§ 29.337. Limit maneuvering load factor.
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/us/cfr/t14/s§ 29.337·A research copy — for the controlling text, always check the official state or federal source. Not legal advice.
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]
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§ 29.337
Limit maneuvering load factor.
Fed. Reg.×1
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