[Federal Register Volume 78, Number 116 (Monday, June 17, 2013)]
[Rules and Regulations]
[Page 36084]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-14327]


=======================================================================
-----------------------------------------------------------------------

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; Withdrawal

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final special conditions; withdrawal.

-----------------------------------------------------------------------

SUMMARY: The FAA is withdrawing a previously published notice granting 
special conditions for the Cirrus Design Corporation model SF50 
airplane. We are withdrawing Special Condition No. 23-248-SC through 
mutual agreement with Cirrus Design Corporation.

DATES: This special condition published on August 18, 2010 at 75 FR 
50853 is withdrawn, effective June 17, 2013.

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 August 18, 2010, the FAA published Special Condition No. 23-248-
SC for the Cirrus Design Corporation 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 
MMO will not exceed 0.62 Mach. The maximum takeoff weight 
will be at or below 6000 pounds 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

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 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.
    The model SF50 certification project was granted an extension on 
September 19, 2011. 14 CFR part 21, Amendment 95, published in the 
Federal Register (76 FR 64229) on October 18, 2011, incorporated 
Special Condition No. 23-248-SC. On December 11, 2012, Cirrus Design 
Corporation elected to adjust the model SF50 certification basis to 
Amendment 21-95.

Reason for Withdrawal

    The FAA is withdrawing Special Condition No. 23-248-SC because 
Cirrus elected to revise the model SF50 certification basis to 
Amendment 21-95.
    The authority citation for this Special Condition withdrawal is 49 
U.S.C. 106(g), 40113 and 44701; 14 CFR 21.16 and 21.17; and 14 CFR 
11.38 and 11.19.

Conclusion

    Withdrawal of this special condition does not preclude the FAA from 
issuing another notice on the subject matter in the future or 
committing the agency to any future course of action.

    Issued in Kansas City, Missouri on June 7, 2013.
Earl Lawrence,
Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2013-14327 Filed 6-14-13; 8:45 am]
BILLING CODE 4910-13-P