Abstract: Embodiments of the inventive concepts disclosed herein may provide visual and audible flight direction cues to the pilot of a helicopter to maintain an optimum energy sustaining profile to successfully perform an autorotation maneuver. From the moment the engine fails or fails to provide adequate power to the main rotor system, systems described herein provide airspeed, attitude, and altitude guidance to the pilot to intercept and fly the correct path for a successful autorotation entry and autorotation descent. The system displays specific cues as the helicopter approaches the determined flare altitude and guides the pilot through the autorotation flare and minimum rate of descent touchdown.