This article addresses the problem of simultaneous vibration and three-axis maneuvering control of a flexible spacecraft with a defective actuator. The spacecraft's solar panels are modeled as a cantilevered Euler-Bernoulli beam attached to a rigid body. An integral sliding mode fault-tolerant control algorithm is developed to stabilize the system subjected to external disturbances and actuator failures. As part of the fault control algorithm, a time-varying additive fault function is considered in order to improve performance and address issues associated with the excitation of high-frequency modes. The strain rate feedback control algorithm is activated simultaneously with the fault control algorithm to reduce residual vibrations during and after the maneuver. Lyapunov stability theory has been used to demonstrate the system's overall stability in the presence of external disturbances. The numerical simulations show that despite the effects of actuator faults on flexible dynamics, the proposed hybrid algorithm improves the performance of the defective system in terms of agility, the control effort, and flexibility mode excitation.