---
title: "CS 25.371 Gyroscopic loads — CS-25 · Avioverse"
description: "The structure supporting any engine or auxiliary power unit must be designed for the loads, including gyroscopic loads, arising from the conditions…"
url: "https://avioverse.aero/regulations/easa/cs-25/subpart-c/cs-25-371"
---

# CS 25.371 Gyroscopic loads

Large Aeroplanes (CS-25) · CS-25 · EAR revision 26 Jan 2023

IR Implementing rule

## CS 25.371 Gyroscopic loads

The structure supporting any engine or auxiliary power unit must be designed for the loads, including gyroscopic loads, arising from the conditions specified in CS 25.331, CS 25.341, CS 25.349, CS 25.351, CS 25.473, CS 25.479, and CS 25.481, with the engine or auxiliary power unit at the maximum rpm appropriate to the condition. For the purposes of compliance with this paragraph, the pitch manoeuvre in CS 25.331(c)(1) must be carried out until the positive limit manoeuvring load factor (point A2 in CS 25.333(b)) is reached.

\[Amdt 25/1]

IR · CS 25.371 — CS-25 · ED Decision 2005/006/R · CS-25 Easy Access Rules · EAR revision 26 Jan 2023

[All rules in SUBPART C – STRUCTURE](https://avioverse.aero/regulations/easa/cs-25/subpart-c)

Consolidated from the EASA Easy Access Rules (revision 26 Jan 2023, extracted 13 Oct 2026) for convenience. Not the official publication — verify against the Official Journal of the European Union and the EASA publications before operational use.