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.