Fatigue evaluation of flight structure.

CFR · 2024-01-01 · US · Title 14

(a) (1) The procedure for the evaluation must be approved. (2) The locations of probable failure must be determined. (3) Inflight measurement must be included in determining the following: (i) Loads or stresses in all critical conditions throughout the range of limitations in § 27.309, except that maneuvering load factors need not exceed the maximum values expected in operation. (ii) The effect of altitude upon these loads or stresses. (4) The loading spectra must be as severe as those expected in operation including, but not limited to, external cargo operations, if applicable, and ground-air-ground cycles. The loading spectra must be based on loads or stresses determined under paragraph (a)(3) of this section. (b) (c) (d) (1) It must be shown that all partial failures will become readily detectable under inspection procedures furnished under section A27.4 of appendix A. (2) The interval between the time when any partial failure becomes readily detectable under paragraph (d)(1) of this section, and the time when any such failure is expected to reduce the remaining strength of the structure to limit or maximum attainable loads (whichever is less), must be determined. (3) It must be shown that the interval determined under paragraph (d)(2) of this section is long enough, in relation to the inspection intervals and related procedures furnished under section A27.4 of appendix A, to provide a probability of detection great enough to ensure that the probability of catastrophic fai

official document · source cfr-2024 · id 14:§ 27.571