Composite laminates with various lay-up configurations (namely, zero, angle and quasi-isotropic configuration) are extensively used in high performance structures due to various advantages offered by composites. However, the laminates are highly susceptible to damages arising due to impact loading, which could occur due to various in-service conditions. These damages grow significantly during the repeated loading-unloading cycles during the service and affect the structural integrity. Thus the repair of composites has drawn significant attention of the researchers. In this regards, the work presented in this seminar involves an experimental assessment of key parameters of the external patch repaired CFRP laminates under different loading conditions. The repair was performed by bonding the hard cured external patches over parent laminates. The specimens were tested under load controlled tensile-tensile fatigue loading, four point flexural static and fatigue loading and compression after impact (CAI) loading. The tensile fatigue tests were performed to study the influence of stacking sequence of parent laminates and the stiffness of the patch on the repair performance. The results reveal that the angle of orientation of plies of both the patch and the parent laminate is an important design parameter under tensile loading. The fatigue life, damage onset and its growth are significantly influenced by the orientation of the plies under tensile loading. The examination of specimens during the tests reveal that the damage initiates in the form of delamination and the failure of patch-parent interface, which grows further as the number of cycles increase and lead to the ultimate failure. Under flexural loading, the effects due to single sided and double sided patch repair along with the thickness and orientation of parent laminates and patch were investigated. The effect of orientation of plies of the patch is undermined by the effects arising due to placement of the patch on the face experiencing tensile or compressive stresses due to flexural loading. A patch bonded on the face experiencing tensile stress is less likely to restore the strength after repair compared to patch bonded on compression side. Furthermore, under the cyclic loading the damage initiates at an early stage and grows significantly for the patch bonded on tensile face. The CAI tests were conducted under static loading for the parent laminates and patches of different stacking sequence to investigate the effect of orientation of plies on the compressive behaviour of repaired laminates. Results revealed the orientation dependent distinctive failure modes in the parent laminates and a difference in the extent of compliance of .patches of different orientations.