A rotary wing aircraft comprising: an airframe including an extending tail , the airframe including a longitudinal axis (L) that extends through the extending tail ; a main rotor assembly including at least one rotor hub supporting a plurality of rotor blades configured and disposed to rotate about a main rotor axis (A); at least one elevator 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 , 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 ; 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 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 based on an input from the pitch rate and attitude feedback system . an airframe including an extending tail , the airframe including a longitudinal axis (L) that extends through the extending tail ; a main rotor assembly including at least one rotor hub supporting a plurality of rotor blades configured and disposed to rotate about a main rotor axis (A); at least one elevator 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 , 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 ; 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 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 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 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 based on an input from the pitch rate and attitude feedback system . <EOS>