(b)
Eachduct connected to componentsbetween which relative motion could exist must have means for .exibility.

(c)
[Each .exible induction system duct must be capable ofwithstanding the e.ects of temperature extremes, fuel, oil, water, and solvents to which it is expected to be exposed in service and maintenance without hazardous deterioration or delamina-tion.

(d)
For reciprocating engine installations, each induction system duct must be–

(1)
Strongenoughtopreventinduction systemfailures resultingfrom normalback-.re conditions; and

(2)
Fire resistant in any compartment for which a .re extinguishing system is required.

(e)
Eachinlet systemductfor an auxiliarypower unit mustbe–

(1)
Fireproof withinthe auxiliarypower unit compartment;

(2)
Fireproof for a su.cient distance upstream of the auxiliary power unit com-partment to prevent hot gas reverse .ow from burning through the duct and entering any other compartment of the airplane in which a hazard would be created by the entry of the hot gases;

(3)
Constructed of materials suitable to the environmental conditions expected in service, except in those areas requiring .reproof or .re resistant materials; and

(4)
Constructed of materials that will not absorb or trap hazardous quantities of .ammable .uids that could be ignited by a surge or reverse-.ow condition.

(f)
Induction system ducts that supply air to a cabin pressurization system must be suitably constructed of material that will notproducehazardousquantities of toxic gases or isolated to prevent hazardous quantities of toxic gases from entering the cabin during a powerplant .re.]

Amdt. 23-43, E.. 05/10/93
FAR 23.1105 : Induction system screens.
If induction system screens are used–
(a)
[Eachscreen must be upstream of the carburetor or fuel injection system.]

(b)
No screen may be in any part of the induction system that is the only passage through which air can reach the engine, unless–

(1)
The availablepreheatis atleast100'F.; and

(2)
The screen can be deiced by heated air;

(c)
No screen may be deiced by alcohol alone; and

(d)
It must be impossible for fuel to strike any screen. Amdt. 23-51, E.. 03/11/96

′
Elodie Roux. Septembre 2003
Subpart E : Powerplant
FAR 23.1107 : Induction system .lters.
[Ifan air .lter is used to protect the engine against foreign material particles in the induction air supply–]
(a)
Each air .lter must be capable of withstanding the e.ects of temperature extremes, rain, fuel, oil, and solvents to which it is expected to be exposed in service and maintenance; and

(b)
Each air .lter shall have a design feature to prevent material separated from the

.lter media from interfering with proper fuel metering operation. Amdt. 23-51, E.. 03/11/96
FAR23.1109 :[Turbochargerbleed air system.]
[The followingapplies to turbo-charged bleed air systems used for cabin pressuriza-tion :
(a)
The cabin air system may not be subject to hazardous contamination following any probable failure of the turbocharger or its lubrication system.

(b)
The turbocharger supply air must be taken from a source where it cannot be conta-minatedby harmful orhazardousgases or vaporsfollowing anyprobablefailure or malfunction of the engine exhaust, hydraulic, fuel, or oil system.]

Amdt. 23-42, E.. 02/04/91
FAR 23.1111 : Turbine engine bleed air system.
For turbine engine bleed air systems, the following apply :
(a)
No hazard may result if duct rupture or failure occurs anywhere between the engine port and the airplane unit served by the bleed air.

(b)
The e.ect on airplaneand engineperformanceof using maximumbleed airmustbe established.
　
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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(71)