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.
Damage-Tolerant Aircraft Design
1984
30 pages
Report
No indication
English
Aircraft , Aircraft design , Aircraft structures , Structural design criteria , Tolerances (Mechanics) , Aircraft maintenance , Aircraft maneuvers , Aircraft reliability , Crack propagation , Data acquisition , Fatigue (Materials) , Fatigue tests , Flight operations , Gust loads , In-flight monitoring , Nondestructive tests , Service life , Foreign technology