Fatigue Tolerance Evaluation of Metallic Structure.

CFR · 2024-01-01 · US · Title 14

(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. The fatigue tolerance evaluation must consider the effects of both fatigue and the damage determined under paragraph (e)(4) of this section. Parts to be evaluated include PSEs of 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. (b) For the purposes of this section, the term— (1) (2) (c) The methodology used to establish compliance with this section must be submitted to and approved by the Administrator. (d) Considering all rotorcraft structure, structural elements, and assemblies, each PSE must be identified. (e) Each fatigue tolerance evaluation required by this section must include: (1) In-flight measurements to determine the fatigue loads or stresses for the PSEs identified in paragraph (d) of this section in all critical conditions throughout the range of design limitations required by § 29.309 (including altitude effects), except that maneuvering 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 paragraph (e)(1) of

official document · source cfr-2024 · id 14:§ 29.571