Amdt. 23-51, E.. 03/11/96
FAR 23.967 : Fuel tank installation.
(a)
Each fuel tank must be supported so that tank loads are not concentrated. In addition–
(1)
There must be pads, if necessary, to prevent cha.ng between each tank and its supports;
(2)
Padding mustbe non-absorbent ortreated topreventthe absorption offuel;
(3)
If a .exible tank liner is used, it must be supported so that it is not required to withstand .uid loads;
(4)
Interior surfaces adjacent to theliner mustbe smoothandfreefromprojections that could cause wear, unless–
(i)
Provisions are madeforprotection of theliner atthosepoints; or
(ii)
The construction of the liner itself provides such protection;
(5)
Apositivepressure mustbe maintained within the vapor space of eachbladder cell under all conditions of operation exceptfor aparticular conditionfor which it is shown that a zero or negative pressure will not cause the bladder cell to collapse; and
(6)
Siphoning offuel(otherthanminorspillage) ofcollapseofbladderfuel cells may not result from improper securing or loss of the fuel .ller cap.
(b)
Eachtankcompartment mustbe ventilated anddrainedtoprevent the accumulation of .ammable .uids or vapors. Each compartment adjacent to a tank that is an integralpart of the airplane structure must alsobe ventilated anddrained.
(c)
No fuel tank may be on the engine side of the .rewall. There must be at least one-halfinch of clearancebetweenthefuel tank and the .rewall.Nopartof theengine nacelle skin that lies immediately behind a major air opening from the engine compartment may act as the wall of an integral tank.
(d)
[Each fueltank may be isolated form personnel compartments by a fume-proof and fuel-proof enclosure that is vented and drained to the exterior of the airplane. The required enclosure must sustain any personnel compartment pressurization loads withoutpermanentdeformationorfailureunderthe conditionsofSecs.23.365 and
23.843 of this part. A bladder-type fuel cell, if used, must have a retaining shell at least equivalent to a metal fuel tank in structural integrity.]
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Elodie Roux. Septembre 2003
Subpart E : Powerplant
(e) Fuel tanks must be designed, located, and installed so as to retain fuel–
(1)
When subjected to the inertia loads resulting from the ultimate static load factorsprescribedinSec.23.561(b)(2) of thispart; and
(2)
Under conditionslikely to occur when an airplanelands onapaved runway at a normal landing speed under each of the following conditions :
(i)
The airplane in a normal landing attitude and its landing gear retracted.
(ii)
The most critical landing gear leg collapsed and the other landing gear legs extended.
In showing compliance withparagraph(e)(2) of this section, the tearing away of an engine mount must be considered unless all the engines are installed above the wing or on the tail or fuselage of the airplane.
Amdt. 23-43, E.. 05/10/93
FAR 23.969 : Fuel tank expansion space.
Eachfuel tank must have an expansion space of notless than twopercent of the tank capacity, unless the tank ventdischarges clear of the airplane(in which case no expansion space is required). It must be impossible to .ll the expansion space inadvertently with the airplane in the normal ground attitude.
FAR 23.971 : Fuel tank sump.
(a) [Eachfueltank musthave adrainable sump with an e.ective capacity,in the normal ground and .ight attitudes, of 0.25 percent of the tank capacity, or 1 gallon,
16
whichever is greater.
(b)
Each fuel tank must allow drainage of any hazardous quantity of water from any part of thetanktoits sump withthe airplaneinthe normalground attitude.
(c)
Each reciprocating enginefuel system must have a sediment bowl or chamber thatis accessible for drainage; has a capacity of 1 ounce for every 20 gallons of fuel tank capacity; and eachfuel tank outletislocated sothat,inthenormal .ightattitude, water will drain from all parts of the tank except the sump to the sediment bowl or chamber.
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本文链接地址：FAA规章 美国联邦航空规章 Federal Aviation Regulations 2(60)
