Abstract: The present paper aims at designing of Automatic Landing System for CHARLIE aircraft based on root locus modern control system. The control method is used to determine the gains of the controllers. To apply the root locus method, the nonlinear model of the flight system with controllers is established and developed .Then the nonlinear model is linearized about certain operating point. A CHARLIE aircraft with flight condition parameters used for proposed flight path control system is described .The block diagram of the proposed control system with required controller gains is established. The transfer functions for open loop and then the closed loop are obtained with the help of automatic control principle. The root locus for open loop is drawn and then K values are found for given damping ratios. Finally the step responses of the closed loop system with Automatic Landing system controller autopilot are drawn. The digital simulation results prove the effectiveness of proposed control system in terms of fast response after applying external disturbances.