(i)
Restarting any engine of a multiengine airplane in .ight, and

(ii)
Stopping any engine in .ight, after engine failure, if continued engine rotation would cause a hazard to the airplane.

(2)
In addition, for commuter category airplanes, the following apply :

(i)
Each component of the stopping system on the engine side of the .rewall that might be exposed to .re must be at least .re resistant.

(ii)
If hydraulic propeller feathering systems are used for this purpose, the feathering lines must be at least .re resistant under the operating condi-tions that may be expected to exist during feathering.

(e)
Starting and stopping (turbine engine). Turbine engine installations must comply with the following :

(1)
The design of the installation must be such that risk of .re or mechanical damage to the engine or the airplane, as a result of starting the engine in any conditionsin which startingis to bepermitted, is reduced to a minimum. Any techniques and associated limitations must be established and included in the Airplane Flight Manual, approved manual material, or applicable operating placards.

(2)
There must be means for stopping combustion within any engine and for stop-ping the rotation of any engine if continued rotation would cause a hazard to the airplane. Each component of the engine stopping system located in any .re zone must be .re resistant. If hydraulic propeller feathering systems are used for stopping the engine, the hydraulic feathering lines or hoses must be .re resistant.

′
Elodie Roux. Septembre 2003
Subpart E : Powerplant
(3)
Itmustbepossibletorestart anenginein .ight.Anytechniquesand associated limitations must be established and included in the Airplane Flight Manual, approved manual material, or applicable operating placards.

(4)
It mustbedemonstratedin .ightthat whenrestarting enginesfollowing afalse start, all fuel or vapor is discharged in such a way that it does not constitute a .re hazard.

(f)
Restart envelope. An altitude and airspeed envelope must be established for the airplaneforin.ightengine restarting and eachinstalled engine musthavearestart capability within that envelope.

(g)
Restart capability. For turbine enginepowered airplanes,ifthe minimum windmilling speed of the engines, following the in.ight shutdown of all engines, is insu.cient to provide the necessary electrical power for engine ignition, a power source inde-pendent of the engine-driven electrical power generating system must be provided to permit in.ight engine ignition for restarting.

Amdt. 23-54, E.. 12/13/2000
FAR23.904 :[Automaticpower reserve system.]
[Ifinstalled, an automaticpower reserve(APR)systemthat automatically advances the power or thrust on the operating engine(s), when any engine fails during takeo., must comply with appendix H of this part.] Amdt. 23-43, E.. 05/10/93
FAR 23.905 : Propellers.
(a)
Each propeller must have a type certi.cate.

(b)
Engine power and propeller shaft rotational speed may not exceed the limits for which the propeller is certi.cated.

(c)
Each featherable propeller must have a means to unfeather it in .ight.

(d)
Each component of thepropellerbladepitch control system must meetthe require-ments of Sec. 35.42 of this chapter.

(e)
[Allareas ofthe airplaneforward ofthepusherpropellerthat arelikelyto accumulate and shediceinto thepropellerdiscduring any operating condition mustbe suitably protected to prevent ice formation, or it must be shown that any ice shed into the propeller disc will not create a hazardous condition.

(f)
Eachpusherpropeller mustbe marked sothatthediscis conspicuous under normal daylightground conditions.

(g)
If the engine exhaust gases are discharged into the pusher propeller disc, it must be shown by tests, or analysis supported by tests, that the propeller is capable of continuous safe operation.
　
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本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 2(53)