(5)
[Notmorethanonequartof .ammable .uidmay escapeintotheenginecom-partment after engine shuto.. For those installations where the .ammable .uid that escapes after shutdown cannot be limited to one quart, it must be demonstrated that this greater amount can be safely contained or drained overboard.]

(6)
There must be means to guard against inadvertent operations of each shuto. means, and to make it possible for the crew to reopen the shuto. means in .ight after it has been closed.

(b)
Turbine engine installations need not have an engine oil system shuto. if–

(1)
The oil tankisintegral with, or mounted on,the engine; and

(2)
All oil system components external to the engine are .reproof or located in areas not subject to engine .re conditions.

(c) Poweroperated valvesmusthavemeanstoindicatetothe .ight crewwhenthevalve has reached the selected position and must be designed so that the valve will not move from the selected position under vibration conditions likely to exist at the valve location.
Amdt. 23-43, E.. 05/10/93
FAR 23.1191 : Firewalls.
(a)
Each engine, auxiliarypowerunit,fuelburning heater,and othercombustionequip-ment must be isolated from the rest of the airplane by .rewalls, shrouds, or equi-valent means.

(b)
[Each.rewallorshroud mustbeconstructed sothat nohazardousquantity ofliquid, gas, or .ame can pass from the compartment created by the .rewall or shroud to other parts of the airplane.]

(c)
Each opening in the .rewall or shroud must be sealed with close .tting, .reproof grommets, bushings, or .rewall .ttings.

(d)
Removed and Reserved.

(e)
Each .rewall and shroud must be .reproof and protected against corrosion.

(f)
Compliance with the criteria for .reproof materials or components must be shown as follows :

(1)
The .ame to which the materials or components are subjected must be 2,000 ±150'F.

(2)
Sheet materialsapproximately10inchessquaremustbesubjected tothe .ame from a suitable burner.

(3)
The .ame must be large enough to maintain the required test temperature over an area approximately .ve inches square.

(g)
Firewall materialsand .ttingsmustresist .amepenetrationforatleast15 minutes.

(h)
The following materials may be used in .rewalls or shrouds without being tested as required by this section :

(1)
Stainless steel sheet, 0.015 inch thick.

(2)
Mild steel sheet(coated with aluminium or otherwiseprotected against corro-sion) 0.018 inch thick.

(3)
Terne plate, 0.018 inch thick.

(4)
Monel metal, 0.018 inch thick.

(5)
Steel or copper base alloy .rewall .ttings.

(6)
Titanium sheet, 0.016 inch thick. Amdt. 23-51, E.. 03/11/96

FAR23.1192 :[Engine accessory compartmentdiaphragm.]
[For aircooledradial engines, the enginepower section and allportions of the exhaust system must be isolated from the engine accessory compartment by a diaphragm that meets the .rewall requirements of Sec. 23.1191.] Amdt. 23-14, E.. 12/20/73
′
Elodie Roux. Septembre 2003
Subpart E : Powerplant
FAR 23.1193 : Cowling and nacelle.
(a)
Each cowling must be constructed and supported so that it can resist any vibration, inertia, and air loads to which it may be subjected in operation.

(b)
[There must be means for rapidand complete drainage of each part of the cowling in the normal ground and .ight attitudes. Drain operation may be shown by test, analysis, or both, to ensure that under normal aerodynamic pressure distribution expected in service each drain will operate as designed. No drain may discharge where it will cause a .re hazard.]

(c)
Cowling must be at least .re resistant.

(d)
Each part behind an opening in the engine compartment cowling must be at least .re resistant for a distance of at least 24 inches aft of the opening.
　
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本文鏈接地址：FAA規(guī)章 美國(guó)聯(lián)邦航空規(guī)章 Federal Aviation Regulations 2(76)