Abstract: When the upper and/or lower panels of the loading box of the aircraft wing or tail are made of the fiber reinforced composite laminates, they can frequently be simplified as a non-moment plate. This paper introduces an optimum design （i. e. minimum weight design） procedure of the laminated plate on static failure strength condition. The mathematical tool used in the procedure is Lagrangian Multiplier method, and the static failure strength condition is adopted as Hill-Tsai criteria or Norris criteria.The formulae for optimum design have been not only derived, but also reformed to be convenient for the computer. How to establish the ultimate strength of laminates is discussed in detail. An example, illustrating the solution procedure and how to select the optimum scheme of lamination design, is presented in the paper. Some technical problems are briefly discussed in the last part.At the stage of the preliminary structural design, this procedure can be considered as an engineering method of lamination optimum design for the loading panel of laminated composite, which works under tension or compression （assuming that the buckling failure would not occur）.