When the transport aircraft is upgraded serially or refitted to special aircraft, due to the change of weight and the center of gravity, the load distribution of the landing gear deviates from the prototype, it may be necessary to move the wing and main landing gear to match the stationary load. In this paper, based on the principle of statics equilibrium of the nose gear load analysis, an innovative method for analyzing two independent variables based on main landing gear load line relative position of mean aerodynamic chord (MAC) and wing movement is proposed. Through linear interpolation of only four boundary points data, contours and contour lines of constrained variables are generated and form the carpet diagrams, to help designer conveniently analyze the complete design feasible region and carry out the comprehensive analysis of the stationary load matching of transport aircraft. An example is given to illustrate the analysis method, and the main principles of the design of stationary load matching are discussed.