---
kind: "section"
citation: "14 C.F.R. § 23.2225"
title: "14"
number: "23.2225"
heading: "Component loading conditions."
url: "https://uscodex.org/cfr/14/23.2225"
---

# §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.

## Notes

### Authority

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

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