RF4,
Look again at the figures you kindly posted. On figure 27 you can see that at 02:10:49 the pitch stabilized at 6 degrees and the PF's sidestick going from push to pull. On figure 28 you see the PF continuing to pull. The response of the airplane is immediate, it starts to pitch up. It is that pitch change that causes the AoA to increase and to exceed the stall warning threshold.
Not shown on these figures, the load factor changes from 0.85 to 1.15 in those 4 seconds.
The thrust levers are moved back to 33° at 02:10:47 and the N1 decrease to 85% in 4 seconds. That may have added a nose-down moment change, but did certainly not contribute to the pitch-up.
The following graph illustrates the drastic maneuver:
