Component loading conditions.

§ 23.2225 Component loading conditions. The applicant must determine the structural design loads acting on: (a) Each engine mount and its supporting structure such that both are designed to withstand loads resulting from— (1) Powerplant operation combined with flight gust and maneuver loads; and (2) For non-reciprocating powerplants, sudden powerplant stoppage. (b) Each flight control and high-lift surface, their associated system and supporting structure resulting from— (1) The inertia of each surface and mass balance attachment; (2) Flight gusts and maneuvers; (3) Pilot or automated system inputs; (4) System induced conditions, including jamming and friction; and (5) Taxi, takeoff, and landing operations on the applicable surface, including downwind taxi and gusts occurring on the applicable surface. (c) A pressurized cabin resulting from the pressurization differential— (1) From zero up to the maximum relief pressure combined with gust and maneuver loads; (2) From zero up to the maximum relief pressure combined with ground and water loads if the airplane may land with the cabin pressurized; and (3) At the maximum relief pressure multiplied by 1.33, omitting all other loads.