This paper deals with the problem of flight tracking control against actuator faults based on linear matrix inequality (LMI) method and adaptive method. The type of faults under consideration is loss of actuator effectiveness. An adaptive fault-tolerant flight controller design method is developed based on the on-line estimation of an eventual fault and the addition of a new control law to the normal control law in order to reduce the fault effect on the system without the need for an FDI (fault detection and isolation) mechanism. In the framework of linear matrix inequality (LMI) approach, the normal tracking performance of the resultant closed-loop system is optimized without any conservativeness and the states of fault modes asymptotically track those of the normal mode. A numerical example of an F-16 aircraft model and its simulation results are given.