Embraer 190 - Fuel

Fuel is stored in two integral wing tanks, which are interconnected by a crossfeed valve. This means that the fuel is distributed between these two tanks and can be transferred from one tank to another using the crossfeed valve.

The crossfeed selector knob is set to LOW 2 position, which means that the crossfeed valve is opened and AC PUMP 1 is activated. This allows fuel to be fed from wing tank 1 to both engines. Therefore, the correct answer is wing tank 1.

When the wings fuel imbalance reaches 360 kg, which is its maximum operational limit, the EICAS CAUTION message FUEL IMBALANCE is displayed.

The collector tank keeps the fuel pumps submerged, ensuring a constant fuel flow to the respective engine. This tank collects and stores fuel from various sources, such as fuel tanks, and then distributes it to the engines as needed. By keeping the fuel pumps submerged, it helps prevent any interruptions or fluctuations in fuel flow, ensuring a steady supply of fuel to the engine.

The wing tanks AC electric fuel pump serves as a backup pump in the event of ejector pump failure. This means that if the ejector pump, which is responsible for drawing fuel from the tanks, fails to operate properly, the AC electric fuel pump can take over and ensure a continuous fuel supply to the aircraft's engines.

The low level warning message activation point is set at 400 kg of fuel in the associated wing tank under normal conditions.

If there is up to 2800 kg of fuel inside the tank, it is possible that the fuel level equivalent to the low level warning activation point will be reached as the fuel level inside the collector box decreases. This will cause the FUEL 1 (2) LO LEVEL warning EICAS message to display, indicating that the fuel level is below the low level sensor. Therefore, even if the fuel quantity indication on the EICAS or MFD Fuel System Synoptic Page shows a higher amount, the EICAS WARNING message FUEL 1 (2) LO LEVEL may still display.

A surge tank is designed to collect any fuel that may enter the vent system during wing down and uncoordinated maneuvers. This helps prevent fuel from entering the engine and causing damage. A collector tank, on the other hand, is not specifically designed for this purpose and may not effectively collect fuel during such maneuvers. Therefore, a surge tank is the correct answer.

A vent system is designed to ensure that the differential pressure between the tank and surrounding environment remains within structural limits and to prevent fuel spillage during flight maneuvers and hard braking. This system allows for the release of excess pressure and prevents the tank from becoming over-pressurized, which could lead to structural damage or fuel leakage.

Scavenge jet pumps are responsible for maintaining the fuel level in the collector tank. This ensures that there is a constant flow of fuel to the engine during normal flight.

When the wings fuel imbalance reduces to 45 kg, the EICAS ADVISORY message FUEL EQUAL – XFEED OPEN is displayed, indicating that there is no fuel imbalance condition and the crossfeed valve is open.

The right wing AC electric fuel pump (AC PUMP 2) is powered by the AC ESS BUS.

When the crossfeed selector knob is set to LOW 1 position, it opens the crossfeed valve and activates AC PUMP 2. This means that fuel is being transferred from wing tank 2 to both engines, feeding them. Therefore, the correct answer is wing tank 2.

The primary wing fuel pump is a venturi ejector pump, also known as a jet pump. This type of pump uses the Venturi effect to create a pressure difference, which draws fuel from the tank and ejects it into the engine. It does not rely on electricity and is commonly used in aircraft to provide fuel flow in low-pressure systems.

The Fuel Low Level sensor is independent of the fuel quantity indication system. This means that it operates separately from the system that provides information about the fuel quantity in the tanks. The sensor is located in the collector box and when the fuel level in the box falls below the sensor level, it sends a signal to the warning system, triggering the FUEL LO LEVEL warning message on the EICAS (Engine Indicating and Crew Alerting System).

If the airplane is subjected to attitudes greater than 15° nose up or down, uncoordinated maneuvers, or negative g's, it can lead to engine flameout due to fuel starvation. This means that if the aircraft is tilted at an angle greater than 15° in either direction, or if it is performing maneuvers that are not coordinated or involves negative g-forces, there is a risk of the engine losing fuel supply and shutting down.

The left wing fuel tank contains several pumps: the ejector fuel pump, the wing AC electric fuel pump, and three scavenge ejector pumps. These pumps are responsible for ensuring a constant flow of fuel to the engine and maintaining proper fuel pressure. The ejector fuel pump uses the Venturi effect to draw fuel from the tank, while the wing AC electric fuel pump is powered by the aircraft's electrical system. The three scavenge ejector pumps help to remove any excess fuel or vapors from the tank. Together, these pumps ensure the efficient and reliable operation of the aircraft's fuel system.

Three magnetic level indicators (dripsticks) mounted under each wing provide an alternate means for fuel measuring.

The maximum fuel quantities indicated to the flight crew are 6550 each tank and 13100 total. This means that each tank can hold a maximum of 6550 units of fuel, and the total fuel capacity of both tanks combined is 13100 units.

The FUEL USED indication is automatically reset by the FMS upon the first engine start.

Setting the AC PUMP 1 or 2 selector knob to any position different than AUTO overrides the fuel crossfeed pumps command. This means that if the selector knob is set to ON, for example, the fuel crossfeed pumps will not operate automatically as they would in the AUTO position.

The left wing AC electric fuel pump (AC PUMP 1) is powered by AC BUS 1.

The correct answer is that the wing tanks AC electric fuel pump supplies fuel to the onside engine during engine starts, the cross side engine during crossfeed operations, and the APU when the engine is not running.

When the crossfeed knob is selected to LOW 1 or LOW 2, the amount of fuel supplied to the lower level side is higher than the actual fuel burn of the engine on that side. This means that more fuel is being supplied to the lower level side than is being consumed by the engine. This excess fuel then flows from the lower level tank to the higher level tank, causing fuel to be transferred from one tank to the other.

If any scavenge pump stops transferring fuel to the Collector Box, the fuel contained in the Collector Box flows out so that the fuel level inside the Collector Box and the rest of the tank reaches the same level. This means that the fuel will flow out of the Collector Box and into the rest of the tank, equalizing the fuel levels.

The right-wing fuel tank contains several pumps: the ejector fuel pump, the wing AC electric fuel pump, three scavenge ejector pumps, and the DC electric fuel pump. These pumps are responsible for various functions such as transferring fuel, maintaining pressure, and scavenging excess fuel. Therefore, all of these pumps are present in the right-wing fuel tank.

The correct answer is "One." This suggests that there is only one water drain valve in each tank, and it collects water by gravity.

The correct answer is "One." This suggests that there is only one additional independent fuel low-level sensor installed in each tank to detect the fuel low-level condition.

The DC electric fuel pump is powered by the DC ESS BUS 2. This bus provides electrical power to essential systems in the aircraft, including the fuel pump. The pump is installed in the right wing tank and is used for normal APU operation and engine start when AC power or the AC fuel pump is not available. It can be used both in flight and on the ground.