight deck controls.
Gear change dynamics test is acceptable
using the same data acquisition methodology.
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Notes and reminders
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE B2F.—ALTERNATIVE DATA SOURCES, PROCEDURES, AND INSTRUMENTATION LEVEL 6 FTD—Continued
<<>>
The standards in this table are required if the data gathering methods described in paragraph 9 of Appendix B are not used.
Objective test reference number and title
Alternative data sources, procedures,
and instrumentation
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 flight
deck controls position (previously calibrated to show
related surface position) and 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. Hand-record 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 flight deck 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 flight deck controls.
2.c.11. .........................................................
Handling qualities
Longitudinal control tests
Gear and flap/slat operating times.
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 flight deck lateral controls.
2.d.3. ...........................................................
Handling qualities
Lateral directional tests
(a) Roll overshoot
OR
(b) Roll response to flight deck 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 flight deck 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 flight deck 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 flight deck controls.
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Notes and reminders
Airspeeds may be cross checked with
those in the TIR and AFM.
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59733
TABLE B2F.—ALTERNATIVE DATA SOURCES, PROCEDURES, AND INSTRUMENTATION LEVEL 6 FTD—Continued
<<>>
The standards in this table are required if the data gathering methods described in paragraph 9 of Appendix B are not used.
Objective test reference number and title
Alternative data sources, procedures,
and instrumentation
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 flight deck controls.
Attachment 3 to Appendix B to Part 60—
Flight Training Device (FTD) Subjective
Evaluation
lllllllllllllllllllll
Begin Information
1. Discussion
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.
c. 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 specific operation (e.g., 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
<<>>
Number
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 flight deck (or flight deck area) design and functions replicate the appropriate airplane.
2. Surface Operations (pre-takeoff)
2.a. .......
Engine start:
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; 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.
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TABLE B3A.—TABLE OF FUNCTIONS AND SUBJECTIVE TESTS LEVEL 6 FTD—Continued
<<>>
Number
3.b.3. ....
Operations tasks
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.7. ....
In-Flight engine shutdown (procedures only).
4.b.8. ....
In-Flight engine restart (procedures only).
4.b.9. ....
Specific flight characteristics.
4.b.10. ..
Response to loss of flight control power.
4.b.11. ..
Response to other flight control system failure modes.
4.b.12. ..
Operations during icing conditions.
4.b.13. ..
Effects of airframe/engine icing.
4.c. .......
Other flight phase:
4.c.1. ....
Approach to stalls in the following configurations:
4.c.1.a.
Cruise.
4.c.1.b.
Takeoff or approach.
4.c.1.c.
Landing.
4.c.2. ....
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. Approaches
5.a.
5.a.1. ....
With use of autopilot and autothrottle, as applicable.
5.a.2. ....
Without use of autopilot and autothrottle, as applicable.
5.a.3. ....
With 10 knot tail wind.
5.a.4. ....
With 10 knot crosswind.
5.b. .......
Precision Instrument Approaches:
5.b.1. ....
With use of autopilot, autothrottle, and autoland, as applicable.
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TABLE B3A.—TABLE OF FUNCTIONS AND SUBJECTIVE TESTS LEVEL 6 FTD—Continued
<<>>
Number
Operations tasks
5.b.2. ....
Without use of autopilot, autothrottle, and autoland, as applicable.
5.b.3. ....
With 10 knot tail wind.
5.b.4. ....
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. Functions in this section are subject to evaluation only if appropriate for the airplane and/or installed on the specific FTD involved
8.a. .......
Power Switch(es).
8.b. .......
Airplane conditions.
8.b.1. ....
Gross weight, center of gravity, and fuel loading and allocation.
8.b.2. ....
Airplane systems status.
8.b.3. ....
Ground crew functions (e.g., external power, push back).
8.c. .......
Airports.
8.c.1. ....
Selection.
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).
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TABLE B3A.—TABLE OF FUNCTIONS AND SUBJECTIVE TESTS LEVEL 6 FTD—Continued
<<>>
Number
Operations tasks
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
TABLE B3B.—TABLE OF FUNCTIONS AND SUBJECTIVE TESTS LEVEL 5 FTD
<<>>
Number
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 flight deck (or flight deck area) design and functions replicate the appropriate airplane.
2. Surface Operations (pre-takeoff)
2.a. .......
Engine start (if installed):
2.a.1. ....
Normal start.
2.a.2. ....
Alternative procedures start.
2.a.3. ....
Abnormal/Emergency procedures start/shut down.
3. In-Flight Operations
3.a. .......
Normal climb.
3.b. .......
Cruise:
3.b.1. ....
Performance characteristics (speed vs. power).
3.b.2. ....
Normal turns.
3.c. .......
Normal descent.
4. Approaches
4.a. .......
Coupled instrument approach maneuvers (as applicable for the systems installed).
5. Any Flight Phase
5.a. .......
Normal system operation (Installed systems).
5.b. .......
Abnormal/Emergency system operation (installed systems).
5.c. .......
Flap operation.
5.d. .......
Landing gear operation.
5.e. .......
Engine Shutdown and Parking (if installed).
5.e.1. ....
Systems operation.
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TABLE B3B.—TABLE OF FUNCTIONS AND SUBJECTIVE TESTS LEVEL 5 FTD—Continued
<<>>
Number
5.e.2. ....
Operations tasks
Parking brake operation.
6. Instructor Operating Station (IOS)
6.a. .......
Power Switch(es).
6.b. .......
Preset positions—ground, air.
6.c. .......
Airplane system malfunctions (Installed systems).
6.c.1. ....
Insertion/deletion.
6.c.2. ....
Problem clear.
TABLE B3C.—TABLE OF FUNCTIONS AND SUBJECTIVE TESTS LEVEL 4 FTD
<<>>
Number
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 operational system. The NSPM will accomplish a functions check of all installed systems, switches, indicators, and equipment at all crewmembers’ and instructors’ stations, and determine that the flight deck (or flight
deck area) design and functions replicate the appropriate airplane.
Attachment 4 to Appendix B to Part 60—
Sample Documents
lllllllllllllllllllll
Begin Information
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
BILLING CODE 4910–13–P
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
BILLING CODE 4910–13–C
Attachment 5 to Appendix B to Part 60—
FSTD Directives Applicable to Airplane
Flight Training Devices
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.
Table of Contents
1. Introduction
2. Applicability (§ 60.1) and (§ 60.2)
3. Definitions (§ 60.3)
4. Qualification Performance Standards
(§ 60.4)
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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
FSTD (§ 60.14)
11. Initial (and Upgrade) Qualification
Requirements (§ 60.15)
12. Additional Qualifications for a Currently
Qualified FSTDs (§ 60.16)
13. Previously Qualified FSTDs (§ 60.17)
14. Inspection, Continuing Qualification
Evaluation, and Maintenance
Requirements (§ 60.19)
15. Logging FSTD Discrepancies (§ 60.20)
16. Interim Qualification of FSTDs for New
Helicopter Types or Models (§ 60.21)
17. Modifications to FSTDs (§ 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)
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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
Attachment 2 to Appendix C to Part 60—Full
Flight Simulator Objective Tests
Attachment 3 to Appendix C to Part 60—
Simulator Subjective Evaluation
Attachment 4 to Appendix C to Part 60—
Sample Documents
Attachment 5 to Appendix C to Part 60—
FSTD Directives Applicable to
Helicopter Full Flight Simulators
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. Questions regarding the contents of this
publication should be sent to the U.S.
Department of Transportation, Federal
Aviation Administration, Flight Standards
Service, National Simulator Program Staff,
AFS–205, 100 Hartsfield Centre Parkway,
Suite 400, Atlanta, Georgia 30354. Telephone
contact numbers for the NSP are: phone,
404–832–4700; fax, 404–761–8906. The
general e-mail address for the NSP office is:
9-aso-avr-sim-team@faa.gov. The NSP
Internet Web Site address is: https://
www.faa.gov/safety/programs_initiatives/
aircraft_aviation/nsp/. On this Web Site you
will find an NSP personnel list with
telephone and e-mail contact information for
each NSP staff member, a list of qualified
flight simulation devices, advisory circulars,
a description of the qualification process,
NSP policy, and an NSP ‘‘In-Works’’ section.
Also linked from this site are additional
information sources, handbook bulletins,
frequently asked questions, a listing and text
of the Federal Aviation Regulations, Flight
Standards Inspector’s handbooks, and other
FAA links.
c. The NSPM encourages the use of
electronic media for all communication,
including any record, report, request, test, or
statement required by this appendix. The
electronic media used must have adequate
security provisions and be acceptable to the
NSPM. The NSPM recommends inquiries on
system compatibility, and minimum system
requirements are also included on the NSP
Web site.
d. 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) 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.
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(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 and 60.2)
lllllllllllllllllllll
Begin Information
No additional regulatory or informational
material 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 of this part 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
No additional regulatory or informational
material applies to § 60.4, Qualification
Performance Standards.
End Information
lllllllllllllllllllll
5. Quality Management System (§ 60.5)
lllllllllllllllllllll
Begin Information
See Appendix E of this part for additional
regulatory and informational material
regarding Quality Management Systems.
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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 May 30,
2008, the 12-month period begins on the date
of the first continuing qualification
evaluation conducted in accordance with
§ 60.19 after (60 days after date of publication
of the final rule in the Federal Register) and
continues for each subsequent 12-month
period;
(ii) A device qualified on or after May 30,
2008, 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
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
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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
represent 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. FSTD Use (§ 60.11)
lllllllllllllllllllll
Begin Information
No additional regulatory or informational
material applies to § 60.11, FSTD Use.
End Information
lllllllllllllllllllll
9. FSTD Objective Data Requirements
(§ 60.13)
lllllllllllllllllllll
Begin QPS Requirements
a. Flight test data used to validate FFS
performance and handling qualities must
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17:31 Oct 19, 2007
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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 rescaled, 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. The sponsor must—
(1) Within 10 calendar days, notify the
NSPM of the existence of this data; and
(2) Within 45 calendar days, notify the
NSPM of—
(a) The schedule to incorporate this data
into the FFS; or
(b) The reason for not incorporating this
data into the FFS.
e. In those cases where the objective test
results authorize a ‘‘snapshot test’’ or a
‘‘series of snapshot test results’’ in lieu of a
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Sfmt 4702
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.’’ The steady state
condition must exist from 4 seconds prior to,
through 1 second following, the instant of
time captured by the snapshot.
End QPS Requirements
lllllllllllllllllllll
Begin Information
f. 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 who supplied the aircraft
data package for the FFS in order to facilitate
the notification required by § 60.13(f).
g. 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.
h. 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.
i. The NSPM will consider, on a case-bycase basis, whether to approve supplemental
validation data derived from flight data
recording systems such as a Quick Access
Recorder or Flight Data Recorder.
End Information
lllllllllllllllllllll
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10. Special Equipment and Personnel
Requirements for Qualification of the FSTD
(§ 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 users of the
FFS that raise questions about 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:
(a) Objective data obtained from aircraft
testing or another approved source.
(b) Correlating objective test results
obtained from the performance of the FFS as
prescribed in the appropriate QPS.
(c) The result of FFS subjective tests
prescribed in the appropriate 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 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
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17:31 Oct 19, 2007
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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 source of the basic aerodynamic
model and the aerodynamic coefficient data
used to modify the basic model.
(e) The engine model(s) and its data
revision number or reference.
(f) The flight control data revision number
or reference.
(g) The flight management system
identification and revision level.
(h) The FFS model and manufacturer.
(i) The date of FFS manufacture.
(j) The FFS computer identification.
(k) The visual system model and
manufacturer, including display type.
(l) 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 requirement, a
rationale explaining how the referenced
material is used, mathematical equations and
parameter values used, and the conclusions
reached; i.e., that the FFS complies with the
requirement.
(9) Recording procedures or equipment
required to accomplish the objective tests.
(10) The following information for each
objective test designated in Attachment 2,
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59753
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 QTG for
the first helicopter model and a supplement
to that QTG for each additional 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
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
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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 May 30,
2014, 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 May 30, 2014. 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.
l. During the initial (or upgrade)
qualification evaluation conducted by the
NSPM, the sponsor must also provide a
person who is a user of the device (e.g., a
qualified pilot or instructor pilot with flight
time experience in that aircraft) and
knowledgeable about the operation of the
aircraft and the operation of the FFS.
End QPS Requirements
lllllllllllllllllllll
Begin Information
m. 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.
n. 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) 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) Flight deck 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).
(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.
o. 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.
p. 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.
q. 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
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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.
r. 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.
s. After an FFS is successfully evaluated,
the NSPM issues a certificate of qualification
(COQ) to the sponsor. The NSPM
recommends the FFS to the TPAA, who will
approve the FFS for use in a flight training
program. The COQ will be issued at the
satisfactory conclusion of the initial or
continuing qualification evaluation and will
list the tasks for which the FSTD is qualified,
referencing the tasks described in Table C1B
in attachment 1. However, it is the sponsor’s
responsibility to obtain TPAA approval prior
to using the FSTD in an FAA-approved flight
training program.
t. 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.
u. 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.
v. 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).
w. 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
takeoffs and landing from slopes and
pinnacles.
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End Information
lllllllllllllllllllll
12. Additional Qualifications for a Currently
Qualified FSTD (§ 60.16)
No additional regulatory or informational
material applies to § 60.16, Additional
Qualifications for a Currently Qualified FFS.
13. Previously Qualified FSTDs (§ 60.17)
lllllllllllllllllllll
Begin QPS Requirements
a. In instances where a sponsor plans to
remove an 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 May 30,
2008, are not required to meet the general
simulation requirements, the objective test
requirements, and the subjective test
requirements of attachments 1, 2, and 3, of
this appendix as long as the simulator
continues to meet the test requirements
contained in the MQTG developed under the
original qualification basis.
c. After (1 year after date of publication of
the final rule in the Federal Register) each
visual scene or airport model beyond the
minimum required for the FSTD qualification
level that is installed in and available for use
in a qualified FSTD must meet the
requirements described in Attachment 3 of
this appendix.
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
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Jkt 214001
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,
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
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59755
location, including any item found to be
missing, malfunctioning, or inoperative.
d. During the continuing qualification
evaluation conducted by the NSPM, the
sponsor must also provide a person
knowledgeable about the operation of the
aircraft and the operation of the FFS.
e. The NSPM will conduct continuing
qualification evaluations every 12 months
unless:
(1) The NSPM becomes aware of
discrepancies or performance problems with
the device that warrants more frequent
evaluations; or
(2) The sponsor implements a QMS that
justifies less frequent evaluations. However,
in no case shall the frequency of a continuing
qualification evaluation exceed 36 months.
End QPS Requirements
lllllllllllllllllllll
Begin Information
f. 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.
g. 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.
h. 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
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station, and the normal functions and
simulated malfunctions of the simulated
helicopter systems. This examination is
normally accomplished simultaneously with
the subjective evaluation requirements.
Begin Information
16. Interim Qualification of FSTDs for New
Helicopter Types or Models (§ 60.21)
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
15. Logging FSTD Discrepancies (§ 60.20)
lllllllllllllllllllll
Begin Information
No additional regulatory or informational
material applies to § 60.20. Logging FFS
Discrepancies.
End Information
lllllllllllllllllllll
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)
lllllllllllllllllllll
Begin Information
No additional regulatory or informational
material applies to § 60.33, Applications,
Logbooks, Reports, and Records: Fraud,
Falsification, or Incorrect Statements.
lllllllllllllllllllll
End Information
23. [Reserved]
Begin Information
lllllllllllllllllllll
24. [Reserved]
No additional regulatory or informational
material applies to § 60.21, Interim
Qualification of FFSs for New Helicopter
Types or Models.
19. Automatic Loss of Qualification and
Procedures for Restoration of Qualification
(§ 60.27)
End Information
Begin Information
lllllllllllllllllllll
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.
25. FSTD Qualification on the Basis of a
Bilateral Aviation Safety Agreement (BASA)
(§ 60.37)
No additional regulatory or informational
material applies to § 60.37, FSTD
Qualification on the Basis of a Bilateral
Aviation Safety Agreement (BASA).
lllllllllllllllllllll
17. Modifications to FSTDs (§ 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
(3) FSTD Directives are considered
modifications of an FFS. See Attachment 4
for a sample index of effective FSTD
Directives. See Attachment 6 for a list of all
effective FSTD Directives applicable to
Helicopter FFSs.
End Information
lllllllllllllllllllll
18. Operation with Missing, Malfunctioning,
or Inoperative Components (§ 60.25)
lllllllllllllllllllll
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End Information
Attachment 1 to Appendix C to Part 60—
General Simulator Requirements
lllllllllllllllllllll
Begin QPS Requirements
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.
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 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 Information
lllllllllllllllllllll
End QPS Requirements
lllllllllllllllllllll
21. Recordkeeping and Reporting (§ 60.31)
lllllllllllllllllllll
Begin Information
End Information
lllllllllllllllllllll
20. Other Losses of Qualification and
Procedures for Restoration of Qualification
(§ 60.29)
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
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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.
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b. The material contained in this
attachment is divided into the following
categories:
(1) General flight deck 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.
d. Table C1B provides the tasks that the
sponsor will examine to determine whether
the FSTD satisfactorily meets the
requirements for flight crew training, testing,
and experience, and provides the tasks for
which the simulator may be qualified.
e. Table C1C provides the functions that an
instructor/check airman must be able to
control in the simulator.
59757
f. It is not required that all of the tasks that
appear on the List of Qualified Tasks (part of
the SOQ) be accomplished during the initial
or continuing qualification evaluation.
g. Table C1A addresses only Levels B, C,
and D helicopter simulators because there are
no Level A Helicopter simulators.
End Information 1
lllllllllllllllllllll
TABLE C1A.—MINIMUM SIMULATOR REQUIREMENTS
<<>>
Number
<>
Simulator levels
General Simulator Requirements
B
C
D
Notes
For simulator purposes, the flight deck 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
items such as landing gear pin storage compartments, fire axes or extinguishers, spare light bulbs,
and aircraft documents pouches are not considered
essential and may be omitted.
1. General Flight Deck Configuration
1.a. .......
The simulator must have a flight deck that is a replica of
the helicopter being simulated. The simulator must
have controls, equipment, observable flight deck 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 flight deck windows must be
included, but the actual windows need not be operable. 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
1.b. .......
Those circuit breakers that affect procedures and/or result in observable flight deck indications must be
properly located and functionally accurate
An SOC is required.
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 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:
A subjective test is required.
2.c.1. ....
Ground effect ....................................................................
X
X
X
Applicable areas include flare and touch down from a
running landing as well as for in-ground-effect (IGE)
hover. A reasonable simulation of ground effect includes modeling of lift, drag, pitching moment, trim,
and power while in ground effect.
Level B does not require hover programming.
An SOC is required.
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TABLE C1A.—MINIMUM SIMULATOR REQUIREMENTS—Continued
<<>>
Number
<>
Simulator levels
General Simulator Requirements
2.c.2. ....
B
C
D
Notes
Ground reaction ................................................................
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) may differ with changes in
gross weight, airspeed, rate of descent on touchdown,
and slide slip.
X
X
This may include an automated system, which could be
used for conducting at least a portion of the QTG
tests. Automatic ‘‘flagging’’ of out-of-tolerance situations is encouraged.
Level B does not require hover programming.
An SOC is required.
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. .......
The relative responses of the motion system, visual system, and flight deck instruments must be 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. ....
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 simulate brake and tire failure dynamics (including antiskid failure, if appropriate).
X
X
Simulator pitch, side loading, and directional control
characteristics should be representative of the helicopter.
X
X
See Attachment 2 for further information on ground effect.
X
X
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
An SOC is required.
2.g. .......
The aerodynamic modeling in the simulator must include:
(1) Ground effect,
(2) Effects of airframe and rotor icing (if applicable),.
(3) Aerodynamic interference effects between the
rotor wake and fuselage,.
(4) Influence of the rotor on control and stabilization
systems,.
(5) Representations of settling with power, and.
(6) Retreating blade stall..
An SOC is required.
A demonstration of icing effects (if applicable) is required.
2.h. .......
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
3. Equipment Operation
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59759
TABLE C1A.—MINIMUM SIMULATOR REQUIREMENTS—Continued
<<>>
Number
<>
Simulator levels
General Simulator Requirements
B
C
D
3.a. .......
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 helicopter 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. .......
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 the helicopter under the same flight
conditions.
An objective test is required.
X
X
X
3.e. .......
Simulator control feel dynamics must replicate the helicopter simulated. This must be determined by comparing a recording of the control feel dynamics of the
simulator to helicopter measurements. For initial and
upgrade evaluations, the control dynamic characteristics must be measured and recorded directly from the
flight deck controls, and must be accomplished in
takeoff, cruise, and landing conditions and configurations.
Objective tests are required.
X
Notes
X
See Attachment 3 for further information regarding longrange navigation equipment.
4. Instructor/Evaluator Facilities
4.a. .......
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 ability to present ground and air hazards.
A subjective test is required.
X
X
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The NSPM will consider alternatives to this standard for
additional seats based on unique flight deck configurations.
For example, another aircraft crossing the active runway
and converging airborne traffic.
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TABLE C1A.—MINIMUM SIMULATOR REQUIREMENTS—Continued
<<>>
Number
General Simulator Requirements
4.e. .......
<>
Simulator levels
B
C
D
Notes
X
X
This is a selectable condition that is not required for all
operations on or near the ground.
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 simulator must provide the instructor or evaluator
the ability to present the effect of re-circulating dust or
snow conditions that develop as a result of rotor
downwash.
A subjective test is required.
5. Motion System
5.a. .......
The simulator must have motion (force) cues perceptible
to the pilot that are representative of the motion in a
helicopter.
X
A subjective test is required.
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.
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 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.
X
(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.
X
For air turbulence, general purpose disturbance models
that approximate demonstrable flight test data are acceptable.
5.f. ........
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 flight deck.
A subjective test is required.
An objective test is required.
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-of-the-flight deck view.
A subjective test is required.
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Additional horizontal field of view capability may be
added at the sponsor’s discretion provided the minimum field of view is retained.
X
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X
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TABLE C1A.—MINIMUM SIMULATOR REQUIREMENTS—Continued
<<>>
Number
<>
Simulator levels
General Simulator Requirements
B
6.b. .......
The simulator must provide a continuous field of view of
at least 75° horizontally and 30° vertically per pilot
seat. Both pilot seat visual systems must be operable
simultaneously. The minimum horizontal field of view
coverage must be plus and minus one-half (1⁄2) of the
minimum continuous field of view requirement, centered on the zero degree azimuth line relative to the
aircraft fuselage. An SOC must explain the geometry
of the installation.
An SOC is required.
X
6.c. .......
The simulator must provide a continuous visual field of
view of at least 146° horizontally and 36° 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. The minimum horizontal field of
view coverage must be plus and minus one-half (1⁄2)
of the minimum continuous field of view requirement,
centered on the zero degree azimuth line relative to
the aircraft fuselage. An SOC must explain the geometry of the installation. Capability for a field of view in
excess of the minimum is not required for qualification
at Level C. However, where specific tasks require extended fields of view beyond the 146° by 36° (e.g., to
accommodate the use of ‘‘chin windows’’ where the
accommodation is either integral with or separate
from the primary visual system display), then the extended fields of view must be provided. When considering the installation and use of augmented fields of
view, the sponsor must meet with the NSPM to determine the training, testing, checking, and experience
tasks for which the augmented field of view capability
may be required.
An SOC is required.
A subjective test is required.
6.d. .......
The simulator must provide a continuous visual field of
view of at least 176° horizontally and 56° 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. The minimum horizontal field of
view coverage must be plus and minus one-half (1⁄2)
of the minimum continuous field of view requirement,
centered on the zero degree azimuth line relative to
the aircraft fuselage. An SOC must explain the geometry of the installation. Capability for a field of view in
excess of the minimum is not required for qualification
at the Zero Flight Time (ZFT) level. However, where
specific tasks require extended fields of view beyond
the 176° by 56° (e.g., to accommodate the use of
‘‘chin windows’’ where the accommodation is either
integral with or separate from the primary visual system display), then the extended fields of view must be
provided. When considering the installation and use
of augmented fields of view, the sponsor must meet
with the NSPM to determine the training, testing,
checking, and experience tasks for which the augmented field of view capability may be required.
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.
C
D
X
Notes
Optimization of the vertical field of view may be considered with respect to the specific helicopter flight deck
cut-off angle. The sponsor may request the NSPM to
evaluate the FFS for specific authorization(s) for the
following:
(1) Specific areas within the database needing higher
resolution to support landings, take-offs and ground
cushion exercises and training away from a heliport,
including elevated heliport, helidecks and confined
areas.
(2) For cross-country flights, sufficient scene details to
allow for ground to map navigation over a sector
length equal to 30 minutes at an average cruise
speed.
(3) For offshore airborne radar approaches (ARA), harmonized visual/radar representations of installations.
X
X
X
Optimization of the vertical field of view may be considered with respect to the specific airplane flight deck
cut-off angle. The sponsor may request the NSPM to
evaluate the FFS for specific authorization(s) for the
following:
(1) Specific areas within the database needing higher
resolution to support landings, take-offs and ground
cushion exercises and training away from a heliport,
including elevated heliport, helidecks and confined
areas.
(2) For cross-country flights, sufficient scene details to
allow for ground to map navigation over a sector
length equal to 30 minutes at an average cruise
speed.
(3) For offshore airborne radar approaches (ARA), harmonized visual/radar representations of installations.
X
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.
A subjective test is required.
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TABLE C1A.—MINIMUM SIMULATOR REQUIREMENTS—Continued
<<>>
Number
<>
Simulator levels
General Simulator Requirements
B
C
D
6.f. ........
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) Visibility in statute miles (kilometers) and runway visual range (RVR) in ft. (meters).
(2) Airport or landing area selection.
(3) Airport or landing area lighting.
A subjective test is required.
X
X
X
6.h. .......
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
6.i. ........
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) arcminutes resolution on day scenes.
A subjective test is required.
X
X
X
6.j. ........
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 flight deck is the
same as from the helicopter flight deck (within established tolerances) when at the correct airspeed and
altitude, at a main wheel height of 100 feet (30 meters) above the touchdown zone.
An SOC is required.
An objective test is required.
X
X
X
This will show the modeling accuracy of the scene with
respect to a pre-determined position from the end of
the runway ‘‘in use.’’
6.l. ........
The simulator must provide visual cues necessary to assess rate of change of height, height AGL, and
translational displacement and rates during takeoffs
and landings.
A subjective test is required.
X
6.m. ......
The simulator must have night and dusk (or twilight) visual scene capability, including general terrain characteristics and significant landmarks, free from apparent
quantization. The dusk (or twilight) scene must enable
identification of a visible horizon and general terrain
characteristics.
A subjective test is required.
X
X
Examples of general terrain characteristics are fields,
roads, and bodies of water.
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59763
TABLE C1A.—MINIMUM SIMULATOR REQUIREMENTS—Continued
<<>>
Number
<>
Simulator levels
General Simulator Requirements
B
6.n. .......
6.o. .......
The simulator must provide for accurate portrayal of the
visual environment relating to the simulator attitude.
X
D
X
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.
C
X
X
X
Notes
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.
6.p ........
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 be capable of producing at least 10
levels of occulting.
A subjective test is required.
X
X
6.r. ........
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
6.s. .......
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
X
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59764
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE C1A.—MINIMUM SIMULATOR REQUIREMENTS—Continued
<<>>
Number
General Simulator Requirements
6.t. ........
<>
Simulator levels
B
C
Daylight Visual Scenes. The simulator must have 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. No ambient lighting may ‘‘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.
D
Notes
X
A subjective test is required.
Objective tests are required.
6.w. ......
The simulator must provide operational visual scenes
that portray physical relationships known to cause
landing illusions to pilots.
A subjective test is required.
X
6.x. .......
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
snow-covered runways, including runway lighting reflections for wet conditions, and partially obscured
lights for snow conditions.
A subjective test is required.
X
6.z. .......
The simulator must present realistic
directionality of all airport lighting.
A subjective test is required.
X
7.a. .......
The simulator must provide flight deck 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 flight deck 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.
An objective test is required.
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For example: short runways, landing approaches over
water, uphill or downhill runways, rising terrain on the
approach path, unique topographic features.
The NSPM will consider suitable alternative effects.
X
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59765
TABLE C1B.—TABLE OF TASKS VS. SIMULATOR LEVEL
<<>>
Number
Simulator levels
Subjective Requirements
The simulator must be able to perform the tasks associated with that level of qualification.
B
C
D
X
X
X
1. Preflight Procedures
1.a. ......
Preflight Inspection (Flight deck only) switches, indicators, systems, and equipment ..............
1.b. ......
APU/Engine start and run-up.
1.b.1. ...
Normal start procedures .............................................................................................................
X
X
X
1.b.2. ...
Alternate start procedures ..........................................................................................................
X
X
X
1.b.3. ...
Abnormal starts and shutdowns (hot start, hung start) .............................................................
X
X
X
1.c. .......
Taxiing—Ground ........................................................................................................................
X
X
X
1.d. ......
Taxiing—Hover ...........................................................................................................................
X
X
X
1.e. ......
Pre-takeoff Checks .....................................................................................................................
X
X
X
2. Takeoff and Departure Phase
2.a. ......
Normal takeoff
2.a.1. ...
From ground ...............................................................................................................................
X
X
X
2.a.2. ...
From hover .................................................................................................................................
X
X
X
2.a.3. ...
Running ......................................................................................................................................
X
X
X
2.b. ......
Instrument ...................................................................................................................................
X
X
X
2.c. .......
Powerplant Failure During Takeoff ............................................................................................
X
X
X
2.d. ......
Rejected Takeoff ........................................................................................................................
X
X
X
2.e. ......
Instrument Departure .................................................................................................................
X
X
X
3.a. ......
Normal ........................................................................................................................................
X
X
X
3.b. ......
Obstacle clearance .....................................................................................................................
X
X
X
3.c. .......
Vertical ........................................................................................................................................
X
X
X
3.d. ......
One engine inoperative ..............................................................................................................
X
X
X
3. Climb
4. In-flight Maneuvers
4.a. ......
Turns (timed, normal, steep) ......................................................................................................
X
X
X
4.b. ......
Powerplant Failure—Multiengine Helicopters ............................................................................
X
X
X
4.c. .......
Powerplant Failure—Single-Engine Helicopters ........................................................................
X
X
X
4.d. ......
Recovery From Unusual Attitudes .............................................................................................
X
X
X
4.e. ......
Settling with Power .....................................................................................................................
X
X
X
4.f. .......
Specific Flight Characteristics incorporated into the user’s FAA approved flight training program.
A
A
A
5. Instrument Procedures
5.a. ......
Instrument Arrival .......................................................................................................................
X
X
X
5.b. ......
Holding .......................................................................................................................................
X
X
X
5.c. .......
Precision Instrument Approach
5.c.1. ....
Normal—All engines operating ..................................................................................................
X
X
X
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Notes
59766
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE C1B.—TABLE OF TASKS VS. SIMULATOR LEVEL—Continued
<<>>
Number
Simulator levels
Subjective Requirements
The simulator must be able to perform the tasks associated with that level of qualification.
B
C
D
5.c.2. ....
Manually controlled—One or more engines inoperative ............................................................
X
X
X
5.d. ......
Non-precision Instrument Approach ...........................................................................................
X
X
X
5.e. ......
Missed Approach
5.e.1. ...
All engines operating ..................................................................................................................
X
X
X
5.e.2. ...
One or more engines inoperative ..............................................................................................
X
X
X
5.e.3. ...
Stability augmentation system failure ........................................................................................
X
X
X
X
X
X
6. Landings and Approaches to Landings
6.a. ......
Visual Approaches (normal, steep, shallow) ..............................................................................
6.b. ......
Landings
6.b.1. ...
Normal/crosswind
6.b.1.a.
Running ......................................................................................................................................
X
X
X
6.b.1.b.
From Hover ................................................................................................................................
X
X
X
6.b.2. ...
One or more engines inoperative ..............................................................................................
X
X
X
6.b.3. ...
Rejected Landing .......................................................................................................................
X
X
X
7. Normal and Abnormal Procedures
7.a. ......
Powerplant ..................................................................................................................................
X
X
X
7.b. ......
Fuel System ...............................................................................................................................
X
X
X
7.c. .......
Electrical System ........................................................................................................................
X
X
X
7.d. ......
Hydraulic System .......................................................................................................................
X
X
X
7.e. ......
Environmental System(s) ...........................................................................................................
X
X
X
7.f. .......
Fire Detection and Extinguisher Systems ..................................................................................
X
X
X
7.g. ......
Navigation and Aviation Systems ..............................................................................................
X
X
X
7.h. ......
Automatic Flight Control System, Electronic Flight Instrument System, and Related Subsystems.
X
X
X
7.i. ........
Flight Control Systems ...............................................................................................................
X
X
X
7.j. ........
Anti-ice and Deice Systems .......................................................................................................
X
X
X
7.k. .......
Aircraft and Personal Emergency Equipment ............................................................................
X
X
X
7.l. ........
Special Missions tasks (e.g., Night Vision goggles, Forward Looking Infrared System, External Loads and as may be listed on the Statement of Qualification.).
A
A
X
8. Emergency Procedures (as applicable)
8.a. ......
Emergency Descent ...................................................................................................................
X
X
X
8.b. ......
Inflight Fire and Smoke Removal ...............................................................................................
X
X
X
8.c. .......
Emergency Evacuation ..............................................................................................................
X
X
X
8.d. ......
Ditching .......................................................................................................................................
X
X
X
8.e. ......
Autorotative Landing ..................................................................................................................
X
X
X
8.f. .......
Retreating blade stall recovery ..................................................................................................
X
X
X
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Notes
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
59767
TABLE C1B.—TABLE OF TASKS VS. SIMULATOR LEVEL—Continued
<<>>
Number
Simulator levels
Subjective Requirements
The simulator must be able to perform the tasks associated with that level of qualification.
B
C
D
8.g. ......
Mast bumping .............................................................................................................................
X
X
X
8.h. ......
Loss of tail rotor effectiveness ...................................................................................................
X
X
X
X
X
Information
X
Notes
9. Postflight Procedures
9.a. ......
After-Landing Procedures ..........................................................................................................
9.b. ......
Parking and Securing
9.b.1. ...
Rotor brake operation ................................................................................................................
X
X
X
9.b.2. ...
Abnormal/emergency procedures ..............................................................................................
X
X
X
Note: An ‘‘A’’ in the table indicates that the system, task, or procedure may be examined if the appropriate aircraft system or control is simulated in the FSTD and is working properly.
TABLE C1C.—TABLE OF TASKS VS. SIMULATOR LEVEL
<<>>
Number
Subjective requirements
The simulator must be able to perform the tasks associated with that level of qualification
Information
notes
Simulator levels
B
C
D
1. ..........
Instructor Operating Station (IOS), as appropriate
1.a. .......
Power switch(es) ..............................................................
X
X
X
1.b. .......
Helicopter conditions ........................................................
X
X
X
e.g., GW, CG, Fuel loading, Systems, Ground Crew.
1.c. .......
Airports/Heliports/Helicopter Landing Areas ....................
X
X
X
e.g., Selection, Surface, Presets, Lighting controls.
1.d. .......
Environmental controls .....................................................
X
X
X
e.g., Clouds, Visibility, RVR, Temp, Wind, Ice, Snow,
Rain, and Windshear.
1.e. .......
Helicopter system malfunctions (Insertion/deletion) ........
X
X
X
1.f. ........
Locks, Freezes, and Repositioning ..................................
X
X
X
2. ..........
Sound Control
2.a. .......
On/off/adjustment .............................................................
X
X
X
3. ..........
Motion/Control Loading System
3.a. .......
On/off/emergency stop .....................................................
X
X
X
4. ..........
Observer Seats/Stations
4.a. .......
Position/Adjustment/Positive restraint system .................
X
X
X
Attachment 2 to Appendix C to Part 60—Full
Flight Simulator Objective Tests
lllllllllllllllllllll
Begin Information
TABLE OF CONTENTS
Paragraph
No.
Title
1. ..................
Introduction.
2. ..................
Test Requirements.
Table C2A, Objective Test.
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59768
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE OF CONTENTS—Continued
Paragraph
No.
Title
3. ..................
General.
4. ..................
Control Dynamics.
5. ..................
[Reserved].
6. ..................
Motion System.
7. ..................
Sound System.
8. ..................
Additional Information About Flight Simulator Qualification for New or Derivative Helicopter.
9. ..................
Engineering Simulator—Validation Data.
10. ................
[Reserved].
11. ................
Validation Test Tolerances.
12. ................
Validation Data Roadmap.
13. ................
Acceptance Guidelines for Alternative Engines Data.
14. ................
Acceptance Guidelines for Alternative Avionics (Flights-Related Computers and Controllers).
15. ................
Transport Delay Testing.
16 .................
Continuing Qualification Evaluations—Validation Test Data Presentation.
17 .................
Alternative Data Sources, Procedures, and Instrumentation: Level A and Level B Simulators Only.
1. Introduction
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).
c. Table C2A addresses helicopter
simulators at Levels B, C, and D because
there are no Level A Helicopter simulators.
End Information
lllllllllllllllllllll
Begin QPS Requirements
2. Test Requirements
A. The ground and flight tests required for
qualification are listed in Table C2A. FFS
Objective Tests. Computer generated
simulator tests 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 be
qualification level sought, it may be
disregarded (e.g., an engine out missed
approached for a single-engine helicopter, or
a hover test for a Level B simulator) Each test
result if compared against the validation data
described in § 6013 and in this appendix.
Although use of a driver program designed to
automatically accomplish the test is
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encouraged for all simulators and required
for level C and Level D simulators, each test
must be able to be accomplished manually
while recording all appropriate parameters.
The request must be produced on an
appropriate recording device accepted to the
NSPM and must include simulator number,
data, time, condition, 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 value 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 may 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
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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. The FFS may not be programmed so that
the mathematical modeling is correct 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 mid-conditions or as
close as possible to the other extreme must
be included. 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
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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.’’ The steady state
condition must exist from 4 seconds prior to,
through 1 second following, the instant of
time captured by the snap shot.
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,
identifiable reference points and must 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 effect 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 flight deck (e.g., ‘‘helicopter
modular controller’’). These exceptions are
noted in Table C2A of this attachment.
However, in these cases, the sponsor must
59769
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 within 10 percent 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 C2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS
<<>>
<>
Test
Simulator level
Tolerance(s)
Number
Flight condition
Test details
Notes
Title
B
C
D
1. Performance
1.a. ........
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, if
applicable.
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, or ±0.5%
change of rotor 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%,
1.5%.
Climb and 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. ........
Surface Operations
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59770
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TABLE C2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
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Test
Simulator level
Tolerance(s)
Flight condition
Test details
Number
1.b.1. .....
Minimum Radius Turn ......
±3 ft. (0.9m) or 20% of helicopter turn radius.
Ground ......................
1.b.2. .....
Rate of Turn vs. Pedal
Deflection, Brake Application, or Nosewheel
Angle, as applicable.
±10% or ±2°/sec. Turn Rate .......
1.b.3. .....
Taxi ..................................
1.b.4. .....
Brake Effectiveness .........
1.c. ........
Takeoff
1.c.1. .....
Notes
Title
B
C
D
If brakes are used,
brake pedal position and brake system pressure must
be matched to the
helicopter flight test
value.
X
X
X
Ground Takeoff .........
If brakes are used,
brake pedal position and brake system pressure must
be matched to the
helicopter flight test
value.
X
X
X
Pitch Angle—±1.5°, Torque—
±3%, Longitudinal Control Position—±5%, Lateral Control
Position—±5%,
Directional
Control Position ±5%, Collective Control Position—±5%.
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
±10% of time and distance .........
Ground ......................
X
X
X
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
continued takeoff.
Airspeed—±3 kt, Altitude—±20 ft Ground/Takeoff; and
(6.1m), Torque—±3%, Rotor
Initial Segment of
Speed—±1.5%,Vertical VelocClimb.
ity—±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%.
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.c.3. .....
One Engine inoperative,
rejected takeoff.
Airspeed ± 3 kt; Altitude ± 20 ft
(6.1m), Torque ± 3%, Rotor
Speed ± 1.5%, Pitch Attitude ±
1.5°, Roll angle ± 1.5°, Heading ± 2°, Longitudinal Control
Position ± 10%, Lateral Control Position ± 10%, Directional
Control Position ± 10%, Collective Control Position ± 10%,
Distance: ± 7.5% or ± 30m
(100ft).
Time history from the
takeoff point to
touchdown. Test
conditions near limiting performance.
X
X
1.d. ........
Hover
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59771
TABLE C2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
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Test
Simulator level
Tolerance(s)
Number
D
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
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
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%.
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
X
Level Flight
Performance and
Trimmed Flight Control
Positions.
1.g. ........
Notes
C
Vertical Climb
Performance .....................
1.f. .........
Test details
B
Performance .....................
1.e. ........
Flight condition
Title
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
(5 m/sec) 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.
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 10%, 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.) Data must
be recorded for
speeds from 50 kts,
±5 kts through at
least maximum
glide distance airspeed. May be a
series of snapshot
tests.
X
X
X
1.i. .........
Autorotation
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This test validates
performance at
speeds above maximum endurance
airspeed.
59772
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TABLE C2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
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Test
Simulator level
Tolerance(s)
Number
Flight condition
Test details
Notes
Title
B
Entry .................................
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 .........
D
X
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.
C
X
1.j. .........
Landing
1.j.1. ......
All Engines .......................
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 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
1.j.2. ......
One Engine Inoperative ...
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 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
1.j.3. ......
Balked Landing ................
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
1.j.4. ......
Autorotational Landing .....
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 Characteristics
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
59773
TABLE C2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
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Test
Simulator level
Tolerance(s)
Number
Flight condition
Test details
Notes
Title
B
C
D
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 flight deck controls, and must be accomplished in hover, climb,
cruise, and autorotation.
Contact the NSPM for
clarification of any
issue regarding helicopters with reversible controls or
where the required
validation data is
not attainable.
2.a.1. .....
Cyclic ................................
Breakout—±0.25 lbs (0.112 daN)
or 25%; Force—±1.0 lb (0.224
daN) or 10%.
Ground; Static conditions with the hydraulic system (if
applicable) pressurized; supplemental
hydraulic pressurization system may
be used. Trim On
and Off. Friction Off
Augmentation (if
applicable) 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.)
X
X
X
Flight Test Data for
this test does not
require the rotor to
be engaged/turning. The phrase ‘‘if
applicable’’ regarding stability augmentation systems
means if an augmentation system
is available and if
this system may be
operational on the
ground under static
conditions as described here.
2.a.2. .....
Collective/Pedals ..............
Breakout—±0.5 lb (0.224 daN)
or 25%; Force—±1.0 lb (0.224
daN) or 10%.
Ground; Static conditions with the hydraulic system (if
applicable) pressurized; supplemental
hydraulic pressurization system may
be used. Trim On
and Off. Friction
Off. Augmentation
(if applicable) On
and Off.
Record results for an
uninterrupted control sweep to the
stops.
X
X
X
Flight Test Data for
this test does not
require the rotor to
be engaged/turning. The phrase ‘‘if
applicable’’ regarding stability augmentation system
means if a stability
augmentation system is available
and if this system
may be operational
on the ground
under static conditions as described
here.’’
2.a.3. .....
Brake Pedal Force vs. Position.
±5 lbs (2.224 daN) or 10% .........
Ground; Static conditions.
...................................
X
X
X
2.a.4. .....
Trim System Rate (all applicable systems).
Rate—±10% ...............................
Ground; Static conditions. Trim On,
Friction Off.
The tolerance applies
to the recorded
value of the trim
rate.
X
X
X
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.
Results must be recorded for a normal
control displacement in both directions in each axis.
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.
59774
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE C2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
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<>
Test
Simulator level
Tolerance(s)
Number
2.a.6. .....
Control System Freeplay
2.b. ........
Trimmed Flight Control
Positions.
2.b.2. .....
Critical Azimuth ................
2.b.3. .....
Notes
Control Response
2.b.3.a. ..
Test details
Low Airspeed Handling Qualities
2.b.1. .....
Flight condition
Title
B
±2% control displacement, but
not to exceed ±0.15 in.
C
D
X
X
X
Ground; Static conditions; with the hydraulic system (if
applicable) pressurized; supplemental
hydraulic pressurization system may
be used.
Record and compare
results for all controls.
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.
Record results for
several airspeed increments to the
translational airspeed limits and for
45 kts forward airspeed. May be a
series of snapshot
tests.
X
X
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%.
Stationary Hover.
Augmentation On
and Off.
Record results for
three relative wind
directions (including
the most critical
case) in the critical
quadrant. May be a
series of snapshot
tests.
X
X
Longitudinal ......................
Pitch 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
This is a ‘‘short time’’
test conducted in a
hover, in ground effect, without entering translational
flight, to provide
better visual reference.
2.b.3.b. ..
Lateral ..............................
Roll Rate—±10% or ±3°/sec.
Roll Attitude Change—±10%
or ±3°.
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
This is a ‘‘short time’’
test conducted in a
hover, in ground effect, without entering translational
flight, to provide
better visual reference.
2.b.3.c. ..
Directional ........................
Yaw Rate—±10% or ±2°/sec,
Heading Change—±10% or
±2°.
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
This is a ‘‘short time’’
test conducted in a
hover, in ground effect, without entering translational
flight, to provide
better visual reference.
2.b.3.d. ..
Vertical .............................
Normal Acceleration—±0.1 g .....
Hover ........................
Record results for a
step control input.
The Off-axis response must show
correct trend for
unaugmented
cases.
X
X
2.c. ........
Longitudinal Handling Qualities
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Flight Test Data for
this test does not
require the rotor to
be engaged/turning.
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
59775
TABLE C2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
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Test
Simulator level
Tolerance(s)
Flight condition
Test details
Number
2.c.1. .....
Control Response ............
Pitch Rate—±10% or ±2°/sec,
Pitch Attitude Change—±10%
or ±1.5°.
Cruise Augmentation
On and Off.
2.c.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%.
2.c.3. .....
Dynamic Stability
2.c.3.a. ..
Long Term Response ......
2.c.3.b. ..
Notes
Title
B
C
D
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
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
±10% of calculated period, ±10%
of time to 1⁄2 or double amplitude, or ±0.02 of damping
ratio. For non-periodic responses, the time history must
be matched within ±10% pitch;
and ±10% airspeed over a 20sec period following release of
the controls.
Cruise Augmentation
On and Off.
For periodic responses, 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 non-periodic responses, the test
may be terminated
prior to 20 sec if
the test pilot determines that the results are becoming
uncontrollably divergent.
X
X
X
The response may be
unrepeatable
throughout the stated time for certain
helicopters. In
these cases, the
test should show at
least that a divergence is identifiable. For example:
displacing the cyclic for a given time
normally excites
this test or until a
given pitch attitude
is achieved and
then return the cyclic to the original
position.
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
A control doublet inserted at the natural frequency of
the aircraft normally
excites this test.
2.c.4. .....
Maneuvering Stability .......
Longitudinal Control Position—
10% of change from trim or
±0.25 in. (6.3 mm) 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
at 30°-45° roll
angle. The force
may be shown as a
cross plot for irreversible systems.
May be a series of
snapshot tests.
X
X
X
2.d. ........
Lateral and Directional Handling Qualities
2.d.1. .....
Control Response
2.d.1.a. ..
Lateral ..............................
Cruise Augmentation
On and Off.
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
Off-axis response
must show correct
trend for unaugmented cases.
X
X
X
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Roll Rate—±10% or ±3°/sec.,
Roll Attitude Change—±10%
or ±3°.
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59776
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE C2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
<>
Test
Simulator level
Tolerance(s)
Flight condition
Test details
Number
2.d.1.b. ..
Directional ........................
Yaw Rate—±10% or ±2°/sec.,
Yaw Attitude Change—±10%
or ±2°.
Cruise Augmentation
On and Off.
2.d.2. .....
Directional Static Stability
Lateral Control Position—±10%
of change from trim or ±0.25
in. (6.3 mm) 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. (6.3 mm) or Directional Control Force—±1 lb.
(0.448 daN) or 10%., Longitudinal Control Position—±10%
of change from trim or ±0.25
in. (6.3 mm), Vertical Velocity—±100 fpm (0.50m/sec) or
10%.
2.d.3. .....
Dynamic Lateral and Directional Stability
2.d.3.a. ..
Lateral-Directional Oscillations.
2.d.3.b. ..
Spiral Stability ..................
Notes
Title
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B
C
D
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% or ±1 sec of time
difference between peaks of
bank and sideslip. For nonperiodic responses, the time
history must be matched within ±10% yaw; ±10% roll angle,
and ±10% airspeed, over a 20
sec period roll angle following
release of the controls.
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 or
double amplitude,
whichever is less.
For non-periodic response, the test
may be terminated
prior to 20 sec if
the test pilot determines that the results are becoming
uncontrollably divergent.
X
X
X
±2° or ±10% roll angle ................
Cruise or Climb. Augmentation On and
Off.
Record the results of
a release from
pedal only or cyclic
only turns for 20
sec. Results must
be recorded from
turns in both directions. Terminate
check at zero roll
angle or when the
test pilot determines that the attitude is becoming
uncontrollably divergent.
X
X
X
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This is a steady
heading sideslip
test.
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
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TABLE C2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
<>
Test
Simulator level
Tolerance(s)
Number
2.d.3.c. ..
Adverse/Proverse Yaw ....
Flight condition
Test details
Notes
Title
B
Correct Trend,
sideslip angle.
±2°
C
D
transient
Cruise or Climb. Augmentation On and
Off.
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.
X
X
X
Based on Simulator Capability ...
N/A ............................
Required as part of
MQTG but not required as part of
continuing qualification evaluations.
The test must demonstrate frequency
response of the
motion system as
specified by the applicant for flight
simulator qualification.
X
X
X
Based on Simulator Capability ...
N/A ............................
Required as part of
MQTG but not required as part of
continuing evaluations. The test must
demonstrate motion
system leg balance
as specified by the
applicant for flight
simulator qualification.
X
X
X
Based on Simulator Capability ...
N/A ............................
Required as part of
MQTG but not required as part of
continuing qualification evaluations.
The test must demonstrate a smooth
turn-around (shift to
opposite direction
of movement) of
the motion system
as specified by the
applicant for flight
simulator qualification.
X
X
X
3. Motion System
3.a. ........
3.b. ........
Frequency Response
Leg Balance
Leg Balance .....................
3.c. ........
Turn Around
Turn Around .....................
3.d .........
Motion System Repeatability
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59778
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE C2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
<>
Test
Simulator level
Tolerance(s)
Number
Flight condition
Notes
B
With the same input signal, the
test results must be repeatable to within ±0.05g actual
platform linear acceleration in
each axis.
3.e. ........
Test details
Title
Accomplished in both
the ‘‘ground’’ mode
and in the ‘‘flight’’
mode of the motion
system operation.
Required as part of
the MQTG and at
each continuing
qualification evaluation. The test is accomplished by injecting a motion
signal to generate
movement of the
platform. The input
must be such that
the rotational accelerations, rotational
rates, and linear
accelerations are
inserted before the
transfer from helicopter center of
gravity to the pilot
reference point with
a minimum amplitude of 5°/sec/sec,
10°/sec and 0.3g,
respectively.
C
D
X
X
X
See Paragraph 5.c. in
this attachment for
additional information. Note: if there
is no difference in
the model for
‘‘ground’’ and
‘‘flight’’ operation of
the motion system,
this should be described in an SOC
and will not require
tests in both
modes.
Motion Cueing Performance Signature
Required as part of
MQTG but not required as part of
continuing qualification evaluations.
These tests must
be run with the motion buffet mode
disabled.
3.e.1. .....
Takeoff (all engines) ........
As specified by the sponsor for
flight simulator qualification.
Ground ......................
Pitch attitude due to
initial climb should
dominate over cab
tilt due to longitudinal acceleration.
3.e.2. .....
Hover performance (IGE
and OGE).
As specified by the sponsor for
flight simulator qualification.
Ground ......................
3.e.3. .....
Autorotation (entry) ..........
As specified by the sponsor for
flight simulator qualification.
3.e.4. .....
Landing (all engines) .......
3.e.5. .....
Autorotation (landing) .......
3.e.6. .....
Control Response
3.e.6.a. ..
See paragraph 5.d.,
of this attachment,
Motion cueing performance signature.
X
X
Associated to test
number 1.c.1.
...................................
X
X
Associated to test
number 1.d.
Flight .........................
...................................
X
X
Associated to test
number 1.i.
As specified by the sponsor for
flight simulator qualification.
Flight .........................
...................................
X
X
Associated to test
number 1.j.1.
As specified by the sponsor for
flight simulator qualification.
Flight .........................
...................................
X
X
Associated to test
number 1.j.4.
Longitudinal ......................
As specified by the sponsor for
flight simulator qualification.
Flight .........................
...................................
X
X
X
Associated to test
number 2.c.1.
3.e.6.b. ..
Lateral ..............................
As specified by the sponsor for
flight simulator qualification.
Ground ......................
...................................
X
X
X
Associated to test
number 2.d.1.a.
3.e.6.c. ..
Directional ........................
As specified by the sponsor for
flight simulator qualification.
...................................
...................................
X
X
X
Associated to test
number 2.d.1.c.
3.f. .........
Characteristic Motion Cues—For all of the following tests, the simulator test results must exhibit the overall appearance and trends of the helicopter data, with at least three (3) of the predominant frequency ‘‘spikes’’ being
present within ±2 Hz.
3.f.1. ......
Thrust effect with brakes
set.
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X
X
The test must be conducted within 5% of
the maximum possible thrust with
brakes set.
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Characteristic motion
cues may be separate from the
‘‘main’’ motion system.
X
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
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TABLE C2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
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Test
Simulator level
Tolerance(s)
Number
Flight condition
Test details
Notes
Title
B
C
D
3.f.2. ......
Buffet with landing gear
extended.
.....................................................
Flight .........................
The test must be conducted at an airspeed below landing gear limiting airspeed.
X
3.f.3. ......
Buffet at approach-to-stall
.....................................................
Flight .........................
The test must be conducted for approach to stall.
Post stall characteristics are not required.
X
3.f.4. ......
Buffet at high airspeeds ...
.....................................................
Flight .........................
...................................
X
3.f.5. ......
In-flight vibrations .............
.....................................................
Flight (clean configuration).
...................................
X
3.f.6. ......
Thrust effect with brakes
set.
.....................................................
Ground ......................
The test must be conducted within 5% of
the maximum possible thrust with
brakes set.
X
The airspeed selected for this test
should be within
the range where
the operator typically conducts operations with the
landing gear extended.
4. Visual System
4.a. ........
Visual System Response Time: (Choose either test 4.a.1. or 4.a.2. to satisfy test 4.a., Visual System Response Time Test. This test is also sufficient for motion system response timing and flight deck instrument response timing.)
4.a.1. .....
Latency
150 ms (or less) after helicopter
response.
One test is required
in each axis (pitch,
roll and yaw) for
each of the three
conditions (take-off,
cruise, and approach or landing).
100 ms (or less) after helicopter
response.
4.a.2. .....
Takeoff, climb, and
descent.
Climb, cruise, descent, and hover.
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
X
Transport Delay
If Transport Delay is
the chosen method
to demonstrate relative responses,
the sponsor and
the NSPM will use
the latency values
to ensure proper
simulator response
when reviewing
those existing tests
where latency can
be identified (e.g.,
short period, roll response, rudder response).
150 ms (or less) after controller
movement.
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A separate test is required in each axis
(pitch, roll, and
yaw).
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X
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59780
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE C2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
<>
Test
Simulator level
Tolerance(s)
Number
Flight condition
Test details
Notes
Title
B
100 ms (or less) after controller
movement.
N/A ............................
4.b. ........
Continuous field of view ...
The simulator must provide a
continuous field of view of at
least 75° horizontally and 30°
vertically per pilot seat or the
number of degrees necessary
to meet the visual ground segment requirement, whichever
is greater. Both pilot seat visual systems must be operable
simultaneously.
Wide-angle
systems providing cross-flight
deck viewing (for both pilots
simultaneously) must provide
a minimum field of view of at
least 146° horizontally and 36°
vertically. Any geometric error
between the Image Generator
eye point and the pilot eye
point must be 8° or less.
N/A ............................
An SOC is required
and must explain
the geometry of the
installation. Additional horizontal
field of view capability may be added
at the sponsor’s
discretion provided
the minimum field
of view is retained.
4.b.2. .....
Continuous field of view ...
The simulator must provide a
continuous field of view of at
least 146° horizontally and 36°
vertically or the number of degrees necessary to meet the
visual ground segment requirement, whichever is greater. The minimum horizontal
field of view coverage must be
plus and minus one-half (1⁄2)
of the minimum continuous
field of view requirement, centered on the zero degree azimuth line relative to the aircraft fuselage. Any geometric
error between the Image Generator eye point and the pilot
eye point must be 8° or less.
N/A ............................
An SOC is required
and must explain
the geometry of the
installation. Horizontal field of view
of at least 146° (including not less
than 73° measured
either side of the
center of the design eye point). Additional horizontal
field of view capability may be added
at the sponsor’s
discretion provided
the minimum field
of view is retained.
Vertical field of
view of at least 36°
measured from the
pilot’s and co-pilot’s
eye point.
X
Field of View
4.b.1. .....
D
X
A separate test is required in each axis
(pitch, roll, and
yaw).
C
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X
22OCP2
Horizontal field of
view is centered on
the zero degree
azimuth line relative to the aircraft
fuselage. 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.
X
Horizontal field of
view is centered on
the zero degree
azimuth line relative to the aircraft
fuselage. 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.
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
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TABLE C2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
<>
Test
Simulator level
Tolerance(s)
Flight condition
Test details
Notes
Number
Title
4.b.3. .....
Continuous field of view ...
Continuous field of view of at
least 176° horizontal and 56°
vertical field of view for each
pilot simultaneously. Any geometric error between the
Image Generator eye point
and the pilot eye point must
be 8° or less.
N/A ............................
An SOC is required
and must explain
the geometry of the
installation. Horizontal field of view
is centered on the
zero degree azimuth line relative to
the aircraft fuselage. Horizontal
field of view must
be at least 176° (including not less
than 88° either side
of the center of the
design eye point).
Additional horizontal field of view
capability may be
added at the sponsor’s discretion provided the minimum
field of view is retained. Vertical field
of view must not be
less than a total of
56° measured from
the pilot’s and copilot’s eye point.
X
The horizontal field of
view is traditionally
described as a
180° field of view.
However, the field
of view is technically no less than
176°. 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.
4.c. ........
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/m2)
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.
4.d. ........
Highlight brightness .........
Not less than six (6) foot-lamberts (20 cd/m2).
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.
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.
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C
D
59782
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TABLE C2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
<>
Test
Simulator level
Tolerance(s)
Flight condition
Test details
Number
4.e. ........
Surface resolution ............
Not greater than two (2) arc minutes.
N/A ............................
4.f. .........
Light point size .................
Not greater than five (5) arc-minutes.
4.g. ........
Light point contrast ratio ..
4.g.1. .....
Notes
Title
C
D
An SOC is required
and must include
the appropriate calculations and an
explanation of
those calculations.
X
X
The eye will subtend
two (2) 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 4-foot
gaps between the
bars. This requirement is the same
as 4 arc minutes
per optical line pair.
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.
.....................................................
...................................
...................................
..........................................
Not less than 10:1 ......................
N/A ............................
An SOC is required
and must include
the relevant calculations.
4.g.2. .....
..........................................
Not less than 25:1 ......................
N/A ............................
An SOC is required
and must include
the relevant calculations.
4.h. ........
Visual ground segment
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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 aftcab and flight deck
ambient light levels
should be zero.
X
X
22OCP2
X
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
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TABLE C2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
<>
Test
Simulator level
Tolerance(s)
Number
Flight condition
Test details
Notes
Title
B
The visible segment in the simulator must be within 20% of
the segment computed to be
visible from the helicopter
flight deck. The tolerance(s)
may be applied at either or
both ends of the displayed
segment. However, lights and
ground objects computed to
be visible from the helicopter
flight deck at the near end of
the visible segment must be
visible in the simulator.
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).
The QTG must contain appropriate
calculations and a
drawing showing
the data used to
establish the helicopter location and
the segment of the
ground that is visible considering design eyepoint, the
helicopter attitude,
flight deck cut-off
angle, and a visibility of 1200 ft
(350 m) RVR. Simulator performance
must be measured
against the QTG
calculations.
The data submitted
must include at
least the following:
(1) Static helicopter
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 flight deck
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.
If non-homogenous
fog is used to obscure visibility, the
vertical variation in
horizontal visibility
must be described
and be included in
the slant range visibility calculation
used in the computations.
C
D
X
X
X
5. Sound System
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Pre-position for this
test is encouraged,
and may be
achieved via manual or autopilot
control to the desired position.
59784
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE C2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
<>
Test
Simulator level
Tolerance(s)
Number
Flight condition
Test details
Notes
Title
B
C
D
The sponsor will not be required to repeat the helicopter tests (i.e., tests 5.a.1. through 5.a.8. (or 5.b.1. through 5.b.9.) and 5.c., as appropriate) during
continuing qualification evaluations if frequency response and background noise test results are within tolerance when compared to the initial qualification
evaluation results, and the sponsor shows that no software changes have occurred that will affect the helicopter test results. If the frequency response
test method is chosen and fails, the sponsor may elect to fix the frequency response problem and repeat the test or the sponsor may elect to repeat the
helicopter tests. If the helicopter tests are repeated during continuing qualification evaluations, the results may be compared against initial qualification
evaluation results or helicopter master data
5.a. ........
Basic requirements
5.a.1. .....
Ready for engine start .....
± 5 dB per 1⁄3 octave band .........
Ground ......................
Normal condition prior
to engine start. The
APU should be on
if appropriate.
X
5.a.2. .....
All engines at idle; rotor
not turning (if applicable) and rotor turning.
± 5 dB per 1⁄3 octave band .........
Ground ......................
Normal condition prior
to lift-off.
X
5.a.3. .....
Hover ...............................
±5 dB per 1⁄3 octave band ..........
Hover ........................
...................................
X
5.a.4. .....
Climb ................................
± 5 dB per ⁄ octave band .........
En-route climb ...........
Medium altitude ........
X
5.a.5. .....
Cruise ...............................
± 5 dB per 1⁄3 octave band .........
Cruise ........................
Normal cruise configuration.
X
5.a.6. .....
Final approach .................
± 5 dB per 1⁄3 octave band .........
Landing .....................
Constant airspeed,
gear down.
X
5.b. ........
Special cases
± 5 dB per 1⁄3 octave band .........
As appropriate ..........
...................................
X
These special cases
are identified as
particularly significant during critical
phases of flight and
ground operations
for a specific helicopter type or
model.
±3 dB per 1⁄3 octave band ..........
As appropriate ..........
Results of the background noise at initial qualification
must be included in
the MQTG. Measurements must be
made with the simulation running, the
sound muted, and
a ‘‘dead’’ flight deck.
X
The simulated sound
will be evaluated to
ensure that the
background noise
does not interfere
with training, testing, or checking.
5.c. ........
5.d. ........
13
Background noise
Frequency response
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
59785
TABLE C2A.—FULL FLIGHT SIMULATOR (FFS) OBJECTIVE TESTS—Continued
<<>>
<>
Test
Simulator level
Tolerance(s)
Number
Flight condition
Notes
B
±5 dB on three (3) consecutive
bands when compared to initial evaluation; and ± 2 dB
when comparing the average
of the absolute differences between initial and continuing
qualification evaluation.
lllllllllllllllllllll
Begin Information
3. 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.
4. 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 an FFS to be representative, it
should ‘‘feel’’ like the helicopter being
simulated. Compliance with this requirement
is determined by comparing a recording of
the control feel dynamics of the FFS to actual
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Title
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Applicable only to
Continuing Qualification Evaluations.
If frequency response
plots are provided
for each channel at
the initial evaluation, these plots
may be repeated at
the continuing qualification evaluation
with the following
tolerances applied:.
(a) The continuing
qualification 1⁄3 octave band amplitudes should not
exceed ± 5 dB for
three consecutive
bands when compared to initial results.
(b) The average of
the sum of the absolute differences
between initial and
continuing qualification results must
not exceed 2 dB
(refer to table C2C
in Appendix C).
helicopter 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 helicopter system is essential. The
required dynamic control tests are described
in Table C2A of this attachment.
(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 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.
(3) For helicopters with irreversible control
systems, measurements may be obtained on
the ground if proper pilot-static inputs are
provided to represent airspeeds typical of
those encountered in flight. Likewise, it may
be shown that for some helicopters, hover,
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
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C
D
X
Measurements are
compared to those
taken during initial
qualification evaluation.
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 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:
(1) For Levels C and D simulators. Tests to
verify that control feel dynamics represent
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
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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 helicopter 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 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
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.
(b) Critically damped and Overdamped
Response. Due to the nature of critically
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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.
(c) Special considerations. Control systems
that exhibit characteristics other than
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 summarizes the
tolerances, ‘‘T’’ for underdamped systems,
and ‘‘n’’ is the sequential period of a full
cycle of oscillation. See Figure C2A 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 overFirst overshoot and
shoots.
±1 subsequent
overshoots.
artificial feel systems is by the measurement
of control force and rate of movement. For
each axis of pitch, roll, and yaw, the control
must be forced to its maximum extreme
position for the following distinct rates.
These tests are conducted under normal
flight and ground conditions.
(a) Static test—Slowly move the control so
that a full sweep is achieved within 95–105
seconds. 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 within 8–12 seconds.
(c) Fast dynamic test—Achieve a full
sweep in within 3–5 seconds.
Note: Dynamic sweeps may be limited to
forces not exceeding 100 lbs. (44.5 daN).
(d) Tolerances.
(i) Static test—see Table C2A, Full Flight
Simulator (FFS) Objective Tests, Items 2.a.1.,
2.a.2., and 2.a.3.
(ii) Dynamic test ±2 lbs (0.9 daN) or ±10%
on dynamic increment above static test.
(b) The following tolerance applies to
critically damped and overdamped systems
only. See Figure C2B for an illustration of the
reference measurements:
T(P0) .......................... ±10% of P0.
d. The FAA is open to alternative means
that are justified and appropriate to the
application. For example, the method
described here may not apply to all
manufacturers’ systems and certainly not to
aircraft with reversible control systems. Each
case is considered on its own merit on an ad
hoc basis. If the FAA finds that alternative
methods do not result in satisfactory
performance, more conventionally accepted
methods will have to be used.
End Information
lllllllllllllllllllll
Begin QPS Requirement
c. Alternative method for control dynamics
evaluation.
(1) An alternative means for validating
control dynamics for aircraft with
hydraulically powered flight controls and
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Begin Information
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Begin Information
End Information
6. Motion System
a. General.
(1) Pilots use continuous information
signals to regulate the state of the helicopter.
In concert with the instruments and outsideworld visual information, whole-body
motion feedback is essential in assisting the
pilot to control the helicopter dynamics,
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5. [Reserved]
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particularly in the presence of external
disturbances. The motion system should
meet basic objective performance criteria,
and be subjectively tuned at the pilot’s seat
position to represent the linear and angular
accelerations of the helicopter during a
prescribed minimum set of maneuvers and
conditions. The response of the motion
cueing system should be repeatable.
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(2) The Motion System tests in Section 3
of Table C2A are intended to qualify the FFS
motion cueing system from a mechanical
performance standpoint. Additionally, the
list of motion effects provides a
representative sample of dynamic conditions
that should be present in the flight simulator.
An additional list of representative, trainingcritical maneuvers, selected from Section 1,
(Performance tests) and Section 2, (Handling
Qualities tests) in Table C2A, that should be
recorded during initial qualification (but
without tolerance) to indicate the flight
simulator motion cueing performance
signature have been identified (reference
Section 3.e). These tests are intended to help
improve the overall standard of FFS motion
cueing.
b. Motion System Checks. The intent of test
3a, Frequency Response, test 3b, Leg Balance,
and test 3c, Turn-Around Check, as described
in the Table of Objective Tests, is to
demonstrate the performance of the motion
system hardware, and to check the integrity
of the motion set-up with regard to
calibration and wear. These tests are
independent of the motion cueing software
and should be considered robotic tests.
c. Motion System Repeatability. The intent
of this test is to ensure that the motion
system software and motion system hardware
have not degraded or changed over time. This
diagnostic test should be completed during
continuing qualification checks in lieu of the
robotic tests. This will allow an improved
ability to determine changes in the software
or determine degradation in the hardware.
The following information delineates the
methodology that should be used for this test.
(1) Input: The inputs should be such that
rotational accelerations, rotational rates, and
linear accelerations are inserted before the
transfer from helicopter center of gravity to
pilot reference point with a minimum
amplitude of 5 deg/sec/sec, 10 deg/sec and
0.3 g, respectively, to provide adequate
analysis of the output.
(2) Recommended output:
(a) Actual platform linear accelerations; the
output will comprise accelerations due to
both the linear and rotational motion
acceleration;
(b) Motion actuators position.
d. Motion Cueing Performance Signature.
(1) Background. The intent of this test is to
provide quantitative time history records of
motion system response to a selected set of
automated QTG maneuvers during initial
qualification. It is not intended to be a
comparison of the motion platform
accelerations against the flight test recorded
accelerations (i.e., not to be compared against
helicopter cueing). If there is a modification
to the initially qualified motion software or
motion hardware (e.g., motion washout filter,
simulator payload change greater than 10%)
then a new baseline may need to be
established.
(2) Test Selection. The conditions
identified in Section 3.e. in Table C2A are
those maneuvers where motion cueing is the
most discernible. They are general tests
applicable to all types of helicopters and
should be completed for motion cueing
performance signature at any time acceptable
to the NSPM prior to or during the initial
qualification evaluation, and the results
included in the MQTG.
(3) Priority. Motion system should be
designed with the intent of placing greater
importance on those maneuvers that directly
influence pilot perception and control of the
helicopter motions. For the maneuvers
identified in section 3.e. in Table C2A, the
flight simulator motion cueing system should
have a high tilt co-ordination gain, high
rotational gain, and high correlation with
respect to the helicopter simulation model.
(4) Data Recording. The minimum list of
parameters provided should allow for the
determination of the flight simulator’s
motion cueing performance signature for the
initial qualification evaluation. The following
parameters are recommended as being
acceptable to perform such a function:
(a) Flight model acceleration and rotational
rate commands at the pilot reference point;
(b) Motion actuators position;
(c) Actual platform position;
(d) Actual platform acceleration at pilot
reference point.
e. Motion Vibrations.
(1) Presentation of results. The
characteristic motion vibrations may be used
to verify that the flight simulator can
reproduce the frequency content of the
helicopter when flown in specific conditions.
The test results should be presented as a
Power Spectral Density (PSD) plot with
frequencies on the horizontal axis and
amplitude on the vertical axis. The helicopter
data and flight simulator data should be
presented in the same format with the same
scaling. The algorithms used for generating
the flight simulator data should be the same
as those used for the helicopter data. If they
are not the same then the algorithms used for
the flight simulator data should be proven to
be sufficiently comparable. As a minimum
the results along the dominant axes should
be presented and a rationale for not
presenting the other axes should be provided.
(2) Interpretation of results. The overall
trend of the PSD plot should be considered
while focusing on the dominant frequencies.
Less emphasis should be placed on the
differences at the high frequency and low
amplitude portions of the PSD plot. During
the analysis, certain structural components of
the flight simulator have resonant
frequencies that are filtered and may not
appear in the PSD plot. If filtering is
required, the notch filter bandwidth should
be limited to 1 Hz to ensure that the buffet
feel is not adversely affected. In addition, a
rationale should be provided to explain that
the characteristic motion vibration is not
being adversely affected by the filtering. The
amplitude should match helicopter data as
described below. However, if the PSD plot
was altered for subjective reasons, a rationale
should be provided to justify the change. If
the plot is on a logarithmic scale it may be
difficult to interpret the amplitude of the
buffet in terms of acceleration. For example,
a 1×10¥3 grams2/Hz would describe a heavy
buffet and may be seen in the deep stall
regime. Alternatively, a 1×10¥6 grams2/Hz
buffet is almost imperceptable; but may
represent a flap buffet at low speed. The
previous two examples differ in magnitude
by 1000. On a PSD plot this represents three
decades (one decade is a change in order of
magnitude of 10; and two decades is a change
in order of magnitude of 100).
f. Table C2B, Motion System
Recommendations for Level C and Level D
Helicopter Simulators, contains a description
of the parameters that should be present in
a ZFT level simulator motion system to
provide adequate on-set motion cues to
helicopter pilots. The information provided
covers the six axes of motion (pitch, roll,
yaw, vertical, lateral, and longitudinal) and
addresses displacement, velocity, and
acceleration. Also included is information
about the parameters for initial rotational and
linear acceleration. The parameters listed in
this table apply only to ZFT level simulators,
and are presented here as recommended
targets for motion system capability. They are
not requirements.
TABLE C2B.—MOTION SYSTEM RECOMMENDATIONS FOR LEVEL C AND LEVEL D HELICOPTER SIMULATORS
a. .........
a.1. ......
a.1.a. ...
a.1.b. ...
a.1.c. ...
a.2. ......
a.2.a. ...
a.2.b. ...
a.2.c. ...
a.3. ......
a.3.a. ...
a.3.b. ...
a.3.c. ...
a.4. ......
a.4.a. ...
Motion System Envelope
Pitch
Displacement .................................................................................................................................
Velocity ..........................................................................................................................................
Acceleration ...................................................................................................................................
Roll
Displacement .................................................................................................................................
Velocity ..........................................................................................................................................
Acceleration ...................................................................................................................................
Yaw
Displacement .................................................................................................................................
Velocity - .......................................................................................................................................
Acceleration ...................................................................................................................................
Vertical
Displacement .................................................................................................................................
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±25°.
±20°/sec.
±100°/sec2.
±25°.
±20°/sec.
±100°/sec2.
±25°.
±20°/sec.
±100°/sec2.
±34 in.
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59789
TABLE C2B.—MOTION SYSTEM RECOMMENDATIONS FOR LEVEL C AND LEVEL D HELICOPTER SIMULATORS—Continued
a.4.b. ...
a.4.c. ...
a.5. ......
a.5.a. ...
a.5.b. ...
a.5.c. ...
a.6. ......
a.6.a. ...
a.6.b. ...
a.6.c. ...
a.7. ......
a.8. ......
a.8.a. ...
a.8.b. ...
a.8.c. ...
Velocity ..........................................................................................................................................
Acceleration ...................................................................................................................................
Lateral
Displacement .................................................................................................................................
Velocity ..........................................................................................................................................
Acceleration ...................................................................................................................................
Longitudinal
Displacement .................................................................................................................................
Velocity ..........................................................................................................................................
Acceleration ...................................................................................................................................
Initial Rotational Acceleration Ratio
........................................................................................................................................................
Initial Linear Acceleration Ratio
Vertical ..........................................................................................................................................
Lateral ...........................................................................................................................................
Longitudinal ...................................................................................................................................
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±24 in.
±0.8 g.
±45 in.
±28 in/sec.
±0.6 g.
±34 in.
±28 in/sec.
±0.6 g.
All axes 300°/ sec2/sec.
±6g/sec.
±3g/sec.
±3g/sec.
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Note: Motion system baseline performance
repeatability tests should be repeated if the
simulator weight changes for any reason (i.e.,
visual change or structural change). The new
results should be used for future comparison.
7. Sound System
a. General. The total sound environment in
the helicopter is very complex, and changes
with atmospheric conditions, helicopter
configuration, airspeed, altitude, and power
settings. Flight deck sounds are an important
component of the flight deck operational
environment and provide valuable
information to the flight crew. These aural
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cues can either assist the crew (as an
indication of an abnormal situation), or
hinder the crew (as a distraction or
nuisance). For effective training, the flight
simulator should provide flight deck sounds
that are perceptible to the pilot during
normal and abnormal operations, and that are
comparable to those of the helicopter. The
flight simulator operator should carefully
evaluate background noises in the location
where the device will be installed. To
demonstrate compliance with the sound
requirements, the objective or validation tests
in this attachment were selected to provide
a representative sample of normal static
conditions typically experienced by a pilot.
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b. Alternate propulsion. For FFS with
multiple propulsion configurations, any
condition listed in Table C2A in this
attachment should be presented for
evaluation as part of the QTG if identified by
the helicopter manufacturer or other data
supplier as significantly different due to a
change in propulsion system (engine or
propeller).
c. Data and Data Collection System.
(1) Information provided to the flight
simulator manufacturer should be presented
in the format suggested by the ‘‘International
Air Transport Association (IATA) Flight
Simulator Design and Performance Data
Requirements,’’ as amended. This
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information should contain calibration and
frequency response data.
(2) The system used to perform the tests
listed in Table C2A should comply with the
following standards:
(a) The specifications for octave, half
octave, and third octave band filter sets may
be found in American National Standards
Institute (ANSI) S1.11–1986.
(b) Measurement microphones should be
type WS2 or better, as described in
International Electrotechnical Commission
(IEC) 1094–4–1995.
(3) Headsets. If headsets are used during
normal operation of the helicopter they
should also be used during the flight
simulator evaluation.
(4) Playback equipment. Playback
equipment and recordings of the QTG
conditions should be provided during initial
evaluations.
(5) Background noise.
(a) Background noise is the noise in the
flight simulator that is not associated with
the helicopter, but is caused by the flight
simulator’s cooling and hydraulic systems
and extraneous noise from other locations in
the building. Background noise can seriously
impact the correct simulation of helicopter
sounds, and should be kept below the
helicopter sounds. In some cases, the sound
level of the simulation can be increased to
compensate for the background noise.
However, this approach is limited by the
specified tolerances and by the subjective
acceptability of the sound environment to the
evaluation pilot.
(b) The acceptability of the background
noise levels is dependent upon the normal
sound levels in the helicopter being
represented. Background noise levels that fall
59791
below the lines defined by the following
points, may be acceptable:
(i) 70 dB @ 50 Hz;
(ii) 55 dB @ 1000 Hz;
(iii) 30 dB @ 16 kHz.
(Note: These limits are for unweighted 1/
3 octave band sound levels. Meeting these
limits for background noise does not ensure
an acceptable flight simulator. Helicopter
sounds that fall below this limit require
careful review and may require lower limits
on background noise.)
(6) Validation testing. Deficiencies in
helicopter recordings should be considered
when applying the specified tolerances to
ensure that the simulation is representative
of the helicopter. Examples of typical
deficiencies are:
(a) Variation of data between tail numbers.
(b) Frequency response of microphones.
(c) Repeatability of the measurements.
TABLE C2C.—EXAMPLE OF RECURRENT FREQUENCY RESPONSE TEST TOLERANCE
Initial results
(dBSPL)
Band center frequency
50 .................................................................................................................................................
63 .................................................................................................................................................
80 .................................................................................................................................................
100 ...............................................................................................................................................
125 ...............................................................................................................................................
160 ...............................................................................................................................................
200 ...............................................................................................................................................
250 ...............................................................................................................................................
315 ...............................................................................................................................................
400 ...............................................................................................................................................
500 ...............................................................................................................................................
630 ...............................................................................................................................................
800 ...............................................................................................................................................
1000 .............................................................................................................................................
1250 .............................................................................................................................................
1600 .............................................................................................................................................
2000 .............................................................................................................................................
2500 .............................................................................................................................................
3150 .............................................................................................................................................
4000 .............................................................................................................................................
5000 .............................................................................................................................................
6300 .............................................................................................................................................
8000 .............................................................................................................................................
10000 ...........................................................................................................................................
12500 ...........................................................................................................................................
16000 ...........................................................................................................................................
Recurrent
results
(dBSPL)
75.0
75.9
77.1
78.0
81.9
79.8
83.1
78.6
79.5
80.1
80.7
81.9
73.2
79.2
80.7
81.6
76.2
79.5
80.1
78.9
80.1
80.7
84.3
81.3
80.7
71.1
Average
8. Additional Information About Flight
Simulator Qualification for New or
Derivative Helicopters
a. Typically, a helicopter manufacturer’s
approved final data for performance,
handling qualities, systems or avionics is not
available until well after a new or derivative
helicopter has entered service. However,
flight crew training and certification often
begins several months prior to the entry of
the first helicopter into service.
Consequently, it may be necessary to use
preliminary data provided by the helicopter
manufacturer for interim qualification of
flight simulators.
b. In these cases, the NSPM may accept
certain partially validated preliminary
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helicopter and systems data, and early
release ‘‘red label’’ avionics data in order to
permit the necessary program schedule for
training, certification, and service
introduction.
c. Simulator sponsors seeking qualification
based on preliminary data should consult the
NSPM to make special arrangements for
using preliminary data for flight simulator
qualification. The sponsor should also
consult the helicopter and flight simulator
manufacturers to develop a data plan and
flight simulator qualification plan.
d. The procedure to be followed to gain
NSPM acceptance of preliminary data will
vary from case to case and between
helicopter manufacturers. Each helicopter
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73.8
75.6
76.5
78.3
81.3
80.1
84.9
78.9
78.3
79.5
79.8
80.4
74.1
80.1
82.8
78.6
74.4
80.7
77.1
78.6
77.1
80.4
85.5
79.8
80.1
71.1
Absolute
difference
1.2
0.3
0.6
0.3
0.6
0.3
1.8
0.3
1.2
0.9
0.9
1.5
0.9
0.9
2.1
3.0
1.8
1.2
3.0
0.3
3.0
0.3
1.2
1.5
0.6
0.0
1.1
manufacturer’s new helicopter development
and test program is designed to suit the needs
of the particular project and may not contain
the same events or sequence of events as
another manufacturer’s program or even the
same manufacturer’s program for a different
helicopter. Therefore, there cannot be a
prescribed invariable procedure for
acceptance of preliminary data; instead there
should be a statement describing the final
sequence of events, data sources, and
validation procedures agreed by the
simulator sponsor, the helicopter
manufacturer, the flight simulator
manufacturer, and the NSPM. Note: A
description of helicopter manufacturerprovided data needed for flight simulator
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modeling and validation is to be found in the
IATA Document ‘‘Flight Simulator Design
and Performance Data Requirements,’’ as
amended.
e. The preliminary data should be the
manufacturer’s best representation of the
helicopter, with assurance that the final data
will not deviate significantly from the
preliminary estimates. Data derived from
these predictive or preliminary techniques
should be validated by available sources
including, at least, the following:
(1) Manufacturer’s engineering report. The
report should explain the predictive method
used and illustrate past success of the
method on similar projects. For example, the
manufacturer could show the application of
the method to an earlier helicopter model or
predict the characteristics of an earlier model
and compare the results to final data for that
model.
(2) Early flight test results. This data is
often derived from helicopter certification
tests and should be used to maximum
advantage for early flight simulator
validation. Certain critical tests that would
normally be done early in the helicopter
certification program should be included to
validate essential pilot training and
certification maneuvers. These tests include
cases where a pilot is expected to cope with
a helicopter failure mode or an engine
failure. The early data available will depend
on the helicopter manufacturer’s flight test
program design and may not be the same in
each case. The flight test program of the
helicopter manufacturer should include
provisions for generation of very early flight
tests results for flight simulator validation.
f. The use of preliminary data is not
indefinite. The helicopter manufacturer’s
final data should be available within 12
months after the helicopter first entry into
service or as agreed by the NSPM, the
simulator sponsor, and the helicopter
manufacturer. When applying for interim
qualification using preliminary data, the
simulator sponsor and the NSPM should
agree on the update program. This includes
specifying that the final data update will be
installed in the flight simulator within a
period of 12 months following the final data
release, unless special conditions exist and a
different schedule is acceptable. The flight
simulator performance and handling
validation would then be based on data
derived from flight tests. Initial helicopter
systems data should be updated after
engineering tests. Final helicopter systems
data should also be used for flight simulator
programming and validation.
g. Flight simulator avionics should stay
essentially in step with helicopter avionics
(hardware and software) updates. The
permitted time lapse between helicopter and
flight simulator updates should be minimal.
It may depend on the magnitude of the
update and whether the QTG and pilot
training and certification are affected.
Differences in helicopter and flight simulator
avionics versions and the resulting effects on
flight simulator qualification should be
agreed between the simulator sponsor and
the NSPM. Consultation with the flight
simulator manufacturer is desirable
throughout the qualification process.
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h. The following describes an example of
the design data and sources that might be
used in the development of an interim
qualification plan.
(1) The plan should consist of the
development of a QTG based upon a mix of
flight test and engineering simulation data.
For data collected from specific helicopter
flight tests or other flights the required design
model or data changes necessary to support
an acceptable Proof of Match (POM) should
be generated by the helicopter manufacturer.
(2) For proper validation of the two sets of
data, the helicopter manufacturer should
compare their simulation model responses
against the flight test data, when driven by
the same control inputs and subjected to the
same atmospheric conditions as recorded in
the flight test. The model responses should
result from a simulation where the following
systems are run in an integrated fashion and
are consistent with the design data released
to the flight simulator manufacturer:
(a) Propulsion.
(b) Aerodynamics.
(c) Mass properties.
(d) Flight controls.
(e) Stability augmentation.
(f) Brakes/landing gear.
i. A qualified test pilot should be used to
assess handling qualities and performance
evaluations for the qualification of flight
simulators of new helicopter types.
End Information
lllllllllllllllllllll
Begin QPS Requirement
9. Engineering Simulator—Validation Data
a. When a fully validated simulation (i.e.,
validated with flight test results) is modified
due to changes to the simulated helicopter
configuration, the helicopter manufacturer or
other acceptable data supplier must
coordinate with the NSPM to supply
validation data from an ‘‘audited’’
engineering simulator/simulation to
selectively supplement flight test data. The
NSPM must be provided an opportunity to
audit the use of the engineering simulation
or the engineering simulator during the
acquisition of the data that will be used as
validation data. Audited data may be used for
changes that are incremental in nature.
Manufacturers or other data suppliers should
be able to demonstrate that the predicted
changes in helicopter performance are based
on acceptable aeronautical principles with
proven success history and valid outcomes.
This should include comparisons of
predicted and flight test validated data.
b. Helicopter manufacturers or other
acceptable data suppliers seeking to use an
engineering simulator for simulation
validation data as an alternative to flight-test
derived validation data, must contact the
NSPM and provide the following:
(1) A description of the proposed aircraft
changes, a description of the proposed
simulation model changes, and the use of an
integral configuration management process,
including an audit of the actual simulation
model modifications that includes a step-bystep description leading from the original
model(s) to the current model(s).
(2) A schedule for review by the NSPM of
the proposed plan and the subsequent
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validation data to establish acceptability of
the proposal.
(3) Information that demonstrates an ability
to qualify the FFS in which this data is to be
used in accordance with the criteria
contained in § 60.15.
c. To be qualified to supply engineering
simulator validation data, for aerodynamic,
engine, flight control, or ground handling
models, a helicopter manufacturer or other
acceptable data supplier must:
(1) Be able to verify their ability to:
(a) Develop and implement high fidelity
simulation models; and
(b) Predict the handling and performance
characteristics of a helicopter with sufficient
accuracy to avoid additional flight test
activities for those handling and performance
characteristics.
(2) Have an engineering simulator that:
(a) Is a physical entity, complete with a
flight deck representative of the simulated
class of helicopter;
(b) Has controls sufficient for manual
flight;
(c) Has models that run in an integrated
manner;
(d) Had fully flight-test validated
simulation models as the original or baseline
simulation models;
(e) Has an out-of-the-flight deck visual
system;
(f) Has actual avionics boxes
interchangeable with the equivalent software
simulations to support validation of released
software;
(g) Uses the same models as released to the
training community (which are also used to
produce stand-alone proof-of-match and
checkout documents);
(h) Is used to support helicopter
development and certification; and
(i) Has been found to be a high fidelity
representation of the helicopter by the
manufacturer’s pilots (or other acceptable
data supplier), certificate holders, and the
NSPM.
(3) Use the engineering simulator to
produce a representative set of integrated
proof-of-match cases.
(4) Use a configuration control system
covering hardware and software for the
operating components of the engineering
simulator.
(5) Demonstrate that the predicted effects
of the change(s) are within the provisions of
sub-paragraph ‘‘a’’ of this section, and
confirm that additional flight test data are not
required.
d. Additional Requirements for Validation
Data
(1) When used to provide validation data,
an engineering simulator must meet the
simulator standards currently applicable to
training simulators except for the data
package.
(2) The data package used must be:
(a) Comprised of the engineering
predictions derived from the helicopter
design, development, or certification process;
(b) Based on acceptable aeronautical
principles with proven success history and
valid outcomes for aerodynamics, engine
operations, avionics operations, flight control
applications, or ground handling;
(c) Verified with existing flight-test data;
and
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(d) Applicable to the configuration of a
production helicopter, as opposed to a flighttest helicopter.
(3) Where engineering simulator data are
used as part of a QTG, an essential match
must exist between the training simulator
and the validation data.
(4) Training flight simulator(s) using these
baseline and modified simulation models
must be qualified to at least internationally
recognized standards, such as contained in
the ICAO Document 9625, the ‘‘Manual of
Criteria for the Qualification of Flight
Simulators.’’
End QPS Requirement
lllllllllllllllllllll
10. [Reserved]
lllllllllllllllllllll
Begin QPS Requirement
11. Validation Test Tolerances
a. Non-Flight-Test Tolerances. If
engineering simulator data or other nonflight-test data are used as an allowable form
of reference validation data for the objective
tests listed in Table C2A of this attachment,
the data provider must supply a welldocumented mathematical model and testing
procedure that enables a replication of the
engineering simulation results within 20% of
the corresponding flight test tolerances.
End QPS Requirement
lllllllllllllllllllll
Begin Information
b. Background
(1) The tolerances listed in Table C2A of
this attachment are designed to measure the
quality of the match using flight-test data as
a reference.
(2) Good engineering judgment should be
applied to all tolerances in any test. A test
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is failed when the results fall outside of the
prescribed tolerance(s).
(3) Engineering simulator data are
acceptable because the same simulation
models used to produce the reference data
are also used to test the flight training
simulator (i.e., the two sets of results should
be ‘‘essentially’’ similar).
(4) The results from the two sources may
differ for the following reasons:
(a) Hardware (avionics units and flight
controls);
(b) Iteration rates;
(c) Execution order;
(d) Integration methods;
(e) Processor architecture;
(f) Digital drift, including:
(i) Interpolation methods;
(ii) Data handling differences;
(iii) Auto-test trim tolerances.
(5) Any differences must be within 20% of
the flight test tolerances. The reasons for any
differences, other than those listed above,
should be explained.
(6) Guidelines are needed for the
application of tolerances to engineeringsimulator-generated validation data because:
(a) Flight-test data are often not available
due to sound technical reasons;
(b) Alternative technical solutions are
being advanced; and
(c) The costs are high.
12. Validation Data Roadmap
a. Helicopter manufacturers or other data
suppliers should supply a validation data
roadmap (VDR) document as part of the data
package. A VDR document contains guidance
material from the helicopter validation data
supplier recommending the best possible
sources of data to be used as validation data
in the QTG. A VDR is of special value when
requesting interim qualification, qualification
of simulators for helicopters certificated prior
to 1992, and qualification of alternate engine
or avionics fits. A sponsor seeking to have a
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device qualified in accordance with the
standards contained in this QPS appendix
should submit a VDR to the NSPM as early
as possible in the planning stages. The NSPM
is the final authority to approve the data to
be used as validation material for the QTG.
The NSPM and the Joint Aviation
Authorities’ Synthetic Training Devices
Advisory Board have committed to maintain
a list of agreed VDRs.
b. The VDR should identify (in matrix
format) sources of data for all required tests.
It should also provide guidance regarding the
validity of these data for a specific engine
type, thrust rating configuration, and the
revision levels of all avionics affecting
helicopter handling qualities and
performance. The VDR should include
rationale or explanation in cases where data
or parameters are missing, engineering
simulation data are to be used, flight test
methods require explanation, or where there
is any deviation from data requirements.
Additionally, the document should refer to
other appropriate sources of validation data
(e.g., sound and vibration data documents).
c. The VDR table shown in Table C2D
depicts a generic roadmap matrix identifying
sources of validation data for an abbreviated
list of tests. A complete matrix should
address all test conditions.
d. Two examples of rationale pages are
presented in Appendix F of IATA Flight
Simulator Design and Performance Data
Requirements document. These illustrate the
type of helicopter and avionics configuration
information and descriptive engineering
rationale used to describe data anomalies,
provide alternative data, or provide an
acceptable basis for obtaining deviations
from QTG validation requirements.
End Information
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Begin Information
13. [Reserved]
14. Acceptance Guidelines for Alternative
Avionics (Flight-Related Computers and
Controllers)
a. Background
(1) For a new helicopter type, the majority
of flight validation data are collected on the
first helicopter configuration with a
‘‘baseline’’ flight-related avionics ship-set;
(see subparagraph b.(2) in this paragraph.)
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These data are then used to validate all flight
simulators representing that helicopter type.
(2) Additional validation data may be
needed for flight simulators representing a
helicopter with avionics of a different
hardware design than the baseline, or a
different software revision than that of
previously validated configurations.
(3) When a flight simulator with additional
or alternate avionics configurations is to be
qualified, the QTG should contain tests
against validation data for selected cases
where avionics differences are expected to be
significant. b. Approval Guidelines For
Validating Alternate Avionics
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(1) The following guidelines apply to flight
simulators representing helicopters with a
revised avionics configuration, or more than
one avionics configuration.
(2) The baseline validation data should be
based on flight test data, except where other
data are specifically allowed (e.g.,
engineering flight simulator data).
(3) The helicopter avionics can be
segmented into two groups, systems or
components whose functional behavior
contributes to the aircraft response presented
in the QTG results, and systems that do not.
The following avionics are examples of
contributory systems for which hardware
design changes or software revisions may
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lead to significant differences in the aircraft
response relative to the baseline avionics
configuration: flight control computers and
controllers for engines, autopilot, braking
system, and nose wheel steering system, if
applicable. Related avionics such as
augmentation systems should also be
considered.
(4) The acceptability of validation data
used in the QTG for an alternative avionics
fit should be determined as follows:
(a) For changes to an avionics system or
component that do not affect QTG validation
test response, the QTG test can be based on
validation data from the previously validated
avionics configuration.
(b) For an avionics change to a contributory
system, where a specific test is not affected
by the change (e.g., the avionics change is a
Built In Test Equipment (BITE) update or a
modification in a different flight phase), the
QTG test can be based on validation data
from the previously-validated avionics
configuration. The QTG should include
authoritative justification (e.g., from the
helicopter manufacturer or system supplier)
that this avionics change does not affect the
test.
(c) For an avionics change to a contributory
system, the QTG may be based on validation
data from the previously-validated avionics
configuration if no new functionality is
added and the impact of the avionics change
on the helicopter response is based on
acceptable aeronautical principles with
proven success history and valid outcomes.
This should be supplemented with avionicsspecific validation data from the helicopter
manufacturer’s engineering simulation,
generated with the revised avionics
configuration. The QTG should include an
explanation of the nature of the change and
its effect on the helicopter response.
(d) For an avionics change to a
contributory system that significantly affects
some tests in the QTG, or where new
functionality is added, the QTG should be
based on validation data from the previously
validated avionics configuration and
supplemental avionics-specific flight test
data sufficient to validate the alternate
avionics revision. Additional flight test
validation data may not be needed if the
avionics changes were certified without the
need for testing with a comprehensive flight
instrumentation package. The helicopter
manufacturer should coordinate flight
simulator data requirements in advance with
the NSPM.
(5) A matrix or ‘‘roadmap’’ should be
provided with the QTG indicating the
appropriate validation data source for each
test. The roadmap should include
identification of the revision state of those
contributory avionics systems that could
affect specific test responses.
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15. Transport Delay Testing
a. This paragraph describes how to
determine the introduced transport delay
through the flight simulator system so that it
does not exceed a specific time delay. The
transport delay should be measured from
control inputs through the interface, through
each of the host computer modules and back
through the interface to motion, flight
instrument, and visual systems. The
transport delay should not exceed the
maximum allowable interval.
b. Four specific examples of transport
delay are:
(1) Simulation of classic non-computer
controlled helicopters;
(2) Simulation of computer controlled
helicopters using real helicopter black boxes;
(3) Simulation of computer controlled
helicopters using software emulation of
helicopter boxes;
(4) Simulation using software avionics or
re-hosted instruments.
c. Figure C2C illustrates the total transport
delay for a non-computer-controlled
helicopter or the classic transport delay test.
Since there are no helicopter-induced delays
for this case, the total transport delay is
equivalent to the introduced delay.
d. Figure C2D illustrates the transport
delay testing method using the real
helicopter controller system.
e. To obtain the induced transport delay for
the motion, instrument and visual signal, the
delay induced by the helicopter controller
should be subtracted from the total transport
delay. This difference represents the
introduced delay and should not exceed the
standards prescribed in Table C1A.
f. Introduced transport delay is measured
from the flight deck control input to the
reaction of the instruments and motion and
visual systems (See Figure C2C).
g. The control input may also be
introduced after the helicopter controller
system input and the introduced transport
delay may be measured directly from the
control input to the reaction of the
instruments, and simulator motion and
visual systems (See Figure C2D).
h. Figure C2E illustrates the transport delay
testing method used on a flight simulator that
uses a software emulated helicopter
controller system.
i. It is not possible to measure the
introduced transport delay using the
simulated helicopter controller system
architecture for the pitch, roll and yaw axes.
Therefore, the signal should be measured
directly from the pilot controller. The flight
simulator manufacturer should measure the
total transport delay and subtract the
inherent delay of the actual helicopter
components because the real helicopter
controller system has an inherent delay
provided by the helicopter manufacturer. The
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flight simulator manufacturer should ensure
that the introduced delay does not exceed the
standards prescribed in Table C1A.
j. Special measurements for instrument
signals for flight simulators using a real
helicopter instrument display system instead
of a simulated or re-hosted display. For flight
instrument systems, the total transport delay
should be measured and the inherent delay
of the actual helicopter components
subtracted to ensure that the introduced
delay does not exceed the standards
prescribed in Table C1A.
(1) Figure C2FA illustrates the transport
delay procedure without airplane display
simulation. The introduced delay consists of
the delay between the control movement and
the instrument change on the data bus.
(2) Figure C2FB illustrates the modified
testing method required to measure
introduced delay due to software avionics or
re-hosted instruments. The total simulated
instrument transport delay is measured and
the helicopter delay should be subtracted
from this total. This difference represents the
introduced delay and should not exceed the
standards prescribed in Table C1A. The
inherent delay of the helicopter between the
data bus and the displays is indicated in
figure C2FA. The display manufacturer
should provide this delay time.
k. Recorded signals. The signals recorded
to conduct the transport delay calculations
should be explained on a schematic block
diagram. The flight simulator manufacturer
should also provide an explanation of why
each signal was selected and how they relate
to the above descriptions.
l. Interpretation of results. Flight simulator
results vary over time from test to test due
to ‘‘sampling uncertainty.’’ All flight
simulators run at a specific rate where all
modules are executed sequentially in the
host computer. The flight controls input can
occur at any time in the iteration, but these
data will not be processed before the start of
the new iteration. For example, a flight
simulator running at 60 Hz may have a
difference of as much as 16.67 msec between
results. This does not mean that the test has
failed. Instead, the difference is attributed to
variation in input processing. In some
conditions, the host simulator and the visual
system do not run at the same iteration rate,
so the output of the host computer to the
visual system will not always be
synchronized.
m. The transport delay test should account
for both daylight and night modes of
operation of the visual system. In both cases,
the tolerances prescribed in Table C1A
should be met and the motion response
should occur before the end of the first video
scan containing new information.
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16. Continuing Qualification Evaluations—
Validation Test Data Presentation
a. Background.
(1) The MQTG is created during the initial
evaluation of a flight simulator. This is the
master document, as amended, to which
flight simulator continuing qualification
evaluation test results are compared.
(2) The currently accepted method of
presenting continuing qualification
evaluation test results is to provide flight
simulator results over-plotted with reference
data. Test results are carefully reviewed to
determine if the test is within the specified
tolerances. This can be a time consuming
process, particularly when reference data
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exhibits rapid variations or an apparent
anomaly requiring engineering judgment in
the application of the tolerances. In these
cases, the solution is to compare the results
to the MQTG. The continuing qualification
results are compared to the results in the
MQTG for acceptance. The flight simulator
operator and the NSPM should look for any
change in the flight simulator performance
since initial qualification.
b. Continuing Qualification Evaluation
Test Results Presentation.
(1) Flight simulator operators are
encouraged to over-plot continuing
qualification validation test results with
MQTG flight simulator results recorded
during the initial evaluation and as amended.
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Any change in a validation test will be
readily apparent. In addition to plotting
continuing qualification validation test and
MQTG results, operators may elect to plot
reference data.
(2) There are no suggested tolerances
between flight simulator continuing
qualification and MQTG validation test
results. Investigation of any discrepancy
between the MQTG and continuing
qualification flight simulator performance is
left to the discretion of the flight simulator
operator and the NSPM.
(3) Differences between the two sets of
results, other than variations attributable to
repeatability issues that cannot be explained
should be investigated.
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(4) The flight simulator should retain the
ability to over-plot both automatic and
manual validation test results with reference
data.
End Information
lllllllllllllllllllll
Begin QPS Requirements
17. Alternative Data Sources, Procedures,
and Instrumentation: Level B Simulators
Only
a. Sponsors are not required to use the
alternative data sources, procedures, and
instrumentation. However, any sponsor
choosing to use alternative sources must
comply with the requirements in Table C2E.
End QPS Requirements
lllllllllllllllllllll
Begin Information
b. It has become standard practice for
experienced simulator manufacturers to use
such techniques as a means of establishing
data bases 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 appropriate experience, are
dependable and accurate for the development
of aerodynamic models for use in 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 for
simulator application can successfully use
these modeling techniques to alter the
method for acquiring flight test data for Level
B simulators.
d. The information in Table C2E
(Alternative Data Sources, Procedures, and
Information) 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 Helicopter Maintenance Manual, the
Rotorcraft Flight Manual (RFM), Helicopter
Design Data, the Type Inspection Report
(TIR), Certification Data or acceptable
supplemental flight test data.
(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 on the use of these
alternative data sources, procedures, and
instrumentation is based on 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. The model does not require
control surface position measurements in the
flight test objective data in these limited
applications.
f. Data may be acquired by using an inertial
measurement system and a synchronized
video of the calibrated helicopter
instruments, including the inclinometer; the
force/position measurements of flight deck
controls; and a clear visual directional
reference for a known magnetic bearing (e.g.,
a runway centerline). Ground track and wind
corrected heading may be used for sideslip
angle.
g. The sponsor is urged to contact the
NSPM for clarification of any issue regarding
helicopters with reversible control systems.
This table is not applicable to Computer
Controlled Aircraft flight simulators.
h. Use 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 B FFSs.
i. The term ‘‘inertial measurement system’’
is used in table C2E include the use of a
functional global positioning system (GPS).
j. Synchronized video for the use of
alternative data sources, procedures, and
instrumentation should have:
(1) sufficient resolution to allow
magnification of the display to make
appropriate measurement and comparisons;
and
(2) sufficient size and incremental marking
to allow similar measurement and
comparison. The detail provided by the video
should provide sufficient clarity and
accuracy to measure the necessary
parameter(s) to at least 1⁄2 of the tolerance
authorized for the specific test being
conducted and allow an integration of the
parameter(s) in question to obtain a rate of
change.
End Information
lllllllllllllllllllll
TABLE C2E.—ALTERNATIVE DATA SOURCES, PROCEDURES, AND INSTRUMENTATION
[The standards in this table are required if the data gathering methods described in paragraph 9 of Appendix C are not used.]
QPS requirements
Table of objective tests
Level B only
Test reference number and title
1.a.1.a. Performance. Engine Start and
Accelerations.
X
1.a.1.b. Performance. Steady State Idle
and Operating RPM Conditions.
X
1.a.2. Performance.
Speed Trim.
Turbine
X
1.a.3. Performance. Engine and Rotor
Speed Governing.
X
1.b.1. Performance. On Surface Taxi.
Minimum Radius turn.
X
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Alternative data sources, procedures,
and instrumentation
Notes and reminders
Data may be acquired using a synchronized video recording of all engine instruments, start buttons,
means for fuel introduction and
means for moving from ‘‘idle’’ to
‘‘flight.’’ A stopwatch is necessary.
Data may be acquired using a synchronized video recording of all engine instruments, and include the status of the means for moving from
‘‘idle’’ to ‘‘flight.’’
Data may be acquired using a synchronized video recording of all engine instruments. Speed trim actuator
position may be hand recorded.
Data may be acquired by using a synchronized video of the calibrated helicopter instruments and the force/position measurements of flight deck controls.
TIR, AFM, or Design data may be used.
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TABLE C2E.—ALTERNATIVE DATA SOURCES, PROCEDURES, AND INSTRUMENTATION—Continued
[The standards in this table are required if the data gathering methods described in paragraph 9 of Appendix C are not used.]
QPS requirements
Table of objective tests
Level B only
Test reference number and title
1.b.2. Performance. On Surface Taxi
Rate of Turn vs. Nosewheel Steering
Angle.
X
1.b.3
Performance. Taxi ........................
X
1.b.4.
Performance. Brake .....................
X
1.c.1.
Performance. Running Takeoff ....
X
1.c.2 Performance. One Engine Inoperative (OEI), continued takeoff.
X
1.f. Performance. Level Flight. Trimmed
Flight Control Positions.
X
1.g. Performance.
Normal
Climb.
Trimmed Flight Control Positions.
X
1.h.1. Descent
Performance
Trimmed Flight Control Positions.
and
X
1.h.2. Autorotation Performance
Trimmed Flight Control Positions.
and
X
1.j.1. Performance. Running Landing All
Engines.
X
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Alternative data sources, procedures,
and instrumentation
Notes and reminders
Data may be acquired by using a constant tiller position (measured with a
protractor), or full pedal application
for steady state turn, and synchronized video of heading indicator.
If less than full pedal is used, pedal
position must be recorded.
Data may be acquired by using a synchronized video of the calibrated helicopter instruments and the force/position measurements of flight deck controls.
Data may be acquired using a stopwatch and a means for measuring
distance such as runway distance
markers conforming with runway distance marker standards.
Preliminary certification data may be
used. Data may be acquired by using
a synchronized video of the calibrated
helicopter instruments and the force/
position measurements of flight deck
controls. Collective, cyclic, and pedal
position time history should be recorded from the start of collective
movement through to normal climb.
Indicated torque settings may be
hand recorded at the moment of liftoff and in a steady normal climb.
Data may be acquired by using a synchronized video of the calibrated helicopter instruments and the force/position measurements of flight deck controls. Collective, cyclic, and pedal position time history should be recorded
from the start of collective movement
through to normal OEI climb. Indicated torque settings may be hand
recorded at the moment of lift-off and
in a steady normal OEI climb.
Data may be acquired by using a synchronized video of the calibrated helicopter instruments and the force/position measurements of flight deck controls.
Data may be acquired by using a synchronized video of the calibrated helicopter instruments and the force/position measurements of flight deck controls.
Data may be acquired by using a synchronized video of the calibrated helicopter instruments and the force/position measurements of flight deck controls.
Data may be acquired by using a synchronized video of the calibrated helicopter instruments and the force/position measurements of flight deck controls.
Data may be acquired by using a synchronized video of the calibrated helicopter instruments and the force/position measurements of flight deck controls.
A single procedure may not be adequate for all rotorcraft steering systems. Appropriate measurement procedures must be devised and proposed for NSPM concurrence.
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TABLE C2E.—ALTERNATIVE DATA SOURCES, PROCEDURES, AND INSTRUMENTATION—Continued
[The standards in this table are required if the data gathering methods described in paragraph 9 of Appendix C are not used.]
QPS requirements
Table of objective tests
Level B only
Test reference number and title
1.j.2. Performance. Running
One Engine Inoperative.
Landing
X
Performance. Balked Landing ......
X
2.a.1. Handling Qualities. Static Control
Checks. Cyclic Controller Position vs.
Force.
X
2.a.2. Handling Qualities. Static Control
Checks. Collective/Pedals vs. Force.
X
2.a.3. Handling Qualities. Brake Pedal
Force vs. Position.
X
2.a.4. Handling Qualities. Trim System
Rate (all applicable systems).
X
2.a.6. Handling Qualities. Control System Freeplay.
2.c.1. Longitudinal Handling qualities.
Control Response.
X
2.c.2. Longitudinal Handling qualities.
Static Stability.
X
2.c.3.a Longitudinal Handling qualities.
Dynamic Stability, Long Term Response.
X
2.c.3.b. Longitudinal Handling qualities.
Dynamic Stability, Short Term Response.
X
1.j.3.
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Alternative data sources, procedures,
and instrumentation
Notes and reminders
Data may be acquired by using a synchronized video of the calibrated helicopter instruments and the force/position measurements of flight deck controls.
Data may be acquired by using a synchronized video of the calibrated helicopter instruments and the force/position measurements of flight deck controls. The synchronized video must
record the time of the ‘‘balk landing’’
decision.
Control positions can be obtained using
continuous control position recordings. Force data may be acquired by
using a hand held force gauge so
that the forces can be cross-plotted
against control position in each of the
control axes.
Control positions can be obtained using
continuous control position recordings. Force data may be acquired by
using a hand held force gauge so
that the forces can be cross-plotted
against control position in each of the
control axes.
Brake pedal positions can be obtained
using continuous position recordings.
Force data may be acquired by using
a hand held force gauge so that the
forces can be cross-plotted against
brake pedal position.
Control positions can be obtained using
continuous control position recordings
plotted against time to provide rate in
each applicable system.
Data may be acquired by direct measurement.
Data may be acquired by using an inertial measurement system, a synchronized video of the calibrated helicopter instruments and the force/position measurements of flight deck controls.
Data may be acquired by using an inertial measurement system, a synchronized video of the calibrated helicopter instruments and the force/position measurements of flight deck controls.
Data may be acquired by using an inertial measurement system, a synchronized video of the calibrated helicopter instruments and the force/position measurements of flight deck controls.
Data may be acquired by using an inertial measurement system, a synchronized video of the calibrated helicopter instruments and the force/position measurements of flight deck controls.
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TABLE C2E.—ALTERNATIVE DATA SOURCES, PROCEDURES, AND INSTRUMENTATION—Continued
[The standards in this table are required if the data gathering methods described in paragraph 9 of Appendix C are not used.]
QPS requirements
Table of objective tests
Level B only
Test reference number and title
2.c.4. Longitudinal Handling qualities.
Maneuvering stability.
X
2.d.1.a Lateral Handling qualities. Control Response.
X
2.d.1.b Directional Handling
Control response.
qualities.
X
Directional
X
2.d.3.a Handling qualities Dynamic Lateral and Directional Stability Lateral-Directional Oscillations.
X
2.d.3.b. Handling qualities Dynamic Lateral and Directional Stability Spiral Stability.
X
2.d.3.c Handling qualities. Dynamic Lateral and Directional Stability. Adverse/
Proverse Yaw.
X
2.d.2. Handling
Static Stability.
qualities.
lllllllllllllllllllll
Begin Information
18. Visual Display Systems
a. Basic principles of an FSTD collimated
display:
(1) The essential feature of a collimated
display is that light rays coming from a given
point in a picture are parallel. There are two
main implications of the parallel rays:
(a) The viewer’s eyes focus at infinity and
have zero convergence, providing a cue that
the object is distant; and
(b) The angle to any given point in the
picture does not change when viewed from
a different position so the object behaves
geometrically as though it were located at a
significant distance from the viewer. These
cues are self-consistent, and are appropriate
for any object that has been modelled as
being at a significant distance from the
viewer.
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Alternative data sources, procedures,
and instrumentation
Data may be acquired by using an inertial measurement system, a synchronized video of the calibrated helicopter instruments and the force/position measurements of flight deck controls.
Data may be acquired by using an inertial measurement system, a synchronized video of the calibrated helicopter instruments and the force/position measurements of flight deck controls.
Data may be acquired by using an inertial measurement system and a synchronized video of calibrated helicopter instruments and force/position
measurements of flight deck directional controls.
Data may be acquired by using an inertial measurement system and a synchronized video of calibrated helicopter instruments and force/position
measurements of flight deck directional controls.
Data may be acquired by using an inertial measurement system and a synchronized video of the calibrated helicopter instruments, the force/position
measurements of flight deck controls,
and a stop watch.
Data may be acquired by using an inertial measurement system and a synchronized video of the calibrated helicopter instruments, the force/position
measurements of flight deck controls,
and a stop watch.
Data may be acquired by using an inertial measurement system and a synchronized video of the calibrated helicopter instruments, the force/position
measurements of flight deck controls.
(2) In an ideal situation the rays are
perfectly parallel, but most implementations
provide only an approximation to the ideal.
Typically, an FSTD display provides an
image located not closer than about 20–33 ft
(6–10 m) from the viewer, with the distance
varying over the field of view. A schematic
representation of a collimated display is
provided in Figure C2A.
(3) Collimated displays are well suited to
many simulation applications as the area of
interest is relatively distant from the observer
so the angles to objects should remain
independent of viewing position. Consider
the view of the runway seen by the flight
crew lined up on an approach. In the real
world, the runway is distant and the light
rays from the runway to the eyes are parallel.
The runway appears to be straight ahead to
both crew members. This situation is well
simulated by a collimated display and is
presented in Figure C2B. Note that the
distance to the runway has been shortened
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for clarity. If drawn to scale, the runway
would be farther away and the rays from the
two seats would be closer to being parallel.
(4) While the horizontal field of view of a
collimated display can be extended to
approximately 210°–220°, the vertical field of
view has been limited to about 40°–45°.
These limitations result from tradeoffs in
optical quality and interference between the
display components and flight deck
structures, but were sufficient to meet FSTD
regulatory approval for Helicopter FSTDs.
However, recent designs have been
introduced with vertical fields of view of up
to 60° for helicopter applications.
b. Basic principles of an FSTD dome (or
non-collimated) display:
(1) The situation in a dome display is
shown in Figure C2C. As the angles can be
correct for only one eye point at a time, the
visual system in the figure has been aligned
for the right seat eye point position. The
runway appears to be straight ahead of the
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aircraft for this viewer. For the left seat
viewer, however, the runway appears to be
somewhat to the right of the aircraft. As the
aircraft is still moving towards the runway,
the perceived velocity vector will be directed
towards the runway and this will be
interpreted as the aircraft having some yaw
offset.
(2) The situation is substantially different
for near field objects encountered in
helicopter operations close to the ground. In
those cases, objects that should be
interpreted as being close to the viewer will
be misinterpreted as being distant in a
collimated display. The errors can actually be
reduced in a dome display.
(3) The field of view possible with a dome
display can be larger than that of a collimated
display. Depending on the configuration, a
field of view of 240° by 90° is possible and
can be exceeded.
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c. Additional display considerations
(1) While the situations described above
are for discrete viewing positions, the same
arguments can be extended to moving eye
points produced by the viewer’s head
movement. In the real world, the parallax
effects resulting from head movement
provide distance cues. The effect is
particularly strong for relative movement of
flight deck structure in the near field and
modelled objects in the distance. Collimated
displays will provide accurate parallax cues
for distant objects, but increasingly
inaccurate cues for near field objects. The
situation is reversed for dome displays.
(2) Stereopsis cues resulting from the
different images presented to each eye for
objects relatively close to the viewer also
provide depth cues. Again, the collimated
and dome displays provide more or less
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accurate cues depending on the modelled
distance of the objects being viewed.
d. Training implications
(1) In view of the basic principles
described above, it is clear that neither
display approach provides a completely
accurate image for all possible object
distances. The sponsor should consider the
training role of the FSTD when configuring
the display system to make the optimum
choice. Factors that should be considered
include relative importance of training tasks
at low altitudes, the role of the two crew
members in the flying tasks, and the field of
view required for specific training tasks.
BILLING CODE 4910–13–P
lllllllllllllllllllll
End Information
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BILLING CODE 4910–13–C
Attachment 3 to Appendix C to Part 60—
Simulator Subjective Evaluation
lllllllllllllllllllll
Begin QPS Requirements
1. Requirements
a. Except for special use visual scenes and
airport models described below, all visual
scenes and airport models required by this
part must be representations of real-world,
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operational airports or representations of
fictional airports and must meet the
requirements set out in Tables C3B and C3C
of this attachment, as appropriate.
b. If fictional airports are used, the sponsor
must ensure that navigational aids and all
appropriate maps, charts, and other
navigational reference material for the
fictional airports (and surrounding areas as
necessary) are compatible, complete, and
accurate with respect to the visual
presentation and scene content of the visual
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59803
model of this fictional airport. An SOC must
be submitted that addresses navigation aid
installation and performance and other
criteria (including obstruction clearance
protection) for all instrument approaches to
the fictional airports that are available in the
simulator. The SOC must reference and
account for information in the terminal
instrument procedures manual and the
construction and availability of the required
maps, charts, and other navigational material.
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This material must be clearly marked ‘‘for
training purposes only.’’
c. When the simulator is being used by an
instructor or evaluator for purposes of
training, checking, or testing under this
chapter, only visual scenes and airport
models classified as Class I, Class II, or Class
III may be available to the instructor or
evaluator. The classifications are as follows:
(1) Class I (whether modeling real world
airports or fictional airports), for those visual
scenes and airport models used for simulator
qualification at a specified level. These visual
scenes and airport models must meet the
minimum requirements in Table C3B of this
attachment, be evaluated by the NSPM, be
listed on the Statement of Qualification
(SOQ), and be available for use at the
simulator IOS.
(2) Class II (whether modeling real world
airports or fictional airports), for those visual
scenes and airport models that are in excess
of those used for simulator qualification at a
specified level. These visual scenes and
airport models must meet the minimum
requirements set out in Table C3C of this
attachment. These visual scenes and airport
models may be made available on the
simulator IOS without further involvement of
the NSPM or the TPAA.
(3) For an interim period (ending 2 years
after the publication of the final rule in the
Federal Register), Class III visual scenes and
airport models (whether modeling real world
airports, generic airports, or fictional
airports) may be approved for specific
purposes by the TPAA or a foreign regulatory
authority for a foreign user of the device.
Examples of approved activities include
specific airport or runway qualification, very
low visibility operations training, including
Surface Movement Guidance System (SMGS)
operations, or use of a specific airport visual
model aligned with an instrument procedure
for another airport for instrument training. At
the end of the interim period, all Class III
visual scenes and airport models must be
classified as either a Class I or a Class II
visual scene or airport model or be removed
from availability at the simulator IOS.
However, Class III visual scenes and airport
models may continue to be used after the end
of the interim period if they are part of a
training program specifically approved by the
TPAA or other regulatory authority that uses
a task and capability analysis as the basis for
approval of this specific media element, (i.e.,
the specific scene or model selected for use
in that program).
d. When a person sponsors an FSTD
maintained by a person other than a U.S.
certificate holder, the sponsor is accountable
for that FSTD originally meeting, and
continuing to meet, the criteria under which
it was originally qualified and the
appropriate part 60 criteria, including the
visual scenes and airport models that may be
used by instructors or evaluators for purposes
of training, checking, or testing under this
chapter.
e. Neither Class II nor Class III airport
visual models are required to appear on the
SOQ. However, the sponsor is accountable
that the FSTD originally meets, and
continues to meet, the visual scene and
airport model requirements for Class II or
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Class III visual scenes and airport models
that may be used by instructors or evaluators
for training, checking, or testing under this
chapter.
f. When the visual scenes and airport
models represent real world airports and a
permanent change is made to that real world
airport (e.g., a new runway, an extended
taxiway, a new lighting system, a runway
closure) without a written extension grant
from the NSPM (described below), an update
to that visual scene or airport model must be
made in accordance with the following time
limits:
(1) For a new airport runway, a runway
extension, a new airport taxiway, a taxiway
extension, or a runway/taxiway closure—
within 60 days of the opening for use of the
new airport runway, runway extension, new
airport taxiway, or taxiway extension; or
within 60 days of the closure of the runway
or taxiway.
(2) For a new or modified approach light
system—within 30 days of the activation of
the new or modified approach light system.
(3) For other facility or structural changes
on the airport (e.g., new terminal, relocation
of Air Traffic Control Tower)—within 6
months of the opening of the new or changed
facility or structure.
g. If a sponsor desires an extension to the
time limit for an update to a visual scene or
airport model, the sponsor must provide a
written extension request to the POI/TCPM
stating the reason for the update delay and
a proposed completion date. A copy of this
request must also be sent to the NSPM. The
sponsor will forward a copy of the POI/
TCPM’s response to the NSPM. If the POI/
TCPM has granted an extension, the NSPM
will issue an extension authorization, not to
exceed an additional 12 months.
End QPS Requirements
lllllllllllllllllllll
Begin Information
2. Discussion
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 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 may 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 C3A, Operations
Tasks, in this attachment address pilot
functions, including maneuvers and
procedures (called flight tasks), and are
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 C3A, Operations
Tasks, and Table C3G, Instructor Operating
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Station, in this attachment address 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. This appendix addresses helicopter
simulators at Levels B, C, and D because
there are no Level A Helicopter simulators.
h. The FAA intends to allow the use of
Class III visual scenes and airport models on
a limited basis when the sponsor provides
the TPAA (or other regulatory authority) an
appropriate analysis of the skills, knowledge,
and abilities (SKAs) necessary for competent
performance of the tasks in which this
particular media element is used. The
analysis should describe the ability of the
FSTD/visual media to provide an adequate
environment in which the required SKAs
may be satisfactorily performed and learned.
The analysis should also include the specific
media element, such as the visual scene or
airport model. Additional sources of
information on the conduct of task and
capability analysis may be found on the
FAA’s Advanced Qualification Program
(AQP) Web site at: https://www.faa.gov/
education_research/training/aqp/.
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i. Previously qualified simulators with
certain early generation Computer Generated
Image (CGI) visual systems, are limited by the
capability of the Image Generator or the
display system used. These systems are:
(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) Rediffusion SP1, SP1T, and SP2.
(2) Early CGI visual systems are excepted
from the necessity of including runway
numbers unless the 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) Rediffusion 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 are:
(a) Rediffusion 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
<<>>
Number
Simulator
level
Operations tasks
B
C
D
Tasks in this table are subject to evaluation if appropriate for the airplane simulated as indicated in the SOQ Configuration List 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. .....................
Flight deck check: switches, indicators, systems, and equipment .........................................................................
X
X
X
2. APU/Engine start and run-up
2.a. .....................
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. .....................
Rotor engagement ...................................................................................................................................................
X
X
X
2.e. .....................
System checks ........................................................................................................................................................
X
X
X
3. Taxiing—Ground
3.a. .....................
Power required to taxi .............................................................................................................................................
X
X
X
3.b. .....................
Brake effectiveness .................................................................................................................................................
X
X
X
3.c. .....................
Ground handling ......................................................................................................................................................
X
X
X
3.d. .....................
Water handling (if applicable) .................................................................................................................................
X
X
3.e. .....................
Abnormal/emergency procedures:
X
X
3.e.1. ..................
Brake system failure ............................................................................................................................................
X
3.e.2. ..................
Ground resonance ...............................................................................................................................................
X
X
3.e.3. ..................
Dynamic rollover ..................................................................................................................................................
X
X
3.e.4. ..................
Deployment of emergency floats/water landing ..................................................................................................
X
X
3.e.5. ..................
Others listed on the Statement of Qualification ..................................................................................................
A
X
X
4.a. .....................
Takeoff to a hover ...................................................................................................................................................
X
X
X
4.b. .....................
Instrument response:
4. Taxiing—Hover
4.b.1. ..................
Engine instruments ..............................................................................................................................................
X
X
X
4.b.2. ..................
Flight instruments ................................................................................................................................................
X
X
X
4.b.3. ..................
Hovering turns .....................................................................................................................................................
X
X
X
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TABLE C3A.—FUNCTIONS AND SUBJECTIVE TESTS—Continued
<<>>
Number
Simulator
level
Operations tasks
B
4.c. .....................
C
D
Hover power checks:
4.c.1. ..................
In ground effect (IGE) ..........................................................................................................................................
X
X
X
4.c.2. ..................
Out of ground effect (OGE) .................................................................................................................................
X
X
X
4.d. .....................
Crosswind/tailwind hover .........................................................................................................................................
X
X
X
4.e. .....................
Translating tendency ...............................................................................................................................................
X
X
X
4.f. ......................
External load operations:
4.f.1. ...................
Hookup .................................................................................................................................................................
X
X
4.f.2. ...................
Release ................................................................................................................................................................
X
X
4.f.3. ...................
Winch operations .................................................................................................................................................
X
X
4.g. .....................
Abnormal/emergency procedures:
4.g.1. ..................
Engine failure .......................................................................................................................................................
X
X
X
4.g.2. ..................
Fuel governing system failure .............................................................................................................................
X
X
X
4.g.3. ..................
Settling with power (OGE) ...................................................................................................................................
X
X
X
4.g.4. ..................
Hovering autorotation ..........................................................................................................................................
X
X
4.g.5. ..................
Stability augmentation system failure ..................................................................................................................
X
X
X
4.g.6. ..................
Directional control malfunction ............................................................................................................................
X
X
X
4.g.7. ..................
Loss of tail rotor effectiveness (LTE) ..................................................................................................................
X
X
4.g.8. ..................
Others listed on the Statement of Qualification ..................................................................................................
A
X
X
4.h. .....................
Pre-takeoff checks ...................................................................................................................................................
X
X
X
5. Takeoff/Translational Flight
5.a. .....................
Forward (up to effective translational lift) ................................................................................................................
X
X
5.b. .....................
Sideward (up to limiting airspeed) ..........................................................................................................................
X
X
5.c. .....................
Rearward (up to limiting airspeed) ..........................................................................................................................
X
X
6. Takeoff and Departure Phase
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. ..................
Takeoff from a confined area ..............................................................................................................................
X
X
X
6.a.8. ..................
Takeoff from a pinnacle/platform .........................................................................................................................
X
X
X
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE C3A.—FUNCTIONS AND SUBJECTIVE TESTS—Continued
<<>>
Number
Simulator
level
Operations tasks
B
C
D
X
X
X
X
X
6.a.9. ..................
Takeoff from a slope ............................................................................................................................................
6.a.10. ................
External load operations ......................................................................................................................................
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
6.b.1.b. ...............
Cat B ................................................................................................................................................................
X
X
6.c. .....................
Rejected takeoff:
6.c.1. ..................
Land .....................................................................................................................................................................
X
X
X
6.c.2. ..................
Water (if appropriate) ...........................................................................................................................................
X
X
X
6.d. .....................
Instrument departure ...............................................................................................................................................
X
X
X
6.e. .....................
Others as listed on the Statement of Qualification .................................................................................................
A
X
X
7.a. .....................
Normal .....................................................................................................................................................................
X
X
X
7.b. .....................
Obstacle clearance ..................................................................................................................................................
X
X
X
7.c. .....................
Vertical .....................................................................................................................................................................
X
X
7.d. .....................
One engine inoperative ...........................................................................................................................................
X
X
X
7.e. .....................
Others as listed on the Statement of Qualification .................................................................................................
A
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)
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
7. Climb
8. Cruise
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE C3A.—FUNCTIONS AND SUBJECTIVE TESTS—Continued
<<>>
Number
Simulator
level
Operations tasks
B
C
D
8.g.8. ..................
Rotor vibrations ....................................................................................................................................................
X
X
X
8.g.9. ..................
Recovery from unusual altitudes .........................................................................................................................
X
X
X
9.a. .....................
Normal .....................................................................................................................................................................
X
X
X
9.b. .....................
Maximum rate ..........................................................................................................................................................
X
X
X
9.c. .....................
Autorotative:
9. Descent
9.c.1. ..................
Straight-in .............................................................................................................................................................
X
X
X
9.c.2. ..................
With turn ..............................................................................................................................................................
X
X
X
9.d. .....................
External Load ..........................................................................................................................................................
X
X
10. Approach
10.a. ...................
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. .............
Circling .............................................................................................................................................................
X
X
X
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. ................
Manually controlled—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. .............
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
10.b.3.c. .............
Autopilot*only ...................................................................................................................................................
X
X
X
10.b.3.c. .............
Cat I ..................................................................................................................................................................
X
X
X
10.b.3.c. .............
Cat II .................................................................................................................................................................
X
X
X
10.b.4. ................
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE C3A.—FUNCTIONS AND SUBJECTIVE TESTS—Continued
<<>>
Number
Simulator
level
Operations tasks
B
C
D
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. ...................
Others as listed on the Statement of Qualification .................................................................................................
A
X
X
11. Landings and Approaches to Landings
11.a. ...................
Visual approaches:
11.a.1. ................
Normal .................................................................................................................................................................
X
X
X
11.a.2. ................
Steep ....................................................................................................................................................................
X
X
X
11.a.3. ................
Shallow ................................................................................................................................................................
X
X
X
11.a.4. ................
Crosswind ............................................................................................................................................................
X
X
X
11.a.5. ................
Category A profile ................................................................................................................................................
X
X
11.a.6. ................
Category B profile ................................................................................................................................................
X
X
11.a.7. ................
External Load .......................................................................................................................................................
X
X
11.b. ...................
Abnormal/emergency procedures:
11.b.1. ................
Directional control failure .....................................................................................................................................
X
X
X
11.b.2. ................
Hydraulics failure .................................................................................................................................................
X
X
X
11.b.3. ................
Fuel governing failure ..........................................................................................................................................
X
X
X
11.b.4. ................
Autorotation ..........................................................................................................................................................
X
X
X
11.b.5. ................
Stability system failure .........................................................................................................................................
X
X
X
11.b.6. ................
Others listed on the Statement of Qualification ..................................................................................................
A
X
X
11.c. ...................
Landings:
11.c.1. ................
Normal .................................................................................................................................................................
X
X
X
11.c.1.a. .............
Running ............................................................................................................................................................
X
X
X
11.c.1.b. .............
From Hover ......................................................................................................................................................
X
X
X
11.c.2. ................
Pinnacle/platform .................................................................................................................................................
X
X
X
11.c.3. ................
Confined area ......................................................................................................................................................
X
X
X
11.c.4. ................
Slope ....................................................................................................................................................................
X
X
11.c.5. ................
Crosswind ............................................................................................................................................................
X
X
X
11.c.6. ................
Tailwind ................................................................................................................................................................
X
X
X
11.c.7. ................
Rejected Landing .................................................................................................................................................
X
X
X
11.c.8. ................
Abnormal/emergency procedures:
X
X
11.c.8.a. .............
From autorotation .............................................................................................................................................
11.c.8. ................
One or more engines inoperative ........................................................................................................................
X
X
X
11.c.8. ................
Directional control failure .....................................................................................................................................
X
X
X
11.c.8. ................
Hydraulics failure .................................................................................................................................................
X
X
X
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE C3A.—FUNCTIONS AND SUBJECTIVE TESTS—Continued
<<>>
Number
Simulator
level
Operations tasks
B
C
D
11.c.8. ................
Stability augmentation system failure ..................................................................................................................
X
X
X
11.c.8. ................
Other (as may be listed on the Statement of Qualification) ................................................................................
A
X
X
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. Any Flight Phase
12.b. ...................
Flight management and guidance system:
12.b.1. ................
Airborne radar ......................................................................................................................................................
X
X
X
12.b.2. ................
Automatic landing aids ........................................................................................................................................
X
X
X
12.b.3. ................
Autopilot ...............................................................................................................................................................
X
X
X
12.b.4. ................
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
12.b.8. ................
Navigation systems ..............................................................................................................................................
X
X
X
12.c. ...................
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
12.c.5. ................
Loss of directional control ....................................................................................................................................
X
X
X
12.c.6. ................
Loss of tail rotor effectiveness .............................................................................................................................
X
X
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE C3A.—FUNCTIONS AND SUBJECTIVE TESTS—Continued
<<>>
Number
Simulator
level
Operations tasks
B
12.c.7. ................
Others listed on the Statement of Qualification ..................................................................................................
C
D
A
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
Note: An ‘‘A’’ in the table indicates that the system, task, or procedure may be examined if the appropriate aircraft system or control is simulated in the FFS and is working properly.
TABLE C3B.—FUNCTIONS AND SUBJECTIVE TESTS
<<< QPS requirements>>>
Simulator
level
Visual scene content requirements for qualification at the stated level
Class I visual scenes/visual models
Number
B
C
D
This table specifies the minimum airport visual model content and functionality to qualify a simulator at the indicated level. This table applies
only to the airport scenes required for simulator qualification; i.e., two helicopter landing area models for Level B simulators; four helicopter
landing area models for Level C and Level D simulators.
1. .........
Functional test content requirements for Non-Zero Flight Time (NZFT) Level simulators
The following is the minimum airport/landing area model content requirement to satisfy visual capability tests, and provides suitable
visual cues to allow completion of all functions and subjective tests described in this attachment for simulators at Level B.
1.a. ......
A minimum of one (1) representative airport and one (1) representative helicopter landing area model. The airport and
the helicopter landing area may be contained within the same model. If this option is selected, the approach path to
the airport runway(s) and the approach path to the helicopter landing area must be different. The model(s) used to
meet the following requirements may be demonstrated at either a fictional or a real-world airport or helicopter landing
area, but each must be acceptable to the sponsor’s TPAA, selectable from the IOS, and listed on the Statement of
Qualification.
X
1.b. ......
The fidelity of the visual scene must be sufficient for the aircrew to visually identify the airport and/or helicopter landing
area; determine the position of the simulated helicopter within the visual scene; successfully accomplish take-offs,
approaches, and landings; and maneuver around the airport on the ground, or hover taxi, as necessary.
X
1.c. ......
Runways:
1.c.1. ...
Visible runway number ...........................................................................................................................................................
X
1.c.2. ...
Runway threshold elevations and locations must be modeled to provide sufficient correlation with helicopter systems
(e.g., altimeter).
X
1.c.3. ...
Runway surface and markings ..............................................................................................................................................
X
1.c.4. ...
Lighting for the runway in use including runway edge and centerline ..................................................................................
X
1.c.5. ...
Lighting, visual approach aid (VASI or PAPI) and approach lighting of appropriate colors .................................................
X
1.c.6. ...
Representative taxiway lights ................................................................................................................................................
X
1.d. ......
Other helicopter landing area:
1.d.1. ...
Standard heliport designation (‘‘H’’) marking, properly sized and oriented ...........................................................................
X
1.d.2. ...
Perimeter markings for the Touchdown and Lift-Off Area (TLOF) or the Final Approach and Takeoff Area (FATO), as
appropriate.
X
1.d.3. ...
Perimeter lighting for the TLOF or the FATO areas, as appropriate. ...................................................................................
X
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE C3B.—FUNCTIONS AND SUBJECTIVE TESTS—Continued
<<< QPS requirements>>>
Simulator
level
Visual scene content requirements for qualification at the stated level
Class I visual scenes/visual models
Number
B
C
D
1.d.4. ...
Appropriate markings and lighting to allow movement from the runway or helicopter landing area to another part of the
landing facility.
X
2. .........
Functional test content requirements for Level C and Level D simulators
The following is the minimum airport/landing area model content requirement to satisfy visual capability tests, and provide suitable visual cues to allow completion of all functions and subjective tests described in this attachment for simulators at Level C and Level D.
Not all of the elements described in this section must be found in a single airport/landing area scene. However, all of the elements described in this section must be found throughout a combination of the four (4) airport/landing area models described in item 2.a. The
representations of the hazards (as described in 2.d.) must be ‘‘hard objects’’ that interact as such if contacted by the simulated helicopter. Additionally, surfaces on which the helicopter lands must be ‘‘hard surfaces.’’ The model(s) used to meet the following requirements must be demonstrated at either a fictional or a real-world airport or helicopter landing area, and each must be acceptable to the
sponsor’s TPAA, selectable from the IOS, and listed on the Statement of Qualification.
2.a. ......
There must be at least the following airport/helicopter landing areas
2.a.1. ...
At least one (1) representative airport ...................................................................................................................................
2.a.2. ...
At least three representative non-airport landing areas, as follows:
2.a.2.a.
X
X
At least one (1) representative helicopter landing area situated on a substantially elevated surface with respect to the
surrounding structures or terrain (e.g., building top, offshore oil rig).
X
X
2.a.2.b.
At least one (1) helicopter landing area that meets the definition of a ‘‘confined landing area’’ ..........................................
X
X
2.a.2.c.
At least one (1) helicopter landing area on a sloped surface where the slope is at least 21⁄2° ...........................................
X
X
2.b. ......
For each of the airport/helicopter landing areas described in 2.a., the simulator must be able to provide at least the following:.
X
X
2.b.1. ...
A night and twilight (dusk) environment ................................................................................................................................
X
X
2.b.2. ...
A daylight environment ..........................................................................................................................................................
X
X
2.c. ......
Non-airport helicopter landing areas must have the following:
2.c.1. ...
Representative buildings, structures, and lighting within appropriate distances ...................................................................
X
X
2.c.2. ...
Representative moving and static clutter (e.g., other aircraft, power carts, tugs, fuel trucks) ..............................................
X
X
2.c.3. ...
Representative depiction of terrain and obstacles as well as significant and identifiable natural and cultural features,
within 25 NM of the reference landing area.
X
X
2.c.4. ...
Standard heliport designation (‘‘H’’) marking, properly sized and oriented ...........................................................................
X
X
2.c.5. ...
Perimeter markings for the Touchdown and Lift-Off Area (TLOF) or the Final Approach and Takeoff Area (FATO), as
appropriate.
X
X
2.c.6. ...
Perimeter lighting for the TLOF or the FATO areas, as appropriate ....................................................................................
X
X
2.c.7. ...
Appropriate markings and lighting to allow movement from the area to another part of the landing facility, if appropriate
X
X
2.c.8. ...
Representative markings, lighting, and signage, including a windsock that gives appropriate wind cues ...........................
X
X
2.c.9. ...
Appropriate markings, lighting, and signage necessary for position identification, and to allow movement from the landing area to another part of the landing facility.
X
X
2.c.10.
Representative moving and static ground traffic (e.g., vehicular and aircraft), including the ability to present surface
hazards (e.g., conflicting traffic, vehicular or aircraft, on or approaching the landing area).
X
X
2.c.11.
Portrayal of landing surface contaminants, including lighting reflections when wet and partially obscured lights when
snow is present, or suitable alternative effects.
X
X
2.d. ......
All of the following three (3) hazards must be presented in a combination of the three (3) non-airport landing areas (described in item
2.a.2.) and each of these non-airport landing areas must have at least one of the following hazards:
2.d.1. ...
Other airborne traffic ..............................................................................................................................................................
X
X
2.d.2. ...
Buildings, trees, or other vertical obstructions in the immediate landing area .....................................................................
X
X
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE C3B.—FUNCTIONS AND SUBJECTIVE TESTS—Continued
<<< QPS requirements>>>
Simulator
level
Visual scene content requirements for qualification at the stated level
Class I visual scenes/visual models
Number
B
C
D
X
X
2.d.3. ...
Suspended wires in the immediate landing area ..................................................................................................................
2.e. ......
Airport applications. Each airport must have the following:
2.e.1. ...
At least one runway designated as ‘‘in-use,’’ appropriately marked and capable of being lighted fully ..............................
X
X
2.e.2. ...
Runway threshold elevations and locations must be modeled to provide sufficient correlation with helicopter systems
(e.g., HGS, GPS, altimeter); slopes in runways, taxiways, and ramp areas may not cause distracting or unrealistic effects, including pilot eye-point height variation.
X
X
2.e.3. ...
Appropriate approach lighting systems and airfield lighting for a VFR circuit and landing, non-precision approaches and
landings, and precision approaches and landings, as appropriate.
X
X
2.e.4. ...
Representative taxiway lights ................................................................................................................................................
3. .........
Visual scene management
The following is the minimum visual scene management requirements for simulators at the NZFT and ZFT levels.
3.a. ......
Runway and helicopter landing area approach lighting must fade into view in accordance with the environmental conditions set in the simulator.
X
X
X
3.b. ......
The direction of strobe lights, approach lights, runway edge lights, visual landing aids, runway centerline lights, threshold lights, touchdown zone lights, and TLOF or FATO lights must be replicated.
X
X
X
4. .........
Visual feature recognition
The following are the minimum distances at which runway features must be visible for simulators at the NZFT and ZFT simulator levels. Distances are measured from runway threshold or a helicopter landing area to a helicopter aligned with the runway or helicopter
landing area on an extended 3° glide-slope in simulated meteorological conditions. For circling approaches, all tests apply to the runway used for the initial approach and to the runway of intended landing.
4.a. ......
For runways: runway definition, strobe lights, approach lights, and runway edge lights from 5 sm (8 km) of the runway
threshold.
X
X
X
4.b. ......
For runways: centerline lights and taxiway definition from 3 sm (5 km) ...............................................................................
X
X
X
4.c. ......
For runways: Visual Approach Aid lights (VASI or PAPI) from 3 sm (5 km) of the threshold ..............................................
X
X
X
4.d. ......
For runways: Visual Approach Aid lights (VASI or PAPI) from 5 sm (8 km) of the threshold ..............................................
X
X
4.e. ......
For runways: runway threshold lights and touchdown zone lights from 2 sm (3 km) ..........................................................
X
X
X
4.f. .......
For runways and helicopter landing areas: markings within range of landing lights for night/twilight scenes and the surface resolution test on daylight scenes, as required.
X
X
X
4.g. ......
For circling approaches, the runway of intended landing and associated lighting must fade into view in a non-distracting
manner.
X
X
X
4.h. ......
For helicopter landing areas: landing direction lights and raised FATO lights from 1 sm (1.5 km) .....................................
X
X
X
4.i. .......
For helicopter landing areas: Flush mounted FATO lights, TOFL lights, and the lighted windsock from 0.5 sm (750 m) ..
X
4.j. .......
Hover taxiway lighting (yellow/blue/yellow cylinders) from TOFL area .................................................................................
X
5. .........
Airport or Helicopter Landing Area Model Content
The following prescribes the minimum requirements for an airport/helicopter landing area visual model and identifies other aspects of
the environment that must correspond with that model for simulators at Level B, Level C, and Level D. For circling approaches, all
tests apply to the runway used for the initial approach and to the runway of intended landing. If all runways or landing areas in a visual model used to meet the requirements of this attachment are not designated as ‘‘in use,’’ then the ‘‘in use’’ runways/landing areas
must be listed on the Statement of Qualification (e.g., KORD, Rwys 9R, 14L, 22R). Models of airports or helicopter landing areas with
more than one runway or landing area must have all significant runways or landing areas not ‘‘in-use’’ visually depicted for airport runway/landing area recognition purposes. The use of white or off-white light strings that identify the runway or landing area for twilight
and night scenes are acceptable for this requirement; and rectangular surface depictions are acceptable for daylight scenes. A visual
system’s capabilities must be balanced between providing visual models with an accurate representation of the airport and a realistic
representation of the surrounding environment. Each runway or helicopter landing area designated as an ‘‘in-use’’ runway or area
must include the following detail that is either modeled using airport/heliport pictures, construction drawings and maps, U.S. National
Imagery and Mapping Agency data, or other data, or modeled in accordance with published regulatory material.
5.a. ......
The surface and markings for each ‘‘in-use’’ runway or helicopter landing area must include the following:
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE C3B.—FUNCTIONS AND SUBJECTIVE TESTS—Continued
<<< QPS requirements>>>
Simulator
level
Visual scene content requirements for qualification at the stated level
Class I visual scenes/visual models
Number
B
C
D
5.a.1. ...
For airports: runway threshold markings, runway numbers, touchdown zone markings, fixed distance markings, runway
edge markings, and runway centerline stripes.
X
X
X
5.a.2. ...
For helicopter landing areas: markings for standard heliport identification (‘‘H’’) and TOFL, FATO, and safety areas .......
X
X
X
5.b. ......
The lighting for each ‘‘in-use’’ runway or helicopter landing area must include the following:
5.b.1. ...
For airports: runway approach, threshold, edge, end, centerline (if applicable), touchdown zone (if applicable), leadoff,
and visual landing aid lights or light systems for that runway.
X
X
X
5.b.2. ...
For helicopter landing areas: landing direction, raised and flush FATO, TOFL, windsock lighting ......................................
X
X
X
5.c. ......
The taxiway surface and markings associated with each ‘‘in-use’’ runway or helicopter landing area must include the following:
5.c.1. ...
For airports: taxiway edge, centerline (if appropriate), runway hold lines, and ILS critical area(s) ......................................
X
X
X
5.c.2. ...
For helicopter landing areas: taxiways, taxi routes, and aprons ...........................................................................................
X
X
X
5.d. ......
The taxiway lighting associated with each ‘‘in-use’’ runway or helicopter landing area must include the following:
5.d.1. ...
For airports: runway edge, centerline (if appropriate), runway hold lines, ILS critical areas ................................................
X
X
X
5.d.2. ...
For helicopter landing areas: taxiways, taxi routes, and aprons ...........................................................................................
X
X
X
5.d.3. ...
For airports: taxiway lighting of correct color .........................................................................................................................
5.e. ......
Airport signage associated with each ‘‘in-use’’ runway or helicopter landing area must include the following:
5.e.1. ...
For airports: signs for runway distance remaining, intersecting runway with taxiway, and intersecting taxiway with taxiway.
X
X
X
5.e.2. ...
For helicopter landing areas: as may be appropriate for the model used ............................................................................
X
X
X
5.f. .......
Required visual model correlation with other aspects of the airport or helicopter landing environment simulation:
5.f.1. ....
The airport or helicopter landing area model must be properly aligned with the navigational aids that are associated
with operations at the ‘‘in-use’’ runway or helicopter landing area.
X
X
X
5.f.2. ....
The simulation of runway or helicopter landing area contaminants must be correlated with the displayed runway surface
and lighting where applicable.
X
X
6. .........
Correlation with helicopter and associated equipment
The following are the minimum correlation comparisons that must be made for simulators at Level B, Level C, and Level D.
6.a. ......
Visual system compatibility with aerodynamic programming ................................................................................................
X
X
X
6.b. ......
Visual cues to assess sink rate and depth perception during landings ................................................................................
X
X
X
6.c. ......
Accurate portrayal of environment relating to flight simulator attitudes ................................................................................
X
X
X
6.d. ......
The visual scene must correlate with integrated helicopter systems, where fitted (e.g., terrain, traffic and weather avoidance systems and Head-up Guidance System (HGS)).
X
X
X
6.e. ......
Representative visual effects for each visible, own-ship, helicopter external light(s) ...........................................................
X
X
X
6.f. .......
The effect of rain removal devices ........................................................................................................................................
X
X
7. .........
Scene quality
The following are the minimum scene quality tests that must be conducted for simulators at Level B, Level C, and Level D.
7.a. ......
Surfaces and textural cues must be free from apparent quantization (aliasing) ..................................................................
X
X
7.b. ......
System capable of portraying full color realistic textural cues ..............................................................................................
X
X
7.c. ......
The system light points must be free from distracting jitter, smearing or streaking .............................................................
X
X
X
7.d. ......
Demonstration of occulting through each channel of the system in an operational scene ..................................................
X
X
X
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE C3B.—FUNCTIONS AND SUBJECTIVE TESTS—Continued
<<< QPS requirements>>>
Simulator
level
Visual scene content requirements for qualification at the stated level
Class I visual scenes/visual models
Number
B
C
D
7.e. ......
Demonstration of a minimum of ten levels of occulting through each channel of the system in an operational scene ......
X
X
7.f. .......
System capable of providing focus effects that simulate rain ...............................................................................................
X
X
7.g. ......
System capable of providing focus effects that simulate light point perspective growth ......................................................
X
X
7.h. ......
Runway light controls capable of six discrete light steps (0–5) ............................................................................................
X
X
8. .........
Environmental effects
The following are the minimum environmental effects that must be available in simulators at Level B, Level C, and Level D.
8.a. ......
The displayed scene corresponding to the appropriate surface contaminants and include appropriate lighting reflections
for wet, partially obscured lights for snow, or alternative effects.
8.b. ......
Special weather representations which include:
8.b.1. ...
The sound, motion and visual effects of light, medium and heavy precipitation near a thunderstorm on take-off, approach, and landings at and below an altitude of 2,000 ft (600 m) above the surface and within a radius of 10 sm (16
km) from the airport or helicopter landing area.
X
8.b.2. ...
One airport or helicopter landing area with a snow scene to include terrain snow and snow-covered surfaces ................
X
8.c. ......
In-cloud effects such as variable cloud density, speed cues and ambient changes ............................................................
X
X
8.d. ......
The effect of multiple cloud layers representing few, scattered, broken and overcast conditions giving partial or complete obstruction of the ground scene.
X
X
8.e. ......
Visibility and RVR measured in terms of distance. Visibility/RVR checked at 2,000 ft (600 m) above the airport or helicopter landing area and at two heights below 2,000 ft with at least 500 ft of separation between the measurements.
The measurements must be taken within a radius of 10 sm (16 km) from the airport or helicopter landing area.
X
X
8.f. .......
Patchy fog giving the effect of variable RVR .........................................................................................................................
8.g. ......
Effects of fog on airport lighting such as halos and defocus ................................................................................................
X
X
8.h. ......
Effect of own-ship lighting in reduced visibility, such as reflected glare, including landing lights, strobes, and beacons ...
X
X
8.i. .......
Wind cues to provide the effect of blowing snow or sand across a dry runway or taxiway selectable from the instructor
station.
X
8.j. .......
‘‘White-out’’ or ‘‘Brown-out’’ effects due to rotor downwash beginning at a distance above the ground equal to the rotor
diameter.
X
9. .........
Instructor control of the following:
The following are the minimum instructor controls that must be available in simulators at the NZFT and ZFT simulator levels.
9.a. ......
Environmental effects, e.g. cloud base, cloud effects, cloud density, visibility in statute miles/kilometers and RVR in
feet/meters.
X
X
X
9.b. ......
Airport or helicopter landing area selection ...........................................................................................................................
X
X
X
9.c. ......
Airport or helicopter landing area lighting, including variable intensity .................................................................................
X
X
X
9.d. ......
Dynamic effects including ground and flight traffic ................................................................................................................
X
X
X
X
X
X
End QPS Requirement
Begin Information
10. .......
An example of being able to combine two airport models to achieve two ‘‘in-use’’ runways: One runway designated as the ‘‘in-use’’
runway in the first model of the airport, and the second runway designated as the ‘‘in-use’’ runway in the second model of the same
airport. For example, the clearance is for the ILS approach to Runway 27, Circle to Land on Runway 18 right. Two airport visual models might be used: the first with Runway 27 designated as the ‘‘in use’’ runway for the approach to runway 27, and the second with
Runway 18 Right designated as the ‘‘in use’’ runway. When the pilot breaks off the ILS approach to runway 27, the instructor may
change to the second airport visual model in which runway 18 Right is designated as the ‘‘in use’’ runway, and the pilot would make a
visual approach and landing. This process is acceptable to the FAA as long as the temporary interruption due to the visual model
change is not distracting to the pilot.
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE C3B.—FUNCTIONS AND SUBJECTIVE TESTS—Continued
<<< QPS requirements>>>
Simulator
level
Visual scene content requirements for qualification at the stated level
Class I visual scenes/visual models
Number
B
11. .......
C
D
Sponsors are not required to provide every detail of a runway, but the detail that is provided should be correct within
reasonable limits.
End Information
TABLE C3C.—FUNCTIONS AND SUBJECTIVE TESTS
<<>>
Visual scene content additional visual models beyond minimum required for qualification
Class II visual scenes/visual models
Number
Simulator
level
B
C
D
This table specifies the minimum airport or helicopter landing area visual model content and functionality necessary to add visual models to a
simulator’s visual model library (i.e., beyond those necessary for qualification at the stated level) without the necessity of further involvement
of the NSPM or TPAA.
1. ..........
Visual scene management
The following is the minimum visual scene management requirements for simulators at Levels B, C, and D.
1.a. .......
The installation and direction of the following lights must be replicated for the ‘‘in-use’’ surface:
1.a.1. ....
For ‘‘in-use’’ runways: Strobe lights, approach lights, runway edge lights, visual landing aids, runway centerline lights,
threshold lights, and touchdown zone lights.
X
X
X
1.a.2. ....
For ‘‘in-use’’ helicopter landing areas: Ground level TLOF perimeter lights, elevated TLOF perimeter lights (if applicable), Optional TLOF lights (if applicable), ground FATO perimeter lights, elevated TLOF lights (if applicable), landing
direction lights.
X
X
X
2. ..........
Visual feature recognition
The following are the minimum distances at which runway or landing area features must be visible for simulators at Level B, C, and
D. Distances are measured from runway threshold or a helicopter landing area to an aircraft aligned with the runway or helicopter
landing area on a 3° glide-slope from the aircraft to the touchdown point, in simulated meteorological conditions. For circling approaches, all tests apply to the runway used for the initial approach and to the runway of intended landing.
2.a. .......
For Runways:
2.a.1. ....
Strobe lights, approach lights, and edge lights from 5 sm (8 km) of the threshold .............................................................
X
X
X
2.a.2. ....
Centerline lights and taxiway definition from 3 sm (5 km) ....................................................................................................
X
X
X
2.a.3. ....
Visual Approach Aid lights (VASI or PAPI) from 3 sm (5 km) of the threshold ...................................................................
X
X
X
2.a.4. ....
Visual Approach Aid lights (VASI or PAPI) from 5 sm (8 km) of the threshold ...................................................................
X
X
X
2.a.5. ....
Threshold lights and touchdown zone lights from 2 sm (3 km) ............................................................................................
X
X
X
2.a.6. ....
Markings within range of landing lights for night/twilight (dusk) scenes and as required by the surface resolution test on
daylight scenes.
X
X
X
2.a.7. ....
For circling approaches, the runway of intended landing and associated lighting must fade into view in a non-distracting
manner.
X
X
X
2.b. .......
For Helicopter landing areas:
2.b.1. ....
Landing direction lights and raised FATO lights from 1 sm (1.5 km) ...................................................................................
X
X
X
2.b.2. ....
Flush mounted FATO lights, TOFL lights, and the lighted windsock from 0.5 sm (750 m) .................................................
X
X
2.b.3. ....
Hover taxiway lighting (yellow/blue/yellow cylinders) from TOFL area .................................................................................
X
X
2.b.4. ....
Markings within range of landing lights for night/twilight (dusk) scenes and as required by the surface resolution test on
daylight scenes.
X
X
3. ..........
Airport or Helicopter Landing Area Model Content
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE C3C.—FUNCTIONS AND SUBJECTIVE TESTS—Continued
<<>>
Visual scene content additional visual models beyond minimum required for qualification
Class II visual scenes/visual models
Number
Simulator
level
B
C
D
The following prescribes the minimum requirements for what must be provided in an airport visual model and identifies other aspects
of the airport environment that must correspond with that model for simulators at Level B, C, and D. The detail must be modeled
using airport pictures, construction drawings and maps, or other data, or modeled in accordance with published regulatory material;
however, this does not require that airport or helicopter landing area models contain details that are beyond the designed capability of
the currently qualified visual system. For circling approaches, all requirements of this section apply to the runway used for the initial
approach and to the runway of intended landing.
3.a. .......
The surface and markings for each ‘‘in-use’’ runway or helicopter landing area must include the following:
3.a.1. ....
For airports: Runway threshold markings, runway numbers, touchdown zone markings, fixed distance markings, runway edge markings, and runway centerline stripes.
X
X
X
3.a.2. ....
For helicopter landing areas: Standard heliport marking (‘‘H’’), TOFL, FATO, and safety areas ........................................
X
X
X
3.b. .......
The lighting for each ‘‘in-use’’ runway or helicopter landing area must include the following:
3.b.1. ....
For airports: Runway approach, threshold, edge, end, centerline (if applicable), touchdown zone (if applicable), leadoff,
and visual landing aid lights or light systems for that runway.
X
X
X
3.b.2. ....
For helicopter landing areas: Landing direction, raised and flush FATO, TOFL, windsock lighting ....................................
X
X
X
3.c. .......
The taxiway surface and markings associated with each ‘‘in-use’’ runway or helicopter landing area must include the following:
3.c.1. ....
For airports: Taxiway edge, centerline (if appropriate), runway hold lines, and ILS critical area(s) ....................................
X
X
X
3.c.2. ....
For helicopter landing areas: Taxiways, taxi routes, and aprons .........................................................................................
X
X
X
3.d. .......
The taxiway lighting associated with each ‘‘in-use’’ runway or helicopter landing area must include the following:
3.d.1. ....
For airports: Runway edge, centerline (if appropriate), runway hold lines, ILS critical areas ..............................................
X
X
X
3.d.2. ....
For helicopter landing areas: Taxiways, taxi routes, and aprons .........................................................................................
X
X
X
3.d.3. ....
For airports: Taxiway lighting of correct color .......................................................................................................................
4. ..........
Required visual model correlation with other aspects of the airport environment simulation
The following are the minimum visual model correlation tests that must be conducted for simulators at the NZFT and ZFT simulator
levels.
4.a. .......
The airport model must be properly aligned with the navigational aids that are associated with operations at the ‘‘inuse’’ runway.
X
X
X
4.b. .......
Slopes in runways, taxiways, and ramp areas must not cause distracting or unrealistic effects ........................................
X
X
X
5. ..........
Correlation with helicopter and associated equipment
The following are the minimum correlation comparisons that must be made for simulators at Level B, C, and D.
5.a. .......
Visual system compatibility with aerodynamic programming ................................................................................................
X
X
X
5.b. .......
Accurate portrayal of environment relating to flight simulator attitudes ................................................................................
X
X
X
5.c. .......
Visual cues to assess sink rate and depth perception during landings ................................................................................
X
X
X
6. ..........
Scene quality
The following are the minimum scene quality tests that must be conducted for simulators at Level B, C, and D.
6.a. .......
Light points free from distracting jitter, smearing or streaking ..............................................................................................
X
X
X
6.b. .......
Surfaces and textural cues free from apparent quantization (aliasing) ................................................................................
X
X
6.c. .......
Correct color and realistic textural cues ................................................................................................................................
7. ..........
Instructor controls of the following:
The following are the minimum instructor controls that must be available in simulators at the NZFT and ZFT simulator levels.
7.a. .......
Environmental effects, e.g., cloud base (if used), cloud effects, cloud density, visibility in statute miles/kilometers and
RVR in feet/meters.
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X
X
X
X
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE C3C.—FUNCTIONS AND SUBJECTIVE TESTS—Continued
<<>>
Visual scene content additional visual models beyond minimum required for qualification
Class II visual scenes/visual models
Number
Simulator
level
B
C
D
7.b. .......
Airport/Heliport selection ........................................................................................................................................................
X
X
X
7.c. .......
Airport lighting including variable intensity ............................................................................................................................
X
X
X
7.d. .......
Dynamic effects including ground and flight traffic ...............................................................................................................
X
X
X
X
End QPS Requirements
Begin Information
8. ..........
Sponsors are not required to provide every detail of a runway or helicopter landing area, but the detail that is provided
must be correct within the capabilities of the system.
X
End Information
TABLE C3D.—FUNCTIONS AND SUBJECTIVE TESTS
<<>>
Simulator level
Number
Motion system effects
Information
B
C
D
This table specifies motion effects that are required to indicate the threshold at which a flight crewmember must be able to recognize an event
or situation. Where applicable, flight simulator pitch, side loading and directional control characteristics must be representative of the helicopter.
1. ..........
Runway rumble, oleo deflection, ground speed, uneven runway, runway and taxiway centerline light
characteristics:
Procedure: After the helicopter has been pre-set to the
takeoff position and then released, taxi at various
speeds with a smooth runway and note the general
characteristics of the simulated runway rumble effects
of oleo deflections. Repeat the maneuver with a runway roughness of 50%, then with maximum roughness. The associated motion vibrations should be affected by ground speed and runway roughness.
2. ..........
Friction Drag from Skid-type Landing Gear:
Procedure: Perform a running takeoff or a running landing and note an increase in a fuselage vibration (as
opposed to rotor vibration) due to the friction of dragging the skid along the surface. This vibration will
lessen as the ground speed decreases.
3. ..........
Rotor Out-of-Track and/or Out-of-Balance condition:
Procedure: Select the malfunction or condition from the
IOS. Start the engine(s) normally and check for an
abnormal vibration for an Out-of-Track condition and
check for an abnormal vibration for an Out-of-Balance
condition.
4. ..........
X
X
X
X
X
X
X
Does not require becoming airborne. The abnormal vibration for Out-of-Track and Out-of-Balance conditions should be recognized in the frequency range of
the inverse of the period for each; i.e., 1/P for vertical
vibration, and 1/P for lateral vibration.
Bumps associated with the landing gear:
Procedure: Perform a normal take-off paying special attention to the bumps that could be perceptible due to
maximum oleo extension after lift-off.
X
X
X
When the landing gear is extended or retracted, motion
bumps can be felt when the gear locks into position.
5. ..........
Buffet during extension and retraction of landing
gear:
Procedure: Operate the landing gear. Check that the
motion cues of the buffet experienced represent the
actual helicopter.
X
X
X
6. ..........
Failure of Dynamic Vibration Absorber or similar
system as appropriate for the helicopter (e.g.,
droop stop or static stop):
X
X
X
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If time permits, different gross weights can also be selected as this may also affect the associated vibrations depending on helicopter type. The associated
motion effects for the above tests should also include
an assessment of the effects of rolling over centerline
lights, surface discontinuities of uneven runways, and
various taxiway characteristics.
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
59819
TABLE C3D.—FUNCTIONS AND SUBJECTIVE TESTS—Continued
<<>>
Simulator level
Number
Motion system effects
Information
B
C
D
Procedure: May be accomplished any time the rotor is
engaged. Select the appropriate failure at the IOS,
note an appropriate increase in vibration and check
that the vibration intensity and frequency increases
with an increase in RPM and an increase in collective
application.
7. ..........
Tail Rotor Drive Failure:
Procedure: With the engine(s) running and the rotor engaged—select the malfunction and note the immediate increase of medium frequency vibration.
X
X
X
8. ..........
Touchdown cues for main and nose gear:
Procedure: Conduct several normal approaches with
various rates of descent. Check that the motion cues
for the touchdown bumps for each descent rate are
representative of the actual helicopter.
X
X
X
9. ..........
Tire failure dynamics:
Procedure: Simulate a single tire failure and a multiple
tire failure.
X
X
10. ........
Engine malfunction and engine damage:
Procedure: The characteristics of an engine malfunction
as prescribed in the malfunction definition document
for the particular flight simulator must describe the
special motion effects felt by the pilot. The associated
engine instruments should also vary according to the
nature of the malfunction.
X
X
X
11. ........
Tail boom strikes:
Procedure: Tail-strikes can be checked by over-rotation
of the helicopter at a quick stop or autorotation to the
ground.
X
X
X
The motion effect should be felt as a noticeable nose
down pitching moment.
12. ........
Settling with Power:
Procedure: To enter the maneuver, reduce power below
hover power. Hold altitude with aft cyclic until the airspeed approaches 20 knots. Then allow the sink rate
to increase to 300 feet per minute or more as the attitude is adjusted to obtain an airspeed of less than 10
knots.
X
X
When the aircraft begins to shudder, the application of
additional up collective increases the vibration and
sink rate.
13. ........
Retreating Blade Stall:
Procedure: To enter the maneuver, increase forward airspeed; the effect should be recognized when the forward speed is equal to the speed of the retreating
blade. The onset can be felt through the development
of a low frequency vibration, pitching up of the nose,
and a roll in the direction of the retreating blade. High
weight, low rotor RPM, high density altitude, turbulence or steep, abrupt turns are all conducive to retreating blade stall at high forward airspeeds.
X
X
Correct recovery from retreating blade stall requires the
collective to be lowered first, which reduces blade angles and the angle of attack. Aft cyclic can then be
used to slow the helicopter.
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The tail rotor operates in the medium frequency range,
normally estimated by multiplying the tail rotor gear
box ratio by the main rotor RPM. The failure can be
recognized by an increase in the vibrations in this frequency range.
The pilot may notice some yawing with a multiple tire
failure selected on the same side. This should require
the use of the pedal to maintain control of the helicopter. Dependent on helicopter type, a single tire
failure may not be noticed by the pilot and may not
cause any special motion effect. Sound or vibration
may be associated with the actual tire losing pressure.
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TABLE C3D.—FUNCTIONS AND SUBJECTIVE TESTS—Continued
<<>>
Simulator level
Number
Motion system effects
Information
B
14. ........
Translational Lift Effects:
Procedure: From a stabilized in-ground-effect (IGE)
Hover begin a forward acceleration. When passing
through the effective translational lift range, the noticeable effect will be a nose pitch-up, increase in the
rate of climb, and a temporary increase vibration level
(in some cases this vibration may be pronounced).
This effect is experienced again upon deceleration
through the appropriate speed range. During deceleration, the pitch and rate of climb will have the reverse effect, but there will be a similar, temporary increase in vibration level.
C
D
X
X
X
TABLE C3E.—FUNCTIONS AND SUBJECTIVE TESTS
<<>>
Simulator level
Number
Sound system
B
C
D
X
X
X
X
X
X
X
X
X
X
The following checks are performed during a normal flight profile, motion system ON.
1.
2.
3.
4.
..........
..........
..........
..........
5. ..........
Precipitation .....................................................................................................................................................................
Rain removal equipment .................................................................................................................................................
Helicopter noises used by the pilot for normal helicopter operation ..............................................................................
Abnormal operations for which there are associated sound cues, including engine malfunctions, landing gear or tire
malfunctions, tail boom.
Sound of a crash when the flight simulator is landed in excess of limitations ...............................................................
TABLE C3F.—FUNCTIONS AND SUBJECTIVE TESTS
<<>>
Simulator level
Number
Special effects
B
C
D
This table specifies the minimum special effects necessary for the specified simulator level.
1. ..........
Braking Dynamics:
Representations of the dynamics of brake failure (flight simulator pitch, side-loading, and directional control characteristics representative of the helicopter), including antiskid and decreased brake efficiency due to high brake
temperatures (based on helicopter related data), sufficient to enable pilot identification of the problem and implementation of appropriate procedures.
X
X
2. ..........
Effects of Airframe and Engine Icing:
Required only for those helicopters authorized for operations in known icing conditions.
Procedure: With the simulator airborne, in a clean configuration, nominal altitude and cruise airspeed, autopilot on
and auto-throttles off, engine and airfoil anti-ice/de-ice systems deactivated; activate icing conditions at a rate
that allows monitoring of simulator and systems response.
Icing recognition will include an increase in gross weight, airspeed decay, change in simulator pitch attitude,
change in engine performance indications (other than due to airspeed changes), and change in data from pitot/
static system, or rotor out-of-track/balance. Activate heating, anti-ice, or de-ice systems independently. Recognition will include proper effects of these systems, eventually returning the simulated helicopter to normal flight.
X
X
TABLE C3G.—FUNCTIONS AND SUBJECTIVE TESTS
<<>>
Simulator level
Instructor operating station (IOS)
(As appropriate)
Number
B
Functions in this table are subject to evaluation only if appropriate for the helicopter or the system is installed on the specific simulator.
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TABLE C3G.—FUNCTIONS AND SUBJECTIVE TESTS—Continued
<<>>
Simulator level
Instructor operating station (IOS)
(As appropriate)
Number
B
C
D
X
X
X
1. ..........
Simulator Power Switch(es) .........................................................................................................................................
2. ..........
Helicopter conditions
2.a. .......
Gross weight, center of gravity, fuel loading and allocation ...........................................................................................
X
X
X
2.b. .......
Helicopter systems status ...............................................................................................................................................
X
X
X
2.c. .......
Ground crew functions ....................................................................................................................................................
X
X
X
3. ..........
Airports/Heliports
3.a. .......
Number and selection .....................................................................................................................................................
X
X
X
3.b. .......
Runway or landing area selection ...................................................................................................................................
X
X
X
3.c. .......
Landing surface conditions (rough, smooth, icy, wet, dry, snow) ...................................................................................
X
X
X
3.d. .......
Preset positions ...............................................................................................................................................................
X
X
X
3.e. .......
Lighting controls ..............................................................................................................................................................
X
X
X
4. ..........
Environmental controls
4.a ........
Visibility (statute miles/kilometers) ..................................................................................................................................
X
X
X
4.b. .......
Runway visual range (in feet/meters) .............................................................................................................................
X
X
X
4.c. .......
Temperature ....................................................................................................................................................................
X
X
X
4.d. .......
Climate conditions ...........................................................................................................................................................
X
X
X
4.e. .......
Wind speed and direction ...............................................................................................................................................
X
X
X
4.f. ........
Windshear .......................................................................................................................................................................
......
X
X
5. .........
Helicopter system malfunctions (Insertion/deletion) ...................................................................................................
X
X
X
6. .........
Locks, Freezes, and Repositioning
6.a. .......
Problem (all) freeze/release ............................................................................................................................................
X
X
X
6.b. .......
Position (geographic) freeze/release ..............................................................................................................................
X
X
X
6.c. .......
Repositioning (locations, freezes, and releases) ............................................................................................................
X
X
X
6.d. .......
Ground speed control ......................................................................................................................................................
X
X
X
7. ..........
Remote IOS ....................................................................................................................................................................
X
X
X
8. ..........
Sound Controls. On/off/adjustment ...............................................................................................................................
X
X
X
9. .........
Motion/Control Loading System
9.a. .......
On/off/emergency stop.
X
X
X
10. ........
Observer Seats/Stations. Position/Adjustment/Positive restraint system.
X
X
X
Attachment 4 to Appendix C to Part 60—
Sample Documents
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 4910–13–P
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
BILLING CODE 4910–13–C
Attachment 5 to Appendix C to Part 60—
FSTD Directives Applicable to Helicopter
Full Flight Simulators
Flight Simulation Training Device (FSTD)
Directive (FD)
FSTD Directive Number 1. Applicable to
all Full Flight Simulators (FFS), regardless of
the original qualification basis and
qualification date (original or upgrade),
having Class II visual scenes or airport
models available.
Federal Aviation Administration (FAA),
DOT
This is a retroactive requirement to have all
Class II visual scenes or airport models meet
current requirements.
lllllllllllllllllllll
SUMMARY: Notwithstanding the authorization
listed in paragraph 13b in Appendices A and
C, this FSTD Directive (FD) requires each
sponsor to ensure that, by [date 1 year after
effective date of the final rule], each Class II
visual scene or airport model available in an
FFS, meets the requirements of 14 CFR part
60, Appendix A, Attachment 3, Table A3C,
or Appendix C, Attachment 3, Table C3C, as
applicable. The completion of this
requirement will not require a report. The
fact that the scene or model is available in
the FFS is the sponsor’s testament that the
requirements are met.
DATES: This FD becomes effective on
[effective date of the final rule].
FOR FURTHER INFORMATION CONTACT: Ed Cook,
Senior Advisor to the Division Manager, Air
Transportation Division, AFS–200, 800
Independence Ave, SW., Washington, DC
20591: telephone: (404) 832–4701; fax: (404)
761–8906.
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Specific Requirements
1. Part 60 requires that each FSTD be:
a. Sponsored by a person holding or
applying for an FAA operating certificate
under Part 119, Part 141, or Part 142, or
holding or applying for an FAA-approved
training program under Part 63, Appendix C,
for flight engineers, and
b. Evaluated and issued a Statement of
Qualification for a specific FSTD level.
2. Full flight simulators (FFS) also require
the installation of a visual system that is
capable of providing an out-of-the-flight-deck
view of visual scenes or airport models. To
be qualified, each FFS must have available
for use a minimum number of visual scenes
or airport models that have certain features.
These are called Class I visual scenes or
airport models, the required features of
which are listed in Part 60. Additional scenes
or models that are beyond those necessary for
qualification may also be used for various
additional training program applications,
including Line Oriented Flight Training, are
classified as Class II. However, historically
these visual scenes or airport models were
not routinely evaluated or required to meet
any standardized criteria. This has led to
qualified simulators containing visual scenes
or airport models being used to meet FAAapproved training, testing, or checking
requirements with potentially incorrect or
inappropriate visual references.
3. To prevent this from occurring in the
future, by [date 1 year after effective date of
the final rule], each FSTD sponsor must
assure that each Class II visual scene or
airport model available in a qualified FFS
meets the requirements found in 14 CFR part
60, Appendix A, Attachment 3, Table A3C or
Appendix C, Attachment 3, Table C3C, as
applicable. These references describe the
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requirements for visual scene management
and the minimum distances from which
runway or landing area features must be
visible for all levels of simulator. The visual
scene or airport model must provide, for each
‘‘in-use runway’’ or ‘‘in-use landing area,’’
runway or landing area surface and markings,
runway or landing area lighting, taxiway
surface and markings, and taxiway lighting.
Additional requirements include correlation
of the visual scenes or airport models with
other aspects of the airport environment,
correlation of the aircraft and associated
equipment, scene quality assessment
features, and the extent to which the
instructor is able to exercise control of these
scenes or models.
4. For circling approaches, all requirements
of this section apply to the runway used for
the initial approach and to the runway of
intended landing.
5. The details in these scenes or models
must be developed using airport pictures,
construction drawings and maps, or other
similar data, or be developed in accordance
with published regulatory material. However,
this FD does not require that visual scenes or
airport models contain details that are
beyond the initially designed capability of
the visual system, as currently qualified. The
recognized limitations to visual systems are
as follows:
a. Visual systems not required to have
runway numbers as a part of the specific
runway marking requirements are:
(1) Link NVS and DNVS.
(2) Novoview 2500 and 6000.
(3) FlightSafety VITAL series up to, and
including, VITAL III, but not beyond.
(4) Redifusion SP1, SP1T, and SP2.
b. Visual systems required to display
runway numbers only for LOFT scenes are:
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(1) FlightSafety VITAL IV.
(2) Redifusion SP3 and SP3T.
(3) Link-Miles Image II.
c. Visual systems not required to have
accurate taxiway edge lighting are:
(1) Redifusion SP1.
(2) FlightSafety Vital IV.
(3) Link-Miles Image II and Image IIT.
(4) XKD displays (even though the XKD
image generator is capable of generating blue
colored lights, the display cannot
accommodate that color).
6. A copy of this Directive must be filed
in the Master Qualification Test Guide in the
designated FSTD Directive Section, and its
inclusion must be annotated on the Index of
Effective FSTD Directives chart. See
Attachment 4, Appendices A through D for
a sample MQTG Index of Effective FSTD
Directives chart.
Appendix D to Part 60—Qualification
Performance Standards for Helicopter Flight
Training Devices
lllllllllllllllllllll
Begin Information
This appendix establishes the standards for
Helicopter Flight Training Device (FTD)
evaluation and qualification at Level 4, Level
5, Level 6, or Level 7. 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 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 FSTDs (§ 60.16)
13. Previously Qualified FSTDs (§ 60.17)
14. Inspection, Continuing Qualification
Evaluation, and Maintenance
Requirements (§ 60.19)
15. Logging FSTD Discrepancies (§ 60.20)
16. Interim Qualification of FSTDs for New
Helicopter Types or Models (§ 60.21)
17. Modifications to FSTDs (§ 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)
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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
Attachment 5 to Appendix D to Part 60—
FSTD Directives Applicable to
Helicopter Flight Training Devices
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. Questions regarding the contents of this
publication should be sent to the U.S.
Department of Transportation, Federal
Aviation Administration, Flight Standards
Service, National Simulator Program Staff,
AFS–205, 100 Hartsfield Centre Parkway,
Suite 400, Atlanta, Georgia, 30354.
Telephone contact numbers for the NSP are:
phone, 404–832–4700; fax, 404–761–8906.
The general email address for the NSP office
is: 9-aso-avr-sim-team@faa.gov. The NSP
Internet Web Site address is: https://
www.faa.gov/safety/programs_initiatives/
aircraft_aviation/nsp/. On this Web Site you
will find an NSP personnel list with
telephone and email contact information for
each NSP staff member, a list of qualified
flight simulation devices, advisory circulars,
a description of the qualification process,
NSP policy, and an NSP ‘‘In-Works’’ section.
Also linked from this site are additional
information sources, handbook bulletins,
frequently asked questions, a listing and text
of the Federal Aviation Regulations, Flight
Standards Inspector’s handbooks, and other
FAA links.
c. The NSPM encourages the use of
electronic media for all communication,
including any record, report, request, test, or
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59835
statement required by this appendix. The
electronic media used must have adequate
security provisions and be acceptable to the
NSPM. The NSPM recommends inquiries on
system compatibility, and minimum system
requirements are also included on the NSP
Web site.
d. 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.
(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 and 60.2)
lllllllllllllllllllll
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Begin Information
No additional regulatory or informational
material 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
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)
lllllllllllllllllllll
Begin Information
No additional regulatory or informational
material applies to § 60.4, Qualification
Performance Standards.
End Information
lllllllllllllllllllll
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
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 May
30, 2008, the 12-month period begins on the
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17:31 Oct 19, 2007
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date of the first continuing qualification
evaluation conducted in accordance with
§ 60.19 after May 30, 2008, and continues for
each subsequent 12-month period;
(ii) A device qualified on or after May 30,
2008, 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)
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 helicopter (as
described in § 60.7(d)(1));
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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. FSTD Use (§ 60.11)
lllllllllllllllllllll
Begin Information
No additional regulatory or informational
material applies to § 60.11, FSTD Use.
End Information
lllllllllllllllllllll
9. FSTD 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.
(vi) All other information necessary to
recreate the flight test conditions in the FTD.
(2) Appropriately qualified flight test
personnel.
(3) 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.
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(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. The
sponsor must—
(1) Within 10 calendar days, notify the
NSPM of the existence of this data; and
(a) Within 45 calendar days, notify the
NSPM of—
(b) The schedule to incorporate this data
into the FTD; or
(c) The reason for not incorporating this
data into the FTD.
e. 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, the sponsor or other data
provider must ensure that a steady state
condition exists at the instant of time
captured by the ‘‘snapshot.’’ The steady state
condition must exist from 4 seconds prior to,
through 1 second following, the instant of
time captured by the snapshot.
End QPS Requirements
lllllllllllllllllllll
Begin Information
f. 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.
g. 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
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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.
h. 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 FTD evaluation. For this reason
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.
i. The NSPM will consider, on a case-bycase basis, whether 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 users of the
FTD that raise questions about 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).
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59837
(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 appropriate QPS.
(c) The result of FTD subjective tests
prescribed in the appropriate 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
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.
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(c) The aerodynamic data revision number
or reference.
(d) The source of the basic aerodynamic
model and the aerodynamic coefficient data
used to modify the basic model.
(e) The engine model(s) and its data
revision number or reference.
(f) The flight control data revision number
or reference.
(g) The flight management system
identification and revision level.
(h) The FTD model and manufacturer.
(i) The date of FTD manufacture.
(j) The FTD computer identification.
(k) The visual system model and
manufacturer, including display type.
(l) 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.
(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
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 QTG for the first helicopter model and a
supplement to that QTG for each additional
helicopter model. The NSPM will conduct
evaluations for each helicopter 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 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 may 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 May 30,
2014, 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 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 May 30, 2014.
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.
l. During the initial (or upgrade)
qualification evaluation conducted by the
NSPM, the sponsor must also provide a
person knowledgeable about the operation of
the aircraft and the operation of the FTD.
End QPS Requirements
lllllllllllllllllllll
Begin Information
m. 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.
n. 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) Flight deck 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).
(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.
o. 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
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
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.
p. 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.
q. 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.
r. 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.
s. 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 evaluation and will
list the tasks for which the FTD is qualified,
referencing the tasks described in Table D1B
in attachment 1. However, it is the sponsor’s
responsibility to obtain TPAA approval prior
to using the FTD in an FAA-approved flight
training program.
t. Under normal circumstances, the NSPM
establishes a date for the initial or upgrade
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Jkt 214001
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.
u. 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.
v. 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).
w. 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 FSTDs (§ 60.16)
lllllllllllllllllllll
Begin Information
No additional regulatory or informational
material applies to § 60.16, Additional
Qualifications for a Currently Qualified FTD.
End Information
lllllllllllllllllllll
13. Previously Qualified FSTDs (§ 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 and replacement FTD systems
qualified prior to May 30, 2008, are not
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59839
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 as long as the FTD continues to
meet the test requirements contained in the
MQTG developed under the original
qualification basis.
c. After (1 year after date of publication of
the final rule in the Federal Register) each
visual scene and airport model installed in
and available for use in a qualified FTD must
meet the requirements described in
Attachment 3 of this appendix.
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
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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 Qualification,
Evaluation, and Maintenance Requirements
(§ 60.19)
lllllllllllllllllllll
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.
d. During the continuing qualification
evaluation conducted by the NSPM, the
sponsor must also provide a person
knowledgeable about the operation of the
aircraft and the operation of the FTD.
End QPS Requirements
lllllllllllllllllllll
Begin Information
e. 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.
f. 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.
g. 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:
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(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
simulated helicopter systems. This
examination is normally accomplished
simultaneously with the subjective
evaluation requirements.
h. 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 FSTD Discrepancies (§ 60.20)
Begin Information
No additional regulatory or informational
material applies to § 60.20. Logging FSTD
Discrepancies.
End Information
lllllllllllllllllllll
16. Interim Qualification of FSTDs for New
Helicopter Types or Models (§ 60.21)
lllllllllllllllllllll
Begin Information
No additional regulatory or informational
material applies to § 60.21, Interim
Qualification of FSTDs for New Helicopter
Types or Models.
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. See Attachment 6 for a list
of all effective FSTD Directives applicable to
Helicopter FTDs.
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 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
17. Modifications to FSTDs (§ 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
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
End Information
lllllllllllllllllllll
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20. Other Losses of Qualification and
Procedures for Restoration of Qualification
(§ 60.29)
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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,
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.
End QPS Requirements
lllllllllllllllllllll
22. Applications, Logbooks, Reports, and
Records: Fraud, Falsification, or Incorrect
Statements (§ 60.33)
lllllllllllllllllllll
Begin Information
No additional regulatory or informational
material applies to § 60.33, Applications,
Logbooks, Reports, and Records: Fraud,
Falsification, or Incorrect Statements.
23. [Reserved]
End Information
lllllllllllllllllllll
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 Level 4 device is one that
may have an open helicopter-specific flight
deck area, or an enclosed helicopter-specific
flight deck and at least one operating system.
Air/ground logic is required (no aerodynamic
programming required). All displays may be
flat/LCD panel representations or actual
representations of displays in the aircraft. All
controls, switches, and knobs may be touch
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sensitive activation (not capable of manual
manipulation of the flight controls) or may
physically replicate the aircraft in control
operation.
(2) Level 5. A Level 5 device is one that
may have an open helicopter-specific flight
deck area, or an enclosed helicopter-specific
flight deck and a generic aerodynamic
program with at least one operating system
and control loading representative of the
simulated helicopter. The control loading
need only represent the helicopter at an
approach speed and configuration. All
displays may be flat/LCD panel
representations or actual representations of
displays in the aircraft. Primary and
secondary flight controls (e.g., rudder,
aileron, elevator, flaps, spoilers/speed brakes,
engine controls, landing gear, nose wheel
steering, trim, brakes) must be physical
controls. All other controls, switches, and
knobs may be touch sensitive activation.
(3) Level 6. A Level 6 device is one that has
an enclosed helicopter-specific flight deck
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. All displays may be flat/LCD
panel representations or actual
representations of displays in the aircraft, but
all controls, switches, and knobs must
physically replicate the aircraft in control
operation.
(4) Level 7. A Level 7 device is one that has
an enclosed helicopter-specific flight deck
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. All displays may be flat/LCD
panel representations or actual
representations of displays in the aircraft, but
all controls, switches, and knobs must
physically replicate the aircraft in control
operation. It also has a visual system that
provides an out-of-the-flight deck view,
providing cross-flight deck viewing (for both
pilots simultaneously) of a field of view of at
least 146° horizontally and 36° vertically as
well as a vibration cueing system for
characteristic helicopter vibrations noted at
the pilot station(s).
End Information
lllllllllllllllllllll
25. FSTD Qualification on the Basis of a
Bilateral Aviation Safety Agreement (BASA)
(§ 60.37)
lllllllllllllllllllll
Begin Information
No additional regulatory or informational
material applies to § 60.37, FSTD
Qualification on the Basis of a Bilateral
Aviation Safety Agreement (BASA).
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59841
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
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 QPS Requirements
lllllllllllllllllllll
Begin Information
2. Discussion
a. This attachment describes the general
requirements for qualifying Level 4 through
Level 7 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 Flight Deck 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.
d. Table D1B provides the tasks that the
sponsor will examine to determine whether
the FSTD satisfactorily meets the
requirements for flight crew training, testing,
and experience.
e. Table D1C provides the functions that an
instructor/check airman must be able to
control in the simulator.
f. It is not required that all of the tasks that
appear on the List of Qualified Tasks (part of
the SOQ) be accomplished during the initial
or continuing qualification evaluation.
End Information
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TABLE D1A.—MINIMUM FTD REQUIREMENTS
<<>>
<>
notes
FTD level
Number
General FTD requirements
4
5
6
7
X
X
X
X
X
X
X
X
1. General Flight Deck Configuration
1.a. ......
The FTD must have a flight deck that is a replica of the
helicopter, or set of helicopters simulated with controls, equipment, observable flight deck 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 helicopter or set of helicopters. Crewmember seats must
afford the capability for the occupant to be able to
achieve the design ‘‘eye position.’’ Equipment for the
operation of the flight deck windows must be included, but the actual windows need not be operable.
Fire axes, extinguishers, and spare light bulbs must
be available in the flight simulator, 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.
1.b. ......
The FTD must have equipment (i.e., 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 configuration, and
may be in a flight deck or an open flight deck area.
Additional equipment required for the authorized
training and checking events must be available in the
FTD but may be located in a suitable location as near
as practical to the spatially correct position. Actuation
of this equipment must replicate the appropriate function in the helicopter. Fire axes, landing gear pins,
and any similar purpose instruments need only be
represented in silhouette.
An SOC is required.
X
For FTD purposes, the flight deck 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.
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 helicopter attitude, thrust, drag, altitude, temperature, and configuration.
Levels 6 and 7 additionally require the effects of
changes in gross weight and center of gravity.
Level 5 requires only generic aerodynamic programming.
An SOC is required.
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.
An SOC is required.
2.c. .......
Relative responses of the flight deck instruments must
be measured by latency tests or transport delay tests,
and may not exceed 150 milliseconds. The instruments must respond to abrupt input at the pilot’s position within the allotted time, but not before the time
that the helicopter or set of helicopters would respond
under the same conditions.
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TABLE D1A.—MINIMUM FTD REQUIREMENTS—Continued
<<>>
<>
notes
FTD level
Number
General FTD requirements
4
6
7
X
• Latency: The FTD instrument and, if applicable, the
motion system and the visual system response must
not be prior to that time when the helicopter responds
and may respond up to 150 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.
An objective test is required.
5
X
X
The intent is to verify that the FTD provides instrument
cues that are, within the stated time delays, like the
helicopter responses. For helicopter response, acceleration in the appropriate, corresponding rotational
axis is preferred.
3. Equipment Operation
3.a. ......
All relevant instrument indications involved in the simulation of the helicopter must automatically respond
to control movement or external disturbances to the
simulated helicopter or set of helicopters; e.g., turbulence or winds.
A subjective test is required.
A
X
X
X
3.b. ......
Navigation equipment must be installed and operate
within the tolerances applicable for the helicopter or
set of helicopters.
Levels 6 and 7 must also include communication equipment (inter-phone and air/ground) like that in the helicopter.
Level 5 only needs that navigation equipment necessary to fly an instrument approach.
A subjective test is required.
A
X
X
X
3.c. .......
Installed systems must simulate the applicable helicopter 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 sponsor’s training
programs can be accomplished.
Levels 6 and 7 must simulate all applicable helicopter
flight, navigation, and systems operation.
Level 5 must have functional flight and navigational
controls, displays, and instrumentation.
A subjective test is required.
A
X
X
X
3.d. ......
The lighting environment for panels and instruments
must be sufficient for the operation being conducted.
A subjective test is required.
X
X
X
X
3.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.
A subjective test is required.
X
X
3.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.
A subjective test is required.
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Back-lighted panels and instruments may be installed
but are not required.
X
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TABLE D1A.—MINIMUM FTD REQUIREMENTS—Continued
<<>>
<>
notes
FTD level
Number
General FTD requirements
4
5
6
7
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).
A subjective test is required.
X
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.
A subjective test is required.
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
5. Motion System
5.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.
A subjective test is required.
X
X
X
5.b. ......
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 may 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
helicopter would respond under the same conditions,
it must be measured by latency tests or transport
delay tests and may not exceed 150 milliseconds. Instrument response may not occur prior to motion
onset.
An objective test is required.
X
X
X
5.c. .......
The FTD must have at least a vibration cueing system
for characteristic helicopter vibrations noted at the
pilot station(s).
If a motion system is installed, although it is not required, it must be measured by latency tests or transport delay tests and may not exceed 100 milliseconds. Instrument response may not occur prior to
motion onset.
A subjective test is required.
X
May be accomplished by a ‘‘seat shaker’’ or a bass
speaker sufficient to provide the necessary cueing.
6. Visual System
6.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:.
6.a.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.a.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.a.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
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59845
TABLE D1A.—MINIMUM FTD REQUIREMENTS—Continued
<<>>
<>
notes
FTD level
Number
General FTD requirements
4
5
6
6.a.4. ...
The visual system must provide for a maximum parallax
of 10° per pilot.
An SOC is required.
X
X
X
6.a.5. ...
The visual scene content may not be distracting ............
An SOC is required.
A Subjective Test is required.
X
X
X
6.a.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.a.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
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, a visual system
meeting the standards set out for at least a Level A
FFS (see Appendix A of this part) will be required. A
‘‘direct-view,’’ non-collimated visual system (with the
other requirements for a Level A visual system met)
may be considered satisfactory for those installations
where the visual system design ‘‘eye point’’ is appropriately adjusted for each pilot’s position such that the
parallax error is at or less than 10° simultaneously for
each pilot.
An SOC is required.
An objective test is required.
X
X
X
6.c. .......
The FTD must provide a continuous visual field of view
of at least 146° horizontally and 36° vertically for both
pilot seats, simultaneously. The minimum horizontal
field of view coverage must be plus and minus onehalf (1⁄2) of the minimum continuous field of view requirement, centered on the zero degree azimuth line
relative to the aircraft fuselage. Additional horizontal
field of view capability may be added at the sponsor’s
discretion provided the minimum field of view is retained. Capability for a field of view in excess of
these minima is not required for qualification at Level
7. However, where specific tasks require extended
fields of view beyond the 146° by 36° (e.g., to accommodate the use of ‘‘chin windows’’ where the accommodation is either integral with or separate from the
primary visual system display), then such extended
fields of view must be provided.
An SOC is required and must explain the geometry of
the installation.
An objective test is required.
7
X
Optimization of the vertical field of view may be considered with respect to the specific helicopter flight deck
cut-off angle. When considering the installation/use of
augmented fields of view, as described here, it will be
the responsibility of the sponsor to meet with the
NSPM to determine the training, testing, checking, or
experience tasks for which the augmented field of
view capability may be critical to that approval.
7. Sound System
7.a. ......
The FTD must simulate significant flight deck sounds
resulting from pilot actions that correspond to those
heard in the helicopter.
A subjective test is required.
X
X
Note: An ‘‘A’’ in the table indicates that the system, task, or procedure may be examined if the appropriate helicopter system or control is simulated in the FTD and is working properly.
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TABLE D1B.—MINIMUM FTD REQUIREMENTS
<<>>
Number
<<>>
Subjective requirements
The FTD must be able to perform the tasks associated
with the level of qualification sought.
FTD level
Notes
4
5
6
7
A
A
X
X
1. Preflight Procedures
1.a. ......
Preflight Inspection (Flight Deck Only) switches, indicators, systems, and equipment.
1.b. ......
APU/Engine start and run-up.
1.b.1. ...
Normal start procedures ..................................................
A
A
X
X
1.b.2. ...
Alternate start procedures ...............................................
A
A
X
X
1.b.3. ...
Abnormal starts and shutdowns (hot start, hung start) ...
A
A
X
X
1.c. .......
Taxiing—Ground ..............................................................
X
1.d. ......
Taxiing—Hover ................................................................
X
1.e. ......
Pre-takeoff Checks ..........................................................
A
A
X
X
2. Takeoff and Departure Phase
2.a. ......
Normal takeoff.
2.a.1. ...
From ground ....................................................................
X
2.a.2. ...
From hover ......................................................................
X
2.a.3 ....
Running ...........................................................................
X
2.b. ......
Instrument ........................................................................
X
X
2.c. .......
Powerplant Failure During Takeoff ..................................
X
X
2.d. ......
Rejected Takeoff ..............................................................
2.e. ......
Instrument Departure .......................................................
X
X
3.a. ......
Normal .............................................................................
X
X
3.b. ......
Obstacle clearance ..........................................................
3.c. .......
Vertical .............................................................................
X
X
3.d. ......
One engine inoperative ...................................................
X
X
X
X
X
3. Climb
X
4. In-flight Maneuvers
4.a. ......
Turns (timed, normal, steep) ...........................................
X
4.b. ......
Powerplant Failure—Multiengine Helicopters ..................
X
X
4.c. .......
Powerplant Failure—Single-Engine Helicopters ..............
X
X
4.d. ......
Recovery From Unusual Attitudes ...................................
X
4.e. ......
Settling with Power ..........................................................
X
5. Instrument Procedures
5.a. ......
Instrument Arrival .............................................................
X
X
5.b. ......
Holding .............................................................................
X
X
5.c. .......
Precision Instrument Approach
5.c.1. ....
Normal—All engines operating ........................................
X
X
5.c.2. ....
Manually controlled—One or more engines inoperative
X
X
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE D1B.—MINIMUM FTD REQUIREMENTS—Continued
<<>>
Number
<<>>
Subjective requirements
The FTD must be able to perform the tasks associated
with the level of qualification sought.
FTD level
Notes
4
5
6
7
X
X
X
5.d. ......
Non-precision Instrument Approach ................................
5.e. ......
Missed Approach
5.e.1. ...
All engines operating .......................................................
X
X
5.e.2. ...
One or more engines inoperative ....................................
X
X
5.e.3. ...
Stability augmentation system failure ..............................
X
X
6. Landings and Approaches to Landings
6.a. ......
Visual Approaches (normal, steep, shallow) ...................
X
6.b. ......
Landings
6.b.1. ...
Normal/crosswind
6.b.1.a.
Running ...........................................................................
X
6.b.1.b.
From Hover ......................................................................
X
6.b.2. ...
One or more engines inoperative ....................................
X
6.b.3. ...
Rejected Landing .............................................................
X
7. Normal and Abnormal Procedures
7.a. ......
Powerplant .......................................................................
A
A
X
X
7.b. ......
Fuel System .....................................................................
A
A
X
X
7.c. .......
Electrical System .............................................................
A
A
X
X
7.d. ......
Hydraulic System .............................................................
A
A
X
X
7.e. ......
Environmental System(s) .................................................
A
A
X
X
7.f. .......
Fire Detection and Extinguisher Systems .......................
A
A
X
X
7.g. ......
Navigation and Aviation Systems ....................................
A
A
X
X
7.h. ......
Automatic Flight Control System, Electronic Flight Instrument System, and Related Subsystems.
A
A
X
X
7.i. ........
Flight Control Systems ....................................................
A
A
X
X
7.j. ........
Anti-ice and Deice Systems ............................................
A
A
X
X
7.k. .......
Aircraft and Personal Emergency Equipment .................
A
A
X
X
7.l. ........
Special Missions tasks (e.g., Night Vision goggles, Forward Looking Infrared System, External Loads and as
may be listed on the Statement of Qualification).
X
8. Emergency procedures (as applicable)
8.a. ......
Emergency Descent ........................................................
X
X
8.b. ......
Inflight Fire and Smoke Removal ....................................
X
X
8.c. .......
Emergency Evacuation ....................................................
X
X
8.d. ......
Ditching ............................................................................
X
8.e. ......
Autorotative Landing ........................................................
X
8.f. .......
Retreating blade stall recovery ........................................
X
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59847
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE D1B.—MINIMUM FTD REQUIREMENTS—Continued
<<>>
Number
<<>>
Subjective requirements
The FTD must be able to perform the tasks associated
with the level of qualification sought.
8.g. ......
Notes
4
5
Loss of tail rotor effectiveness .........................................
6
Mast bumping ..................................................................
8.h. ......
FTD level
7
X
X
X
9. Postflight Procedures
9.a. ......
After-Landing Procedures ................................................
A
A
X
X
9.b. ......
Parking and Securing
9.b.1. ...
Rotor brake operation ......................................................
A
A
X
X
9.b.2. ...
Abnormal/emergency procedures ....................................
A
A
X
X
Note: An ‘‘A’’ in the table indicates that the system, task, or procedure may be examined if the appropriate aircraft system or control is simulated in the FSTD and is working properly.
TABLE D1C.—TABLE OF FTD SYSTEM TASKS
<<>>
Number
<< Information >>
Subjective requirements
In order to be qualifed at the FTD qualification level indicated, the FTD must be able to perform at least the
tasks associate with that level of qualification.
FTD level
Notes
4
5
6
7
1. Instructor Operating Station (IOS)
1.a. ......
Power switch(es) .............................................................
A
X
X
X
1.b. ......
Helicopter conditions .......................................................
A
A
X
X
e.g., GW, CG, Fuel loading, Systems, Ground. Crew.
1.c. .......
Airports / Heliports / Helicopter Landing Areas ...............
A
X
X
X
e.g., Selection, Surface, Presets, Lighting controls.
1.d. ......
Environmental controls ....................................................
A
X
X
X
e.g., Temp and Wind.
1.e. ......
Helicopter system malfunctions (Insertion / deletion) .....
A
A
X
X
1.f. .......
Locks, Freezes, and Repositioning (as appropriate) ......
A
X
X
X
1.g. ......
Sound Controls. (On / off / adjustment) ..........................
X
X
X
1.fh ......
Motion / Control Loading System, as appropriate. On /
off / emergency stop.
A
X
X
X
X
X
2. Observer Seats / Stations
2.a. ......
Position / Adjustment / Positive restraint system ............
Attachment 2 to Appendix D to Part 60—
Flight Training Device (FTD) Objective Tests
lllllllllllllllllllll
Begin Information
1. Discussion
a. If relevant winds are present in the
objective data, the wind vector (magnitude
and direction) should be noted as part of the
data presentation, expressed in conventional
terminology, and related to the runway being
used for the test.
b. The format for numbering the objective
tests in Appendix C, Attachment 2, Table
C2A, and the objective tests in Appendix D,
Attachment 2, Table D2A, is identical.
However, each test required for FFSs is not
necessarily required for FTDs, and each test
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A
required for FTDs is not necessarily required
for FFSs. 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
objective test numbers for either FFSs or
FTDs.
c. A Level 4 FTD does not require objective
tests and is not addressed in the following
table.
End Information
lllllllllllllllllllll
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Begin QPS Requirements
2. Test Requirements
a. The ground and flight tests required for
qualification are listed in Table D2A
Objective Evaluation Tests. 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
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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. The FTD may not be programmed so that
the mathematical modeling is correct only at
the validation test points. Unless 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.
(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.’’ The steady state
condition must exist from 4 seconds prior to,
through 1 second following, the instant of
time captured by the snap shot.
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. 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
59849
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 effect 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 flight deck (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 within 10 percent of the
average of the numerical values of the BOW
and the maximum certificated gross 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.
End QPS Requirements
lllllllllllllllllllll
Begin Information
Refer to Advisory Circular 120–27,
‘‘Aircraft Weight and Balance;’’ and FAA–H–
8083–1, ‘‘Aircraft Weight and Balance
Handbook’’ for more information.
End Information
lllllllllllllllllllll
TABLE D2A.—FLIGHT TRAINING DEVICE (FTD) OBJECTIVE TESTS
<<>>
Test
Number
Flight conditions
Test details
Title
5
1. Performance
1.a. Engine Assessment
1.a.1. .................
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Notes
FTD level
Tolerances
Start Operations.
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7
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TABLE D2A.—FLIGHT TRAINING DEVICE (FTD) OBJECTIVE TESTS—Continued
<<>>
Test
<>
Notes
FTD level
Tolerances
Flight conditions
Test details
Number
Title
5
6
7
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
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
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
1.a.2.a. ..............
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
1.a.3. .................
Reserved.
Airspeed—±3 kt, AltiGround/Takeoff
tude—±20 ft (6.1 m)
and Initial SegTorque—±3%, Rotor
ment of Climb.
Speed—±1.5%, Vertical
Velocity—±100 fpm
(0.50 m/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%.
Record results of
takeoff flight
path (running
takeoff and
takeoff from a
hover). 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
(61 m) AGL.
X
1.b. Reserved
1.c. Takeoff
1.c.1. .................
All Engines ........
1.c.2. through
1.c.3.
X
Reserved.
1.d. Hover
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59851
TABLE D2A.—FLIGHT TRAINING DEVICE (FTD) OBJECTIVE TESTS—Continued
<<>>
Test
Number
<>
Notes
FTD level
Tolerances
Flight conditions
Test details
Title
5
6
7
Performance ......
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
Performance ......
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
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 and CG
combinations
with varying
trim speeds
throughout the
airspeed envelope. May be a
series of snapshot tests.
X
X
X
Performance and
Trimmed Flight
Control Positions.
Vertical 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
X
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 (5 m/sec)
rate of descent
(RoD) at normal approach
speed. Augmentation System(s) On and
Off.
Record results
for two gross
weight and CG
combinations.
May be a series of snapshot tests.
X
X
X
1.e. Vertical Climb
1.f. Level Flight
1.g. Climb
1.h. Descent
1.h.1. .................
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This test validates
performance at
speeds above
maximum endurance airspeed.
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TABLE D2A.—FLIGHT TRAINING DEVICE (FTD) OBJECTIVE TESTS—Continued
<<>>
Test
<>
Notes
FTD level
Tolerances
Flight conditions
Test details
Number
Title
5
1.h.2. .................
Autorotation Performance and
Trimmed Flight
Control Positions.
Pitch Attitude—±1.5°
Sideslip Angle—±2°
Longitudinal Control
Position—±5% Lateral
Control Position—±5%
Directional Control Position—±5% Collective
Control Position—±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.) Data
must be recorded for
speeds from
50 kts., ±5 kts
through at
least maximum
glide distance
airspeed. May
be a series of
snapshot tests.
Entry ..................
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
6
7
X
X
X
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.
X
X
1.i. Autorotation
1.j. Landing
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59853
TABLE D2A.—FLIGHT TRAINING DEVICE (FTD) OBJECTIVE TESTS—Continued
<<>>
Test
<>
Notes
FTD level
Tolerances
Number
All Engines ........
1.j.2. through
1.j.3.
Reserved.
1.j.4. ..................
Autorotational
Landing.
Test details
Title
1.j.1. ..................
Flight conditions
5
6
7
Airspeed—±3 kts., AltiApproach ...........
tude—±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%.
Record results of
the approach
and landing
profile (running
landing or approach to a
hover). The
criteria apply
only to those
segments at
airspeeds
above effective
translational
lift. Record the
results from
200 ft. AGL
(61 m) to the
landing or to
where the
hover is established prior to
landing.
X
Torque—±3%, Rotor
Landing ..............
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%.
Record the results of an
autorotational
deceleration
and landing
from a stabilized
autorotational
descent, to
touch down.
X
2. Handling Qualities
2.a. ....................
Control System
Contact the NSPM for
Mechanical
clarification of any
Characteristics.
issue regarding helicopters with reversible
controls.
2.a.1. .................
Cyclic .................
Breakout—±0.25 lbs.
(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.)
X
X
X
2.a.2. .................
Collective and
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.
Record results
for an uninterrupted control
sweep to the
stops.
X
X
X
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59854
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE D2A.—FLIGHT TRAINING DEVICE (FTD) OBJECTIVE TESTS—Continued
<<>>
Test
<>
Notes
FTD level
Tolerances
Flight conditions
Test details
Number
Title
5
2.a.3. .................
Brake Pedal
Force vs. Position.
2.a.4. .................
Trim System
Rate—±10% ....................
Rate (all applicable systems).
Ground; Static
conditions.
Trim On Friction Off.
The tolerance
applies to the
recorded value
of the trim rate.
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.
Results must be
recorded for a
normal control
displacement
in both directions in each
axis, using
25% to 50% of
full throw.
2.a.6. .................
Freeplay ............
±0.10 in ...........................
Ground; Static
conditions.
Record and compare results for
all controls.
±5 lbs. (2.224 daN) or
10%.
7
X
Ground; Static
conditions.
6
X
X
X
X
X
X
X
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.
Record results
for several airspeed increments to the
translational
airspeed limits
and for 45 kts.
forward airspeed. May be
a series of
snapshot tests.
X
2.b.2. .................
Critical Azimuth
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%.
Stationary Hover.
Augmentation
On and Off.
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.3. .................
Control Response.
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Control Dynamics
for irreversible
control systems
may be evaluated in a ground/
static condition.
Refer to paragraph 3 of this
attachment for
additional information. ‘‘N’’ is
the sequential
period of a full
cycle of oscillation.
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
59855
TABLE D2A.—FLIGHT TRAINING DEVICE (FTD) OBJECTIVE TESTS—Continued
<<>>
Test
<>
Notes
FTD level
Tolerances
Flight conditions
Test details
Number
Title
5
6
7
2.b.3.a. ..............
Longitudinal .......
Pitch 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. This
test must be
conducted in a
hover, in
ground effect,
without entering
translational
flight.
X
This is a ‘‘short
time’’ test.
2.b.3.c. ..............
Directional .........
Yaw Rate—±10% or ±2°/
sec. Heading
Change—±10% or ±2°.
Hover Augmentation On
and Off.
Record results
for a step control input. The
Off-axis response must
show correct
trend for unaugmented
cases. This
test must be
conducted in a
hover, in
ground effect,
without entering
translational
flight.
X
This is a ‘‘short
time’’ test.
2.b.3.d. ..............
Vertical ..............
Normal Acceleration
±0.1g.
Hover .................
Record results
for a step control input. The
Off-axis response must
show correct
trend for unaugmented
cases.
X
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 Off-axis
response must
show correct
trend for unaugmented
cases.
2.c. Longitudinal Handling Qualities
2.c.1. .................
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X
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X
X
59856
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE D2A.—FLIGHT TRAINING DEVICE (FTD) OBJECTIVE TESTS—Continued
<<>>
Test
<>
Notes
FTD level
Tolerances
Number
Static Stability ....
2.c.3. .................
Dynamic Stability.
2.c.3.a. ..............
2.c.3.b. ..............
Test details
Title
2.c.2. .................
Flight conditions
VerDate Aug<31>2005
5
6
7
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. For non-periodic
responses, the time
history must be
matched within ±10%
pitch; and ±10% airspeed over a 20 sec
period following release
of the controls.
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 nonperiodic responses, the
test may be
terminated
prior to 20 sec
if the test pilot
determines
that the results
are becoming
uncontrollably
divergent. Displace the cyclic for one
second or less
to excite the
test. The result
will be either
convergent or
divergent and
must be recorded. If this
method fails to
excite the test,
displace the
cyclic to the
predetermined
maximum desired pitch attitude and return to the
original position. If this
method is
used, record
the results.
X
X
X
The response for
certain helicopters may be
unrepeatable
throughout the
stated time.
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
A control doublet
inserted at the
natural frequency
of the aircraft
normally excites
this test.
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
59857
TABLE D2A.—FLIGHT TRAINING DEVICE (FTD) OBJECTIVE TESTS—Continued
<<>>
Test
Number
Flight conditions
Test details
Title
2.c.4. .................
<>
Notes
FTD level
Tolerances
5
Maneuvering
Stability.
Longitudinal Control Position—±10% of change
from trim or ±0.25 in.
(6.3 mm) or Longitudinal Control Forces—
±0.5 lb. (0.223 daN) or
±10%.
Cruise or Climb.
Augmentation
On and Off.
7
X
Record results
for at least two
airspeeds at
30°–45° bank
angle. The
force may be
shown as a
cross plot for
irreversible
systems. May
be a series of
snapshot tests.
6
X
2.d. Lateral and Directional Handling Qualities
2.d.1. .................
Control Response.
2.d.1.a ...............
Lateral ...............
Roll Rate—±10% or ±3°/
sec. Roll Attitude
Change—±10% or ±3°.
Cruise Augmentation On
and Off.
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.
X
X
X
2.d.1.b. ..............
Directional .........
Yaw Rate—±10% or ±2°/
sec. Yaw Attitude
Change—±10% or ±2°.
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 Offaxis response
must show
correct trend
for unaugmented cases.
X
X
X
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59858
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE D2A.—FLIGHT TRAINING DEVICE (FTD) OBJECTIVE TESTS—Continued
<<>>
Test
<>
Notes
FTD level
Tolerances
Number
Directional Static
Stability.
2.d.3. .................
Dynamic Lateral
and Directional
Stability.
2.d.3.a. ..............
Lateral-Directional Oscillations.
Test details
Title
2.d.2. .................
Flight conditions
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5
6
7
Lateral Control Position—
±10% of change from
trim or ±0.25 in. (6.3
mm) 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. (6.3 mm) or
Directional Control
Force—±1 lb. (0.448
daN) or 10%. Longitudinal Control Position—
±10% of change from
trim or ±0.25 in. (6.3
mm). Vertical Velocity—±100 fpm (0.50m/
sec) or 10%.
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% or ±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 test may
be terminated
prior to 20 sec
if the test pilot
determines
that the results
are becoming
uncontrollably
divergent.
X
X
X
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This is a steady
heading sideslip
test.
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
59859
TABLE D2A.—FLIGHT TRAINING DEVICE (FTD) OBJECTIVE TESTS—Continued
<<>>
Test
<>
Notes
FTD level
Tolerances
Flight conditions
Number
Title
2.d.3.b. ..............
Spiral Stability ...
±2° or ±10% roll angle ....
Cruise or Climb.
Augmentation
On and Off.
2.d.3.c. ..............
Adverse/
Proverse Yaw.
Correct Trend, ±2° transient sideslip angle.
Cruise or Climb.
Augmentation
On and Off.
Test details
5
6
7
Record the results of a release from
pedal only or
cyclic only
turns for 20
sec. Results
must be recorded from
turns in both
directions. Terminate check
at zero roll
angle or when
the test pilot
determines
that the attitude is becoming uncontrollably divergent.
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.
X
X
X
3. Reserved
4. Visual System
4.a. Visual System Response Time: (Choose either test 4.a.1. or 4.a.2. to satisfy test 4.a., Visual System Response Time Test. This test is also
sufficient for flight deck instrument response timing.)
4.a.1. .................
Latency.
150 ms (or less) after helicopter response.
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
150 ms (or less) after
controller movement.
4.a.2. .................
Takeoff, climb,
and descent.
N/A ....................
A separate test
is required in
each axis
(pitch, roll, and
yaw).
X
Transport Delay.
4.b. Field of View
4.b.1. .................
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Reserved.
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59860
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE D2A.—FLIGHT TRAINING DEVICE (FTD) OBJECTIVE TESTS—Continued
<<>>
Test
Number
<>
Notes
FTD level
Tolerances
Flight conditions
Test details
Title
5
4.b.2. .................
Continuous visual field of
view.
4.b.3. .................
Surface contrast
ratio.
7
Reserved.
4.c. ....................
6
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Minimum continuous field
of view providing 146°
horizontal and 36°
vertical field of view for
each pilot simultaneously and any geometric error between
the Image Generator
eye point and the pilot
eye point is 8° or less.
N/A ....................
An SOC is required and
must explain
the geometry
of the installation. Horizontal
field of view
must not be
less than a
total of 146°
(including not
less than 73°
measured either side of the
center of the
design eye
point). Additional horizontal field of
view capability
may be added
at the sponsor’s discretion
provided the
minimum field
of view is retained. Vertical
field of view:
Not less than
a total of 36°
measured from
the pilot’s and
co-pilot’s eye
point.
X
Horizontal field of
view is centered
on the zero degree azimuth line
relative to the aircraft fuselage.
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/m2) 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 aft-cab and
flight deck ambient light levels
should be zero.
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Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
59861
TABLE D2A.—FLIGHT TRAINING DEVICE (FTD) OBJECTIVE TESTS—Continued
<<>>
Test
Number
<>
Notes
FTD level
Tolerances
Flight conditions
Test details
Title
5
6
7
4.d. ....................
Highlight brightness.
Not less than three (3)
foot-lamberts (10 cd/
m2).
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,
but measuring
light points is
not acceptable.
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.
4.e. ....................
Surface resolution.
Not greater than two (2)
arc minutes.
N/A ....................
An SOC is required and
must include
the relevant
calculations.
X
The eye will subtend two (2) 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.
This requirement
is the same as 4
arc minutes per
optical line pair.
4.f. .....................
Light point size ..
Not greater than five (5)
arc-minutes.
N/A ....................
An SOC is required and
must include
the relevant
calculations.
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.
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59862
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
TABLE D2A.—FLIGHT TRAINING DEVICE (FTD) OBJECTIVE TESTS—Continued
<<>>
Test
Number
<>
Notes
FTD level
Tolerances
Flight conditions
Test details
Title
5
4.g. ....................
7
Light point contrast ratio.
4.g.1. .................
6
Reserved.
4.g.2. .................
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.
Not less than 25:1 ...........
N/A ....................
An SOC is required and
must include
the relevant
calculations.
X
The visible segment in
the simulator must be
within 20% of the segment computed to be
visible from the helicopter flight deck. The
tolerance(s) may be
applied at either end or
at both ends of the displayed segment. However, lights and ground
objects computed to be
visible from the helicopter flight deck at the
near end of the visible
segment must be visible in the simulator.
Landing configuration, trimmed
for appropriate
airspeed, at
100 ft (30 m)
above the
touchdown
zone, on glide
slope with an
RVR value set
at 1,200 ft
(350 m).
The QTG must
contain relevant calculations and a
drawing showing the data
used to establish the helicopter location
and the segment of the
ground that is
visible considering design
eyepoint, helicopter attitude,
flight deck cutoff angle, and
a visibility of
1200 ft (350
m) RVR. Simulator performance must be
measured
against the
QTG calculations. The data
submitted
must include
at least the following:
X
4.h. Visual ground segment
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Pre-position for this
test is encouraged, but may be
achieved via
manual or autopilot control to
the desired position.
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
59863
TABLE D2A.—FLIGHT TRAINING DEVICE (FTD) OBJECTIVE TESTS—Continued
<<>>
Test
Number
Flight conditions
Test details
Title
5
(1) Static helicopter 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 flight
deck 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. If
non-homogenous fog is
used to obscure visibility,
the vertical
variation in
horizontal visibility must be
described and
be included in
the slant range
visibility calculation used
in the computations.
5. Reserved
VerDate Aug<31>2005
<>
Notes
FTD level
Tolerances
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6
7
59864
Federal Register / Vol. 72, No. 203 / Monday, October 22, 2007 / Proposed Rules
lllllllllllllllllllll
Begin Information
3. Control Dynamics
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
helicopter is the ‘‘feel’’ provided through the
flight deck 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
the pilot with the proper feel; that of the
respective helicopter.
(1) Recordings such as free response to an
impulse or step function are classically used
to estimate the dynamic properties of
electromechanical systems. 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 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.
(2) For initial and upgrade evaluations, it
is required that control dynamic
characteristics be measured at and recorded
directly from the flight deck 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 pitot-static inputs (if
appropriate) must be provided to represent
airspeeds typical of those encountered in
flight.
(3) 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
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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.
b. Control Dynamics Evaluations. The
dynamic properties of control systems are
often stated in terms of frequency, damping,
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.
(1) 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.
(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 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)
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on Figure 1 of this attachment is ±5 percent
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.
(c) 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.
(d) Special considerations. Control systems
that exhibit characteristics other than
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 summarizes the
tolerances, ‘‘T’’ for underdamped systems,
and ‘‘n’’ is the sequential period of a full
cycle of oscillation. See Figure D2A 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
First overshoot and ±1
overshoots.
subsequent overshoots
(b) The following tolerance applies to
critically damped and overdamped systems
only. See Figure D2B for an illustration of the
reference measurements:
T(P0) ................. ±10% of P0
BILLING CODE 4910–13–P
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Begin QPS Requirement
BILLING CODE 4910–13–C
c. Alternative method for control dynamics
evaluation.
(1) An alternative means for validating
control dynamics for aircraft with
hydraulically powered flight controls and
artificial feel systems is by the measurement
of control force and rate of movement. For
each axis of pitch, roll, and yaw, the control
must be forced to its maximum extreme
position for the following distinct rates.
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These tests are conducted at under normal
flight and ground conditions.
(a) Static test—Slowly move the control so
that a full sweep is achieved within 95–105
seconds. 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 within 8–12 seconds.
(c) Fast dynamic test—Achieve a full
sweep within 3–5 seconds.
Note: Dynamic sweeps may be limited to
forces not exceeding 100 lbs. (44.5 daN).
(d) Tolerances
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(i) Static test; see Table D2A, Flight
Training Device (FTD) Objective Tests, Items
2.a.1., 2.a.2., and 2.a.3.
(ii) Dynamic test—±2 lbs (0.9 daN) or ±10%
on dynamic increment above static test.
End QPS Requirement
lllllllllllllllllllll
Begin Information
d. The FAA is open to alternative means
that are justified and appropriate to the
application. For example, the method
described here may not apply to all
manufacturers’ systems and certainly not to
aircraft with reversible control systems. Each
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case is considered on its own merit on an ad
hoc basis. If the FAA finds that alternative
methods do not result in satisfactory
performance, more conventionally accepted
methods will have to be used.
4. For Additional Information on the
Following Topics, Please Refer to Appendix
C, Attachment 2, and the Indicated
Paragraph Within That Attachment
• Additional Information About Flight
Simulator Qualification for New or
Derivative Helicopters, paragraph 8.
• Engineering Simulator Validation Data,
paragraph 9.
• Validation Test Tolerances, paragraph
11.
• Validation Data Road Map, paragraph 12.
• Acceptance Guidelines for Alternative
Avionics, paragraph 13.
• Transport Delay Testing, paragraph 14.
• Continuing Qualification Evaluation
Validation Data Presentation, paragraph 15.
End Information
lllllllllllllllllllll
Attachment 3 to Appendix D to Part 60—
Flight Training Device (FTD) Subjective
Evaluation
lllllllllllllllllllll
Begin QPS Requirements
1. Requirements
a. Except for special use visual scenes and
airport models described below, all visual
scenes and airport models required by this
part must be representations of real-world,
operational airports or representations of
fictional airports and must meet the
requirements set out in Tables D3B and D3C
of this attachment, as appropriate.
b. If fictional airports are used, the sponsor
must ensure that navigational aids and all
appropriate maps, charts, and other
navigational reference material for the
fictional airports (and surrounding areas as
necessary) are compatible, complete, and
accurate with respect to the visual
presentation and scene content of the visual
model of this fictional airport. An SOC must
be submitted that addresses navigation aid
installation and performance and other
criteria (including obstruction clearance
protection) for all instrument approaches to
the fictional airports that are available in the
simulator. The SOC must reference and
account for information in the terminal
instrument procedures manual and the
construction and availability of the required
maps, charts, and other navigational material.
This material must be clearly marked ‘‘for
training purposes only.’’
c. When the simulator is being used by an
instructor or evaluator for purposes of
training, checking, or testing under this
chapter, only visual scenes and airport
models classified as Class I, Class II, or Class
III may be available to the instructor or
evaluator. The classifications are as follows:
(1) Class I (whether modeling real world
airports or fictional airports), for those visual
scenes and airport models used for FTD
qualification at a specified level. These visual
scenes and airport models must meet the
minimum requirements in Table D3B of this
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attachment, be evaluated by the NSPM, be
listed on the Statement of
Qualification(SOQ), and be available for use
at the FTD IOS.
(2) Class II (whether modeling real world
airports or fictional airports), for those visual
scenes and airport models that are in excess
of those used for FTD qualification at a
specified level. These visual scenes and
airport models must meet the minimum
requirements set out in Table C3C of this
attachment. These visual scenes and airport
models may be made available on the FTD
IOS without further involvement of the
NSPM or the TPAA.
(3) For an interim period ending (2 years
after date of publication of the final rule in
the Federal Register), Class III visual scenes
and airport models (whether modeling real
world airports, generic airports, or fictional
airports) may be approved for specific
purposes by the TPAA or a foreign regulatory
authority for a foreign user of the device.
Examples of approved activities include
specific airport or runway qualification, very
low visibility operations training, including
Surface Movement Guidance System (SMGS)
operations, or use of a specific airport visual
model aligned with an instrument procedure
for another airport for instrument training. At
the end of the interim period, all Class III
visual scenes and airport models must be
classified as either a Class I or a Class II
visual scene or airport model or be removed
from availability at the simulator IOS.
However, Class III visual scenes and airport
models may continue to be used after the end
of the interim period if they are part of a
training program specifically approved by the
TPAA or other regulatory authority that uses
a task and capability analysis as the basis for
approval of this specific media element, (i.e.,
the specific scene or model selected for use
in that program).
d. When a person sponsors an FSTD
maintained by a person other than a U.S.
certificate holder, the sponsor is accountable
for that FSTD originally meeting, and
continuing to meet, the criteria under which
it was originally qualified and the
appropriate Part 60 criteria, including the
visual scenes and airport models that may be
used by instructors or evaluators for purposes
of training, checking, or testing under this
chapter.
e. Neither Class II nor Class III airport
visual models are required to appear on the
SOQ. However, the sponsor is accountable
that the FSTD originally meets, and
continues to meet, the visual scene and
airport model requirements for Class II or
Class III visual scenes and airport models
that may be used by instructors or evaluators
for training, checking, or testing under this
chapter.
f. When the visual scenes and airport
models represent real world airports and a
permanent change is made to that real world
airport (e.g., a new runway, an extended
taxiway, a new lighting system, a runway
closure) without a written extension grant
from the NSPM (described below), an update
to that visual scene or airport model must be
made in accordance with the following time
limits:
(1) For a new airport runway, a runway
extension, a new airport taxiway, a taxiway
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extension, or a runway/taxiway closure—
within 60 days of the opening for use of the
new airport runway, runway extension, new
airport taxiway, or taxiway extension; or
within 60 days of the closure of the runway
or taxiway.
(2) For a new or modified approach light
system—within 30 days of the activation of
the new or modified approach light system.
(3) For other facility or structural changes
on the airport (e.g., new terminal, relocation
of Air Traffic Control Tower)—within 6
months of the opening of the new or changed
facility or structure.
g. If a sponsor desires an extension to the
time limit for an update to a visual scene or
airport model, the sponsor must provide a
written extension request to the POI/TCPM
stating the reason for the update delay and
a proposed completion date. A copy of this
request must also be sent to the NSPM. The
sponsor will forward a copy of the POI/
TCPM’s response to the NSPM. If the POI/
TCPM has granted an extension, the NSPM
will issue an extension authorization, not to
exceed an additional 12 months.
End QPS Requirements
lllllllllllllllllllll
Begin Information
2. Discussion
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
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.
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.
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 specific operation (e.g., a Line
Oriented Flight Training (LOFT) scenario) or
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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.
e. The FAA intends to allow the use of
Class III visual scenes and airport models on
a limited basis when the sponsor provides
the TPAA (or other regulatory authority) an
appropriate analysis of the skills, knowledge,
and abilities (SKAs) necessary for competent
performance of the tasks in which this
particular media element is used. The
analysis should describe the ability of the
FSTD/visual media to provide an adequate
environment in which the required SKAs
may be satisfactorily performed and learned.
The analysis should also include the specific
media element, such as the visual scene or
59867
airport model. Additional sources of
information on the conduct of task and
capability analysis may be found on the
FAA’s Advanced Qualification Program
(AQP) Web site at: https://www.faa.gov/
education_research/training/aqp/.
End Information
lllllllllllllllllllll
TABLE D3A.—TABLE OF FUNCTIONS AND SUBJECTIVE TESTS LEVEL 7 FTD
<<>>
Number
Operations tasks
Tasks in this table are subject to evaluation if appropriate for the helicopter simulated as indicated in the SOQ Configuration List or a Level 7
FTD. Items not installed, not functional on the FTD, and not appearing on the SOQ Configuration List, are not required to be listed as exceptions on the SOQ.
1. Preflight Procedures
1.a. ................
Preflight Inspection (Flight Deck Only) switches, indicators, systems, and equipment.
1.b. ................
APU/Engine start and run-up.
1.b.1. .............
Normal start procedures.
1.b.2. .............
Alternate start procedures.
1.b.3. .............
Abnormal starts and shutdowns (hot start, hung start).
1.b.4. .............
Rotor engagement.
1.b.5. .............
System checks.
1.c. ................
Taxiing—Ground.
1.c.1. .............
Power required to taxi.
1.c.2. .............
Brake effectiveness.
1.c.3. .............
Ground handling.
1.c.4. .............
Abnormal/emergency procedures, for example:
1.c.4.a. ..........
Brake system failure.
1.c.4.b. ..........
Ground resonance.
1.c.4.c. ..........
Other (as may be listed on the Statement of Qualification).
1.d. ................
Taxiing—Hover.
1.d.1. .............
Takeoff to a hover.
1.d.2. .............
Instrument response.
1.d.2.a. ..........
Engine instruments.
1.d.2.a. ..........
Flight instruments.
1.d.3. .............
Hovering turns.
1.d.4. .............
Hover power checks.
1.d.4.a. ..........
In ground effect (IGE).
1.d.4.b. ..........
Out of ground effect (OGE).
1.d.5. .............
Crosswind/tailwind hover.
1.d.6. .............
Abnormal/emergency procedures:
1.d.6.a. ..........
Engine failure.
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TABLE D3A.—TABLE OF FUNCTIONS AND SUBJECTIVE TESTS LEVEL 7 FTD—Continued
<<>>
Number
Operations tasks
1.d.6.b. ..........
Fuel governing system failure.
1.d.6.c. ..........
Settling with power (OGE).
1.d.6.d. ..........
Stability augmentation system failure.
1.d.6.e. ..........
Directional control malfunction (including Loss of Tail Rotor Effectiveness, LTE).
1.d.6.f. ...........
Other (as may be listed on the Statement of Qualification).
1.e. ................
Pre-takeoff Checks.
2. Takeoff and Departure Phase
2.a. ................
Normal and Crosswind Takeoff.
2.a.1. .............
From ground.
2.a.2. .............
From hover.
2.a.3. .............
Running.
2.a.4. .............
Crosswind/tailwind.
2.a.5. .............
Maximum performance.
2.b. ................
Instrument.
2.c. ................
Powerplant Failure During Takeoff.
2.c.1. .............
Takeoff with engine failure after critical decision point (CDP).
2.d. ................
Rejected Takeoff.
2.e. ................
Instrument Departure.
2.f. .................
Other (as may be listed on the Statement of Qualification).
3. Climb
3.a. ................
Normal.
3.b. ................
Obstacle clearance.
3.c. ................
Vertical.
3.d. ................
One engine inoperative.
3.e. ................
Other (as may be listed on the Statement of Qualification).
4. Inflight Maneuvers
4.a. ................
Performance.
4.b. ................
Flying qualities.
4.c. ................
Turns.
4.c.1. .............
Timed.
4.c.2. .............
Normal.
4.c.3. .............
Steep.
4.d. ................
Accelerations and decelerations.
4.e. ................
High-speed vibrations.
4.f. .................
Abnormal/emergency procedures, for example:
4.f.1. ..............
Engine fire.
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TABLE D3A.—TABLE OF FUNCTIONS AND SUBJECTIVE TESTS LEVEL 7 FTD—Continued
<<>>
Number
Operations tasks
4.f.2. ..............
Engine failure.
4.f.2.a. ...........
Powerplant Failure—Multiengine Helicopters.
4.f.2.b. ...........
Powerplant Failure—Single-Engine Helicopters.
4.f.3. ..............
In-flight engine shutdown (and restart, if applicable).
4.f.4. ..............
Fuel governing system failures (e.g., FADEC malfunction).
4.f.5. ..............
Directional control malfunction.
4.f.6. ..............
Hydraulic failure.
4.f.7. ..............
Stability augmentation system failure.
4.f.8. ..............
Rotor vibrations.
4.f.9. ..............
Recovery From Unusual Attitudes.
4.f.10. ............
Settling with Power.
4.g. ................
Other (as may be listed on the Statement of Qualification).
5. Instrument Procedures
5.a. ................
Instrument Arrival.
5.b. ................
Holding.
5.c. ................
Precision Instrument Approach.
5.c.1. .............
Normal—All engines operating.
5.c.2. .............
Manually controlled—One or more engines inoperative.
5.c.3. .............
Approach procedures:
5.c.3.a. ..........
PAR.
5.c.3.b. ..........
GPS.
5.c.3.c. ..........
ILS.
5.c.3.c.1. .......
Manual (raw data).
5.c.3.c.2. .......
Autopilot* only.
5.c.3.c.3. .......
Flight director only.
5.c.3.c.4. .......
Autopilot* and flight director (if appropriate) coupled.
5.c.3.d. ..........
Other (as may be listed on the Statement of Qualification).
5.d. ................
Non-precision Instrument Approach.
5.d.1. .............
Normal—All engines operating.
5.d.2. .............
One or more engines inoperative.
5.d.3. .............
Approach procedures:
5.d.3.a. ..........
NDB.
5.d.3.b. ..........
VOR, RNAV, TACAN, GPS.
5.d.3.c. ..........
ASR.
5.d.3.d. ..........
Circling.
5.d.3.e. ..........
Helicopter only.
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TABLE D3A.—TABLE OF FUNCTIONS AND SUBJECTIVE TESTS LEVEL 7 FTD—Continued
<<>>
Number
Operations tasks
5.d.3.f. ...........
Other (as may be listed on the Statement of Qualification.
5.e. ................
Missed Approach.
5.e.1. .............
All engines operating.
5.e.2. .............
One or more engines inoperative.
5.e.3. .............
Stability augmentation system failure.
5.e.4. .............
Other (as may be listed on the Statement of Qualification).
6. Landings and Approaches to Landings
6.a. ................
Visual Approaches.
6.a.1. .............
Normal.
6.a.2. .............
Steep.
6.a.3. .............
Shallow.
6.a.4. .............
Crosswind.
6.b. ................
Landings.
6.b.1. .............
Normal.
6.b.1.a. ..........
Running.
6.b.1.b. ..........
From Hover.
6.b.2. .............
Crosswind.
6.b.3. .............
Tailwind.
6.b.4. .............
One or more engines inoperative.
6.b.5. .............
Rejected Landing.
6.b.6. .............
Other (as may be listed on the Statement of Qualification).
7. Normal and Abnormal Procedures (any phase of flight)
7.a. ................
Helicopter and powerplant systems operation (as applicable).
7.a.1. .............
Anti-icing/deicing systems.
7.a.2. .............
Auxiliary power-plant.
7.a.3. .............
Communications.
7.a.4. .............
Electrical system.
7.a.5. .............
Environmental system.
7.a.6. .............
Fire detection and suppression.
7.a.7. .............
Flight control system.
7.a.8. .............
Fuel system.
7.a.9. .............
Engine oil system.
7.a.10. ...........
Hydraulic system.
7.a.11. ...........
Landing gear.
7.a.12. ...........
Oxygen.
7.a.13. ...........
Pneumatic.
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TABLE D3A.—TABLE OF FUNCTIONS AND SUBJECTIVE TESTS LEVEL 7 FTD—Continued
<<>>
Number
Operations tasks
7.a.14. ...........
Powerplant.
7.a.15. ...........
Flight control computers.
7.a.16. ...........
Fly-by-wire controls.
7.a.17. ...........
Stabilizer.
7.a.18. ...........
Stability augmentation and control augmentation system(s).
7.a.19. ...........
Other (as may be listed on the Statement of Qualification).
7.b. ................
Flight management and guidance system (as applicable).
7.b.1. .............
Airborne radar.
7.b.2. .............
Automatic landing aids.
7.b.3. .............
Autopilot*.
7.b.4. .............
Collision avoidance system.
7.b.5. .............
Flight data displays.
7.b.6. .............
Flight management computers.
7.b.7. .............
Head-up displays.
7.b.8. .............
Navigation systems.
7.b.9. .............
Other (as may be listed on the Statement of Qualification).
8. Emergency procedures (as applicable)
8.a. ................
Autorotative Landing.
8.b. ................
Air hazard avoidance.
8.c. ................
Ditching.
8.d. ................
Emergency evacuation.
8.e. ................
Inflight fire and smoke removal.
8.f. .................
Retreating blade stall recovery.
8.g. ................
Mast bumping.
8.h. ................
Loss of tail rotor effectiveness.
8.i. .................
Other (as may be listed on the Statement of Qualification).
9. Postflight Procedures
9.a. ................
After-Landing Procedures.
9.b. ................
Parking and Securing.
9.b.1. .............
Engine and systems operation.
9.b.2. .............
Parking brake operation.
9.b.3. .............
Rotor brake operation.
9.b.4. .............
Abnormal/emergency procedures.
10. Instructor Operating Station (IOS), as appropriate
10.a. ..............
Power Switch(es).
10.b. ..............
Helicopter conditions.
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TABLE D3A.—TABLE OF FUNCTIONS AND SUBJECTIVE TESTS LEVEL 7 FTD—Continued
<<>>
Number
Operations tasks
10.b.1. ...........
Gross weight, center of gravity, fuel loading and allocation, etc.
10.b.2. ...........
Helicopter systems status.
10.b.3. ...........
Ground crew functions (e.g., ext. power).
10.c. ..............
Airports.
10.c.1. ...........
Selection.
10.c.2. ...........
Runway selection.
10.c.3. ...........
Preset positions (e.g., ramp, over final approach fix).
10.d. ..............
Environmental controls.
10.d.1. ...........
Temperature.
10.d.2. ...........
Climate conditions (e.g., ice, rain).
10.d.3. ...........
Wind speed and direction.
10.e. ..............
Helicopter system malfunctions.
10.e.1. ...........
Insertion/deletion.
10.e.2. ...........
Problem clear.
10.f. ...............
Locks, Freezes, and Repositioning.
10.f.1. ............
Problem (all) freeze/release.
10.f.2. ............
Position (geographic) freeze/release.
10.f.3. ............
Repositioning (locations, freezes, and releases).
10.f.4. ............
Ground speed control.
10.g. ..............
Sound Controls.
10.g.1. ...........
On/off/adjustment.
10.h. ..............
Control Loading System (as applicable).
10.h.1. ...........
On/off/emergency stop.
10.i. ...............
Observer Stations.
10.i.1. ............
Position.
10.i.2. ............
Adjustments.
*‘‘Autopilot’’ means attitude retention mode of operation.
TABLE D3B.—TABLE OF FUNCTIONS AND SUBJECTIVE TESTS LEVEL 7 FTD
<<>>
Number
Visual scene content requirements for qualification at Level 7
This table specifies the minimum airport visual model content and functionality to qualify an FTD at the indicated level. This table applies only to
the airport/helicopter landing area scenes required for FTD qualification.
1. ...................
Functional test content requirements for Level 7 Flight Training Devices.
The following is the minimum airport/landing area model content requirement to satisfy visual capability tests, and provides suitable visual cues to allow completion of all functions and subjective tests described in this attachment for FTDs at Levels 7.
1.a. ................
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A minimum of one (1) representative airport and one (1) representative helicopter landing area model.
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TABLE D3B.—TABLE OF FUNCTIONS AND SUBJECTIVE TESTS LEVEL 7 FTD—Continued
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Number
Visual scene content requirements for qualification at Level 7
The airport and the helicopter landing area may be contained within the same visual model. If this option is selected, the approach path to the airport runway(s) and the approach path to the helicopter landing area must be different. The model(s)
used to meet the following requirements may be demonstrated at either a fictional or a real-world airport or helicopter landing
area, but each must be acceptable to the sponsor’s TPAA, selectable from the IOS, and listed on the Statement of Qualification.
1.b. ................
Fidelity of the Visual Scene.
The fidelity of the visual scene must be sufficient for the aircrew to visually identify the airport and/or helicopter landing area;
determine the position of the simulated helicopter within the visual scene; successfully accomplish take-offs, approaches, and
landings; and maneuver around the airport and/or helicopter landing area on the ground, or hover taxi, as necessary.
1.b.1. .............
For each of the airport/helicopter landing areas described in 1.a., the FTD visual system must be able to provide at least the following:
1.b.1.a. ..........
A night and twilight (dusk) environment.
1.b.1.b. ..........
A daylight environment.
1.c. ................
Runways:
1.c.1. .............
Visible runway number.
1.c.2. .............
Runway threshold elevations and locations must be modeled to provide sufficient correlation with helicopter systems (e.g., altimeter).
1.c.3. .............
Runway surface and markings.
1.c.4. .............
Lighting for the runway in use including runway edge and centerline.
1.c.5. .............
Lighting, visual approach aid (VASI or PAPI) and approach lighting of appropriate colors.
1.c.6. .............
Taxiway lights.
1.d. ................
Helicopter landing area.
1.d.1. .............
Standard heliport designation (‘‘H’’) marking, properly sized and oriented.
1.d.2. .............
Perimeter markings for the Touchdown and Lift-Off Area (TLOF) or the Final Approach and Takeoff Area (FATO), as appropriate.
1.d.3. .............
Perimeter lighting for the TLOF or the FATO areas, as appropriate.
1.d.4. .............
Appropriate markings and lighting to allow movement from the runway or helicopter landing area to another part of the landing
facility.
2. ...................
Visual scene management.
The following is the minimum visual scene management requirements for a Level 7 FTD.
2.a. ................
Runway and helicopter landing area approach lighting must fade into view appropriately in accordance with the environmental
conditions set in the FTD.
2.b. ................
The direction of strobe lights, approach lights, runway edge lights, visual landing aids, runway centerline lights, threshold lights,
touchdown zone lights, and TLOF or FATO lights must be replicated.
3. ...................
Visual feature recognition.
The following are the minimum distances at which runway features must be visible. Distances are measured from runway
threshold or a helicopter landing area to a helicopter aligned with the runway or helicopter landing area on an extended 3°
glide-slope in simulated meteorological conditions. For circling approaches, all tests apply to the runway used for the initial
approach and to the runway of intended landing.
3.a. ................
For runways: runway definition, strobe lights, approach lights, and edge lights from 5 sm (8 km) of the threshold.
3.b. ................
For runways: centerline lights and taxiway definition from 3 sm (5 km).
3.c. ................
For runways: Visual Approach Aid lights (VASI or PAPI) from 3 sm (5 km) of the threshold.
3.d. ................
For runways: Visual Approach Aid lights (VASI or PAPI) from 5 sm (8 km) of the threshold.
3.e. ................
For runways: runway threshold lights and touchdown zone from 2 sm (3 km).
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TABLE D3B.—TABLE OF FUNCTIONS AND SUBJECTIVE TESTS LEVEL 7 FTD—Continued
<<>>
Number
Visual scene content requirements for qualification at Level 7
3.f. .................
For runways and helicopter landing areas: markings within range of landing lights for night/twilight scenes and the surface resolution test on daylight scenes, as required.
3.g. ................
For circling approaches: the runway of intended landing and associated lighting must fade into view in a non-distracting manner.
3.h. ................
For helicopter landing areas: landing direction lights and raised FATO lights from 1 sm (1.5 km).
3.i. .................
For helicopter landing areas: Flush mounted FATO lights, TOFL lights, and the lighted windsock from 0.5 sm (750 m).
4. ...................
Airport or Helicopter Landing Area Model Content.
The following prescribes the minimum requirements for an airport/helicopter landing area visual model and identifies other aspects of the environment that must correspond with that model for a Level 7 FTD. For circling approaches, all tests apply to
the runway used for the initial approach and to the runway of intended landing. If all runways or landing areas in a visual
model used to meet the requirements of this attachment are not designated as ‘‘in use,’’ then the ‘‘in use’’ runways/landing
areas must be listed on the Statement of Qualification (e.g., KORD, Rwys 9R, 14L, 22R). Models of airports or helicopter
landing areas with more than one runway or landing area must have all significant runways or landing areas not ‘‘in-use’’ visually depicted for airport/runway/landing area recognition purposes. The use of white or off white light strings that identify the
runway or landing area for twilight and night scenes are acceptable for this requirement; and rectangular surface depictions
are acceptable for daylight scenes. A visual system’s capabilities must be balanced between providing visual models with an
accurate representation of the airport and a realistic representation of the surrounding environment. Each runway or helicopter landing area designated as an ‘‘in-use’’ runway or area must include the following detail that is either modeled using
airport/heliport pictures, construction drawings and maps, U.S. National Imagery and Mapping Agency data other appropriate
data, or modeled in accordance with published regulatory material.
4.a. ................
The surface and markings for each ‘‘in-use’’ runway or helicopter landing area must include the following:
4.a.1. .............
For airports: runway threshold markings, runway numbers, touchdown zone markings, fixed distance markings, runway edge
markings, and runway centerline stripes.
4.a.2. .............
For helicopter landing areas: markings for standard heliport identification (‘‘H’’) and TOFL, FATO, and safety areas.
4.b. ................
The lighting for each ‘‘in-use’’ runway or helicopter landing area must include the following:
4.b.1. .............
For airports: runway approach, threshold, edge, end, centerline (if applicable), touchdown zone (if applicable), leadoff, and visual landing aid lights or light systems for that runway.
4.b.2. .............
For helicopter landing areas: landing direction, raised and flush FATO, TOFL, windsock lighting.
4.c. ................
The taxiway surface and markings associated with each ‘‘in-use’’ runway or helicopter landing area must include the following:
4.c.1. .............
For airports: taxiway edge, centerline (if appropriate), runway hold lines, and ILS critical area(s).
4.c.2. .............
For helicopter landing areas: taxiways, taxi routes, and aprons.
4.d. ................
The taxiway lighting associated with each ‘‘in-use’’ runway or helicopter landing area must include the following:
4.d.1. .............
For airports: taxiway edge, centerline (if appropriate), runway hold lines, ILS critical areas.
4.d.2. .............
For helicopter landing areas: taxiways, taxi routes, and aprons.
4.d.3. .............
For airports: taxiway lighting of correct color.
4.e. ................
Airport signage associated with each ‘‘in-use’’ runway or helicopter landing area must include the following:
4.e.1. .............
For airports: signs for runway distance remaining, intersecting runway with taxiway, and intersecting taxiway with taxiway.
4.e.2. .............
For helicopter landing areas: as may be appropriate for the model used.
4.f. .................
Required visual model correlation with other aspects of the airport or helicopter landing environment simulation:
4.f.1. ..............
The airport or helicopter landing area model must be properly aligned with the navigational aids that are associated with operations at the ‘‘in-use’’ runway or helicopter landing area.
4.f.2. ..............
The simulation of runway or helicopter landing area contaminants must be correlated with the displayed runway surface and
lighting, if applicable.
5. ...................
Correlation with helicopter and associated equipment.
The following are the minimum correlation comparisons that must be made for a Level 7 FTD.
5.a. ................
Visual system compatibility with aerodynamic programming.
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TABLE D3B.—TABLE OF FUNCTIONS AND SUBJECTIVE TESTS LEVEL 7 FTD—Continued
<<>>
Number
Visual scene content requirements for qualification at Level 7
5.b. ................
Visual cues to assess sink rate and depth perception during landings.
5.c. ................
Accurate portrayal of environment relating to FTD attitudes.
5.d. ................
The visual scene must correlate with integrated helicopter systems, where fitted (e.g., terrain, traffic and weather avoidance systems and Head-up Guidance System (HGS)).
5.e. ................
Representative visual effects for each visible, own-ship, helicopter external light(s).
5.f. .................
The effect of rain removal devices.
6. ...................
Scene quality.
The following are the minimum scene quality tests that must be conducted for a Level 7 FTD.
6.a. ................
System light points should be free from distracting jitter, smearing or streaking.
6.b. ................
Demonstration of occulting through each channel of the system in an operational scene.
6.c. ................
Six discrete light step controls (0–5).
7. ...................
Special weather representations, which include visibility and RVR, measured in terms of distance. Visibility/RVR checked at
2,000 ft (600 m) above the airport or helicopter landing area and at two heights below 2,000 ft with at least 500 ft of separation between the measurements. The measurements must be taken within a radius of 10 sm (16 km) from the airport or helicopter landing area.
7.a. ................
Effects of fog on airport lighting such as halos and defocus.
7.b. ................
Effect of own-ship lighting in reduced visibility, such as reflected glare, including landing lights, strobes, and beacons.
8. ...................
Instructor control of the following:
The following are the minimum instructor controls that must be available in a Level 7 FTD.
8.a. ................
Environmental effects: e.g., cloud base, cloud effects, cloud density, visibility in statute miles/kilometers and RVR in feet/meters.
8.b. ................
Airport or helicopter landing area selection.
8.c. ................
Airport or helicopter landing area lighting, including variable intensity.
8.d. ................
Dynamic effects including ground and flight traffic.
End QPS Requirement
Begin Information
9. ...................
An example of being able to ‘‘combine two airport models to achieve two ‘‘in-use’’ runways: One runway designated as the ‘‘inuse’’ runway in the first model of the airport, and the second runway designated as the ‘‘in-use’’ runway in the second model
of the same airport. For example, the clearance is for the ILS approach to Runway 27, Circle to Land on Runway 18 right.
Two airport visual models might be used: the first with Runway 27 designated as the ‘‘in use’’ runway for the approach to runway 27, and the second with Runway 18 Right designated as the ‘‘in use’’ runway. When the pilot breaks off the ILS approach to runway 27, the instructor may change to the second airport visual model in which runway 18 Right is designated as
the ‘‘in use’’ runway, and the pilot would make a visual approach and landing. This process is acceptable to the FAA as long
as the temporary interruption due to the visual model change is not distracting to the pilot.
10. .................
Sponsors are not required to provide every detail of a runway, but the detail that is provided should be correct within reasonable
limits.
End Information
TABLE D3C.—TABLE OF FUNCTIONS AND SUBJECTIVE TESTS LEVEL 7 FTD
<<>>
Number
Visual scene content requirements additional visual models beyond minimum required for qualification
This table specifies the minimum airport or helicopter landing area visual model content and functionality necessary to add visual models to an
FTD’s visual model library (i.e., beyond those necessary for qualification at the stated level) without the necessity of further involvement of the
NSPM or TPAA.
1. ...................
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Visual scene management.
The following is the minimum visual scene management requirements.
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TABLE D3C.—TABLE OF FUNCTIONS AND SUBJECTIVE TESTS LEVEL 7 FTD—Continued
<<>>
Number
Visual scene content requirements additional visual models beyond minimum required for qualification
1.a. ................
The installation and direction of the following lights must be replicated for the ‘‘in-use’’ surface:
1.a.1. .............
For ‘‘in-use’’ runways: strobe lights, approach lights, runway edge lights, visual landing aids, runway centerline lights, threshold
lights, and touchdown zone lights.
1.a.2. .............
For ‘‘in-use’’ helicopter landing areas: ground level TLOF perimeter lights, elevated TLOF perimeter lights (if applicable), Optional TLOF lights (if applicable), ground FATO perimeter lights, elevated TLOF lights (if applicable), landing direction lights.
2. ...................
Visual feature recognition.
The following are the minimum distances at which runway or landing area features must be visible. Distances are measured
from runway threshold or a helicopter landing area to an aircraft aligned with the runway or helicopter landing area on a 3°
glide-slope from the aircraft to the touchdown point, in simulated meteorological conditions. For circling approaches, all tests
apply to the runway used for the initial approach and to the runway of intended landing.
2.a. ................
For Runways.
2.a.1. .............
Strobe lights, approach lights, and edge lights from 5 sm (8 km) of the threshold.
2.a.2. .............
Centerline lights and taxiway definition from 3 sm (5 km).
2.a.3. .............
Visual Approach Aid lights (VASI or PAPI) from 3 sm (5 km) of the threshold.
2.a.4. .............
Visual Approach Aid lights (VASI or PAPI) from 5 sm (8 km) of the threshold.
2.a.5. .............
Threshold lights and touchdown zone lights from 2 sm (3 km).
2.a.6. .............
Markings within range of landing lights for night/twilight (dusk) scenes and as required by the surface resolution test on daylight
scenes.
2.a.7. .............
For circling approaches, the runway of intended landing and associated lighting must fade into view in a non-distracting manner.
2.b. ................
For Helicopter landing areas.
2.b.1. .............
Landing direction lights and raised FATO lights from 2 sm (3 km).
2.b.2. .............
Flush mounted FATO lights, TOFL lights, and the lighted windsock from 1 sm (1500 m).
2.b.3. .............
Hover taxiway lighting (yellow/blue/yellow cylinders) from TOFL area.
2.b.4. .............
Markings within range of landing lights for night/twilight (dusk) scenes and as required by the surface resolution test on daylight
scenes.
3. ...................
Airport or Helicopter Landing Area Model Content.
The following prescribes the minimum requirements for what must be provided in an airport visual model and identifies other aspects of the airport environment that must correspond with that model. The detail must be modeled using airport pictures,
construction drawings and maps, U.S. National Imagery and Mapping Agency data or other data, or modeled in accordance
with published regulatory material; however, this does not require that airport or helicopter landing area models contain details
that are beyond the designed capability of the currently qualified visual system. For circling approaches, all requirements of
this section apply to the runway used for the initial approach and to the runway of intended landing.
3.a. ................
The surface and markings for each ‘‘in-use’’ runway or helicopter landing area must include the following:
3.a.1. .............
For airports: runway threshold markings, runway numbers, touchdown zone markings, fixed distance markings, runway edge
markings, and runway centerline stripes.
3.a.2. .............
For helicopter landing areas: Standard heliport marking (‘‘H’’), TOFL, FATO, and safety areas.
3.b. ................
The lighting for each ‘‘in-use’’ runway or helicopter landing area must include the following:
3.b.1. .............
For airports: runway approach, threshold, edge, end, centerline (if applicable), touchdown zone (if applicable), leadoff, and visual landing aid lights or light systems for that runway.
3.b.2. .............
For helicopter landing areas: landing direction, raised and flush FATO, TOFL, windsock lighting.
3.c. ................
The taxiway surface and markings associated with each ‘‘in-use’’ runway or helicopter landing area must include the following:
3.c.1. .............
For airports: taxiway edge, centerline (if appropriate), runway hold lines, and ILS critical area(s),
3.c.2. .............
For helicopter landing areas: taxiways, taxi routes, and aprons.
3.d. ................
The taxiway lighting associated with each ‘‘in-use’’ runway or helicopter landing area must include the following:
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TABLE D3C.—TABLE OF FUNCTIONS AND SUBJECTIVE TESTS LEVEL 7 FTD—Continued
<<>>
Number
Visual scene content requirements additional visual models beyond minimum required for qualification
3.d.1. .............
For airports: runway edge, centerline (if appropriate), runway hold lines, ILS critical areas.
3.d.2. .............
For helicopter landing areas: taxiways, taxi routes, and aprons.
4. ...................
Required visual model correlation with other aspects of the airport environment simulation.
The following are the minimum visual model correlation tests that must be conducted for Level 7 FTD.
4.a. ................
The airport model must be properly aligned with the navigational aids that are associated with operations at the ‘‘in-use’’ runway.
4.b. ................
Slopes in runways, taxiways, and ramp areas must not cause distracting or unrealistic effects.
5. ...................
Correlation with helicopter and associated equipment.
The following are the minimum correlation comparisons that must be made.
5.a. ................
Visual system compatibility with aerodynamic programming.
5.b. ................
Accurate portrayal of environment relating to flight simulator attitudes.
5.c. ................
Visual cues to assess sink rate and depth perception during landings.
6. ...................
Scene quality.
The following are the minimum scene quality tests that must be conducted.
6.a. ................
Light points free from distracting jitter, smearing or streaking.
6.b. ................
Surfaces and textural cues free from apparent quantization (aliasing).
7. ...................
Instructor controls of the following.
The following are the minimum instructor controls that must be available.
7.a. ................
Environmental effects, e.g., cloud base (if used), cloud effects, cloud density, visibility in statute miles/kilometers and RVR in
feet/meters.
7.b. ................
Airport/Heliport selection.
7.c. ................
Airport/Heliport lighting including variable intensity.
7.d. ................
Dynamic effects including ground and flight traffic.
End QPS Requirements
Begin Information
8. ...................
Sponsors are not required to provide every detail of a runway or helicopter landing area, but the detail that is provided must be
correct within the capabilities of the system.
End Information
TABLE D3D.—TABLE OF FUNCTIONS AND SUBJECTIVE TESTS LEVEL 6 FTD
<<>>
Number
Operations tasks
Tasks in this table are subject to evaluation if appropriate for the helicopter simulated as indicated in the SOQ Configuration List or for a Level 6
FTD. Items not installed or not functional on the FTD and not appearing on the SOQ Configuration List, are not required to be listed as exceptions on the SOQ.
1. Preflight Procedures
1.a. ................
Preflight Inspection (Flight Deck Only) switches, indicators, systems, and equipment.
1.b. ................
APU/Engine start and run-up.
1.b.1. .............
Normal start procedures.
1.b.2. .............
Alternate start procedures.
1.b.3. .............
Abnormal starts and shutdowns.
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TABLE D3D.—TABLE OF FUNCTIONS AND SUBJECTIVE TESTS LEVEL 6 FTD—Continued
<<>>
Number
Operations tasks
1.b.4. .............
Rotor engagement.
1.b.5. .............
System checks.
2. Takeoff and Departure Phase
2.a. ................
Instrument.
2.b. ................
Takeoff with engine failure after critical decision point (CDP).
3. Climb
3.a. ................
Normal.
3.b. ................
One engine inoperative.
4. Inflight Maneuvers
4.a. ................
Performance.
4.b. ................
Flying qualities.
4.c. ................
Turns.
4.c.1. .............
Timed.
4.c.2. .............
Normal.
4.c.3. .............
Steep.
4.d. ................
Accelerations and decelerations.
4.e. ................
Abnormal/emergency procedures:
4.e.1. .............
Engine fire.
4.e.2. .............
Engine failure.
4.e.3. .............
In-flight engine shutdown (and restart, if applicable).
4.e.4. .............
Fuel governing system failures (e.g., FADEC malfunction).
4.e.5. .............
Directional control malfunction (restricted to the extent that the maneuver may not terminate in a landing).
4.e.6. .............
Hydraulic failure.
4.e.7. .............
Stability augmentation system failure.
5. Instrument Procedures
5.a. ................
Holding.
5.b. ................
Precision Instrument Approach.
5.b.1. .............
All engines operating.
5.b.2. .............
One or more engines inoperative.
5.b.3. .............
Approach procedures:
5.b.4. .............
PAR.
5.b.5. .............
ILS.
5.b.6. .............
Manual (raw data).
5.b.7. .............
Flight director only.
5.b.8. .............
Autopilot* and flight director (if appropriate) coupled.
5.c. ................
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Non-precision Instrument Approach.
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TABLE D3D.—TABLE OF FUNCTIONS AND SUBJECTIVE TESTS LEVEL 6 FTD—Continued
<<>>
Number
Operations tasks
5.c. ................
Normal—All engines operating.
5.c. ................
One or more engines inoperative.
5.c. ................
Approach procedures:
5.c.1. .............
NDB.
5.c.2. .............
VOR, RNAV, TACAN, GPS.
5.c.3. .............
ASR.
5.c.4. .............
Helicopter only.
5.d. ................
Missed Approach.
5.d.1. .............
All engines operating.
5.d.2. .............
One or more engines inoperative.
5.d.3. .............
Stability augmentation system failure.
6. Normal and Abnormal Procedures (any phase of flight)
6.a. ................
Helicopter and powerplant systems operation (as applicable).
6.a.1. .............
Anti-icing/deicing systems.
6.a.2. .............
Auxiliary power-plant.
6.a.3. .............
Communications.
6.a.4. .............
Electrical system.
6.a.5. .............
Environmental system.
6.a.6. .............
Fire detection and suppression.
6.a.7. .............
Flight control system.
6.a.8. .............
Fuel system.
6.a.9. .............
Engine oil system.
6.a.10. ...........
Hydraulic system.
6.a.11. ...........
Landing gear.
6.a.12. ...........
Oxygen.
6.a.13. ...........
Pneumatic.
6.a.14. ...........
Powerplant.
6.a.15. ...........
Flight control computers.
6.a.16. ...........
Stability augmentation and control augmentation system(s).
6.b. ................
Flight management and guidance system (as applicable).
6.b.1. .............
Airborne radar.
6.b.2. .............
Automatic landing aids.
6.b.3. .............
Autopilot.*
6.b.4. .............
Collision avoidance system.
6.b.5. .............
Flight data displays.
6.b.6. .............
Flight management computers.
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TABLE D3D.—TABLE OF FUNCTIONS AND SUBJECTIVE TESTS LEVEL 6 FTD—Continued
<<>>
Number
6.b.7. .............
Operations tasks
Navigation systems.
7. Postflight Procedures
7.a. ................
Parking and Securing.
7.b. ................
Engine and systems operation.
7.c. ................
Parking brake operation.
7.d. ................
Rotor brake operation.
7.e. ................
Abnormal/emergency procedures.
8. Instructor Operating Station (IOS), as appropriate
8.a. ................
Power Switch(es).
8.b.1. .............
Helicopter conditions.
8.b.2. .............
Gross weight, center of gravity, fuel loading and allocation, etc.
8.b.3. .............
Helicopter systems status.
8.b.4. .............
Ground crew functions (e.g., ext. power).
8.c. ................
Airports and landing areas.
8.c.1. .............
Number and selection.
8.c.2. .............
Runway or landing area selection.
8.c.3. .............
Preset positions (e.g., ramp, over FAF).
8.c.4. .............
Lighting controls.
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. ................
Helicopter 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.g. ................
Sound Controls. On/off/adjustment.
8.h. ................
Control Loading System (as applicable On/off/emergency stop.)
8.i. .................
Observer Stations.
8.i.1. ..............
Position.
8.i.2. ..............
Adjustments.
* ‘‘Autopilot’’ means attitude retention mode of operation.
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TABLE D3E.—TABLE OF FUNCTIONS AND SUBJECTIVE TESTS LEVEL 5 FTD
<<>>
Number
Operations tasks
Tasks in this table are subject to evaluation if appropriate for the helicopter simulated as indicated in the SOQ Configuration List or for a Level 5
FTD. Items not installed or not functional on the FTD and not appearing on the SOQ Configuration List, are not required to be listed as exceptions on the SOQ.
1. Preflight Procedures
1.a. ................
Preflight Inspection (Flight Deck Only) switches, indicators, systems, and equipment.
1.b. ................
APU/Engine start and run-up.
1.b.1. .............
Normal start procedures.
1.b.2. .............
Alternate start procedures.
1.b.3. .............
Abnormal starts and shutdowns.
2. Climb
2.a. ................
Normal.
3. Inflight Maneuvers
3.a. ................
Performance.
3.b. ................
Turns, Normal.
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).
6. Postflight Procedures
6.a. ................
Parking and Securing.
6.b. ................
Engine and systems operation.
6.c. ................
Parking brake operation.
6.d. ................
Rotor brake operation.
6.e. ................
Abnormal/emergency procedures.
7. Instructor Operating Station (IOS), as appropriate
7.a. ................
Power Switch(es).
7.b. ................
Preset positions (ground; air)
7.c. ................
Helicopter system malfunctions.
7.c.1. .............
Insertion / deletion.
7.c.2. .............
Problem clear.
7.d. ................
Control Loading System (as applicable) On / off / emergency stop.
7.e. ................
Observer Stations.
7.e1. ..............
Position.
7.e.2. .............
Adjustments.
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TABLE D3F.—TABLE OF FUNCTIONS AND SUBJECTIVE TESTS LEVEL 4 FTD
<<>>
Number
Operations tasks
Tasks in this table are subject to evaluation if appropriate for the helicopter simulated as indicated in the SOQ Configuration List or for a Level 4
FTD. Items not installed or not functional on the FTD and not appearing on the SOQ Configuration List, are not required to be listed as exceptions on the SOQ.
1. Preflight Procedures
1.a. ................
Preflight Inspection (Flight Deck Only) switches, indicators, systems, and equipment.
1.b. ................
APU/Engine start and run-up.
1.b.1. .............
Normal start procedures.
1.b.2. .............
Alternate start procedures.
1.b.3. .............
Abnormal starts and shutdowns.
2. Normal and Abnormal Procedures (any phase of flight)
2.a. ................
Normal system operation (Installed systems).
2.b. ................
Abnormal/Emergency system operation (installed systems).
3. Postflight Procedures
3.a. ................
Parking and Securing.
3.b. ................
Engine and systems operation.
3.c. ................
Parking brake operation.
4. Instructor Operating Station (IOS), as appropriate
4.a. ................
Power Switch(es).
4.b. ................
Preset positions (ground; air)
4.c. ................
Helicopter system malfunctions.
4.c.1. .............
Insertion / deletion.
4.c.2. .............
Problem clear.
Attachment 4 to Appendix D to Part 60—
Sample Documents
Table of Contents
Figure D4A Sample Letter, Request for
Initial, Upgrade, or Reinstatement
Evaluation.
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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
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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
BILLING CODE 4910–13–P
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BILLING CODE 4910–13–C
Attachment 5 to Appendix D to Part 60—
FSTD Directives Applicable to Helicopter
Flight Training Devices
Appendix E to Part 60—Qualification
Performance Standards for Quality
Management Systems for Flight Simulation
Training Devices
lllllllllllllllllllll
Begin QPS Requirements
a. Not later than May 30, 2010, each
current sponsor of an FSTD must submit to
the NSPM a proposed Quality Management
System (QMS) program as described in this
appendix. The NSPM will notify the sponsor
of 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 audits, make required
program adjustments as a result of any
internal audit, and schedule the NSPM initial
audit.
b. First-time FSTD sponsors must submit to
the NSPM the proposed QMS program no
later than 120 days before the initial FSTD
evaluation. The NSPM will notify the
sponsor of 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 audits, make required
program adjustments as a result of any
internal audit, and schedule the NSPM initial
audit.
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
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sponsor must designate a Management
Representative (MR) who has the authority to
establish and modify the sponsor’s policies,
practices, and procedures regarding the QMS
program for the recurring qualification and
the daily use of each FSTD.
d. The minimum content required for an
acceptable QMS is found in Table E1. The
policies, processes, 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
recurring periodic assessments;
(2) The NSPM-conducted initial and
recurring 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.
e. The sponsor must conduct assessments
of its QMS program in segments. The
segments will be established by the NSPM at
the initial assessment, and the interval for the
segment assessments will be every 6 months.
The intervals for the segment assessments
may be extended beyond 6 months as the
QMS program matures, but will not be
extended beyond 12 months. The entire QMS
program must be assessed every 24 months.
f. The periodic assessments conducted by
the NSPM will be conducted at intervals not
less than once every 24 months, and include
a comprehensive review of the QMS
program. These reviews will be conducted
more frequently if warranted.
End QPS Requirements
lllllllllllllllllllll
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Begin Information
g. An example of a segment assessment—
At the initial QMS assessment, the NSPM
will divide the QMS program into segments
(e.g., 6 separate segments). There must be an
assessment of a certain number of segments
every 6 months (i.e., segments 1 and 2 at the
end of the first 6 month period; segments 3
and 4 at the end of the second 6 month
period (or one year); and segments 5 and 6
at the end of the third 6 month period (or 18
months). As the program matures, the
interval between assessments may be
extended to 12 months (e.g., segments 1, 2,
and 3 at the end of the first year; and
segments 4, 5, and 6 at the end of the second
year). In both cases, the entire QMS program
is assessed at least every 24 months.
h. The National Simulator Program
Manager has available, on the NSP Web site,
(https://www.faa.gov/safety/
programs_initiatives/aircraft_aviation/nsp/
sqms/) the following materials to assist
sponsors in preparing for an NSPM
evaluation of a mandatory or voluntary QMS
program. The sample documents include:
(1) The NSPM desk assessment tool for
initial evaluation of the required elements of
a QMS program.
(2) The NSPM on-site assessment tool for
initial and continuing evaluation of the
required elements of a QMS program.
(3) The NSPM desk assessment tool for
initial evaluation of the voluntary elements
of a QMS program.
(4) The NSPM on-site assessment tool for
initial and continuing evaluation of the
voluntary elements of a QMS program.
(5) An Element Assessment Table that
describes the circumstances that exist to
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warrant a finding of ‘‘non-compliance,’’ or
‘‘non-conformity;’’ ‘‘partial compliance,’’ or
‘‘partial conformity;’’ and ‘‘acceptable
compliance,’’ or ‘‘acceptable conformity.’’
(6) A sample Continuation Sheet for
additional comments that may be added by
the sponsor or the NSPM during a QMS
evaluation.
(7) A sample Sponsor Checklist to assist
the sponsor in verifying the elements that
comprise the required QMS program.
(8) A sample Sponsor Checklist to assist
the sponsor in verifying the elements that
comprise the voluntary portion of QMS
program.
(9) A table showing the essential functions,
processes, and procedures that relate to the
required and voluntary QMS components
and a cross-reference to each represented
task.
i. 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 or MR may delegate duties
associated with maintaining the qualification
of the FSTD (e.g., corrective and preventive
maintenance, scheduling and conducting
tests or inspections, functional preflight
checks) but retain the responsibility and
authority for the day-to-day qualification of
the FSTD. One person may serve as the
sponsor or MR for more than one FSTD, but
one FSTD may not have more than one
sponsor or MR.
(3) A QMS program may be applicable to
more than one certificate holder (e.g., part
119 and part 142 or two part 119 certificate
holders) and an MR may work for more than
one certificate holder (e.g., part 119 and part
142 or two part 119 certificate holders) as
long as the QMS program requirements and
the MR requirements are met for each
certificate holder.
(4) Standard Measurements for Flight
Simulator Quality: A quality system based on
FSTD performance will improve and
maintain training quality. See https://
www.faa.gov/safety/programs_initiatives/
aircraft_aviation/nsp/sqms/ for more
information on measuring FSTD
performance.
(5) 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 to extend the
intervals between NSPM-conducted
evaluations.
j. The FAA does not mandate a specific
QMS program format, but an acceptable QMS
program should contain the following:.
(1) 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) A MR who has overall authority for
monitoring the on-going qualification of
assigned FSTDs to ensure that all FSTD
qualification issues are resolved as required
by this part. The MR should ensure that the
QMS program is properly implemented and
maintained, and should:
(a) Brief the sponsor’s management on the
qualification processes;
(b) Serve as the primary contact point for
all matters between the sponsor and the
NSPM regarding the qualification of the
assigned FSTDs; and
(c) 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 and a statement
acknowledging completion of a periodic
review by the MR should include the
following:
(a) A maintenance facility that provides
suitable FSTD hardware and software tests
and maintenance capability.
(b) 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.
(c) Routine maintenance of the FSTD and
performance of the QTG tests with adequate
staffing to cover FSTD operating periods.
(d) 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.
End Information
lllllllllllllllllllll
TABLE E1.—FSTD QUALITY MANAGEMENT SYSTEM
Information
(reference)
Number
<<