Aviation safety is critically threatened by bird strikes. Airworthiness and structural integrity are directly determined by the failure behavior of fastener joints under impact loading, as these joints serve as the key load-transfer nodes of aircraft structures. In this study, single-row and double-row joint specimens were designed and investigated. These specimens consisted of 7075-T6 aluminum alloy and CCF800G/EC-PAEK2 thermoplastic composite plates connected by hi-lok or countersunk bolts. Impact experiments were conducted by using an air gun to launch gelatin bird projectiles at a velocity of 68.1 m/s. The fluid-like deformation of the bird and the transient structural failure process were captured by high-speed cameras. Meanwhile, the load transfer paths were analyzed through dynamic strain histories. According to the results, single-row joints exhibit a progressive and symmetric failure mode that propagates outward from the impact center to the edges. In contrast, due to minor initial load asymmetries, double-row joints trigger intense dynamic load redistribution and stress wave superposition, ultimately resulting in a sudden, unilateral chain-reaction failure. This study extracts the damage evolution law of thermoplastic composite/metal hybrid joints under high-energy impact, providing critical experimental evidence and theoretical support for the fault-tolerant design against bird strikes and the airworthiness compliance verification of aeronautical fastened structures.