′
Elodie Roux. Septembre 2003
Subpart E : Powerplant
(e)
Each fuel quantity indicator must be adjusted, as speci.ed in Sec. 23.1337(b), to accountforthe unusablefuel supply determined under[Sec.23.959(a).]
(f)
[Removed.] Amdt. 23-51, E.. 03/11/96
FAR 23.965 : Fuel tank tests.
(a)
Each fuel tank must be able to withstand the following pressures without failure or leakage :
(1)
For each conventional metal tank and nonmetallic tank with walls not suppor-tedbythe airplane structure, apressure of3.5p.s.i., orthatpressuredeveloped during maximum ultimate acceleration with a full tank, whichever is greater.
(2)
For each integral tank, the pressure developed during the maximum limit ac-celeration of the airplane with a full tank, with simultaneous application of the critical limit structural loads.
(3)
For each nonmetallic tank with walls supported by the airplane structure and constructedin an acceptable manner using acceptablebasic tank material, and with actual orsimulated supportconditions,apressureof2p.s.i.forthe .rst tank of a speci.c design. The supporting structure must be designed for the critical loads occurring in the .ight or landing strength conditions combined with the fuel pressure loads resulting from the corresponding accelerations.
(b)
Eachfuel tank withlarge,unsupported,orunsti.ened .atsurfaces,whosefailureor deformation could cause fuel leakage, must be able to withstand the following test without leakage, failure, or excessive deformation of the tank walls :
(1)
Each complete tank assembly and its support must be vibration tested while mounted to simulate the actual installation.
(2)
Except as speci.edinparagraph(b)(4) of this section, the tank assembly must
1
be vibrated for 25 hours at a total displacement of not less than of an inch
32
(unless another displacement is substantiated) while 2 .lled with water or
3
other suitable test .uid.
(i)
[Ifno frequency of vibration resulting from any r.p.m. within the normal operating range of engine orpropeller speedsis critical, the testfrequency of vibration is :
(A)
The number of cyclesper minute obtainedby multiplying the maxi-mum continuous propeller speed in r.p.m. by 0.9 for propeller-driven airplanes, and
(B)
For non-propeller driven airplanes the test frequency of vibration is 2,000 cycles per minute.]
(ii)
If only one frequency of vibration resulting from any r.p.m. within the normal operating range of engine or propeller speeds is critical, that fre-quency of vibration must be the test frequency.
(iii) If more than one frequency of vibration resulting from any r.p.m. within the normal operating range of engine or propeller speeds is critical, the most critical of these frequencies must be the test frequency.
(4) Underparagraph(b)(3)(ii) and(iii) ofthis section,thetimeoftestmustbe adjusted to accomplish the same number of vibration cycles that would be accomplishedin25hours atthefrequency speci.edinparagraph(b)(3)(i) of this section.
(5) During the test, the tank assembly must be rocked at a rate of 16 to 20 com-plete cycles per minute, through an angle of 15 degrees on either side of the horizontal(30degrees total), about an axisparallel to the axis of the fuselage, for 25 hours.
(c)
Eachintegral tank using methods of construction and sealing notpreviouslyproven to be adequate by test data or service experience must be able to withstand the vibrationtest speci.edin subparagraphs(1) through(4) ofparagraph(b).
(d)
Each tank with a nonmetallic liner must be subjected to the sloshing test outlined in subparagraph(5) ofparagraph(b) ofthis section,withthefuel at roomtem-perature. In addition, a specimen liner of the same basic construction as that to be used in the airplane must, when installed in a suitable test tank, withstand the sloshing test with fuel at a temperature of 110'F.
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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(59)
