[Federal Register Volume 78, Number 116 (Monday, June 17, 2013)]
[Rules and Regulations]
From the Federal Register Online via the Government Publishing 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50853 is withdrawn, effective June 17, 2013.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.
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
Flight Into Known Icing
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
Reason for Withdrawal
The FAA is withdrawing Special Condition No. 23-248-SC because
Cirrus elected to revise the model SF50 certification basis to
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.
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.
Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2013-14327 Filed 6-14-13; 8:45 am]
BILLING CODE 4910-13-P