The requirement to provide satisfactory performance in the face of variation in the system parameters and the uncertainty in the design model, was the original motivation for the development of the CAD approach represented in this paper. Such an approach embraces system geometric theory together with modern multivariable frequency—response theory to establish a design main framework that would be compatible with a large class of practical control problems. The application of the proposed approach is undertaken to design an automatic flight control system for a real aircraft. The adequancy of the result-ing feedback configuration is confirmed via simulation.