Adhesive-bonded composite integrated structures (ACIS) are widely used in civil and military aircrafts now. The failure laws of such structures should be studied obligatorily to design them reasonably. In a composite wing-box test debonding damage was found at the connection between the skin and the wall in mechanical-joint region while the load was added up to certain magnitude. However the shear stress of the adhesive layer in plane was not high. The real reason of the damage is that there is significant out-plane normal tensile stress at the local place. The main factors, which induced out-of-plane normal tensile stress, include out-of-plane force resulting from changing of force transfer path and sudden change stiffness. In this paper an integrated composite I-beam is investigated to expound the existing objectively of out-of-plane force, and analyze the relationships between out-of-plane force, sudden change stiffness and out-plane normal tensile stress or peeling stress. Research indicates that the out-of-plane force and debonding damage resulted from it should be highly valued for ACIS in mechanical-joint region.