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14 CFR 27.691

§ 27.691 Autorotation control mechanism.

United States · 14 CFR — Aeronautics and Space · Status: effective

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14 CFR 27.691, § 27.691 Autorotation control mechanism, United States, version 1 as recorded 2026-07-09, yourstate.us, https://yourstate.us/provision/54510
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Each main rotor blade pitch control mechanism must allow rapid entry into autorotation after power failure.

Legislative history

This is a federal regulation, adopted through agency rulemaking under the Administrative Procedure Act — not enacted by a recorded vote of Congress.