Section 23.2225 - Component loading conditionsThe 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.