The characteristics of MSD fatigue initiation and early crack growth in transport aircraft fuselage longitudinal lap splices were determined fractographically for samples from three aircraft types, of which two from service and one from a full-scale test. The results are compared with NASA data from a full-scale test. The most MSD-susceptible rivet row was the upper one in the outer sheets of the lap splices. Cracks initiated mainly at faying surfaces near or at rivet hole corners. There was no evidence from the service aircraft that corrosion was involved in crack initiation. Early crack growth rates, from cracks 30 micrometers-5 mm in size were above 10 to the minus 18th power m/cycle (or flight), which means one should not expect 'short' crack behaviour. This facilitates crack growth modeling. However, it also makes questionable the usefulness of testing sub-scale specimens. For the service aircraft the environmental effects on crack growth were mild, if any. All the results are placed in the context of MSD fatigue modeling.
Fractographic Investigation of Pressure Cabin MSD
2000
36 pages
Report
No indication
English
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