Lonewolf, I think that you are trying too hard to find an adverse scenario, not to say that there isn’t one.
First you might consider that a rapid thrust reduction gives a nose down pitching moment (not withstanding any basic C* demands);
and second, it’s possible that the control law incorporates a pitch rate or alpha rate term which advances the protective control. Even quite modest stall warning and stick pusher systems in conventional aircraft have rate advancement for warnings and activations.
In addition, even in the most adverse of scenarios it might be possible to experience a temporary over-swing of the alpha protect value, but this is not the aerodynamic stall alpha or loss of control.