The Power Management Unit (PMU) is designed to take the input power up to 28 VDC and provide power to essential components, as well as across a variety of critical subsystems. Power is distributed to actuation, mission-critical & backup systems, pulsed high-power sensors, radar, and self-protection capabilities. Battery backed 28 VDC power is provided to the internal avionics components including (but not limited to) the Fuel control system including Main Flow Meter and Linearizer, Transfer Flow Meter and Linearizer, Fuel Quality Sensor, Fuel Boost Pump, APS, Radar Altimeter, Command & Control Transponder, Engine Control Unit, Antenna Switch, EED, GPS antenna, IFC, Pitot Heaters and IFF Transponder. The PMU can also provide switched power to Servo actuators including Rudder, Stabilator, Aileron, & Speed Brakes, Fuel Pumps, Air Data Module, Strobe Light, Engine Igniter & Scoring, and APC-4 (up to 10 amps @ 28 VDC) for future payload use. Spare switched power (5, 12, and 25 amp) can be initiated by Discrete commands from the Integrated Flight Controller (IFC) to provide switched power to the onboard components for current and future payload use.