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§ 23.2225 - Component loading conditions.

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The applicant must determine the structural design loads acting on:

Each engine mount and its supporting structure such that both are designed to withstand loads resulting from—

Powerplant operation combined with flight gust and maneuver loads; and

For non-reciprocating powerplants, sudden powerplant stoppage.

Each flight control and high-lift surface, their associated system and supporting structure resulting from—

The inertia of each surface and mass balance attachment;

Flight gusts and maneuvers;

Pilot or automated system inputs;

System induced conditions, including jamming and friction; and

Taxi, takeoff, and landing operations on the applicable surface, including downwind taxi and gusts occurring on the applicable surface.

A pressurized cabin resulting from the pressurization differential—

From zero up to the maximum relief pressure combined with gust and maneuver loads;

From zero up to the maximum relief pressure combined with ground and water loads if the airplane may land with the cabin pressurized; and

At the maximum relief pressure multiplied by 1.33, omitting all other loads.

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§ 23.2220 - Ground and water load conditions.
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§ 23.2230 - Limit and ultimate loads.