A rotary wing aircraft (350, 360) comprising a first variable pitch rotor blade (20, 362) supported for rotation about a common rotor axis of rotation in a first rotor plane of rotation and the first variable pitch rotor blade (20, 362) includes cyclic pitch control, a second variable pitch rotor blade (22, 375) supported for rotation about the common rotor axis of rotation in a second rotor plane of rotation and the second variable pitch rotor blade (22, 375) includes cyclic pitch control, three first servo actuators (354, 355, 365) located between the first rotor plane of rotation and the second rotor plane of rotation and configured to vary a pitch of the first variable pitch rotor blade (20, 362), a non-rotating structural backbone (330, 364) formed to include a generally hollow interior extending along the common rotor axis of rotation through the second rotor plane of rotation and the first servo actuators (354, 355, 365) are coupled to the non-rotating structural backbone (330, 364), a first blade pitch controller (279, 385) located between the first rotor plane of rotation and the second rotor plane of rotation for controlling a pitch of the first variable pitch rotor blade (20, 362) and the first servo actuators (354, 355, 365) are coupled to the first blade pitch controller (279, 385) by three first pitch linkages, characterized in that the rotary wing aircraft further comprises three second servo actuators (354, 355, 365) coupled to the non-rotating structural backbone (330, 364) between the first rotor plane of rotation and the second rotor plane of rotation and three second pitch linkages interconnecting the second servo actuators (354, 355, 365) and a second blade pitch controller (280, 384) to vary a pitch of the second variable pitch rotor blade (22, 375). a first variable pitch rotor blade (20, 362) supported for rotation about a common rotor axis of rotation in a first rotor plane of rotation and the first variable pitch rotor blade (20, 362) includes cyclic pitch control, a second variable pitch rotor blade (22, 375) supported for rotation about the common rotor axis of rotation in a second rotor plane of rotation and the second variable pitch rotor blade (22, 375) includes cyclic pitch control, three first servo actuators (354, 355, 365) located between the first rotor plane of rotation and the second rotor plane of rotation and configured to vary a pitch of the first variable pitch rotor blade (20, 362), a non-rotating structural backbone (330, 364) formed to include a generally hollow interior extending along the common rotor axis of rotation through the second rotor plane of rotation and the first servo actuators (354, 355, 365) are coupled to the non-rotating structural backbone (330, 364), a first blade pitch controller (279, 385) located between the first rotor plane of rotation and the second rotor plane of rotation for controlling a pitch of the first variable pitch rotor blade (20, 362) and the first servo actuators (354, 355, 365) are coupled to the first blade pitch controller (279, 385) by three first pitch linkages, characterized in that the rotary wing aircraft further comprises three second servo actuators (354, 355, 365) coupled to the non-rotating structural backbone (330, 364) between the first rotor plane of rotation and the second rotor plane of rotation and three second pitch linkages interconnecting the second servo actuators (354, 355, 365) and a second blade pitch controller (280, 384) to vary a pitch of the second variable pitch rotor blade (22, 375).