An automatic engine driven pump depressurization system for an aircraft, the aircraft including at least two engine driven pumps (30a, 30b, 32a, 32b) driven by a main engine (20a, 20b) for converting mechanical power provided by the main engine into hydraulic power for distribution by a hydraulic system (52a, 52b), the engine driven pump depressurization system comprising: a depressurization device (70a, 70b, 72a, 72b) corresponding to each of the at least two engine driven pumps, wherein the depressurization devices are each energized to depressurize a respective one of the at least two engine driven pumps; and a control module in signal communication with each of the depressurization devices, the control module including control logic for automatically generating a depressurization signal (90a, 90b, 92a, 92b) that energizes one of the depressurization devices based on a plurality of operational conditions of the aircraft. characterized in that the engine driven pump depressurization system further comprises: a sensor for placing at a pump outlet of each of the at least two engine driven pumps, the sensor configured to generate a pressure signal (104; 106; 108; 110) representative of the hydraulic pressure at the pump outlet of the respective one of the at least two engine driven pumps for receipt by the control module; and further characterized in that: the control module includes control logic for generating the depressurization signal if a plurality of flight conditions indicate the aircraft is operating in cruise cycle, both of the at least two engine driven pumps are operating above a threshold hydraulic pressure, and if the hydraulic system has a low hydraulic demand. a depressurization device (70a, 70b, 72a, 72b) corresponding to each of the at least two engine driven pumps, wherein the depressurization devices are each energized to depressurize a respective one of the at least two engine driven pumps; and a control module in signal communication with each of the depressurization devices, the control module including control logic for automatically generating a depressurization signal (90a, 90b, 92a, 92b) that energizes one of the depressurization devices based on a plurality of operational conditions of the aircraft. a sensor for placing at a pump outlet of each of the at least two engine driven pumps, the sensor configured to generate a pressure signal (104; 106; 108; 110) representative of the hydraulic pressure at the pump outlet of the respective one of the at least two engine driven pumps for receipt by the control module; and further characterized in that: the control module includes control logic for generating the depressurization signal if a plurality of flight conditions indicate the aircraft is operating in cruise cycle, both of the at least two engine driven pumps are operating above a threshold hydraulic pressure, and if the hydraulic system has a low hydraulic demand. the control module includes control logic for generating the depressurization signal if a plurality of flight conditions indicate the aircraft is operating in cruise cycle, both of the at least two engine driven pumps are operating above a threshold hydraulic pressure, and if the hydraulic system has a low hydraulic demand.