TAIL ROTORFIXED PITCH MALFUNCTIONS
2. Fixed Pitch malfunctions may be caused by a jam, binding, or failure in the flight controls or tail rotor quadrant. The amount of anti-torque applied, aircraft gross weight, forward airspeed, and altitude at the time of the malfunction will determine the appropriate action. In most cases, except low airspeed and altitude combinations where acceleration is not possible continued flight will be possible. When altitude and time permit, every effort should be made to achieve level trimmed flight between 25-145 KIAS. In all fixed pitch situations the nose of the helicopter will turn to the right when power or airspeed is increased and turn to the left when collective or airspeed is decreased. Complete collective travel is available for most control combinations during a quadrant jam provided the pedals are allowed to move as the collective is displaced. If large sideslip angles are allowed to develop causing low indicated airspeed, the stabilator will program down and make it more difficult to increase airspeed and to maintain airspeed. Landing the aircraft into the wind or with a crosswind component opposite the yaw may aid in maintaining heading control for landing. Aircraft gross weight, amount of anti-torque applied at time of failure, and airspeeds that allow for trimmed flight must be considered when determining the type of landing.