CS-E 810 Compressor and Turbine Blade Failure

• ED Decision 2018/014/R found in: CS-E Amdt 5 - Engines (Dec 2018)

CS-E 810 Compressor and Turbine Blade Failure ED Decision 2018/014/R (See [AMC E 810](#_DxCrossRefBm1371447818)) (a) It must be demonstrated that any single compressor or turbine blade will be contained after Failure and that no Hazardous Engine Effect can arise as a result of other Engine damage likely to occur before Engine shut down following a blade Failure. (b) Where, in the Failure analysis of [CS-E 510](#_DxCrossRefBm1371447574), 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](#_DxCrossRefBm1371447574) 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]