Today, the application of adhesive bonding technology for primary aerospace structures is limited due to the certification regulations. State of the art is the widely used "chicken rivet" as crack arrestor which is limiting the benefits of bonding technology, particularly in composite bonded joints. In this paper results from fatigue testing of novel design approaches for damage tolerant high load transfer (HLT) joints as e.g. Panel Joints or large bonded repairs will be discussed for CFRP and for Fiber Matel Laminates'(FML) adherents. Results from fatigue testing with Wide Single Lapshear (WSLS) specimen will be presented for different configurations to proof the crack stopping behavior of sate of the art fasteners as reference crack arrestor concept.
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