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Part 27
§ 27.691

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14 CFR · Part 27

14 CFR § 27.691

Autorotation control mechanism.

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Read in Subpart D

Part 27 Contents

Subpart A: General
Subpart B: Flight
Subpart C: Strength Requirements
Subpart D: Design and Construction
Subpart E: Powerplant
Subpart F: Equipment
Subpart G: Operating Limitations and Information
Appendix A to Part 27: Instructions for Continued Airworthiness
Appendix B to Part 27: Airworthiness Criteria for Helicopter Instrument Flight
Appendix C to Part 27: Criteria for Category A
Appendix D to Part 27: HIRF Environments and Equipment HIRF Test Levels

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

Reflects the eCFR edition current as of September 29, 2026. Retrieved from ecfr.gov on October 16, 2026.

Primary Source

Official Source (14 CFR · Part 27)