rudderrudderrat.
I dont think that AOA of the wing will be ever in practice less than 0 deg. Only in that case the wing lift will change direction to the opposit so the stibilizer lift will have been changed accordingly to the opposit in order to provide the a\c stability.
Lets assume that the a\c flys with the Vmo and the wing lift will be close to 0. In that case the wing still produses the counter clockwise lift due to assymetrical pressure distribution on the upper and lower parts of the wing surface.
the only case when I mention the stabilizer in down position (approximately 0.5 down) is during takeoff but after flaps/slats retraction till landing it is only in up position.
The task for me is to find the actual stabiliser position figures as I was kindly advised by the Microburst2002!