Fractography Results for Fatigue Coupon Testing of Clad and Unclad 2024-T3 Aluminum Alloys

As aircraft age, the extent of interactions between fatigue and other damage mechanisms, such as corrosion and fretting, increases. At present, however, there is no generally accepted methodology within the Aircraft Structural Integrity Program (ASIP) framework to account for the effects of these interactions on life and the residual strength of aging aircraft components. A comprehensive program is being carried out by the National Research Council Canada in collaboration with Analytical Processes/Engineered Solutions, using the Holistic Structural Integrity Process (HOLSIP) to address time and cyclic load issues. This approach predicts the evolution of a discontinuity state in a material from production to retirement. This paper summarizes the results of a study on the 2024-T3 aluminium alloy in different forms (clad and unclad), thickness, and specimen geometry. This study consisted of identifying the microstructural features associated with crack nucleation sites and relating them to the testing parameters and fatigue life. Several coupons were fabricated and fatigue-tested. The fracture surfaces were carefully examined, and the physical characteristics of the microstructural features found near the crack nucleation sites were analyzed. Effect of stress level, loading direction, coupon geometry and surface condition on the number of crack nucleation sites, and fracture origin size has been discussed. Four distinctive mechanisms were found to be responsible for crack nucleation: for unclad materials constituent particles, oxide residue, surface irregularities and for clad samples the clad layer was the sole fracture origin.