(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]
NEXT: Sec. 27.475 - Tires and shock absorbers.
PREVIOUS: Sec. 27.471 - General.