(a) For specified landing conditions, a design maximum weight must be used that is not less than the maximum weight. A rotor lift may be assumed to act through the center of gravity throughout the landing impact. This lift may not exceed two-thirds of the design maximum weight.
(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 § 27.725.
[Amdt. 27-2, 33 FR 963, Jan. 26, 1968]
source: Docket No. 5074, 29 FR 15695, Nov. 24, 1964, unless otherwise noted.
cite as: 14 CFR 27.473