Originally Posted by takata post 1185
Sure, a brutal right bank increasing to 40° while full left stick was maintained continuously for 50 seconds, and a sharp pitch change of -28° nose down while full aft stick was maintained continuously for 40 seconds, is certainly related to aircraft stability when stalling with no speed worth to be mentioned.
But what changed the previous equilibrum (16° NU, TOGA, continuous oscillations in roll) seems to be the sharp reduction of thrust.
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TOGA put the aircraft back in stable attitude, close to zero pitch for a while and wings could be put barely level again.
Could the airflow created by the thrust alter the direction of "natural" airflow due to the flight path? And the resulting AoA of the rear surfaces would be very different of the one of the wing?
Another question: at the same moment (when a/c right banked until 40°), what stopped this right wing plunge? The low wings configuration vs fuselage (so the entire fuselage has a "lateral drag" in this attitude) or the "lateral drag" of the vertical stabiliser (and then initiated the right turn: begining of a spin dive?)?