This paper presents a fault-tolerant controller for the attitude tracking problem of hypersonic vehicles, subject to uncertainties, external disturbances within certain bounds, and sudden actuator faults including partial failure, stuck, and constant bias. A control-oriented aerodynamic attitude tracking error model is considered to generate the direct fin deflection commands. The controller is then proposed using predefined-time control technique such that the tracking errors are bounded within a predetermined time. Numerical simulations with application to a hypersonic vehicle model are conducted to validate the effectiveness and robust fault tolerance of the employed controller.