Abstract: The disclosed electrically controlled starter valve (10) regulates the flow of compressed gas to an air turbine starter (11) and precisely controls the way in which the flow is reduced after start of the aircraft engine. The electronic control system (30) is responsive to previously uncompensated for engine system variables. The main valve is a butterfly valve (12) controlled by an air actuator (14). A solenoid valve (16) in the air supply line (15, 17) to the actuator (14) is switched on and off at discrete intervals to provide for positioning of the butterfly valve (12). A position transducer (R2) senses position of the butterfly valve (12) and provides a position feedback signal. A pressure transducer (R1) senses pressure at the inlet to the butterfly valve (12) and provides an inlet pressure feedback signal. The position and pressure feedback signals are fed to an electronic control circuit (30) and are used to compensate for changing conditions to provide a consistent valve (12) closing pattern.