Current through May 31, 2024
Section 29.337 - Limit maneuvering load factorThe 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.Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as amended by Amdt. 27-26, 55 FR 8002, Mar. 6, 1990