(c)
The fuel tank installation must include either–

(1)
Meanstominimizethedevelopmentof .ammablevaporsinthefuel tanks(in the context of this rule, ”minimize” means to incorporate practicable design methods to reduce the likelihood of .ammable vapors); or

(2)
Means to mitigate the e.ects of an ignition of fuel vapors within fuel tanks such that no damage caused by an ignition will prevent continued safe .ight and landing.]

Amdt. 25-102, E.. 6/6/2001
48.3 Fuel System Components
FAR 25.991 : Fuel pumps.
(a)
Main pumps. Each fuel pump required for proper engine operation, or required to meetthefuel system requirements ofthis subpart(otherthan thoseinparagraph (b)ofthis section),is a mainpump.For each mainpump,provision mustbe madeto allow thebypass of eachpositivedisplacementfuelpump other than afuelinjection pump(apump thatsuppliestheproper .owandpressureforfuelinjectionwhen the injection is not accomplished in a carburetor) approved as part of the engine.

(b)
Emergency pumps.There mustbe emergencypumps or another mainpump tofeed each engineimmediately afterfailure of any mainpump(other than afuelinjection pump approved as part of the engine).

FAR 25.993 : 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)
Flexible hose must be approved or 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 shut-down.

(f)
[Each fuel line within the fuselage must be designedand installed to allow a reaso-nable degree of deformation and stretching without leakage.]

Amdt. 25-15, E.. 10/24/67
FAR 25.994 : Fuel system components.
[Fuel system components in an engine nacelle or in the fuselage must be protected from damage which could result in spillage of enough fuel to constitute a .re hazard as a result of a wheels-up landing on a paved runway.] Amdt. 25-57, E.. 3/26/84
FAR 25.995 : Fuel valves.
In addition to the requirements of Sec. 25.1189 for shuto. means, each fuel valve must–
(a)
[[Reserved.]]

(b)
Be supported so that no loads resulting from their operation or from accelerated .ight conditions are transmitted to the lines attached to the valve.

Amdt. 25-40, E.. 5/2/77
′
Elodie Roux. Septembre 2003
Subpart E : Powerplant
FAR 25.997 : Fuel strainer or .lter.
There must be a fuel strainer or .lter between the fuel tank outlet and the inlet of either thefuel meteringdevice or an enginedrivenpositivedisplacementpump, whichever is nearer the fuel tank outlet. This fuel strainer or .lter must–
(a)
Be accessible for draining and cleaning and must incorporate a screen or element which is easily removable;

(b)
Have a sediment trap and drain except that it need not have a drain if the strainer or .lter is easily removable for drain purposes;

(c)
[Be mounted so that its weight is not supported by the connecting lines or by the inlet or outlet connections of the strainer or .lter itself, unless adequate strength margins under allloading conditions areprovidedin the lines and connections; and

(d)
Havethe capacity(with respectto operating limitations establishedforthe engine) to ensure that engine fuel system functioning is not impaired, with the fuel conta-minated to adegree(with respecttoparticle size anddensity) thatisgreaterthan that established for the engine in Part 33 of this chapter.]
　
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本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 3(119)