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Structural analysis of aircraft components has involved the use of finite element method (FEM) analysis for many years. The transition from all metallic aircraft to hybrid constructions of composite and metallic materials has added complexity. Analysts have traditionally viewed each component individually, with a simplified attaching procedure, and generated the corresponding interface loads. This can be critical to the design details since composite components are often critical for fastener loads. Traditional analysis techniques for composite materials are a combination of simplified assumptions and empirical test data. This approach worked well when both the modeling technique for the two mating structures and the interface were of the same order of complexity.