The fuselage structure suffers large impact and vibration from the ground in landing and taxiing. In order to predict local hazard areas of the structure and provide a reference for structural strength design, it is necessary to implement an analysis on fuselage dynamic performance in landing and taxiing. This paper innovatively considered about changes of aeroplane taxiing rate and the aerodynamic force, so exact aerodynamic and landing gears' forces were gained, which provided a reliable set of external input for finite element calculation. To reduce the size of the calculation, reasonable constrains were set by Patran, half-body finite element aeroplane model was established. Finally, the external loads were added to the half-body model, Nastran was used to calculate the dynamic response, and the peak load response of each airframe station was extracted to make dynamic response envelope, so the local hazardous positions can be pre-estimated to provide references for the structure design, such as the location where the wing and fuselage are connected.