Abstract:
A directional control margin investigation of the MH-60M Black Hawk helicopter was conducted to address the loss of directional control when operating at high density altitudes and high gross weights. This paper will discuss the flight test techniques used to assess directional control margin, the process for determining gross weight for flight testing at high density altitude, and resolution of the loss of directional control on the MH-60M. Additionally, low density altitude, low gross weight, and low power flight tests were performed to ensure adequate right directional control margin remained after implementation of changes to improve the loss of directional control at high density altitudes and high gross weights. A relationship between power required and directional control margin was established. Based on that relationship, a flight test methodology was developed to successfully quantify the directional control margin (DCM) of the MH-60M in stabilized hover and in the low airspeed flight regimes.