Actions to be taken to realize a damage-tolerant aircraft structure and to have it certified are listed. Studies to define aircraft usage, missions; develop load spectra, sequences; select critical locations for an evaluation; develop stress spectra for those locations; determine environmental conditions for those locations; compile crack growth data for each material and environment; compile fracture toughness data; produce crack growth curves; determine residual strength; decide on inspection techniques; determine detectable crack length; and decide on inspection intervals are summarized. Full scale tests on an F-28 aircraft wing are described.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Damage-tolerant aircraft design

    Leeuwen, H. P. | TIBKAT | 1984


    Damage Tolerant Design of the Aircraft Components

    Jelaska, D. / Podrug, S. / Grljusic, M. et al. | British Library Conference Proceedings | 2002


    Damage Tolerant Design: Long Life for Today's Aircraft

    Aarons, R. N. | British Library Online Contents | 1999


    Risk-Based Design Plots for Aircraft Damage Tolerant Design

    Dwire, Heather / Penmetsa, Ravi / Tuegel, Eric | AIAA | 2008


    Risk-Based Design Plots for Aircraft Damage Tolerant Design

    Dwire, H. / Penmetsa, R. / Tuegel, E. et al. | British Library Conference Proceedings | 2008