Considering the impact of coupling effect of several failure modes, residual thermal stress, additional bending moment and crack ununiform propagation in fatigue life analysis for damaged aircraft metallic structure repaired with single-side adhesively bonded composite patch, a life evaluating method for the repaired structure is put forward. Analysis results of example are accordant with experimental results, which shows that the method can be used for preliminary analysis of fatigue life of damaged metallic structure repaired with single-side adhesively bonded composite patch.