Composite-metal hybrid joints are widely used in critical load-bearing regions of aircraft structures. The significant differences in material properties between the joined components lead to complex failure mechanisms, making strength design and analysis particularly challenging. This study establishes a damage failure model for a carbon fiber reinforced polymer (CFRP)-aluminum alloy three-bolt single-lap joint using the commercial finite element software ABAQUS. Numerical simulations were conducted to investigate the effects of clearance and interference fit on the tensile failure behavior of the hybrid joint. The damage evolution in composite laminates during assembly and loading, as well as the stiffness degradation trends of the joint, were systematically analyzed. Results reveal that bolt-hole fit parameters significantly influence load distribution among bolts and final failure modes, with interference fit effectively delaying delamination propagation. This research provides theoretical guidance for optimizing hybrid joint design and proposes a simulation framework incorporating damage evolution for strength analysis. Key findings offer practical references for tolerance design and assembly process improvement in aerospace applications.