The applicant must determine the structural design loads acting on:

1. (a) Each engine mount and its supporting structure such that both are designed to withstand loads resulting from—

   1. (1) Powerplant operation combined with flight gust and maneuver loads; and
   2. (2) For non-reciprocating powerplants, sudden powerplant stoppage.

2. (b) Each flight control and high-lift surface, their associated system and supporting structure resulting from—

   1. (1) The inertia of each surface and mass balance attachment;
   2. (2) Flight gusts and maneuvers;
   3. (3) Pilot or automated system inputs;
   4. (4) System induced conditions, including jamming and friction; and
   5. (5) Taxi, takeoff, and landing operations on the applicable surface, including downwind taxi and gusts occurring on the applicable surface.

3. (c) A pressurized cabin resulting from the pressurization differential—

   1. (1) From zero up to the maximum relief pressure combined with gust and maneuver loads;
   2. (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. (3) At the maximum relief pressure multiplied by 1.33, omitting all other loads.