By 2154:45, the AOA had increased to the point that both the stickshaker and the stickpusher activated. The control column moved forward rapidly in response to the activation of the stickpusher, decreasing the pitch angle to -3.5°, the AOA to 0°, and the vertical load to 0 G. The stickpusher then deactivated, and the flight crew moved the control column past neutral to about 5° ANU, which caused the pitch angle to increase to 8° and the AOA to increase to 11°.