Quyết định 1062/QĐ-CHK 2024 ngân hàng câu hỏi thi giấy phép, năng định bảo dưỡng tàu bay B737NG, B737Max

QUYẾT ĐỊNH

Về việc phê duyệt ngân hàng câu hỏi thi sát hạch giấy phép, năng định

bảo dưỡng tàu bay B737NG và B737MAX

^{_________________________}

CỤC TRƯỞNG CỤC HÀNG KHÔNG VIỆT NAM

Căn cứ Nghị định số 66/2015/NĐ-CP ngày 12/08/2015 của Chính phủ quy định về nhà chức trách hàng không;

Căn cứ Nghị định số 66/2015/NĐ-CP ngày 12/08/2015 của Chính phủ quy định về nhà chức trách hàng không;

Căn cứ Thông tư số 01/2011/TT-BGTVT ngày 27/01/2011 của Bộ trưởng Bộ Giao thông vận tải ban hành Bộ quy chế an toàn hàng không dân dụng lĩnh vực tàu bay và khai thác tàu bay và Thông tư số 03/2016/TT-BGTVT ngày 31/03/2016, Thông tư số 21/2017/TT-BGTVT ngày 30/6/2017, Thông tư số 56/2018/TT-BGTVT ngày 11/12/2018 và Thông tư số 42/2020/TT-BGTVT ngày 31/12/2020, Thông tư số11/2022/TT-BGTVT ngày 29/06/2022, Thông tư số 09/2023/TT-BGTVT ngày 09/06/2023 sửa đổi, bổ sung một số điều của Bộ quy chế an toàn hàng không dân dụng lĩnh vực tàu bay và khai thác tàu bay;

Căn cứ Quyết định số 651/QĐ-BGTVT ngày 29/05/2023 của Bộ trưởng Bộ Giao thông vận tải quy định chức năng, nhiệm vụ, quyền hạn và cơ cấu tổ chức của Cục Hàng không Việt Nam và quyết định số 371/QĐ-BGTVT ngày 02/04/2024 về việc sửa đổi quyết định 651/QĐ-BGTVT ngày 29/05/2023;

Theo đề nghị của Trưởng phòng Tiêu chuẩn an toàn bay – Cục Hàng không Việt Nam.

QUYẾT ĐỊNH:

Điều 1. Phê duyệt ngân hàng câu hỏi thi sát hạch giấy phép, năng định bảo dưỡng tàu bay B737NG và B737Max chi tiết nêu tại phụ lục I và II kèm theo.

Điều 2. Quyết định này có hiệu lực kể từ ngày ký.

Điều 3. Trưởng phòng Tiêu chuẩn an toàn bay- Cục Hàng không Việt Nam, Thủ trưởng các cơ quan, đơn vị và cá nhân liên quan chịu trách nhiệm thi hành Quyết định này.

PHỤ LỤC I:

SỐ LƯỢNG CÂU HỎI THI SÁT HẠCH GIẤY PHÉP, NĂNG ĐỊNH

BẢO DƯỠNG TÀU BAY B737NG VÀ B737MAX

(kèm theo quyết định số 1062/QĐ-CHK ngày 13/05/2024)

PHỤ LỤC II:

CÁC BỘ CÂU HỎI THI SÁT HẠCH GIẤY PHÉP, NĂNG ĐỊNH

BẢO DƯỠNG TÀU BAY B737NG VÀ B737MAX

(kèm theo quyết định số 1062/QĐ-CHK ngày 13/05/2024)

A. QUESTION BANK FOR B737NG CAT A (AIRFRAME)

B. QUESTION BANK FOR B737NG CAT B1 (AIRFRAME)

C. QUESTION BANK FOR B737NG CAT B2 (AIRFRAME)

D. QUESTION BANK FOR CFM56 (B737NG) CAT A (ENGINE)

E. QUESTION BANK FOR CFM56 (B737NG) CAT B1 (ENGINE)

F. QUESTION BANK FOR CFM56 (B737NG) CAT B2 (ENGINE)

G. QUESTION BANK FOR B737MAX CAT A (AIRFRAME)

H. QUESTION BANK FOR B737MAX CAT B1 (AIRFRAME)

I. QUESTION BANK FOR B737MAX CAT B2 (AIRFRAME)

J. QUESTION BANK FOR CFM LEAP-1B (B737MAX) CAT A (ENGINE)

K. QUESTION BANK FOR CFM LEAP-1B (B737MAX) CAT B1 (ENGINE

A. QUESTION BANK FOR B737NG CAT A (AIRFRAME)

ATA 6:

1. The body station line (STA) is a

a) Lateral dimension

b) Horizontal dimension.

c) Height dimension.

(A) AMM TASK 06-21-00-800-801

2. The body buttock line (BL) is a

a) Lateral dimension

b) Height dimension

c) Horizontal dimension

(A) AMM TASK 06-21-00-800-801

3. The water line (WL) is a

a) Lateral dimension

b) Horizontal dimension.

c) Height dimension.

(A) AMM TASK 06-21-00-800-801

4. The airplane has

a) Eight major zones

b) Six major zones

c) Seven

(A) AMM TASK 06-30-00-800-801

5. The general left wing section base number is

a) 500

b) 600

c) 700

(A) AMM TASK 06-30-00-800-801

6. Location zone for Lower Half of Fuselage is

a) 100

b) 200

c) 300

(A) AMM TASK 06-30-00-800-801

7. Location zone for Landing Gear and Landing Gear Doors is

a) 600

b) 700

c) 800

(A) AMM TASK 06-30-00-800-801

8. Fuselage station diagram gives reference to find out components, features and major fuselage structural openings in relation to

a) Datum plane which is perpendicular to fuselage centerline and located 130.0 Inch forward of airplane nose

b) Nose of airplane

c) Floor of airplane passenger cabin

(A) AMM TASK 06-21-00-800-801

9. Major zone 200 is

a) Lower half of fuselage

b) Upper half of fuselage

c) L/H and R/H wing

(A) AMM TASK 06-30-00-800-801

ATA 7:

10. The airplane has

a) Three main jack points and four auxiliary jack points

b) Four main jack points and three auxiliary jack points.

c) Three main jack points and three auxiliary jack points (A) AMM TASK 07-11-01-580-815

12. Can the aircraft be jacked at axle jack points

a) Yes, at Max Zero Fuel Weight

b) Yes, At Max Taxi Weight

c) Not permitted

(A) AMM TASK 07-11-01-580-815

ATA 8:

13. The location of the inclinometers are in

a) main wheel gear well

b) the nose wheel well

c) The E & E compartment

(A) AMM TASK 08-21-04-000-801

ATA 9:

14. The design of the airplane will permit you to tow the airplane from

a) The nose landing gear

b) The main landing gear

c) The nose landing gear or main landing gear

(A) AMM TASK 09-11-00-580-801

15. The maximum normal towing turning limits are indicated by the painted stripes on

a) The lower fuselage below left pax door

b) The nose gear doors.

c) The lower fuselage below right pax door

(A) AMM TASK 09-11-00-580-801

16. When tow the aircraft, maximum normal turning angle is

a) 68 degrees

b) 78 degrees

c) 88 degrees

(A) AMM TASK 09-11-00 PAGE 206

17. What is the correct sequence

a) Install the tow bar on the tow fitting then install the tow lever safety pin

b) Install the tow lever safety pin then install the tow bar on the tow fitting

c) There is no specific sequence.

(A) AMM TASK 09-11-00 PAGE 204 & 205

ATA 10:

18. Prolonged Parking means

a) When an airplane is not operated for 7 days or more

b) When an airplane is not operated for 14 days or more

c) When an airplane is not operated for 30 days or more (A) AMM TASK 10-12-02-550-802

19. When aircraft stop overnight

a) Pitot probe and static port are covered.

b) Static port are covered

c) Pitot port are covered

(A) AMM TASK 10-11-01-580-801

ATA 12:

20. When you do the Aircraft Grounding for the Refuel/Defuel Operations

a) Connect the ground cable to parking ground point before you connect it to the aircraft

b) Attach the cable to aircraft first then connect to parking ground point

c) Grounding is not necessary

(A) AMM TASK 20-40-11-760-801

23. When doing the Hydraulic Fluid Reservoir Filling

a) The reservoirs air pressurize system must be depressurized

b) Do not depressurize the system reservoirs

c) The hydraulic system operating normally

(A) AMM TASK 12-12-00-610-801

ATA 20:

24. Which statement is NOT correct for Lockwire Procedure

a) Do not use lockwire more than twice

b) Install lockwire so it is in tension when the parts become loose

c) Make three to six twists at the end of the wire. Bend the twists back or under to give the ends protection so they will not catch something

(A) AMM 20-10-44

25. How to find out broken wire of control cable

a) rub along cable by hand to find out broken wire

b) rub along cable by a cloth, the cloth will catch any broken cable

c) remove cable

(A) AMM 20-20-31

26. What type of locking wire is to be used on emergency equipment

a) stainless steel wire

b) plastic tie

c) copper wire

(A) AMM 20-10-44

ATA 21:

27. On B737-800/900 which component controls pack cooling temperature?

a) Pack/zone temperature controller

b) Cabin temperature controller

c) Air conditioning accessory unit

(A) Reference: ATA 21 Air conditioning system (1 of 2) - B737 Training book - Page 12

28. On B737 800/900, these components in the EE compartment control the functions of the air conditioning system:

a) Two cabin temperature controller and two air conditioning accessory units (ACAU)

b) Two pack/zone temperature controllers and two air conditioning accessory units (ACAU)

c) Two pack/zone temperature controllers and two cabin pressure controller

(A) Reference: ATA 21 Air conditioning system (1 of 2) - B737 Training book - Page 12

29. On B737-800/900, the primary parts of the air conditioning (A/C) system are

a) Pack flow control, Pack cooling system, Zone temperature control, Air distribution.

b) Pack flow control, Pack/Zone temperature control, Recirculation, Air distribution.

c) Pack flow control, Pack cooling system, Zone temperature control, Recirculation, Air distribution.

(A) Reference: ATA 21 Air conditioning system (1 of 2) - B737 Training book - Page 19

30. On B737-800/900, the pack has overheat protection components that automatically stop operation of the pack, these are:

a) Compressor discharge overheat switch, Turbine inlet overheat switch, Pack discharge overheat switch.

b) Compressor discharge overheat switch, Turbine inlet overheat switch, Pack temp sensor.

c) Compressor discharge overheat switch, Ram air sensor, Pack discharge overheat switch. (A) Reference: ATA 21 Air conditioning system (1 of 2) - B737 Training book - Page 36

31. How to control and actuate the flow control and shutoff valve (FCSOV) ?

a) The FCSOV is electrically controlled and electrically actuated.

b) The FCSOV is electrically controlled and pneumatically actuated.

c) The FCSOV is pneumatically controlled and pneumatically actuated.

(A) Reference: ATA 21 Air conditioning system (1 of 2) - B737 Training book - Page 40

32. What is the primary heat exchanger used for ?

a) The primary heat exchanger removes heat from bleed air going to the compressor section of the air cycle machine.

b) The primary heat exchanger removes heat from bleed air that comes from the compressor section of the air cycle machine.

c) The primary heat exchanger removes heat from bleed air that comes from the reheater.

(A) Reference: ATA 21 Air conditioning system (1 of 2) - B737 Training book - Page 46

33. These are the three modes of control for the ram air system:

a) Open, Partial open, Close.

b) Ground, Takeoff/ Landing, Cruise.

c) Ground, Flight (flaps not up), Flight cruise (flaps up).

(A) Reference: ATA 21 Air conditioning system (1 of 2) - B737 Training book - Page 57, 61

34. The air cycle machine is a high-speed rotating assembly. It has these sections:

a) Turbine, Compressor and Ram air impeller fan.

b) Turbine and Compressor.

c) Turbine, Compressor and Gearbox.

(A) Reference: ATA 21 Air conditioning system (1 of 2) - B737 Training book - Page 64

35. What is the secondary heat exchanger used for ?

a) The secondary heat exchanger removes heat from bleed air going to the compressor section of the air cycle machine.

b) The secondary heat exchanger removes heat from bleed air that comes from the compressor section of the air cycle machine.

c) The secondary heat exchanger removes heat from bleed air that comes from pneumatic system.

(A) Reference: ATA 21 Air conditioning system (1 of 2) - B737 Training book - Page 80

36. How many water extractors are installed on B737-800/900 ?

a) There are four water extractors, two in each air conditioning pack

b) There are two water extractors, one in each air conditioning pack

c) This aircraft type does not use water extractor

(A) Reference: ATA 21 Air conditioning system (1 of 2) - B737 Training book - Page 88

37. What are the indications when a pack trip occurs on B737 800/900:

a) MASTER CAUTION and AIR COND annunciator lights.

b) PACK amber light, MASTER CAUTION and AIR COND annunciator lights.

c) PACK amber light and MASTER CAUTION lights.

(A) Reference: ATA 21 Air conditioning system (1 of 2) - B737 Training book - Page 114

38. The flight compartment gets conditioned air from

a) the right pack and the mix manifold.

b) the mix manifold.

c) the left pack and the mix manifold.

(A) Reference: ATA 21 Air conditioning system (1 of 2) - B737 Training book - Page 118

39. Where are the main air distribution components ?

a) in the distribution compartment aft of the forward cargo compartment.

b) in the distribution compartment in aft cargo compartment.

c) in the distribution compartment in avionic compartment.

(A) Reference: ATA 21 Air conditioning system (1 of 2) - B737 Training book - Page 122

40. On the temperature controls panel, which component controls the trim air pressure regulating and shutoff valve ?

a) The three temperature selectors

b) The trim air switch

c) The air temperature source selector

(A) Reference: ATA 21 Air conditioning system (1 of 2) - B737 Training book - Page 196

41. On B737 800/900, primary flight compartment zone temperature control channel is

a) a channel of ACAU.

b) a channel of LEFT pack/zone temperature controller.

c) a channel of RIGHT pack/zone temperature controller.

(A) Reference: ATA 21 Air conditioning system (1 of 2) - B737 Training book - Page 203

42. Which components are the interface between the normal temperature control system and the airplane safety logic ?

a) Two ACAUs.

b) Two pack/zone temperature controller.

c) Related ducting and wires.

(A) Reference: ATA 21 Air conditioning system (1 of 2) - B737 Training book - Page 221

43. What system removes heat from electronic components in the flight compartment and the E/E compartment ?

a) The ram air system

b) The equipment cooling system

c) The ventilation system

(A) Reference: ATA 21 Air conditioning system (1 of 2) - B737 Training book - Page 242

44. On the ground, to give a warning when there is not sufficient cooling air flow, the equipment cooling system has

a) indicator lights

b) the crew call horn

c) indicator lights and the crew call horn

(A) Reference: ATA 21 Air conditioning system (1 of 2) - B737 Training book - Page 248

45. The supply and exhaust fans move air around electrical equipment to remove heat. There are

a) two sets of fans (normal and alternate) for the supply and the exhaust systems

b) two fans for the supply and the exhaust systems

c) two fans (normal and alternate) for both supply and exhaust systems

(A) Reference: ATA 21 Air conditioning system (1 of 2) - B737 Training book - Page 252

46. These are the parts of the heating system:

a) Flight compartment heating, Supplemental heating and Aft cargo compartment heating

b) Forward cargo compartment heating, Supplemental heating and Aft cargo compartment heating

c) Flight compartment heating, Passenger compartment heating and Cargo compartment heating (A) Reference: ATA 21 Air conditioning system (1 of 2) - B737 Training book - Page 274

47. The cabin pressure control system controls

a) the rate that the air flows into the cabin.

b) the rate that the air flows into and out of the cabin.

c) the rate that the air flows out of the cabin.

(A) Reference: ATA 21 Air conditioning system (2 of 2) - B737 Training book - Page 2

48. The CPCs show FAULT on the front panel display only when

a) there is an existing fault on cabin pressure control system.

b) there is a history fault on cabin pressure control system.

c) there is a fault on CPCs.

(A) Reference: ATA 21 Air conditioning system (2 of 2) - B737 Training book - Page 18

49. How many motors does the outflow valve have ?

a) three automatic mode motors

b) two automatic mode motors and one manual mode motor

c) one automatic mode motors and one manual mode motor

(A) Reference: ATA 21 Air conditioning system (2 of 2) - B737 Training book - Page 38

50. The amber AUTO FAIL light gives the flight crew an indication that

a) one auto channels are inoperative.

b) all auto channels are inoperative

c) one or both auto channels are inoperative.

(A) Reference: ATA 21 Air conditioning system (2 of 2) - B737 Training book - Page 45

51. The off schedule descent (OFF SCHED DESCENT) indication tells the crew that

a) the cabin pressure control system will control cabin pressure for a return to the take-off field.

b) the cabin pressure control system will turn off cabin pressure control in descent mode.

c) the cabin pressure control system turned off the schedule descent mode.

(A) Reference: ATA 21 Air conditioning system (2 of 2) - B737 Training book - Page 50

52. Which componets prevent damage to the airplane structure during sudden decompression in the cargo compartment.

a) The pressure equalization valves

b) The cargo compartment blowout panels

c) The negative pressure relief valve

(A) Reference: ATA 21 Air conditioning system (2 of 2) - B737 Training book - Page 60

53. The E & E compartment is cooled by?

a) The equipment cooling system

b) The ram air system

c) The AUTO or STANDBY pressurisation systems

(A) AMM 21-27-00 PAGE 2

54. The Re-circulating Fan air shroud is located

a) Forward of the E & E compartment.

b) Above the forward cargo compartment

c) Above the aft cargo compartment

(A) AMM 21-25-00

55. The Re-circulating Fan system provides?

a) A filtered air supply into the mix manifold

b) An unfiltered air supply into the mix manifold

c) An air supply directly from the mix manifold into the passenger cabin only

(A) AMM 21-25-00

56. The aft cargo compartment is heated by

a) The exhaust air from the control cabin

b) The exhaust air from the passenger cabin

c) The exhaust air from the E & E compartment

(A) AMM 21-40-00

ATA 22:

57. These are part of the stall management function of the SMYD:

a) Stall warning, EFS, Autoslat, Performance data.

b) Stall warning, Yaw damping, Autoslat, Performance data.

c) Stall warning, Turn coordination, Autoslat, Performance data.

(A) ATA 22 Autoflight system - B737 Training book - Page 13

58. You engage the yaw damper system with a switch on the flight control panel. These conditions are necessary for primary yaw damping:

a) The system A hydraulic pressure is available and the FLT CTRL A switch must be ON.

b) The system B hydraulic pressure is available and the FLT CTRL B switch must be ON.

c) The system A & B hydraulic pressure is available.

(A) ATA 22 Autoflight system - B737 Training book - Page 46

59. The wheel-to-rudder interconnect system (WTRIS) moves the rudder to help turns during flight control manual reversion

a) When on standby hydraulics.

b) When put the FLT CONT A or B switches to ON position.

c) When put the yaw damper switch to OFF.

(A) ATA 22 Autoflight system - B737 Training book - Page 58

60. The digital flight control system (DFCS) does these functions:

a) Autopilot, Flight director, Altitude alert, Speed trim, Mach trim, Autothrottle.

b) Autopilot, Flight director, Altitude alert, Speed trim, Mach trim.

c) Autopilot, Altitude alert, Speed trim, Mach trim, Autothrottle. (A) ATA 22 Autoflight system - B737 Training book - Page 93

61. When does the receivers use the VOR/LOC antenna in the vertical stabilizer ?

a) When the FCC is in the approach or localizer mode and a localizer frequency is selected on the navigation control panel.

b) When the FCC is in the approach or localizer mode and an ILS frequency is not selected on the navigation control panel.

c) Always use when the FCC is in the approach or localizer mode.

(A) ATA 22 Autoflight system - B737 Training book - Page 186

62. When does the receivers use the localizer antenna in the nose radome ?

a) When the FCC is in the approach or localizer mode and a localizer frequency is selected on the navigation control panel.

b) When the FCC is in the approach or localizer mode and an ILS frequency is not selected on the navigation control panel.

c) Always use when the FCC is in the approach or localizer mode.

(A) ATA 22 Autoflight system - B737 Training book - Page 186

63. The red A/T warning lights on the ASAs come on

a) Only when the A/T disconnects.

b) Only when the A/T is in BITE.

c) When the A/T disconnects or when the A/T is in BITE.

(A) ATA 22 Autoflight system - B737 Training book - Page 348

64. This is the takeoff sequence:

a) Preflight, Takeoff start, Takeoff roll, Climb out.

b) Preflight, Takeoff roll, Takeoff start, Climb out.

c) Preflight, Takeoff roll, Climb out, Takeoff start.

(A) ATA 22 Autoflight system - B737 Training book - Page 364

65. The localizer antenna switches

a) Turn ON/OFF the localizer antenna.

b) Determine if the dual VOR/LOC antenna or the localizer antenna is supplying the RF signals to the receivers.

c) Receive the localizer signal and send it directly to the localizer antenna.

(A) ATA 22 Autoflight system - B737 Training book - Page 186

66. When the crew push a TO/GA switch one time during a fully automatic approach

a) The autothrottle decreased thrust go-around mode operate.

b) The autothrottle maximum thrust go-around mode operate.

c) The autothrottle disengage.

(A) ATA 22 Autoflight system - B737 Training book - Page 381

ATA 23:

67. Where is the pilots audio selector panel located.

a) In Cockpit P8 panel

b) In Cockpit P8 and P6 panels

c) In cockpit Captain side only

(A) ATA 23 Communication System - B737 Training book - Page 36

68. The Cockpit Voice Recorder in AUTO:

a) Always powers the CVR when DC bus 1 is powered.

b) Always powers the CVR when DC bus 2 is powered.

c) Always powers the CVR from first engine start until 5 minutes after last engine shutdown.

(A) ATA 23 Communication System - B737 Training book - Page 387

69. Where is observer audio control panel?

a) On the P5 aft overhead panel or the P8 aft electronics panel

b) On the P5 aft overhead panel or the P11 fwd electronics panel

c) On the P8 aft electronics panel and P11 fwd electronics panel

(A) ATA 23 Communication System - B737 Training book - Page 36

70. The CVR (orange box) is located:

a) In the forward Electronic & Equipment bay (E&E).

b) In the aft right side of the aft cargo compartment.

c) In the flight deck (under the captain's seat).

(A) ATA 23 Communication System - B737 Training book - Page 368

71. Where are The REU and the audio switching relays?

a) Above overhead panel in the cabin compartment

b) on the E4-1 rack in Electronic Equipment Compartment

c) In the flight compartment

(A) ATA 23 Communication System - B737 Training book - Page 37

72. Where is the external flight interphone jack?

a) On the P19 external power panel

b) In the electronic equipment compartment

c) In the main wheel well

(A) ATA 23 Communication System - B737 Training book - Page 40

73. The Service Interphone switch on the Aft overhead panel when selected ON

a) Deactivates external jacks sockets from the Service Interphone system.

b) Allows communications between the flight deck and the flight attendants when using the Flight Interphone system.

c) Adds external jack sockets to the Service Interphone system.

(A) ATA 23 Communication System - B737 Training book - Page 83

74. The Cockpit CALL (blue) light will illuminate along with an associated chime whenever the cockpit is being called

a) By the flight attendants or the ground crew

b) By the ground crew only.

c) By the flight attendants only.

(A) ATA 23 Communication System - B737 Training book - Page 59, 91

75. To test the Cockpit Voice Recorder

a) Press the test CVR test switch and after a slight delay observe the Monitor Indicator rise into the red band.

b) Plug a headset into the jack socket in the CVR panel and press the Erase switch.

c) Press the test CVR test switch and after a slight delay observe the Monitor Indicator rise into the green band.

(A) ATA 23 Communication System - B737 Training book - Page 385

76. Where are the HF antenna couplers?

a) On the top of the vertical stabilizer

b) Inside the vertical stabilizer

c) On the E6 rack at the aft cargo compartment

(A) ATA 23 Communication System - B737 Training book - Page 184

77. Each radio communication panel can

a) Tune only one transceiver at a time

b) Tune all transceivers at a time

c) Tune only one transceiver

(A) ATA 23 Communication System - B737 Training book - Page 152

78. The ATTEND (attendants call) is pressed and released in the cockpit and

a) A HIGHT chime sound will be heard in the passenger cabin.

b) A LOW tone chime sound will be heard in the passenger cabin.

c) A HIGHT/LOW chime sound will be heard in the passenger cabin.

(A) ATA 23 Communication System - B737 Training book - Page 59

79. Where is observer audio control panel?

a) On the P5 aft overhead panel or the P8 aft electronics panel

b) On the P5 aft overhead panel or the P11 fwd electronics panel

c) On the P8 aft electronics panel and P11 fwd electronics panel

(A) ATA 23 Communication System - B737 Training book - Page 36

80. Communications between the cockpit and the ground crew is possible by using the

a) Flight interphone system or the Service Interphone system provided the Service Interphone switch is ON.

b) Flight interphone system only.

c) The Service interphone system irrespective of the position of the Service Interphone switch.

(A) ATA 23 Communication System - B737 Training book - Page 29,71

81. The VHF-1 transmitter selector switch on an audio selector panel is illuminated

a) Reception on VHF-1 is automatically provided

b) The ALT/NORM switch must be in NORM to obtain reception at a comfortable volume level.

c) Reception is achieved by pulling and rotating VHF-1 receiver switch.

(A) ATA 23 Communication System - B737 Training book - Page 162

82. Where are the service interphone jacks located.

a) External power only

b) At all flight attendance stations

c) C.APU, R&L W W, refuel station, external power, aft cabin rear ceiling, E&E, lower fuselage section 48.

(A) ATA 23 Communication System - B737 Training book - Page 82

83. The Cockpit Voice Recorder in ON:

a) Power the CVR and will go back to the AUTO position only when you put the switch to AUTO position

b) Power the CVR and will go back to AUTO position when you manual put switch to AUTO or when engine running relay energizes.

c) Power the CVR and will go back to AUTO position when you manual put switch to AUTO or when engine running relay de-energizes.

(A) ATA 23 Communication System - B737 Training book - Page 387

84. The selcal system monitors selected frequencies in use on the

a) HF communications radios.

b) HF and VHF communications radios.

c) VHF communications radios.

(A) ATA 23 Communication System - B737 Training book - Page 213

85. The cockpit voice recorder keeps

a) Last 25 hour of communication data in memory.

b) Last 60 minutes of communication data in memory

c) Last 120 minutes of communication data in memory.

(A) ATA 23 Communication System - B737 Training book - Page 358

ATA 24:

86. The GROUND POWER AVAILABLE light will extinguish when:

a) The GROUND POWER switch is positioned ON

b) The GROUND SERVICE switch is positioned ON

c) The AC ground power cart has been disconnected

(A) ATA 24 Electrical Power System - B737 Training book - Page 33

87. Generator Drive Disconnect switch when operated

a) Disconnects the Generator Drive from the engine in the event of a Generator Drive malfunction, only if the engine has been shut down first

b) Disconnects the Generator Drive from the engine in the event of a Generator Drive malfunction

c) Disconnects the CSD from the generator in the event of a Generator Drive malfunction

(A) ATA 24 Electrical Power System - B737 Training book - Page 81

88. Re-coupling of the Generator Drive drive shaft to the engine may be accomplished

a) At any time in flight provided the Generator Breaker and the Generator Control Relay have previously been tripped.

b) Only on the ground.

c) At any time on the ground or in flight.

(A) ATA 24 Electrical Power System - B737 Training book - Page 71

89. One of the basic principles of the electrical system is

a) The AC sources of power can be connected in parallel if necessary

b) There is no paralleling of the AC sources of power.

c) The AC sources of power are always connected in parallel.

(A) ATA 24 Electrical Power System - B737 Training book - Page 91

90. When both engines are running with external power connected then

a) External power will automatically disconnect when both engine generators are brought on line.

b) External power must be selected OFF before the engine generators are brought on-line.

c) External power will automatically disconnect when either engine generator is brought on-line.

(A) ATA 24 Electrical Power System - B737 Training book - Page 91,110

91. An engine electrical generator is rated at

a) 90 KVA

b) 45 KVA

c) 55 KVA

(A) ATA 24 Electrical Power System - B737 Training book - Page 9

92. To connect the External Ground power to the aircraft's Generator busses

a) The Battery switch must be OFF

b) The Battery switch must be ON.

c) The Bus Transfer switch must be in the AUTO position

(A) ATA 24 Electrical Power System - B737 Training book - Page 59

94. The 115V AC Standby Bus is powered by:

a) The 115V Transfer Bus No.1 under normal conditions.

b) The Battery Bus through the Static Inverter under normal conditions.

c) The Battery through the Static Inverter with a failure of both engine driven generators.

(A) ATA 24 Electrical Power System - B737 Training book - Page 172

95. Illumination of the GND POWER AVAILABLE light indicates:

a) The Ground Service Bus is powered by a ground power supply.

b) Ground power is connected however no airplane power quality is measured.

c) Ground power is connected and meets airplane power quality standards.

(A) ATA 24 Electrical Power System - B737 Training book - Page 33

96. The switched hot battery bus is powered whenever:

a) Transfer bus 1 is powered.

b) AC ground service bus is powered.

c) The battery switch is ON.

(A) ATA 24 Electrical Power System - B737 Training book - Page 25

97. After an overload situation has been resolved, how do you recover the galley buses?

a) It happens automatically.

b) Move the CAB/UTIL switch to OFF then ON.

c) A ground engineer should reselect the appropriate switch in the E/E

(A) ATA 24 Electrical Power System - B737 Training book - Page 190

98. To connect the External Ground power to the aircraft's Generator busses

a) The Battery switch must be OFF

b) The Battery switch must be ON.

c) The Bus Transfer switch must be in the AUTO position

(A) ATA 24 Electrical Power System - B737 Training book - Page 59

99. The APU generator has

a) A Generator drive unit which will disconnect when the APU Generator drive disconnect switch is activated from the flight deck.

b) A Generator drive unit which will automatically disconnect when its oil temperature is high.

c) No Generator drive unit since the APU itself is governed and will maintain a constant generator speed.

(A) ATA 24 Electrical Power System - B737 Training book - Page 118

100. To have all three Generators (APU and engines) on-line simultaneously

a) Is possible in flight only.

b) Is not possible.

c) Is possible on the ground only.

(A) ATA 24 Electrical Power System - B737 Training book - Page 91

101. Under normal conditions the Standby AC bus is energised from the

a) 115-volt Transfer bus No. 1

b) 115-volt Transfer bus No. 2

c) The Static Invertor.

(A) ATA 24 Electrical Power System - B737 Training book - Page 21

102. If ground power is available and the Ground Service switch on the forward attendant's panel is switched on, then power is supplied to

a) All the aircraft electrical busses.

b) The Ground Service bus for utility outlets, cabin lighting and battery charger.

c) The Ground Service bus for utility outlets and cabin lighting only

(A) ATA 24 Electrical Power System - B737 Training book - Page 22

103. The TR UNIT will illuminate in flight if:

a) Any TR unit fails.

b) TR1 fails or TR2 and TR3 fail.

c) TR2 fails.

(A) ATA 24 Electrical Power System - B737 Training book - Page 25

104. The ELEC light will illuminate in flight if:

a) A fault exists in the AC or Standby power system.

b) A fault exists in the AC, DC or the Standby system.

c) The ELEC light only operates on the ground.

(A) ATA 24 Electrical Power System - B737 Training book - Page 25

105. What is the purpose of the GROUND SERVICE switch?

a) Provide automatic control of ground handling bus.

b) Provide manual control of ground service bus.

c) Provide automatic control of ground service bus.

(A) ATA 24 Electrical Power System - B737 Training book - Page 22

106. Illumination of the STANDBY POWER OFF light indicates:

a) DC bus 1 unpowered

b) DC bus 2 unpowered

c) AC standby bus unpowered

(A) ATA 24 Electrical Power System - B737 Training book - Page 29

107. The purpose of the DC BUS tie relay is to:

a) Isolate DC bus 1 and DC bus 2

b) Connect DC bus 1 and DC bus 2

c) Disconnect TR1 and TR3

(A) ATA 24 Electrical Power System - B737 Training book - Page 147

108. With the STANDBY switch in the AUTO position, battery switch ON, the loss of all engine or APU electrical power results in the automatic switching from the normal power source to the alternate source for standby power:

a) On the ground only.

b) Either inflight or on the ground.

c) Will not occur.

(A) ATA 24 Electrical Power System - B737 Training book - Page 177

109. The constant speed drive (CSD):

a) Are not use in this A/C

b) Turn the generator at variable speed

c) Turn the generator at constant speed

(A) ATA 24 Electrical Power System - B737 Training book - Page 81

110. DC Standby Bus power is normally supplied from

a) The Battery Bus

b) The Hot Battery Bus

c) DC Bus No. 1

(A) ATA 24 Electrical Power System - B737 Training book - Page 13

ATA 25:

111. The captain and first officer seats are

a) Difference

b) Oppsite assemblies

c) Identical

(A) ATA 25 Equipments and Furnishings system - B737 Training book - Page 6

112. The fight compartment seats are

a) Manually control

b) Electrically control

c) Manually and electrically control

(A) ATA 25 Equipments and Furnishings system - B737 Training book - Page 6-7

113. How many observer seat can be installed?

a) One observer seat

b) Two observer seats

c) Three observer seats

(A) ATA 25 Equipments and Furnishings system - B737 Training book - Page 9

114. The first and second observer seats are

a) Adjustable seats

b) Non-adjustable seats

c) Identical

(A) ATA 25 Equipments and Furnishings system - B737 Training book - Page 9

115. In passenger cabin the service outlets provide

a) 115 Volt ac

b) 28 Volt dc power

c) 115 Volt ac and 28 Volt dc power

(A) ATA 25 Equipments and Furnishings system - B737 Training book - Page 11

116. Where are the escape slides installed?

a) On the lower inboard face of each entry and service door

b) On the lower inboard face of each entry and emergency exit door

c) On the lower inboard face of each entry, service and emergency exit door

(A) ATA 25 Equipments and Furnishings system - B737 Training book - Page 42

117. Put the slide warning pennant across the door window when

a) The slide is armed

b) The slide is dis-armed

c) The slide is Unserviceable

(A) ATA 25 Equipments and Furnishings system - B737 Training book - Page 43

118. To ARM the escape slide

a) Move the ARM-DISARM handle to ARM position

b) Remove the girt bar from the stowage hooks on the door and install it in the floor brackets

c) Remove the girt bar from the floor brackets and install it in the stowage hooks

(A) ATA 25 Equipments and Furnishings system - B737 Training book - Page 45

119. The lowered ceiling panels are installed in

a) Entry areas and lavatories

b) Entry areas and galleys

c) Entry areas, galleys and lavatories

(A) ATA 25 Equipments and Furnishings system - B737 Training book - Page 14

120. Fiberglass insulation blankets are

a) Thermally insulates the passenger compartment

b) Acoustically insulates the passenger compartment

c) Thermally and acoustically insulates the passenger compartment

(A) ATA 25 Equipments and Furnishings system - B737 Training book - Page 14-15

121. Emergency equipment typically includes

a) Overwing escape strap, Escape lanyards, Overwater survival equipment, Escape slides

b) Overwing escape strap, Escape lanyards, Detachable emergency equipment, Escape slides

c) Overwing escape strap, Escape lanyards, Overwater survival equipment, Detachable emergency equipment, Escape slides

(A) ATA 25 Equipments and Furnishings system - B737 Training book - Page 35

122. Where are the overwing escape straps?

a) In stowage tubes above each emergency exit door

b) In stowage tubes above each entry door

c) In stowage tube above the flight compartment door

(A) ATA 25 Equipments and Furnishings system - B737 Training book - Page 37

123. The escape lanyard kevlar cord rated at

a) 1000 pounds

b) 1500 pounds

c) 2000 pounds

(A) ATA 25 Equipments and Furnishings system - B737 Training book - Page 39

124. Where are the escape lanyard located?

a) In the stowage bag behind doors in the flight compartment lining above the number 2 windows

b) In the stowage bag above the flight compartment door

c) In the stowage bag below the second observer seat

(A) ATA 25 Equipments and Furnishings system - B737 Training book - Page 39

125. Where are the escape slides installed?

a) On the lower inboard face of each entry and service door

b) On the lower inboard face of each entry and emergency exit door

c) On the lower inboard face of each entry, service and emergency exit door

(A) ATA 25 Equipments and Furnishings system - B737 Training book - Page 42

126. Put the slide warning pennant across the door window when

a) The slide is armed

b) The slide is dis-armed

c) The slide is Unserviceable

(A) ATA 25 Equipments and Furnishings system - B737 Training book - Page 43

127. If the escape slide does not inflate automatically

a) Pull the inflation handle sharply to inflate the escape slide manually

b) Push the inflation handle to inflate the escape slide manually

c) Push and pull the inflation handle to inflate the escape slide manually

(A) ATA 25 Equipments and Furnishings system - B737 Training book - Page 45

128. The escape slide will fully inflate in

a) Approximately 03 seconds

b) Approximately 06 seconds

c) Approximately 10 seconds

(A) ATA 25 Equipments and Furnishings system - B737 Training book - Page 45

129. The inflation cylinder pressure relief valve opens at

a) 3500 PSIG

b) 4000 PSIG

c) 4500 PSIG

(A) ATA 25 Equipments and Furnishings system - B737 Training book - Page 49

130. How do you check an escape slide cylinder pressure?

a) The pressure indicator

b) The pop out indicator on ACP

c) The bottle must be removed and weighted

(A) ATA 25 Equipments and Furnishings system - B737 Training book - Page 49

131. How to deflate the slide after inflation test?

a) Open the pressure relief valve

b) Open the deflation valve

c) Hold the aspirator flapper valve open

(A) ATA 25 Equipments and Furnishings system - B737 Training book - Page 49

132. The escape slide light system power by

a) The 28 Volts dc BAT BUS

b) The 28 Volts dc HOT BAT BUS

c) Its own battery

(A) ATA 25 Equipments and Furnishings system - B737 Training book - Page 51

133. Which equipment protects the escape slide inflation cylinder from hight temperature?

a) The fusible plug

b) The pressure relief valve

c) The frangible disk

(A) ATA 25 Equipments and Furnishings system - B737 Training book - Page 49

134. What precaution should be taken when removing a door escape slide?

a) Install the safety pin

b) Remove the safety pin

c) Remove the airplane power

(A) ATA 25 Equipments and Furnishings system - B737 Training book - Page 49

135. The air return grilles

a) Let air move from the upper lobe to the lower lobe for normal conditioned air circulation

b) Let air move from the upper lobe to the lower lobe for air circulation during rapid decompression

c) Let air move from the upper lobe to the lower lobe for normal conditioned air circulation or air circulation during rapid decompression

(A) ATA 25 Equipments and Furnishings system - B737 Training book - Page 19

136. The passenger service units provide

a) Emergency oxygen and advisory information

b) Emergency oxygen and call switches

c) Emergency oxygen, advisory information and call switches

(A) ATA 25 Equipments and Furnishings system - B737 Training book - Page 21

137. How to open the passenger service units?

a) Insert a small allen wrench or other applicable tool into the latch release hole, then lower the service unit

b) Push the passenger service units up to release the latch, then lower the service unit

c) Remove the lanyard then lower the service unit

(A) ATA 25 Equipments and Furnishings system - B737 Training book - Page 21

ATA 26:

138. The fire protection systems monitor the airplane for these conditions:

a) Fire, Smoke, Overheat, Pneumatic duct leaks.

b) Fire, Smoke, Overheat.

c) Fire, Smoke, Pneumatic duct leaks.

(A) Reference: ATA 26 Fire protection system - B737 Training book - Page 6

139. The fire alarms provide visual and aural indication to the flight crew about a fire in any of

Engine, APU and

a) Avionic compartment, Forward cargo compartment, Aft cargo compartment and Main wheel well.

b) Forward cargo compartment, Aft cargo compartment and Main wheel well.

c) Forward cargo compartment, Aft cargo compartment and Avionic compartment.

(A) Reference: ATA 26 Fire protection system - B737 Training book - Page 8

140. How many engine fire detectors in each engine ?

a) Six detectors.

b) Fours detectors.

c) Eight detectors.

(A) Reference: ATA 26 Fire protection system - B737 Training book - Page 16

141. Which components monitor detectors for overheat and fire conditions on the engine and fire conditions on the APU.

a) The engine and APU fire detection module.

b) The engine and APU fire detection controller.

c) The engine fire detection unit and APU fire detection unit.

(A) Reference: ATA 26 Fire protection system - B737 Training book - Page 18

142. The FAULT/INOP test does

a) a check of the module overheat and fire detection circuitry and flight compartment indications.

b) a check of the module fault detection circuitry and related flight compartment indications.

c) a check of the module fault and fire detection circuitry and related flight compartment indications.

(A) Reference: ATA 26 Fire protection system - B737 Training book - Page 21

143. How many fire extinguisher bottles supply the halon to engine ?

a) Two fire extinguisher bottles supply the halon to each engine (04 bottles for 02 engines).

b) One fire extinguisher bottles supply the halon to one engine (02 bottles for 02 engines).

c) Two fire extinguisher bottles supply the halon to either engine (02 bottles for 02 engines).

(A) Reference: ATA 26 Fire protection system - B737 Training book - Page 24

144. How many APU fire detectors ?

a) Two detectors.

b) Three detectors.

c) Four detectors.

(A) Reference: ATA 26 Fire protection system - B737 Training book - Page 46

145. The APU fire extinguishing bottle is in

a) The horizontal stabilizer accessory compartment

b) The APU compartment foward bulkhead

c) Right hand side of aft cargo compartment

(A) Reference: ATA 26 Fire protection system - B737 Training book - Page 50, 54

146. When you pull the APU fire control handle on APU ground control panel (P28)

a) The APU system stops and APU fire extinguisher bottle discharges

b) The APU continute operates but isolates from other systems

c) The APU system stops and arm the fire extinguisher toggle switch

(A) Reference: ATA 26 Fire protection system - B737 Training book - Page 58

147. If the detector senses smoke or heat, a signal goes to

a) the cargo smoke detection module.

b) the cargo electronic unit.

c) the cargo smoke detection unit.

(A) Reference: ATA 26 Fire protection system - B737 Training book - Page 64

148. When smoke is detected in a lavatory,

a) the smoke detection system gives aural alarm.

b) the smoke detection system gives aural and visual alarm indications.

c) the smoke detection system gives visual alarm indications.

(A) Reference: ATA 26 Fire protection system - B737 Training book - Page 98

149. The lavatory fire extinguishing systems are

a) in the ceiling of each lavatory.

b) in the side wall panel of each lavatory.

c) in the lavatories below the wash basin.

(A) Reference: ATA 26 Fire protection system - B737 Training book - Page 106

150. The wheel well fire detection system uses

a) overheat sensing elements in the main wheel well.

b) fire detector in the main wheel well.

c) smoke detector in the main wheel well.

(A) Reference: ATA 26 Fire protection system - B737 Training book - Page 108

151. Which component monitors sensing elements for overheat and fire conditions in the wheel well and the wing and body areas ?

a) The wheel well and wing detection module.

b) The compartment overheat detection unit.

c) The compartment overheat detection controller.

(A) Reference: ATA 26 Fire protection system - B737 Training book - Page 114

ATA 27:

152. The primary flight control system has these components:

a) Ailerons, Elevators and Rudder.

b) Ailerons, Horizontal Stabiliser, Elevators and Rudder.

c) Ailerons, Spoilers, Elevators and Rudder.

(A) Reference: ATA 27 Flight controls - B737 Training book - Page 10

153. The secondary flight control system has these components:

a) Leading edge devices, Trailing edge flaps, Spoilers and speedbrakes.

b) Leading edge devices, Trailing edge flaps, Spoilers and speedbrakes and Horizontal stabilizer

c) Leading edge devices, Trailing edge flaps and Horizontal stabilizer

(A) Reference: ATA 27 Flight controls - B737 Training book - Page 10

154. Which component controls manual operation of the ailerons and flight spoilers ?

a) The rudder pedals

b) The elevator control column

c) The aileron control wheel

(A) Reference: ATA 27 Flight controls - B737 Training book - Page 17

155. Where is the stabilizer electric trim switch ?

a) It is on the outboard side of each control wheel.

b) It is on the top of the elevator control column.

c) It is on the P5 aft overhead panel

(A) Reference: ATA 27 Flight controls - B737 Training book - Page 17

156. Where are the aileron trim switches ?

a) The switches are on the outboard side of each control wheel.

b) The switches are on the aileron/rudder trim panel on the aft electronic P8 panel.

c) The switches are on the top of the elevator control column.

(A) Reference: ATA 27 Flight controls - B737 Training book - Page 20

157. The flight crew uses two control wheels for

a) pitch control operation.

b) yaw control operation.

c) roll control operation.

(A) Reference: ATA 27 Flight controls - B737 Training book - Page 50

158. How many Spoiler on each wing ?

a) Six. There is one spoiler inboard of each engine strut and five spoilers outboard of each engine strut.

b) Five. There is two spoiler inboard of each engine strut and three spoilers outboard of each engine strut.

c) Six. There is two spoiler inboard of each engine strut and four spoilers outboard of each engine strut.

(A) Reference: ATA 27 Flight controls - B737 Training book - Page 78

159. How many ground spoiler on each wing ?

a) Four. The ground spoilers are two outboard and two inboard spoiler on each wing.

b) Two. The ground spoilers are the most outboard and the most inboard spoiler on each wing.

c) One. The ground spoilers are the most inboard spoiler on each wing.

(A) Reference: ATA 27 Flight controls - B737 Training book - Page 78

160. On manual operation, the flight spoiler control system receives inputs from

a) the control columns and the control wheels.

b) the pedal and the speedbrake lever.

c) the control wheels and the speedbrake lever.

(A) Reference: ATA 27 Flight controls - B737 Training book - Page 84

161. The Flight Spoiler actuators are powered by

a) The hydraulic system A.

b) The hydraulic system B.

c) The hydraulic systems A or B.

(A) Reference: ATA 27 Flight controls - B737 Training book - Page 102

162. Which module controls the automatic operation of the speedbrakes ?

a) Flight control computer

b) The auto speedbrake module

c) Antiskid/autobrake control unit

(A) Reference: ATA 27 Flight controls - B737 Training book - Page 115

163. The SPEED BRAKE ARMED light shows when

a) the automatic operation of the speedbrake system arms correctly.

b) the speedbrake lever in ARMED position.

c) the SPEED BRAKE ARM function inoperatived.

(A) Reference: ATA 27 Flight controls - B737 Training book - Page 116

164. The Ground Spoiler actuators are powered by

a) Both hydraulic systems A and B.

b) The hydraulic system A.

c) The hydraulic system B.

(A) Reference: ATA 27 Flight controls - B737 Training book - Page 118

165. Which component lets the ground spoilers operate only when the airplane is on the ground ?

a) PSEU

b) The auto speedbrake module

c) The ground spoiler interlock valve

(A) Reference: ATA 27 Flight controls - B737 Training book - Page 143

166. During stabilizer electric trim operation, if the pilot moves the control column in the opposite direction,

a) the column cutout switches stop the stabilizer electric trim.

b) the stabilizer electric trim will change to the opposite direction.

c) the stabilizer electric trim keeps priority and continues to operation.

(A) Reference: ATA 27 Flight controls - B737 Training book - Page 165

167. These are the elevator controls and indications in the flight compartment:

a) Elevator control wheel, FLIGHT CONTROL switches and Elevator FEEL DIFF PRESS light.

b) Elevator control columns, FLIGHT CONTROL switches and Elevator FEEL DIFF PRESS light.

c) Elevator control columns, Elevator trim switches and Elevator FEEL DIFF PRESS light.

(A) Reference: ATA 27 Flight controls - B737 Training book - Page 168

168. Where is the elevator feel computer ?

a) The elevator feel computer is in forward equipment compartment.

b) The elevator feel computer is in aft cargo compartment.

c) The elevator feel computer is on the aft right wall of the stabilizer compartment.

(A) Reference: ATA 27 Flight controls - B737 Training book - Page 186

169. The elevator feel computer receives hydraulic pressure, mechanical inputs and

a) pitot pressure.

b) data from ADIRU.

c) data form FCC.

(A) Reference: ATA 27 Flight controls - B737 Training book - Page 193

170. These are the stabilizer controls in the flight compartment:

a) Stabilizer trim wheels, Stabilizer trim cutout switches and Stabilizer trim override switch.

b) Stabilizer trim switches, Stabilizer trim wheels, Stabilizer trim cutout switches and Stabilizer trim override switch.

c) Stabilizer trim switches, Stabilizer trim wheels and Stabilizer trim override switch.

(A) Reference: ATA 27 Flight controls - B737 Training book - Page 216

171. How to control the rudder in manual operation ?

a) The pilot uses the rudder pedals to control the rudder.

b) The pilot uses the rudder pedals or control column to control the rudder.

c) The pilot uses the rudder pedals or the rudder trim control to control the rudder.

(A) Reference: ATA 27 Flight controls - B737 Training book - Page 241

172. Which components make the command to move the TE flaps ?

a) The flap lever for normal operation and the ALTERNATE FLAPS switches for alternate operation.

b) The FSEU for normal operation and the flap lever for alternate operation.

c) The FSEU for normal operation and the ALTERNATE fLAPS switches for alternate operation.

(A) Reference: ATA 27 Flight controls - B737 Training book - Page 283

173. Flap position indication is a function of

a) Flap Control Unit

b) FSEU

c) PSEU

(A) Reference: ATA 27 Flight controls - B737 Training book - Page 296

174. During the normal operation, if two or more LE devices move away from their commanded position,

a) LE devices automatically switch to alternate operation.

b) the LE cruise depressurization function prevents extension of the LE flaps and slats.

c) the LE UCM detection function stops the LE normal operation.

(A) Reference: ATA 27 Flight controls - B737 Training book - Page 429

175. During the normal operation, if the airplane comes near a stall condition,

a) the autoslat function causes the LE slats to move from the extend position to the full extend position.

b) the LE UCM detection function stops the LE normal operation.

c) the LE cruise depressurization function prevents extension of the LE flaps and slats.

(A) Reference: ATA 27 Flight controls - B737 Training book - Page 429

176. During the alternate operation, what functions are not available.

a) the LE flaps extension function, LE UCM detection function and autoslat function

b) the LE cruise depressurization function, LE UCM detection function and autoslat function

c) the LE cruise depressurization function and autoslat function

(A) Reference: ATA 27 Flight controls - B737 Training book - Page 429

177. How many positions can the LE flaps and slats move to ?

a) two positions.

b) The LE flaps move to two positions, and the LE slats move to three positions.

c) three positions.

(A) Reference: ATA 27 Flight controls - B737 Training book - Page 429

178. During normal operation, the LE flap and slat actuators use power from

a) hydraulic system A.

b) hydraulic system A or B.

c) hydraulic system B.

(A) Reference: ATA 27 Flight controls - B737 Training book - Page 433

179. Why does the LE devices annunciator panel have only the transit and extend lights for the LE flaps but has all three types of lights for the LE slats ?

a) Because the LE flaps have only two positions.

b) Because the LE flaps only need to indicate the transit and extend positions.

c) Because the LE devices annunciator panel doesn't have enough place to indicate more.

(A) Reference: ATA 27 Flight controls - B737 Training book - Page 438

180. Which computers calculate the autoslat commands ?

a) FSEU

b) SMYD.

c) FCC

(A) Reference: ATA 27 Flight controls - B737 Training book - Page 458

181. The takeoff warning function is in

a) PSEU

b) FCC

c) SMYD

(A) Reference: ATA 27 Flight controls - B737 Training book - Page 470

ATA 28:

182. A SHUT-OFF SYSTEM IS USED DURING REFUELLING TO

a) AUTOMATICALLY CLOSE THE MANUAL DEFUELLING VALVE WHEN THE WING TANKS ARE FULL.

b) AUTOMATICALLY CLOSE THE FUELLING VALVE IN EACH FUEL TANK WHEN THE TANK IS FULL.

c) PREVENT REFUELLING PRESSURES IN EXCESS OF 50 PSI.

(A) SDS-AMM 28-21-00 PAGE4/18

183. TO DEFUEL NO. 1 TANK

a) SELECT THE NO. 1 MAIN TANK FUEL PUMPS ON, THE CROSSFEED VALVE OPEN AND THE MANUAL DEFUELLING VALVE OPEN.

b) SELECT THE NO. 1 MAIN TANK FUEL PUMPS ON, THE CROSSFEED VALVE CLOSED AND THE MANUAL DEFUELLING VALVE OPEN.

c) SELECT THE NO. 1 AND NO. 2 MAIN TANK FUEL PUMPS ON, THE CROSSFEED VALVE OPEN AND THE MANUAL DEFUELLING VALVE OPEN.

(A) AMM TASK28-26-00

184. THE FUEL TEMPERATURE INDICATOR READS THE TEMPERATURE OF THE FUEL IN

a) THE CENTRE TANK

b) THE NO. 2 TANK.

c) THE NO. 1 TANK.

(A) SDS-AMM 28-00-00 PAGE4

185. THE MANUAL DE-FUELLING VALVE IS LOCATED

a) OUTBOARD OF THE NO. 2 ENGINE

b) OUTBOARD OF THE NO. 1 ENGINE.

c) INBOARD OF THE NO. 2 ENGINE

(A) SDS-AMM 28-26-00 PAGE6

186. DRIPSTICKS (OR FLOATSTICKS) ARE INSTALLED IN

a) 5 IN EACH MAIN TANK AND 2 IN THE CENTRE TANK

b) 7 IN EACH MAIN TANK AND 6 IN THE CENTRE TANK.

c) 6 IN EACH MAIN TANK AND 4 IN THE CENTRE TANK (A) SDS-AMM 28-44-00 PAGE2

187. THE FUELLING VALVE POSITION LIGHTS ON THE EXTERNAL FUELING PANEL ILLUMINATE (BLUE) WHEN

a) THE RESPECTIVE FUELLING VALVE IS IN TRANSIT

b) THE RESPECTIVE FUELLING VALVE IS OPEN AND FUEL IS BEING TRANSFERRED INTO THE TANK.

c) THERE IS POWER TO THE RESPECTIVE FUELLING VALVE SOLENOID

(A) SDS-AMM 28-21-00 PAGE12&22

188. WHEN THE APU IS INOPERATIVE AND NO EXTERNAL POWER IS AVAILABLE, REFUELLING CAN BE ACCOMPLISHED AS FOLLOWS

a) BATTERY SWITCH ON, STANDBY POWER SWITCH BAT, THE ENTIRE FUEL SYSTEM WILL OPERATE NORMALLY

b) BATTERY SWITCH OFF, STANDBY POWER SWITCH BAT, THE ENTIRE FUEL SYSTEM WILL OPERATE NORMALLY

c) BATTERY SWITCH ON,STANDBY POWER SWITCH BAT, THE ENTIRE FUEL SYSTEM WILL OPERATE NORMALLY, EXCEPT FOR THE FUEL SHUT-OFF SYSTEM.

(A) SDS-AMM 28-21-00 PAGE 22

189. TO DEFUEL NO. 2 TANK ONLY

a) SELECT THE NO. 1 AND NO. 2 MAIN TANK FUEL PUMPS ON, THE CROSSFEED VALVE OPEN AND THE MANUAL DEFUELING VALVE OPEN.

b) SELECT THE NO. 2 MAIN TANK FUEL PUMPS ON, THE CROSSFEED VALVE OPEN AND THE MANUAL DEFUELING VALVE OPEN.

c) SELECT THE NO. 2 MAIN TANK FUEL PUMPS ON AND THE MANUAL DEFUELLING VALVE OPEN

(A) SDS-AMM 28-26-00 PAGE 10

190. THE CROSSFEED VALVE WHEN OPEN

a) CLOSES THE BYPASS VALVE IN EACH WING TANK.

b) ALLOWS TRANSFER OF FUEL BETWEEN WING TANKS ONLY.

c) ALLOWS FUEL TRANSFER FROM ANY TANK TO EITHER ENGINE OR APU.

(A) SDS-AMM 28-22-00 PAGE 26

191. THE CROSSFEED SELECTOR IN THE OPEN POSITION

a) EXTINGUISHES THE BLUE VALVE OPEN LIGHT

b) CONNECTS THE ENGINE NO 1 AND NO. 2 FUEL FEED LINES BY OPENING THE FUEL CROSSFEED AND FUEL SHUT-OFF VALVES.

c) CONNECTS THE ENGINE NO 1 AND NO. 2 FUEL FEED LINES BY OPENING THE FUEL CROSSFEED VALVE.

(A) SDS-AMM 28-22-00 PAGE 26&28

192. THE CENTRE TANK FUELLING VALVE POSITION LIGHT ON THE EXTERNAL FUELLING PANEL IS

a) BLUE AND IS ILLUMINATED WHEN THE CENTRE TANK FUELLING VALVE IS CLOSED.

b) BLUE AND IS EXTINGUISHED WHEN THE CENTRE TANK FUELLING VALVE IS CLOSED.

c) RED AND IS EXTINGUISHED WHEN THE CENTRE TANK FUELLING VALVE IS CLOSED.

(A) SDS-AMM 28-21-00 PAGE12&22

193. THE EXTERNAL FUELLING PANEL IS LOCATED

a) ON THE OPPOSITE WING TO THE DE-FUELLING PANEL.

b) AT THE LEFT WING LEADING EDGE

c) AT THE RIGHT WING LEADING EDGE.

(A) SDS-AMM 28-00-00 PAGE4

194. EACH FUEL TANK CONTAINS

a) 1 AC POWERED FUEL PUMPS WHICH IS FUEL COOLED AND LUBRICATED, AND 1 DC FUEL PUMP.

b) 2 DC POWERED FUEL PUMPS.

c) 2 AC POWERED FUEL PUMPS WHICH ARE FUEL COOLED AND LUBRICATED.

(A) SDS-AMM 28-22-00 PAGE 14;20 & 22

195. WHICH VALVE CONNECTS THE FUEL (ENGINE 2) MANIFOLD TO THE FUELLING MANIFOLD

a) THE CROSSFEED VALVE

b) THE FUELLING VALVE

c) THE MANUAL DEFUELLING VALVE.

(A) SDS-AMM 28-26-00 PAGE 8

196. THE ENGINE FUEL SHUT OFF VALVES

a) ARE CABLE OPERATED TO CLOSE OR OPEN.

b) ARE HOT BATTERY BUS POWERED AND MAY BE CLOSED BY THE ENGINE START LEVER OR THE RESPECTIVE ENGINE FIRE SWITCH.

c) ARE AC OPERATED TO OPEN, AND MECHANICALLY CLOSED BY THE ENGINE START LEVER OR FIRE SWITCH.

(A) SDS-AMM 28-22-00 PAGE 32 & 33

ATA 29:

197. IF AN ELECTRIC HYDRAULIC PUMP OVERHEAT LIGHT COMES ON

a) THE PUMP WILL BE AUTOMATICALLY SWITCHED OFF AND THE OVERHEAT LIGHT EXTINGUISHED

b) TURN THE ASSOCIATED SYSTEM ELECTRIC AND ENGINE HYDRAULIC PUMPS OFF.

c) TURN THE ASSOCIATED SYSTEM ELECTRIC HYDRAULIC PUMP OFF.

(A) SDS-AMM 29-10-00 PAGE 6

198. THE STANDBY SYSTEM LOW PRESSURE LIGHT IS ARMED

a) ONLY WHEN THE STANDBY PUMP OPERATION HAS BEEN SELECTED OR AUTOMATIC STANDBY FUNCTION IS ACTIVATED.

b) AT ALL TIMES.

c) ONLY WHEN THE STANDBY PUMP OPERATION HAS BEEN SELECTED OR EITHER SPOILER SWITCH HAS BEEN SELECTED TO OFF.

(A) SDS-AMM 29-30-00 PAGE 28

199. THE STANDBY HYDRAULIC PUMP ONLY SUPPLIES PRESSURE TO THE

a) STANDBY RUDDER AND LEADING EDGE SLATS.

b) STANDBY RUDDER ACTUATOR, LEADING EDGE DEVICES AND THRUST REVERSERS.

c) STANDBY RUDDER, LEADING EDGE DEVICES AND BRAKES.

(A) SDS-AMM 29-22-00 PAGE 4

200. IF EITHER FLIGHT CONTROL SWITCH IS MOVED TO THE STBY RUD POSITION

a) THE STANDBY PUMP WILL BE ACTIVATED AND THE STANDBY HYDRAULIC LOW QUANTITY LIGHT WILL BE ARMED

b) THE STANDBY PUMP WILL BE DE-ACTIVATED ALLOWING SYSTEM A PRESSURE TO POWER THE RUDDER AND THE STANDBY HYDRAULIC LOW PRESSURE LIGHT WILL BE ARMED.

c) THE STANDBY PUMP WILL BE ACTIVATED AND THE STANDBY HYDRAULIC LOW PRESSURE LIGHT WILL BE ARMED.

(A) SDS-AMM 29-22-00 PAGE 21

201. LOW FLUID QUANTITY IN THE RESERVOIR OF SYSTEM A OR B CAN BE INDICATED BY ONE OF THE FOLLOWING

a) MECHANICAL INDICATION ON THE RESERVOIR

b) LOW QUANTITY LIGHT ON THE CENTRE INSTRUMENT PANEL

c) LOW QUANTITY LIGHT ON THE CENTRE INSTRUMENT PANEL ALONG WITH A MASTER CAUTION ENG ANNUNCIATOR LIGHT.

(A) SDS-AMM 29-10-00 PAGE 8

202. THE A AND B HYDRAULIC RESERVOIRS ARE PRESSURISED BY

a) AIR FROM THE 14TH STAGE ONLY.

b) AIR FROM THE PNEUMATIC MANIFOLD.

c) HYDRAULIC FLUID FROM THE STANDBY RESERVOIR.

(A) SDS-AMM 29-09-00 PAGE 2

203. SELECTING AN ENGINE DRIVEN HYDRAULIC PUMP SWITCH TO OFF WILL

a) ELECTRICALLY CLOSE THE FLUID SUPPLY VALVE AT THE RESERVOIR.

b) DE-ACTIVATE THE SOLENOID-HELD BLOCKING VALVE AND ISOLATE FLUID FROM THE USING UNIT.

c) ACTIVATE THE SOLENOID-HELD BLOCKING VALVE AND ISOLATE FLUID FROM THE USING UNIT.

(A) SDS-AMM 29-10-00 PAGE 6

204. THE NORMAL AND MAXIMUM READINGS ON THE HYDRAULIC SYSTEM PRESSURE INDICATOR ARE

a) 3000 : 3500PSI

b) 2500 : 3200PSI

c) 3000 : 3750PSI

(A) SDS-AMM 29-10-00 PAGE 1 & 21

205. THE STANDBY HYDRAULIC RESERVOIR IS KEPT TOPPED UP FROM

a) OIL CONTAINERS USED BY ENGINEERS BEFORE EACH FLIGHT.

b) THE SYSTEM A RESERVOIR c) THE SYSTEM B RESERVOIR.

(A) SDS-AMM 29-22-00 PAGE 8

206. HYDRAULIC SYSTEM A POWER SOURCES ARE

a) ONE ENGINE DRIVEN PUMP (ENG 1) AND ONE ELECTRICAL MOTOR PUMP (ELECT 1).

b) ONE ENGINE DRIVEN PUMP (ENG 1) AND ONE ELECTRICAL MOTOR PUMP (ELECT 2).

c) ONE ENGINE DRIVEN PUMP (ENG 1), ONE ELECTRICAL MOTOR PUMP (ELECT 1) AND ONE STANDBY ELECTRIC PUMP.

(A) SDS-AMM 29-10-00 PAGE 6

207. ILLUMINATION OF A HYDRAULIC ELECTRIC PUMP OVERHEAT LIGHT INDICATES

a) AN OVERHEAT CONDITION IN THE HYDRAULIC RESERVOIR.

b) AN OVERHEAT CONDITION OF THE PUMP HYDRAULIC SUPPLY LINE.

c) AN OVERHEAT CONDITION IN THE CASE DRAIN LINE OR THE PUMP HOUSING.

(A) SDS-AMM 29-30-00 PAGE 30

208. THE MAXIMUM HYDRAULIC SYSTEM A OR B PRESSURE IS

a) 3000PSI

b) 3250PSI

c) 3500PSI

(A) SDS-AMM 29-10-00 PAGE 21

209. THE STANDBY HYDRAULIC FLUID

a) IS COOLED BY A HEAT EXCHANGER LOCATED IN NO. 2 TANK.

b) IS COOLED BY A HEAT EXCHANGER LOCATED IN NO. 1 TANK.

c) IS NOT COOLED

(A) SDS-AMM 29-22-00 PAGE 10

210. THE ENGINE DRIVEN HYDRAULIC PUMP SWITCH

a) IN THE OFF POSITION WILL DE-ACTIVATE THE HYDRAULIC LOW PRESS LIGHT.

b) IS LEFT IN THE ON POSITION ON SHUTDOWN TO PROLONG THE LIFE OF THE BLOCKING VALVE SOLENOID.

c) SHOULD BE SWITCHED OFF IN THE EVENT OF THE ELECTRIC HYDRAULIC PUMP OVERHEAT LIGHT ILLUMINATING

(A) SDS-AMM 29-10-00 PAGE 6

ATA 30:

211. THERE ARE 8 ELECTRICALLY HEATED PITOT PRESSURE, ALPHA VANE AND TAT PROBES ON THE AIRPLANE. HOW MANY SWITCHES CONTROL THE SYSTEM?

a) 8

b) 2

c) 4

(A) STORMAVIATION-30-30 PAGE 40

212. WHICH SLATS HAVE ANTI-ICING PROTECTION?

a) ALL SLATS HAVE ANTI-ICING PROTECTION

b) THREE INBOARD LEADING EDGE SLATS OF THE WING

c) THREE OUTBOARD LEADING EDGE SLATS OF THE WING

(A) STORMAVIATION-30-11 PAGE 8

213. WHAT IS INDICATED BY FOUR AMBER WINDOW OVERHEAT LIGHTS ON THE WINDOWS ANTI-ICING PANEL?

a) THEY GIVE THE CREW VISUAL INDICATION OF APPLY CURRENT TO THE WINDOW HEAT SYSTEM WHEN NECESSARY

b) THEY GIVE INDICATION OF OVERHEAT CONDITION ON No1 AND No2 WINDOWS

c) THEY GIVE THE CREW VISUAL INDICATION OF OVERHEAT CONDITIONS FOR THE No1, 2, 3 AND 4 WINDOWS

(A) STORMAVIATION-30-41 PAGE 58

214. WHEN WILL THE WING THERMAL ANTI-ICE (WTAI) VALVES OPEN

a) WHEN THE THRUST LEVERS ARE LESS THAN 60 TRA

b) WHEN THE AIRPLANE IS ON THE GROUND AND OVERHEAT CONDITION OCCURS

c) ANY TIME WHEN THE WING ANTI-ICE SWITCH IS IN THE ON POSITION

(A) STORMAVIATION-30-11 PAGE 24

215. THE BLUE VALVE OPEN LIGHT ON THE ENGINE AND WING ANTI-ICE PANEL (P5) ILLUMINATES BRIGHT. WHAT DOES IT MEAN?

a) THE SWITCH POSITION AND VALVE POSITION DISAGREE, OR THE VALVE IS IN TRANSIT

b) THE SWITCH IS IN THE OFF POSITION, AND THE VALVE IS CLOSED

c) THE SWITCH IS IN THE ON POSITION, AND THE VALVE IS FULLY OPEN

(A) STORMAVIATION-30-11 PAGE 24

216. WHICH PROBES ARE CONTROLED BY THE PROBE HEAT B SWITCH?

a) FIRST OFFICER PITOT, RIGHT ELEVATOR PITOT, RIGHT ALPHA VANE, AUXILARY PITOT

b) COWL THERMAL ANTI-ICE, AIR DATA PROBE, TOTAL AIR TEMPERATURE (TAT) PROBE

c) CAPTAIN PITOT, LEFT ELEVATOR PITOT, LEFT ALPHA VANE, TOTAL AIR TEMPERATURE (TAT) PROBE

(A) STORMAVIATION-30-30 PAGE 40

217. WITH THE THRUST RESOLVER ANGLE GREATER THAN 60 DEGREES, WHAT IS THE EFFECT ON THE ANTI-ICE SYSTEM?

a) WING ANTI-ICE SOLENOID VALVE IS USED TO GIVE MAXIMUM COOLING

b) WING ANTI-ICE SHUTOFF VALVES ARE SIGNALLED FULLY CLOSED

c) ANTI-ICE BLEED AIR FLOW RATE IS REDUCED

(A) STORMAVIATION-30-11 PAGE 24

218. WHICH WINDOW(S) ARE HEATED WITH THE LEFT FWD WINDOW HEAT SWITCH ON?

a) L1, L2, L3

b) L2, L4, L5

c) L1 ONLY

(A) STORMAVIATION-30-41 PAGE 58

219. THE WINDOW HEAT ON LIGHT (GREEN) ILLUMINATES TO INDICATE

a) THE ASSOCIATED WINDOW HEAT SWITCH HAS BEEN SELECTED TO OVHT TEST.

b) THE WINDOW HEAT CONTROLLER IS APPLYING HEAT TO THE ASSOCIATED WINDOW

c) THE ASSOCIATED WINDOW HEAT SWITCH IS POSITIONED TO ON.

(A) STORMAVIATION-30-41 PAGE 58

220. THE COWL ANTI-ICE LIGHT IS

a) AMBER IN COLOUR, INDICATING OVER-TEMPERATURE ONLY.

b) AMBER IN COLOUR, INDICATING OVER-PRESSURE ONLY.

c) AMBER IN COLOUR, INDICATING OVER-TEMPERATURE OR OVER-PRESSURE.

(A) STORMAVIATION-30-20 PAGE 28

ATA 31:

221. AT POWER UP, EACH DISPLAY UNIT (DU) READS THE POSITION PINS (PIN PROGRAMING) AND CALCULATES ITS POSITION. IF A DU FAILS TO READ THE POSITION PINS, THEN:

a) IT WILL BE BLANK

b) THE MESSAGE "DU FAIL" WILL APPEAR ON THE DU

c) A WHITE DIAGONAL LINE WILL BE VISIBLE

(A) STORMAVIATION 31-62 PAGE 72

222. WITH WHICH UNIT DOES THE PRINTER HAVE AN INTERFACE?

a) ACARS MANAGEMENT UNIT AND FDAU (FLIGHT DATA ACQUISITION UNIT)

b) FDAU (FLIGHT DATA ACQUISITION UNIT) AND FMS

c) FDAU (FLIGHT DATA ACQUISITION UNIT) AND DEU (A) STORMAVIATION 31-62 PAGE 182

223. WHEN PERFORMING THE "DU LOOP TEST", A WHITE HIGHLIGHT BOX SHOWS AROUND ONE OF THE COAX CABLE INPUTS (e.g. Y[Y]YN) TO THE DISPLAY UNIT (DU). WHAT IS THE MEANING OF THIS INDICATION?

a) COAX CABLE INPUT ACTIVITY(THE SPECIFIC COAX CABLE THAT IS CURRENTLY BEING USED BY THE DU)

b) THIS COAX CABLE INPUT HAS A FAILURE

c) THIS COAX CABLE INPUT IS CURRENTLY INACTIVE

(A) STORMAVIATION 31-62 PAGE 124

224. WHAT IS THE PURPOSE OF THE 28VDC "HOLD UP" VOLTAGE?

a) ALL 6 DISPLAY UNIT (DU) USE THIS AS A BACK OF TRANSIENT CONDITION OF UP TO 10 SECONDS

b) THE DISPLAY ELECTRONICS UNIT (DEU) AND DUs USE THIS WHEN OPERATING ON STANDBY POWER

c) THE DEUs UES THIS FOR TRANSIENT CONDITIONS (POWER INTERRUPTIONS) OF UP TO 1 SECOND AND FOR ORDERLY SHUTDOWN OF THE PROCESSORS (UP TO 10 SECONDS)

(A) STORMAVIATION 31-62 PAGE 24

225. IF THE CONTROL PANEL SELECT SWITCH WAS SET TO BOTH ON 1 POSITION, WHICH OF THE FOLLOWING STATEMENTS IS TRUE?

a) CAPTAIN'S EFIS CONTROL PANEL CONTROLS THE CAPTAIN AND THE FIRST OFFICER'S PFD AND ND DISPLAYS

b) FIRST OFFICER'S EFIS CONTROL PANEL CONTROLS THE CAPTAIN AND THE FIRST OFFICER'S PFD AND ND DISPLAYS

c) CAPTAIN'S CONTROL & DISPLAY UNIT (CDU) CONTROLS THE CAPTAIN AND THE FIRST OFFICER'S PFD AND ND DISPLAYS

(A) STORMAVIATION 31-62 PAGE 95

226. IF THE DISPLAY ELECTRONICS UNIT (DEU) No2 FAIL THEN

a) COAX COUPLER No1 & 3, WILL SWITCH THEIR INPUT TO DEU NO1 AUTOMATICALLY

b) COAX COUPLERS No3 & 4 WILL LOSE THEIR INPUT

c) ONE INPUT IS LOST FOR EACH ONE OF THE FOUR COAX COUPLER UNIT

(A) STORMAVIATION 31-62 PAGE 26 & 27

227. WHEN THE AIRPLANE IS IN THE AIR, THE AURAL WARNING SYSTEM WILL PROVIDE A TAKE-OFF WARNING, IF

a) LEADING EDGE (LE) FLAPS AND SLATS ARE NOT EXTENDED AND TAKE-OFF INTERLOCK VALVE IS CLOSED

b) LEADING EDGE (LE) & TRAILING EDGE (TE) FLAPS AND SLATS ARE RETRACTED AND GROUND SPOILER INTERLOCK VALVE IS CLOSED

c) LEADING EDGE (LE) FLAPS ARE NOT EXTENDED AND GROUND SPOILER INTERLOCK VALVE IS OPENED

(A) STORMAVIATION 31-50 PAGE 248

228. THE IRS MASTER CAUTION UNIT PROVIDES DISCRETE INPUTS TO THE

a) MASTER CAUTION SYSTEM

b) MULTI MODE RECEIVERS

c) AUDIO WARNING UNIT

(A) STORMAVIATION 31-50 PAGE 218

229. WHAT IS THE SOURCE OF UTC DATE AND TIME FOR THE CLOCKS

a) DISPLAY ELECTRONICS UNIT (DEU)

b) FLIGHT MANEGEMENT COMPUTER (FMC)

c) MULTI MODE RECEIVER (MMR)

(A) STORMAVIATION 31-25 PAGE 196

230. FLIGHT DATA RECORDER (FDR) SYSTEM IS NORMAL NOT POWER ON THE GROUND. HOW IS IT POSSIBLE TO POWER IT ON GROUND FOR MAINTENANCE PURPOSES?

a) PLACING THE "TEST/NORMAL" SWITCH, ON THE FLIGHT RECORDER/MACH AIRSPEED WARNING TEST MODULE, TO THE "TEST" POSITION

b) PLACING THE "TEST/NORMAL" SWITCH, ON THE FLIGHT RECORDER/MACH AIRSPEED WARNING TEST MODULE, TO THE "NORMAL" POSITION, WHITE THE "AIR/GROUND WARN" CIRCUIT BREAKER ON THE P6 PANEL IS PULLED OUT

c) PLACING THE "TEST" SWITCH ON THE FDR'S FRONT FACE TO THE "ON" POSITION

(A) STORMAVIATION 31-62 PAGE 160

ATA 32:

231. VARIOUS AIRPLANE SYSTEMS USE COMMANDS AIR-GROUND RELAYS. WHICH COMPONENT GIVES DISCRETE SIGNAL TO THE AIR-GROUND RELAYS?

a) AIR-GROUND SENSORS

b) THE LANDING GEAR LOGIC SHELF

c) THE PROXIMITY SWITCH ELECTRONICS UNIT

(A) SDS-AMM 32-09-00 PAGE 16

232. THE AMBER PSEU LIGHT ON THE P5 PANEL COMES ON FOLLOWING BY THE MASTER CAUTION AND OVHD AMBER ANNUNCIATOR LIGHT AFTER LANDING AND EXTINGUISHES IMMEDIATELY AFTER PARKING BRAKE HAS BEEN SET. WHAT DOES IT MEAN?

a) NON-DISPATCHABLE FAULT HAS BEEN SENSED BY THE PSEU

b) DISPATCHABLE FAULT HAS BEEN SENSED BY THE PSEU

c) PSEU IS IN OVERRIDE CONDITION

(A) SDS-AMM 32-09-00 PAGE 40

233. THERE ARE THREE BITE TESTS YOU DO ON THE SUPPLEMENTAL PROXIMITY SWITCH ELECTRONICS UNIT (SPSEU) 1. THEY CAN BE DONE BY USING:

a) FRONT PANEL BITE ON THE PSEU

b) THE BITE CONTROLS AND INDICATION ON THE FRONT OF THE SPSEU

c) SPSEU GROUND TEST MENU THROUGH FMS CDU

(A) SDS-AMM 32=64-00 PAGE 10

234. THE GEAR WARNING HORN CAN ONLY BE CANCELLED IF

a) FLAPS ARE LESS THAN 10 AND RA ALT IS BETWEEN 200 AND 800 FEET

b) FLAPS ARE LESS THAN 15 AND THRUST LEVERS AT IDLE

c) FLAPS ARE GREATER THAN 25 BELOW 800 FEET

(A) SDS-AMM 32-61-00 PAGE 20

235. COMPLETE THE SENTENCE. HYDRAULIC PRESSURE FOR NOSE WHEEL STEERING TO THE STEERING METERING VALVE COMES:

a) DIRECTLY FROM HYDRAULIC SYSTEM A

b) FROM EXTEND PRESSURE LINE FROM THE LANDING GEAR EXTENSION AND RETRACTION SYSTEM

c) FROM B OR STANDBY HYDRAULIC SYSTEM, AS SELECTED BY LANDING GEAR TRANSFER VALVE

(A) SDS-AMM 32-51-00 PAGE 1

236. THE RUDDER PEDALS MOVEMENT DON'T INFLUENCE NOSE WHEEL STEERING, WHEN AIRCRAFT IS IN AIR. HOW IT IS ACHIEVED?

a) PSEU GIVES ELECTRIC SIGNAL TO STEERING SHUTOFF VALVE, IF AIR MODE IS DETECTED

b) THE ROTARY ACTUATOR DISENGAGES THE RUDDER PEDAL STEERING IN THE AIR

c) SWIVEL VALVE CUTS OFF HYDRAULIC PRESSURE, WHEN NOSE LANDING GEAR RETRACTS

(A) SDS-AMM 32-51-00 PAGE 2

237. WHAT HAPPENS IF STEERING WHEEL AND RUDDER PEDALS GIVE INPUT SIMULTANEOUSLY?

a) INPUTS WILL BE ADDED TOGETHER ALGEBRAICALLY

b) STEERING WHEEL INPUT WILL BE ACCOMPLISHED

c) RUDDER PEDAL INPUT WILL BE ACCOMPLISHED (A) SDS-AMM 32-51-00 PAGE 12

238. FROM WHERE DOES HYDRAULIC PRESSURE COME TO TAIL SKID ACTUATOR?

a) B OR STANDBY HYDRAULIC SYSTEM, AS SELECTED BY LANDING TRANSFER VALVE

b) EXTEND PRESSURE LINE FROM THE LANDING GEAR EXTENSION AND RETRACTION SYSTEM

c) THE SYSTEM A FLIGHT CONTROL HYDRAULIC MODULE PACKAGE

(A) SDS-AMM 32-71-01 PAGE 10

239. WHEN USING THE PSEU (PROXIMITY SENSING ELECTRONICS UNIT) BITE MENU, WHERE IS THE SENSOR RIGGING INFORMATION FOUND?

a) OTHER FUNCTIONS

b) INPUT/OUTPUT MONITORS

c) GROUND TEST

(A) SDS-AMM 32-09-00 PAGE 66

240. HOW MANY SENSORS ARE USED FOR THE AIR-GROUND SYSTEM?

a) 6

b) 3

c) 4

(A) SDS-AMM 32-09-00 PAGE 8

241. HOW IS THE PARKING BRAKE SHUTOFF VALVE POWERED?

a) HOT BATTERY BUS

b) DC BUS 1

c) 28V AC TRANSFER BUS

(A) SDS-AMM 32-44-00 PAGE 14

242. THE FUNCTION OF THE COMPENSATOR IN THE NOSE WHEEL STEERING SYSTEM IS TO:

a) ENSURE THE ACTUATORS STAY IN THEIR CURRENT POSITIONS WHEN THERE IS NO INPUT

b) ENHANCE SHIMMY DAMPING

c) PREVENT VIOLENT TURNING OF THE NOSE GEAR

(A) SDS-AMM 32-51-00 PAGE 14

243. IN THE GEAR AUDIO WARNING SYSTEM, RADIO ALTIMETER DATA IS SUPPLIED BY THE:

a) DISPLAY ELECTRONIC UNITS

b) FLIGHT CONTROL COMPUTERS

c) RADIO ALTIMETER RECEIVER (A) SDS-AMM 32-61-00 PAGE 23

244. WHEN THE LANDING GEAR LEVER IS OPERATED, WHICH OF THE FOLLOWING CORRECTLY DESCRIBES THE SYSTEM OPERATION?

a) AN ELECTRICAL SIGNAL IS SEND TO THE PSEU WHICH ELECTRICALLY RELEASES THE UPLOCKS IN THE PREDETERMINED SEQUENCE

b) A PUSH-PULL CABLE OPERATES THE LANDING GEAR SELECTOR AND THEN THE

TRANSFER VALVES

c) A RELEASE CABLE OPERATES THE UPLOCKS AND THE TRANSFER VALVE

(A) SDS-AMM 32-31-00 PAGE 6

245. IN AN UPLOCK SENSOR FAILED, WHICH POSITION WOULD IT FAIL IN?

a) NEAR OR FAR DEPENDING ON WHEN IT FAILED

b) ALWAYS FAIL FAR ELECTRICALLY

c) OPERATIONAL

(A) SDS-AMM 32-09-00 PAGE 10

246. THE LANDING WARNING HORN SOUND IF THE GEAR IS NOT DOWN AND LOCKED CAN BE CANCELLED PROVIDED THAT

a) FLAP POSITION IS FROM 0 TO 10 UNITS, RADIO ALT IS MORE THAN 200 FEET BUT LESS THAN 800 FEET

b) THRUST LEVERS ARE SET FOR LANDING, FLAP POSITION IS 15 UNITS

c) FLAP POSITION IS 30 UNITS

(A) SDS-AMM 32-61-00 PAGE 20

247. HOW IS NOSE LANDING GEAR DOORS MOVEMENT CONTROLLED DURING LG EXTENSION OR RETRACTION?

a) BY HYDRAULICALLY OPERATED ACTUATOR

b) BY ELECTRICALLY OPERATED ACTUATOR

c) MECHANICALLY BY RODS

(A) SDS-AMM 32-20-00 PAGE 8

248. COMPLETE THE SENTENCE. LANDING GEAR CONTROL LEVER POSITION IS CONTROLLED BY:

a) 2 CONTROL LEVER UP POSITION SWITCHES AND 2 CONTROL LEVER DOWN POSITION SWITCHES

b) 2 CONTROL LEVER UP POSITION SWITCHES ONLY

c) 2 LVDT (LINEAR VARIABLE DISPLACEMENT TRANSDUCER

(A) SDS-AMM 32-31-00 PAGE 4

249. IN WHICH OF THE FOLLOWING CONDITIONS WILL LANDING GEAR CONTROL LEVER LOCK SOLENOID BE ENERGIZED?

a) GROUND SPOILER INTERLOCK VALVE CLOSED, AIR/GROUND SYSTEM 1 IN AIR MODE

b) GROUND SPOILER INTERLOCK VALVE CLOSED, AIR/GROUND SYSTEM 1 IN GROUND MODE

c) GROUND SPOILER INTERLOCK VALVE OPEN, AIR/GROUND SYSTEM 1 OVERRIDDEN TO AIR MODE

(A) SDS-AMM 32-31-00 PAGE 13

250. A TIME DELAY, REQUIRED FOR THE MAIN LANDING GEAR DOWNLOCK OR UPLOCK ACTUATORS TO UNLOCK BEFORE THE MAIN GEAR ACTUATOR RECEIVES PRESSURE, DURING EXTENSION/RETRACTION OF MAIN LANDING GEAR (MLG) IS INITIATED BY:

a) TIMED OUT RELAY IN THE SELECTOR VALVE

b) TRANSFER CYLINDER LOCATED ON EACH REAR SPAR

c) RESTRICTOR/CHECK VALVE, LOCATED IN MAIN GEAR ACTUATOR

(A) SDS-AMM 32-32-00 PAGE 14

251. THE PSEU (PROXIMITY SENSING ELECTRONICS UNIT) SENDS A SIGNAL TO ENERGIZE THE LEVER LOCK SOLENOID WHEN

a) BOTH SYSTEM A AND B ARE PRESSURIZED

b) GROUND SPOILER INTERLOCK VALVE IS CLOSED

c) LEADING EDGE DEVICES CONTROL VALVE IS CLOSED

(A) SDS-AMM 32-31-00 PAGE 13

252. WHEN DOES THE TRANSFER CYLINDER GIVE A TIMER DELAY?

a) AIRCRAFT TOUCH DOWN

b) LG LOCKING

c) EXTENSION AND RETRACTION CYCLES

(A) SDS-AMM 32-32-00 PAGE 14

253. WHAT IS THE PURPOSE OF THE FRANGIBLE FITTING, INSTALLED ON THE INBOARD AND OUTBOARD SIDES OF BOTH WHEEL WELL RING IN THE MAIN LANDING GEAR WHEEL WELL

a) REMOVES UP PRESSURE FROM THE MAIN LANDING GEAR ACTUATOR WHEN A DAMAGED TIRE MOVE INTO THE MAIN LANDING GEAR WHEEL WELL

b) PREVENTS HYDRAULIC SYSTEM FLUID LOSS WHEN THE HYDRAULIC TUBE SYSTEM A IS BROKEN

c) INCREASES PRESSURE IN THE MAIN LANDING GEAR ACTUATOR WHEN THE MAIN LANDING GEAR DOES NOT EXTEND

(A) SDS-AMM 32-32-00 PAGE 16

254. WHAT IS THE MAXIMUM TURN ANGLE OF THE NOSE WHEEL THAT CAN BE COMMANDED BY THE RUDDER PEDALS?

a) 17 DEGREES

b) 7 DEGREES

c) 78 DEGREES

(A) SDS-AMM 32-51-00 PAGE 1

255. HYDRAULIC POWER FOR THE NORMAL BRAKES IS SUPPLIED BY

a) SYSTEM A TO OUTBOARD AND SYSTEM B TO THE INBOARD BRAKES

b) SYSTEM B

c) SYSTEM A

(A) SDS-AMM 32-41-00 PAGE 2

256. AFTER MANUAL EXTENSION OF THE LANDING GEAR, THE INDICATION ON THE FLIGHT DECK THAT THE CORRECT PROCEDURE HAS BEEN CARRIED OUT IS

a) 3 GREEN LIGHTS AND 3 RED LIGHTS

b) 3 GREEN LIGHTS

c) 3 RED LIGHTS

(A) SDS-AMM 32-61-00 PAGE 4

257. THE ALTERNATE BRAKE SYSTEM IS POWERED BY

a) SYSTEM B HYDRAULIC

b) ACCUMMULATOR PRESSURE

c) SYSTEM A HYDRAULIC

(A) SDS-AMM 32-41-00 PAGE 2

258. SELECTING THE NOSE WHEEL STEERING SWITCH ON THE CAPTAINS INSTRUMENT PANEL TO ALT PROVIDES THE

a) STANDBY HYDRAULIC SYSTEM PRESSURE FOR STEERING

b) B HYDRAULIC SYSTEM PRESSURE FOR STEERING

c) A HYDRAULIC SYSTEM PRESSURE FOR STEERING

(A) SDS-AMM 32-51-00 PAGE 1

259. THE NORMAL PRESSURE FOR THE HYDRAULIC BRAKE PRESSURE INDICATOR IS

a) 3000PSI

b) 1000PSI

c) 2800PSI

(A) SDS-AMM 32-41-00 PAGE 2

260. THE PRECHARGE PRESSURE IN THE BRAKE ACCUMULATOR IS

a) 3000PSI

b) 1500PSI

c) 1000PSI

(A) SDS-AMM 32-41-00 PAGE 16

261. THE 737 BRAKE SYSTEM HAS

a) TWO HYDRAULIC BRAKE ACCUMULATORS

b) ONE HYDRAULIC BRAKE ACCUMULATOR

c) NO HYDRAULIC BRAKE ACCUMULATORS (A) SDS-AMM 32-41-00 PAGE 2

262. THE NOSE WHEEL STEERING LOCKOUT PIN WHEN INSTALLED

a) LIMITS THE NOSE WHEEL STEERING TO +/- 7 DEGREES

b) ALLOWS PUSHBACK WITH HYDRAULIC SYSTEM A PRESSURISED

c) LOCKS THE NOSEWHEEL IN THE CENTRAL POSITION.

(A) SDS-AMM 32-51-00 PAGE 23

263. IF THE NOSE GEAR LOCKOUT PIN IS NOT INSTALLED

a) PUSHBACK MUST BE WITH BOTH SYSTEM A HYDRAULIC PUMPS OFF

b) PUSHBACK MUST BE WITH SYSTEM A ELEC. PUMP OFF

c) PUSHBACK MUST BE WITH BOTH SYSTEM A HYDRAULIC PUMPS ON

(A) SDS-AMM 32-51-00 PAGE 23

264. RUDDER PEDAL STEERING

a) CAN BE OVERRIDDEN BY THE NOSE WHEEL STEERING WHEEL

b) IS AVAILABLE UP TO +/- 7 DEGREES ON THE CAPTAIN'S RUDDER PEDALS ONLY.

c) IS ACTIVATED ANYTIME THE NOSE GEAR STRUT IS EXTENDED.

(A) SDS-AMM 32-51-00 PAGE 12

ATA 33:

265. MOST OF THE FLIGHT COMPARTMENT LIGHT USE

a) 28 VAC

b) 115 VAC

c) 28 VDC

(A) STORMAVIATION DOC ATA 33 PAGE 10

266. WHERE IS THE SPARE BULB STOWAGE

a) CABIN FWD PURSE PANEL

b) COCKPIT RIGHT HAND SIDE

c) E/E COMPARTMENT

(A) ( AMM 33-11-00 , page 201 )

267. HOW DO YOU TEST COCKPIT LIGHT

a) TEST SWITCH ON P1 PANEL

b) TEST SWITCH ON P6 PANEL

c) TEST SWITCH IN E/E PANEL (A) ( AMM 33-11-00 , page 202 )

268. FAILURE OF ONE MAIN A.C. BUS CAUSES

a) PARTIAL LOSS OF COCKPIT AND PASSENGER LIGHTING

b) ALL CABIN LIGHTS TO EXTINGUISH

c) A. NO EFFECT ON THE COCKPIT OR PASSENGER LIGHTING

(A) SDS-AMM 33-11-00 PAGE 2 & 33-22-00 PAGE 2

269. THE EMERGENCY EXIT LIGHTS AND SIGNS ARE POWERED

a) FROM SEPARATE EMERGENCY POWER SUPPLIES INSTALLED IN THE PASSENGER CABIN

b) FROM THE HOT BATTERY BUS

c) A. FROM THE BATTERY BUS

(A) SDS-AMM 33-51-00 PAGE 14

270. MOST OF THE FLIGHT COMPARTMENT LIGHTS USE

a) 28 VAC

b) 115 VAC

c) 28 VDC

(A) SDS-AMM 33-11-00 PAGE 2

271. WHEN ARMED, THE EMERGENCY EXIT LIGHTS WILL AUTOMATICALLY COME ON

a) WHEN THE AIRCRAFT REACHES A PRESET G-LOAD LIMIT

b) IF ELECTRICAL POWER TO DC BUS 1 FAILS OR AC POWER IS TURNED OFF

c) UPON CONTACT WITH WATER

(A) SDS-AMM 33-51-00 PAGE 16

272. THE NO SMOKING SIGNS WHEN SELECTED TO AUTO

a) A. ILLUMINATE WHEN THE LANDING GEAR IS EXTENDED.

b) ILLUMINATE WHEN THE FLAPS ARE EXTENDED AND THE LANDING GEAR IS RETRACTED

c) ILLUMINATE WHEN THE LANDING GEAR IS EXTENDED AND THE FLAPS ARE GREATER THAN 10 DEGREES

(A) SDS-AMM 33-25-00 PAGE 9

273. THE FASTEN BELTS SIGNS WHEN SELECTED TO AUTO WILL

a) EXTINGUISH WHEN THE FLAPS ARE EXTENDED AND THE LANDING GEAR IS UP

b) ILLUMINATE WHEN THE AUTO-PILOT IS NOT ENGAGED.

c) ILLUMINATE WHEN LANDING GEAR OR FLAPS ARE EXTENDED

(A) SDS-AMM 33-25-00 PAGE 9

274. IF THERE IS A COMPLETE ELECTRICAL POWER FAILURE

a) THE LEFT DOME LIGHT SUPPLIES EMERGENCY GENERAL LIGHTING

b) THE RIGHT DOME LIGHT SUPPLIES EMERGENCY GENERAL LIGHTING

c) THE MAP LIGHT SUPPLIES EMERGENCY GENERAL LIGHTING

(A) SDS-AMM 33-14-00 PAGE 8

275. IN EACH WHEEL WELL HAVE

a) A DOME LIGHT AND A FLOODLIGHT

b) A DOME LIGHT

c) A FLOODLIGHT

(A) SDS-AMM 33-32-00 PAGE 2

276. WITH THE NO SMOKING & FASTEN BELTS SWITCHES IN THE AUTO POSITION

a) THE NO SMOKING SIGNS WILL ILLUMINATE ANY TIME THE FLAPS ARE EXTENDED

b) THE NO SMOKING SIGNS WILL ILLUMINATE ANY TIME THE GEAR IS EXTENDED.

c) THE NO SMOKING SIGNS WILL ILLUMINATE ONLY WHEN GEAR AND FLAPS ARE EXTENDED

(A) SDS-AMM 33-25-00 PAGE 9

277. PLACING THE LIGHTS TEST SWITCH TO THE TEST POSITION

a) INHIBITS THE MASTER CAUTION RECALL SYSTEM

b) ILLUMINATES ALL AMBER CAUTION LIGHTS ONLY

c) ILLUMINATES ALL COCKPIT LIGHTING AND WARNING LIGHTS

(A) SDS-AMM 33-18-00 PAGE 2

278. THE P5 SWITCH IS IN THE ARM POSITION. WHEN DO THE EMERGENCY LIGHTS COME ON?

a) WHEN THE MAIN LIGHTING SYTEM HAS FAILED

b) WHEN THE 28VDC BUS 2 VOLTAGE DECREASES BELOW 12 VOLTS

c) WHEN THE 28VDC BUS 1 VOLTAGE DECREASES BELOW 12 VOLTS

(A) SDS-AMM 33-51-00 PAGE 16

279. WITH THE TAXI LIGHT SWITCH SET TO AUTO POSITION, WHEN THE TAXI LIGHT OFF?

a) AFTER THE FIRST ENGINE STOP

b) WHEN THE NOSE LANDING GEAR IS NOT IN THE DOWN AND LOCKED POSITION

c) WHEN THE MAIN LANDING GEAR IS NOT IN THE DOWN AND LOCKED POSION

(A) SDS-AMM 33-45-00 PAGE 6

ATA 34:

280. THE AIRPLANE PITOT SYSTEM CONSISTS OF

a) CAPTAIN'S, FIRST OFFICER'S, AUXILIARY NO. 1

b) CAPTAIN'S, FIRST OFFICER'S

c) CAPTAIN'S, FIRST OFFICER'S, AUXILIARY NO. 1 AND AUXILIARY NO. 2

(A) SDS-AMM 34-11-00 PAGE 14

281. 139. THE AIRPLANE STATIC SYSTEM CONSISTS OF

a) A. CAPTAIN'S, FIRST OFFICER'S, AUXILIARY NO. 1, AUXILIARY NO. 2 AND ALTERNATE

b) CAPTAIN'S, FIRST OFFICER'S, AUXILIARY NO. 1, AUXILIARY NO. 2

c) A. CAPTAIN'S, FIRST OFFICER'S

(A) SDS-AMM 34-11-00 PAGE 14

282. 139. THE ELECTRONIC HORIZONTAL SITUATION INDICATOR (EHSI) PROVIDES

a) A MULTICOLOR DISPLAY OF VARIOUS NAVIGATIONAL AND WEATHER RADAR DATA

b) A. A MULTICOLOR DISPLAY OF VARIOUS NAVIGATIONAL DATA

c) A. WEATHER RADAR DATA

(A) SDS-AMM 31-62-00 PAGE 98.140

283. HOW MANY NAVIGATION UNIT (VOR/ILS RECEIVERS) ARE INSTALLED ON AIRCRAFT

a) 02 UNIT

b) 01 UNIT

c) 03 UNIT

(A) SDS-AMM 34-51-00 PAGE 32

284. THE SUPP NAV DATA PAGES ARE ACCESSIBLE

a) IN FLIGHT ONLY

b) AT ANY TIME

c) ON THE GROUND ONLY

(A) SDS-AMM 34-61-00 PAGE 98.178

285. MARKER BEACON ANTENNA RECEIVERS THE 75 MHZ SIGNAL AND SENDS IT TO

a) VOR/MARKER BEACON (VOR/MB) RECEIVER 1

b) VOR/MB RECEIVER 2

c) VOR/MB RECEIVER 1 & VOR/MB RECEIVER 2

(A) SDS-AMM 34-32-00 PAGE 20

286. THE WEATHER RADAR WX/TURB MODE DISPLAYS DETECTED TURBULENCE WITHIN

a) 160 NM

b) 80 NM.

c) 40 NM.

(A) SDS-AMM 34-43-00 PAGE 41

287. WHAT HAPPENS IF AN ATTITUDE FAILURE OCCURS?

a) THE ATTITUDE SCALE GOES OUT OF THE VIEW ONLY

b) THE ATTITUDE SCALE GOES OUT OF THE VIEW AND ALT FLAG IS DISPLAYED

c) THE ALT FLAG IS DISPLAYED ONLY

(A) SDS-AMM 34-21-00 PAGE98.26

288. THE TCAS/ATC CONTROL PANEL CONTROLS

a) TCAS COMPUTER DIRECTLY AND ATC TRANSPONDERS THROUGH THE TCAS COMPUTER

b) ATC TRANSPONDERS AND THE TCAS COMPUTER DIRECTLY

c) ATC TRANSPONDERS DIRECTLY AND THE TCAS COMPUTER THROUGH THE ATC TRANSPONDERS

(A) SDS-AMM 34-45-00 PAGE56

289. IF THE ALTERNATE VMO/MMO SWITCH IS IN THE "ALTN" POSITION THEN THE

a) THE AIR DATA AND INERTIAL REFERENCE UNITS (ADIRU) ADJUST THE VMO/MMO CURVE TO COMPENSATE FOR A FLIGHT WITH THE LANDING GEAR DOWN

b) THE AIR DATA AND INERTIAL REFERENCE UNITS (ADIRU) USES THE ALTERNATE STATIC PORTS AS INPUT IN ORDER TO CALCULATE THE VMO/MMO CURVE, FOR NORMAL FLIGHT

c) THE AIR DATA AND INERTIAL REFERENCE UNITS (ADIRU) USES THE ALTERNATE PITOT PROBE AND STATIC PORTS AS INPUT IN ORDER TO CALCULATE THE VMO/MMO CURVE, FOR A FLIGHT WITH FLAPS/SLATS DOWN

(A) SDS-AMM 34-21-00 PAGE 6

290. COMPLETE THE SENTENCE. THE WHITE "ALIGN" ANNUCIATOR ON THE AIR DATA AND INERTIAL REFERENCE UNITS (ADIRU) MODE SELECT UNIT (MSU) WILL

a) FLASHING DURING THE ADIRU ALIGNMENT AND WILL COME ON STEADY, WHEN THE ADIRU NEEDS INFORMATION

b) COME ON STEADY DURING ADIRU ALIGNMENT AND WILL FLASH, WHEN THE ADIRU NEEDS INFORMATION

c) COME ON STEADY DURING ADIRU ALIGNMENT AND WILL FLASH, WHEN AN ADIRU FAULT IS DETECTED

(A) SDS-AMM 34-21-00 PAGE 64

291. WHICH OF THE FOLLOWING OCCURS WHEN "B/CRS" (BACK COURSE) IS SELECTED ON THE STANDBY ATTITUDE INDICATOR?

a) THE LOCALIZER AND GLIDESLOPE DEVIATION BAR GO OUT OF VIEW

b) THE LOCALIZER DEVIATION BAR GOES OUT OF VIEW AND THE GLIDESLOPE DEVIATION BAR REVERSES POLARITY

c) THE LOCALIZER DEVIATION BAR RESERVES POLARITY AND THE GLIDESLOPE DEVIATION BAR GOES OUT OF VIEW

(A) SDS-AMM 34-24-00 PAGE 12

292. WHAT IS THE PURPOSE OF THE ELEVATION AND SCAN DISABLE SWITCHES LOCATED ON THE ANTENNA PEDESTAL?

a) TO STOP THE RF TRANSMISSIONS FROM THE WXR R/T, DURING MAINTENCE

b) TO REMOVE POWER TO THE SCAN AND ELEVATION MOTORS IN ORDER TO PREVENT MOVEMENT OF THE ANTENNA DURING MAINTENCE

c) TO SET THE ANTENNA TO THE NEUTRAL POSITION, BEFORE REMOVAL

(A) SDS-AMM 34-43-00 PAGE 53

293. WHICH OF THE FOLLOWING STATEMENTS, IS THE CORRECT ONE ABOUT INSTRUMENT LANDING SYSTEM (ILS) No1 BITE?

a) IN ORDER TO BE PERFORMED, A TEST SET IS REQUIRED

b) IT MAY BE PERFORMED FROM THE CONTROL DISPLAY UNITS (CDS) IN THE FLIGHT DECK

c) IT IS PERFORMED FROM THE FRONT PANEL OF THE MULTI MODE RECEIVER (MMR) No1

(A) SDS-AMM 34-31-00 PAGE 27

294. WHICH IS THE PURPOSE, OF THE "TONE" SELECTOR ON THE AUTOMATIC DIRECTION FINDER (ADF) CONTROL PANEL?

a) TO TURN ON THE ANTENNA/TONE MODULATORS CIRCUIT IN THE ADF RECEIVER

b) TO TURN ON THE BEAT FREQUENCY OSCILLATOR (BFO) IN THE ADF RECEIVER

c) TO ADJUST THE TONE OF THE OUTPUT SIGNALS (STATION AUDIO TONE)

(A) SDS-AMM 34-57-00 PAGE 28

ATA 35:

295. THE PASSENGER OXYGEN SYSTEM IS ACTIVATED WHEN THE CABIN REACHES AN ALTITUDE OF

a) 14,000 FEET

b) 10,000 FEET

c) 9,500 FEET

(A) SDS-AMM 35-20-00 PAGE 26

296. THE OXYGEN SYSTEM ON BOARD THE AIRCRAFT HAS

a) TWO SEPARATE SYSTEMS, ONE FOR THE FLIGHT DECK AND ONE FOR THE CABIN

b) A. ONE SINGLE SYSTEM FOR ALL OXYGEN REQUIREMENTS

c) THREE SEPARATE SYSTEMS, ONE FOR THE FLIGHT DECK, ONE FOR THE CABIN AND ONE FOR THE AFT GALLEY CABIN ATTENDANTS

(A) SDS-AMM 35-00-00 PAGE 02

297. DURING A DECOMPRESSION, THE PASSENGER OXYGEN WILL AUTOMATICALLY DROP FROM ITS STOWAGE COMPARTMENT. OXYGEN WILL FLOW TO ALL MASKS

a) IMMEDIATELY

b) ONLY WHEN ANY ONE OF THE MASKS OF AN OXYGEN GENERATOR UNIT IS PULLED DOWN

c) WHEN THE PASSENGER BREATHES, - THE SYSTEM IS ON DEMAND

(A) SDS-AMM 35-20-00 PAGE 24

298. IN EACH LAVATORY THERE IS

a) A TWO MASK PASSENGER OXYGEN UNIT

b) A ONE MASK PASSENGER OXYGEN UNIT

c) NO PASSENGER OXYGEN UNIT

(A) SDS-AMM 35-20-00 PAGE 21

299. TO USE THE PASSENGER PORTABLE OXYGEN

a) TURN THE YELLOW KNOB IN AN ANTICLOCKWISE DIRECTION AND PLUG THE BOTTLE INTO THE OVERHEAD CONNECTION

b) TURN THE YELLOW KNOB IN A COUNTERCLOCKWISE DIRECTION AND PLUG THE MASK INTO THE DESIRED BOTTLE OUTLET

c) PLUG THE MASK INTO THE DESIRED OUTLET ONLY

(A) SDS-AMM 35-30-00 PAGE 4

300. EACH PASSENGER OXYGEN UNIT IN THE CABIN

a) A. CAN BE SHUT OFF ONCE THE FLOW OF OXYGEN HAS STARTED - BY CABIN STAFF ACTION ONLY.

b) CANNOT BE SHUT OFF ONCE THE FLOW OF OXYGEN HAS STARTED

c) CAN BE SHUT OFF BY PULLING ANY MASK DOWN A SECOND TIME (A) SDS-AMM 35-20-00 PAGE 15

301. THE PASSENGER OXYGEN SYSTEM

a) IS SUPPLIED FROM THE PASSENGER OXYGEN BOTTLE LOCATED IN THE FORWARD CARGO COMPARTMENT

b) IS SUPPLIED BY INDIVIDUAL CHEMICAL OXYGEN GENERATORS, ONE FOR EACH PASSENGER

c) IS SUPPLIED BY INDIVIDUAL CHEMICAL OXYGEN GENERATORS LOCATED AT EACH PASSENGER SERVICE UNIT

(A) SDS-AMM 35-20-00 PAGE 2

302. PASSENGER OXYGEN FLOWING TO A MASK IS VISUALLY CONFIRMED BY

a) AN AMBER IN-LINE FLOW INDICATOR

b) A GREEN IN-LINE FLOW INDICATOR

c) A. A WHITE IN-LINE FLOW INDICATOR

(A) SDS-AMM 35-20-00 PAGE 24

303. NORMAL PRESSURE OF THE FLIGHT CREW OXYGEN SYSTEM IS

a) 1850 P.S.I

b) 2000 P.S.I.

c) A. 1500 P.S.I.

(A) SDS-AMM 35-10-00 PAGE 12

304. CREW OXYGEN SYSTEM PRESSURE IS CORRECTLY INDICATED WHEN

a) THE BATTERY SWITCH IS ON

b) DOES NOT REQUIRE ELECTRICAL POWER

c) A. THE BATTERY SWITCH IS OFF ( HOT BATTERY BUS ).

(A) SDS-AMM 35-10-00 PAGE 12

305. EACH PASSENGER OXYGEN GENERATOR WHEN ACTIVATED

a) WILL PRODUCE OXYGEN FOR APPROXIMATELY 12 MINUTES

b) WILL PRODUCE OXYGEN FOR APPROXIMATELY 7 MINUTES

c) WILL ONLY PRODUCE OXYGEN ON DEMAND FOR APPROXIMATELY 20 MINUTES

(A) SDS-AMM 35-20-00 PAGE 15

306. THE PASSENGER OXYGEN MASK STOWAGE UNITS ARE ACTIVATED

a) A. AUTOMATICALLY BY A BAROMETRIC PRESSURE SWITCH WHEN THE CABIN ALTITUDE IS 14,000 FEET OR WHEN THE PASS OXYGEN SWITCH ON THE OVERHEAD PANEL IS POSITIONED TO NORMAL

b) AUTOMATICALLY BY A BAROMETRIC PRESSURE SWITCH WHEN THE CABIN ALTITUDE IS 10,000 FEET OR WHEN THE PASS OXYGEN SWITCH ON THE OVERHEAD PANEL IS POSITIONED TO ON

c) AUTOMATICALLY BY A BAROMETRIC PRESSURE SWITCH WHEN THE CABIN ALTITUDE IS 14,000 FEET, OR WHEN THE PASS OXYGEN SWITCH ON THE OVERHEAD PANEL IS POSITIONED TO ON

(A) SDS-AMM 35-20-00 PAGE 2

ATA 36:

307. THE AMOUNT OF FAN AIR THAT IS DUCTED THROUGH THE PRE-COOLER +C46:G51IS CONTROLLED BY THE

a) RAM AIR CONTROLLER

b) THERMOSTATIC PRE-COOLER VAVLE

c) MODULATING AND SHUT-OFF VAVLE

(A) DOCUMENT STORM AVIATION ATA 36 PAGE 44

308. THE DUAL BLEED LIGHT WILL BE ON

a) WITH No.1 AND No. 2 BLEED VAVLES CLOSED AND APU BLEED VAVLE OPEN

b) WITH No. 2 ENGINE BLEED VAVLE OPEN, THE ISOLATION VAVLE OPEN AND APU BLEED VAVLE OPEN

c) WITH THE AIR CONDITIONING PANEL SET FOR A BLEEDS-OFF TAKEOFF

(A) DOCUMENT STORM AVIATION ATA 36 PAGE 62

309. THE PNEUMATIC DUCT PRESSURE GAUGE

a) INDICATES PRESSURE IN LEFT AND RIGHT PNERMATIC DUCTS

b) INDICATES PRESSURE AVAILABLE FOR ENGINE ANTI-ICING

c) IS DC POWERED

(A) DOCUMENT STORM AVIATION ATA 36 PAGE 14

310. THE SOURCE OF ENGINE BLEED ARE

a) 5TH AND 9TH STAGES OF THE TURBINE SECTION

b) 5TH AND 9TH STAGES OF THE COMPRESSOR SECTION

c) 5TH AND 13TH STAGES OF THE FAN SECTION

(A) DOCUMENT STORM AVIATION ATA 36 PAGE 18

311. THE ENGINE BLEED VAVLE ARE

a) DC ACTIVATED AND PNEUMATICALLY OPERATED

b) PNEUMATICALLY ACTIVATED AMD OPERATED

c) AC ACTIVATED AND PNEUMATICALLY OPERATED.

(A) DOCUMENT STORM AVIATION ATA 36 PAGE 18

312. WATER TANK PRESSURISATION IN FLIGHT IS NORMALLY PROVIDED BY

a) 5TH AND 9TH STAGE AIR FROM ENGINE No. 2

b) 5TH AND 9TH STAGE AIR FROM ENGINE No. 1

c) BLEED AIR FROM THE APU

(A) DOCUMENT STORM AVIATION ATA 36 PAGE 4

313. BOTH HYDRAULIC RESERVOIRS ARE PRESSURISED BY

a) SEPARATE ENGINE BLEEDS DRICECTLY TO THE RESERVOIRS

b) 5TH AND 9TH STAGE AIR FROM ENGINE No. 2 ONLY

c) AIR FROM THE PNEUMATIC MANIFOLD

(A) DOCUMENT STORM AVIATION ATA 36 PAGE 4

314. THE SOURCE AIR DUCTED THROUGH THE PRE-COOLER IS

a) PrRESSUR CONTROLLED RAM AIR

b) 5TH STAGE BLEED AIR

c) FAN AIR

(A) DOCUMENT STORM AVIATION ATA 36 PAGE 12

315. THE PRE-COOLER CONTROL VAVLE IS

a) DC CONTROLLED AND PNEUMATICALLY OPERATED

b) PNEUMATICALLY CONTROLLED AND OPERATED

c) AC CONTROLLED AND PNEUMATICALLY OPERATED

(A) DOCUMENT STORM AVIATION ATA 36 PAGE 42

316. THE ISOLATION VAVLE IS

a) AC OPERATED

b) AC CONTROLLED AND PNEUMATICALLY OPERATED

c) DC OPERATED

(A) DOCUMENT STORM AVIATION ATA 36 PAGE 54

ATA 38:

317. HOW MANY SUBSYSTEMS OF WATER AND WASTE SYSTEM

a) 1

b) 2

c) 3

(A) AMM PART 1/ 38-00-00 PAGE 2

318. HOW MANY SUBSYSTEMS OF POTABLE WATER SYSTEM

a) 1

b) 2

c) 3

(A) AMM PART 1/ 38-10-00 PAGE 2

319. WHEN YOU DRAIN THE POTABLE WATER SYSTEM, YOU MUST DRAIN WATER FROM:

a) WATER SERVICE PANEL

b) FORWARD LAVATORY

c) WATER SERVICE PANEL and FORWARD LAVATORY

(A) AMM PART 1/ 38-11-00 PAGE 2

320. THE WATER SERVICE PANEL IS LOCATED:

a) THE AFT SECTION OF THE FUSELAGE, BOTTOM RIGHT SIDE

b) THE AFT SECTION OF THE FUSELAGE, BOTTOM LEFT SIDE

c) THE CENTER SECTION OF THE FUSELAGE

(A) AMM PART 1/ 38-11-00 PAGE 2

323. THE PRESSURE RELIEF VALVE PRESENTS AN OVER-PRESSURE CONDITION IN THE WATER TANK PRESSURE LINES, THE VALVE RESETS AT:

a) 50PSIG

b) 55PSIG

c) 60PSIG

(A) AMM PART 1/ 38-42-00 PAGE 7

324. THE AIR COMPRESSOR OF WATER SYSTEM IS ON

a) THE LEFT SIDE OF THE AFT CARGO COMPARTMENT

b) THE RIGHT SIDE OF AFT THE CARGO COMPARTMENT

c) THE LEFT SIDE OF THE FWD CARGO COMPARTMENT

(A) AMM PART 1/ 38-42-00 PAGE 10

325. WHAT TIME IS DUTY CIRCLE INHIBIT OF FLUSH CONTROL UNIT

a) 10 SECONDS

b) 15 SECONDS

c) 20 SECONDS

(A) AMM PART 1/38-32-00 PAGE 17

326. THE VACUUM BLOWER BAROMETRIC SWITCH OPENS WHEN THE ALTITUDE IS ABOVE

a) 15,000FT

b) 16,000FT

c) 17,000FT

(A) AMM PART 1/ 38-32-00 PAGE 36

327. WHAT TYPE OF THE VACUUM CHECK VALVE

a) FLAPPER TYPE VALVE

b) BYPASS TYPE VALVE

c) BALL TYPE VALVE

(A) AMM PART 1/ 38-32-00 PAGE 40

328. THE LOGIC CONTROL MODULE LCM OF WATER TANK SYSTEM IS LOCATED?

a) ON THE RIGHT SIDE OF THE CARGO COMPARTMENT

b) ON THE LEFT SIDE OF THE CARGO COMPARTMENT

c) ON THE AFT SIDE OF THE CARGO COMPARTMENT

(A) AMM PART 1/ 38-33-00 PAGE 14

330. THE VACUUM BLOWER OF WASTE TANK SYSTEM IS

a) THREE-PHASE, LOW-SPEED, MOTOR-OPERATED FAN

b) THREE-PHASE, HIGH-SPEED, MOTOR-OPERATED FAN

c) ONE-PHASE, LOW-SPEED, MOTOR-OPERATED FAN

(A) AMM PART 1/ 38-32-00 PAGE 31

ATA 47:

331. CHOOSE THE CORRECT STATEMENT REGARDING THE NGS SHUTOFF VALVE

a) AN ELECTRICALLY COMMANDED PNEUMATICALLY ACTUATED PRESSURE REGULATING AND SHUTOFF VALVE (SPRING LOADED CLOSED)

b) A PNEUMATICALLY COMMANDED AND ACTUATED PRESSURE REGULATING AND SHUTOFF VALVE (SPRING LOADED CLOSED)

c) AN ELECTRICALLY COMMANDED PNEUMATICALLY ACTUATED PRESSURE REGULATING AND SHUTOFF VALVE (SPRING LOADED OPENED)

(A) SDS- AMM 47-10-00 PAGE 6

332. WHICH OF THE FOLLOWING CORRECTLY DESCRIBES THE RAM AIR VALVE (RAV)

a) FULLY PNEUMATICALLY COMMANDED ACTUATED, SPRING LOADED OPENED

b) TORQUE MOTOR COMMANDED, PNEUMATICALLY ACTUATED, SPRING LOADED CLOSED

c) TORQUE MOTOR COMMANDED, PNEUMATICALLY ACTUATED, SPRING LOADED OPENED

(A) SDS-AMM 47-10-00 PAGE 16

333. WHAT IS REQUIRED TO DISPATCH THE AIRCRAFT IF THE AMBER INOPERATIVE LIGHT LOCATED ON OPERABILITY INDICATOR ILLUMINATES?

a) ITS REQUIRED TO MANUALLY OPEN AND LOCK THE NITROGEN GENERATION SYSTEM SHUTOFF VALVE BEFORE FLIGHT

b) ITS REQUIRED TO MANUALLY CLOSE AND LOCK THE NITROGEN GENERATION SYSTEM SHUTOFF VALVE BEFORE FLIGHT

c) NO MAINTENANCE IS NECCESSARY

(A) SDS=AMM 47-40-00 PAGE 2

334. WHAT IS REQUIRED TO DISPATCH THE AIRCRAFT IF THE BLUE DEGRADED LIGHT LOCATED ON OPERABILITY INDICATOR ILLUMINATES?

a) ITS REQUIRED TO MANUALLY OPEN AND LOCK THE NITROGEN GENERATION SYSTEM SHUTOFF VALVE BEFORE FLIGHT

b) ITS REQUIRED TO MANUALLY CLOSE AND LOCK THE NITROGEN GENERATION SYSTEM SHUTOFF VALVE BEFORE FLIGHT

c) NO MAINTENANCE IS NECCESSARY

(A) SDS=AMM 47-40-00 PAGE 2

335. THE OVERTEMPERATURE SHUTOFF VALVE IS

a) ELECTRICALLY CONTROLLED AND PNEUMATICALLY OPERATED, SPRING LOADED CLOSED

b) PNEUMATICALLY CONTROLLED AND OPERATED, SPRING LOADED CLOSED

c) ELECTRICALLY CONTROLLED AND PNEUMATICALLY OPERATED, SPRING LOADED OPENED

(A) SDS-AMM 47-10-00 PAGE 26

ATA 49:

336. THE APU MAY BE OPERATED WITH APU BLEED ONLY UP TO A MAXIMUM ALTITUDE OF

a) 35.000 FT

b) 17.000 FT

c) 10.000 FT

(A) AMM PART 1/ 49-00-00 PAGE 4

337. THE APU LOW OIL PRESSURE LIGHT IS

a) ALWAYS ILLUMINATED WHEN THE APU SWITCH IS IN OFF POSITION

b) DISARMED WHEN THE APU SWITCH IS IN THE OFF POSITION

c) INHIBITED DURING APU START

(A) AMM PART 1/ 49-00-00 PAGE 16

338. ON THE 737NG, THE APU WILL AUTOMATICALLY SHUT-DOWN WHEN

a) THE BATTERY SWITCH IS PLACED OFF AT ANY TIME

b) THE BATTERY SWITCH IS PLACED OFF IN FLIGHT ONLY

c) THE BATTERY SWITCH IS PLACED OFF ON THE GROUND ONLY

(A) AMM PART 1/ 49-00-00 PAGE 16

339. HOW LONG DOES APU COOLING DOWN CIRCLE?

a) 50 SECONDS

b) 60 SECONDS

c) 55 SECONDS

(A) AMM PART 1/ 49-00-00 PAGE 16

341. WHICH POWER SOURCE SUPPLY APU INDICATION LIGHT OPERATIVE?

a) 115V AC

b) 12V DC

c) 220 V AC

(A) AMM PART 1/ 49-00-00 PAGE 20

342. THE APU FIRE WARNING SYSTEM GIVES AURAL AND VISUAL WARNINGS

a) IN THE FLIGHT DECK AND MAIN WHEEL WELL

b) ONLY IN THE FLIGHT DECK

c) IN THE FLIGHT DECK AND THE APU COMPARTMENT

(A) AMM PART 1/ 49-60-00 PAGE 3

343. DURING A NORMAL APU START

a) THE AMBER LOW OIL PRESSURE LIGHT IS LLUMINATED UNTIL THE APU OIL PRESSURE IS NORMAL (APPROX. 30% RPM)

b) THE STARTER MOTOR IS ENGAGED AS SOON AS THE MASTER SWITCH IS RELEASED FROM START TO ON

c) THE BLUE APU GEN OFF BUS BUS LIGHT GOES OUT AT 95% RPM

(A) AMM PART 1/ 49-00-00 PAGE 14

344. WHEN DOES INLET DOOR CLOSE DURING SHITDOWN APU?

a) AT 25% SPEED b) AT 30% SPEED c) AT 35% SPEED

(A) AMM PART 1/ 49-00-00 PAGE 16

345. IF AN APU FIRE WARNING IS SENSED

a) THE APU WILL SHUT-DOWN AND THE EXTINGUISHER IS DISCHARGED AUTOMATICALLY

b) THE APU WILL SHUT-DOWN AUTOMATICALLY

c) THE APU MUST BE SHUT-DOWN BY PULLING UP THE FIRE SWITCH

(A) AMM PART 1/ 49-00-00 PAGE 18

346. THE ALLIED SIGNAL 131-9(B) APU GENERATOR IS RATED AT

a) 45 KVA IN-FLIGHT AND 55KVA ON THE GROUND

b) THE SAME RATING AS AN ENGINE DRIVEN GENERATOR

c) 90 KVA UP TO 32,000FT AND 66 KVA UP TO 41,000FT

(A) AMM PART 1/ 49-00-00 PAGE 4

347. HOW IS THE APU IS SWITCHED ONTO THE AC ELECTRICAL SYSTEM?

a) AUTOMATICALLY WHEN THE PREVIOUS POWER SOURCE IS DISCONNECTED

b) AUTOMATICALLY IF THE APU GENERATOR IS RUNNING

c) BY TWO APU SWITCHES INDIVIDUALLY OPERATED

(A) AMM PART 1/ 49-60-00 PAGE 3

348. WHAT TYPE OF BLEED AIR VALVE

a) BUTTERFLY TYPE VALVE

b) BALL TYPE VALVE

c) BYPASS TYPE VALVE

(A) AMM PART 1/ 49-50-00 PAGE 6

349. THE 737NG APU START CYCLE

a) MAY TAKE AS LONG AS 120 SECONDS

b) MAY TAKE AS LONG AS 180 SECONDS

c) MAY TAKE AS LONG AS 60 SECONDS (A) AMM PART 1/ 49-00-00 PAGE 15

350. THE MAXIMUM AIRCRAFT ALTITUDE FOR BOTH APU BLEED AND ELECTRICAL LOAD IS

a) 17,000FT

b) 35,000FT

c) 15,000FT

(A) AMM PART 1/ 49-00-00 PAGE 2

351. WHEN DOES THE APU FUEL SOLENOID VALVE OPEN?

a) WHEN OIL TEMPERATURE HAS REACHED A MINIMUM VALUE

b) WHEN OIL PRESSURE HAS REACHED 13PSI

c) WHEN START APU AT 7% SPEED

(A) AMM PART 1/ 49-00-00 PAGE 14

353. ILLUMINATION OF THE APU DET INOP LIGHT

a) DOES NOT ACTIVATE THE MASTER CAUTION SYSTEM

b) ACTIVATES MASTER CAUTION "OVHT/DET"

c) ACTIVATES MASTER CAUTION "APU"

(A) AMM PART 1/ 49-00-00 PAGE 13

ATA 52:

354. WHAT IS THE FUNCTION OF THE COUNTERBALANCE ASSEMBLY ON THE CARGO DOOR?

a) TO HOLD THE CARGO DOOR IN THE FULLY CLOSE POSITION

b) TO REDUCE THE FORCE REQUIRED TO LIFT THE CARGO DOOR

c) TO LIMIT THE SPEED OF DOOR MOTION DURING OPENING OR CLOSING

(A) AMM PART 1/ 52-30-00 PAGE 9

355. ON THE PASSENGER ENTRY DOOR, WHERE IS THE PROXIMITY SWITCH FOR THE DOOR WARNING SYSTEM?

a) ON THE INTERIOR CONTRONL HANDLE

b) ADJACENT TO THE LOWER HINGE

c) ADJACENT TO THE UPPER LATCH (A) AMM PART 1/ 52-10-00 PAGE 2

356. WHEN ARE THE EMERGENCY EXIT DOOR LOCKED (FLIGHT LOCK MECHANISM)?

a) DURING THE TAKE OFF ROLL

b) TWO OR MORE ENTRY/SERVICE DOORS CLOSED

c) ONE ENGINE IS MORE THAN 50% N2

(A) AMM PART 1/ 52-22-00 PAGE 14

357. WHAT IS THE FUNCTION OF THE FLIGHT LOCK MECHANISM ON THE EMERGENCY DOOR?

a) TO PREVENT OPERATION OF THE EMERGENCY DOOR ON GROUND

b) TO TURN THE EMERGENCY DOOR OUT OF THE FUSELAGE CUT-OUT

c) TO PREVENT OPERATION OF THE EMERGENCY IN FLIGHT

(A) AMM PART 1/ 52-22-00 PAGE 12

358. HOW IS THE CARGO DOOR HELD IN THE OPEN POSITION?

a) DOOR OPEN LOCK SOLENOID

b) HYDRAULIC ACTUATOR

c) COUNTERBALANCE ASSEMBLY

(A) AMM PART 1/ 52-30-00 PAGE 9

359. WHAT INDICATIONS WILL BE TRIGGERED IF AN OVERWING DOOR IS UNLOCKED WHEN IT SHOULD BE LOCKED?

a) THE PROXIMITY SWITCHING ELECTRONIC UNIT (PSEU) LIGHT ON THE P5AFT OVERHEAD PANEL WILL COME ON (NOT RESETTABLE)

b) THE RELATED OVERWING LIGHT ON THE P5-20 DOOR WARNING ANNUNCIATOR MODULE WILL COME ON

c) THE OVERWING DOOR LOCK MESSAGE WILL BE DISPLAYED ON FMS CDU

(A) AMM PART 1/ 52-71-00 PAGE 9

360. WHAT ARE THE DOOR SEALS CONSTRUCTED FROM?

a) SILICON RBBER

b) SILICON FABRIC

c) CARBON FIBRE

(A) AMM PART 1/ 52-09-00 PAGE 2

361. WHAT IS THE MAXIMUM SPEED THAT THE MAINTENANCE ENGINEER CAN OPEN AND CLOSE ENTRY, GALLEY SERVICE AND CARGO DOORS?

a) 40 KNOTS

b) 15 KNOTS

c) 65 KNOTS

(A) AMM PART 1/ 52-00-00 PAGE 2

362. THE EMERGENCY EXIT DOOR OPEN

a) FROM INSIDE OR OUTSIDE THE AIRPLANE

b) FROM OUTSIDE THE AIRPLANE

c) FROM INSIDE THE AIRPLANE (A) AMM PART 1/ 52-22-00 PAGE 2

363. HOW MANY TYPE OF DOORS ON THE AIRPLANE

a) 3

b) 4

c) 5

(A) AMM PART 1/ 52-00-00 PAGE 2

364. YOU CAN OPEN AND CLOSE FORWARD ENTRY, FORWARD GALLEY SERVICE AND CARGO DOORS IN WINDS UP TO

a) 35 KNOTS

b) 40 KNOTS

c) 45 KNOTS

(A) AMM PART 1/ 52-10-00 PAGE 28

365. HOW MANY TYPES OF DOOR SEAL SHAPES

a) 3

b) 4

c) 5

(A) AMM PART 1/ 52-09-00 PAGE 2

369. WHEN YOU OPEN CARGO DOOR, THE DOOR MOVES

a) UPWARD AND INWARD

b) DOWNWARD AND INWARD

c) UPWARD AND INWARD

(A) AMM PART 1/ 52-30-00 PAGE 10

370. HOW MANY LATCH OF APU ACCESS DOOR

a) 3

b) 4

c) 5

(A) AMM PART 1/ 52-40-00 PAGE 17

371. HOW MANY PUSH-BUTTON LATCHES OF REFUELING STATION ACCESS DOOR

a) 3

b) 4

c) 5

(A) AMM PART 1/ 52-40-00 PAGE 19

373. THE DOOR WARNING AMBER LIGHTS ARE ON

a) THE P3 FORWARD OVERHEAD PANEL

b) THE P4 FORWARD OVERHEAD PANEL

c) THE P5 FORWARD OVERHEAD PANEL (A) AMM PART 1/ 52-71-00 PAGE 2

ATA 51-57:

377. THE VERTICAL STABILIZER IS MADE FROM

a) ALUMINIUM

b) GRAPHITE COMPOSITE

c) TITANIUM

(A) STORMAVIATION DOC ATA 51-57 PAGE 282

378. WHICH WINDOWS CAN NOT BE OPENED?

a) 1 AND 2

b) 1 AND 3

c) 2 AND 3

(A) STORMAVIATION DOC ATA 51-57 PAGE 288

379. WHICH PANE OF THE CABIN WINDOW DOESN’T STRUCTURE?

a) OUTER PANE

b) INNER PANE

c) MIDDLE PANE

(A) STORMAVIATION DOC ATA 51-57 PAGE 6

380. WHAT IS THE MAIN MATERIAL IN THE WING?

a) ALUMINIUM

b) GRAPHITE COMPOSITE

c) TITANIUM

(A) STORMAVIATION DOC ATA 51-57 PAGE 282

382. HOW MANY LIGHTNING DIVERTER STRIPS ON RANDOME

a) 5

b) 6

c) 7

(A) AMM PART 1/ 53-00-00 PAGE 5

383. WHAT IS THE METERIAL OF RUDDER?

a) ALUMINIUM

b) GRAPHITE COMPOSITE

c) TITANIUM

(A) STORMAVIATION DOC ATA 51-57 PAGE 282

384. HOW IS OPEN THE FIRST OFFICERS SLIDING WINDOW?

a) OPENED FROM THE INSIDE ONLY

b) OPENED FROM THE OUTSIDE ONLY

c) OPENED FROM THE INSIDE AND OUTSIDE

(A) STORMAVIATION DOC ATA 51-57 PAGE 294

385. The length of the B737-700 airplane:

a. 33.6 M

b. 31.2 M

c. 39.5 M

(A) Ref: Reference: ATA 51 STRUCTURES (Book 1) - B737 Training book - Page 10

386. Use these dimensions to find components on the fuselage:

a. Body station line, Body buttock line, Water line

b. Body station line, Water line

c. Body station line, Water line

(A) Ref: Reference: ATA 51 STRUCTURES (Book 1) - B737 Training book - Page 12

387. The body buttock line (BL) is

a. is a horizontal dimension. It starts at station line zero

b. is a height dimension. Measure the water line from a horizontal reference plane below the airplane

c. a lateral dimension. Measure the buttock line to the left (LBL) or right (RBL) of the airplane center line

(A) Ref: Reference: ATA 51 STRUCTURES (Book 1) - B737 Training book - Page 12

388. The nose of the airplane is

a. station 140

b. station 130

c. station 150

(A) Ref: Reference: ATA 51 STRUCTURES (Book 1) - B737 Training book - Page 12

389. Measure the vertical stabilizer station

a. perpendicular to the rudder hinge centerline. Rudder station 0 starts at the body crown line.

b. perpendicular to the vertical stabilizer leading edge. Vertical stabilizer leading edge station 0 starts at the body crown line

c. Perpendicular to the vertical stabilizer rear spar. Vertical stabilizer station 0 starts at the body crown line

(A) Ref: Reference: ATA 51 STRUCTURES (Book 1) - B737 Training book - Page 16

390. Measure the vertical stabilizer waterline

a. Perpendicular to the vertical stabilizer rear spar b. perpendicular to the rudder hinge centerline

c. parallel to the body waterline

(A) Ref: Reference: ATA 51 STRUCTURES (Book 1) - B737 Training book - Page 16

391. Measure stabilizer stations

a. perpendicular to the horizontal stabilizer rear spar

b. Perpendicular to the horizontal stabilizer leading edge

c. perpendicular to the elevator hinge centerline

(A) Ref: Reference: ATA 51 STRUCTURES (Book 1) - B737 Training book - Page 18

392. What is not primary structure:

a. Doors

b. Radome

c. Landing Gear

(A) Ref: Reference: ATA 51 STRUCTURES (Book 1) - B737 Training book - Page 22

393. Most of the material in the radome is

a. steel

b. fiberglass

c. Aluminium

(A) Ref: Reference: ATA 51 STRUCTURES (Book 1) - B737 Training book - Page 32

394. The lightning diverter strips

a. increase lightning energy and transmit it to the airframe

b. decrease lightning energy and transmit it to the wing

c. decrease lightning energy and transmit it to the airframe

(A) Ref: Reference: ATA 51 STRUCTURES (Book 1) - B737 Training book - Page 32

395. The winglets are made of

a. graphite spars, aluminum ribs and aluminum skins

b. graphite spars, aluminum ribs and graphite skins

c. aluminum spars, aluminum ribs and aluminum skins

(A) Ref: Reference: ATA 51 STRUCTURES (Book 1) - B737 Training book - Page 46

396. Flight compartment windows can be opened?

a. windows 1 and 3

b. windows 2

c. windows 2 and 3

(A) Ref: Reference: ATA 56 WINDOWS (Book 1) - B737 Training book - Page 5

397. Which windows get heat from the window anti-ice system?

a. Flight compartment windows 1, 2 and 3

b. Flight compartment windows 1 and 3

c. Flight compartment windows 1 and 2

(A) Ref: Reference: ATA 56 WINDOWS (Book 1) - B737 Training book - Page 5

398. Which windows have a small hole in the upper forward corner of the inner pane?

a. Flight compartment window 3

b. Flight compartment window 1

c. Flight compartment window 2

(A) Ref: Reference: ATA 56 WINDOWS (Book 1) - B737 Training book - Page 9

399. The passenger compartment, which pane is not structural?

a. Outer pane

b. Inner pane

c. Middle pane

(A) Ref: Reference: ATA 56 WINDOWS (Book 1) - B737 Training book - Page 15

400. Control cabin sliding windows can be opened from

a. inside and outside

b. only inside

c. only outside

(A) Ref: Reference: ATA 56 WINDOWS (Book 1) - B737 Training book - Page 12 

B. QUESTION BANK FOR B737NG CAT B1 (AIRFRAME)

ATA 0:

1. How to ground the airplane?

a. There is no spectial sequence.

b. Always attach the grouding cable to the airplane first

c. Always attach the grouding cable to the ground connection first

(B1) Ref: Reference: ATA 00 Introduction - B737 Training book - Page 169

2. When are the pitot probe covers and static port covers recommended to install?

a. When the airplane is parked for more than a standard turnaround or conditions such as insect activity, dust stoms or volcanic ash

b. When conditions such as insect activity, dust stoms or volcanic ash

c. When the airplane is parked for more than a standard turnaround

(B1) Ref: Reference: ATA 00 Introduction - B737 Training book - Page 167

3. Where can you find the turning limits when airplane is towed or pushed for dispatch?

a. The painted stripes are on the lower fuselage below left pax door

b. The painted stripes are on the nose gear doors

c. The painted stripes are on the lower fuselage below right pax door

(B1) Ref: Reference: ATA 00 Introduction - B737 Training book - Page 185, 191

ATA 5:

4. In which chapter would you find the Fuselage Bird Strike Inspection

a. Chapter 5

b. Chapter 3

c. MEL Maintenance procedures

(B1) Ref: Reference: AMM Part PP Task 05-51-18-210-801

5. Overweight Landing Inspection

a. ATA 32

b. ATA 5

c. Flight Operating Manual

(B1) Ref: Reference: AMM Part PP Task 05-51-35

6. In what chapter is the pressure leak rate chart for fuselage leakage rates.

a. ATA 21

b. MEL, limitations

c. Chapter 5

(B1) Ref: Reference: AMM Part PP Task 05-51-91

7. During a pressurisation test what is max. pressure during a normal test.

a. 6.0 p.s.i.

b. 32 p.s.i.

c. 4.0 p.s.i.

(B1) Ref: Reference: AMM Part PP Task 05-51-91-790-801

ATA 6:

8. The body station line (STA) is a:

a. Lateral dimension.

b. Horizontal dimension.

c. Height dimension.

(B1) Ref: Reference: AMM Part PP Task 06-10-00-800-801

9. The body buttock line (BL) is a

a. Lateral dimension.

b. Height dimension.

c. Horizontal dimension.

(B1) Ref: Reference: AMM Part PP Task 06-10-00-800-801

10. The water line (WL) is a

a. Lateral dimension.

b. Horizontal dimension.

c. Height dimension.

(B1) Ref: Reference: AMM Part PP Task 06-10-00-800-801

11. The airplane has

a. Eight major zones

b. Six major zones

c. Seven major zones

(B1) Ref: Reference: AMM Part PP Task 06-30-00-800-801

12. The general left wing section base number is:

a. 500

b. 600

c. 700

(B1) Ref: Reference: AMM Part PP Task 06-24-00-800-801

13. The airplane is divided into

a. Stations, waterlines, and buttock lines.

b. Stations, waterlines lines.

c. Waterlines, and buttock lines.

(B1) Ref: Reference: AMM Part PP Task 06-10-00-800-801

ATA 7:

15. The airplane has

a. Three main jack points and four auxiliary jack points.

b. Four main jack points and three auxiliary jack points.

c. Three main jack points and three auxiliary jack points. (B1) Ref: Reference: AMM Part PP Task 07-11-01-580-815

16. On each wing has:

a. 02 jack points

b. 03 jack points

c. 01 jack point

(B1) Ref: Reference: AMM Part PP Task 07-11-01-580-815

17. In which document you will find the detail instruction for shoring the aircraft?

a. Airplane Recovery Document.

b. Structure Repair Manual.

c. Aircraft Maintenance Manual.

(B1) Ref: Reference: AMM Part PP Task 07-20-00-580-801

18. When Lifting the aircraft

a. No requirement.

b. All the doors must be closed

c. The passenger/crew doors, the emergency exits and the cargo doors are closed and locked or fully open and locked.

(B1) Ref: Reference: AMM Part PP Task 07-11-01-580-815

ATA 8:

19. The main purpose of weighing aircraft is:

a. Calculate of aircraft weight

b. Know the aircraft weight for passenger loading

c. Calculate the position of the center of gravit.

(B1) Ref: Reference: Weight and Balance Manual

ATA 9:

20. The design of the airplane will permit you to tow the airplane from

a. The nose landing gear

b. The main landing gear

c. The nose landing gear or main landing gear

(B1) Ref: Reference: AMM Part PP Task 09-11-00-580-801

21. The maximum normal towing turning limits are indicated by the painted stripes on

a. The lower fuselage below left pax door

b. The nose gear doors.

c. The lower fuselage below right pax door

(B1) Ref: Reference: AMM Part PP Task 09-11-00-580-801

22. What is the correct sequence?

a. Install the tow bar on the tow fitting then install the tow lever safety pin

b. Install the tow lever safety pin then install the tow bar on the tow fitting.

c. There is no specific sequence.

(B1) Ref: Reference: AMM Part PP Task 09-11-00-580-801

23. When tow the aircraft, maximum normal turning angle is:

a. 68 degrees

b. 78 degrees

c. 88 degrees

(B1) Ref: Reference: AMM Part PP Task 09-11-00-580-801

ATA 10:

24. When aircraft stop overnight:

a. Pitot probe and static port are covered.

b. Static port are covered.

c. Pitot port are covered.

(B1) Ref: Reference: AMM Part PP Task 10-11-01-580-801

25. The aircraft is usually parked for a small quantity of time as follows:

a. Chocks in front of and behind a minimum of one of the main gear wheels

b. Chocks in front of and behind a minimum of one of the main gear wheels

c. No need chocks

(B1) Ref: Reference: AMM Part PP Task 10-11-01-580-801

ATA 11:

26. Letters of marking or placard EXIT and EMERGENCY EXIT are in

a. red color

b. orange color

c. blue color

(B1) Ref: Reference: AMM Part PP Task 11-32-01

28. Red strip markings on nose gear doors are

a. used during airplane towing

b. used for airplane nose jacking

c. used to indicated hazard area during nose landing gear retraction and extension

(B1) Ref: Reference: AMM Part PP Task 09-11-00-580-801

29. Marking SMOKE DETECTOR - DO NOT BLOCK is used for

a. lavatory smoke detector

b. engine fire detection system

c. cargo fire detection system

(B1) Ref: Reference: AMM Part PP Task 11-37-01-2-2

ATA 12:

32. When doing the Hydraulic Fluid Reservoir Filling

a. The reservoirs air pressurize system must be depressurized

b. Do not depressurize the system reservoirs

c. The hydraulic system operating normally

(B1) Ref: Reference: AMM Part PP Task 12-12-00-610-801

ATA 20:

33. When you do the Aircraft Grounding for the Refuel/Defuel Operations

a. Connect the ground cable to parking ground point before you connect it to the aircraft

b. Attach the cable to aircraft first then connect to parking ground point

c. Grounding is not necessary

(B1) Ref: Reference: AMM Part PP Task 20-40-11-910-801

ATA 21:

34. Pack overheat condition cause the PACK/ PACK TRIP OFF light to turn on. To reset the system,

a. Push the TRIP RESET switch when PACK/ PACK TRIP OFF turn on.

b. Let the overheat condition to be cooled and then push the TRIP RESET.

c. Do nothing.

(B1) Ref: Reference: ATA 21 Air Conditioning (1) - B737 Training book - Page 36

35. The PACK/ PACK TRIP OFF light turns on, possible switches that could cause this

a. Duct overheat switch

b. Cabin overheat switch

c. Compressor discharge overheat switch, turbine inlet overheat switch or pack discharge overheat switch.

(B1) Ref: Reference: ATA 21 Air Conditioning (1) - B737 Training book - Page 36

36. B737-800/900, the LEFT recirculating fan operates with the switch in the AUTO position in the AIR, except:

a. When both packs are on and one or both pack switches are selected to HIGH

b. When one pack is off.

c. When both pack switches are selected to AUTO

(B1) Ref: Reference: ATA 21 Air Conditioning (1) - B737 Training book - Page 149

37. B737-800/900, the LEFT recirculating fan operates with the switch in the AUTO position on the GROUND, except:

a. When both packs are on and one pack switches are selected to HIGH

b. When one pack is off.

c. When both pack switches are selected to HIGH

(B1) Ref: Reference: ATA 21 Air Conditioning (1) - B737 Training book - Page 149

38. The RIGHT recirculating fan operates with the switch in the AUTO position, except:

a. When both pack switches are selected to HIGH

b. When both packs are on and one pack switches are selected to HIGH

c. When one pack is off.

(B1) Ref: Reference: ATA 21 Air Conditioning (1) - B737 Training book - Page 149

39. Water separator coalescer (bag) condition indicator will be observed

a. While the pack operates in high flow and the air mix valve is in full cold position.

b. While the pack operates in low flow and the air mix valve is in AUTO position.

c. While the pack operates in low flow and the air mix valve is in full warm position.

(B1) Ref: Reference: ATA 21 Air Conditioning (1) - B737 Training book - Page 68

40. The coalescer bag must be changed if the indicator disk is

a. in the blue range

b. In the red range

c. In the amber range.

(B1) Ref: Reference: ATA 21 Air Conditioning (1) - B737 Training book - Page 68

41. During flight cruise mode, the RAM DOOR FULL OPEN light is ON

a. This is a normal condition.

b. There is a problem in bleed air system

c. The ram air system has a blockage

(B1) Ref: Reference: ATA 21 Air Conditioning (1) - B737 Training book - Page 58

42. During flight cruise mode, the RAM DOOR FULL OPEN light

a. is OFF

b. is ON

c. is ON or OFF depend on the PACK schedules.

(B1) Ref: Reference: ATA 21 Air Conditioning (1) - B737 Training book - Page 62

43. Mode(s) of control for the ram air system is(are)

a. Only one mode for all phases.

b. Two modes: On ground and in flight.

c. Three modes: Ground, flight (flaps not up) and flight (flaps up)

(B1) Ref: Reference: ATA 21 Air Conditioning (1) - B737 Training book - Page 61

44. When you install a recirculation fan:

a. Make sure the flow arrow on the fan is in the correct direction and shoud point to the distribution manifold.

b. The flow arrow on the fan shoud point out of the distribution manifold.

c. There is not any arrow on the recirculation fan

(B1) Ref: Reference: ATA 21 Air Conditioning (1) - B737 Training book - Page 140

45. The recirculation fan is

a. DC powered

b. AC powered

c. Pneumatically powered from APU or engine bleed air

(B1) Ref: Reference: ATA 21 Air Conditioning (1) - B737 Training book - Page 144

46. The air supply for the recirculation fans is

a. From the distribution compartment

b. From the collector shroud in the aft cargo compartment

c. From the collector shroud in the forward cargo compartment and the distribution compartment

(B1) Ref: Reference: ATA 21 Air Conditioning (1) - B737 Training book - Page 206

47. The E & E compartment is cooled by?

a. The equipment cooling system.

b. The ram air system.

c. The AUTO or STANDBY pressurisation systems

(B1) Ref: Reference: ATA 21 Air Conditioning (1) - B737 Training book - Page 244

48. The aft cargo compartment is heated by

a. The exhaust air from the control cabin

b. The air from the passenger compartment through the foot level grilles

c. The exhaust air from the equipment cooling system

(B1) Ref: Reference: ATA 21 Air Conditioning (1) - B737 Training book - Page 274

49. The forward cargo compartment is heated by

a. The air from the passenger compartment.

b. The exhaust air from the equipment cooling system

c. The exhaust air from the equipment cooling system and the air from the passenger compartment.

(B1) Ref: Reference: ATA 21 Air Conditioning (1) - B737 Training book - Page 274

50. The cabin altitude warning alarm will sound

a. When the cabin altitude increases to more than 10000 feet.

b. When the cabin altitude increases to more than 12000 feet.

c. When the cabin altitude increases to more than 14000 feet.

(B1) Ref: Reference: ATA 21 Air Conditioning (2) - B737 Training book - Page 5

51. When the cabin altitude warning alarm sound

a. You can not deactivate the alarm.

b. You can push the ALT HORN CUTOUT switch to deactivate the alarm.

c. You can push the BELL CUTOUT switch to deactivate the alarm.

(B1) Ref: Reference: ATA 21 Air Conditioning (2) - B737 Training book - Page 5

52. The maximum cabin altitude for most flight is

a. 10000 feet.

b. 6000 feet

c. 8000 feet

(B1) Ref: Reference: ATA 21 Air Conditioning (2) - B737 Training book - Page 5

53. The negative pressure relief valve opens when pressure external to the airplane is X psi more than the pressure in the airplane.

a. X=1.5

b. X=1.0

c. X=2.0

(B1) Ref: Reference: ATA 21 Air Conditioning (2) - B737 Training book - Page 58

54. The negative pressure relief valve is

a. Controlled by a switch in the flight compartment.

b. Controlled by a CPC in pressurization system.

c. A mechanical device and operates independently.

(B1) Ref: Reference: ATA 21 Air Conditioning (2) - B737 Training book - Page 58

55. If the amber AUTO FAIL light and the green ALTN light come on

a. Positioning the pressurization mode selector to ALTN will extinguish the AUTO FAIL light.

b. It will automatically extinguish when the pressurisation controller reverts to the ALTN mode

c. Positioning the Pressurisation Mode Selector to ALTN will have no effect on the AUTO FAIL light.

(B1) Ref: Reference: ATA 21 Air Conditioning (2) - B737 Training book - Page 45, 46

56. The maximum cabin differential pressure for take-off and landing is

a. 0.10psi

b. 0.25psi

c. 0.125psi

(B1) Ref: Reference: ATA 21 Air Conditioning (2) - B737 Training book - Page 17

57. The AUTO FAIL light will illuminate when there is

a. A loss of power, or an excessive rate of cabin altitude change (>2000 sea level feet/minute), or a high cabin altitude (>15800 feet).

b. A loss of power, or an excessive rate of cabin altitude change (>1500 sea level feet/minute), or a high cabin altitude (>9800 feet).

c. A loss of power, or an excessive rate of cabin altitude change (>1000 sea level feet/minute), or a high cabin altitude (>14000 feet).

(B1) Ref: Reference: ATA 21 Air Conditioning (2) - B737 Training book - Page 45

58. The Aft outflow valve has

a. 2 automatic mode motors and 1 manual mode motor with 2 electronic actuators

b. 1 automatic mode motor and 1 manual mode motor with 1 electronic actuators

c. 2 automatic mode motors and 1 manual mode motor with 1 electronic actuators

(B1) Ref: Reference: ATA 21 Air Conditioning (2) - B737 Training book - Page 38

59. The OFF SCHED DESCENT light illuminates if

a. The aircraft has temporarily levelled off before reaching the selected flight altitude (as set on the cabin pressure selector panel)

b. The airplane begin a descent before reaching the selected flight altitude (as set on the cabin pressure selector panel)

c. The aircraft has climbed above the selected flight altitude (as set on the cabin pressure selector panel)

(B1) Ref: Reference: ATA 21 Air Conditioning (2) - B737 Training book - Page 50

60. The maximum differential pressure (positive pressure relief valve operation) is

a. 8.95 psi

b. 7.95 psi

c. 8.40 psi

(B1) Ref: Reference: ATA 21 Air Conditioning (2) - B737 Training book - Page 56

61. The positive pressure relief valves are

a. Controlled by a switch in the flight compartment.

b. Controlled by a CPC in pressurization system.

c. mechanical devices and operate independently.

(B1) Ref: Reference: ATA 21 Air Conditioning (2) - B737 Training book - Page 56

62. What could cause a RAM AIR DOOR Light to come on in cruise

a. Ram air system has a blockage, heat exchangers are dirty, Electrical failure.

b. Compressor outlet overheat c. Missing Ram Air Door

(B1) Ref: Reference: ATA 21 Air Conditioning (1) - B737 Training book - Page 62

63. What sensor controls the Ram Air Inlet Doors

a. ACM Compressor Inlet temperature

b. ACM Compressor Oulet - 110°C

c. Pack discharge temperature

(B1) Ref: Reference: ATA 21 Air Conditioning (1) - B737 Training book - Page 62

64. What commands the Ram Air Door Actuator

a. Ram Air Controller

b. Ram Air Switch

c. Pack/Zone Temperature Controller

(B1) Ref: Reference: ATA 21 Air Conditioning (1) - B737 Training book - Page 62

65. To use the APU for air conditioning, on the ground/engines shut down, you should select

a. Isolation Valve Switch AUTO/ON; APU Bleed Air Switch ON; Left or Right Air Conditioning

Pack Switch AUTO or HIGH

b. Isolation Valve Switch CLOSE; APU Bleed Air Switch ON; Left and Right Air Conditioning Pack Switch AUTO or HIGH

c. Isolation Valve Switch CLOSE; APU Bleed Air Switch ON; Left or Right Air Conditioning Pack Switch AUTO or HIGH

(B1) Ref: Reference: AMM Part PP Task 21-00-00-800-803

66. What is the location of and reason for the Pressure Equalisation Valves?

a. Aft cargo compartment, allow temperature to be regulated

b. Aft of each cargo compartment, keeps the cargo compartment pressure as the same level as cabin pressure

c. Fwd and Aft of FWD cargo compartment, allow equalisation of cargo pressure

(B1) Ref: Reference: ATA 21 Air Conditioning (2) - B737 Training book - Page 62

67. A differential pressure of X psid will push the cargo compartment blowout panel out of the frame.

a. X=1.5

b. X=1.0

c. X=2.0

(B1) Ref: Reference: ATA 21 Air Conditioning (2) - B737 Training book - Page 60

68. During a cabin pressure leak test what is maximum differential pressure for a normal test?

a. 6 psi

b. 8 psi

c. 4 psi

(B1) Ref: Reference: AMM Part PP Task 05-51-91-790-801

69. B737-600/700, the bleed air from the pneumatic manifold will go through these PACK component in sequence?

a. FCSOV-Primary HX- ACM compressor-Secondary HX-ACM Turbine-Water separator-Conditioned Air Check Valve

b. FCSOV-Primary HX- ACM compressor-Secondary HX-Reheater-Condenser-Water extractors- Reheater-ACM Turbine-Condenser-Conditioned Air Check Valve

c. FCSOV-Secondary HX- ACM compressor-Primary HX-ACM Turbine-Water extractors- Conditioned Air Check Valve

(B1) Ref: Reference: ATA 21 Air Conditioning (1) - B737 Training book - Page 33

70. B737-800/900, the bleed air from the pneumatic manifold will go through these PACK component in sequence?

a. FCSOV-Primary HX- ACM compressor-Secondary HX-ACM Turbine-Water separator-Conditioned Air Check Valve

b. FCSOV-Primary HX- ACM compressor-Secondary HX-Reheater-Condenser-Water extractors- Reheater-ACM Turbine-Condenser-Conditioned Air Check Valve

c. FCSOV-Secondary HX- ACM compressor-Primary HX-Reheater-Condenser-Water separator- Reheater-ACM Turbine-Condenser-Conditioned Air Check Valve

(B1) Ref: Reference: ATA 21 Air Conditioning (1) - B737 Training book - Page 33

71. B737-600/700, in EE compartment, there are

a. 01 air conditioning accessory unit (ACAU and 02 cabin temperature controller (CTCs)

b. 02 air conditioning accessory units (ACAUs) and 02 pack/zone controllers (PZCs)

c. 01 air conditioning accessory unit (ACAU and 01 cabin temperature controller (CTC)

(B1) Ref: Reference: ATA 21 Air Conditioning (1) - B737 Training book - Page 30

72. B737-800/900, in EE compartment, there are

a. 01 air conditioning accessory unit (ACAU and 02 cabin temperature controllers (CTCs)

b. 02 air conditioning accessory units (ACAUs) and 02 pack/zone controllers (PZCs)

c. 01 air conditioning accessory unit (ACAU and 01 pack/zone controller (PZC)

(B1) Ref: Reference: ATA 21 Air Conditioning (1) - B737 Training book - Page 30

73. B737-600/700, when the PACK switch is in AUTO position (normal flow), the flow rate of the air is

a. 55 ppm

b. 65 ppm

c. 80 ppm

(B1) Ref: Reference: ATA 21 Air Conditioning (1) - B737 Training book - Page 42

74. B737-600/700, when the PACK switch is in HIGH position (high flow), the flow rate of the air is

a. 60 ppm

b. 80 ppm

c. 100 ppm

(B1) Ref: Reference: ATA 21 Air Conditioning (1) - B737 Training book - Page 42

75. B737-600/700, when the PACK switch is in HIGH position, the airplane is on ground with APU supplying bleed air (APU high flow), the flow rate of the air is

a. 80 ppm

b. 100 ppm

c. 120 ppm

(B1) Ref: Reference: ATA 21 Air Conditioning (1) - B737 Training book - Page 42

76. B737-800/900, when the PACK switch is in AUTO position (normal flow), the flow rate of the air is

a. 65 ppm

b. 75 ppm

c. 80 ppm

(B1) Ref: Reference: ATA 21 Air Conditioning (1) - B737 Training book - Page 42

77. B737-800/900, when the PACK switch is in HIGH position (high flow), the flow rate of the air is

a. 90 ppm

b. 105 ppm

c. 115 ppm

(B1) Ref: Reference: ATA 21 Air Conditioning (1) - B737 Training book - Page 42

78. B737-800/900, when the PACK switch is in HIGH position, the airplane is on ground with APU supplying bleed air (APU high flow), the flow rate of the air is

a. 115 ppm

b. 131 ppm

c. 140 ppm

(B1) Ref: Reference: ATA 21 Air Conditioning (1) - B737 Training book - Page 42

79. The PACK flow is in the APU high flow mode when

a. The airplan is on the ground, the pack switch is in the HIGH position, the APU operates above 95%

b. The pack switch is in the HIGH position, the APU bleed switch is in the ON position, the APU operates above 95%, the airplan is on the ground.

c. The APU bleed switch is in the ON position, the APU operates above 95%, the airplan is on the ground

(B1) Ref: Reference: ATA 21 Air Conditioning (1) - B737 Training book - Page 44

80. The pressurization control is in the AUTO mode, if single channel failure occures, there are these indications

a. Amber AUTO FAIL light comes on, MASTER CAUTION and AIR COND annuciator lights come on, green ALTN light come on.

b. Amber ALTN and AUTO FAIL light come on, MASTER CAUTION and AIR COND annuciator lights come on.

c. Amber AUTO FAIL light comes on, the FLT ALT display shows five dashes.

(B1) Ref: Reference: ATA 21 Air Conditioning (2) - B737 Training book - Page 45, 46

81. In the pressurization control system, if dual channel failure occures, there are these indications

a. The AUTO FAIL and MASTER CAUTION lights come on, the FLT ALT and LAND ALT displays show five dashes.

b. Amber ALTN and AUTO FAIL light come on, MASTER CAUTION and AIR COND annuciator lights come on.

c. Amber AUTO FAIL light comes on, the FLT ALT display shows five dashes.

(B1) Ref: Reference: ATA 21 Air Conditioning (2) - B737 Training book - Page 45

82. The green ALTN light comes on when

a. Two CPC controllers fail and the backup system is active.

b. One CPC controller fails and the backup system is active.

c. One CPC controller fails and the manual system is active.

(B1) Ref: Reference: ATA 21 Air Conditioning (2) - B737 Training book - Page 45,46

83. In the pressurization control system, there are two digital cabin pressure controllers (CPCs). Choose the correct state?

a. Two CPCs controll the system at the same time.

b. One CPC controlls the system at a time, the other is a backup. The system changes active control from one CPC to the other with each flight.

c. Only one CPC controls the system for the whole flight. There is no backup. The system changes active control from one CPC to the other with each flight.

(B1) Ref: Reference: ATA 21 Air Conditioning (2) - B737 Training book - Page 41

84. The cabin pressure controllers use data from these system:

a. 2 ADIRUs, 2 SMYDs and PSEU

b. 1 ADIRUs, 1 SMYDs

c. 1 ADIRUs, PSEU

(B1) Ref: Reference: ATA 21 Air Conditioning (2) - B737 Training book - Page 41

85. The MANUAL light comes on when

a. Both CPCs are not active.

b. The selector switch is in the MANUAL position.

c. The selector switch is in the ALTN position.

(B1) Ref: Reference: ATA 21 Air Conditioning (2) - B737 Training book - Page 48

86. Which one is correct for the pressure equalization valve?

a. The pressure equaliztion valve has two swing check valve and spring-loaded to close position.

b. The pressure equaliztion valve has butterfly plate and is control from flight compartment.

c. he pressure equaliztion valve has two swing check valve and is controlled by CPC.

(B1) Ref: Reference: ATA 21 Air Conditioning (2) - B737 Training book - Page 62

87. The aft outflow valve goes to full closed if the cabin pressure altitude gets to 14.650 feet. This is the function of:

a. A fail-safe aneroid switch on each electronic actuator of the valve in normal automatic control only.

b. A switch on the flight compartment.

c. A fail-safe aneroid switch on each electronic actuator of the valve in any mode of cabin pressurization system.

(B1) Ref: Reference: ATA 21 Air Conditioning (2) - B737 Training book - Page 38

88. To move the aft outflow valve to a desired position, you have to

a. Move the mode selector AUTO position and use outflow valve toggle switch.

b. Move the mode selector ALTN position and use outflow valve toggle switch.

c. Move the mode selector MANUAL position and use outflow valve toggle switch.

(B1) Ref: Reference: ATA 21 Air Conditioning (2) - B737 Training book - Page 15

ATA 22:

89. Choose the correct state: when doing the stall warning system (SWS) test,

a. Use only one switch to do the test of both system

b. Switch No.1 is for SWS 1 with operation of control column shaker on captain control column, Switch No.2 is for SWS 2 with operation of control column shaker on first officer control column.

c. Switch No.1 is for SWS 1 and Switch No.2 is for SWS 2 with operation of both control column shakers when pushing each switch.

(B1) Ref: Reference: ATA 22 Auto Flight - B737 Training book - Page 39

90. How can you know the SWS has faults?

a. Pushing the SWS test switch and the fault light coms on.

b. Pushing the SWS test switch and the on side control column shaker operates

c. Pushing the SWS test switch and the on side control column shaker does not operate.

(B1) Ref: Reference: ATA 22 Auto Flight - B737 Training book - Page 39

91. For primary yaw damping, what is correct for rudder movement?

a. Rudder movement is limited to 2 degrees with flaps up and 3 degrees with flaps not up.

b. Rudder movement is limited to 2 degrees.

c. Rudder movement is limited to 3 degrees.

(B1) Ref: Reference: ATA 22 Auto Flight - B737 Training book - Page 47

92. To put the WTRIS and standby yaw damper on, do these steps

a. Put the FLT CONT A and B switches to OFF position; Put the yaw damper switch to ON.

b. Put the FLT CONT A and B switches to positions other than the ON position; Put at least one of these switches to STBY RUD; Put the yaw damper switch to ON.

c. Put the FLT CONT A and B switches to positions other than the ON position; Put the yaw damper switch to OFF.

(B1) Ref: Reference: ATA 22 Auto Flight - B737 Training book - Page 61

93. What is the function of the mach trim system?

a. The mach trim system moves the elevators to prevent a nose down maneuver at high speeds.

b. The mach trim system moves the ailerons to prevent a nose down maneuver at high speeds

c. The mach trim system moves the stabilizers to prevent a nose up maneuver at high speeds (B1) Ref: Reference: ATA 22 Auto Flight - B737 Training book - Page 204

94. The autothrottle function is in

a. Flight control computer B (FCC B)

b. Flight control computer A (FCC A)

c. Flight control computer A and B (FCC A+FCC B)

(B1) Ref: Reference: ATA 22 Auto Flight - B737 Training book - Page 326

95. During an autoland, the alert messages do not show when the airplane

a. Less than 200 feet above the runway.

b. Less than 300 feet above the runway.

c. Less than 400 feet above the runway.

(B1) Ref: Reference: ATA 22 Auto Flight - B737 Training book - Page 219

96. You push either master caution recall switch, the mach trim fail light comes on. You then push the master caution reset switch, the light goes off.

a. The mach trim funcion is normal.

b. There is only one function failure in the FCC system.

c. There are two function failures in the FCC system.

(B1) Ref: Reference: ATA 22 Auto Flight - B737 Training book - Page 208

97. To do the A/T BITE test, you use

a. A/T computer BITE module

b. FCC BITE module

c. The CDU

(B1) Ref: Reference: ATA 22 Auto Flight - B737 Training book - Page 383

98. When does the red A/P annunciator flash? a. When an A/P changes from CMD to CWS.

b. When an A/P disconnects.

c. When the power up test fails on the ground

(B1) Ref: Reference: ATA 22 Auto Flight - B737 Training book - Page 164

99. The autopilot has these actuators:

a. Four autopilot actuators:two actuators control the ailerons and two actuators control the elevators

b. Four autopilot actuators: one actuator controls the ailerons, one actuator controls rudder and two actuators control the elevators

c. our autopilot actuators: one actuator controls the ailerons, two actuators controls rudder and one actuator control the elevators

(B1) Ref: Reference: ATA 22 Auto Flight - B737 Training book - Page 144

100. How to disengage autopilot (A/P)?

a. By the A/P disengage switch on captain control wheel.

b. By the A/P disengage switch on captain/first officer control wheel or A/P disengage bar

c. By the A/P disengage switch on the thrust levers.

(B1) Ref: Reference: ATA 22 Auto Flight - B737 Training book - Page 157, 161

101. How to cancel the autothrottle (A/T) disengage warning?

a. Push the red ASA A/T light or one of the A/T disconnect switches on the thrust levers.

b. Push the red ASA A/T light or one of the A/T disconnect switches on control wheels.

c. Push the A/T Warning Cancel Switch on overhead panel

(B1) Ref: Reference: ATA 22 Auto Flight - B737 Training book - Page 331

102. What is not the A/T mode showing on FMA?

a. THR HLD

b. ADVANCED

c. RETARD

(B1) Ref: Reference: ATA 22 Auto Flight - B737 Training book - Page 356

103. What happens when you push the A/T disconnect switch?

a. The autothrottle system disengage and the MCP A/T arm switch goes to OFF.

b. The autothrottle system disengages, the ASA A/T amber warning light goes on and off.

c. The autothrottle system disengages, the ASA A/T red warning light goes on and off and the MCP A/T arm switch goes to OFF.

(B1) Ref: Reference: ATA 22 Auto Flight - B737 Training book - Page 345

104. Both master flight director indicator (MA) lights on the MCP panel are illuminated during Takeoff Roll indicate?

a. Approach mode is armed.

b. Independent Flight Director operation.

c. Flight Director malfunction.

(B1) Ref: Reference: ATA 22 Auto Flight - B737 Training book - Page 144

ATA 23:

105. When the ACP ALT/NORM is in ALT, the flight interphone system operates in the emergency mode for that station. How can the pilot use the ACP?

a. The BOOM-MASK switch and the R/T or RADIO position of the PTT switch are the only ACP switches that operate.

b. The BOOM-MASK switch and the hand-mic operate.

c. The R/T or RADIO position of the PTT switch and the hand-mic operate.

(B1) Ref: Reference: ATA 23 Communications - B737 Training book - Page 47

106. A microphone (mic) on these components lets the flight crew speak on the flight interphone system.

a. Oxygen mask and headset boom mic.

b. Oxygen mask, headset boom mic and hand mic

c. Headset boom mic and hand mic

(B1) Ref: Reference: ATA 23 Communications - B737 Training book - Page 32

107. The VHF communications system operates in the frequency range of

a. 2.000 MHz to 29.999 MHz

b. 99.100 MHz - 120.00 MHz

c. 118.000 MHz to 136.975 MHz

(B1) Ref: Reference: ATA 23 Communications - B737 Training book - Page 153

108. To do a test of the 121.5/243.0 MHz ELT transmitter:

a. Use a VHF transceiver to listen to the ELT transmission

b. Use special test equipment

c. Use a HF transceiver to listen to the ELT transmission

(B1) Ref: Reference: ATA 23 Communications - B737 Training book - Page 247

109. Pushing the ATTEND switch on the forward overhead panel in the flight compartment, what will happen?

a. A blue light on all the cabin exit locator signs comes on.

b. The passenger address system sends a HI/LO chime to the cabin speakers two times.

c. A pink light on all the cabin exit locator signs comes on and the passenger address system sends a HI/LO chime to the cabin speakers

(B1) Ref: Reference: ATA 23 Communications - B737 Training book - Page 59

110. The cockpit CALL (blue) light will illuminate along with an associated chime whenever the cockpit is being called

a. By the flight attendants only

b. By the flight attendants or the ground crew

c. By the ground crew only

(B1) Ref: Reference: ATA 23 Communications - B737 Training book - Page 59 and 91

111. Is it possible for the cabin attendants to communicate with the ground personnel from their respective stations

a. Yes, using the flight interphone system with the Service Interphone switch selected OFF

b. No

c. Yes, using the service interphone system.

(B1) Ref: Reference: ATA 23 Communications - B737 Training book - Page 73

112. Pushing the GRD CALL switch in the flight compartment to call the ground crew, what will happen?

a. A blue light on the external power panel comes on.

b. A horn in the nose wheel well makes a sound.

c. A blue light on the external power panel comes on and a horn in the nose wheel well makes a sound.

(B1) Ref: Reference: ATA 23 Communications - B737 Training book - Page 90

113. VHF communication system has

a. Three antennas. One antenna is on the top of the fuselage and two antennas are on the bottom of the fuselage

b. Three antennas. Two antennas are on the top of the fuselage and one antenna is on the bottom of the fuselage

c. Two antennas. One antenna is on the top of the fuselage and one antenna is on the bottom of the fuselage

(B1) Ref: Reference: ATA 23 Communications - B737 Training book - Page 141,142

114. In PA system, audio output has this order of priority

a. Flight compartment announcements, flight attendant announcements, pre-recorded announcements, boarding music

b. Flight compartment announcements, pre-recorded announcements, flight attendant announcements, boarding music.

c. There is no priority in the system.

(B1) Ref: Reference: ATA 23 Communications - B737 Training book - Page 120

115. The HF communications system operates in the frequency range of

a. 2.000 MHz to 29.999 MHz

b. 99.100 MHz - 120.00 MHz

c. 118.000 MHz to 136.975 MHz

(B1) Ref: Reference: ATA 23 Communications - B737 Training book - Page 176

116. To do a test of the 406 MHz ELT transmitter:

a. Use a VHF transceiver to listen to the ELT transmission

b. Use special test equipment

c. Use a HF transceiver to listen to the ELT transmission

(B1) Ref: Reference: ATA 23 Communications - B737 Training book - Page 247

117. How long can the voice recorder unit keep communication data in memory?

a. The last 90 minutes

b. The last 100 minutes

c. The last 120 minutes

(B1) Ref: Reference: ATA 23 Communications - B737 Training book - Page 358

118. Where can you find a service interphone jack?

a. At all flight attendance stations.

b. P19 external power panel, electronic equipment compartment, fueling station, left/right wheel well, Aft cabin on the ceiling, APU service area.

c. External power panel only

(B1) Ref: Reference: ATA 23 Communications - B737 Training book - Page 81

119. How can you erase the audio that the voice recorder keeps?

a. You can not erase the audio of the voice recorder.

b. Use the erase switch when the airplane is in the air.

c. Use the erase switch when the airplane is on the ground, and the parking brake is set.

(B1) Ref: Reference: ATA 23 Communications - B737 Training book - Page 359

120. When the captain ALT/NORM switch is in the ALT position,

a. Only VHF-1 is set as the communication system on captain side.

b. Only VHF-2 is set as the communication system on captain side.

c. VHF-1 and VHF-2 are set as the communication system on captain side.

(B1) Ref: Reference: ATA 23 Communications - B737 Training book - Page 47

121. When the F/O ALT/NORM switch is in the ALT position,

a. Only VHF-1 is set as the communication system on F/O side.

b. Only VHF-2 is set as the communication system on F/O side.

c. VHF-1 and VHF-2 are set as the communication system on F/O side.

(B1) Ref: Reference: ATA 23 Communications - B737 Training book - Page 47

122. When the voice recorder switch is in AUTO position,

a. The voice recorder gets power when when DC bus 1 is powered.

b. The voice recorder gets power when when DC bus 2 is powered.

c. The voice recorder always gets from the engine start until 5 minutes after engine stop.

(B1) Ref: Reference: ATA 23 Communications - B737 Training book - Page 358

123. The emergency locator transmitter (ELT) system automatically sends emergency signals

a. On the VHF channel only.

b. On the UHF channel only.

c. On the VHF and UHF channels

(B1) Ref: Reference: ATA 23 Communications - B737 Training book - Page 231

ATA 24:

124. The STANDBY PWR OFF light (amber) illuminated means

a. The AC standby bus is inactive.

b. The Hot Battery Bus is inactive

c. The DC 1 bus is inactive.

(B1) Ref: Reference: ATA 24 Electrical Power System - B737 Training book - Page 29

125. The AC transfer bus 1 does not have power, the stanby buses and battery bus have power when

a. The standby power switch is in the AUTO position, the BAT switch is in the ON position.

b. The standby power switch is in the AUTO position, the BAT switch is in the OFF position.

c. The standby power switch is in the OFF position, the BAT switch is in the ON position.

(B1) Ref: Reference: ATA 24 Electrical Power System - B737 Training book - Page 29

126. Choose the INCORRECT statement about BPCU:

a. The BPCU gives the protection logic for overvoltage faults.

b. The BPCU gives the protection logic for undervoltage faults.

c. The BPCU does not give the protection logic for overcurrent faults.

(B1) Ref: Reference: ATA 24 Electrical Power System - B737 Training book - Page 59

127. The TR UNIT light will illuminate to indicate a TRU fail condition in flight if

a. TRU 2 and TRU 3 fail.

b. TRU 3 fails

c. TRU 2 fails

(B1) Ref: Reference: ATA 24 Electrical Power System - B737 Training book - Page 25

128. The ELEC light will illuminate in flight with

a. The DC system failure

b. The stanby system failure

c. The amber ELEC light comes on only when the airplane is on the ground.

(B1) Ref: Reference: ATA 24 Electrical Power System - B737 Training book - Page 25

129. The ELEC light gives a failure indication of

a. The normal power system

b. The DC system

c. The AC system

(B1) Ref: Reference: ATA 24 Electrical Power System - B737 Training book - Page 25

130. To connect the external Ground power to the transfer busses

a. The Battery switch must be OFF

b. The Battery switch must be ON

c. The Bus Transfer switch must be in the AUTO position.

(B1) Ref: Reference: ATA 24 Electrical Power System - B737 Training book - Page 59

131. In flight, the left SOURCE OFF light comes on,

a. The AC transfer bus 1 is de-energized

b. The AC transfer bus 1 is powered from AC standby bus.

c. IDG 2 power AC transfer bus 1

(B1) Ref: Reference: ATA 24 Electrical Power System - B737 Training book - Page 33

132. The amber DRIVE light comes on and a manual disconnect is done. Can the IDG be reset?

a. Yes, in flight with the drive disconnect switch.

b. No, IDG must be replaced.

c. Yes, on ground at the IDG.

(B1) Ref: Reference: ATA 24 Electrical Power System - B737 Training book - Page 81

133. The IDG is automatically disconnected when the IDG oil temperature gets too hot. Can the IDG be reset on-wing?

a. Yes, IDG is automatically reset when oil temperature decreases.

b. Yes, on ground at the IDG.

c. No, you must remove and disassemble the IDG to reset a thermal disconnect.

(B1) Ref: Reference: ATA 24 Electrical Power System - B737 Training book - Page 81

134. Which is the power source for the AC standby bus

a. Transfer bus 1 under normal conditions

b. Transfer bus 2

c. AC main bus 1

(B1) Ref: Reference: ATA 24 Electrical Power System - B737 Training book - Page 13

135. Which is the power source for the DC standby bus

a. DC bus 1 under normal conditions

b. DC bus 2

c. TRU 3

(B1) Ref: Reference: ATA 24 Electrical Power System - B737 Training book - Page 13

136. The IDGs are the normal power sources for

a. The main buses

b. The AC transfer buses

c. The ground service buses

(B1) Ref: Reference: ATA 24 Electrical Power System - B737 Training book - Page 13

137. Which is the power source for the the battery bus

a. TRU 3 under normal conditions

b. DC bus 1

c. DC bus 2

(B1) Ref: Reference: ATA 24 Electrical Power System - B737 Training book - Page 13

138. On the ground, with the battery switch OFF and STANBY POWER Switch in AUTO, the Battery Bus is

a. Powered by TRU 3

b. Not powered

c. Powered by the Hot Battery Bus

(B1) Ref: Reference: ATA 24 Electrical Power System - B737 Training book - Page 29, 30

139. An illuminated TR UNIT light while on the ground indicates that at least two TRUs have failed.

a. True

b. False

c. Not given.

(B1) Ref: Reference: ATA 24 Electrical Power System - B737 Training book - Page 25

140. The DC bus tie relay opens when

a. Airplane is in cruise mode, bus transfer switch is in the AUTO position and AC transfer bus 1 has power

b. Airplane is in cruise mode, bus transfer switch is in the AUTO position and AC transfer bus 2 has power

c. Autopilot system is in the approach mode with glideslope capture, bus transfer switch is in the AUTO position and AC transfer buses have power

(B1) Ref: Reference: ATA 24 Electrical Power System - B737 Training book - Page 147

141. The battery charger takes 3 phase, 115v ac power and converts it to DC power with

a. Constant voltage output in the transformer rectifier mode.

b. Constant voltage output in the charge mode.

c. Variable voltage output in the transformer rectifier mode.

(B1) Ref: Reference: ATA 24 Electrical Power System - B737 Training book - Page 155

142. The amber BAT DISCHARGE light comes on when

a. Current draw is more than 100 amps for 10 seconds. b. Current draw is more than 100 amps for 12 seconds.

c. Current draw is more than 100 amps for 1.2 seconds.

(B1) Ref: Reference: ATA 24 Electrical Power System - B737 Training book - Page 158

143. The electrical system incorporates an automatic load shedding feature in case of overcurrent load shed. What is (are) the bus(es) that is normally shed first?

a. Galley and main buses on transfer bus 1 are shed first.

b. Galley and main buses on transfer bus 2 are shed first.

c. The AC standby bus is shed first

(B1) Ref: Reference: ATA 24 Electrical Power System - B737 Training book - Page 191

144. On the external power receptacle, the NOT IN USE light comes on, it means

a. External power is available, the EPC open, both ground service transfer relays are de-energized

b. External power is available, the EPC close, both ground service transfer relays are de-energized

c. External power is available, the EPC close, both ground service transfer relays are energized (B1) Ref: Reference: ATA 24 Electrical Power System - B737 Training book - Page 49

145. The external power receptacle has these six pins:

a. Three pins for each AC power phase, two pin for ground, one short pins for BPCU interlock logic.

b. Three pins for each AC power phase, one pin for ground, two short pins for BPCU interlock logic.

c. Three pins for each AC power phase, one pin for ground, one short pins for BPCU interlock logic, one short pins for back up.

(B1) Ref: Reference: ATA 24 Electrical Power System - B737 Training book - Page 50

146. The electrical system design makes sure that

a. Two AC power sources can not supply power to the same transfer bus at the same time

b. one AC power source can not supply power to both transfer buses

c. Two AC power sources can supply power to the same transfer bus at the same time