A fuel supply apparatus for an aircraft engine, the apparatus comprising: a fuselage fuel tank of an aircraft; a first fuel tank provided in a left wing of the aircraft; a second fuel tank provided in a right wing of the aircraft; a first engine provided in the left wing of the aircraft; a second engine provided in the right wing of the aircraft; a first pump unit configured to supply fuel from the fuselage fuel tank to the first engine ; a second pump unit configured to supply fuel from the first and second fuel tanks to the first engine ; a third pump unit configured to supply the fuel from the fuselage fuel tank to the second engine ; a fourth pump unit configured to supply the fuel from the first and second fuel tanks to the second engine ; a first central fuel flow passage configured to connect between the fuselage fuel tank and the first pump unit ; a first main fuel flow passage configured to connect between the first fuel tank and the second pump unit ; a second central fuel flow passage configured to connect between the fuselage fuel tank and the third pump unit ; a second main fuel flow passage configured to connect between the second fuel tank and the fourth pump unit ; a central communication flow passage configured to connect between the first main fuel flow passage and the second main fuel flow passage ; and a switching unit configured to selectively switch the pump units (7a-7d) that supply the fuel to the each engine (5a-5b), respectively, wherein each pump unit (7a-7d) has: a booster and a measuring unit ; the booster includes: a centrifugal pump and a gear pump configured to boost and supply fuel to the corresponding engine (5a-5b), and an electric motor configured to rotationally drives the centrifugal pump and the gear pump ; and the measuring unit is configured to measure a supply amount of the fuel to the corresponding engine (5a-5b). a fuselage fuel tank of an aircraft; a first fuel tank provided in a left wing of the aircraft; a second fuel tank provided in a right wing of the aircraft; a first engine provided in the left wing of the aircraft; a second engine provided in the right wing of the aircraft; a first pump unit configured to supply fuel from the fuselage fuel tank to the first engine ; a second pump unit configured to supply fuel from the first and second fuel tanks to the first engine ; a third pump unit configured to supply the fuel from the fuselage fuel tank to the second engine ; a fourth pump unit configured to supply the fuel from the first and second fuel tanks to the second engine ; a first central fuel flow passage configured to connect between the fuselage fuel tank and the first pump unit ; a first main fuel flow passage configured to connect between the first fuel tank and the second pump unit ; a second central fuel flow passage configured to connect between the fuselage fuel tank and the third pump unit ; a second main fuel flow passage configured to connect between the second fuel tank and the fourth pump unit ; a central communication flow passage configured to connect between the first main fuel flow passage and the second main fuel flow passage ; and a switching unit configured to selectively switch the pump units (7a-7d) that supply the fuel to the each engine (5a-5b), respectively, wherein each pump unit (7a-7d) has: a booster and a measuring unit ; the booster includes: a centrifugal pump and a gear pump configured to boost and supply fuel to the corresponding engine (5a-5b), and an electric motor configured to rotationally drives the centrifugal pump and the gear pump ; and a centrifugal pump and a gear pump configured to boost and supply fuel to the corresponding engine (5a-5b), and an electric motor configured to rotationally drives the centrifugal pump and the gear pump ; and the measuring unit is configured to measure a supply amount of the fuel to the corresponding engine (5a-5b). <EOS>