This paper addresses the development and testing of an actuator for a Miniature Trailing- Edge Effector (MiTE). The optimal deployment schedule for MiTEs to enhance rotorcraft performance is an on/off type deployment as opposed to a single-frequency harmonic deployment. In this work, the desired on/off square-wave deployment is approximated by a fiveterm Fourier series. A piezoelectric bimorph was designed to minimize the required drive voltage and integrated into an airfoil section for verification of the design under aerodynamic loading. For this research, the MiTE had a height of 1% of the chord and was located approximately 10% of the chord upstream of the trailing edge. A bench test was conducted to verify the actuator dynamics and it was determined that the required deflections could be obtained without exceeding the limits of the piezoelectric material. Results showed that the flap deflection approximated a square-wave for angles of attack of 0.84° and 12° and wind speeds up to 40 m/s.