GAS TURBINE FUEL SYSTEM – Air – DGCA Question Bank For Politics

#1. With an increase in altitude the boiling point of fuel will:

Stay the same.

Increase.

Decrease.

Increase up to FL80 then remain the same.

#2. Modern jet aircraft fuel tanks are pressurised:

By air from the engine compressor to prevent cavitation.

By air from the air conditioning system to prevent cavitation.

By ram air to prevent cavitation.

By ram air to stabilise the boiling point.

#3. Fuel is heated from which of the following?

Air conditioning air.

Air from the compressor.

Air from the Bootstrap.

Air from the turbine.

#4. Fuel is heated to:

Prevent waxing.

Ensure vapour losses are minimised.

Make it more viscous.

Make it easier to flow under all conditions.

#5. Fuel booster pumps are situated in:

The fuel tanks.

In the line between the main fuel tanks and the engine.

Low pressure side of the engine.

High-pressure side of the engine.

#6. In a fuel cooled oil cooler the is maintained than the ____.

Fuel pressure, higher, oil pressure

Oil pressure, lower, fuel

Fuel pressure, same, oil pressure

Oil pressure, higher, fuel pressure

#7. In a high by pass engine fuel pumps are driven by:

High pressure turbine.

High pressure compressor.

Low pressure compressor.

Intermediate compressor.

#8. The effect of the high pressure compressor outlet pressure exceeding its maximum value would be:

Pressure sensor input to fuel control unit (FCU) FCU reduce fuel, reduce RPM.

Pressure sensor input to fuel control unit (FCU) FCU increase fuel, increase RPM.

Pressure sensor input to fuel control unit (FCU). Bleed valve open, bleed off excess volume of air.

Pressure sensor input to fuel control unit (FCU). Bleed valve open, bleed off excess pressure.

#9. Which of the following is a normal stopping device for a gas turbine?

LP shut off valve close.

Fuel tank booster pumps select off.

HP shut off valve close.

Isolate electrics from engine.

#10. Which of the following is a correct statement?

When an engine is running, the combustion chamber drain is closed by a pressure operated NRV.

When an engine is running, the combustion chamber drains tank is opened by a pressure operated NRV

When the engine is shut down the drains tank closes to minimise fuel losses.

When the engine is shut down, residual fuel is syphoned directly back to the fuel tanks to minimise fuel losses.

#11. The fuel flow-meter is situated:

Between LP pump and the FCOC.

Between LP pump and HP pump.

Just after FCU.

Between HP shut off valve and fuel nozzles.

#12. An overheat in the turbine will result in:

An electrical signal from the thermocouple sent directly to the FCU and fuel being reduced.

An electrical signal from the thermocouple amplified then sent directly to the FCU and fuel being reduced.

Pilot observing overheat on temperature gauge then subsequently throttling back the engine, therefore reducing fuel.

Pilot observing overheat on temperature gauge then subsequently increasing RPM to increase airflow, to increase cooling air, to decrease turbine temperature.

#13. Aircraft flying at FL 420. If the booster pumps feeding the engine cease to work:

The engine would close down immediately.

The LP pump will draw fuel from the tank, but there may be a possibility of cavitation due to the low pressure and low boiling point of the fuel.

The LP pump will draw fuel from the tank, but there may be a possibility of cavitation due to the low pressure and higher boiling point of the fuel.

The LP pump will draw fuel from the tank, but there may be a possibility of cavitation due to the higher pressure and higher boiling point of the fuel.

#14. The fuel cooled oil cooler:

Heats the oil and cools the fuel.

Heats the fuel only.

Cools the oil only.

Heats the fuel and cools the oil.

Dgca Question Bank For Pilots

Results