Special Conditions; Cessna Aircraft Company Model 510 Airplane; Turbofan Engines and Engine Location, 36040-36042 [06-5636]

Agencies

• Federal Aviation Administration
• DEPARTMENT OF TRANSPORTATION

[Federal Register Volume 71, Number 121 (Friday, June 23, 2006)]
[Proposed Rules]
[Pages 36040-36042]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-5636]


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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