The subject of this investigation is focused on developing a computation procedure for optimal design of aircraft structural components with respect to stress, displacement and technology constraints. Attention is focused on minimal weight design of plates with a reinforced hole. The optimal design procedure is based on combining the finite element method (FEM) for structural analysis with using optimality criteria (OC) method in the optimisation process. Special attention is focused on optimal design of structural components with reinforced holes. The effect of the shape of reinforcements around the hole on the optimal design is analysed. Some practical design examples are used to illustrate the capability of this procedure.