I suppose we have to define AOA, then...
Strictly speaking, AOA is the angle between the mean chord line and the local airflow. However, when speaking of indicated AOA in an airplane, the AOA gauge is fixed to the fuselage, so indicated AOA is relative to the mean chord line of the clean wing only. So in that case, the AOA does not change.
If we go with the strict definition, Old Smokey is correct for MOST airplanes. Slats USUALLY extend forward and downward. Flaps USUALLY extend aft and downward. However, Fowler flaps MAY initially extend aft only, so the AOA may not change at all. Also, if slats and flaps extend downward the same amount, the chord line will not change, so neither will the AOA -- only the camber changes (plus thickness and all those other details...).