[Federal Register: June 23, 2006 (Volume 71, Number 121)]
[Proposed Rules]
[Page 36040-36042]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr23jn06-15]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Docket No. CE253, Notice No. 23-06-05-SC]
Special Conditions; Cessna Aircraft Company Model 510 Airplane;
Turbofan Engines and Engine Location
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed special conditions.
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SUMMARY: This notice proposes special conditions for the Cessna
Aircraft Company, Model 510 airplane. This new airplane will have novel
and unusual design features not typically associated with normal,
utility, acrobatic, and commuter category airplanes. These design
features include turbofan engines and engine location, for which the
applicable regulations do not contain adequate or appropriate
airworthiness standards. These proposed special conditions contain the
additional airworthiness standards that the Administrator considers
necessary to establish a level of safety equivalent to that established
by the existing airworthiness standards.
DATES: Comments must be received on or before July 24, 2006.
ADDRESSES: Comments on this proposal may be mailed in duplicate to:
Federal Aviation Administration, Regional Counsel, ACE-7, Attention:
Rules Docket Clerk, Docket No. CE253, Room 506, 901 Locust, Kansas
City, Missouri 64106. All comments must be marked: Docket No. CE253.
Comments may be inspected in the Rules Docket weekdays, except Federal
holidays, between 7:30 a.m. and 4 p.m.
FOR FURTHER INFORMATION CONTACT: Peter L. Rouse, Aerospace Engineer,
Standards Office (ACE-110), Small Airplane Directorate, Aircraft
Certification Service, Federal Aviation Administration, Room 301, 901
Locust
[[Page 36041]]
Street, Kansas City, Missouri 64106; telephone (816) 329-4135.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of
these special conditions by submitting such written data, views, or
arguments as they may desire. Communications should identify the
regulatory docket or notice number and be submitted in duplicate to the
address specified above. All communications received on or before the
closing date for comments will be considered by the Administrator. The
proposals described in this notice may be changed in light of the
comments received. All comments received will be available in the Rules
Docket for examination by interested persons, both before and after the
closing date for comments. A report summarizing each substantive public
contact with FAA personnel concerning this rulemaking will be filed in
the docket. Persons wishing the FAA to acknowledge receipt of their
comments submitted in response to this notice must include with those
comments a self-addressed stamped postcard on which the following
statement is made: ``Comments to Docket No. CE253.'' The postcard will
be date stamped and returned to the commenter.
Background
On January 28, 2004, Cessna Aircraft Company; One Cessna Boulevard;
Post Office Box 7704; Wichita, KS 67277, made an application to the FAA
for a new Type Certificate for the Cessna Model 510 Mustang. If
approved, the Cessna 510 would be approved under TC No. A24CE. The
Cessna Model 510 Mustang is an all new, high performance, low wing, aft
fuselage mounted twin turbofan engine powered aircraft in the Normal
Category including flight into known icing conditions and single pilot
operations. The Model 510 is to use existing Cessna Citation
construction materials and methods. The design criteria includes: 8,480
pounds maximum ramp weight, 8,395 pounds maximum takeoff weight, 250
KCAS/0.63 Mach VMO/MMO, and a 41,000 foot maximum altitude.
Type Certification Basis
Under the provisions of 14 CFR, part 21, Sec. 21.17, Cessna
Aircraft Company must show that the Cessna Model 510 Mustang meets the
applicable provisions of 14 CFR, part 23, effective February 1, 1965,
as amended by Amendments 23-1 through Amendment 23-54, effective
September 14, 2000; 14 CFR, part 36, effective December 1, 1969,
through the amendment effective on the date of type certification; 14
CFR, part 34; exemptions, if any; and the special conditions adopted by
this rulemaking action.
Discussion
Special conditions, as appropriate, as defined in Sec. 11.19, are
issued in accordance with Sec. 11.38, and become part of the type
certification basis in accordance with Sec. 21.17.
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 the provisions of Sec. 21.101.
Novel or Unusual Design Features
The Cessna Model 510 Mustang will incorporate the following novel
or unusual design features:
Engine Fire Extinguishing System
The Model 510 design includes engines mounted aft on the fuselage;
therefore, early visual detection of engine fires is precluded. The
applicable existing regulations do not require fire extinguishing
systems for engines. Aft mounted engine installations were not
envisaged in the development of part 23; therefore, special conditions
for a fire extinguishing system with the applicable agents, containers,
and materials for the engines of the Model 510 are appropriate.
Applicability
As discussed above, these special conditions are applicable to the
Cessna Model 510. Should Cessna Aircraft Company 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 under the provisions of
Sec. 21.101.
Conclusion
This action affects only certain novel or unusual design features
on one model of airplane. It is not a rule of general applicability,
and it affects only the applicant who applied to the FAA for approval
of these features on the airplane identified.
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 Proposed Special Conditions
Accordingly, the Federal Aviation Administration (FAA) proposes the
following special conditions as part of the type certification basis
for the Cessna Model 510 airplane:
SC23.1195 Engine Fire Extinguishing System
(a) Fire extinguishing systems must be installed and compliance
must be shown with the following:
(1) Except for combustor, turbine, and tailpipe sections of
turbine-engine installations that contain lines or components carrying
flammable fluids or gases for which a fire originating in these
sections is shown to be controllable, a fire extinguisher system must
serve each engine compartment.
(2) The fire extinguishing system, the quantity of the
extinguishing agent, the rate of discharge, and the discharge
distribution must be adequate to extinguish fires. An individual ``one
shot'' system may be used.
(3) The fire extinguishing system for a nacelle must be able to
simultaneously protect each compartment of the nacelle for which
protection is provided.
(b) Fire extinguishing agents must meet the following requirements:
(1) Be capable of extinguishing flames emanating from any burning
fluids or other combustible materials in the area protected by the fire
extinguishing system; and
(2) Have thermal stability over the temperature range likely to be
experienced in the compartment in which they are stored.
(3) If any toxic extinguishing agent is used, provisions must be
made to prevent harmful concentrations of fluid or fluid vapors (from
leakage during normal operation of the airplane or as a result of
discharging the fire extinguisher on the ground or in flight) from
entering any personnel compartment, even though a defect may exist in
the extinguishing system. This must be shown by test except for built-
in carbon dioxide fuselage compartment fire extinguishing systems for
which:
(i) Five pounds or less of carbon dioxide will be discharged, under
established fire control procedures, into any fuselage compartment; or
(ii) Protective breathing equipment is available for each flight
crewmember on flight deck duty.
[[Page 36042]]
(c) Fire extinguishing agent containers must meet the following
requirements:
(1) Each extinguishing agent container must have a pressure relief
to prevent bursting of the container by excessive internal pressures.
(2) The discharge end of each discharge line from a pressure relief
connection must be located so that discharge of the fire extinguishing
agent would not damage the airplane. The line must also be located or
protected to prevent clogging caused by ice or other foreign matter.
(3) A means must be provided for each fire extinguishing agent
container to indicate that the container has discharged or that the
charging pressure is below the established minimum necessary for proper
functioning.
(4) The temperature of each container must be maintained, under
intended operating conditions, to prevent the pressure in the container
from falling below that necessary to provide an adequate rate of
discharge, or rising high enough to cause premature discharge.
(5) If a pyrotechnic capsule is used to discharge the extinguishing
agent, each container must be installed so that temperature conditions
will not cause hazardous deterioration of the pyrotechnic capsule.
(d) Fire extinguisher system materials must meet the following
requirements:
(1) No material in any fire extinguishing system may react
chemically with any extinguishing agent so as to create a hazard.
(2) Each system component in an engine compartment must be
fireproof.
Issued in Kansas City, Missouri on June 16, 2006.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-5636 Filed 6-22-06; 8:45 am]
BILLING CODE 4910-13-P