The rotorcraft must be designed for—
A limit maneuvering load factor ranging from a positive limit of 3.5 to a negative limit of −1.0; or
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—
The probability of being exceeded is shown by analysis and flight tests to be extremely remote; and
The selected values are appropriate to each weight condition between the design maximum and design minimum weights.
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