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This paper provides a mathematical model for a hypersonic flight vehicle system with actuator faults and then, proposes a fault-tolerant algorithm to increase the reliability of the attitude system. A terminal sliding mode controller for attitude angular loop is introduced to obtain the virtual control input. Thus, the required deflection angle of aerodynamic surfaces can be calculated via dynamic surface technique in inner angular rate loop. When the aero-surfaces are saturated and unable to supply the moment vector commanded by the fault tolerant controller, a reaction control system will be driven by quadratic programming allocator to provide the residual control torque. The system stability is analyzed utilizing the Lyapunov function. Several simulation results validate that the system output can track the desired command even under fault situations.