<p>The finite element method (FEM) was employed to evaluate the performance of bonded composite patch repairs applied to cracked aircraft structures. Traditionally, most studies have assessed repair effectiveness based solely on the reduction in the fracture stress intensity factor (SIF, K). In this work, a parametric and geometric optimization of the patch led to the development of a set of coupled and interdependent multi-criteria for assessing repair performance. Three key and correlated criteria were identified, each directly associated with one of the three components of the repair system: the plate, the adhesive, and the patch. These criteria respectively represent the fracture energy gain (ΔK/K), indicative of plate stability; the adhesive shear stress gain (Δτ/τ), reflecting the integrity of the adhesive bond; and the patch mass gain (Δm/m), characterizing the patch’s structural efficiency. The study demonstrated that these criteria can only be simultaneously optimized through geometric improvement of the conventional rectangular patch. After analyzing six different configurations, the optimization process resulted in the design of the final Double Arrow patch, referred to as DAFOFRT. This configuration significantly enhances repair performance, achieving a 95% mass gain, a 51% increase in adhesive shear stress, and improved crack stability, despite a moderate 20% reduction in fracture energy performance—an acceptable trade-off given the overall gains. These results clearly show that fracture energy reduction alone is insufficient for a complete assessment of bonded repair performance; it must be considered in conjunction with the adhesive integrity and the patch’s mechanical contribution. The multi-criteria approach developed in this study, integrating energetic, mechanical, and structural parameters, represents a major advancement in the evaluation and optimization of bonded composite repair systems for aircraft structures.</p>