---
title: "CS-E 810 Compressor and Turbine Blade Failure — CS-E · Avioverse"
description: "(See AMC E 810) (a) It must be demonstrated that any single compressor or turbine blade will be radially contained by the Engine after Failure and that…"
url: "https://avioverse.aero/regulations/easa/cs-e/subpart-e/cs-e-810-compressor-and-turbine-blade-failure"
---

# CS-E 810 Compressor and Turbine Blade Failure

Engines (CS-E) · CS-E · EAR revision 7 Dec 2023

IR Implementing rule

## CS-E 810 Compressor and Turbine Blade Failure

(See AMC E 810)

(a) It must be demonstrated that any single compressor or turbine blade will be radially contained by the Engine after Failure and that the blade Failure will not lead to a Hazardous Engine Effect as a result of other damage before Engine shutdown at a rate in excess of that defined as Extremely Remote.

(b) Where, in the Failure analysis of CS-E 510, reliance is placed on the shedding of turbine blades in order to protect the rotating system in over-speed conditions, tests must be made to demonstrate that –

(1) The shedding will occur at a speed which provides a reasonable margin –

(i) Above the maximum Engine speed to be approved (including the Maximum Engine Overspeed) and

(ii) Below the minimum rotor burst speed.

(2) No Hazardous Engine Effect is likely to arise as a consequence of the blades shedding.

(c) In addition, for composite fan blades where the release of the fan blade is considered to be in the Engine flow path:

(1) it must be substantiated that, during the service life of the Engine, the total probability of the occurrence of a Hazardous Engine Effect defined in CS-E 510 due to an individual blade retention system Failure from all possible causes will be Extremely Improbable, with a calculated probability of Failure of less than 10–9 per Engine flight hour;

(2) it must be substantiated by test or analysis that a lightning strike to the composite fan blade structure will not prevent the continued safe operation of the affected Engine.

\[Amdt No: E/1]

\[Amdt No: E/5]

IR — CS-E · ED Decision 2018/014/R · CS-E Easy Access Rules · EAR revision 7 Dec 2023

[All rules in SUBPART E – TURBINE ENGINES: TYPE SUBSTANTIATION](https://avioverse.aero/regulations/easa/cs-e/subpart-e)

Consolidated from the EASA Easy Access Rules (revision 7 Dec 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.