Effect of lamination sequence on the compressive response of a thick plane strain cross-ply ring (very long cylindrical shell) weakened by the presence of a modal imperfection is investigated. A fully nonlinear finite element analysis, that employs a cylindrically curved 16-node layer-element, and is based on the assumption of layer-wise linear displacements distribution through thickness (LLDT), is utilized in the analysis of the afore-mentioned cross-ply ring. Hitherto unavailable numerical results pertaining to the influence of lamination sequence on the localization of buckling patterns and the ensuing shear crippling instability are also presented. (c) 2006 Elsevier Ltd. All rights reserved.