See, that is what I'm not seeing the same as you guys. I understand that the AOA is the is the reference of the cord line to the direction of the air over the wing. If the plane pitches up, the AOA increases until the slip of the plane is gone and it is again stable at that vector of flight. I don't see how a roll induced would change the AOA. I'm dense I guess, but I just don't see the AOA being a factor here. Are you saying that the cord line changes as the plane yaws? It seems to me that the cord line of both wings is fixed and not a variable. What is variable is the angle of the cord to tha air flow across the wings, due to someting influencing the the cord angle, IE elevator change.

I'll understand this sooner or later.

Don