A flight control system for a rotary aircraft, the rotary aircraft having a longitudinal controller, a lateral controller, a directional controller, and a vertical controller, the control system comprising: a longitudinal loop design having: a forward speed hold loop; a pitch attitude loop; and a pitch rate loop; wherein the forward speed hold loop automatically engages when the longitudinal controller is returned to a detent position and the aircraft groundspeed is outside a first groundspeed threshold; and wherein longitudinal maneuverability of the rotary aircraft is controlled by either the pitch attitude loop or the pitch rate loop when the longitudinal controller is out of the detent position; a lateral loop design having: a lateral speed hold loop; and a roll rate loop; wherein the lateral speed hold loop automatically engages when the lateral controller is returned to a detent position and the aircraft groundspeed is outside the first groundspeed threshold; and wherein lateral maneuverability of the rotary aircraft is controlled by either the lateral speed hold loop or the roll rate loop when the lateral controller is out of the detent position; a directional loop design having: a yaw rate command loop; and a heading hold loop; wherein the heading hold loop will be re-engaged automatically during flight in the first groundspeed threshold when the directional controller is in detent; and a vertical control loop design having: a vertical speed hold loop; and an altitude hold loop; wherein the altitude hold loop automatically engages when the vertical controller is returned to a detent position and the aircraft groundspeed is inside the first groundspeed threshold; and wherein vertical maneuverability of the rotary aircraft is controlled by the vertical speed hold loop if the vertical controller is out of the detent position. a longitudinal loop design having: a forward speed hold loop; a pitch attitude loop; and a pitch rate loop; wherein the forward speed hold loop automatically engages when the longitudinal controller is returned to a detent position and the aircraft groundspeed is outside a first groundspeed threshold; and wherein longitudinal maneuverability of the rotary aircraft is controlled by either the pitch attitude loop or the pitch rate loop when the longitudinal controller is out of the detent position; a forward speed hold loop; a pitch attitude loop; and a pitch rate loop; wherein the forward speed hold loop automatically engages when the longitudinal controller is returned to a detent position and the aircraft groundspeed is outside a first groundspeed threshold; and wherein longitudinal maneuverability of the rotary aircraft is controlled by either the pitch attitude loop or the pitch rate loop when the longitudinal controller is out of the detent position; a lateral loop design having: a lateral speed hold loop; and a roll rate loop; wherein the lateral speed hold loop automatically engages when the lateral controller is returned to a detent position and the aircraft groundspeed is outside the first groundspeed threshold; and wherein lateral maneuverability of the rotary aircraft is controlled by either the lateral speed hold loop or the roll rate loop when the lateral controller is out of the detent position; a lateral speed hold loop; and a roll rate loop; wherein the lateral speed hold loop automatically engages when the lateral controller is returned to a detent position and the aircraft groundspeed is outside the first groundspeed threshold; and wherein lateral maneuverability of the rotary aircraft is controlled by either the lateral speed hold loop or the roll rate loop when the lateral controller is out of the detent position; a directional loop design having: a yaw rate command loop; and a heading hold loop; wherein the heading hold loop will be re-engaged automatically during flight in the first groundspeed threshold when the directional controller is in detent; and a yaw rate command loop; and a heading hold loop; wherein the heading hold loop will be re-engaged automatically during flight in the first groundspeed threshold when the directional controller is in detent; and a vertical control loop design having: a vertical speed hold loop; and an altitude hold loop; wherein the altitude hold loop automatically engages when the vertical controller is returned to a detent position and the aircraft groundspeed is inside the first groundspeed threshold; and wherein vertical maneuverability of the rotary aircraft is controlled by the vertical speed hold loop if the vertical controller is out of the detent position. a vertical speed hold loop; and an altitude hold loop; wherein the altitude hold loop automatically engages when the vertical controller is returned to a detent position and the aircraft groundspeed is inside the first groundspeed threshold; and wherein vertical maneuverability of the rotary aircraft is controlled by the vertical speed hold loop if the vertical controller is out of the detent position.