(c)
The diameter of each strainer must be at least that of the fuel tank outlet.

(d)
[Eachstrainer must be accessible for inspection and cleaning.]

Amdt. 23-43, E.. 05/10/93
FAR 23.979 : Pressure fueling systems.
For pressure fueling systems, the following apply :
(a)
Each pressure fueling system fuel manifold connection must have means to prevent the escape of hazardous quantities of fuel from the system if the fuel entry valve fails.

(b)
[An automatic shuto. means mustbeprovidedtoprevent thequantityoffuelin each tank from exceeding the maximum quantity approved for that tank. This means must–

(1)
Allow checkingforproper shuto. operationbefore eachfueling ofthetank; and

(2)
For commuter category airplanes, indicate at each fueling station, a failure of theshuto.meanstostop thefuel .owatthemaximumquantity approvedfor that tank.]

(c)
A means must be provided to prevent damage to the fuel system in the event of failure of the automatic shuto. meansprescribedinparagraph(b) of this section.

(d)
All parts of the fuel system up to the tank which are subjected to fueling pressures must have a proof pressure of 1.33 times, and an ultimate pressure of at least 2.0 times,the surgepressurelikely to occurduring fueling.

Amdt. 23-51, E.. 03/11/96
32.3 Fuel System Components
FAR 23.991 : Fuel pumps.
(a) Main pumps. For main pumps, the following apply :
(1)
For reciprocating engine installations having fuel pumps to supply fuel to the engine, atleast onepumpfor each engine mustbedirectlydrivenbythe engine and must meet Sec. 23.955. This pump is a main pump.

(2)
For turbine engineinstallations, eachfuelpumprequiredforproper engine ope-ration, or required to meet thefuel system requirements of this subpart(other thanthoseinparagraph(b) of this section),is a mainpump.In addition–

(i)
There must be at least one main pump for each turbine engine :

(ii)
Thepower supplyforthe mainpumpfor eachengine mustbeindependent of the power supply for each main pump for any other engine; and

(iii) For each main pump, provision must be made to allow the bypass of each positive displacement fuel pump other than a fuel injection pump approved as part of the engine.
(b)
Emergency pumps. There must be an emergency pump immediately available to supply fuel to the engine if any main pump (other than a fuel injection pump approved as part of the engine) fails. The power supply for each emergency pump must be independent of the power supply for each corresponding main pump.

(c)
Warning means.Ifboth the[main]pump and emergencypump operate continuously, there must be a means to indicate to the appropriate .ight crewmembers a mal-function of either pump.

(d)
Operation ofanyfuelpump may not a.ect engine operation so as to create ahazard, regardless of the enginepower or thrust setting or thefunctional status of any other fuel pump.

Amdt. 23-43, E.. 05/10/93
FAR 23.993 : Fuel system lines and .ttings.
(a)
Eachfuelline mustbeinstalled and supported toprevent excessivevibrationand to withstand loads due to fuel pressure and accelerated .ight conditions.

(b)
Each fuel line connected to components of the airplane between which relative mo-tioncould existmusthaveprovisionsfor .exibility.

(c)
Each .exible connection in fuel lines that may be under pressure and subjected to axial loading must use .exible hose assemblies.

(d)
[Each .exible hose must be shown to be suitable for the particular application.]

(e)
No .exible hose that might be adversely a.ected by exposure to high temperatures may be used where excessive temperatures will exist during operation or after engine shutdown.

Amdt. 23-43, E.. 05/10/93
　
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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(62)