In airplanes like the F-22, both the main wings and the tailerons provide (at least at subsonic speed) positive lift. My question is this: when performing a roll using all control surfaces asymmetrically, specially the tailerons, it seems that the longitudinal moment around the center of gravity wouldn't be zero, since one of the tailerons goes down, so the aircraft should tend to pitch (up) adversely. Is this true?
I guess the surfaces don't move completely asymmetrically but in a differential fashion, so the up going taileron moves further up to compensate for the negative lift of the down going taileron, or maybe the forces distribution is such that this is negligible. Also I'm disregarding important effects like drag.
So, does this adverse pitch may really happen?