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    Effect of Prior Corrosion on the S/N Fatigue Performance of Aluminum Sheet Alloys 2024-T3 and 2524-T3

    Published: 01 January 1997

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    Aviation industry demand for continuous safety improvement in the face of trends toward increasing service life of aircraft and cost control necessitates stronger prevention and control measures to avoid the likelihood of structural failures linked to widespread damage involving corrosion and fatigue. New materials with improved damage tolerance attributes can improve the margin of safety in the presence of widespread damage. An excellent example of one such material is new aluminum alloy 2524 (formerly C188) which has improved fracture toughness and fatigue crack growth resistance relative to incumbent alloy 2024. In this study, the effect of prior corrosion on the S/N fatigue performance of 1.60 and 3.17-mm thick 2524-T3 and 2024-T3 bare sheet was evaluated. The fatigue strength of 2524 was approximately 10% greater and the lifetime to failure 30 to 45% longer than that of the 2024. Two main factors are believed to have contributed to the better performance of 2524: a less damaging configuration of corrosion pits and its better fatigue crack growth resistance.


    fatigue initiation, fatigue crack propagation, corrosion pitting, aluminum alloys, aircraft

    Author Information:

    Bray, GH

    Bucci, RJ

    Colvin, EL

    Kulak, M
    Staff Engineer, Technical Consultant, Technical Supervisor, and Senior Technical Specialist, Alcoa Technical Center, Aluminum Company of America, Alcoa Center, PA

    Committee/Subcommittee: E08.09

    DOI: 10.1520/STP19955S