Paper 3 ct JUNE 2015.pdf

CT June 2015(www.dgcaquestionpapers.blogspot.com)

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1. Where do stress rupture cracks usually appear on turbine blades?

A. Across the blade root,parallel to the fir tree.

B. Along the leading edge,parallel to the edge

C. Across the leading edge or trailing edge at a right angle to the edge length.

2. Reduce the Blade vibration and improve the airflow characterstics in GTE are brought about by

A. Fir tree blade attachment.

B. Impulse type blade

C. Shrouded turbine rotor blades.

3. Which of the following factors Affect the thermal efficiency of the Engine?

1.Turbine inlet temperature 2.compression ratio 3.speed of aircraft

4.Turbine and compressor efficiency. 5.Ambient temperature.

A. 3,4,5

B. 1,2,4

C. 1,2,5

4. A cool off period prior to shutdown of the engine is accomplished in order to..

A. Prevent vapor lock in the fuel control/fuel lines.

B. Prevent seizure of the engine bearings.

C. Allow the turbine wheel to cool before the case contracts around it.

5. A transfer of metal from one surface to another surface, severe condition of chaffing or fretting occurs is

called

A. Scoring

B. Brinelling

C. galling

6. High Bypass Tubrofan engine thrust is the indication of..

A. fanspeed.

B. IEPR

C. EPR

D. Both 1 & 2.

7. Fire detection system that will not test due to a broken detector element are the..

A. Kidde system and Lindberg system

B. Kidde system and Fenwal system

C. Thermocouples system and Lindberg system.

8. In a supervisory EEC system,any fault in the EEC that adversely affect the engine operation

A. Causes redundant or backup units to take over and continue normal operation

B. Usually degrades the performance to the extent that continued operation can cause damage to the

engine.

C. Causes an immediate reversion to control by hydromechanical fuel control unit.

9. The purpose of the Bellmouth compressor inlet is to..

A. Provide an increased ram air effect at low airspeeds.

B. Maximize the aerodynamic efficiency of the inlet.

C. Provide an increased pressure drop in the inlet.

10. How is the aircraft electrical power for propeller deicer system transferred from engine to propeller hub

ass.?



A. By slip rings.

B. By segment plates

C. By flexible electrical connectors.

11. Propeller aerodynamic imbalance can be largely eliminated by..

A. Correct blade contouring

B. Static balancing

C. Angle setting

D. Both 1 & 3.

12. When necessary , APU engine cooling before shutdown may be accomplished by..

A. Unloading the generators

B. Closing the bleed air valve

C. Opening the bleed air valve.

13. APU equipped with a free turbine and load compressor, the primary function of the load compressor is

to

A. Provide air for combustion and cooling in the engine gas path.

B. Supply the turning force for operation of the APU generators..

C. Provide bleed air for aircraft Pneumatic systems

14. What are the engine parameters are to be monitored to determine the aerodynamic performance of the

engine?

A. EPR, FUEL flow, Vibration amplitude, Oil consumption.

B. EPR, FUEL flow, EGT, Oil consumption.

C. EPR, FUEL flow, EGT, Throttle position.

D. EGT, FUEL flow, Vibration amplitude, throttle position.

15. The AME observes that that idle TGT, same even after substaintial change,and the engine operation is

normal at high RPM, the snag is at

A. CIT system.

B. CDP system.

C. FCU temperature compensation.

D. Throttle rigging mis match.

16. A system of Routine comparision of engine performance parameters with a red line, Same parameters

established when the engine was newly overhauled is called

A. On condition maintenance

B. Power assurance check

C. Trend monitoring.

17. The Basic formula for the appropriate thrust of a Gas Turbine engine is Fn = Wa/g(V2-V1 ) in this V1

represents

A. Speed of aircraft.

B. Velocity of exhaust Gas at nozzle.

C. Initial velocity of gases.

D. Both 1 & 3 are correct.

18. ACC stands for.

A. Active clear control



B. Active control clearance

C. Active clearance control

19. Engine Rumbles during starting and at low cruise conditions .The possible cause is.

A. P & D valve malfunction

B. Cracked air duct.

C. Fuel control malfunction

D. All.

20. Purpose of exciter unit...

A. Convert 28V DC into 115V AC.

B. Convert 28V DC into high voltage.

C. Convert 115V AC into high voltage.

D. Both 2 & 3.

21. Input of FADEC.

A. Aircraft main electrical system.

B. Aircraft 36 volt electrical system.

C. Aircraft engine driven generator.

22. Purpose of sprag clutch in Air turbine Starter.

A. Non reversible wheel rotate only in one direction.

B. Non reversible wheel rotate in both direction.

C. Reversible wheel rotate in one direction.

23. MTCS inspection of ignition harness

A. Check for crack, discontinuity

B. Oil deposit on harness

C. Chaffing

D. All

24. In which engine EPR indicate on flight deck..

A. Turbofan & turbojet.

B. Turbofan & turboprop

C. Turboprop & turboshaft.

25. starter not continuous start

A. Engine accelerate more than 1 minute.

B. Engine exceed EGT limits

26. Engine start but not accelerate to idle RPM.

A. Low voltage

B. Low current

C. High intensity voltage.

27. NO. of Engine bearing depends upon.

A. Length of the engine.

B. Spool of the engine

C. Temperature

D. Operating speed.

28. The force act on the propeller which control the blade angle

A. Centrifugal twisting moment



B. Oil pressure.

C. Torque of propeller.

D. Both 1 and 2

29. In turboprop engine Power units fails to turn over during attempt start..

A. No air supply

B. Propeller brake locked.

C. Both A & B.

30. Engine has Low RPM,EGT and fuel flow When set to expected EPR

A. EPR indication has high reading error.

B. EPR fluctuates.

C. EPR indication has low reading error.

31. MTCS during Engine overhaul.

Inspection, cleaning, disassembly, repairing, assembly, testing, storage.

Cleaning, inspection, repairing ,disassembly, testing, assembly, storage.

Disassembly, cleaning, inspection, repairing, assembly, testing, storage.

Assembly, cleaning, inspection, repairing, disassembly, testing, storage.

32. purpose of straitening vanes in exhaust nozzle..

Turn the air to 45 to axial direction.

Reduces air disturbances.

Decrease the velocity and increase the pressure.

All.

33. High pressure turbine is cooled by

By using bleed air from HPC.

By Fan cooled air.

By atmospheric air.

34. principle forces acting on the propeller.

Centrifugal force.

Torque bending force.

Aerodynamic twisting force

All.

35. The hub assembly of propeller consist of..

Blade assembly.

Spider

Barrel assembly.

all

36. MTCS Under speed condition..

Centrifugal force exerted by flyweights.

Speeder spring lower the pilot valve.

Both A & B.

37. Hung start occurs..

Rich/ air fuel mixture.

Insufficient power to the starter.

Both A & B.



38. Water injection is used on

Low engine power

High engine power

Idle RPM

None of the above.

39. If engine thread are stripped and drill out it..,then..

Threaded bushing

Oversize stud.

Insert helicoil.

All.

40. Great influence on structural design

Compressibility effect

Thermal barrier

Sonic barrier.

All.

41. At Unsafe humidity condition..

Pink

Blue

Green

Yellow.

42. For better fuel automization

Two stages fuel nozzles

Swirl type fuel nozzles

Duplex fuel nozzle.

Both A & C

43. Which type of seal is re used.?

Carbon / rubbing seals

Metal type.

Rubber type.

Both 1 & 2.

44. Which type of Air filter replace periodically?

Cartige type

Disk type.

Screen type.

All.

45. If the temperature of oil is lower than Normal temperature, oil is by passed from

Thermostatic valve

By pass valve

Pressure sensing unit.

Both 1 & 3.

46. MTCS spectrometric oil analysis programme.

Metal content wear out.

Type of metal wear out.



Both A & B.

47. Compresibility phenomenon

Sonic & subsonic velocities create shockwaves.

Sonic & supersonic velocities create shockwaves.

Subsonic flow velocities create shock waves.

48. Distance of propeller would have to advance in one revolution to produce No thrust is called

Geometric pitch

Effective pitch

Zero pitch

Experimental mean pitch

49. Distance of propeller element should advance in one revolution to produce is called

Geometric pitch

Effective pitch

Zero pitch

Experimental mean pitch

50. Diffrence between Turbo prop & turbine engine.

Arrangement of compressor

Gas flow of combustion chamber

Number of Turbine stages

all

51. The power section of Gas turbine engine is.

Compressor.

Reduction gear box.

Torque meter assembly.

All.

52. prevent for combat stall

Fixed IGV.

Variable stator vanes

Long exhaust duct.

All.

53. Static thrust is measured by

Strain guage.

Dynamometer.

Microammeter

54. The force act on the bearing, and it permanently damage

Dynamic load.

Radial load.

Thrust load.

Static load.

55. Regarding NTS back up

Auto feathering

TSS

Safety coupling.



56. Location of fly weight in governor

Governor inside & upward position.

Governor inside & downward position.

Governor outside & downward position.

Governor outside & upward position.

57. Fuel/oil system valve used to prevent the spillage of oil.

Staging valve.

Check valve

Pilot valve.

58. Which cleaning solution must be avoided for cleaning of parts made of titanium?

Organic solvents.

Trichloroethylene

Cholrine base solvents

Both B & C

59. An Engine trimming is used for..

Up trim engines to compensate for small inlet duct losses or air bleed losses.

Compensate for any thrust deterioration which might result from accumulation deposits of dirt

and/or scale on the compressor blades.

60. When the CDP sensor fail during cruise condition the high power If engine will

Surge

Flame out

Decelerate the idle RPM.

61. If weight of Fuel= 700 gallons., and Fn= 9100 lbs. then Find the SFC?

[1 gallon=6.5 lbs/hr.]

0.5 lbs/hr

13lbs/hr

2lbs/hr.

62. MTCS.

Load control valve adjusted only after shutdown of APU

Surge control valve works in conjuction with load control valve.

APU fuel governor must be adjusted in clockwise to increase the fuel flow.

All.

63. Non dimensional parts inspection can be done by

Non florescent particles

Nonfloroscent dye penetrant

Boroscopes

All

64. If the control cabels are used, the term CUSHION means.

When the control lever on the unit hits its stop before the control lever in the cabin hits its stop.

65. In Fuel system If the continuity found in Magnetic chip detectors..

Magnetic chip detector must be replaced.

Send the MCD for SOAP test.



Both.A & B.

66. MTCS .. Jetcal Analyzer..

Check the aircraft EGT system without running the engine.

Check the aircraft EGT system during engine run up.

Check continuity and resistance of the EGT circuit.

All.

67. purpose of shroud ring

To prevent the escape of exhaust around tip of blade

To prevent blade tip damage

Provide streamline flow of hot air

all

68. Auto Feathering system normally used in

Takeoff

Descent

All.

69. When ambient temperature rises above the sea level standard 15 C , rated thrust can be maintained up to

given temperature increase by advising the throttle is

Full throttle thrust

Flat rated thrust.

Maximum cruise thrust

All

70. Good turbine engine operating techniques are.

Demand maximum power unless absolutely necessary.

Start as slow as possible to eliminate high temperature for long periods of time.

Warm up and stabilize engine temperature for a few minutes at above idle to prevent rubbing and

other damage.

All

71. when ever engine Fails to light..

Shut off the fuel and ignition and continue turning the compressor over with the starter for 10 to 15 sec.

clear out trapped fuel.

If not done, allow a 30 sec fuel draining period before attempting another start.

The starter may be re engaged at any time after the compressor has decelerated to 40% RPM or less.

All.

72. When air bleed from another engine used to operate the starter , Caution necessary

Engine is turning over fast enough to provide an adequately supply of pr. air.

Engine should never be pemitted to take longer than 1 min. tto accelerate idle RPM.

In the event of torching , higher than usual exhaust gas temperature.

1 & 3

73. postion the airplane during ground operation

A/C should be run an concentrate surface.

Keep the area to the rear of engine clear of flameable material.

A/C should face into the wind.



All.

74. The depression in N2 and the increase in EGT are characteristic of..

LPT

HPT

Combustion chamber.

75. When a monitoring plot shows a trend in only one parameter cause is..

EPR

HPT

Istumentation Error.

76. The progressive change in vibration level

Broken turbine blade

Failure of bearing

1 & 2.

77. the general pattern to be expected in failures affecting only the LPT.

N1 marked shift

N2 decrease

EGT & fuel flow decerease

All.

78. Engine system flushed with preservative of.

Oil system

Fuel system

Both A & B

79. Radioactive iridium pill 92 placed in the centre of the engine with a film wrapped around the outer casing

to check..

Combustion chamber

Nozzle vanes for blowing

Compressor blade

All

80. Net thrust is ..

Difference in the velocity b/w incoming & outgoing air.

Gross thrust minus ram drag.

Both.

81. In case of bearing cleaning of inspection..

Bearing require special handling.

Bearing can become magnetized in service & may have to demagnetized in order to properly clean out of

magnetic particle.

Split bearing must be kept as unit.

All.

82. Combustion chamber ceramic coated cleaning done by..

Trichloroethlyne

Tumbling

Cleaning and stripping method uses high pressure up to 55000 psi water stream.

All.



83. Factor which is required to establish TBO

Type of operation & use.

Servicing facilities and experience of maintenance personnel

Total experience gained with the particular engine

All.

84. Tempratutre datum valve is located

B/w fuel control & fuel manifold.

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Paper 3 ct JUNE 2015.pdf