Hi pensador,
Out of curiosity, I set maximum nose down on the trim within the green band (with Y hyd pressure) and looked at the elevator position during the outside check. It was within half a division of the maximum "leading edge up" shown on the fuselage.
It's possible to load the aircraft with a sufficiently aft C of G to warrant a stab setting like that. I'm sure the aircraft would have to be speed stable in flight (in case of problem resulting in direct law) and so the elevator must still produce a down force. (i.e. aircraft nose up moment, or clockwise moment in your example)