Abstract: Analyzing damage tolerance capability of structures with multiple fatigue cracks is an important task for the current assessing of structural fatigue reliability of aging airplanes. Based on probability damage tolerance theory for structures with multiple fatigue cracks under normal environment, a probability damage tolerance analysis method was established for structures with multiple fatigue cracks under corrosive environment. Using the model of logarithmic normal random variables to describe crack propagation processes, a reliability-life curve is presented for the structures with multiple cracks under corrosive environment, by considering the influences of the air during corrosion flight and the randomicity of crack propagation. A numerical example is given to prove the validity of the proposed method.