(b)
Each fuel tank of 10 gallons or greater capacity must have internal ba.es, or must have external support to resist surging.
(c)
Each fuel tank must be separated from the engine compartment by a .rewall. At least one-half inch of clear airspace must be provided between the tank and the .rewall.
(d)
Spaces adjacent to the surfaces offuel tanks mustbe ventilated so thatfumes cannot accumulate in the tank compartment in case of leakage. If two or more tanks have interconnected outlets, they must be considered as one tank, and the airspaces in those tanks must be interconnected to prevent the .ow of fuel from one tank to another as a result of a di.erence in pressure between those airspaces.
(e)
The maximum exposed surface temperature of any component in the fuel tank must be less, by a safe margin as determined by the Administrator, than the lowest expected autoignition temperature of thefuel orfuel vaporin the tank.Compliance with this requirement must be shown under all operating conditions and under all failure or malfunction conditions of all components inside the tank.
(f)
[Eachfueltankinstalledinpersonnel compartments mustbeisolatedby fume-proof and fuel-proof enclosures that are drained and vented to the exterior of the ro-torcraft. The design and construction of the enclosures must provide necessary protection for the tank, must be crash resistant during a survivable impact in ac-cordance with Sec. 27.952, and must be adequate to withstand loads and abrasions to be expected in personnel compartments.
(g)
Each .exiblefuel tankbladderorlinermustbeapproved orshowntobesuitablefor theparticular application and mustbepuncture resistant.Puncture resistance must be shownby meeting theTSO-C80paragraph16.0 requirements using a minimum punctureforce of370pounds.
(h)
Eachintegralfuel tank musthaveprovisionsforinspection and repair ofitsinterior.] Amdt. 27-30, E.. 11/2/94
FAR27.965 :[Fuel tank tests.]
(a)
[Eachfueltank mustbe able to withstand the applicablepressuretestsin this section withoutfailure orleakage.Ifpracticable, testpressures maybe appliedin a manner simulating the pressure distribution in service.
(b)
Eachconventional metal tank, nonmetallic tank with walls that are not supportedby rotorcraftstructure, andintegral tank mustbe subjected to apressure of3.5p.s.i. unless the pressure developed during maximum limit acceleration or emergency deceleration with a full tank exceeds this value, in which case a hydrostatic head, or equivalent test, must be applied to duplicate the acceleration loads as far as possible. However, the pressure need 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.edinparagraph(c)(2) of this section.
(2)
A pressure 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 maximumlimit acceleration or emergencydeceleration.However, thepressure need not exceed2.0p.s.i. on surfaces not exposed tothe accelerationloading.
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本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 4(109)
