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.
2726, 55 FR 8002, Mar. 6, 1990]
