(1)
[Lines, .ttings, andcomponents forming an integral part of an engine; and

(2)
Oil systems for turbine engine installations in which all components of the systeminadesignated.rezone,includingtheoiltanks, are .reproof orlocated in areas not subject to engine .re conditions.]

(b)
The closing of any fuel shuto. valve for any engine may not make fuel unavailable to the remaining engines.

(c)
Operation of any shuto. may not interfere with the later emergency operation of other equipment, such as the means for feathering the propeller.

(d)
Each.ammable .uid shuto.meansand control mustbe .reproof ormustbelocated and protected so that any .re in a .re zone will not a.ect its operation.

(e)
No hazardous quantity of .ammable .uid may drain into any designated .re zone after shuto..

(f)
There must be means to guard against inadvertent operation of the shuto. means and to make it possible for the crew to reopen the shuto. means in .ight after it has been closed.

(g)
Each tank-to-engine shuto. valve must be located so that the operation of the valve will not be a.ected by powerplant or engine mount structural failure.

(h)
Each shuto. valve must have a means to relieve excessive pressure accumulation unless a meansforpressure reliefis otherwiseprovidedinthe system.

Amdt. 25-57, E.. 3/26/84
FAR 25.1191 : Firewalls.
(a)
Each engine, auxiliarypower unit, fuel-burning heater, other combustion equipment intended for operation in .ight, and the combustion, turbine, and tailpipe sections of turbine engines, must be isolated from the rest of the airplane by .rewalls, shrouds, or equivalent means.

(b)
Each .rewall and shroud must be–

(1)
Fireproof;

(2)
Constructed sothatnohazardousquantity of air,.uid,or .amecanpassfrom the compartment to other parts of the airplane;

(3)
Constructed so that each opening is sealed with close .tting .reproof grom-mets,bushings,or .rewall .ttings; and

(4)
Protected against corrosion.

FAR25.1192 :[Engine accessory sectiondiaphragm.]
[For reciprocatingengines, the engine power section and all portions of the exhaust system must be isolated from the engine accessory compartment by a diaphragm that complies with the .rewall requirements of Sec. 25.1191.] Amdt. 25-23, E.. 5/8/70
FAR 25.1193 : Cowling and nacelle skin.
(a)
Each cowling must be constructed and supported so that it can resist any vibration, inertia, and air load to which it may be subjected in operation.

(b)
Cowling must meet the drainage and ventilation requirements of Sec. 25.1187.

(c)
On airplanes with a diaphragm isolating the engine power section from the engine accessory section, each part of the accessory section cowling subject to .ame in case of .re in the engine power section of the powerplant must–

(1)
Be .reproof; and

(2)
Meet the requirements of Sec. 25.1191.

(d)
Eachpart of the cowling subject tohigh temperaturesdue toits nearness to exhaust system parts or exhaust gas impingement must be .reproof.

′
Elodie Roux. Septembre 2003
Subpart E : Powerplant
(e) Each airplane must–
(1)
Be designed and constructed so that no .re originating in any .re zone can enter, either through openings or by burning through external skin, any other zone or region where it would create additional hazards;

(2)
Meet subparagraph(1) ofthisparagraph withthelandinggearretracted(if applicable); and

(3)
Have.reproof skininareassubjectto .ameif a .restartsintheenginepower or accessory sections.

FAR 25.1195 : Fire extinguishing systems.
(a)
Except for combustor, turbine, and tail pipe sections of turbine engine installations that contain lines or components carrying .ammable .uids or gases for which it is shown that a .re originating in these sections can be controlled, there must be a .re extinguisher system serving each designated .re zone.
　
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本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 4(11)