Limit maneuvering load factor.

CFR · 2024-01-01 · US · Title 14

The rotorcraft must be designed for— (a) A limit maneuvering load factor ranging from a positive limit of 3.5 to a negative limit of −1.0; or (b) Any positive limit maneuvering load factor not less than 2.0 and any negative limit maneuvering load factor of not less than −0.5 for which— (1) The probability of being exceeded is shown by analysis and flight tests to be extremely remote; and (2) The selected values are appropriate to each weight condition between the design maximum and design minimum weights.

official document · source cfr-2024 · id 14:§ 29.337