---
title: "CS 23.2240 Structural durability — CS-23 · Avioverse"
description: "The applicant must develop and implement inspections or other procedures to prevent structural failures due to foreseeable causes of strength…"
url: "https://avioverse.aero/regulations/easa/cs-23/subpart-c/cs-23-2240"
---

# CS 23.2240 Structural durability

Normal-Category Aeroplanes (CS-23) · CS-23 · EAR revision 13 May 2026

IR Implementing rule

## CS 23.2240 Structural durability

(a) The applicant must develop and implement inspections or other procedures to prevent structural failures due to foreseeable causes of strength degradation, which could result in serious or fatal injuries, or extended periods of operation with reduced safety margins. Each of the inspections or other procedures developed under CS 23.2240 must be included in the Airworthiness Limitations Section of the Instructions for Continued Airworthiness required by CS 23.2625.

(b) For Level-4 aeroplanes, the procedures developed for compliance with CS 23.2240(a) must be capable of detecting structural damage before the damage could result in structural failure.

(c) For pressurised aeroplanes:

(1) the aeroplane must be capable of continued safe flight and landing following a sudden release of cabin pressure, including sudden releases caused by door and window failures;

(2) for aeroplanes with maximum operating altitude greater than 12 497 m (41 000 ft), the procedures developed for compliance with CS 23.2240(a) must be capable of detecting damage to the pressurised cabin structure before the damage could result in rapid decompression that would result in serious or fatal injuries.

(d) The aeroplane must be designed to minimise hazards to the aeroplane due to structural damage caused by high-energy fragments from an uncontained engine or rotating-machinery failure.

IR · CS 23.2240 — CS-23 · ED Decision 2017/013/R · CS-23 Easy Access Rules · EAR revision 13 May 2026

AMC Acceptable means of compliance

## AMC1 23.2240 Structural durability

ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification

6.9 Structural Durability & 9.11 Equipment Containing High-Energy Rotors

F3061/F3061M-24a Standard Specification for Systems and Equipment in Small Aircraft F3066/F3066M-18 Standard Specification for Aircraft Powerplant Installation Hazard Mitigation F3115/F3115M-15 Standard Specification for Structural Durability for Small Aeroplanes F3380-19 Standard Practice for Structural Compliance of Very Light Aeroplanes

F3116/F3116M-24 Standard Specification for Design Loads and Conditions

F3498-21 Standard Practice for Developing Simplified Fatigue Load Spectra

\[AMC & GM to CS-23: Issue 4]

\[AMC & GM to CS-23: Issue 5]

AMC · AMC1 23.2240 — CS-23 · ED Decision 2026/003/R · CS-23 Easy Access Rules · EAR revision 13 May 2026

AMC Acceptable means of compliance

## AMC2 23.2240 Structural durability

CS-23 Amdt 4

23.571 Metallic pressurized cabin structures

23.572 Metallic wing, empennage, and associated structures

23.573 Damage tolerance and fatigue evaluation of structure

23.574 Metallic damage tolerance and fatigue evaluation of commuter category airplanes

23.575 Inspections and other procedures

23.627 Fatigue strength

23.1461 Equipment containing high-energy rotors

AMC · AMC2 23.2240 — CS-23 · ED Decision 2017/025/R · CS-23 Easy Access Rules · EAR revision 13 May 2026

AMC Acceptable means of compliance

## AMC3 23.2240 Structural durability

CS VLA Amdt 1

VLA.572 Metallic wing, empennage, and associated structures

VLA.627 Fatigue strength

AMC · AMC3 23.2240 — CS-23 · ED Decision 2017/025/R · CS-23 Easy Access Rules · EAR revision 13 May 2026

[All rules in SUBPART C — STRUCTURES](https://avioverse.aero/regulations/easa/cs-23/subpart-c)

Consolidated from the EASA Easy Access Rules (revision 13 May 2026, 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.