If you define AoA with reference to the actual chord line and consider the change in chord line when flap or slat is extended, the Old Smokey's answer is clearly correct for the "bolted at fixed attitude" interpretation of the question.
However, in every case I've seen where aerodynamic coefficients are considered against flap or slat extension as a parameter, the chord line used as a reference against which to measure AoA is the original chord line of the wing without the high lift devices. Thus the answer is, trivially, that the AoA does not change.
M(F)S's interpretation is, of course, more interesting.