14 CFR 29.339
§ 29.339 Resultant limit maneuvering loads.
United States · 14 CFR — Aeronautics and Space · Status: effective
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- Citation
- 14 CFR 29.339, § 29.339 Resultant limit maneuvering loads, United States, version 1 as recorded 2026-07-09, yourstate.us, https://yourstate.us/provision/54729
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Full text
The loads resulting from the application of limit maneuvering load factors are assumed to act at the center of each rotor hub and at each auxiliary lifting surface, and to act in directions and with distributions of load among the rotors and auxiliary lifting surfaces, so as to represent each critical maneuvering condition, including power-on and power-off flight with the maximum design rotor tip speed ratio. The rotor tip speed ratio is the ratio of the rotorcraft flight velocity component in the plane of the rotor disc to the rotational tip speed of the rotor blades, and is expressed as follows:
where—
Legislative history
This is a federal regulation, adopted through agency rulemaking under the Administrative Procedure Act — not enacted by a recorded vote of Congress.