§23.2225. Component loading conditions.

14 C.F.R. § 23.2225

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.

Notes, amendments, and revision history

Authority: 49 U.S.C. 106(f), 106(g), 40113, 44701-44702, 44704, Pub. L. 113-53, 127 Stat. 584 (49 U.S.C. 44704) note.

Source: Doc. No. FAA-2015-1621, Amdt. 23-64, 81 FR 96689, Dec. 30, 2016, unless otherwise noted.