Abstract: The accelerated corrosion tests and then the fatigue tests on LD2 aerospace aluminum alloy test samples were executed under different corrosion times. The fatigue rupture morphologies of the test samples with different corrosion times were gained. The crack growth datum under different corrosion times were measured by judgment of the rupture morphologies. By fitting the datum , it can be found that the relation between crack length and cycle number is of exponential, and the crack growth rate is direct ratio to the crack length where the slope of the crack growth rate vs the crack length depends on the factors of corrosion damage and the fatigue load level. Furthermore, by fatigue tests under different corrosion times and different stress levels, it can be also found that the relation between the slope and the corrosion time is of linear under the same stress level and the slope values under different stress levels are nearly the same, while the intercept of the line of crack growth rate also varies linearly as the stress level.