§29.691 Autorotation control mechanism.

14 CFR 29 · Design and Construction · Control Systems · at 29-59 (current)

Text in force at 29-59: from 29-0, effective 1 Feb 1965.

Each main rotor blade pitch control mechanism must allow rapid entry into autorotation after power failure.

29 FR 16150 · Source

Version history

Version	Effective	Published
29-0	1 Feb 1965	29 FR 16150

No aircraft in the dataset reference this section.

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