14 CFR 27.339
§ 27.339 Resultant limit maneuvering loads.
United States · 14 CFR — Aeronautics and Space · Status: effective
Cite this
- Citation
- 14 CFR 27.339, § 27.339 Resultant limit maneuvering loads, United States, version 1 as recorded 2026-07-09, yourstate.us, https://yourstate.us/provision/54451
- Permanent ID
ys:prov:54451@1- SHA-256
96ef71ac0ce1b80bf5acd3291e213fc140ebd250bb744865ba178e4e9c707abb
The hash is SHA-256 of this version's text, with every run of whitespace collapsed to a single space and the ends trimmed. The ID always leads back here, and checking it says whether the text you cited is still the current version.
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.