Experimental study and finite element analysis has been performed on designed specimen to research the widespread fatigue damage characteristics of fuselage skin repair for civil aircraft. Test and analysis results showed that the initial location of crack at connecting region was basically equal probability of randomly generated. Residual strength of structure decreased originating from the combined effect of multiple-site crack. It caused the acceleration and competition effects of crack initiation. Connecting region failure finally occurred since the propagation and coalescence of main crack which acquired the competition advantage. The main crack propagation curves of damage tolerance analysis and experiments had the same trend, but the calculation of the crack propagation life was less than the test results.