STRUCTURAL INTEGRITY OF 2024-T351 ALUMINUM ALLOY RECYCLED FROM AIRBUS A320 WING SECTIONS UNDER FATIGUE LOADING

Dustmurodov Eldor Eshbobo ugli

Authors

Dustmurodov Eldor Eshbobo ugli Tashkent State Transport University, Faculty of Aviation Transport Engineering, Tashkent, Uzbekistan.

Keywords:

aging aircraft; fatigue crack initiation; fatigue crack propagation; fractography.

Abstract

This study examines the residual fatigue strength of 2024-T351 aluminum alloy recovered from the decommissioned wing panels of an Airbus A320 at the end of its operational life. Fatigue performance was assessed through S-N curves and crack growth rate (da/dN) measurements, and the results were compared with those of unused (virgin) material tested under identical conditions. Fractographic analysis of fracture surfaces supported the interpretation of fatigue behavior, and fatigue life predictions were conducted using the AFGROW software. The findings provide insight into the mechanical integrity and reusability of recycled aerospace-grade aluminum alloys.

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