This report aimed to experimentally verify analytical models that predict the residual strength of representative aircraft structures, such as wide panels, that are subjected to Multiple Site Damage (MSD). As today's transport aircraft become older, the possibility exists for predetermined analysis to be invalidated by the onset of MSD. The MSD can be caused by cyclic leading on the fuselage structure over its life, and the resulting weakening in the structure must be considered as a potential safety risk during repairs and inspections.


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    Pre-Corroded Fastener Hole Multiple Site Damage Testing

    Luzar, J. / Johnson, P. S. / United States; National Aeronautics and Space Administration et al. | British Library Conference Proceedings | 1999


    Fatigue Analysis of Multiple Site Damage at a Row of Holes in a Wide Panel

    Buhler, K. / Grandt, A. F. / Moukawsher, E. J. et al. | British Library Conference Proceedings | 1994


    Flat-Panel Displays

    Kmetz, Allan R. | IEEE | 1987


    Crack Linkup at Multiple Site Damage

    Ma, L. / Kobayashi, A. S. / Atluri, S. N. et al. | British Library Online Contents | 1998


    Crack Linkup at Multiple Site Damage

    Ma, L. / Kobayashi, A. S. / Atluri, S. N. et al. | British Library Conference Proceedings | 1998