14 CFR 23.371 - Gyroscopic and aerodynamic loads.

§ 23.371 Gyroscopic and aerodynamic loads.
(a) Each engine mount and its supporting structure must be designed for the gyroscopic, inertial, and aerodynamic loads that result, with the engine(s) and propeller(s), if applicable, at maximum continuous r.p.m., under either:
(1) The conditions prescribed in § 23.351 and § 23.423; or
(2) All possible combinations of the following—
(i) A yaw velocity of 2.5 radians per second;
(ii) A pitch velocity of 1.0 radian per second;
(iii) A normal load factor of 2.5; and
(iv) Maximum continuous thrust.
(b) For airplanes approved for aerobatic maneuvers, each engine mount and its supporting structure must meet the requirements of paragraph (a) of this section and be designed to withstand the load factors expected during combined maximum yaw and pitch velocities.
(c) For airplanes certificated in the commuter category, each engine mount and its supporting structure must meet the requirements of paragraph (a) of this section and the gust conditions specified in § 23.341 of this part.
[Doc. No. 27805, 61 FR 5145, Feb. 9, 1996]

Title 14 published on 2014-01-01

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United States Code

Title 14 published on 2014-01-01

The following are ALL rules, proposed rules, and notices (chronologically) published in the Federal Register relating to 14 CFR 23 after this date.

  • 2014-03-18; vol. 79 # 52 - Tuesday, March 18, 2014
    1. 79 FR 15062 - Special Conditions: Extra Flugzeugproduktions and Vertriebs [Extra] GmbH, EA-300/LC; Acrobatic Category Aerodynamic Stability
      GPO FDSys XML | Text
      DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration
      Notice of proposed special conditions.
      Send your comments on or before April 17, 2014.
      14 CFR Part 23