The study presents the results of research on thin-walled elements made of aluminum alloy, subjected to pure shear. These elements represent a representative section of the skin of a semi-monocoque aircraft structure, weakened by an inspection hole. The possibility of the occurrence of post-critical deformations under operational load conditions was considered. The results of a numerical analysis conducted under static load conditions using the finite element method are presented. Based on the obtained stress distribution, a fatigue strength simulation was performed, based on the ε-n analysis. The results were verified using experimental static and fatigue tests.