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This paper concerns the application of multi-model based adaptive control approach to accommodate actuator fault for flight control systems. isolation. This approach does not require the exact information about the controlled system and persistent input excitations. The method can increase robustness and provides stable adaptation of unknown faults. Asymptotic model following conditions and adaptive rules are derived and system stability is guaranteed, while appropriate switching of the multiple models ensures asymptotic tracking for system outputs. An aircraft model is given to illustrate the efficiency of the proposed method.