Abstract: Accelerated corrosion tests of simulator specimens of the wing main beam of a kind of fighter plane are carried out for different times which correspond to different years of the plan on grounding, before fatigue test are carried out under load spectrum. By analysis of test data, the curve of grounding corrosion influence factor (C) versus grounding years (T) is obtained. On the basis of load spectrum fatigue test of simulator specimens in various mediums that composed sky part environmental spectrum, sky corrosion fatigue influence factor (K) is determined by the percent weighted composite method. Synthesizing C-T curve and K, fatigue life correction factors of the wing-main-beam under corrosion condition are determined, which correspond to various non-corrosion life and flight hours per year. The results are valuable for evaluation fatigue life of wing-main-beam under corrosion condition.