(b) Unless otherwise prescribed, for each specified landing condition, the rotorcraft must be designed for a limit load factor of not less than the limit inertia load factor substantiated under §29.725.
(c) Triggering or actuating devices for additional or supplementary energy absorption may not fail under loads established in the tests prescribed in §§29.725 and 29.727, but the factor of safety prescribed in §29.303 need not be used.
[Amdt. 29–3, 33 FR 966, Jan. 26, 1968]
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