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CT FEB 2013

1) Engine rumbles during starting and at low powercruise conditions.

a) Pressurizing & drain valve malfunction.

b) Cracked air duct.c) Fuelcontrol malfunction.

d) All of the above. (ref/12A/491)

2) Pressurerelief valve of bearing chamber does not operate , the flow rate of oil will????

a) Increase

b) Decrease

c) Remain same

3) Fuel additive used in GTE.

a) Fungicide

b) Anti-oxidizing agent, de-metal anticorrosiveagent

c) De-additive

d) All of the above

4) Dissolved Water in fuel is detected by

a) Aqua-disk capsule

b) Globus of water

c) Hazy look of fuel

d) Both a & c

5) Types of vibration indicatora) Velocity pick-up

b) Piezo-electric type

c) Both a & b

6) Methods of cooling turbine blade in GTE

a) Leading & trailing holes

b) Film cooling

7) Single crystal blade

a) Turbine blade

8) Igniter plug

a) Wide gap at low pressure

9) Compressor bleed air

a)middle & rear, increase air flow infront of inlet

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10) RPM hung up during turbine start.

11) Propeller slip

12) droop

13) engine trimming

a)on FCU change

14) Before shut down it is essential to run the engine atidle for few minutes.

A) To avoid seizure of turbine blades & turbine case

15) Propeller tracking

a) Constant pitch & controllable pitch at lower pitch.

16) Speed governor

17) Magnetic chip detector (MCD)

a) Bridge gap

18) Dual ball bearing?>

19) Cartridge filter at low pressure &screen filter atoutlet of pump at high pressure.

20) API number liquid lighter then water value

a) Greater than 10

b) Lower then 10

c) Remains up to 10

21) A flow of fluid metered by keeping the pressure drop ordifferential across the metering valve constant

while varying the orifice valve.

22) FADEC power supply

a) Dedicated EDG

23) High by pass engine usea) T/R uses secondary & primary air separately

24) Use of T/R should not cause Re-ingestion of hot gases

25) Thrust rating up to 31c

26) High viscosity index of oil

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27) OIL marked written on filter

28) Lubrication oil to bearings is provided through vane isidentified by

a) Thickest staticvane from lower position to bearing

29) Beta range

a) Propeller lever blocked

30) TSS

a) Auto feathering feature

31) Safety coupling

a) For NTS if it fails

32) Fire extinguisher in engine is distributed bya) Spray nozzles & perforated tubes

33) Thermocouple used for

a) Rate of temp rise detector

34) Turbojet engine largest take-off roll & less weight

35) EGT indication

36) Continues fire detection system

37) fin-wall type eutic salt bed

38) Thrust indication

a) EPR

39) Tail wind on trimming

a) Low trim

40) Auto ignition

a) In flight start possible

41) Modern type ignition system uses

a) Capacitor type

42) Igniter plug in jet engine

a) High intense spark ignition

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43) Centrifugal force tends to decrease blade angle

44) Annular inlet

a) At nose of fuselage

b) Just before start of fuselage

c) Both a & b

45) Nozzle distortion by can type combustion chamber

46) Advantages of annular combustion chamber &disadvantage of can type combustion chamber

47) Disadvantages of shrouded blades

a) Aero dynamic disadvantage due to thinner blade at tip

48) Full flow oil system

49) Functions of reverse flow combustion chamber

50) Wet thrust

a) period of water injected in jet engine for thrust

51) Roller bearing takes only

a) Radial load

52) Rise in temperature of compressor stages is equal todecrease of temp at turbine stages

53) Squeeze film bearing

54) Flat rated engine

a) Part throttle

b) More thrust by forward movement of the lever

c) all of the above

55) Variation of speed in convergent divergent exhaust ductobtained

56) Bell mouth duct to increase inlet pressure then ambientpressure at the inlet of compressor

57) In starter if carbon brushes is worn out

a) Engine will not start

58)boro-scope inspection

59) In impulse turbine inlet & outlet area of blades issame

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60) Impulse turbine blade diagram

61) Input of FCU

62) Mostly used fuel nozzle

a) 2 stageb) Duplex style

c) Both a & b

63) Which type of fuel nozzle atomizer is used

a) Swirl type

64) Equation for universal gas law

65) TSFC is directly proportional to efficiency

66) Efficiency of dual impeller is more than single impeller& dual impeller size is smaller than single

67) Maximum pressure at outlet of compressor

68) Centrifugal impeller takes air in from center &cause to moves outward at diffusion

69) Propfan Otis pg 2-7

70) Calorific value

71) Tip speed Ts=(pie*diam* RPM)/60 ( Otis pg 2-36)

72) Centrifugal compressor material

a) Aluminum alloy

b) Titanium wrought

c) Casting

73) tip speed in compressor blade

a) Mach 1 ( Otis pg 3-14)

74) Shroud aerodynamic drag reduces efficiency (pg 3-17)

75) In succeeding turbine stage pressure, velocity &temp

a) Increase

b) Decrease

c) Remain same

76) GTE is a open cycle (Trg pg155)

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77) Temp datum valve location

78) In combustion burner

a) Pressure remain constant & volume increase

79) TSFC calculation700*6.5=9100/475=0.5

80) Water wash after use of fire extinguisher methyl bromide

81) Exhaust duct

a) Straighten the airflow & increase velocity

b) Increase temp anda)