The fuel system supplies fuel to the engines and auxiliary power unit (APU). Two integral ventilated fuel tanks are located in the wings.

The refuel/defuel system performs gravity refueling, manual or automatic pressure refueling, and suction defueling operations. The aircraft can be refueled through a single-point adapter or manually by overwing refueling. All pressure fueling and defueling operations are controlled from the fuel/defuel control panel adjacent to the single-point fueling adapter. Suction defueling is accomplished at the single-point adapter with suction provided by the ground defueling unit.

The fuel distribution system supplies fuel to the engines and the APU through collector tanks inside each wing tank. Each collector tank is replenished by gravity through flapper check valves and by a scavenge ejector when the engines are operating. Fuel is supplied to the engines and APU from the collector tanks by primary ejectors and DC boost pumps. The right-side DC fuel pump takes fuel from the right collector tank and delivers it to the APU. If a fuel load imbalance occurs, fuel can be transferred from one wing to the other by the boost pumps and a wing transfer shutoff valve.

The fuel management and quantity gauging system (FMQGS) collects fuel system data and manages the refuel/defuel system. The FMQGS also generates indication information. Probes in the wing tanks supply fuel quantity and temperature to the fuel quantity computer. The fuel computer controls automatic refueling, powered crossflow, fuel transfer, and measurement of fuel quantity and temperature. Cockpit control is provided on the fuel system panel on the center pedestal. Fuel system data is presented on the engine indicating and crew alerting system (EICAS) and synoptic pages.