ATA 00 1. Which A/C the lowest fuel consumption? A. A319

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ATA 00

1. Which A/C the lowest fuel consumption?

A. A319

B. A320

C. A321

( Training manual – ATA 00)

2. For A/C A319/A320/A321, what is A/C higher?

A. The same

B. A319

C. A321

(A319/A320 = 12,08m; A321 = 12.1m - AMM 06-10-00 PB 001).

6. The A319, A320 and A321 (A320 family) are:

A. Single Aisle, twin-engine subsonic medium range aircraft,

B. Single Aisle, twin-engine subsonic short range aircraft,

C. Double Aisle, four-engine subsonic long range aircraft.

7. How many jacking points equipped with jacking pads are used to lift the

aircraft?

A. Two,

B. Three,

C. Four.

8. When you work on aircraft, make sure that you obey all the:

A. AMM safety procedures,

B. Team leader ordered,

C. Instruction of experience person.

9. In the AMM tasks, “WARNING” is mean:

A. Calls attention to use of materials, processes, methods, procedures or limits

which must be followed precisely to avoid injury of death to persons

B. Calls attention to methods and procedures which be followed to avoid damage

to equipment

C. Calls attention to methods which make the job easier or provide

supplementary or explanatory information

(6. Definition of Terms

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An AMM Task can contain WARNING/CAUTIONs. They are located directly before the

text to which they relate.

-

WARNING/CAUTIONs at the beginning of a Task (immediately after the Task title) are

applicable to all the Task.

-

WARNING/CAUTIONs at the beginning of a Procedure paragraph are applicable to all

the Procedure.

-

WARNING/CAUTIONs immediately before a work step are applicable to that specific

work step.

The following terms are used in the AMM and are defined as follows:

NOTE:

Calls attention to methods which make the job easier or provide supplementary or

explanatory information.

WARNING : CALLS ATTENTION TO USE OF MATERIAL, PROCESSES, MET

HODS, PROCEDURES OR

LIMITS WHICH MUST BE FOLLOWED PRECISELY TO AVOID I

NJURY OR DEATH TO

PERSONS.

CAUTION : CALLS ATTENTION TO METHODS AND PROCEDURES WHICH MU

ST BE

FOLLOWED TO AVOID DAMAGE TO EQUIPMENT.

AMM: Introduction – Paragraph 6)

10. The captain and first officer seats can be:

A. Controlled electrically only.

B. Controlled mechanically only.

C. Controlled either electrically or mechanically.

11. Access doors and panels are identified by:

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A. The number of the zone in which the panel is located followed by a two-letter

suffix.

B. The number of the zone in which the panel is located followed by one letter

suffix.

C. A two-letter followed by the number of the zone in which the panel is located

suffix.

12. The reference (station 0) for all structural measurements in the X axis is

located.

A. At the rib 1 of the aircraft.

B. 100 in (254cm) forward of aircraft nose.

C. 251.2 in. (638.2 cm) forward of the aircraft nose.

13. The station number is:

A. The distance in millimeters of a cross section from a reference point.

B. The distance in inches of a cross section from a reference point.

C. The distance in millimeters of a cross section from the A/c axis.

ATA 26

14. How many fire extinguisher bottles for cargo extinguishing system of

A319?

A. 1

B. 2

C. 3

15. Where Fire extinguisher bottle for cargo extingushing system of A319 is

installed?

A. From the FWD cargo compartment

B. From the AFT cargo compartment

C. From the BULK cargo compartment

16. How do you know drop pressure of the cargo fire extinguisher bottle?

A. In case of bottle pressure drop, the SDCU sends signals to the ECAM and

CFDS.

B. Must check indication on the Bottle

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C. Must remove the botlle and weighing.

17. For enhance System, the smoke detection function is of:

A. FWC

B. CFDIU

C. CIDS

(AMM 23-73-00 PB 001)

18. How many smoke detectors are installed on A319 AFT cargo

compartment?

A. 1

B. 2

C. 3

19. A320 AFT cargo compartment have 2 smoke detectors, if only one cargo

smoke detector detects smoke and SDCU checks find secondary smoke

detector operate normally, what happen?

A. There is no SMOKE warning in the cockpit

B. The SMOKE warnings are activated

C. Cargo fire extinguisher bottle discharge automatically.

20. For enhance CIDS, if SDF detects smoke in the LAV:

A. The page FAP will come up automatically on the FAP regardless of any other

previous selected page

B. Have massege on ECAM

C. The A red indication SMOKE DETECTED on the Flight Attendant Panel

(FAP) will come up automatically on the FAP regardless of any other previous

selected page and have massege on ECAM

(AMM 26-17-00-00)

21. For enhance CIDS, In case of smoke detected in the Lavatory, If smoke is

no longer detected, how reset warning?

A. pushing the Smoke Reset button on the FAP touchscreen

B. pushing the SMOKE RESET hard key on the FAP subpanel

C. Reset CB of CIDS directors

22. For enhance CIDS, cargo smoke detector is:

A. Connect direct to SDF in director by CAN BUS

B. Connect to SDF in director via lavatory smoke detector

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C. Connect direct to FWC

23. For classic CIDS, cargo smoke detector is

A. Connect direct to SDF in director by CAN BUS

B. Connect to SDCU in director via lavatory smoke detector

C. Connect direct to FWC

24. The engine fire protection is fulfilled by:

A. The FIRE detection system only

B. The FIRE detection system and the FIRE extinguishing system

C. The FIRE extinguishing system only

ATA 28

25. How many fuel pumps are installed on center tank of A319?

A. 1

B. 2

C. 3

26. For A319, when is the fuel in the outer cell used?

A. the fuel load in the center tank decreases to a low level

B. the fuel load in the inner cells decreases to 500 kg

C. the fuel load in the inner cells decreases to a low level

27. When the engine FIRE pushbutton is released out:

A. The related Engine Low Pressure (LP) valve is closed immediately.

B. The related Engine Low Pressure (LP) valve is closed after 150 seconds

C. The related Engine Low Pressure (LP) valve is closed after 200 seconds

28. For enhance system, the jet pumps is replace for:

A. Wing pumps

B. Center pumps

C. Jet pumps are not applied for fuel supply system.

29. The fuel system also feeds the APU directly:

A. from the left side

B. from the right side

C. from the left side and right side

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30. When the APU FIRE pushbutton is released out:

A. The related APU Low Pressure (LP) valve is closed immediately.

B. The related APU Low Pressure (LP) valve is closed after 150 seconds

C. The related APU Low Pressure (LP) valve is closed after 200 seconds

31. For A321, the wing tanks are:

A. not divided

B. divided to inner cell and outer cell

C. not divided between center tank and wing tank

32. The fuel tanks are vented into:

A. The vent surge tanks.

B. The cabin.

C. The cargo

33. Which tank is emptied first?

A. Center tank

B. Wing tank(A321)

C. Inner tank(A320)

34. From the Engine, recirculated fuel returns to:

A. Wing tank

B. Center tank

C. Dry tank

ATA 30

35. CFM LEAP-1A Engine Nacelle Anti - Ice, the hot air leak detection is done

by:

A. Two pressure transduce

B. A dual temperature sensor

C. One pressure sensor and one temperature sensor

36. For CFM LEAP-1A Engine, Hot air for the Nacelle anti - ice system is

supply by:

A. A dedicated HPC 4th Stage bleed

B. A dedicated HPC 7th Stage bleed

C. A dedicated HPC 10th Stage bleed

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37. How many Engine Anti – Ice Pressure Regulating Shut-Off Valve

(PRSOV) installed on each CFM-LEAP-1A Engine?

A. 1

B. 2

C. 3

38. For CFM LEAP-1A Engine, When the Engine Anti – Ice Pressure

Regulating Shut-Off Valve (PRSOV) has failed

A. PRSOV can be manual set locked in open position

B. PRSOV not can be manual set in locked position

C. PRSOV automatic set in locked position

(AMM 31-21-00-040-805)

ATA 36

39. For CFM LEAP-1A Engine, when one BMC has failed

A. Remain BMC can control & monitor both side

B. Related PRV close

C. Related PRV open

40. For CFM LEAP-1A Engine, the position of the Engine Bleed Air System

valve is monitored by:

A. Valve position switch

B. Pressure sensor

C. Temperature sensor

41. When APU bleed P/W is selected ON with cross bleed selector in Auto

position, the lower ECAM BLEED page indicates:

A. APU bleed valve open then the cross bleed valve open

B. APU bleed valve open but the cross bleed valve not open

C. The cross bleed valve opens then APU bleed valve open

42. For CFM LEAP-1A Engine, HPV is:

A. Electric control and Bleed Pressure open

B. Bleed Pressure control and open

C. Electric control and open

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ATA 70-80

43. Function of a programming plug on the Electronic Engine Control (EEC)

to:

A. changes the available thrust

B. identify P/N of EEC

C. identify S/N of EEC

44. Which is correct statement?

A. The IAE V2500-A5 engine is a one spool, axial flow, high bypass ratio turbo

fan power engine

B. The IAE V2500-A5 engine is a two spool, axial flow, high bypass ratio turbo

fan power engine

C. The IAE V2500-A5 engine is a three spool, axial flow, high bypass ratio turbo

fan power engine

45. The thrust setting parameter (V2500) is:

A. Engine Pressure Ratio in normal mode

B. N1 in back up mode

C. Both A and B

46. For CEO A/C, The FADEC system consists of:

A. A single EEC(ECU) with its peripherals for both engines

B. A single EEC(ECU) with its peripherals per engine

C. One main frame computer for all engines

47. During Engine manual start, starter air valve (SAV) open when:

A. Mode selector is set to IGN/START

B. Master switch set to ON

C. Engine MAN START push to ON

48. For CFM LEAP-1A Engine FADEC system, each EEC A & B can control

the Engine System, but :

A. One EEC is control or active at a time

B. Both EECs are in control or active permanently

C. The Standby EEC is never switch automatically

49. For CFM LEAP-1A Engine,The ENG Drain mast gives a leak path exit for

hydraulic, oil and :

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A. Fuel component

B. Reverser system actuators

C. Permanent Magnet Altenator (PMA)

50. For CFM LEAP-1A Engine, Aerodynamic strakes are installed on the

follow side (s) of the Engine fancowls:

A. Inboard side

B. Outboard side

C. Inboard and outboard side

51. With the throttle controll lever in the idle stop position, the reserver can

be set to :

A. Min reverse and Max reverse

B. Reverse idle and Max reverse

C. Reverse idle and continue reverse

52. For CFM LEAP-1A Engine, the accessory drive section includes the

following modules :

A. Inside gear box (IGB), Transfer gear Box (TGB), and component gear

box (CGB)

B. TGB, Angle gear Box (AGB) and main gear box (MGB)

C. IGB, TGB and accessory gear box

53. For CFM LEAP-1A Engine, with the Ignition system of the engine is

supply with power as follows:

A. 115 V from the A/C electrical system

B. 115 V from PMA

C. 115 V from PMA or 115 V from the A/C electrical system depend on N2

speed

54. The ignition system has the following number of Ignition Exciter Boxes

and Igniter Plugs:

A. One Ignition Exciter Box and two Igniter plugs

B. two Ignition Exciter Box and two Igniter plugs

C. One Ignition Exciter Box and one Igniter plugs

55. For CFM LEAP-1A Engine, the Ignition system is controlled by :

A. EEC

B. EIU

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C. PMA

56. The CFM-LEAP1A Engine is:

A. An axial fow, dual-rotor, variable staor and high bypass ratio power

plant

B. Two spool, two axial flow, high bypass ratio turbo fan power plant

C. Tri- spool, two axial flow, high bypass ratio turbo fan power plant

57. How many Fan Cowl Door latches are there on CFM-LEAP 1A?

A. 2

B. 3

C. 4

58. How many Thrust Reverser cowl Door latches are there on CFM-LEAP

1A?

A. 6

B. 7

C. 8

59. A fan cowl loss prevention system is installed with:

A. Mechanically with a flag only

B. Electrcally monitored by proximity switches only

C. Mechanically with a flag and Electrcally monitored by proximity switches

60. Oil cooling system on CFM-LEAP1A has follwing component :

A. Main Heat Exchanger only

B. Surface air cooling oil cooler only

C. Surface air cooling oil cooler and Main Heat Exchanger

61. How many EIU are installed in A/C A320 Family NEO CFM-LEAP 1A ?

A. 2

B. 3

C. 4

62. The Engine oil parameter is displayed on:

A. Engine page only

B. EWD and Engine page

C. Engine page and Cruise page

63. For CFM – LEAP 1A Engine, When slats are fully opned, can you full

open reverser cowls?

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A. Yes

B. Never

C. Yes, if open by hand

64. For CFM – LEAP 1A Engine, The Air Turbine Starter Air Oil System is:

A. Independent

B. Using with Engine Oil System

C. Using IDG Oil System

65. For CFM – LEAP 1A Engine, Engine drain system has :

A. The fan zone drain mast, the core zone drain mast and the pylon drain

tubes,

B. The fan zone drain mast, the gear box drain mast and the rear drain

tubes,

C. The fan zone drain mast, the core zone drain mast and the gear box

drain tubes,

(AMM 71-70-00-00)

66. For CFM – LEAP 1A Engine, The fan zone drain mast drains of:

A. Fuel, oil, hydraulic

B. Fuel, oil, hyraulic, water,

C. Fuel, oil, water.

67. For CFM – LEAP 1A Engine, the Engine fan cowl door latches opening

sequence is:

A. L1 - L2 – L3

B. L1 – L3 – L2

C. L2 – L3 – L1

68. For CFM – LEAP 1A Engine, the Engine fan cowl door latches closing

sequence is:

A. L1 – L2 – L3

B. L2 – L3 – L1

C. L1 – L3 – L2

69. How many Fan cowl hold open rod/rods on each Engine fan cowl door ?

A. 1

B. 2

C. 3

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70. Where is Data Entry plug is located ?

A. On Engine

B. In Aft Avionic Bay

C. In FWD Avionic Bay

71. For CFM – LEAP 1A Engine, Fuel Low pressure Shut-Off Valve can be

controlled close by:

A. Engine Master Lever or Engine Fire Push Button

B. Engine Master Lever or Throtlle Lever

C. Engine Fire Push Button or Throttle Lever

72. How many fuel nozzles are there on CFM-LEAP1A ?

A. 17

B. 18

C. 19

73. For CFM – LEAP 1A Engine, The fuel in the PPMe (pilot Primary/enriched

manifold) leg is monitored by :

A. The Fuel pressure sensor

B. The Fuel temprature sensor

C. The Fuel flow meter

74. The function of the Fuel Filter Differential Pressure (FFDP) sensor is :

A. To detect if the Filter is partially or totally clogged

B. To detect fuel leaking in the FMU

C. To detect fuel leaking in the Main Heat Exchanger

75. For CFM – LEAP 1A Engine, The function of the Pressure Sub-System

(PSS) is :

A. Receives engine air pressure measurements and convers them into

electrical signals to both EECs for engine control and mornitoring

B. Receives engine air pressure measurements and convers them into

electrical signals to the active EEC for engine control and mornitoring

C. Receives engine air pressure measurements and convers them into

electrical signals to the standby EEC for engine control and mornitoring

76. For CFM – LEAP 1A Engine, the function of Cross Channel Data Link

(CCDL) is :

A. To exchange data between the active EEC and the stanby EEC

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B. To exchange data between EIU and the active EEC

C. To exchange data between EIU and the standby EEC

77. For CFM – LEAP 1A Engine, the EECs are ventilated by :

A. One blower

B. Two blowers

C. Fan air

78. For CFM – LEAP 1A Engine, The PMA directly supplies each EEC uinit

with :

A. One- phase AC power

B. Three- phases AC power

C. 28 VDC power

79. For CFM – LEAP 1A Engine, 115 VAC supply to the Ignition Exciter is :

A. A/C power to EIU and then to EEC to the Ignition Exciter

B. A/C power to EIU and to the Ignition Exciter

C. PMA to EIU and then to EEC to Ignition Exciter

80. For CFM – LEAP 1A Engine, When an automatic start is manual aborted,

A. EEC does not dry motor the Engine

B. EEC controls to dry motor the Engine

C. Have message « Abort start Engine XX » on ECAM

81. How many cranking modes ?

A. 1

B. 2

C. 3

82. For CFM – LEAP 1A Engine, The EEC shall enter the automatics start

mode when :

A. Engine is not running and ENG MASTER lever is set to ON,

B. The ENG MODE rotary selector is set to IGN/START and the to

NORMAL

C. ENG MAN START is set to ON

83. For CFM – LEAP 1A Engine, N1 indication is shows on :

A. EWD

B. ENGINE ECAM SD

C. EWD and ENGINE ECAM SD

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84. For CFM – LEAP 1A Engine, N2 indication is shows on :

A. EWD

B. ENGINE ECAM SD

C. EWD and ENGINE ECAM SD

85. For CFM – LEAP 1A Engine, VIB N1 indication shows on :

A. EWD

B. ENGINE ECAM SD

C. EWD and ENGINE ECAM SD

86. For CFM – LEAP 1A Engine, VIB N2 indication shows on :

A. EWD

B. ENGINE ECAM SD

C. EWD and ENGINE ECAM SD

87. For CFM – LEAP 1A Engine, ENG OIL Pressure indication shows on :

A. EWD

B. ENGINE ECAM SD

C. EWD and ENGINE ECAM SD

88. For CFM – LEAP 1A Engine, ENG OIL Quantity indication shows on :

A. EWD

B. ENGINE ECAM SD

C. EWD and ENGINE ECAM SD

89. For CFM – LEAP 1A Engine, ENG OIL Temprature indication shows on :

A. EWD

B. ENGINE ECAM SD

C. EWD and ENGINE ECAM SD

90. For CFM – LEAP 1A Engine, Fuel Flow indication shows on :

A. EWD

B. ENGINE ECAM SD

C. EWD and ENGINE ECAM SD

91. For CFM – LEAP 1A Engine, Fuel USED indication shows on :

A. EWD

B. ENGINE ECAM SD

C. EWD and ENGINE ECAM SD

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92. For CFM – LEAP 1A Engine, ECAM alert « ENG1 START FAULT- HOT

START » when :

A. ENG 1 Auto start attempt fail, the start is aborted

B. ENG 1 Manual start attempt fail, the start is aborted

C. ENG 1 has fire dedected

93. For CFM – LEAP 1A Engine, ECAM alert « ENG1 START FAULT- ENG1

IGNITION FAULT » when :

A. ENG 1 Auto start attempt fail, the start is aborted

B. ENG 1 Manual start attempt fail, the start is aborted

C. ENG 1 has fire dedected

94. For CFM – LEAP 1A Engine, N1 target is computed by :

A. FMGC

B. EEC

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C. EIU

95. For CFM – LEAP 1A Engine, The predicted Max N1 is indicated by :

A. A blue cycle on the N1 indicator

B. A Red mark on the N1 indicator

C. Max N1 number on the N1 indiator

96. For CFM – LEAP 1A Engine, N1 rating limit is computed by :

A. FMGC

B. EEC

C. EIU

97. For CFM – LEAP 1A Engine, the N1 and N2 sensors are :

A. LRU

B. Not LRU

C. The N1 sensor is LRU only

98. For CFM – LEAP 1A Engine, the signal from the Oil Debris Monitoring

Sensor (ODMS) sends to :

A. EEC

B. ODMU

C. EIU

99. For CFM – LEAP 1A Engine, The MAX mark on the oil tanks is:

A. 20 Qts

B. 17 or 17.5 Qts

C. 22 Qts

(AMM 12-13-79-610-806-A)

100. For CFM – LEAP 1A Engine, if Filler CAP of Engine Oil Tank not

locked :

A. Has a message on EWD

B. Has a message on ENGINE ECAM SD

C. No indication