§27.691 Autorotation control mechanism

CS-27 · Subpart D — Design And Construction · at CS27-10 (current)

Text in force at CS27-10: from CS27-0, effective 14 Nov 2003.

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

ED Decision 2003/015/RM · Source

Version history

Version	Effective	Published
CS27-0	14 Nov 2003	ED Decision 2003/015/RM

No aircraft in the dataset reference this section.

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