Originally Posted by
HarryMann
Additionally: Significant drag is contributing to NU trim when and if the tail does stall
I'm not sure I really understood exactly the point you were trying to make here so apologise if I got your point wrong.
However, the drag resulting from a stall of the tail would induce a Nose Down pitching moment rather than Nose Up.
Regarding the recoverability of the stall: Please count me in in the camp of the 'it was technically very likely recoverable' camp.
The A332 is statically stable had a moderate Cg in the given case, has a low tail and a rather short forward fuselage. It is aerodynamically a through and through conventional airliner.
It is no F-16 with negative static stability and massive forebody strakes and Delta wing.