Abstract: Based on the experimental results from dogbone specimens of 7475T761 aluminium alloy under the random spectrum loads, two different stochastic crack growth approaches (i.e., "general" and "analytical" ) are adopted. The probabilistic cumulative damage of the fatigue crack growth in a typical structural detail-fastener hole is studied. The probabilistic crack growth curve, the crack growth damage cumulative distribution and probability of crack exceedance are given. Analytical predictions for both approaches are correlated well with experimental test results. It is satisfatory for the engineering accuracy.These methodologies provide a useful means for the assessment of durability and damage tolerance design for aircraft structures.

Key words: probability of crack exceedance, the probabilistic crack growth curves, the crack growth damage cumulative distribution, the probabilistic cumulative damage