The application of composite materials to civil aircraft structure was growing during the past 25 years with every new aircraft which went into service. With these materials in commercial use it became necessary to define repairs in the case the component becomes damaged. During fatigue testing at component level the limits for allowable damage and maximum repair sizes were determined for standard damage events and manufacturing defects. The values are depending on structural design, material behavior and local strains or stresses. For simple damages on regular structures necessary repair actions are defined in the Structural Repair Manual. With an approved inspection philosophy the structure is under observation during airline service. It will be presented how the repair philosophy within Airbus Industrie partner companies is defined and which damages were reported on aircraft already in service. Some examples should explain the lessons we have learned from those failures occurred during component testing and airline service.
Damage Occurrence on Composites during Testing and Fleet Service: Repair of Airbus Aircraft
1995
8 pages
Report
Keine Angabe
Englisch
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