Abstract
The technology of crack growth life predictions for aircraft structure are reviewed together with the requirements for this technology. Damage tolerance and crack durability requirements imposed on manufacturers of aircraft have led to crack growth life analysis procedures which involve cycle-by-cycle accounting for the types of stress level interaction expected to occur in service. These analysis procedures are based primarily on the principles of linear elastic fracture mechanics and utilize constant-amplitude fatigue crack growth rate databases created specifically for the materials and environments of interest. New aircraft designs are now evolving which require that manufacturers account for the combined influences of stress and thermal environments in a realistic way.
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