Simultaneous bending and torsion control of aircraft wings or helicopter blades can enhance the aerodynamic efficiency and flight maneuverability of aircraft and helicopters. Bending control of plates using parallel segmented piezoelectric actuators was demonstrated in the past. In this paper, a new X-actuator configuration of piezoelectric patches based on the same total actuator area is used to control both bending and torsion vibrations simultaneously. Control effectiveness of the X-actuator configuration is studied and compared with that of the original parallel line-actuator configuration. Finite element analysis data suggest that the new X-actuator configuration is effective to control of both bending and torsion modes.