Abstract: On analyzing the details of kinetic links of parts and structures of aircrafts, one can find few bad links. But fastener hole is the weakest link where abnormal stress is produced and initiation of crack occurs. The initial fatigue quality of aircraft wing flange fastener is the key parameter, which affects the durability of aircraft structure. The initial fatigue quality of structural details is usually characterized by the equivalent initial defect size (EIFS) and the time to crack initiation (TTCI). To evaluate the initial fatigue quality of aircraft wing flange fastener hole details, this paper first carried out fatigue tests at high-, medium- and low-stress levels on the BXXX aluminum alloy fastener hole specimens generally used in aircraft wing flange structures, and obtained three groups of (a?t) datasets about crack length a and fatigue life t through fracture interpretation and back stepping. On this basis, the EIFS governing equation was used to evaluate the EIFS value of each specimen, and it is found out that there is no significant difference in equivalent initial flaw size under different stress levels; TTCI distribution of structural details is obtained, and the economic life of specified stress level under 95% confidence level of fastener hole structural details was predicted, and compared with the design life; a structural detail equivalent to initial flaw size model under different exceedance probability P was proposed. Based on the given 5% crack exceedance probability, the general EIFS distribution of structural details was evaluated. The comprehensive evaluation results were obtained through the above triple evaluation of the initial fatigue quality of the fastener hole details: the general EIFS distribution and the EIFS value of each test piece are less than the allowable value, and the economic life is greater than the allowable value, so the original fatigue quality of the details of the fastening holes of the aircraft flange meets the stringent requirements.