(a) Each fuel tank must be able to withstand, without failure, the
vibration, inertia, fluid, and structural loads to which it may be
subjected in operation.
(b) Each flexible fuel tank bladder or liner must be approved or shown
to be suitable for the particular application and must be puncture
resistant. Puncture resistance must be shown by meeting the TSO-C80,
paragraph 16.0, requirements using a minimum puncture force of 370 pounds.
(c) Each integral fuel tank must have facilities for inspection and
repair of its interior.
(d) The maximum exposed surface temperature of all components in the
fuel tank must be less by a safe margin than the lowest expected
autoignition temperature 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 malfunction conditions of all components inside the
(e) Each fuel tank installed in personnel compartments must be isolated
by 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 necessary protection for the tank, must be crash resistant
during a survivable impact in accordance with §29.952, and must be
adequate to withstand loads and abrasions to be expected in personnel