A hybrid power distribution system for an aircraft having at least one aircraft engine (12a, 12b), the hybrid power distribution system comprising: a plurality of power sources connected to supply energy to a hydraulic distribution channel (16a, 16b, 16c) configured to provide power to hydraulic loads on the aircraft, wherein the plurality of power sources includes: - an electric power distribution bus configured to distribute electrical energy onboard the aircraft, - a pneumatic distribution channel (28a,28b) configured to distribute pneumatic energy onboard the aircraft, and - the at least one aircraft engine configured to provide mechanical energy; an engine driven pump (20a,20b) for converting mechanical energy provided by the at least one aircraft engine to hydraulic energy in the hydraulic distribution channel; an alternating current motor pump (26a,26b,26c,26d) for converting electrical energy provided by the electrical power distribution bus to hydraulic energy in the hydraulic distribution channel; an air driven pump for converting pneumatic energy provided by the pneumatic distribution channel to hydraulic energy in the hydraulic distribution channel, wherein the engine driven pump, the AC motor pump, or the air driven pump are selectively operated based on operating conditions of the aircraft to supply energy to the hydraulic distribution channel; and a controller configured to monitor flight conditions of the aircraft so as to determine a current one of take-off, climbing, cruising, descending or landing flight segments at which the aircraft is operating, to determine which power source will provide the most efficient supply of power corresponding to the current flight segment, and to provide control instructions to selectively activate the engine driven pump, the AC motor pump and the air driven pump based on the determined efficiencies. a plurality of power sources connected to supply energy to a hydraulic distribution channel (16a, 16b, 16c) configured to provide power to hydraulic loads on the aircraft, wherein the plurality of power sources includes: - an electric power distribution bus configured to distribute electrical energy onboard the aircraft, - a pneumatic distribution channel (28a,28b) configured to distribute pneumatic energy onboard the aircraft, and - the at least one aircraft engine configured to provide mechanical energy; - an electric power distribution bus configured to distribute electrical energy onboard the aircraft, - a pneumatic distribution channel (28a,28b) configured to distribute pneumatic energy onboard the aircraft, and - the at least one aircraft engine configured to provide mechanical energy; an engine driven pump (20a,20b) for converting mechanical energy provided by the at least one aircraft engine to hydraulic energy in the hydraulic distribution channel; an alternating current motor pump (26a,26b,26c,26d) for converting electrical energy provided by the electrical power distribution bus to hydraulic energy in the hydraulic distribution channel; an air driven pump for converting pneumatic energy provided by the pneumatic distribution channel to hydraulic energy in the hydraulic distribution channel, wherein the engine driven pump, the AC motor pump, or the air driven pump are selectively operated based on operating conditions of the aircraft to supply energy to the hydraulic distribution channel; and a controller configured to monitor flight conditions of the aircraft so as to determine a current one of take-off, climbing, cruising, descending or landing flight segments at which the aircraft is operating, to determine which power source will provide the most efficient supply of power corresponding to the current flight segment, and to provide control instructions to selectively activate the engine driven pump, the AC motor pump and the air driven pump based on the determined efficiencies.