FUEL SYSTEM
GENERAL CHARACTERISTICS
- The aircraft has two integral wing fuel tanks with a total usable capacity of 2,580 lb (1,170 kg).
- Fuel delivery is fully automatic, with each engine normally fed from its respective tank.
- Fuel is warmed by an oil-to-fuel heat exchanger, eliminating the need for anti-ice additives.
- Each tank contains an electric boost pump used for engine start, transfer operations, and backup during low fuel pressure.
- The FADEC-controlled fuel system manages flow to the engines through engine-driven pumps and fuel metering units. Automatic motive-flow pumps maintain a steady supply throughout all flight phases.
- Fuel transfer between tanks is pilot-controlled as needed.
- Fuel quantity is measured capacitively and displayed on the EICAS.
- Refueling is performed through over-wing filler ports with flush caps.
FUEL BOOST Switches
- The FUEL BOOST switches are located on the lower instrument tilt panel. Each switch (labeled L and R) has three positions: ON, OFF, and NORM. When set to ON or OFF, each switch directly controls its respective boost pump manually.
- In the NORM position, boost pump operation is managed automatically by the system.
- A FUEL BOOST L-R or FUEL BOOST L-R CAS message indicates that the respective boost pump is on and operating.
FUEL TRANSFER Selector Knob
- The FUEL TRANSFER selector knob has three positions: L TANK, OFF, and R TANK.
- Selecting L TANK or R TANK opens the corresponding fuel transfer valve and, with the boost pump switches set to NORM, activates the fuel boost pump on the selected (supply) side. This enables fuel to be drawn from the supply-side engine feed bay by its boost pump and transferred to the opposite engine feed bay.
- The transferred fuel exits through the inactive boost pump located in the receiving engine feed bay.
HYDRAULIC SYSTEM
- The hydraulic system powers the landing gear and the power brakes.
- It uses an electrically driven pump that automatically maintains system pressure through an accumulator.
- Pressure is regulated between approximately 1,100 and 1,500 psi, depending on gear position and weight-on-wheels logic, to ensure quick response and minimize pump operation.
- Normal operation is fully automatic, with cockpit indications limited to EICAS messages in case of malfunction.
- Independent pneumatic systems provide backup for emergency gear extension and braking.