[Federal Register Volume 75, Number 159 (Wednesday, August 18, 2010)]
[Rules and Regulations]
[Pages 50853-50854]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-20416]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Docket No. CE308; Special Conditions No. 23-248-SC]
Special Conditions: Cirrus Design Corporation Model SF50
Airplane; Function and Reliability Testing
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final special conditions.
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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 complex design and performance
features consistent with larger airplanes. 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: Effective Date: September 17, 2010.
FOR FURTHER INFORMATION CONTACT: J. Lowell Foster, Federal Aviation
Administration, Small Airplane Directorate, Aircraft Certification
Service, 901 Locust, Room 301, Kansas City, MO 64106; telephone (816)
329-4125; facsimile (816) 329-4090.
SUPPLEMENTARY INFORMATION:
Background
On September 9, 2008, Cirrus Design Corporation applied for a type
certificate for their new model SF50 ``Vision'' Jet. The 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 Knots True Air Speed (KTAS). Its
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 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.
Discussion
Before Amendment 3-4, Section 3.19 of Civil Air Regulation (CAR)
part 3 required service testing of all airplanes type certificated on
or after May 15, 1947. The purpose of the testing was to ``ascertain
whether there is reasonable assurance that the airplane, its
components, and equipment are reliable, and function properly.''
Amendment 3-4 to CAR part 3 became effective January 15, 1951, and
deleted the service test requirements in Section 3.19 for airplanes of
6,000 pounds maximum weight or less. The introductory text published in
Amendment 3-4 explained that most of the significant changes in the
amendment stemmed from ``the desire for simplification of the rules in
this part with respect to the smaller airplanes, specifically those of
6,000 pounds maximum weight or less, which would be expected to be used
mainly as personal airplanes.'' The introductory material also stated
the service test requirement was removed for airplanes of 6,000 pounds
maximum weight or less because ``experience seems to indicate that this
rule imposes a burden upon the manufacturers not commensurate with the
safety gained.'' The requirement for Function and Reliability (F&R)
testing, and the exception for airplanes of 6,000 pounds or less
maximum weight, is now found in 14 CFR part 21, section 21.35(b)(2).
The decision to exempt airplanes of 6,000 pounds maximum weight or
less from F&R testing was based on the state of technology envisioned
in 1951. At that time, airplanes of 6,000 pounds maximum weight or less
were expected to be used mainly as personal airplanes. They used
simple, ``stand-alone'' systems whose failure was more likely to be an
inconvenience than an accident. The situation is different today.
Technological advances allow airplanes weighing less than 6,000 pounds
to be more complex and integrated than some transport airplanes. New
part 23 airplanes can incorporate sophisticated equipment not
previously used in a part 23 aircraft. Additionally, part 23 airplanes
are being used for business and commercial transportation. They should
no longer be envisioned mainly as personal airplanes. Therefore, a
special condition
[[Page 50854]]
to require F&R testing for airplanes weighing 6,000 pounds or less is
needed where the level of sophistication is beyond evaluating failures
by inspection.
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 23-59 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 section 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 under Sec. 21.101.
Novel or Unusual Design Features
The SF50 will incorporate the following novel or unusual design
features: Complex design and performance features consistent with
technologically advanced aircraft over 6,000 pounds.
Discussion of Comments
Notice of proposed special conditions No. 23-10-02-SC for the
Cirrus Design Corporation model SF50 airplanes was published in the
Federal Register on May 28, 2010, 75 FR 29962. No comments were
received, and the special conditions are adopted as proposed.
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 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.
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 model SF50
airplanes.
1. Function and Reliability Testing.
Flight tests: In place of 14 CFR 21.35(b)(2), the following
applies:
(b) Upon showing compliance with Sec. 21.35, paragraph (a), the
applicant must make all flight tests that the Administrator finds
necessary--
(2) For aircraft to be certificated under this subchapter to
determine whether there is reasonable assurance that the aircraft, its
components, and its equipment are reliable and function properly.
Additionally the provisions of Sec. 21.35, paragraphs (c) and (f)
then apply:
(c) Each applicant must, if practicable, make the tests described
in paragraph (b)(2) of this section upon the aircraft that was used to
show compliance with--
(1) Paragraph (b)(1) of this section; and
(2) ----.
(f) The flight tests prescribed in paragraph (b)(2) of this section
must include--
(1) For aircraft incorporating turbine engines of a type not
previously used in a type certificated aircraft, at least 300 hours of
operation with a full complement of engines that conform to a type
certificate; and
(2) For all other aircraft, at least 150 hours of operation.
Issued in Kansas City, Missouri, on August 9, 2010.
John R. Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-20416 Filed 8-17-10; 8:45 am]
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