14 CFR · Part 27

14 CFR § 27.337

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.

Reflects the eCFR edition current as of September 29, 2026. Retrieved from ecfr.gov on October 16, 2026.

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