A rotary wing aircraft comprising: an airframe including an extending tail, the airframe including a longitudinal axis that extends through the extending tail; a main rotor assembly including at least one rotor hub (36, 39) supporting a plurality of rotor blades (34, 38) configured and disposed to rotate about a main rotor axis; at least one elevator (54, 58) arranged at the extending tail; a hub moment sensor operably connected to the main rotor assembly, or a hub moment estimator; an attitude/pitch rate sensor operably connected to the airframe; a control system operably connected to the main rotor assembly and the at least one elevator (54, 58), the control system being configured and disposed to adjust each of a pitch rate and an attitude of the airframe by selectively adjusting a position of the at least one elevator (54, 58); the control system including a moment mixer which controls hub moment; characterized in that the control system includes a hub moment feedback system operably connected to the hub moment sensor or hub moment estimator, and the rotor hub (36, 39) and the moment mixer, wherein the control system selectively adjusts rotor hub moment based on an input from the hub moment feedback system; and a pitch rate and attitude feedback system operably connected to the attitude/pitch rate sensor and the moment mixer, wherein the control system selectively adjusts a position of the at least one elevator (54, 58) based on an input from the pitch rate and attitude feedback system. an airframe including an extending tail, the airframe including a longitudinal axis that extends through the extending tail; a main rotor assembly including at least one rotor hub (36, 39) supporting a plurality of rotor blades (34, 38) configured and disposed to rotate about a main rotor axis; at least one elevator (54, 58) arranged at the extending tail; a hub moment sensor operably connected to the main rotor assembly, or a hub moment estimator; an attitude/pitch rate sensor operably connected to the airframe; a control system operably connected to the main rotor assembly and the at least one elevator (54, 58), the control system being configured and disposed to adjust each of a pitch rate and an attitude of the airframe by selectively adjusting a position of the at least one elevator (54, 58); the control system including a moment mixer which controls hub moment; characterized in that the control system includes a hub moment feedback system operably connected to the hub moment sensor or hub moment estimator, and the rotor hub (36, 39) and the moment mixer, wherein the control system selectively adjusts rotor hub moment based on an input from the hub moment feedback system; and a pitch rate and attitude feedback system operably connected to the attitude/pitch rate sensor and the moment mixer, wherein the control system selectively adjusts a position of the at least one elevator (54, 58) based on an input from the pitch rate and attitude feedback system. a moment mixer which controls hub moment; characterized in that the control system includes a hub moment feedback system operably connected to the hub moment sensor or hub moment estimator, and the rotor hub (36, 39) and the moment mixer, wherein the control system selectively adjusts rotor hub moment based on an input from the hub moment feedback system; and a pitch rate and attitude feedback system operably connected to the attitude/pitch rate sensor and the moment mixer, wherein the control system selectively adjusts a position of the at least one elevator (54, 58) based on an input from the pitch rate and attitude feedback system.