CS 29.571 Fatigue Tolerance Evaluation of Metallic Structure

• ED Decision 2012/022/R found in: CS-29 Amdt 10 - Large Rotercraft (Jan 2023)

CS 29.571 Fatigue Tolerance Evaluation of Metallic Structure ED Decision 2012/022/R (a) A fatigue tolerance evaluation of each Principal Structural Element (PSE) must be performed, and appropriate inspections and retirement time or approved equivalent means must be established to avoid Catastrophic Failure during the operational life of the rotorcraft. (b) Reserved (c) Reserved (d) Each PSE must be identified. Structure to be considered must include the rotors, rotor drive systems between the engines and rotor hubs, controls, fuselage, fixed and movable control surfaces, engine and transmission mountings, landing gear, and their related primary attachments. (e) Each fatigue tolerance evaluation must include: (1) In-flight measurements to determine the fatigue loads or stresses for the PSEs identified in sub-paragraph (d) in all critical conditions throughout the range of design limitations required in [CS 29.309](#_DxCrossRefBm1513259404) (including altitude effects), except that manoeuvring load factors need not exceed the maximum values expected in operations. (2) The loading spectra as severe as those expected in operations based on loads or stresses determined under sub-paragraph (e)(1), including external load operations, if applicable, and other high frequency power-cycle operations. (3) Take-off, landing, and taxi loads when evaluating the landing gear (including skis and floats) and other affected PSEs. (4) For each PSE identified in sub-paragraph (d), a threat assessment, which includes a determination of the probable locations, types, and sizes of damage taking into account fatigue, environmental effects, intrinsic and discrete flaws, or accidental damage that may occur during manufacture or operation. (5) A determination of the fatigue tolerance characteristics for the PSE with the damage identified in sub-paragraph (e)(4) that supports the inspection and retirement times, or other approved equivalent means. (6) Analyses supported by test evidence and, if available, service experience. (f) A residual strength determination is required that substantiates the maximum damage size assumed in the fatigue tolerance evaluation. In determining inspection intervals based on damage growth, the residual strength evaluation must show that the remaining structure, after damage growth, is able to withstand design limit loads without failure. (g) The effect of damage on stiffness, dynamic behaviour, loads and functional performance must be considered. (h) The inspection and retirement times or approved equivalent means established under this paragraph must be included in the Airworthiness Limitation Section of the Instructions for Continued Airworthiness required by [CS 29.1529](#_DxCrossRefBm1513259459) and paragraph A29.4 of [Appendix A](#_DxCrossRefBm1513259458). (i) If inspections for any of the damage types identified in sub-paragraph (e)(4) cannot be established within the limitations of geometry, inspectability, or good design practice, then supplemental procedures, in conjunction with the PSE retirement time, must be established to minimize the risk of occurrence of these types of damage that could result in a catastrophic failure during the operational life of the rotorcraft. [Amdt 29/3] CS 29.571 Fatigue Tolerance Evaluation of Metallic Structure ED Decision 2012/022/R (a) A fatigue tolerance evaluation of each Principal Structural Element (PSE) must be performed, and appropriate inspections and retirement time or approved equivalent means must be established to avoid Catastrophic Failure during the operational life of the rotorcraft. (b) Reserved (c) Reserved (d) Each PSE must be identified. Structure to be considered must include the rotors, rotor drive systems between the engines and rotor hubs, controls, fuselage, fixed and movable control surfaces, engine and transmission mountings, landing gear, and their related primary attachments. (e) Each fatigue tolerance evaluation must include: (1) In-flight measurements to determine the fatigue loads or stresses for the PSEs identified in sub-paragraph (d) in all critical conditions throughout the range of design limitations required in [CS 29.309](#_DxCrossRefBm1178331792) (including altitude effects), except that manoeuvring load factors need not exceed the maximum values expected in operations. (2) The loading spectra as severe as those expected in operations based on loads or stresses determined under sub-paragraph (e)(1), including external load operations, if applicable, and other high frequency power-cycle operations. (3) Take-off, landing, and taxi loads when evaluating the landing gear (including skis and floats) and other affected PSEs. (4) For each PSE identified in sub-paragraph (d), a threat assessment, which includes a determination of the probable locations, types, and sizes of damage taking into account fatigue, environmental effects, intrinsic and discrete flaws, or accidental damage that may occur during manufacture or operation. (5) A determination of the fatigue tolerance characteristics for the PSE with the damage identified in sub-paragraph (e)(4) that supports the inspection and retirement times, or other approved equivalent means. (6) Analyses supported by test evidence and, if available, service experience. (f) A residual strength determination is required that substantiates the maximum damage size assumed in the fatigue tolerance evaluation. In determining inspection intervals based on damage growth, the residual strength evaluation must show that the remaining structure, after damage growth, is able to withstand design limit loads without failure. (g) The effect of damage on stiffness, dynamic behaviour, loads and functional performance must be considered. (h) The inspection and retirement times or approved equivalent means established under this paragraph must be included in the Airworthiness Limitation Section of the Instructions for Continued Airworthiness required by [CS 29.1529](#_DxCrossRefBm1178331852) and paragraph A29.4 of [Appendix A](#_DxCrossRefBm1178331851). (i) If inspections for any of the damage types identified in sub-paragraph (e)(4) cannot be established within the limitations of geometry, inspectability, or good design practice, then supplemental procedures, in conjunction with the PSE retirement time, must be established to minimize the risk of occurrence of these types of damage that could result in a catastrophic failure during the operational life of the rotorcraft. [Amdt 29/3]