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This paper deals broadly with three aspects of the fatigue substantiation of general aviation aircraft structures. It describes the development of the Australian fatigue substantiation requirements for general aviation aircraft; it presents the results of local work in the acquisition of loads spectra for a range of aircraft, including pressurized and nonpressurized light twins, and it discusses some specific problems affecting the safe life and fail-safe substantiation of general aviation aircraft structures. Recent Australian work on ground taxi load spectra and on the endurance and radiographic inspectability of laminated spar caps is described.