# 14 CFR § 27.351: Yawing conditions

> Federal · Regulations · In force

URL: https://www.frixlaw.com/law-library/statutes/ecfr-14-27.351

## Section

- **Citation:** 14 CFR § 27.351
- **Heading:** Yawing conditions
- **Jurisdiction:** Federal
- **Kind:** Regulations
- **Status:** In force
- **Text as of:** September 22, 2026
- **Source:** Publisher's official text
- **Location:** Title 14—Aeronautics and Space > CHAPTER I—FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION > SUBCHAPTER C—AIRCRAFT > PART 27—AIRWORTHINESS STANDARDS: NORMAL CATEGORY ROTORCRAFT > Subpart C—Strength Requirements > Flight Loads

## Text

(a) Each rotorcraft must be designed for the loads resulting from the maneuvers specified in paragraphs (b) and (c) of this section with—
(1) Unbalanced aerodynamic moments about the center of gravity which the aircraft reacts to in a rational or conservative manner considering the principal masses furnishing the reacting inertia forces; and
(2) Maximum main rotor speed.
(b) To produce the load required in paragraph (a) of this section, in unaccelerated flight with zero yaw, at forward speeds from zero up to 0.6 VNE—
(1) Displace the cockpit directional control suddenly to the maximum deflection limited by the control stops or by the maximum pilot force specified in § 27.397(a);
(2) Attain a resulting sideslip angle or 90°, whichever is less; and
(3) Return the directional control suddenly to neutral.
(c) To produce the load required in paragraph (a) of this section, in unaccelerated flight with zero yaw, at forward speeds from 0.6 VNE up to VNE or VH, whichever is less—
(1) Displace the cockpit directional control suddenly to the maximum deflection limited by the control stops or by the maximum pilot force specified in § 27.397(a);
(2) Attain a resulting sideslip angle or 15°, whichever is less, at the lesser speed of VNE or VH;
(3) Vary the sideslip angles of paragraphs (b)(2) and (c)(2) of this section directly with speed; and
(4) Return the directional control suddenly to neutral.
[Amdt. 27-26, 55 FR 7999, Mar. 6, 1990, as amended by Amdt. 27-34, 62 FR 46173, Aug. 29, 1997]

## Nearby sections

- [14 CFR § 27.301 § 27.301 Loads.](https://www.frixlaw.com/law-library/statutes/ecfr-14-27.301.md)
- [14 CFR § 27.303 § 27.303 Factor of safety.](https://www.frixlaw.com/law-library/statutes/ecfr-14-27.303.md)
- [14 CFR § 27.305 § 27.305 Strength and deformation.](https://www.frixlaw.com/law-library/statutes/ecfr-14-27.305.md)
- [14 CFR § 27.307 § 27.307 Proof of structure.](https://www.frixlaw.com/law-library/statutes/ecfr-14-27.307.md)
- [14 CFR § 27.309 § 27.309 Design limitations.](https://www.frixlaw.com/law-library/statutes/ecfr-14-27.309.md)
- [14 CFR § 27.321 § 27.321 General.](https://www.frixlaw.com/law-library/statutes/ecfr-14-27.321.md)
- [14 CFR § 27.337 § 27.337 Limit maneuvering load factor.](https://www.frixlaw.com/law-library/statutes/ecfr-14-27.337.md)
- [14 CFR § 27.339 § 27.339 Resultant limit maneuvering loads.](https://www.frixlaw.com/law-library/statutes/ecfr-14-27.339.md)
- [14 CFR § 27.341 § 27.341 Gust loads.](https://www.frixlaw.com/law-library/statutes/ecfr-14-27.341.md)
- [14 CFR § 27.351 § 27.351 Yawing conditions.](https://www.frixlaw.com/law-library/statutes/ecfr-14-27.351.md)
- [14 CFR § 27.361 § 27.361 Engine torque.](https://www.frixlaw.com/law-library/statutes/ecfr-14-27.361.md)
- [14 CFR § 27.391 § 27.391 General.](https://www.frixlaw.com/law-library/statutes/ecfr-14-27.391.md)
- [14 CFR § 27.395 § 27.395 Control system.](https://www.frixlaw.com/law-library/statutes/ecfr-14-27.395.md)
- [14 CFR § 27.397 § 27.397 Limit pilot forces and torques.](https://www.frixlaw.com/law-library/statutes/ecfr-14-27.397.md)

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Source: Frix Law Library, https://www.frixlaw.com/law-library/statutes/ecfr-14-27.351. Check the current official text before relying on it. Not legal advice.