Static strength of aircraft components and installations is analyzed by obtaining internal loads through free-body, shear and bending moment diagrams, or numerical methods such as NASTRAN with PATRAN, and then doing a structural analysis using classical handbook solutions.
Damage tolerance (crack growth) is analyzed with NASGRO or AFGROW to determine the required inspection intervals of principal structural elements per 14 CFR 25.571 and 26.43(d)(e).
High cycle fatigue due to flight, acoustic, and random vibration loads is analyzed using stress-life methods. Low cycle fatigue due to mechanical or thermal loads is analyzed using strain-life methods.
Advanced composite sandwich and solid laminate panels are analyzed using classical laminated plate theory for ply-level failure modes, core shear and compression, edge band, and insert strength.