This paper deals with fatigue testing of a 16-ply aerospace laminate based on T800 Toray carbon fibres in Narmco 5245 epoxy resin, under diverse loading regimes including constant-stress bending and tension and block loading in tension-tension and tension-compression. Statistical analysis of the results has been performed by means of the extreme value theory, confirming a Weibull domain of attraction for each sample distribution. This procedure permits the assessment of low probabilities of failure, which can be used as characteristic values for practical design.