ED Decision 2003/9/RM
(a) The maximum stresses developed in the Engine must not exceed values conforming to those established by satisfactory practice for the material involved, due account being taken of the particular form of construction and the most severe operating conditions. Where a new type of material is involved, evidence must be available to substantiate the assumed material characteristics. For Turbine Engines, due consideration must be given to the effects of any residual stresses in Engine Critical Parts.
(b) The Engine components which form part of the Engine mounting and any other parts of the Engine liable to be critically affected must, when the Engine is properly supported by a suitable Enginemounting structure, have sufficient strength to withstand the flight and ground loads for the aircraft as a whole in combination with the local loads arising from the operation of the Engine.
(c) Each Engine must be designed and constructed to function throughout its declared flight envelope and operating range of rotational speeds and power/thrust, without inducing excessive stress in any Engine part because of vibration and without imparting excessive vibration forces to the aircraft structure.
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