Special Conditions: Cirrus Design Corporation Model SF50 Airplane; Function and Reliability Testing, 50853-50854 [2010-20416]

Agencies

• Federal Aviation Administration
• DEPARTMENT OF TRANSPORTATION

[Federal Register Volume 75, Number 159 (Wednesday, August 18, 2010)]
[Rules and Regulations]
[Pages 50853-50854]
From the Federal Register Online via the Government Printing 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]
BILLING CODE 4910-13-P