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Advertisement Sec. 29.337 - Limit maneuvering load factor. 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. [Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as amended by Amdt. 27-26, 55 FR 8002, Mar. 6, 1990]
Previous: Sec. 29.321 - General.
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