(2)
Atleast two vents arrangedto minimize theprobabilityofboth ventsbecoming obstructed simultaneously.

(3)
Filler caps designed to minimize the probability of incorrect installation or in.ight loss.

(4)
Afuel systemin which thoseparts of the systemfrom each tank outletto any engine areindependent of eachpartof the system supplying fuel to any other engine.

Amdt. 23-43, E.. 05/10/93
FAR23.954 :[Fuel systemlightningprotection.]
[Thefuelsystem mustbedesigned and arranged topreventtheignition offuel vapor within the system by–
(a)
Direct lightning strikes to area having a high probability of stroke attachment :

(b)
Swept lightning strokes on area where swept strokes are highly probable; and

(c)
Corona or streamering at fuel vent outlets.] Amdt. 23-7, E.. 09/14/69

FAR 23.955 : Fuel .ow.

(a)
General. The ability of the fuel system to provide fuel at the rates speci.ed in this section and at a pressure su.cient for proper engine operation must be shown in the attitudethatis most critical with respecttofuelfeed andquantity of unusable fuel. These conditions may be simulated in a suitable mockup. In addition–

(1)
[The quantity of fuel in the tank may not exceed the amount established as the unusablefuel supplyforthattank underSec.23.959(a)plusthatquantity necessary to show compliance with this section.

(2)
If there is a fuel .owmeter, it must be blocked during the .ow test and the fuel must .ow through the meter or its bypass.

(3)
If there is a .owmeter without a bypass, it must not have any probable fai-lure mode that would restrict fuel .ow below the level required for this fuel demonstration.

(4)
Thefuel .owmustincludethat .ownecessaryforvaporreturn .ow,jetpump drive .ow, and for all other purposes for which fuel is used.]

(b)
Gravity systems.Thefuel .owrateforgravity systems(mainandreservesupply) must be 150 percent of the takeo. fuel consumption of the engine.

′
Elodie Roux. Septembre 2003
Subpart E : Powerplant
(c)
Pump systems.Thefuel .owrateforeachpump system(mainand reservesupply) for each reciprocating engine must be 125 percent of the fuel .ow required by the engine at the maximum takeo. power approved under this part.

(1)
This .owrateisrequiredforeach mainpump and each emergencypump,and must be available when the pump is operating as it would during takeo..

(2)
For eachhand-operatedpump,this rate must occur atnot morethan60 com-plete cycles(120 single strokes)per minute.

(3)
Thefuelpressure,with main and emergencypumps operating simultaneously, must not exceed the fuel inlet pressure limits of the engine unless it can be shown that no adverse e.ect occurs.

(d)
Auxiliary fuel systems and fuel transfer systems.Paragraphs(b),(c), and(f) of this section apply to each auxiliary and transfer system, except that–

(1)
The required fuel .ow rate must be established upon the basis of maximum continuous power and engine rotational speed, instead of takeo. power and fuel consumption; and

(2)
If thereisaplacardproviding operatinginstructions,alesser .owratemaybe usedfor transferringfuelfrom any auxiliary tankinto alarger main tank.This lesser .ow rate must be adequate to maintain engine maximum continuous powerbutthe .owratemustnot over.llthemaintank atlowerenginepowers.

(e)
Multiple fuel tanks. For reciprocating engines that are supplied with fuel from more than one tank, if engine power loss becomes apparent due to fuel depletion from thetank selected,it mustbepossibleafterswitching toanyfull tank,inlevel .ight, toobtain75percentmaximumcontinuouspoweronthat enginein notmorethan–

(1)
10 seconds for naturally aspirated single-engine airplanes;

(2)
　
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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(57)