PPLANT2 Exam

1. The starting procedure for all jet engines is basically the same, but can be achieved through various methods except

Pneumatic

2. The electric starter is usually an electric motor coupled to the engine through a reduction gear and ratchet mechanism, or clutch, which automatically disengages after the engine has reached a self-sustaining speed

Direct Current (DC)

3. Provides a high-power output and gives rapid starting characteristics. It has a turbine that transmits power through a reduction gear to the engine

Gas turbine starting

4. Is sometimes used on military engines and provides a quick independent method of starting. An electrically fired detonator initiates the burning of the cartridge, which is usually the method of this starting

Cartridge starting

5. Is used on most commercial and some military jet engines. It has many advantages over other starting systems and is comparatively light, simple, and economical to operate

Gas turbine starting

6. Is a starting system used for some jet engines and is completely self-contained. It has its own fuel and ignition system, starting system (usually electric or hydraulic), and self-contained oil system

Gas turbine starting

7. Is controlled by an electrical circuit that also operates hydraulic valves so that on completion of the starting cycle, the pump/starter functions as a normal hydraulic pump

Hydraulic starting

8. Under the ignition system, each H.E. ignition unit receives a voltage supply, controlled by the starting system, from the aircraft electrical system

High

9. Ignition units are rated in

Joules

10. In a Relight Envelope, what is given on the x and y axis

Altitude and Engine speed

11. In a gas turbine engine, what drives the main fuel pumps

Turbine

12. In an air-to-liquid heat exchanger, where is the source of the hot air that is used to heat the fuel

Compressor

13. It is installed between the supply tanks and the engine fuel system to protect the engine-driven fuel pump and various control devices

Micron filter

14. Fuel nozzles that are installed in a mounting pad, which is provided for attachment of the nozzles to the case or the inlet air elbow, with the nozzle near the dome

Internal mounting

15. It creates primary and secondary fuel supplies that are discharged through separate manifolds, providing two separate fuel flows

Flow divider

16. Metered fuel from the fuel control enters the inlet of the flow divider, passes through an orifice, and then on to the

Primary nozzle

17. In this segment, when the fuel flow increases and reaches maximum flow, approximately 50 percent of the fuel is passing through here

Secondary line

18. In this segment, the fuel that flows in it is required for starting and altitude idling

Primary line

19. It drains fuel that accumulates in the combustion chamber after each shutdown and fuel that may have accumulated during a false start

Combustion chamber drain valve

20. If the combustion chamber is of the basket or annular type, the fuel merely drains through and accumulates in a trap in the bottom of the chamber housing, which is connected to the drain line

Drain line

21. In a turbojet engine, the turbine absorbs approximately what percentage of the total pressure energy from the exhaust gases

60-80%

22. This component transforms the kinetic energy in the hot exhaust gases into mechanical energy to drive the compressor and accessories

Turbine

23. Which of the following is not a function of the turbine section

Provides the final boost to the hot exhaust gases

24. Which of the following are elements of a turbine section

I, II, IV, and V

25. Flanges are located on which part of the turbine case

On the front and rear end

26. This component is exposed to the highest temperatures in a gas turbine engine

Turbine Nozzle

27. Which of the following statements is incorrect

The inner and outer shrouds are encased by inner support rings only

28. Which of the following statements is correct

II and III

29. What are the two types of exhaust nozzle designs used on aircraft engines

I and III

30. Which of the following statements about the exhaust section is correct

III and IV

31. How much horsepower can the accessory drive system require from a large bypass engine

500

32. How is power typically obtained to drive the accessories in a turbine engine

From the engine's main power shaft

33. What type of gears are used to transmit power from the engine's main power shaft to the accessory shaft

Helical gears

34. What is the primary advantage of using a single-stage rotor turbine

Lower weight and compactness

35. Which type of turbine blade design is primarily shaped like a bucket at the blade root and an airfoil toward the outer end

Impulse-reaction blade

36. What topic is PowerPoint 67

Turbine, Exhaust, and Accessory Section

37. What envelope is used for engine restart during flight

Relight Envelope

38. The normal spark rate of a typical MIMO system is

60 and 120 sparks per minute

39. It is similar in operation to the conventional electrode and body for the spark to cross in a reciprocating engine spark plug but has a larger air gap between them

Shunted surface discharge type

40. Has the end of the insulator formed by a semi-conducting pellet, which permits electrical leakage from the central high-tension electrode to the body

Shunted surface discharge type

41. Considering level flight, thrust in a turboprop aircraft can be controlled by adjusting the fuel flow to the engines and by adjusting the

Propeller blade angle

42. It occurs when the amount of oxygen in the air supply is insufficient to support combustion and when the mixture is cooled below the combustion temperature by the excess fuel

Rich blowout

43. It occurs if the fuel quantity is reduced proportionally below the air quantity

Lean flame-out

44. These are responsible for atomizing or vaporizing the fuel so that it ignites and burns efficiently

Fuel nozzle

45. Fuel controls have two sections, which are

Computing and metering

46. It has no electronic interface assisting in computing or metering the fuel flow. It is generally driven by the gas generator gear train of the engine to sense engine speed

Pure hydromechanical fuel control

47. What is an EEC

Electronic Engine Control

48. What is an EFCU

Electronic Fuel Control Unit

49. It allows fuel to bypass the fuel filter when the pressure drop across the fuel filter is excessive

Fuel bypass valve

50. What is FADEC

Full Authority Digital Engine Control