I'm sure it is a slip of the tongue. The four forces; pitch down = Lift and Weight. Thrust and Drag = pitch up. Therefore the pitch down moment of the tail plane is primarily balanced by Lift and Weight
No splip of the tongue, homeguard, but perhaps I didn't make it clear.
pitch down = Lift and Weight
Generally, the CofG is in front of the CofP. This causes pitch down. The downforce from the elevator causes pitch up, which counteracts (some of) the pitch down moment from the CofP.
As you correctly say, the thrust/drag couple causes more pitch up too, but I wasn't discussing that. If you add power, the change to the thrust/drag couple will cause the aircraft to pitch up, but very little change in the AoA because it will cause a rate of climb, or a reduced rate of descent, too. That's why I'm not bringing the thrust/drag couple into the equation.
However, as well as providing a pitch up due to the thrust/drag couple, adding power will also increase the (downwards) lift from the elevator - and this
will cause a change in the AoA, and therefore, according to my understanding, a change in the stick position at which the stall occurs.
FFF
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