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The results of an experimental investigation oriented to the analysis of thefatigue damage evolution in plain woven composite laminates subjected to tension-tension and tension-compression fatigue loading are presented and discussed.T300/ET442 carbon/epoxy prepregs were used in the autoclave moulding of thelaminates, which were laid up in three stacking sequences, namely [0] 10, [45] 10 and[03/452] s.. The main fatigue damage mechanisms, identified by means of microscopicobservation, are: transverse matrix cracking, layer delamination and fibre failure. Thesequence of appearance of the different mechanisms depends both on laminate lay-upand type of loading whereas the laminate final failure is generally controlled by apredominant damage mechanism only.