In this paper, the airworthiness compliance of hybrid fiber-reinforced composite wings is analyzed, focusing on the analysis of shear stability, and the theoretical analysis, numerical simulation, and experimental research are carried out systematically. Carbon fiber and glass fiber are used to form a hybrid reinforced epoxy resin system. In the process of testing the properties of the material, the nonlinear constitutive relationship of the material is grasped. In this study, the first-order shear deformation theory and classical laminated theory are used to construct a reasonable model to analyze the shear stability of the wing structure. With the help of refined three-dimensional finite element simulation, the analysis of the parameters is carried out, and the impact of the ply sequence, skin thickness, and the proportion of ±45° plies on the critical load is analyzed. In this study, the static test scheme is designed according to the requirements of China Civil Aviation Regulations Part 25 (CCAR-25) airworthiness, and the ultimate shear load is simulated by four-point bending. During monitoring of the structural response, a variety of technologies are used, including acoustic emission, displacement, and strain. The test results show that when the structure reaches 105% of the design load, it will be unstable. There is a certain deviation between the simulated buckling load and the experimental one, but it is within the acceptable range, which shows that the numerical simulation is reliable. In this study, the whole technical path is constructed, including material characterization, stability analysis, and experimental verification, which can provide a reference for the airworthiness compliance of hybrid fiber composite wings.