14 CFR 29.337
§ 29.337 Limit maneuvering load factor.
United States · 14 CFR — Aeronautics and Space · Status: effective
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- Citation
- 14 CFR 29.337, § 29.337 Limit maneuvering load factor, United States, version 1 as recorded 2026-07-09, yourstate.us, https://yourstate.us/provision/54728
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Full text
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.
Legislative history
This is a federal regulation, adopted through agency rulemaking under the Administrative Procedure Act — not enacted by a recorded vote of Congress.