(2)
For oil systems for turbine engine installations in which all components of the oil system, including oil tanks, are .reproof or located in areas not subjecttoengine .reconditions; or]
(3)
For engine oilsystemsin categoryB rotorcraft using reciprocating engines of less than 500 cubic inches displacement.
(b)
The closing of any fuel shuto. valve for any engine may not make fuel unavai-lable to the remaining engines.
(c)
ForcategoryA rotorcraft,nohazardousquantity of .ammable .uid maydrain into any designated .re zone after shuto. has been accomplished, nor may the closing of any fuel shuto. valve for an engine make fuel unavailable to the remaining engines.
(d)
The operation of any shuto. may not interfere with the later emergency ope-ration of any other equipment, such as the means for declutching the engine from the rotor drive.
(e)
[Eachshuto. valve and its control must be designed, located, andprotected to functionproperly underany conditionlikely toresultfrom .reinadesignated .re zone.
(f)
Except for ground-use-only auxiliary power unit installations, there must be means topreventinadvertent operation of each shuto. and to makeitpossible to reopen it in .ight after it has been closed.]
Amdt. 29-26, E.. 10/3/88
FAR 29.1191 : Firewalls.
(a)
[Each engine, including the combustor, turbine, and tailpipe sections of tur-bine engine installations, must be isolated by a .rewall, shroud, or equivalent means, frompersonnel compartments, structures, controls, rotor mechanisms, and other parts that are–]
(1)
Essential to controlled .ight and landing; and
(2)
Not protected under Sec. 29.861.
(b)
Each auxiliary power unit, combustion heater, and other combustion equip-ment to be used in .ight, must be isolated from the rest of the rotorcraft by .rewalls, shrouds, or equivalent means.
(c)
Each .rewall orshroud mustbeconstructed sothatnohazardousquantity of air, .uid, or .ame can pass from any engine compartment to other parts of the rotorcraft.
(d)
Each opening in the .rewall or shroud must be sealed with close-.tting .re-proof grommets, bushings, or .rewall .ttings.
(e)
Each .rewall and shroud mustbe .reproof andprotected againstcorrosion.
(f)
In meeting this section, account must be taken of the probable path of a .re
as a.ected by the air.ow in normal .ight and in autorotation. Amdt. 29-3, E.. 2/25/68
FAR 29.1193 : Cowling and engine compartment covering.
(a)
Each cowling and engine compartment covering must be constructed and sup-ported so that it can resist the vibration, inertia, and air loads to which it may be subjected in operation.
(b)
Cowling must meet the drainage and ventilation requirements of Sec. 29.1187.
(c)
On rotorcraft with a diaphragm isolating the engine power section from the engine accessory section, eachpartof the accessory sectioncowling subjectto .ame in case of .re in the engine power section of the powerplant must–
(1)
Be .reproof; and
(2)
Meet the requirements of Sec. 29.1191.
(d)
Each part of the cowling or engine compartment covering subject to high temperatures due to its nearness to exhaust system parts or exhaust gas im-pingement must be .reproof.
(e)
Each rotorcraft 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)
Meetthe requirements of subparagraph(1) ofthisparagraphwiththe landinggear retracted(if applicable); and
(3)
Have .reproof skin in areas subject to .ame if a .re starts in or burns out of any designated .re zone.
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本文链接地址：FAA规章 美国联邦航空规章 Federal Aviation Regulations 5(83)
