Abstract
This chapter first summarises the evolution of fatigue design requirements for aircraft structures. For metallic (mainly aluminium alloy) structures, these requirements have developed since the 1950s. Composite materials (notably carbon fibre reinforced plastics) present a relatively new challenge. There follows a concise discussion of the several possible methods for assessing the fatigue lives of aircraft structures. The emphasis is on requirements, but design and operational issues are also addressed.
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