This paper reviews some of the advances that have been made in stress analyses of cracked aircraft components, in the understanding of the fatigue and fatigue-crack growth process, and in the prediction of residual strength of complex aircraft structures with widespread fatigue damage. Finite-element analyses of cracked metallic structures are now used to determine accurate stress-intensity factors for cracks at structural details. Observations of small-crack behavior at open and rivet-loaded holes and the development of small-crack theory has lead to the prediction of stress-life behavior for components with stress concentrations under aircraft spectrum loading. Fatigue-crack growth under simulated aircraft spectra can now be predicted with the crack-closure concept. Residual strength of cracked panels with severe out-of-plane deformations (buckling) in the presence of stiffeners and multiple-site damage can be predicted with advanced elastic-plastic finite-element analyses and the critical crack-tip-opening angle (CTOA) fracture criterion. These advances are helping to assure continued safety of aircraft structures.Newman, J. C., Jr.Langley Research CenterAIRCRAFT STRUCTURES; CRACKS; FINITE ELEMENT METHOD; FRACTURE MECHANICS; STRESS ANALYSIS; METALS; CRACK PROPAGATION; METAL FATIGUE; STRESS INTENSITY FACTORS; RESIDUAL STRENGTH; CRACK CLOSURE; DAMAGE; STRESS CONCENTRATION; RIVETED JOINTS; PLASTIC PROPERTIES...