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Fatigue design of aerospace metallic components is carried out by using two methodologies: damage tolerance and safe-life. At present, regulations mainly recommend the use of the former, which entrusts safety to a suitable inspections plan. Indeed, a crack or a flaw is supposed to have been present in the component since the beginning of its operative life, and it must remain not critical, i.e. it must not cause a catastrophic failure in the life period between two following inspections, (Federal Aviation Administration, 1998; Joint Aviation Authorities, 1994; US Department of Defence, 1998). When a crack is detected, the component is repaired or substituted and the structural integrity is so restored.

A Probabilistic Approach to Fatigue Design of Aerospace Components by Using the Risk Assessment Evaluation