In the case of aircraft control surface damage, the reconfiguration control plays a crucial part in improving the safety and reliability of aircraft. The traditional adaptive reconfiguration control method will cause high-frequency vibration of the system by using high-frequency gain in the control law, while the adoption of low-frequency gain will reduce the rapidity of the system. So, A new control surface damage reconfiguration control method is proposed with reference to L1 adaptive control, which can ensure the system’s fast response and the robustness of resisting interference. Firstly, conforming to the influence of control surface damage on the aircraft aerodynamic property, the mathematical modeling of the faulty aircraft is carried out. Then, according to the characteristics of L1 adaptive control method, the aircraft model is identical as a nonlinear system with unmatched nonlinear uncertainties, and suitable state predictor, adaptive law and filter are selected to design the reconstructed controller. Then controller’s steady-state and temporary performance are proved. Finally, the results of conducted simulation indicate that method offered can be used for the reconfiguration control of partial control surface damage, and it can meet the characteristics of fast self-adaptation and robustness at the same time.