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CS 29.691 Autorotation control mechanism

ED Decision 2003/16/RM

Each main rotor blade pitch control mechanism must allow rapid entry into autorotation after power failure.
Details
Source-Title: CS 29.691 Autorotation control mechanism View latest amendments
Erulesid: ERULES-1963177438-5614 Compare versions
Domain: Initial airworthiness
Amendedby: Initial issue
Applicabilitydate: 14 November, 2003
Entryintoforcedate: 14 November, 2003
Regulatorysource: ED Decision 2003/16/RM Navigate
Regulatorysubject: CS-29
Typeofcontent: CS (Certification specification)
Origin: EASA
Category: EAR