CS 27.691 Autorotation control mechanism

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ED Decision 2003/15/RM

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

Source-Title: CS 27.691 Autorotation control mechanism View latest amendments

Erulesid: ERULES-1963177438-4955 Compare versions

Domain: Initial airworthiness

Amendedby: Initial issue

Applicabilitydate: 14 November, 2003

Entryintoforcedate: 14 November, 2003

Regulatorysource: ED Decision 2003/15/RM Navigate

Regulatorysubject: CS-27

Typeofcontent: CS (Certification specification)

Origin: EASA

Category: EAR