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Suction feed to the engines is possible from: The wing and tip tanks. The outer tanks only. The outer tank transfer valve only. The inner tanks only.

Automatic control of CG (center of gravity): Begins when climbing through FL 255. Is terminated when FMGES time to destination is below 35 minutes. All of the above. Is terminated when descending through FL 245.

If you want the automatic fueling in a correct time you must: Preselect exactly the required fuel on board, or 200 kg more than the required. Preselect 3,000 kg more than of required. Preselect 3,000 kg more than of required.

What happens when fuel is collected in a surge vent tank?. Overpressure protector breaks open. Fuel is sucked by dedicated jet pump. Fuel is drained back into tank.

The main fuel pump system supplies fuel from the ____ tanks to the engines. Inner tank. Center tank. All of the above. Outer tank.

Automatic transfer from the outer tanks to the inner tans occurs when the center tank have been emptied and either inner tank reaches ______ kg. 3,000kg (6,600 lbs). 2,5000 kg (5,500 lbs). 3,5000 kg (7,700 lbs).

How many surge vent tanks are there?. Five. Three. Two.

The main fuel pump system has 2 main fuel pumps and 2 standby fuel pumps. True. False.

What does an amber line across the last two digits of the fuel quantity mean?. A fuel quantity indication is inaccurate. The fuel quantity is not good and should be checked. A disagreement between fuel measured and fuel entered in the MCDU has been detected. Not all the fuel aboard is usable.

From which tanks will fuel gravity feed?. Outer TANK of the wings tank, TO inner TANK of the wing tanks. Inner cell of the wing tanks, and center tank. The center tank only,. Outer cell of the wing tanks, inner cell of the wing tanks, and/or center tank.

To perform a correct pressure fueling in A330's aircraft is important: ADIRU´s must be started. The fueling panel must be energized. Battery SW ON and perform low level test.

There are ___ fuel pumps in each A330 wing tank collector cell. 2. 1. 3. 4.

What is the purpose of fuel control and monitoring system?. The FCMS calculates ZFW, CFCG, and indicates AFT CG Warning. The FCMS control refuel, transfers, CG, FQI and sensing. The FCMS only measures fuel quantity and gives indications.

What is the purpose of the trim fuel transfer system?. Control the center of gravity position. Control all transfers of engine feed. Burn the fuel from the trim tank.

Automatic transfer of fuel from the outer tanks to the inner tanks is performed by gravity. True. False.

If is necessary transfer to DMI any fuel valve actuator, you must remove the actuator and then: -Reinstall the actuator. -Install the connectors removed form the actuator,. -Align dowl and install the valve locking tool. - Install DUMMY plug and receptacle on the connectors removed from the actuator. -Reinstall the actuator. -Install DUMMY plug and receptacle on the connectors removed from the actuator.

Before preselect the Quantity on 990VU refuel panel, you first must do: Stop the pump on the fuel tanker unit. Start the pump on the fuel tanker unit. Lift the guard, then push (in) and hold the HI LEVEL TEST switch 3QJ for 10 seconds.

If the ADIRS does not send aircraft attitude information to the Fuel Control Monitoring System (FCMS). Thus, on battery refuel, theere coud be a difference up to 750 kg (1653.6445 lb) between the set fuel quantity and the actual fuel quantity. True. False.

The engine low pressure fuel valves are controlled by: Engine MASTER switch and ENG FIRE pb. BATT Switch. Engine MASTER switch. ENG FIRE pb.

The only component of the oil system controlled by the ECB is. Thermal bypass valve. Low oil press switch. De-oiling solenoid valve.

The Combustion Chamber design is. Reverse Flow Annular design. Direct Flow Annular design. Continuos Flow Annular design.

The APU fuel Low Pressure Valve opens when. The APU Start pushbutton is pressed. The APU Master Switch is set to ON. The batteries are set to ON.

To prevent an APU load compressor surge. The ECB controls the bleed valve to open. The ECB adjusts the IGVs actuator solenoid. The ECB controls the torque motor of the surge control valve to open.

APU fire on ground. The Automatic Fire Extinguishing Control Unit (AFECU) starts the extinguishing sequence. The Electronic Control Box (ECB) starts the extinguishing sequence. The APU FIRE P/B is released out automatically and extinguishing bottle is discharged.

Is used to store information regarding the health monitoring and life usage of the APU. Flight Warning Computer (FWC). Electronic Control Box (ECB). Data Memory Module (DMM).

The APU START sequence begins when. The APU Master switch is ON. The APU BAT pushbutton is ON. The APU Start pushbutton is ON.

Before the APU starter is energized. Both APU fuel pumps must be selected on. The APU bleed switch must be deselected. The APU air intake flap must be fully open.

The APU provides for automatic fire extinguishing. Only when selected to automatic by ground personnel. On the ground only. On the ground and in flight.

Which component controls and monitors the APU?. Electronic Control Box (ECB). Inlet Guide Vanes (IGV). Fuel Metering Unit (FMU).

Fuel muscle pressure is used to. Operate the Fuel Metering Valve (FMV). Operate the Surge Control Valve actuator & Load Compressor IGV actuator. Fuel flows to the combustion chamber through 12 fuel nozzles.

The AC powered aft auxiliary fuel boost pump from the APU operates whenever the APU is operating and no other pump is on. It has an alternate power source an the AC Static Inverter bus for battery-only starts. True. False.