An active flow control experiment was conducted on a cropped NACA 0018 airfoil to study 3D effects and maneuverability aspects made possible by the 14 addressable, segmented fluidic piezoelectric actuators installed in the airfoil. The actuators were installed at the corner of the cropped region, inclined at 30 degrees to the local surface, facing downstream. Operating all actuators at unison significantly increased lift and generated a pitch-down moment. Operating all actuators at the same magnitude but varying the phase along the span generated larger lift-increment, with respect to the uniform phase excitation, especially when single or pairs of actuators operated at the same phase, and every other pair operated in anti-phase. Significant rolling moment can be generated when only half-span of the wing is actuated. The latter effect persists to the leading edge even though introduced at 88% of the chord. When a pair, out of the possible fourteen actuators is not operating, very little of the control authority is lost. This is an important finding when issues like fault tolerance and robustness of fluidic-Piezo actuators are considered.