In order to analyze the aircraft structural reliability under corrosive environment, stochastic crack growth approach (Cor-SCGA) for durability analysis is established. Assuming the influence of the pre-corrosion in parkand the influence of corrosion in flight are independent, the fatigue quality of structure under corrosive environment has a Weibull distribution. Using a log-normal stochastic variable model to describe crack propagation, an equation for predicting the probability of crack exceedance is established. Compared with the probability fracture mechanics approach under corrosive environment (Cor-PFMA) and probability fracture mechanics approach under normal environment (Nor-PFMA), Cor-SCGA is more efficient. This approach will be better used for durability-based design.