Tag Archives: turbine engine

The primary reason for a limitation being imposed on the temperature of the gas flow is to:

A: ensure that the maximum acceptable temperature within the combustion chamber is not exceeded.
B: ensure that the maximum acceptable temperature at the turbine blades is not exceeded.
C: prevent damage to the combustion chamber from overheating.
D: prevent damage to the jet pipe from overheating.

 

 

 

 

 

 

 

 

 

 

Answer:B

The final reserve fuel for aeroplanes with turbine engines is

A: fuel to fly for 45 minutes at holding speed at 1500 ft (450 m) above aerodrome elevation in standard conditions.
B: fuel to fly for 30 minutes at holding speed at 1500 ft (450 m) above aerodrome elevation in standard conditions.
C: fuel to fly for 45 minutes at holding speed at 1000 ft (300 m) above aerodrome elevation in standard conditions.
D: fuel to fly for 60 minutes at holding speed at 1500 ft (450 m) above aerodrome elevation in standard conditions.

 

 

 

 

 

Answer: B

In a gas turbine engine lubrication system, the oil to fuel heat exchanger provides:

A: automatic controlled fuel heating by engine oil to prevent icing in the fuel filter.
B: fuel cooling to prevent vapour locking interrupting the fuel supply to the nozzles.
C: fuel heating as required whenever fuel filter clogging is detected.
D: oil cooling through thermal exchange with the fuel.

 

 

 

 

 

 

 

 

Answer: D

The accessory units driven by the accessory gearbox of a turbo-jet engine are the: 1. thrust reverser pneumatic motors 2. AC generator and its constant speed drive (CSD) 3. oil pumps 4. hydraulic pumps 5. high pressure fuel pumps The combination regrouping all the correct statements is :

  1. thrust reverser pneumatic motors
  2. AC generator and its constant speed drive (CSD)
  3. oil pumps
  4. hydraulic pumps
  5. high pressure fuel pumps

 

A: 2, 3, 4, 5.
B: 1, 2, 3, 4, 5.
C: 2, 3, 4.
D: 1, 2, 3, 4.

 

 

 

 

 

 

 

 

Answer: A

Which of the following is true according to JAA regulations for turbo propeller powered aeroplanes not performing a steep approach?

A: Maximum use of clearway is 1,5 x runway.
B: Maximum Landing Distance at destination is 0,95 x LDA (Landing Distance Available).
C: Maximum Take-off Run is 0,5 x runway.
D: Maximum Landing Distance at the destination aerodrome and at any alternate aerodrome is 0,7 x LDA (Landing Distance Available).

 

 

 

 

 

 

 

 

Answer: D

In accordance with JAR-OPS 1, the commander of a turbojet engine aeroplane should have a final reserve fuel for:

A: 45 minutes of flight at cruising speed at FL140.
B: 45 minutes of flight at holding speed at 1500 ft above aerodrome elevation in standard conditions.
C: 30 minutes of flight at cruising speed at FL140.
D: 30 minutes of flight at holding speed at 1500 ft above aerodrome elevation in standard conditions.

 

 

 

 

 

 

 

 

Answer: D

Turbine blade stages may be classed as either “impulse” or “reaction”. In an impulse turbine stage:

A: the pressure remains constant across the stator blades and drops across the rotor blades.
B: the pressure rises across the stator blades and remains constant across the rotor blades.
C: the pressure drops across the stator blades and remains constant across the rotor blades.
D: the pressure remains constant across stator blades and rises across the rotor blades.

 

 

 

 

 

 

 

 

Answer: C