Special Conditions: Cirrus Design Corporation Model SF50 Airplane; Full Authority Digital Engine Control (FADEC) System, 20518-20520 [2010-9027]
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20518
Federal Register / Vol. 75, No. 75 / Tuesday, April 20, 2010 / Rules and Regulations
Citation
The authority citation for these
special conditions is as follows:
(2) Protective breathing equipment is
available for each flight member on
flight deck duty.
DEPARTMENT OF TRANSPORTATION
Authority: 49 U.S.C. 106(g), 40113 and
44701; 14 CFR 21.16 and 21.17; and 14 CFR
11.38 and 11.19.
SC 23.1199
Containers
14 CFR Part 23
The Special Conditions
Accordingly, pursuant to the
authority delegated to me by the
Administrator, the following special
conditions are issued as part of the type
certification basis for Cirrus Design
Corporation model SF50 airplanes.
The following applies:
(a) Each extinguishing agent container
must have a pressure relief valve to
prevent bursting of the container by
excessive internal pressures.
(b) The discharge end of each
discharge line from a pressure relief
connection must be located so that
discharge of the fire extinguishing agent
would not damage the airplane. The line
must also be located or protected to
prevent clogging caused by ice or other
foreign matter.
(c) A means must be provided for
each fire extinguishing agent container
to indicate that the container has
discharged or that the charging pressure
is below the established minimum
necessary for proper functioning.
(d) The temperature of each container
must be maintained under intended
operating conditions to prevent the
pressure in the container from —
(1) Falling below that necessary to
provide an adequate rate of discharge; or
(2) Rising high enough to cause
premature discharge.
(e) If a pyrotechnic capsule is used to
discharge the extinguishing agent, each
container must be installed so that
temperature conditions will not cause
hazardous deterioration of the
pyrotechnic capsule.
Fire Extinguishing for Upper Aft
Fuselage Mounted Engine
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SC 23.1195 Fire Extinguishing Systems
Fire extinguishing systems must be
installed and compliance shown with
the following:
(a) Except for combustor, turbine, and
tailpipe sections of turbine-engine
installations that contain lines or
components carrying flammable fluids
or gases for which a fire originating in
these sections is shown to be
controllable, a fire extinguisher system
must serve each engine compartment.
(b) The fire extinguishing system, the
quantity of the extinguishing agent, the
rate of discharge, and the discharge
distribution must be adequate to
extinguish fires. An individual ‘‘two
shot’’ system must be used.
(c) The fire extinguishing system for
a nacelle must be able to simultaneously
protect each compartment of the nacelle
for which protection is provided.
SC 23.1197 Fire Extinguishing Agents
The following applies:
(a) Fire extinguishing agents must—
(1) Be capable of extinguishing flames
emanating from any burning of fluids or
other combustible materials in the area
protected by the fire extinguishing
system; and
(2) Have thermal stability over the
temperature range likely to be
experienced in the compartment in
which they are stored.
(b) If any toxic extinguishing agent is
used, provisions must be made to
prevent harmful concentrations of fluid
or fluid vapors (from leakage during
normal operation of the airplane or as a
result of discharging the fire
extinguisher on the ground or in flight)
from entering any personnel
compartment, even though a defect may
exist in the extinguishing system. This
must be shown by test except for builtin carbon dioxide fuselage compartment
fire extinguishing systems for which—
(1) Five pounds or less of carbon
dioxide will be discharged, under
established fire control procedures, into
any fuselage compartment; or
VerDate Nov<24>2008
13:39 Apr 19, 2010
Jkt 220001
SC 23.1201
Materials
Extinguishing Agent
Fire Extinguishing System
The following apply:
(a) No material in any fire
extinguishing system may react
chemically with any extinguishing agent
so as to create a hazard.
(b) Each system component in an
engine compartment must be fireproof.
Issued in Kansas City, Missouri on April
12, 2010.
Steve Thompson,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2010–9026 Filed 4–19–10; 8:45 am]
BILLING CODE 4910–13–P
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Federal Aviation Administration
[Docket No. CE306; Special Conditions No.
23–246–SC]
Special Conditions: Cirrus Design
Corporation Model SF50 Airplane; Full
Authority Digital Engine Control
(FADEC) System
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Final special conditions; request
for comments.
SUMMARY: These special conditions are
issued for the Cirrus Design Corporation
model SF50 airplane. This airplane will
have a novel or unusual design
feature(s) associated with the use of an
electronic engine control system instead
of a traditional mechanical control
system. The applicable airworthiness
regulations do not contain adequate or
appropriate safety standards for this
design feature. These special conditions
contain the additional safety standards
that the Administrator considers
necessary to establish a level of safety
equivalent to that established by the
existing airworthiness standards.
DATES: The effective date of these
special conditions is April 12, 2010.
We must receive your comments by
May 20, 2010.
ADDRESSES: Mail two copies of your
comments to: Federal Aviation
Administration, Regional Counsel,
ACE–7, Attn: Rules Docket No. CE306,
901 Locust, Kansas City, MO 64106.
You may deliver two copies to the
Regional Counsel at the above address.
Mark your comments: Docket No.
CE306. You may inspect comments in
the Rules Docket weekdays, except
Federal holidays, between 7:30 a.m. and
4 p.m.
FOR FURTHER INFORMATION CONTACT:
Peter L. Rouse, Federal Aviation
Administration, Aircraft Certification
Service, Small Airplane Directorate,
ACE–111, 901 Locust, Room 301,
Kansas City, Missouri 64106; 816–329–
4135, fax 816–329–4090.
SUPPLEMENTARY INFORMATION: The FAA
has determined that notice and
opportunity for prior public comment
hereon are impracticable because these
procedures would significantly delay
issuance of the design approval and
thus delivery of the affected aircraft. In
addition, the substance of these special
conditions has been subject to the
public comment process in several prior
instances with no substantive comments
E:\FR\FM\20APR1.SGM
20APR1
Federal Register / Vol. 75, No. 75 / Tuesday, April 20, 2010 / Rules and Regulations
received. The FAA therefore finds that
good cause exists for making these
special conditions effective upon
issuance.
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Comments Invited
Interested persons are invited to
submit such written data, views, or
arguments as they may desire.
Communications should identify the
regulatory docket or special condition
number and be submitted in duplicate
to the address specified above. All
communications received on or before
the closing date for comments will be
considered by the Administrator. The
special conditions may be changed in
light of the comments received.
All comments received will be
available in the Rules Docket for
examination by interested persons, both
before and after the closing date for
comments. A report summarizing each
substantive public contact with FAA
personnel concerning this rulemaking
will be filed in the docket.
Commenters’ wishing the FAA to
acknowledge receipt of their comments
submitted in response to this notice
must include a self-addressed, stamped
postcard on which the following
statement is made: ‘‘Comments to
Docket No. CE306.’’ The postcard will be
date stamped and returned to the
commenter.
Background
On September 9, 2008, Cirrus Design
Corporation applied for a type
certificate for their new model SF50.
The Cirrus Design Corporation model
SF50 is a low-wing, five-plus-two-place
(2 children), single-engine turbofanpowered aircraft. It incorporates an
Electronic Flight Information System
(EFIS), pressurized cabin, retractable
gear, and a V-tail. The turbofan engine
is mounted on the upper fuselage/tail
cone along the aircraft centerline. It is
constructed largely of carbon and
fiberglass composite materials. Like
other Cirrus products, the SF50 includes
a ballistically deployed airframe
parachute.
The model SF50 has a maximum
operating altitude of 28,000 feet, where
it cruises at speeds up to 300 KTAS. Its
VMO will not exceed 0.62 Mach. The
maximum takeoff weight will be at or
below 6000 lbs with a range at economy
cruise of roughly 1000 nm. Cirrus
intends for the model SF50 to be
certified for single-pilot operations
under 14 CFR part 91 and 14 CFR part
135 operating rules. The following
operating conditions will be included:
• Day and Night VFR.
• IFR.
• Flight Into Known Icing.
VerDate Nov<24>2008
13:39 Apr 19, 2010
Jkt 220001
The Cirrus Design Corporation model
SF50 airplane is equipped with a
Williams International FJ33–5A
turbofan engine using an electronic
engine control system (FADEC) instead
of a traditional mechanical control
system. Even though the engine control
system will be certificated as part of the
engine, the installation of an engine
with an electronic control system
requires evaluation due to critical
environmental effects and possible
effects on or by other airplane systems,
for example, indirect effects of
lightning, radio interference with other
airplane electronic systems, shared
engine and airplane data and power
sources.
The regulatory requirements in 14
CFR part 23 for evaluating the
installation of complex systems,
including electronic systems and critical
environmental effects, are contained in
§ 23.1309. However, when § 23.1309
was developed, the use of electronic
control systems for engines was not
envisioned. Therefore, the § 23.1309
requirements were not applicable to
systems certificated as part of the engine
(reference § 23.1309(f)(1)). Parts of the
system that are not certificated with the
engine could be evaluated using the
criteria of § 23.1309. However, the
integral nature of these systems makes
it unfeasible to evaluate the airplane
portion of the system without including
the engine portion of the system.
In some cases, the airplane that the
engine is used in will determine a
higher classification than the engine
controls are certificated for, requiring
the FADEC systems be analyzed at a
higher classification. As of November
2005, FADEC special conditions
mandated the classification for 23.1309
analysis for loss of FADEC control as
catastrophic for any airplane. This is not
to imply an engine failure is classified
as catastrophic, but that the digital
engine control must provide an
equivalent reliability to mechanical
engine controls.
Type Certification Basis
Under the provisions of 14 CFR part
21, § 21.17, Cirrus Design Corporation
must show that the model SF50 meets
the applicable provisions of part 23, as
amended by Amendments 23–1 through
23–59, thereto.
If the Administrator finds that the
applicable airworthiness regulations
(i.e., part 23) do not contain adequate or
appropriate safety standards for the
model SF50 because of a novel or
unusual design feature, special
conditions are prescribed under the
provisions of § 21.16.
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20519
In addition to the applicable
airworthiness regulations and special
conditions, the model SF50 must
comply with the fuel vent and exhaust
emission requirements of 14 CFR part
34 and the noise certification
requirements of 14 CFR part 36. Also,
the FAA must issue a finding of
regulatory adequacy pursuant to § 611 of
Public Law 92–574, the ‘‘Noise Control
Act of 1972.’’
Special conditions, as appropriate, as
defined in 11.19, are issued in
accordance with § 11.38, and become
part of the type certification basis in
accordance with § 21.17(a)(2).
Special conditions are initially
applicable to the model for which they
are issued. Should the type certificate
for that model be amended later to
include any other model that
incorporates the same novel or unusual
design feature, the special conditions
would also apply to the other model
under the provisions of § 21.101(a)(1).
Novel or Unusual Design Features
The Cirrus Design Corporation model
SF50 will incorporate the following
novel or unusual design features:
Electronic engine control system.
Applicability
As discussed above, these special
conditions are applicable to the model
SF50. Should Cirrus Design Corporation
apply at a later date for a change to the
type certificate to include another
model incorporating the same novel or
unusual design feature, the special
conditions would apply to that model as
well as under the provisions of
§ 21.101(a)(1).
Conclusion
This action affects only certain novel
or unusual design features on the model
SF50 airplanes. It is not a rule of general
applicability and it affects only the
applicant who applied to the FAA for
approval of these features on the
airplane.
Under standard practice, the effective
date of final special conditions would
be 30 days after the date of publication
in the Federal Register; however, as the
certification date for the Cirrus Design
Corporation model SF50 is imminent,
the FAA finds that good cause exists to
make these special conditions effective
upon issuance.
List of Subjects in 14 CFR Part 23
Aircraft, Aviation safety, Signs and
symbols.
Citation
The authority citation for these
special conditions is as follows:
■
E:\FR\FM\20APR1.SGM
20APR1
20520
Federal Register / Vol. 75, No. 75 / Tuesday, April 20, 2010 / Rules and Regulations
Authority: 49 U.S.C. 106(g), 40113 and
44701; 14 CFR 21.16 and 21.17; and 14 CFR
11.38 and 11.19.
The Special Conditions
Accordingly, pursuant to the
authority delegated to me by the
Administrator, the following special
conditions are issued as part of the type
certification basis for Cirrus Design
Corporation model SF50 airplanes.
1. Electronic Engine Control
The installation of the electronic
engine control system must comply
with the requirements of 14 CFR
23.1309(a) through (e) at Amendment
23–49. The intent of this requirement is
not to reevaluate the inherent hardware
reliability of the control itself, but rather
determine the effects, including
environmental effects addressed in 14
CFR 23.1309(e), on the airplane systems
and engine control system when
installing the control on the airplane.
When appropriate, engine certification
data may be used when showing
compliance with this requirement;
however, the effects of the installation
on this data must be addressed.
For these evaluations, the loss of
FADEC control will be analyzed
utilizing the threat levels associated
with a catastrophic failure.
Issued in Kansas City, Missouri, on April
12, 2010.
Steve Thompson,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2010–9027 Filed 4–19–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF COMMERCE
Bureau of Industry and Security
15 CFR Parts 772 and 774
[Docket No. 0912031426–0047–01]
RIN 0694–AE79
Revisions to the Export Administration
Regulations Based on the 2009 Missile
Technology Control Regime Plenary
Agreements
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AGENCY: Bureau of Industry and
Security, Commerce.
ACTION: Final rule.
SUMMARY: The Bureau of Industry and
Security (BIS) is amending the Export
Administration Regulations (EAR) to
reflect changes to the Missile
Technology Control Regime (MTCR)
Annex that were agreed to by MTCR
member countries at the November 2009
Plenary in Rio de Janeiro, Brazil. In
VerDate Nov<24>2008
13:39 Apr 19, 2010
Jkt 220001
addition, this rule corrects an error
published in a final rule on December
10, 2009 (74 FR 65662).
DATES: Effective Date: This rule is
effective: April 20, 2010. Although there
is no formal comment period, public
comments on this regulation are
welcome on a continuing basis.
ADDRESSES: You may submit comments,
identified by RIN 0694–AE79, by any of
the following methods:
E-mail: publiccomments@bis.doc.gov
Include ‘‘RIN 0694–AE79’’ in the subject
line of the message.
Fax: (202) 482–3355. Please alert the
Regulatory Policy Division, by calling
(202) 482–2440, if you are faxing
comments.
Mail or Hand Delivery/Courier:
Timothy Mooney, U.S. Department of
Commerce, Bureau of Industry and
Security, Regulatory Policy Division,
14th St. & Pennsylvania Avenue, NW.,
Room 2705, Washington, DC 20230,
Attn: RIN 0694–AE79.
Send comments regarding the
collection of information associated
with this rule, including suggestions for
reducing the burden, to Jasmeet Seehra,
Office of Management and Budget
(OMB), by e-mail to
Jasmeet_K._Seehra@omb.eop.gov, or by
fax to (202) 395–7285; and to the U.S.
Department of Commerce, Bureau of
Industry and Security, Regulatory Policy
Division, 14th St. & Pennsylvania
Avenue, NW., Room 2705, Washington,
DC 20230. Comments on this collection
of information should be submitted
separately from comments on the final
rule (i.e. RIN 0694–AE79)—all
comments on the latter should be
submitted by one of the three methods
outlined above.
FOR FURTHER INFORMATION CONTACT:
Dennis L. Krepp, Nuclear and Missile
Technology Controls Division, Bureau
of Industry and Security, Telephone:
(202) 482–1309.
SUPPLEMENTARY INFORMATION:
Background
The Missile Technology Control
Regime (MTCR) is an export control
arrangement among 34 nations,
including most of the world’s advanced
suppliers of ballistic missiles and
missile-related materials and
equipment. The regime establishes a
common export control policy based on
a list of controlled items (the Annex)
and on guidelines (the Guidelines) that
member countries implement in
accordance with their national export
controls. The goal of maintaining the
Annex and the Guidelines is to stem the
flow into the global marketplace of
PO 00000
Frm 00008
Fmt 4700
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missile systems capable of delivering
weapons of mass destruction.
While the MTCR was originally
created to prevent the spread of missiles
capable of carrying a nuclear warhead,
it was expanded in January 1992 to also
address threats associated with delivery
systems for chemical and biological
weapons. MTCR members voluntarily
pledge to adopt the regime’s export
Guidelines and to restrict the export of
items contained in the regime’s Annex.
The implementation of the regime’s
Guidelines is effectuated through the
national export control laws and
policies of the regime members.
Amendments to the Export
Administration Regulations
This final rule revises the Export
Administration Regulations (EAR) to
reflect changes to the MTCR Annex
agreed to at the November 2009 Plenary
in Rio de Janeiro, Brazil. Corresponding
MTCR Annex references are provided
below for the MTCR Annex changes
agreed to at the November 2009 Plenary.
MTCR member countries agreed to
clarify the meaning of ‘‘production
facilities’’, the export of which is
prohibited by the MTCR Guidelines for
Category I. This clarification is reflected
in the changes set forth in section 772.1
(Definitions of Terms as Used in the
Export Administration Regulations),
which amend the definition of the term
‘‘production facilities’’ to add the word
production before the word equipment.
The definition will therefore state that
‘‘production facilities’’ means
‘‘production equipment’’ and specially
designed ‘‘software’’ therefor integrated
into installations for ‘‘development’’ or
for one or more phases of ‘‘production’’
(MTCR Annex Change Definitions:
‘‘Production Facilities’’). This
clarification more specifically describes
the type of equipment that is included
under the definition of ‘‘production
facilities’’. BIS expects this change to
have no impact on license applications.
In addition, this rule amends the
Commerce Control List (CCL)
(Supplement No. 1 to Part 774 of the
EAR) to reflect changes to the MTCR
Annex. Specifically, the following
Export Control Classification Numbers
(ECCNs) are affected:
ECCN 1C117 is amended by revising
the heading and the ‘‘items’’ paragraph
in the List of Items Controlled section
(MTCR Annex Change Category II: Item
6.C.7). A significant agreement was
reached by MTCR member countries on
the control of tungsten and
molybdenum on the MTCR Annex. New
controls were added for copper
infiltrated tungsten, silver infiltrated
tungsten, and tungsten alloys in solid
E:\FR\FM\20APR1.SGM
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]]>Agencies
[Federal Register Volume 75, Number 75 (Tuesday, April 20, 2010)]
[Rules and Regulations]
[Pages 20518-20520]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-9027]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Docket No. CE306; Special Conditions No. 23-246-SC]
Special Conditions: Cirrus Design Corporation Model SF50
Airplane; Full Authority Digital Engine Control (FADEC) System
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final special conditions; request for comments.
-----------------------------------------------------------------------
SUMMARY: These special conditions are issued for the Cirrus Design
Corporation model SF50 airplane. This airplane will have a novel or
unusual design feature(s) associated with the use of an electronic
engine control system instead of a traditional mechanical control
system. The applicable airworthiness regulations do not contain
adequate or appropriate safety standards for this design feature. These
special conditions contain the additional safety standards that the
Administrator considers necessary to establish a level of safety
equivalent to that established by the existing airworthiness standards.
DATES: The effective date of these special conditions is April 12,
2010.
We must receive your comments by May 20, 2010.
ADDRESSES: Mail two copies of your comments to: Federal Aviation
Administration, Regional Counsel, ACE-7, Attn: Rules Docket No. CE306,
901 Locust, Kansas City, MO 64106. You may deliver two copies to the
Regional Counsel at the above address. Mark your comments: Docket No.
CE306. You may inspect comments in the Rules Docket weekdays, except
Federal holidays, between 7:30 a.m. and 4 p.m.
FOR FURTHER INFORMATION CONTACT: Peter L. Rouse, Federal Aviation
Administration, Aircraft Certification Service, Small Airplane
Directorate, ACE-111, 901 Locust, Room 301, Kansas City, Missouri
64106; 816-329-4135, fax 816-329-4090.
SUPPLEMENTARY INFORMATION: The FAA has determined that notice and
opportunity for prior public comment hereon are impracticable because
these procedures would significantly delay issuance of the design
approval and thus delivery of the affected aircraft. In addition, the
substance of these special conditions has been subject to the public
comment process in several prior instances with no substantive comments
[[Page 20519]]
received. The FAA therefore finds that good cause exists for making
these special conditions effective upon issuance.
Comments Invited
Interested persons are invited to submit such written data, views,
or arguments as they may desire. Communications should identify the
regulatory docket or special condition number and be submitted in
duplicate to the address specified above. All communications received
on or before the closing date for comments will be considered by the
Administrator. The special conditions may be changed in light of the
comments received.
All comments received will be available in the Rules Docket for
examination by interested persons, both before and after the closing
date for comments. A report summarizing each substantive public contact
with FAA personnel concerning this rulemaking will be filed in the
docket.
Commenters' wishing the FAA to acknowledge receipt of their
comments submitted in response to this notice must include a self-
addressed, stamped postcard on which the following statement is made:
``Comments to Docket No. CE306.'' The postcard will be date stamped and
returned to the commenter.
Background
On September 9, 2008, Cirrus Design Corporation applied for a type
certificate for their new model SF50. The Cirrus Design Corporation
model SF50 is a low-wing, five-plus-two-place (2 children), single-
engine turbofan-powered aircraft. It incorporates an Electronic Flight
Information System (EFIS), pressurized cabin, retractable gear, and a
V-tail. The turbofan engine is mounted on the upper fuselage/tail cone
along the aircraft centerline. It is constructed largely of carbon and
fiberglass composite materials. Like other Cirrus products, the SF50
includes a ballistically deployed airframe parachute.
The model SF50 has a maximum operating altitude of 28,000 feet,
where it cruises at speeds up to 300 KTAS. Its VMO will not
exceed 0.62 Mach. The maximum takeoff weight will be at or below 6000
lbs with a range at economy cruise of roughly 1000 nm. Cirrus intends
for the model SF50 to be certified for single-pilot operations under 14
CFR part 91 and 14 CFR part 135 operating rules. The following
operating conditions will be included:
Day and Night VFR.
IFR.
Flight Into Known Icing.
The Cirrus Design Corporation model SF50 airplane is equipped with
a Williams International FJ33-5A turbofan engine using an electronic
engine control system (FADEC) instead of a traditional mechanical
control system. Even though the engine control system will be
certificated as part of the engine, the installation of an engine with
an electronic control system requires evaluation due to critical
environmental effects and possible effects on or by other airplane
systems, for example, indirect effects of lightning, radio interference
with other airplane electronic systems, shared engine and airplane data
and power sources.
The regulatory requirements in 14 CFR part 23 for evaluating the
installation of complex systems, including electronic systems and
critical environmental effects, are contained in Sec. 23.1309.
However, when Sec. 23.1309 was developed, the use of electronic
control systems for engines was not envisioned. Therefore, the Sec.
23.1309 requirements were not applicable to systems certificated as
part of the engine (reference Sec. 23.1309(f)(1)). Parts of the system
that are not certificated with the engine could be evaluated using the
criteria of Sec. 23.1309. However, the integral nature of these
systems makes it unfeasible to evaluate the airplane portion of the
system without including the engine portion of the system.
In some cases, the airplane that the engine is used in will
determine a higher classification than the engine controls are
certificated for, requiring the FADEC systems be analyzed at a higher
classification. As of November 2005, FADEC special conditions mandated
the classification for 23.1309 analysis for loss of FADEC control as
catastrophic for any airplane. This is not to imply an engine failure
is classified as catastrophic, but that the digital engine control must
provide an equivalent reliability to mechanical engine controls.
Type Certification Basis
Under the provisions of 14 CFR part 21, Sec. 21.17, Cirrus Design
Corporation must show that the model SF50 meets the applicable
provisions of part 23, as amended by Amendments 23-1 through 23-59,
thereto.
If the Administrator finds that the applicable airworthiness
regulations (i.e., part 23) do not contain adequate or appropriate
safety standards for the model SF50 because of a novel or unusual
design feature, special conditions are prescribed under the provisions
of Sec. 21.16.
In addition to the applicable airworthiness regulations and special
conditions, the model SF50 must comply with the fuel vent and exhaust
emission requirements of 14 CFR part 34 and the noise certification
requirements of 14 CFR part 36. Also, the FAA must issue a finding of
regulatory adequacy pursuant to Sec. 611 of Public Law 92-574, the
``Noise Control Act of 1972.''
Special conditions, as appropriate, as defined in 11.19, are issued
in accordance with Sec. 11.38, and become part of the type
certification basis in accordance with Sec. 21.17(a)(2).
Special conditions are initially applicable to the model for which
they are issued. Should the type certificate for that model be amended
later to include any other model that incorporates the same novel or
unusual design feature, the special conditions would also apply to the
other model under the provisions of Sec. 21.101(a)(1).
Novel or Unusual Design Features
The Cirrus Design Corporation model SF50 will incorporate the
following novel or unusual design features:
Electronic engine control system.
Applicability
As discussed above, these special conditions are applicable to the
model SF50. Should Cirrus Design Corporation apply at a later date for
a change to the type certificate to include another model incorporating
the same novel or unusual design feature, the special conditions would
apply to that model as well as under the provisions of Sec.
21.101(a)(1).
Conclusion
This action affects only certain novel or unusual design features
on the model SF50 airplanes. It is not a rule of general applicability
and it affects only the applicant who applied to the FAA for approval
of these features on the airplane.
Under standard practice, the effective date of final special
conditions would be 30 days after the date of publication in the
Federal Register; however, as the certification date for the Cirrus
Design Corporation model SF50 is imminent, the FAA finds that good
cause exists to make these special conditions effective upon issuance.
List of Subjects in 14 CFR Part 23
Aircraft, Aviation safety, Signs and symbols.
Citation
0
The authority citation for these special conditions is as follows:
[[Page 20520]]
Authority: 49 U.S.C. 106(g), 40113 and 44701; 14 CFR 21.16 and
21.17; and 14 CFR 11.38 and 11.19.
The Special Conditions
Accordingly, pursuant to the authority delegated to me by the
Administrator, the following special conditions are issued as part of
the type certification basis for Cirrus Design Corporation model SF50
airplanes.
1. Electronic Engine Control
The installation of the electronic engine control system must
comply with the requirements of 14 CFR 23.1309(a) through (e) at
Amendment 23-49. The intent of this requirement is not to reevaluate
the inherent hardware reliability of the control itself, but rather
determine the effects, including environmental effects addressed in 14
CFR 23.1309(e), on the airplane systems and engine control system when
installing the control on the airplane. When appropriate, engine
certification data may be used when showing compliance with this
requirement; however, the effects of the installation on this data must
be addressed.
For these evaluations, the loss of FADEC control will be analyzed
utilizing the threat levels associated with a catastrophic failure.
Issued in Kansas City, Missouri, on April 12, 2010.
Steve Thompson,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-9027 Filed 4-19-10; 8:45 am]
BILLING CODE 4910-13-P
