The TC4 alloy fastener hole structure parts were researched experimentally and theoretically. Based on the mathematical model of structure detail initial fatigue quality, the corresponding crack size distribution in certain time was determined by the crack growth equation of structure detail under loading spectra. By selecting appropriate referred crack size, the life of fastener hole structure detail in which 5% crack happened was provided and the resulted life was suggested as the economical life of aircraft structure. All the work is helpful to the economic repair of the modern aircraft structure