(3)
20 seconds for multiengine airplanes.

(f)
Turbine engine fuel systems. Each turbine engine fuel system must provide at least 100 percent of the fuel .ow required by the engine under each intended operation condition and maneuver. The conditions may be simulated in a suitable mockup. This .ow must–

(1)
Be shown with the airplane in the most adverse fuel feed condition (with respect to altitudes, attitudes, and other conditions) that is expected in ope-ration; and

(2)
For multiengine airplanes, notwithstanding the lower .ow rate allowed by pa-ragraph (d) of this section, be automatically uninterrupted with respect to any engine until all fuel scheduled for use by that engine has been consumed. In addition–

(i)
For the purposes of this section, ”fuel scheduled for use by that engine” means all fuel in any tank intended for use by a speci.c engine.

(ii)
The fuel system design must clearly indicate the engine for which fuel in any tank is scheduled.

(iii) Compliance with thisparagraph must require nopilot action after com-pletion of the engine starting phase of operations.
(3) For single-engine airplanes, require no pilot action after completion of the en-gine startingphase ofoperations unless means areprovided that unmistakenly alertthepilottotakeany needed actionatleast .veminutespriortothenee-ded action; suchpilot action must not cause any changein engine operation; and such pilot action must not distract pilot attention from essential .ight duties during any phase of operations for which the airplane is approved.
Amdt. 23-51, E.. 03/11/96
FAR 23.957 : Flow between interconnected tanks.
(a)
[It mustbeimpossible,in agravityfeedsystem with interconnected tank outlets,for enough fuel to .ow between the tanks to cause an over.ow of fuel from any tank vent under the conditions in Sec. 23.959, except that full tanks must be used.

(b)
Iffuel canbepumpedfromonetank toanotherin .ight,thefuel tank ventsand the fuel transfer system must be designed so that no structuraldamage to any airplane component can occur because of over.lling of any tank.]

Amdt. 23-43, E.. 05/10/93
FAR 23.959 : Unusable fuel supply.
(a)
[The unusable fuel supply for each tank must be established as not less than that quantityat whichthe .rst evidenceof malfunctioning occursunderthemost adverse fuel feed condition occurring under each intended operation and .ight maneuver involving that tank. Fuel system component failures need not be considered.

(b)
The e.ect on the usable fuel quantity as a result of a failure of any pump shall be determined.]

Amdt. 23-51, E.. 03/11/96
FAR 23.961 : Fuel system hot weather operation.
[Eachfuelsystem mustbefreefrom vaporlock when usingfuel atits critical tempera-ture, with respect to vaporformation, when operatingthe airplanein all critical operating and environmental conditionsfor which approvalis requested.For turbinefuel, theinitial
'''
temperature must be 110F, -0 , +5or the maximum outside air temperature for which
approval is requested, whichever is more critical.] Amdt. 23-43, E.. 05/10/93
FAR 23.963 : Fuel tanks : general.
(a)
Each fuel tank must be able to withstand, without failure, the vibration, inertia, .uid, and structural loads that it may be subjected to in operation.

(b)
[Each .exible fuel tank liner must be shown to be suitable for the particular appli-cation.]

(c)
Each integral fuel tank must have adequate facilities for interior inspection and repair.

(d)
The total usable capacity of the fuel tanks must be enoughfor at least one-halfhour of operation at maximum continuouspower.
　
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本文鏈接地址：FAA規(guī)章 美國(guó)聯(lián)邦航空規(guī)章 Federal Aviation Regulations 2(58)