(a) Each fuel tank must be able to withstand the applicable pressure
tests in this section without failure or leakage. If practicable, test
pressures may be applied in a manner simulating the pressure distribution
in service.
(b) Each conventional metal tank, each nonmetallic tank with walls that
are not supported by the rotorcraft structure, and each integral tank must
be subjected 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 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 alone in conjunction with the test specified in paragraph
(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 maximum limit acceleration or emergency deceleration.
However, the pressure need not exceed 2.0 p.s.i. on surfaces faces not
exposed to the acceleration loading.
(d) Each tank with large unsupported or unstiffened flat 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 fluid. 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, the
test frequency of vibration, in number of cycles per minute, must, unless
a frequency based on a more rational analysis is used, be the number
obtained by averaging the maximum and minimum power-on engine speeds (r.p.m.)
for reciprocating engine powered rotorcraft or 2,000 c.p.m. for turbine
engine powered rotorcraft.
(ii) If only one frequency of vibration resulting from any r.p.m.
within the normal operating range of engine or rotor system speeds is
critical, that frequency 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 rotor system speeds is
critical, the most critical of these frequencies must be the test
frequency.
(4) Under paragraph (d)(3)(ii) and (iii), the time of test must be
adjusted to accomplish the same number of vibration cycles as would be
accomplished in 25 hours at the frequency specified in paragraph (d)(3)(i)
of this section.
(5) During the test, the tank assembly must be rocked at the rate of 16
to 20 complete cycles per minute through an angle of 15 degrees on both
sides of the horizontal (30 degrees total), about the most critical axis,
for 25 hours. If motion about more than one axis is likely to be critical,
the tank must be rocked about each critical axis for 12
1/2 hours. (Secs. 313(a), 601, and 603, 72 Stat. 752, 775, 49
U.S.C. 1354(a), 1421, and 1423; sec. 6(c), 49 U.S.C. 1655 (c))