(e)
Each part of the cowling subjected to high temperatures due to its nearness to exhaust system ports or exhaust gas impingement, must be .reproof.

(f)
Each nacelle of a multiengine airplane with supercharged engines must be designed and constructed so that with the landing gear retracted, a .re in the engine com-partment will not burn through a cowling or nacelle and enter a nacelle area other than the engine compartment.

(g)
In addition, for commuter category airplanes, the airplane must be designed so that no .re originating in any engine compartment can enter, either through openings or by burnthrough, any other region where it would create additional hazards.

Amdt. 23-43, E.. 5/10/93
FAR 23.1195 : Fire extinguishing systems.
(a)
[For commuter categoryairplanes, .re extinguishing systems must be installed and compliance shown with the following :

(1)
Except for combustor, turbine, and tailpipe sections of turbine-engine instal-lations that contain lines or components carrying .ammable .uids or gases for which a .re originating in these sections is shown to be controllable, a .re extinguisher system must serve each engine compartment;

(2)
The .reextinguishing system,thequantity of theextinguishing agent,therate of discharge, and the discharge distribution must be adequate to extinguish .res. An individual ”one shot” system may be used.

(3)
The .re extinguishing system for a nacelle must be able to simultaneously protect each compartment of the nacelle for which protection is provided.

(b)
If an auxiliary power unit is installed in any airplane certi.cated to this part, that auxiliary power unit compartment must be served by a .re extinguishing system meeting the requirements ofparagraph(a)(2) of this section.]

Amdt. 23-43, E.. 05/10/93
FAR23.1197 :[Fire extinguishing agents.]
[For commuter categoryairplanes, the following applies :
(a) Fire extinguishing agents must–
(1) Becapableof extinguishing.amesemanatingfromanyburning.uidsorother combustiblematerialsintheareaprotectedby the .reextinguishing system; and
(2) Have thermal stability over the temperature range likely to be experienced in the compartment in which they are stored.
(b) If any toxic extinguishing agentis used,provisions mustbe made topreventharmful concentrationsof .uid or.uid vapors(fromleakageduring normal operationof the airplaneorasaresult ofdischargingthe .reextinguisherontheground orin .ight) from entering any personnel compartment, even though a defect may exist in the extinguishing system.This mustbe shownby test exceptforbuilt-in carbondioxide fuselage compartment .re extinguishing systems for which–
(1)
Fivepoundsorlessof carbondioxidewillbedischarged,underestablished .re control procedures, into any fuselage compartment; or

(2)
Protective breathing equipment is available for each .ight crewmember on .ight deck duty.]

Amdt. 23-34, E.. 02/17/87
FAR23.1199 :[Extinguishing agent containers.]
[For commuter extinguishingairplanes, the following applies :
(a)
Each extinguishing agent container must have a pressure relief to prevent bursting of the container by excessive internal pressures.

(b)
The discharge end of each discharge line from a pressure relief connection must be located so that discharge of the .re extinguishing agent would not damage the airplane.Theline must alsobelocated orprotected toprevent clogging causedby ice or other foreign matter.

(c)
Ameansmustbeprovidedforeach.reextinguishing agent containertoindicatethat the containerhasdischarged orthatthe chargingpressureisbelowthe established minimum necessary for proper functioning.

(d)
The temperature of each container must be maintained, under intended operating conditions, to prevent the pressure in the container from–
　
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本文鏈接地址：FAA規(guī)章 美國聯(lián)邦航空規(guī)章 Federal Aviation Regulations 2(77)