Electric Solid Propellants are an exciting potential option for propulsion because they are ignited only by an applied electric current. This leads to exciting capabilities such as on-demand throttling and re-ignition, and insensitivity to accidental ignition by spark, impact or open flame. Digital Solid State Propulsion has developed a pulsed microthruster using an electric solid propellant. In this work, the plasma plume created by these microthrusters is investigated using a nude Faraday Probe, an array of single Langmuir Probes, a triple Langmuir probe and Residual Gas Analysis. The thruster was tested at a vacuum level of 2×10-5 Torr. Results indicate a peak centerline ion current density of about 200 mA/cm2, peak electron temperature of about 1 eV and peak electron density of between 1 and 2×1011 cm-3. Additionally, ionization fraction estimates are < 1% of an ablation mass bit of about 250 µg on average. Exhaust velocity estimates are largely inconclusive, but are on the order of a few km/s.