There is a significant interest in developing flight control laws which need minimum gain scheduling across the whole flight envelope while providing required robust performance and stability properties to the closed-loop system.Dynamic inversion and/or feedback linearization technique are considered by many authors as candidates to achieve these objectives[1-6].A common feature of proposed solutions is that dynamic inversion via nonlinear control feedbacks directly compensates coupled nonlinear aircraft dynamics and then the desired command response is prescribed by external robust linear feedback controller.The main advantage of the method is that control laws automatically achieve decoupling of command variables and avoid extensive gain scheduling.