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  5. § 27.1509
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14 CFR · Part 27

14 CFR § 27.1509

Rotor speed.

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Read in Subpart G
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
(a)

Maximum power-off (autorotation). The maximum power-off rotor speed must be established so that it does not exceed 95 percent of the lesser of—

(1)

The maximum design r.p.m. determined under § 27.309(b); and

(2)

The maximum r.p.m. shown during the type tests.

(b)

Minimum power off. The minimum power-off rotor speed must be established so that it is not less than 105 percent of the greater of—

(1)

The minimum shown during the type tests; and

(2)

The minimum determined by design substantiation.

(c)

Minimum power on. The minimum power-on rotor speed must be established so that it is—

(1)

Not less than the greater of—

(i)

The minimum shown during the type tests; and

(ii)

The minimum determined by design substantiation; and

(2)

Not more than a value determined under § 27.33(a)(1) and (b)(1).

Regulations Referenced

14 CFR 27.30914 CFR 27.33

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)