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Structural analysis practices that contribute to the effective analysis of large scale systems are described. The technical approach is via the matrix displacement method of structural analysis based upon finite element idealization. The context is a detailed thermal and mechanical stress analysis of the stacked Apollo Block II Spacecraft Lunar Module Adapter (SLA) and Service Module (SM). This structure is modeled in terms of 34 substructures which lead to an approximate total of 5000 finite elements and 15,000 displacement degrees-of-freedom. This refinement accounts for the complex variations in overall geometry, sizing dimensions, materials, thermal loading, mechanical loading, and boundary conditions. Embodied in the physical model are truss, frame, shear panel, triangular thin shell, quadrilateral thin shell, and triangular prism finite elements. The division into substructures of moderate size is put forward as a key to effective technical management of the stress analysis process.