Retracting mechanism.

CFR · 2024-01-01 · US · Title 14

(a) (1) The landing gear retracting mechanism, wheel well doors, and supporting structure, must be designed for— (i) The loads occurring in the flight conditions when the gear is in the retracted position, (ii) The combination of friction loads, inertia loads, brake torque loads, air loads, and gyroscopic loads resulting from the wheels rotating at a peripheral speed equal to 1.23V (iii) Any load factor up to those specified in § 25.345(a) for the wing-flaps extended condition. (2) Unless there are other means to decelerate the airplane in flight at this speed, the landing gear, the retracting mechanism, and the airplane structure (including wheel well doors) must be designed to withstand the flight loads occurring with the landing gear in the extended position at any speed up to 0.67 (3) Landing gear doors, their operating mechanism, and their supporting structures must be designed for the yawing maneuvers prescribed for the airplane in addition to the conditions of airspeed and load factor prescribed in paragraphs (a)(1) and (2) of this section. (b) (c) (1) Any reasonably probable failure in the normal retraction system; or (2) The failure of any single source of hydraulic, electric, or equivalent energy supply. (d) (e) (1) If switches are used, they must be located and coupled to the landing gear mechanical systems in a manner that prevents an erroneous indication of “down and locked” if the landing gear is not in a fully extended position, or of “up and locked” if the lan

official document · source cfr-2024 · id 14:§ 25.729