Abstract: To address the common issue of panel wrinkling and deformation in a specific aircraft firewall after landing,this study established a refined finite element model using Hypermesh software.Through static analysis on Ansys platform combined with probabilistic reliability methods,we investigated the impact of critical parameters （corner aluminum plates D₂ and D₄ dimensions, and landing gear load F） on structural stress.A response surface model was constructed to verify its accuracy and evaluate post-repair structural reliability.Static strength analysis revealed that maximum stresses predominantly occurred at multi-plate intersections,with displacement distribution matching physical deformation trends.Post-repair structures met strength requirements.Reliability analysis demonstrated significant effects of corner aluminum plate dimensions D₂ and D₄ on stress distribution,while repaired structures maintained high reliability under normal operating conditions.This research identifies key maintenance control parameters,providing quantifiable metrics and decision support for firewall repair process optimization and routine inspections.