Abstract: A reliability and risk analysis methodology is developed for airframe components under scheduled inspection and repair maintenance in service. It is assumed that critical locations in the airframe components are fastener holes,of which the initial fatigue quality(IFQ)is repre- sented by the equivalent initial flaw size(EIFS).a fastener hole must be repaired when a crack is detected. after repair,the fatigue quality of the airframe components is assumed to be renewed,in the sense that the flaw size distribution of the repaired fastener holes is identical to that of the new fastener hole. In this analysis,many quantities involving statistical variabilities have been taken into account,for instance,the initial fatigue quality,crack propagation,residual strength,ervice loading,crack detection probability,etc. A numerical example for the wing main spar of some fighter is given. The numerical results show that the developed analysis methodology is applicable.

Key words: reliability, analysis, damage assessment fracture mechanics