Stability is not a function of what the trim load on the tail is, but a function of the CHANGE in overall aircraft pitching monet as a result of a disturbance in angle of attack. As long as there's a nose-down restoring moment for a nose-up disturbance, the aircraft is stable. Which way the tail is providing the trim load doesn't affect that behaviour
That's exactly what I thought - thank you.
In that case, am I correct that one could have the aircraft set up with positive lift from the elevator assembly, for much of the rearward portion of the loading envelope?