The aviation aluminum alloy accelerated corrosion test spectrum was established according to the environment spectrum conducting process after collecting the airports environment data. Based on the accelerated corrosion test spectrum, aluminum alloy LD2CS pre-corroded fatigue test was carried out. Test data were analyzed statistically and the three main corrosion damage characterization factors, namely maximum pit depth, maximum pit width and pit surface rate, were sifted out by using MIV (mean impact value) method. Then the corrosion damage composite indictor α was computed by applying the normalization non-dimension and the weighted average methods. By comparing the characteristics of fatigue precrack propagation behaviors at different corrosion damage levels, the corrosion acceleration coefficient Ω(α) was defined to correct the classical fatigue crack growth formula. The validity of Ω(α)expression was verified by employing test data corroding the 18th to 20th equivelent years and the relative errors were all below 10%. It demonstrates that the corrected fatigue crack growth function in flight transfer environment is appropriate for reflecting the corrosion damage acceleration effect on crack propagation, which proposing new ideas for aviation aluminum alloy damage tolerance design.