80 FR 57289 - Special Conditions: Cirrus Design Corporation, SF50; Full Authority Digital Engine Control (FADEC) System

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 80, Issue 184 (September 23, 2015)

Page Range		57289-57291
FR Document		2015-24156

These special conditions are issued for the Cirrus Design Corporation 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.

Federal Register, Volume 80 Issue 184 (Wednesday, September 23, 2015)

[Federal Register Volume 80, Number 184 (Wednesday, September 23, 2015)]
[Rules and Regulations]
[Pages 57289-57291]
From the Federal Register Online [www.thefederalregister.org]
[FR Doc No: 2015-24156]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 23

[Docket No. FAA-2015-3881; Special Conditions No. 23-267-SC]

Special Conditions: Cirrus Design Corporation, SF50; Full
Authority Digital Engine Control (FADEC) System

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final special conditions; request for comments.

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SUMMARY: These special conditions are issued for the Cirrus Design
Corporation 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 September 23,
2015.
We must receive your comments by October 23, 2015.

ADDRESSES: Send comments identified by docket number FAA-2015-3881
using any of the following methods:
Federal eRegulations Portal: Go to http://www.regulations.gov and follow the online instructions for sending your
comments electronically.
Mail: Send comments to Docket Operations, M-30, U.S.
Department of Transportation (DOT), 1200 New Jersey Avenue SE., Room
W12-140, West Building Ground Floor, Washington, DC, 20590-0001.
Hand Delivery of Courier: Take comments to Docket
Operations 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 Docket Operations at 202-493-2251.
Privacy: The FAA will post all comments it receives, without
change, to http://regulations.gov, including any personal information
the commenter provides. Using the search function of the docket Web
site, anyone can find and read the electronic form of all comments
received into any FAA docket, including the name of the individual
sending the comment (or signing the comment for an association,
business, labor union, etc.). DOT's complete Privacy Act Statement can
be found in the Federal Register published on April 11, 2000 (65 FR
19477-19478), as well as at http://DocketsInfo.dot.gov.
Docket: Background documents or comments received may be read at
http://www.regulations.gov at any time. Follow the online instructions
for accessing the docket or go to the Docket Operations 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: Jeff Pretz, Federal Aviation
Administration, Small Airplane Directorate, ACE-111, 901 Locust, Room
301, Kansas City, MO 64106; telephone (816) 329-3239; facsimile (816)
329-4090.

SUPPLEMENTARY INFORMATION: The FAA has determined, in accordance with 5
U.S.C. 553(b)(3)(B) and 553(d)(3), that notice and opportunity for
prior public comment hereon are unnecessary because the substance of
these special conditions has been subject to the public comment process
in several prior instances with no substantive comments received. The
FAA therefore finds that good cause exists for making these special
conditions effective upon issuance.

------------------------------------------------------------------------
Special condition number Company/airplane model
------------------------------------------------------------------------
23-237-SC Spectrum Aeronautical Model S-40.
23-246-SC Cirrus Design Corporation Model
SF50.
23-253-SC Diamond Aircraft Industries Model
DA-40NG.
------------------------------------------------------------------------

Comments Invited

We invite interested people to take part in this rulemaking by
sending written comments, data, or views. The most helpful comments
reference a specific portion of the special conditions, explain the
reason for any recommended change, and include supporting data. We ask
that you send us two copies of written comments.
We will consider all comments we receive on or before the closing
date for comments. We will consider comments filed late if it is
possible to do so without incurring expense or delay. We may change
these special conditions based on the comments we receive.

Background

On September 9, 2008, Cirrus Design Corporation applied for a type
certificate for their new Model SF50. On December 11, 2012, Cirrus
Design Corporation requested to revise the SF50 part 23 certification
basis to include amendment 23-62. The Cirrus Design Corporation SF50 is
a low-wing, seven-seat, single-engine turbofan-powered airplane. 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 an
airframe ballistic parachute system.
The model SF50 has a maximum operating altitude of 28,000 feet,
where it cruises at speeds up to 300 knots true airspeed. Its maximum
operating limit speed (VMO) will not exceed 0.62 Mach. The
maximum takeoff weight will be at or below 6,000 pounds with a range at
economy cruise of roughly 1,000 nautical miles. Cirrus intends for the
SF50 to be certified for single-pilot operations under 14 CFR parts 91
and 135 operating rules. The following operating conditions will be
included:

Day and Night VFR
IFR
Flight Into Known Icing

The Cirrus Design Corporation SF50 airplane is equipped with a
Williams International FJ33-5A turbofan engine, which uses an
Electronic Engine Control

[[Page 57290]]

System (EEC, also commonly referred to as a 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 part 23 for evaluating the
installation of complex systems, including electronic systems and
critical environmental effects, are contained in Sec. Sec. 23.1306,
Electrical and electronic system lightning protection; 23.1308, High-
intensity Radiated Fields (HIRF) Protection; and 23.1309, Equipment,
systems, and installations. However, when Sec. 23.1309 was developed,
the use of electronic control systems for engines was not envisioned.
The integral nature of these systems makes it necessary to ensure the
airplane functions included in the EEC are properly evaluated and that
the installation does not degrade the EEC reliability, both of which
are approved under part 33. Sections 23.1306(a) and 23.1308(a) are
applied to the EEC to ensure it remains equivalent to a mechanical
system, which is not generally susceptible to the HIRF and lightning
environments.
In some cases, the airplane, which the engine is being installed
in, will determine a higher classification than the engine controls are
certificated for, requiring the EEC systems be analyzed at a higher
classification. As of November 2005, EEC special conditions mandated
the Sec. 23.1309 classification for loss of EEC control as
catastrophic for any airplane. This is not to imply an engine failure
is classified as catastrophic, but that the EEC must provide an
equivalent reliability to mechanical engine controls. In addition,
Sec. Sec. 23.1141, Powerplant controls: General, paragraph (e) and
25.901, Powerplant--General--Installation, paragraph (b)(2), are
applied to provide the fault tolerant design requirements of turbine
engine mechanical controls to the EEC and ensure adequate inspection
and maintenance interval of the EEC.

Type Certification Basis

Under the provisions of 14 CFR 21.17, Cirrus Design Corporation
must show that the SF50 meets the applicable provisions of part 23, as
amended by amendments 23-1 through 23-62 thereto.
If the Administrator finds that the applicable airworthiness
regulations (i.e., 14 CFR part 23) do not contain adequate or
appropriate safety standards for the 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 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 and the FAA must issue a finding of
regulatory adequacy under Sec. 611 of Public Law 92-574, the ``Noise
Control Act of 1972.''.
The FAA issues special conditions, as defined in Sec. 11.19, under
Sec. 11.38 and they become part of the type certification basis under
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.

Novel or Unusual Design Features

The SF50 will incorporate the following novel or unusual design
features:
Electronic engine control system

Discussion

As discussed in the summary section, the SF50 makes use of an
electronic engine control system instead of a traditional mechanical
control system, which is considered a novel design for this type of
airplane. The applicable airworthiness regulations do not contain
adequate or appropriate safety standards for this design feature.
Mandating a structured assessment to determine potential installation
issues mitigates the concerns that the addition of an electronic engine
control may produce failure conditions not previously considered.

Applicability

As discussed above, these special conditions are applicable to the
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.

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 affects only the applicant who applied to the FAA for approval of
these features on the airplane.
The substance of these special conditions has previously been
subjected to the notice and comment period as identified above, and has
been derived without substantive change from those previously issued.
It is unlikely that prior public comment would result in a significant
change from the substance contained herein. Therefore, notice and
opportunity for prior public comment hereon are unnecessary and the FAA
finds good cause, in accordance with 5 U.S.C. 553(b)(3)(B) and
553(d)(3), making these special conditions effective upon issuance. The
FAA is requesting comments to allow interested persons to submit views
that may not have been submitted in response to the prior opportunities
for comment described above.

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:

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 SF50
airplane.

1. Full Authority Digital Engine Control (FADEC) System

a. For electronic engine control system installations, it must be
established that no single failure or malfunction or probable
combinations of failures of Electronic Engine Control System (EEC)
system components will have an effect on the system, as installed in
the airplane, that causes the LOTC probability of the system to exceed
those allowed in part 33 certification.
b. Electronic engine control system installations must be evaluated
for environmental and atmospheric conditions, including lightning. The
EEC system lightning and HIRF effects that could result in LOTC must be
evaluated in accordance with Sec. Sec. 23.1306(a) and 23.1308(a).
c. The components of the installation must be constructed,
arranged, and installed to ensure their continued safe

[[Page 57291]]

operation between normal inspections or overhauls.
d. Functions incorporated into any electronic engine control that
make it part of any equipment, systems, or installation whose functions
are beyond that of basic engine control, and which may also introduce
system failures and malfunctions, are not exempt from Sec. 23.1309 and
must be shown to meet part 23 levels of safety as derived from Sec.
23.1309. Part 33 certification data, if applicable, may be used to show
compliance with any part 23 requirements. If part 33 data is used to
substantiate compliance with part 23 requirements, then the applicant
must be able to provide this data for showing or compliance.

Issued in Kansas City, Missouri on September 14, 2015.
Mel Johnson,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-24156 Filed 9-22-15; 8:45 am]
BILLING CODE 4910-13-P

57290 Federal Register / Vol. 80, No. 184 / Wednesday, September 23, 2015 / Rules and Regulations

System (EEC, also commonly referred to If the Administrator finds that the applicant who applied to the FAA for
as a FADEC) instead of a traditional applicable airworthiness regulations approval of these features on the
mechanical control system. Even though (i.e., 14 CFR part 23) do not contain airplane.
the engine control system will be adequate or appropriate safety standards The substance of these special
certificated as part of the engine, the for the SF50 because of a novel or conditions has previously been
installation of an engine with an unusual design feature, special subjected to the notice and comment
electronic control system requires conditions are prescribed under the period as identified above, and has been
evaluation due to critical environmental provisions of § 21.16. derived without substantive change
effects and possible effects on or by In addition to the applicable from those previously issued. It is
other airplane systems. For example, airworthiness regulations and special unlikely that prior public comment
indirect effects of lightning, radio conditions, the SF50 must comply with would result in a significant change
interference with other airplane the fuel vent and exhaust emission from the substance contained herein.
electronic systems, shared engine and requirements of 14 CFR part 34 and the Therefore, notice and opportunity for
airplane data and power sources. noise certification requirements of 14 prior public comment hereon are
The regulatory requirements in part CFR part 36 and the FAA must issue a unnecessary and the FAA finds good
23 for evaluating the installation of finding of regulatory adequacy under cause, in accordance with 5 U.S.C.
complex systems, including electronic § 611 of Public Law 92–574, the ‘‘Noise 553(b)(3)(B) and 553(d)(3), making these
systems and critical environmental Control Act of 1972.’’. special conditions effective upon
effects, are contained in §§ 23.1306, The FAA issues special conditions, as issuance. The FAA is requesting
Electrical and electronic system defined in § 11.19, under § 11.38 and comments to allow interested persons to
lightning protection; 23.1308, High- they become part of the type submit views that may not have been
intensity Radiated Fields (HIRF) certification basis under § 21.17(a)(2). submitted in response to the prior
Protection; and 23.1309, Equipment, Special conditions are initially opportunities for comment described
systems, and installations. However, applicable to the model for which they above.
when § 23.1309 was developed, the use are issued. Should the type certificate
for that model be amended later to List of Subjects in 14 CFR Part 23
of electronic control systems for engines
was not envisioned. The integral nature include any other model that Aircraft, Aviation safety, Signs and
of these systems makes it necessary to incorporates the same novel or unusual symbols.
ensure the airplane functions included design feature, the special conditions
would also apply to the other model. Citation
in the EEC are properly evaluated and
that the installation does not degrade Novel or Unusual Design Features The authority citation for these
the EEC reliability, both of which are special conditions is as follows:
approved under part 33. Sections The SF50 will incorporate the
following novel or unusual design Authority: 49 U.S.C. 106(g), 40113 and
23.1306(a) and 23.1308(a) are applied to 44701; 14 CFR 21.16 and 21.17; and 14 CFR
the EEC to ensure it remains equivalent features: 11.38 and 11.19.
to a mechanical system, which is not Electronic engine control system
The Special Conditions
generally susceptible to the HIRF and Discussion
lightning environments. As discussed in the summary section, Accordingly, pursuant to the
In some cases, the airplane, which the the SF50 makes use of an electronic authority delegated to me by the
engine is being installed in, will engine control system instead of a Administrator, the following special
determine a higher classification than traditional mechanical control system, conditions are issued as part of the type
the engine controls are certificated for, which is considered a novel design for certification basis for Cirrus Design
requiring the EEC systems be analyzed this type of airplane. The applicable Corporation SF50 airplane.
at a higher classification. As of airworthiness regulations do not contain 1. Full Authority Digital Engine Control
November 2005, EEC special conditions adequate or appropriate safety standards (FADEC) System
mandated the § 23.1309 classification for this design feature. Mandating a
for loss of EEC control as catastrophic structured assessment to determine a. For electronic engine control
for any airplane. This is not to imply an potential installation issues mitigates system installations, it must be
engine failure is classified as the concerns that the addition of an established that no single failure or
catastrophic, but that the EEC must electronic engine control may produce malfunction or probable combinations
provide an equivalent reliability to failure conditions not previously of failures of Electronic Engine Control
mechanical engine controls. In addition, considered. System (EEC) system components will
§§ 23.1141, Powerplant controls: have an effect on the system, as
General, paragraph (e) and 25.901, Applicability installed in the airplane, that causes the
Powerplant—General—Installation, As discussed above, these special LOTC probability of the system to
paragraph (b)(2), are applied to provide conditions are applicable to the SF50. exceed those allowed in part 33
the fault tolerant design requirements of Should Cirrus Design Corporation apply certification.
turbine engine mechanical controls to at a later date for a change to the type b. Electronic engine control system
the EEC and ensure adequate inspection certificate to include another model installations must be evaluated for
and maintenance interval of the EEC. incorporating the same novel or unusual environmental and atmospheric
design feature, the special conditions conditions, including lightning. The
Type Certification Basis
mstockstill on DSK4VPTVN1PROD with RULES

would apply to that model as well. EEC system lightning and HIRF effects
Under the provisions of 14 CFR 21.17, that could result in LOTC must be
Cirrus Design Corporation must show Conclusion evaluated in accordance with
that the SF50 meets the applicable This action affects only certain novel §§ 23.1306(a) and 23.1308(a).
provisions of part 23, as amended by or unusual design features on the model c. The components of the installation
amendments 23–1 through 23–62 SF50 airplanes. It is not a rule of general must be constructed, arranged, and
thereto. applicability and affects only the installed to ensure their continued safe

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Federal Register / Vol. 80, No. 184 / Wednesday, September 23, 2015 / Rules and Regulations 57291

operation between normal inspections SUPPLEMENTARY INFORMATION: section 611 of Public Law 92–574, the
or overhauls. ‘‘Noise Control Act of 1972.’’
d. Functions incorporated into any Background
The FAA issues special conditions, as
electronic engine control that make it On October 11, 2006, Honda Aircraft defined in 14 CFR 11.19, in accordance
part of any equipment, systems, or Company applied for a type certificate with § 11.38, and they become part of
installation whose functions are beyond for their new Model HA–420. On the type-certification basis under
that of basic engine control, and which October 10, 2013, Honda Aircraft § 21.17(a)(2).
may also introduce system failures and Company requested an extension with Special conditions are initially
malfunctions, are not exempt from an effective application date of October applicable to the model for which they
§ 23.1309 and must be shown to meet 1, 2013. This extension changed the are issued. Should the type certificate
part 23 levels of safety as derived from type certification basis to amendment for that model be amended later to
§ 23.1309. Part 33 certification data, if 23–62. include any other model that
applicable, may be used to show The HA–420 is a four to five incorporates the same or similar novel
compliance with any part 23 passenger (depending on configuration), or unusual design feature, the special
requirements. If part 33 data is used to two crew, lightweight business jet with conditions would also apply to the other
substantiate compliance with part 23 a 43,000-foot service ceiling and a model under § 21.101.
requirements, then the applicant must maximum takeoff weight of 9963
be able to provide this data for showing pounds. The airplane is powered by two Novel or Unusual Design Features
or compliance. GE-Honda Aero Engines (GHAE) HF– The HA–420 will incorporate the
Issued in Kansas City, Missouri on 120 turbofan engines. following novel or unusual design
September 14, 2015. The current regulatory requirements feature: The installation of Li-ion
Mel Johnson, for part 23 airplanes do not contain batteries.
Acting Manager, Small Airplane Directorate, adequate requirements for the The current regulatory requirements
Aircraft Certification Service. application of Li-ion batteries in for part 23 airplanes do not contain
[FR Doc. 2015–24156 Filed 9–22–15; 8:45 am] airborne applications. This type of adequate requirements for the
BILLING CODE 4910–13–P battery possesses certain failure, application of Li-ion batteries in
operational characteristics, and airborne applications. This type of
maintenance requirements that differ battery possesses certain failure,
DEPARTMENT OF TRANSPORTATION significantly from that of the nickel operational characteristics, and
cadmium and lead acid rechargeable maintenance requirements that differ
Federal Aviation Administration batteries currently approved in other significantly from that of the nickel
normal, utility, acrobatic, and commuter cadmium and lead acid rechargeable
14 CFR Part 23 category airplanes. Therefore, the FAA batteries currently approved in other
[Docket No.FAA–2015–0721; Notice No. 23– is proposing this special condition to normal, utility, acrobatic, and commuter
269–SC] require that (1) all characteristics of the category airplanes.
rechargeable lithium batteries and their
Special Conditions: Honda Aircraft installation that could affect safe Discussion
Company, Model HA–420 HondaJet, operation of the HA–420 are addressed, The applicable parts 21 and 23
Lithium-ion Batteries and (2) appropriate Instructions for airworthiness regulations governing the
AGENCY: Federal Aviation Continued Airworthiness which include installation of batteries in general
Administration (FAA), DOT. maintenance requirements are aviation airplanes, including § 23.1353,
ACTION: Final special conditions. established to ensure the availability of were derived from Civil Air Regulations
electrical power from the batteries when (CAR 3) as part of the recodification that
SUMMARY: These special conditions are needed. established 14 CFR part 23. The battery
issued for the Honda Aircraft Company, requirements, which are identified in
Model HA–420 airplane. This airplane Type Certification Basis
§ 23.1353, were a rewording of the CAR
will have a novel or unusual design Under the provisions of 14 CFR 21.17, requirements that did not add any
feature associated with the installation Honda Aircraft Company must show substantive technical requirements. An
of lithium-ion (Li-ion) batteries. The that the HA–420 meets the applicable increase in incidents involving battery
applicable airworthiness regulations do provisions of part 23, as amended by fires and failures that accompanied the
not contain adequate or appropriate Amendments 23–1 through 23–62 increased use of Nickel-Cadmium (Ni-
safety standards for this design feature. thereto. Cad) batteries in aircraft resulted in
These special conditions contain the If the Administrator finds that the rulemaking activities on the battery
additional safety standards that the applicable airworthiness regulations requirements for transport category
Administrator considers necessary to (i.e., 14 CFR part 23) do not contain airplanes. These regulations were
establish a level of safety equivalent to adequate or appropriate safety standards incorporated into § 23.1353(f) and (g),
that established by the existing for the HA–420 because of a novel or which apply only to Ni-Cad battery
airworthiness standards. unusual design feature, special installations.
DATES: These special conditions are conditions are prescribed under the The use of Li-ion batteries on the HA–
effective September 23, 2015. provisions of § 21.16. 420 airplane has prompted the FAA to
FOR FURTHER INFORMATION CONTACT: Les In addition to the applicable review the adequacy of the existing
mstockstill on DSK4VPTVN1PROD with RULES

Lyne, Policies & Procedures Branch, airworthiness regulations and special battery regulations with respect to that
ACE–114, Federal Aviation conditions, the HA–420 must comply chemistry. As the result of this review,
Administration, Small Airplane with the fuel vent and exhaust emission the FAA has determined that the
Directorate, Aircraft Certification requirements of 14 CFR part 34 and the existing regulations do not adequately
Service, 901 Locust; Kansas City, noise certification requirements of 14 address several failure, operational, and
Missouri 64106; telephone (816) 329– CFR part 36, and the FAA must issue a maintenance characteristics of Li-ion
4171; facsimile (816) 329–4090. finding of regulatory adequacy under batteries that could affect safety of the

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Document Created: 2015-12-15 09:44:32
Document Modified: 2015-12-15 09:44:32

Category		Regulatory Information
Collection		Federal Register
sudoc Class		AE 2.7: GS 4.107: AE 2.106:
Publisher		Office of the Federal Register, National Archives and Records Administration
Section		Rules and Regulations
Action		Final special conditions; request for comments.
Dates		The effective date of these special conditions is September 23, 2015.
Contact		Jeff Pretz, Federal Aviation Administration, Small Airplane Directorate, ACE-111, 901 Locust, Room 301, Kansas City, MO 64106; telephone (816) 329-3239; facsimile (816) 329-4090.
FR Citation		80 FR 57289
CFR Associated		Aircraft; Aviation Safety and Signs and Symbols

80 FR 57289 - Special Conditions: Cirrus Design Corporation, SF50; Full Authority Digital Engine Control (FADEC) System

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 80, Issue 184 (September 23, 2015)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration