Retracting mechanism.

CFR · 2024-01-01 · US · Title 14

For rotorcraft with retractable landing gear, the following apply: (a) (1) The loads occurring in any maneuvering condition with the gear retracted; (2) The combined friction, inertia, and air loads occurring during retraction and extension at any airspeed up to the design maximum landing gear operating speed; and (3) The flight loads, including those in yawed flight, occurring with the gear extended at any airspeed up to the design maximum landing gear extended speed. (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. (d) (e) (f) (g)

official document · source cfr-2024 · id 14:§ 29.729