The acceleration effect in the process of collinear hole-edge cracks propagation of aircraft fuselage skin structure is mainly manifested by the interaction of stress intensity factors between multiple fatigue cracks. A modified approximate superposition method based on the Muskhelishvili complex function theory and truncated conformal mapping approach is proposed in this paper to solve the stress intensity factors of multiple hole-edge cracks under remote uniform tension. The influence law of stress intensity factors for three kinds of cracking mode is analyzed,including the cracks of equal length emanating from two holes,the cracks of unequal length emanating from two holes,the cracks of equal length emanating from three holes and the cracks of unequal length emanating from three holes. The results of examples show that the interaction between adjacent cracks is obviously and the dimensionless stress intensity factors increase rapidly when the crack tips approach each other.