(b)
[Each .exible fueltank bladder or liner must be approved or shown to be sui-tablefortheparticular application and mustbepuncture resistant.Puncture resistance must be shown by meeting the TSO-C80, paragraph 16.0, require-ments using a minimumpunctureforce of370pounds.

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

(d)
The maximum exposed surface temperature of all componentsin the fuel tank must be less by a safe margin than the lowest expected autoignition tempera-ture of the fuel or fuel vapor in the tank. Compliance with this requirement must be shown under all operating conditions and under all normal or mal-function conditions of all components inside the tank.

(e)
Eachfuel tankinstalledinpersonnel compartmentsmustbeisolatedby fume-proof and fuel-proof enclosures that are drained and vented to the exterior of the rotorcraft. The design and construction of the enclosures must provide necessaryprotectionforthetank, mustbe crash resistantduring a survivable impact in accordance with Sec. 29.952, and must be adequate to withstand loads and abrasions to be expected in personnel compartments.]

Amdt. 29-35, E.. 11/2/94
FAR 29.965 : Fuel tank tests.
(a) Each fuel tank must be able to withstand the applicable pressure tests in this section withoutfailure orleakage.Ifpracticable, testpressures maybe applied in a manner simulating the pressure distribution in service.
′
Elodie Roux. Septembre 2003
Subpart E : Powerplant
(b)
Each conventional metal tank, each nonmetallic tank with walls that are not supported by the rotorcraft structure, and each integral tank must be subjec-ted to a pressure of 3.5 p.s.i. unless the pressure developed during maximum limit acceleration or emergency deceleration with a full tank exceeds this va-lue, in which case a hydrostatic head, or equivalent test, must be applied to duplicatethe accelerationloadsasfaraspossible.However,thepressureneed not exceed 3.5 p.s.i. on surfaces not exposed to the acceleration loading.

(c)
Each nonmetallic tank with walls supported by the rotorcraft structure must be subjected to the following tests :

(1)
A pressure test of at least 2.0 p.s.i. This test may be conducted on the tank alonein conjunction with the test speci.edin subparagraph(2) of this paragraph.

(2)
Apressure test, with the tank mounted in the rotorcraft structure, equal to the load developed by the reaction of the contents, with the tank full, during maximum limit acceleration or emergency deceleration. However, the pressure need not exceed 2.0 p.s.i. on surfaces not exposed to the acceleration loading.

(d)
Each tank with large unsupported or unsti.ened .at areas, or with other features whose failure or deformation could cause leakage, must be subjected to the following test or its equivalent :

(1)
Each complete tank assembly and its supports must be vibration tested while mounted to simulate the actual installation.

(2)
The tank assembly must be vibrated for 25 hours while two-thirds full of any suitable .uid. The amplitude of vibration may not be less than one thirty-second of an inch unless otherwise substantiated.

(3)
The test frequency of vibration must be as follows :

(i)
[If no frequency of vibration resulting from any r.p.m. within the normal operating range of engine or rotor system speeds is critical, thetestfrequency of vibration,in numberof cyclesperminute, must, unless a frequency based on a more rational analysis is used, be the numberobtainedby averaging the maximum and minimumpower-on engine speeds(r.p.m.) for reciprocating enginepowered rotorcraft or 2,000 c.p.m for turbine engine powered rotorcraft.]
　
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本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 5(68)