Pitching moment
Can somebody verify what happens to the aerodynamics when you lose the horizontal stabilizer in a go-around?
As far as I understand the plane is initially in approach trim with lots of nose-up trim to balance the negative (nose-down) pitching moment added by the flaps and slats. At a normal go-around the engine thrust causes a nose-up pitching moment which is cancelled out by the Airbus's automatic retrim, so the pilots just uses normal stick forces to establish a proper climbing attitude.
The question is when now the tail hits and the stabilizer separates: Will the now tailless wing's negative pitching moment overpower the nose-up pitching moment of the engine thrust? If so, the result would be a quick nosedive into the ground, consistent with the destruction we see. If not, we would get a stall and then a nosedive somewhat later. Which one happened here?