[Federal Register Volume 67, Number 187 (Thursday, September 26, 2002)]
[Rules and Regulations]
[Pages 60555-60556]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-24449]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 23

[Docket No. CE171; Special Conditions No. 23-128-SC


Special Conditions: Eclipse Aviation Corporation, Model 500; Fire 
Extinguishing System for Aft Mounted Engine Installations.

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final special conditions.

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SUMMARY: These special conditions are issued for the Eclipse Aviation 
Corporation, Model 500 airplane. This airplane will have a novel or 
unusual design feature(s) associated with aft mounted turbine engines. 
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.

EFFECTIVE DATE: October 28, 2002.

FOR FURTHER INFORMATION CONTACT: Lowell Foster, FAA, Aircraft 
Certification Service, Small Airplane Directorate, ACE-111, 901 Locust 
Street, Kansas City, Missouri 64106, 816-329-4111.

SUPPLEMENTARY INFORMATION:

Background

    On July 12, 2001, Eclipse Aviation Corporation applied for a type 
certificate for their new Model 500 airplane.
    The Model 500 design includes turbine engines mounted aft on the 
fuselage, which means early visual detection of engine fire is 
precluded. The applicable existing regulations do not require fire 
extinguishing systems for engines. Aft mounted turbine engine 
installations, along with the need to protect such installed engines 
from fires, were not envisioned in the development of part 23; 
therefore, a special condition regarding fire protection for the 
engines of the Model 500 is required.

Type Certification Basis

    Under the provisions of 14 CFR 21.17, Eclipse Aviation Corporation 
must show that the Eclipse Model 500 meets the following:
    (1) Applicable provisions of 14 CFR part 23, effective December 18, 
1964, as amended by Amendments 23-1 through 23-54 (September 14, 2000).
    (2) Part 34 of the Federal Aviation Regulations effective September 
10, 1990, plus any amendments in effect on the date of type 
certification.
    (3) Part 36 of the Federal Aviation Regulations effective December 
1, 1969, as amended by Amendment 36-1 through the amendment in effect 
on the date of type certification.
    (4) Noise Control Act of 1972.
    (5) Special conditions that are not relevant to these special 
conditions;
    (6) Exemptions, if any;
    (7) Equivalent level of safety findings, if any; and
    (8) Special conditions adopted by this rulemaking action.
    In addition to the applicable airworthiness regulations and special 
conditions, the Model 500 must comply with the part 23 fuel vent and 
exhaust emission requirements of 14 CFR part 36, and the FAA must issue 
a finding of regulatory adequacy pursuant to Sec.  611 of Public Law 
92-574, the ``Noise Control Act of 1972.''
    Special conditions, as appropriate, as defined in Sec.  11.19, are 
issued in accordance with Sec.  11.38 after public notice and become 
part of the type certifications basis in accordance with 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 the provisions of Sec.  21.101.

Novel or Unusual Design Features

    The Model 500 will incorporate the following novel or unusual 
design features:
    Turbine engines mounted on the aft of the fuselage. Aft mounted 
turbine engine installations need to be protected from fire since early 
visual detection of engine fires is not possible. This special 
condition covers a fire extinguishing system for the engines of the 
Model 500.

Discussion of Comments

    Notice of proposed special conditions No. 23-01-04-SC-A for the 
Eclipse Model 500 airplanes was published on January 29, 2002 (67 FR 
4215). On June 17, 2002, we published an amended notice of proposed 
special conditions (67 FR 46927). No comments were received, and the 
special conditions are adopted as proposed.

Applicability

    As discussed above, these special conditions are applicable to the 
Eclipse Model 500 airplane. The engine installation used in the Model 
500 does not utilize additional engine compartments other than those 
addressed in the special conditions. Should Eclipse Aviation 
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 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 Eclipse Model 500 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 the Eclipse Aviation Model 500 
airplane.

Engine Fire Extinguishing System

    (a) Fires originating in combustor, turbine, and tailpipe sections 
of the engine installation which contain lines or components carrying 
flammable fluids must either:
    (1) Be demonstrated at critical conditions to be controllable by 
test or a combination of test or analysis; or
    (2) a fire extinguishing system must serve each engine compartment.
    (b) If a fire extinguishing system is installed, the system must 
comply with the following requirements:
    (1) The system must serve each engine compartment;
    (2) The system, the quantity of the extinguishing agent, the rate 
of discharge, and the discharge

[[Page 60556]]

distribution must be adequate to extinguish fires. An individual ``one 
shot'' system may be used; and
    (3) For a nacelle, the system must be able to simultaneously 
protect each compartment of the nacelle for which protection is 
provided.
    (c) If a fire extinguishing system is installed, fire extinguishing 
agents must meet the following requirements:
    (1) Be capable of extinguishing flames emanating from any burning 
of fluids or other combustible materials in the area protected by the 
fire extinguishing system;
    (2) Have thermal stability over the temperature range likely to be 
experienced in the compartment in which they are stored; and
    (3) If any toxic extinguishing agent is used, provisions must be 
made to prevent harmful concentrations of fluid or vapors from entering 
any personnel compartment even though a defect may exist in the 
extinguishing system.
    (d) If fire extinguishing agents are used, the agent containers 
must meet the following requirements:
    (1) 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 the 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; and
    (5) If a pyrotechnic capsule is used to discharge the fire 
extinguishing agent, each container must be installed so that 
temperature conditions will not cause hazardous deterioration of the 
pyrotechnic capsule.
    (e) If a fire extinguishing system is installed, 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; and
    (2) Each system component in an engine compartment must be 
fireproof.

    Issued in Kansas City, Missouri on September 11, 2002.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 02-24449 Filed 9-25-02; 8:45 am]
BILLING CODE 4910-13-P