Abstract: The arresting of a carrier-based aircraft in an attitude of yawing and off-center, will cause the lateral swing motion of the arresting hook along the arresting cable. Using the method of the simulation and the theoretical analysis, by adjusting the vibration frequency range of the lateral dynamic loads on the arresting hook, the dynamic load characteristics of the aircraft fuselage is studied. The results show that the severe loads on the fuselage can be caused at the vibration frequency of 2 Hz, 10 Hz and 20 Hz. The conclusions can be used for the optimal design of the structural stiffness and for reducing the hook head swing.