The continuous effects of aircraft operational environment spectrum will cause corrosion damage to aircraft structures, which is difficult to detect or test in outside field. Based on the material’s S-N statistics and supposing the pitting-corrosion damage as the initial defect, this paper establishes a model to calculate the fatigue life of pitting-corrosion damage by combining the damage mechanics with the finite element method, and proposes an improved damage parameters determining method. By comparing the simulation results of pitting-corrosion damage with the test results, the model is proved to validated, accuracy and feasible in assessing metallic pitting-corrosion damage and can be represented as references for further study in corrosion fatigue.