An actuator is disclosed for an active vibration and noise control system in an aircraft. The actuator is configured to attach a vibrating component, such as a gearbox mounting foot, to an aircraft support structure. The actuator is actuated by the control system to control the transmission of vibratory loads from the gearbox foot. The actuator includes a housing and a mounting member. The housing mounts to the aircraft. The mounting member attaches to the vibrating component within the aircraft. A piston arrangement is attached to the housing and includes a sleeve located within the housing, and a piston slidably disposed within the sleeve. A bearing assembly engages the mounting member with the piston. The bearing assembly includes a first bearing located between the mounting member and an inner bearing member. The first bearing is adapted to transmit axial motions between the mounting member and the piston. A second bearing is located between the inner bearing member and the housing and is adapted to transmit moment and shear loads from the mounting member to the housing. A third bearing is located between the inner bearing member and the piston, and is adapted to permit rotational movement of the inner bearing member relative to the piston.