首页 › 机型题库 › Boeing 737 › Hydraulics

Boeing 737 · Hydraulics 题库（136 题）

Boeing 737 机型「Hydraulics」相关知识共 136 道题。想练习或模拟考试，请到 题库 · 模拟考试。
进入练习 / 模拟考试 »

1.Complete loss of system 'B' pressure will deactivate

  1. The outboard flight spoilers. ✓
  2. The inboard flight spoilers.
  3. The ground spoilers.
正确答案：The outboard flight spoilers.　·　737　·　来源 b737.org.uk

2.If an electric hydraulic pump OVERHEAT light comes on

  1. The pump will be automatically switched off and the OVERHEAT LIGHT extinguished. ✓
  2. Turn the associated system electric and engine hydraulic pumps OFF.
  3. Turn the associated system electric hydraulic pump OFF.
正确答案：The pump will be automatically switched off and the OVERHEAT LIGHT extinguished.　·　737　·　来源 b737.org.uk

3.On the 737 NG/MAX, a leak in the hydraulic system B engine driven pump or its associated lines would be indicated by

  1. System B contents falling to zero. ✓
  2. System B contents falling to 20%.
  3. System B contents falling to 40%.
正确答案：System B contents falling to zero.　·　737　·　来源 b737.org.uk

4.The standby system LOW PRESSURE light is armed

  1. Only when the standby pump operation has been selected or automatic standby function is activated. ✓
  2. At all times.
  3. Only when the standby pump operation has been selected or either Spoiler switch has been selected to OFF.
正确答案：Only when the standby pump operation has been selected or automatic standby function is activated.　·　737　·　来源 b737.org.uk

5.The standby hydraulic pump only supplies pressure to the

  1. Standby rudder and leading edge slats.
  2. Standby rudder actuator, leading edge devices and thrust reversers. ✓
  3. Standby rudder, leading edge devices and brakes.
正确答案：Standby rudder actuator, leading edge devices and thrust reversers.　·　737　·　来源 b737.org.uk

6.If either Flight Control switch is moved to the STBY RUD position

  1. The standby pump will be activated and the standby hydraulic LOW QUANTITY light will be armed.
  2. 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.
  3. The standby pump will be activated and the standby hydraulic LOW PRESSURE light will be armed. ✓
正确答案：The standby pump will be activated and the standby hydraulic LOW PRESSURE light will be armed.　·　737　·　来源 b737.org.uk

7.Low fluid quantity in the A system reservoir can be indicated by one of the following

  1. Mechanical indication on the reservoir. ✓
  2. LOW QUANTITY light on the centre instrument panel.
  3. LOW QUANTITY light on the centre instrument panel along with a Master Caution ENG annunciator light.
正确答案：Mechanical indication on the reservoir.　·　737　·　来源 b737.org.uk

8.If a total failure of both pumps supplying system B pressure occurs, which of the primary flight controls will be totally inoperative

  1. None. ✓
  2. Aileron and elevator.
  3. Rudder only.
正确答案：None.　·　737　·　来源 b737.org.uk

9.The A and B hydraulic reservoirs are pressurised by

  1. Air from the 14th stage only.
  2. Air from the pneumatic manifold. ✓
  3. Hydraulic fluid from the standby reservoir.
正确答案：Air from the pneumatic manifold.　·　737　·　来源 b737.org.uk

10.Selecting an engine driven hydraulic pump switch to OFF will

  1. Electrically close the fluid supply valve at the reservoir.
  2. De-activate the solenoid-held blocking valve and isolate fluid from the using unit.
  3. Activate the solenoid-held blocking valve and isolate fluid from the using unit. ✓
正确答案：Activate the solenoid-held blocking valve and isolate fluid from the using unit.　·　737　·　来源 b737.org.uk

11.The normal and maximum readings on the hydraulic system pressure indicator are

  1. 3000 : 3500psi ✓
  2. 2500 : 3200psi
  3. 3000 : 3750psi
正确答案：3000 : 3500psi　·　737　·　来源 b737.org.uk

12.The Standby hydraulic reservoir is kept topped up from

  1. Oil containers used by engineers before each flight.
  2. The system A reservoir.
  3. The system B reservoir. ✓
正确答案：The system B reservoir.　·　737　·　来源 b737.org.uk

13.Hydraulic system A power sources are

  1. One engine driven pump (ENG 1) and one electrical motor pump (ELECT 1).
  2. One engine driven pump (ENG 1) and one electrical motor pump (ELECT 2). ✓
  3. One engine driven pump (ENG 1), one electrical motor pump (ELECT 1) and one standby electric pump.
正确答案：One engine driven pump (ENG 1) and one electrical motor pump (ELECT 2).　·　737　·　来源 b737.org.uk

14.Illumination of a Hydraulic Electric Pump OVERHEAT light indicates

  1. An overheat condition in the hydraulic reservoir.
  2. An overheat condition of the pump hydraulic supply line.
  3. An overheat condition in the case drain line or the pump housing. ✓
正确答案：An overheat condition in the case drain line or the pump housing.　·　737　·　来源 b737.org.uk

15.Illumination of a electric hydraulic pump OVERHEAT light will

  1. Automatically shut down the associated pump. ✓
  2. Not shut down the associated pump.
  3. Automatically arm the LOW PRESSURE light for the associated pump.
正确答案：Automatically shut down the associated pump.　·　737　·　来源 b737.org.uk

16.The maximum hydraulic system A or B pressure is

  1. 3000psi
  2. 3250psi
  3. 3500psi ✓
正确答案：3500psi　·　737　·　来源 b737.org.uk

17.Loss of the A hydraulic system will result in the complete loss of the following

  1. Ground spoilers. Inboard flight spoilers. Alternate brakes. Autopilot A. ✓
  2. Ground spoilers. Inboard flight spoilers. Normal brakes. Nose wheel steering.
  3. Ground spoilers. Outboard flight spoilers. Elevator feel system. Alternate brakes. Autoslat system.
正确答案：Ground spoilers. Inboard flight spoilers. Alternate brakes. Autopilot A.　·　737　·　来源 b737.org.uk

18.Loss of the B hydraulic system will result in the complete loss of the following

  1. Outboard flight spoilers. Autopilot B. No. 2 thrust reverser. Yaw damper.
  2. Outboard flight spoilers. Autopilot B. Normal brakes. Yaw damper. ✓
  3. Outboard flight spoilers. Autoslats. Autopilot B.
正确答案：Outboard flight spoilers. Autopilot B. Normal brakes. Yaw damper.　·　737　·　来源 b737.org.uk

19.The standby hydraulic pump is automatically activated on the loss of system A or B hydraulic pressure

  1. During the take-off or landing with a wheel speed greater than 60 Kts and the wing flaps extended. ✓
  2. During the take-off or landing with a wheel speed greater than 90 Kts and wing flaps extended.
  3. During the take-off or landing with a wheel speed greater than 60 Kts irrespective of the wing flaps position.
正确答案：During the take-off or landing with a wheel speed greater than 60 Kts and the wing flaps extended.　·　737　·　来源 b737.org.uk

20.On the 737 NG, the indications of a leak in the standby reservoir are

  1. Illumination of the standby hydraulic LOW QUANTITY light and the B system reservoir quantity decreasing and stabilising at approximately 64% full.
  2. Illumination of the standby hydraulic LOW QUANTITY light and the B system reservoir quantity decreasing and stabilising at approximately 70% full. ✓
  3. Illumination of the standby hydraulic LOW QUANTITY light and the B system reservoir quantity decreasing and stabilising at approximately 88% full.
正确答案：Illumination of the standby hydraulic LOW QUANTITY light and the B system reservoir quantity decreasing and stabilising at approximately 70% full.　·　737　·　来源 b737.org.uk

21.On the 737 NG/MAX, a leak in the hydraulic system A engine driven pump or its associated lines would be indicated by

  1. System A contents falling to 0%.
  2. System A contents falling to 20%. ✓
  3. System A contents falling to 40%.
正确答案：System A contents falling to 20%.　·　737　·　来源 b737.org.uk

22.The 737NG/MAX 'B' system reservoir has

  1. One standpipe. ✓
  2. Two standpipes.
  3. One standpipe used for reservoir pressurisation of the standby reservoir.
正确答案：One standpipe.　·　737　·　来源 b737.org.uk

23.Placing the A Flt Control switch to STBY RUD position will

  1. Start the standby pump, arm the standby hydraulic LOW PRESSURE light, close the A system Flight Control Shutoff valve and the A system Flt Control LOW PRESSURE light is de-activated when the standby rudder shutoff valve opens. ✓
  2. Start the standby pump, arm the standby hydraulic LOW PRESSURE light, close the A and B system Flight Control Shutoff valves and the A system Flt Control LOW PRESSURE light is de-activated when the standby rudder shutoff valve opens.
  3. Start the standby pump, close the A system Flight Control Shutoff valve and the A system Flt Control LOW PRESSURE light is de-activated when the standby rudder shutoff valve opens.
正确答案：Start the standby pump, arm the standby hydraulic LOW PRESSURE light, close the A system Flight Control Shutoff valve and the A system Flt Control LOW PRESSURE light is de-activated when the standby rudder shutoff valve opens.　·　737　·　来源 b737.org.uk

24.Using the Standby Hydraulic power for thrust reverser deployment will cause

  1. Deployment time not to be affected.
  2. Deployment time to increase. ✓
  3. Deployment time to decrease.
正确答案：Deployment time to increase.　·　737　·　来源 b737.org.uk

25.The standby system low quantity light is

  1. Armed at all times and will illuminate whenever the reservoir is approximately half empty. ✓
  2. Armed at all times and will illuminate whenever the reservoir is approximately three quarters empty.
  3. Armed only when either Flt Control switch is placed to the STBY RUD position.
正确答案：Armed at all times and will illuminate whenever the reservoir is approximately half empty.　·　737　·　来源 b737.org.uk

26.The Standby hydraulic fluid

  1. Is cooled by a heat exchanger located in NO. 2 tank.
  2. Is cooled by a heat exchanger located in NO. 1 tank.
  3. Is not cooled. ✓
正确答案：Is not cooled.　·　737　·　来源 b737.org.uk

27.Pulling NO.1 Engine Fire switch will

  1. Stop the fluid to the No.1 Engine Driven and electric hydraulic pump by closing the Hydraulic Shutoff valve and de-activate the associated low pressure light.
  2. Stop the fluid to the No. 1 Engine Driven hydraulic pump by closing the Hydraulic Shutoff valve and de-activate the associated low pressure light. ✓
  3. Only stop the fluid to the No. 1 Engine Driven Hydraulic pump by closing the Hydraulic Shutoff valve.
正确答案：Stop the fluid to the No. 1 Engine Driven hydraulic pump by closing the Hydraulic Shutoff valve and de-activate the associated low pressure light.　·　737　·　来源 b737.org.uk

28.The engine driven hydraulic pump switch

  1. In the OFF position will de-activate the hydraulic LOW PRESS light.
  2. Is left in the ON position on shutdown to prolong the life of the blocking valve solenoid. ✓
  3. Should be switched OFF in the event of the electric hydraulic pump OVERHEAT light illuminating.
正确答案：Is left in the ON position on shutdown to prolong the life of the blocking valve solenoid.　·　737　·　来源 b737.org.uk

29.System A Hydraulic Leak - If a leak develops in the electric motor-driven pump or its related lines, or components common to both the engine and electric motor-driven pumps:

  1. the quantity in the reservoir steadily decreases to zero.
  2. The quantity in the reservoir steadily decreases to zero and all system pressure is lost. ✓
  3. The quantity in the reservoir steadily decreases to 20% and system pressure is minimum.
  4. The quantity in the reservoir steadily decreases to 15% and all system pressure partially lost.
正确答案：The quantity in the reservoir steadily decreases to zero and all system pressure is lost.　·　MAX　·　来源 smartcockpit.com

30.Standby Hydraulic System - The standby hydraulic system is provided as a backup if system A and/or B pressure is lost. The standby system can be only activated automatically.

  1. True.
  2. False. ✓
正确答案：False.　·　MAX　·　来源 smartcockpit.com

31.Standby Hydraulic System Leak - The LOW QUANTITY light illuminates when the standby reservoir:

  1. Has a quantity of fluid less or equal to 10% of the maximum level.
  2. Has a quantity of fluid less or equal to 20% of the maximum level.
  3. Has a quantity of fluid less or equal to 30% of the maximum level.
  4. Is approximately half empty. ✓
正确答案：Is approximately half empty.　·　MAX　·　来源 smartcockpit.com

32.STANDBY HYDRAULIC LOW QUANTITY Light - What is the true statement?

  1. If Illuminated amber it indicates low quantity in standby hydraulic reservoir. It is always armed. ✓
  2. If Illuminated amber it indicates low quantity in standby hydraulic reservoir.
  3. If Illuminated amber it indicates low quantity in standby hydraulic reservoir. It is only armed when on ground.
  4. If Illuminated amber it indicates low quantity in standby hydraulic reservoir. It is only armed when in flight.
正确答案：If Illuminated amber it indicates low quantity in standby hydraulic reservoir. It is always armed.　·　MAX　·　来源 smartcockpit.com

33.In addition to hydraulic system A and B, the rudder can also be powered by the standby hydraulic system through the:

  1. Standby Rudder PCU ✓
  2. System A Standby Rudder PCU.
  3. Main Rudder PCU.
  4. System B Standby Rudder PCU.
正确答案：Standby Rudder PCU　·　MAX　·　来源 smartcockpit.com

34.Landing Gear Transfer Unit - The system B engine-driven pump supplies the volume of hydraulic fluid needed to operate the landing gear transfer unit when all of the following conditions exist:

  1. System B engine-driven pump hydraulic pressure drops below limits, airborne,
  2. Airborne, No. 1 engine RPM drops below a limit value, landing gear lever is positioned UP, either main landing gear is not up and locked. ✓
  3. Airborne, No. 1 or No. 2 engine RPM drops below a limit value, landing gear lever is positioned UP, either main landing gear is not up and locked.
  4. Airborne, No. 1 or No. 2 engine RPM drops below a limit value, landing gear lever is positioned UP or DOWN, either main landing gear is not up and locked.
正确答案：Airborne, No. 1 engine RPM drops below a limit value, landing gear lever is positioned UP, either main landing gear is not up and locked.　·　MAX　·　来源 smartcockpit.com

35.The 737NG/MAX 'B' system reservoir has:

  1. One standpipe. ✓
  2. Two standpipes.
  3. One standpipe used for reservoir pressurisation of the standby reservoir.
正确答案：One standpipe.　·　MAX　·　来源 smartcockpit.com

36.Standby Hydraulic System Leak - System B continues to operate normally, however, the system B reservoir fluid level indication decreases and stabilizes at:

  1. Approximately 50% full.
  2. Approximately 72% full. ✓
  3. Approximately 25% full.
  4. Approximately 40% full.
正确答案：Approximately 72% full.　·　MAX　·　来源 smartcockpit.com

37.The amber LOW pressure light for the No.1 Engine Driven Hydraulic Pump illuminates. What should you do?

  1. Position the pump switch to OFF. ✓
  2. Start the ELEC pump
  3. Monitor hydraulic System A pressure.
  4. Select STBY RUD ON.
正确答案：Position the pump switch to OFF.　·　MAX　·　来源 smartcockpit.com

38.Power Transfer Unit (PTU) - The PTU uses system B pressure to power a hydraulic motor-driven pump, which pressurizes system A hydraulic fluid.

  1. True.
  2. False. ✓
正确答案：False.　·　MAX　·　来源 smartcockpit.com

39.With the loss of hydraulic system B and with the system A operating normally:

  1. Main yaw damper functions are available if the FLT CTL B switch is placed to STBY RUD and the yaw damper switch is reset to ON.
  2. Main yaw damper functions are lost. ✓
  3. Normal yaw damper functions are available as long as hydraulic system A is providing normal pressure and the yaw damper switch is ON.
  4. Main yaw daper functions are available as long as hydraulic system A is providing normal pressure and the yaw damper switch is ON.
正确答案：Main yaw damper functions are lost.　·　MAX　·　来源 smartcockpit.com

40.In case of loss of system A:

  1. Autoslats are not available.
  2. Nose wheel steering is not available. ✓
  3. Autopilot B is not available.
  4. Alternate nose wheel steering is not available.
正确答案：Nose wheel steering is not available.　·　MAX　·　来源 smartcockpit.com

41.System A Hydraulic Leak - If a leak develops in the engine-driven pump or its related lines, a standpipe in the reservoir prevents a total system fluid loss. With fluid level at the top of the standpipe, the reservoir quantity displayed indicates approximately _____

  1. 20% full. ✓
  2. 30% full.
  3. 50% full.
  4. 60% full.
正确答案：20% full.　·　MAX　·　来源 smartcockpit.com

42.An engine-driven hydraulic pump supplies approximately _____ the fluid volume of the related electric motor-driven hydraulic pump.

  1. 6 times ✓
  2. 4 times
  3. 3 times
  4. 10 times
正确答案：6 times　·　MAX　·　来源 smartcockpit.com

43.System B Hydraulic Leak - A leak in system B can significantly affect the operation of the standby hydraulic system.

  1. True.
  2. False. ✓
正确答案：False.　·　MAX　·　来源 smartcockpit.com

44.Variations in Hydraulic Quantity Indications - During normal operations, variations in hydraulic quantity indications occur when:

  1. The system becomes pressurized after engine start, raising or lowering the landing gear
  2. Raising or lowering the landing gear, extending leading edge devices
  3. Raising or lowering the landing gear, extending leading edge devices, during severe icing.
  4. The system becomes pressurized after engine start, raising or lowering the landing gear or leading edge devices, cold soaking occurs during long periods of cruise. ✓
正确答案：The system becomes pressurized after engine start, raising or lowering the landing gear or leading edge devices, cold soaking occurs during long periods of cruise.　·　MAX　·　来源 smartcockpit.com

45.Power Transfer Unit (PTU) - The purpose of the PTU is to supply the additional volume of hydraulic fluid needed to operate _____ when system B engine-driven hydraulic pump volume is lost.

  1. The slats and flaps
  2. The autoslats and leading edge flaps and slats at the normal rate ✓
  3. The leading edge flaps and landing gear
  4. The slats and the landing gear
正确答案：The autoslats and leading edge flaps and slats at the normal rate　·　MAX　·　来源 smartcockpit.com

46.Complete loss of system 'B' pressure will deactivate:

  1. The outboard flight spoilers. ✓
  2. The inboard flight spoilers.
  3. The ground spoilers.
正确答案：The outboard flight spoilers.　·　MAX　·　来源 smartcockpit.com

47.Standby Hydraulic System Leak - If a leak occurs in the standby system, the standby reservoir quantity decreases to _____

  1. 10%.
  2. 20%.
  3. Zero. ✓
  4. 30%.
正确答案：Zero.　·　MAX　·　来源 smartcockpit.com

48.The standby hydraulic system uses a single electric motor-driven pump to power:

  1. Thrust reversers, rudder, leading edge flaps and slats (extend only), standby yaw damper. ✓
  2. Rudder, leading edge flaps and slats (extend only), yaw damper.
  3. Partial thrust reversers, standby rudder, leading edge flaps and slats (extend only), standby yaw damper.
  4. Partial thrust reversers, rudder, leading edge flaps and slats (extend only), standby yaw damper.
正确答案：Thrust reversers, rudder, leading edge flaps and slats (extend only), standby yaw damper.　·　MAX　·　来源 smartcockpit.com

49.Loss of an engine-driven hydraulic pump and a high demand on the system may result in an intermittent illumination of the LOW PRESSURE light for the remaining electric motor-driven hydraulic pump.

  1. True. ✓
  2. False.
正确答案：True.　·　MAX　·　来源 smartcockpit.com

50.STANDBY HYDRAULIC LOW PRESSURE Light - When illuminated amber:

  1. It indicates pressure of standby pump is below 20% It is armed only when standby pump operation has been selected.
  2. It indicates output pressure of standby pump is low. It is armed only when standby pump operation has been selected.
  3. It indicates output pressure of standby pump is low. It is armed only when standby pump operation has been selected or automatic standby function is activated. ✓
  4. It indicates pressure of standby pump is below 20% It is armed only when automatic standby function is activated.
正确答案：It indicates output pressure of standby pump is low. It is armed only when standby pump operation has been selected or automatic standby function is activated.　·　MAX　·　来源 smartcockpit.com

51.Both A and B hydraulic systems have an engine-driven pump and an AC electric motor-driven pump. The system A engine-driven pump is powered by the No. 2 engine and the system B engine-driven pump is powered by the No. 1 engine.

  1. True.
  2. False. ✓
正确答案：False.　·　MAX　·　来源 smartcockpit.com

52.On the Boeing B737 NG/MAX, a leak in the hydraulic system B engine driven pump or its associated lines would be indicated by:

  1. System B contents falling to zero. ✓
  2. System B contents falling to 20%.
  3. System B contents falling to 40%.
正确答案：System B contents falling to zero.　·　MAX　·　来源 smartcockpit.com

53.If one FLIGHT CONTROL switch is moved to STBY RUD:

  1. It activates standby pump and opens standby rudder shutoff valve to pressurize standby rudder power control unit. ✓
  2. It deactivates the standby rudder power control unit.
  3. It activates the standby rudder power control unit.
  4. It activates the standby rudder power control unit and deactivates the flight control shutoff valve isolating ailerons, elevators.
正确答案：It activates standby pump and opens standby rudder shutoff valve to pressurize standby rudder power control unit.　·　MAX　·　来源 smartcockpit.com

54.Using the Standby Hydraulic power for thrust reverser deployment will cause:

  1. Deployment time not to be affected.
  2. Deployment time to increase. ✓
  3. Deployment time to decrease.
正确答案：Deployment time to increase.　·　MAX　·　来源 smartcockpit.com

55.The standby hydraulic pump only supplies pressure to the:

  1. Standby rudder and leading edge slats.
  2. Standby rudder actuator, leading edge devices and thrust reversers. ✓
  3. Standby rudder, leading edge devices and brakes.
正确答案：Standby rudder actuator, leading edge devices and thrust reversers.　·　MAX　·　来源 smartcockpit.com

56.The Standby hydraulic fluid:

  1. Is cooled by a heat exchanger located in NO. 2 tank.
  2. Is cooled by a heat exchanger located in NO. 1 tank.
  3. Is not cooled. ✓
正确答案：Is not cooled.　·　MAX　·　来源 smartcockpit.com

57.If the hydraulic system is not properly pressurized, foaming can occur at higher altitudes. Foaming can be recognized by:

  1. Pressure fluctuations and the blinking of the related LOW PRESSURE lights. The MASTER CAUTION and HYD annunciator lights may also illuminate momentarily. ✓
  2. Pressure fluctuations.
  3. Pressure fluctuations and the illumination of the related LOW PRESSURE lights.
  4. Pressure fluctuations and the MASTER CAUTION and HYD annunciator lights illumination.
正确答案：Pressure fluctuations and the blinking of the related LOW PRESSURE lights. The MASTER CAUTION and HYD annunciator lights may also illuminate momentarily.　·　MAX　·　来源 smartcockpit.com

58.Low fluid quantity in the A system reservoir can be indicated by one of the following:

  1. Mechanical indication on the reservoir. ✓
  2. LOW QUANTITY light on the centre instrument panel.
  3. LOW QUANTITY light on the centre instrument panel along with a Master Caution ENG annunciator light.
正确答案：Mechanical indication on the reservoir.　·　MAX　·　来源 smartcockpit.com

59.STBY RUD ON Light - When illuminated amber, it indicates the standby hydraulic system is commanded on to pressurize the standby rudder power control unit.

  1. True. ✓
  2. False.
正确答案：True.　·　MAX　·　来源 smartcockpit.com

60.The RFF indication is displayed:

  1. Only when hydraulic quantity is below 76% in either system A or B and the aircraft is on the ground with both engines shutdown or after landing with flaps up during taxi-in. ✓
  2. Automatically when the hydraulic quantity is below 88% in either system A or B.
  3. Valid only when airplane is on ground and when quantity is below 88% in either system A or B
  4. Valid only when airplane is on ground, with or without engines running and when quantity is below 76% in either system A or B
正确答案：Only when hydraulic quantity is below 76% in either system A or B and the aircraft is on the ground with both engines shutdown or after landing with flaps up during taxi-in.　·　MAX　·　来源 smartcockpit.com

61.Minimum fuel for ground operation of electric motor-driven pumps is _____ in the related main tank.

  1. 760 kgs / 1700 lbs. ✓
  2. 500 kgs / 1100 lbs.
  3. 420 kgs / 900 lbs.
  4. 600 kgs / 1300 lbs.
正确答案：760 kgs / 1700 lbs.　·　MAX　·　来源 smartcockpit.com

62.ALTERNATE FLAPS Master Switch - When placed in the ARM position, the ALTERNATE FLAPS Master switch:

  1. It activates standby pump, and arms ALTERNATE FLAPS position switch.
  2. It closes trailing edge flap bypass valve, activates standby pump, and arms ALTERNATE FLAPS position switch. ✓
  3. It arms ALTERNATE FLAPS position switch.
  4. It closes Slats and trailing edge flap bypass valve, and arms ALTERNATE FLAPS position switch.
正确答案：It closes trailing edge flap bypass valve, activates standby pump, and arms ALTERNATE FLAPS position switch.　·　MAX　·　来源 smartcockpit.com

63.Selecting an engine driven hydraulic pump switch to OFF will:

  1. Electrically close the fluid supply valve at the reservoir.
  2. De-activate the solenoid-held blocking valve and isolate fluid from the using unit.
  3. Activate the solenoid-held blocking valve and isolate fluid from the using unit. ✓
正确答案：Activate the solenoid-held blocking valve and isolate fluid from the using unit.　·　MAX　·　来源 smartcockpit.com

64.The maximum hydraulic system A or B pressure is:

  1. 3000 psi.
  2. 3250 psi.
  3. 3500 psi. ✓
正确答案：3500 psi.　·　MAX　·　来源 smartcockpit.com

65.Hydraulic fluid used for cooling and lubrication of the pumps passes through a heat exchanger before returning to the reservoir. The heat exchanger for system A is located in main fuel tank No. 2 and for system B is in main fuel tank No. 1.

  1. True
  2. False. ✓
正确答案：False.　·　MAX　·　来源 smartcockpit.com

66.The standby system LOW PRESSURE light is armed:

  1. Only when the standby pump operation has been selected or automatic standby function is activated. ✓
  2. At all times.
  3. Only when the standby pump operation has been selected or either Spoiler switch has been selected to OFF.
正确答案：Only when the standby pump operation has been selected or automatic standby function is activated.　·　MAX　·　来源 smartcockpit.com

67.The normal and maximum readings on the hydraulic system pressure indicator are:

  1. 2500 to 3200psi.
  2. 3000 to 3500psi. ✓
  3. 3000 to 3750psi.
正确答案：3000 to 3500psi.　·　MAX　·　来源 smartcockpit.com

68.If a total failure of both pumps supplying system B pressure occurs, which of the primary flight controls will be totally inoperative:

  1. None. ✓
  2. Aileron and rudder.
  3. Rudder only.
正确答案：None.　·　MAX　·　来源 smartcockpit.com

69.The hydraulic brake pressure indicator displays accumulator nitrogen pre-charge pressure of 1000 psi and:

  1. Brake pressure from hydraulic system A if it is greater than 1000 psi.
  2. Brake pressure from the PTU.
  3. Brake pressure from hydraulic system B if it is greater than 1000 psi. ✓
  4. Brake pressure from standby hydraulic system.
正确答案：Brake pressure from hydraulic system B if it is greater than 1000 psi.　·　MAX　·　来源 smartcockpit.com

70.The ELEC 2 (system A) or ELEC 1 (system B) pump ON/OFF switch controls the related electric motor-driven pump. If an overheat is detected in either system, the related OVERHEAT light illuminates.

  1. True. ✓
  2. False.
正确答案：True.　·　MAX　·　来源 smartcockpit.com

71.Electric Hydraulic Pump OVERHEAT Lights - What does this light indicate?

  1. Hydraulic fluid used to cool and lubricate the corresponding electric motor driven pump has overheated or the pump itself has overheated. ✓
  2. Electric motor driven pump has overheated
  3. Electric motor driven pump has overheated or loss of hydraulic fluid.
  4. Electric motor driven pump has lost power and has therefore overheated
正确答案：Hydraulic fluid used to cool and lubricate the corresponding electric motor driven pump has overheated or the pump itself has overheated.　·　MAX　·　来源 smartcockpit.com

72.Both A and B hydraulic systems have an engine-driven pump and an AC electric motor-driven pump. The system A engine-driven pump is powered by the No. 2 engine and the system B engine-driven pump is powered by the No. 1 engine.

  1. True.
  2. False. ✓
正确答案：False.　·　NG　·　来源 smartcockpit.com

73.The ELEC 2 (system A) or ELEC 1 (system B) pump ON/OFF switch controls the related electric motor-driven pump. If an overheat is detected in either system, the related OVERHEAT light illuminates.

  1. True. ✓
  2. False.
正确答案：True.　·　NG　·　来源 smartcockpit.com

74.Standby Hydraulic System Leak - The LOW QUANTITY light illuminates when the standby reservoir:

  1. Has a quantity of fluid less or equal to 10% of the maximum level.
  2. Has a quantity of fluid less or equal to 20% of the maximum level.
  3. Has a quantity of fluid less or equal to 30% of the maximum level.
  4. Is approximately half empty. ✓
正确答案：Is approximately half empty.　·　NG　·　来源 smartcockpit.com

75.STANDBY HYDRAULIC LOW QUANTITY Light - What is the true statement?

  1. If Illuminated amber it indicates low quantity in standby hydraulic reservoir. It is always armed. ✓
  2. If Illuminated amber it indicates low quantity in standby hydraulic reservoir.
  3. If Illuminated amber it indicates low quantity in standby hydraulic reservoir. It is only armed when on ground.
  4. If Illuminated amber it indicates low quantity in standby hydraulic reservoir. It is only armed when in flight.
正确答案：If Illuminated amber it indicates low quantity in standby hydraulic reservoir. It is always armed.　·　NG　·　来源 smartcockpit.com

76.Power Transfer Unit (PTU) - The PTU uses system B pressure to power a hydraulic motor-driven pump, which pressurizes system A hydraulic fluid.

  1. True.
  2. False. ✓
正确答案：False.　·　NG　·　来源 smartcockpit.com

77.STANDBY HYDRAULIC LOW PRESSURE Light - When illuminated amber:

  1. It indicates pressure of standby pump is below 20% It is armed only when standby pump operation has been selected.
  2. It indicates output pressure of standby pump is low It is armed only when standby pump operation has been selected.
  3. It indicates output pressure of standby pump is low It is armed only when standby pump operation has been selected or automatic standby function is activated. ✓
  4. It indicates pressure of standby pump is below 20% It is armed only when automatic standby function is activated.
正确答案：It indicates output pressure of standby pump is low It is armed only when standby pump operation has been selected or automatic standby function is activated.　·　NG　·　来源 smartcockpit.com

78.System A Hydraulic Leak - If a leak develops in the electric motor-driven pump or its related lines, or components common to both the engine and electric motor-driven pumps:

  1. the quantity in the reservoir steadily decreases to zero.
  2. The quantity in the reservoir steadily decreases to zero and all system pressure is lost. ✓
  3. The quantity in the reservoir steadily decreases to 20% and system pressure is minimum.
  4. The quantity in the reservoir steadily decreases to 15% and all system pressure partially lost.
正确答案：The quantity in the reservoir steadily decreases to zero and all system pressure is lost.　·　NG　·　来源 smartcockpit.com

79.Power Transfer Unit (PTU) - The purpose of the PTU is to supply the additional volume of hydraulic fluid needed to operate _____ when system B engine-driven hydraulic pump volume is lost.

  1. The slats and flaps
  2. The autoslats and leading edge flaps and slats at the normal rate ✓
  3. The leading edge flaps and landing gear
  4. The slats and the landing gear
正确答案：The autoslats and leading edge flaps and slats at the normal rate　·　NG　·　来源 smartcockpit.com

80.Landing Gear Transfer Unit - The system B engine-driven pump supplies the volume of hydraulic fluid needed to operate the landing gear transfer unit when all of the following conditions exist:

  1. System B engine-driven pump hydraulic pressure drops below limits, airborne,
  2. Airborne, No. 1 engine RPM drops below a limit value, landing gear lever is positioned UP, either main landing gear is not up and locked. ✓
  3. Airborne, No. 1 or No. 2 engine RPM drops below a limit value, landing gear lever is positioned UP, either main landing gear is not up and locked.
  4. Airborne, No. 1 or No. 2 engine RPM drops below a limit value, landing gear lever is positioned UP or DOWN, either main landing gear is not up and locked.
正确答案：Airborne, No. 1 engine RPM drops below a limit value, landing gear lever is positioned UP, either main landing gear is not up and locked.　·　NG　·　来源 smartcockpit.com

81.If one FLIGHT CONTROL switch is moved to STBY RUD:

  1. It activates standby pump and opens standby rudder shutoff valve to pressurize standby rudder power control unit. ✓
  2. It deactivates the standby rudder power control unit.
  3. It activates the standby rudder power control unit.
  4. It activates the standby rudder power control unit and deactivates the flight control shutoff valve isolating ailerons, elevators.
正确答案：It activates standby pump and opens standby rudder shutoff valve to pressurize standby rudder power control unit.　·　NG　·　来源 smartcockpit.com

82.Standby Hydraulic System - The standby hydraulic system is provided as a backup if system A and/or B pressure is lost. The standby system can be only activated automatically.

  1. True.
  2. False. ✓
正确答案：False.　·　NG　·　来源 smartcockpit.com

83.The RFF indication is displayed:

  1. Only when hydraulic quantity is below 76% in either system A or B and the aircraft is on the ground with both engines shutdown or after landing with flaps up during taxi-in. ✓
  2. Automatically when the hydraulic quantity is below 88% in either system A or B.
  3. Valid only when airplane is on ground and when quantity is below 88% in either system A or B
  4. Valid only when airplane is on ground, with or without engines running and when quantity is below 76% in either system A or B
正确答案：Only when hydraulic quantity is below 76% in either system A or B and the aircraft is on the ground with both engines shutdown or after landing with flaps up during taxi-in.　·　NG　·　来源 smartcockpit.com

84.In addition to hydraulic system A and B, the rudder can also be powered by the standby hydraulic system through the:

  1. Standby Rudder PCU ✓
  2. System A Standby Rudder PCU.
  3. Main Rudder PCU.
  4. System B Standby Rudder PCU.
正确答案：Standby Rudder PCU　·　NG　·　来源 smartcockpit.com

85.The standby hydraulic system uses a single electric motor-driven pump to power:

  1. Thrust reversers, rudder, leading edge flaps and slats (extend only), standby yaw damper. ✓
  2. Rudder, leading edge flaps and slats (extend only), yaw damper.
  3. Partial thrust reversers, standby rudder, leading edge flaps and slats (extend only), standby yaw damper.
  4. Partial thrust reversers, rudder, leading edge flaps and slats (extend only), standby yaw damper.
正确答案：Thrust reversers, rudder, leading edge flaps and slats (extend only), standby yaw damper.　·　NG　·　来源 smartcockpit.com

86.Standby Hydraulic System Leak - System B continues to operate normally, however, the system B reservoir fluid level indication decreases and stabilizes at:

  1. Approximately 50% full.
  2. Approximately 72% full. ✓
  3. Approximately 25% full.
  4. Approximately 40% full.
正确答案：Approximately 72% full.　·　NG　·　来源 smartcockpit.com

87.The hydraulic brake pressure indicator displays accumulator nitrogen pre-charge pressure of 1000 psi and:

  1. Brake pressure from hydraulic system A if it is greater than 1000 psi.
  2. Brake pressure from the PTU.
  3. Brake pressure from hydraulic system B if it is greater than 1000 psi. ✓
  4. Brake pressure from standby hydraulic system.
正确答案：Brake pressure from hydraulic system B if it is greater than 1000 psi.　·　NG　·　来源 smartcockpit.com

88.System A Hydraulic Leak - If a leak develops in the engine-driven pump or its related lines, a standpipe in the reservoir prevents a total system fluid loss. With fluid level at the top of the standpipe, the reservoir quantity displayed indicates approximately _____

  1. 20% full. ✓
  2. 40% full.
  3. 50% full.
  4. 72% full.
正确答案：20% full.　·　NG　·　来源 smartcockpit.com

89.The amber LOW pressure light for the No.1 Engine Driven Hydraulic Pump illuminates. What should you do?

  1. Position the pump switch to OFF. ✓
  2. Start the ELEC pump
  3. Monitor hydraulic System A pressure.
  4. Select STBY RUD ON.
正确答案：Position the pump switch to OFF.　·　NG　·　来源 smartcockpit.com

90.With the loss of hydraulic system B and with the system A operating normally:

  1. Main yaw damper functions are available if the FLT CTL B switch is placed to STBY RUD and the yaw damper switch is reset to ON.
  2. Main yaw damper functions are lost. ✓
  3. Normal yaw damper functions are available as long as hydraulic system A is providing normal pressure and the yaw damper switch is ON.
  4. Main yaw daper functions are available as long as hydraulic system A is providing normal pressure and the yaw damper switch is ON.
正确答案：Main yaw damper functions are lost.　·　NG　·　来源 smartcockpit.com

91.Loss of an engine-driven hydraulic pump and a high demand on the system may result in an intermittent illumination of the LOW PRESSURE light for the remaining electric motor-driven hydraulic pump.

  1. True. ✓
  2. False.
正确答案：True.　·　NG　·　来源 smartcockpit.com

92.System B Hydraulic Leak - A leak in system B can significantly affect the operation of the standby hydraulic system.

  1. True.
  2. False. ✓
正确答案：False.　·　NG　·　来源 smartcockpit.com

93.Standby Hydraulic System Leak - If a leak occurs in the standby system, the standby reservoir quantity decreases to _____

  1. 10%.
  2. 20%.
  3. Zero. ✓
  4. 30%.
正确答案：Zero.　·　NG　·　来源 smartcockpit.com

94.Minimum fuel for ground operation of electric motor-driven pumps is _____ in the related main tank.

  1. 760 kgs / 1700 lbs. ✓
  2. 500 kgs / 1100 lbs.
  3. 420 kgs / 900 lbs.
  4. 600 kgs / 1300 lbs.
正确答案：760 kgs / 1700 lbs.　·　NG　·　来源 smartcockpit.com

95.ALTERNATE FLAPS Master Switch - When placed in the ARM position, the ALTERNATE FLAPS Master switch:

  1. It activates standby pump, and arms ALTERNATE FLAPS position switch.
  2. It closes trailing edge flap bypass valve, activates standby pump, and arms ALTERNATE FLAPS position switch. ✓
  3. It arms ALTERNATE FLAPS position switch.
  4. It closes Slats and trailing edge flap bypass valve, and arms ALTERNATE FLAPS position switch.
正确答案：It closes trailing edge flap bypass valve, activates standby pump, and arms ALTERNATE FLAPS position switch.　·　NG　·　来源 smartcockpit.com

96.An engine-driven hydraulic pump supplies approximately _____ the fluid volume of the related electric motor-driven hydraulic pump.

  1. 6 times ✓
  2. 4 times
  3. 3 times
  4. 10 times
正确答案：6 times　·　NG　·　来源 smartcockpit.com

97.STBY RUD ON Light - When illuminated amber, it indicates the standby hydraulic system is commanded on to pressurize the standby rudder power control unit.

  1. True. ✓
  2. False.
正确答案：True.　·　NG　·　来源 smartcockpit.com

98.If the hydraulic system is not properly pressurized, foaming can occur at higher altitudes. Foaming can be recognized by:

  1. Pressure fluctuations and the blinking of the related LOW PRESSURE lights. The MASTER CAUTION and HYD annunciator lights may also illuminate momentarily. ✓
  2. Pressure fluctuations.
  3. Pressure fluctuations and the illumination of the related LOW PRESSURE lights.
  4. Pressure fluctuations and the MASTER CAUTION and HYD annunciator lights illumination.
正确答案：Pressure fluctuations and the blinking of the related LOW PRESSURE lights. The MASTER CAUTION and HYD annunciator lights may also illuminate momentarily.　·　NG　·　来源 smartcockpit.com

99.Electric Hydraulic Pump OVERHEAT Lights - What does this light indicate?

  1. Hydraulic fluid used to cool and lubricate the corresponding electric motor driven pump has overheated or the pump itself has overheated. ✓
  2. Electric motor driven pump has overheated
  3. Electric motor driven pump has overheated or loss of hydraulic fluid.
  4. Electric motor driven pump has lost power and has therefore overheated
正确答案：Hydraulic fluid used to cool and lubricate the corresponding electric motor driven pump has overheated or the pump itself has overheated.　·　NG　·　来源 smartcockpit.com

100.In case of loss of system A:

  1. Autoslats are not available.
  2. Nose wheel steering is not available. ✓
  3. Autopilot B is not available.
  4. Alternate nose wheel steering is not available.
正确答案：Nose wheel steering is not available.　·　NG　·　来源 smartcockpit.com

101.Variations in Hydraulic Quantity Indications - During normal operations, variations in hydraulic quantity indications occur when:

  1. The system becomes pressurized after engine start, raising or lowering the landing gear
  2. Raising or lowering the landing gear, extending leading edge devices
  3. Raising or lowering the landing gear, extending leading edge devices, during severe icing.
  4. The system becomes pressurized after engine start, raising or lowering the landing gear or leading edge devices, cold soaking occurs during long periods of cruise. ✓
正确答案：The system becomes pressurized after engine start, raising or lowering the landing gear or leading edge devices, cold soaking occurs during long periods of cruise.　·　NG　·　来源 smartcockpit.com

102.Hydraulic fluid used for cooling and lubrication of the pumps passes through a heat exchanger before returning to the reservoir. The heat exchanger for system A is located in main fuel tank No. 2 and for system B is in main fuel tank No. 1.

  1. True
  2. False. ✓
正确答案：False.　·　NG　·　来源 smartcockpit.com

103.On the Boeing B737 NG/MAX, a leak in the hydraulic system B engine driven pump or its associated lines would be indicated by:

  1. System B contents falling to zero. ✓
  2. System B contents falling to 20%.
  3. System B contents falling to 40%.
正确答案：System B contents falling to zero.　·　NG　·　来源 smartcockpit.com

104.If a total failure of both pumps supplying system B pressure occurs, which of the primary flight controls will be totally inoperative:

  1. None. ✓
  2. Aileron and rudder.
  3. Rudder only.
正确答案：None.　·　NG　·　来源 smartcockpit.com

105.The standby hydraulic pump only supplies pressure to the:

  1. Standby rudder and leading edge slats.
  2. Standby rudder actuator, leading edge devices and thrust reversers. ✓
  3. Standby rudder, leading edge devices and brakes.
正确答案：Standby rudder actuator, leading edge devices and thrust reversers.　·　NG　·　来源 smartcockpit.com

106.The standby system LOW PRESSURE light is armed:

  1. Only when the standby pump operation has been selected or automatic standby function is activated. ✓
  2. At all times.
  3. Only when the standby pump operation has been selected or either Spoiler switch has been selected to OFF.
正确答案：Only when the standby pump operation has been selected or automatic standby function is activated.　·　NG　·　来源 smartcockpit.com

107.Selecting an engine driven hydraulic pump switch to OFF will:

  1. Electrically close the fluid supply valve at the reservoir.
  2. De-activate the solenoid-held blocking valve and isolate fluid from the using unit.
  3. Activate the solenoid-held blocking valve and isolate fluid from the using unit. ✓
正确答案：Activate the solenoid-held blocking valve and isolate fluid from the using unit.　·　NG　·　来源 smartcockpit.com

108.The 737NG/MAX 'B' system reservoir has:

  1. One standpipe. ✓
  2. Two standpipes.
  3. One standpipe used for reservoir pressurisation of the standby reservoir.
正确答案：One standpipe.　·　NG　·　来源 smartcockpit.com

109.The Standby hydraulic fluid:

  1. Is cooled by a heat exchanger located in NO. 2 tank.
  2. Is cooled by a heat exchanger located in NO. 1 tank.
  3. Is not cooled. ✓
正确答案：Is not cooled.　·　NG　·　来源 smartcockpit.com

110.Complete loss of system 'B' pressure will deactivate:

  1. The outboard flight spoilers. ✓
  2. The inboard flight spoilers.
  3. The ground spoilers.
正确答案：The outboard flight spoilers.　·　NG　·　来源 smartcockpit.com

111.The normal and maximum readings on the hydraulic system pressure indicator are:

  1. 2500 to 3200psi.
  2. 3000 to 3500psi. ✓
  3. 3000 to 3750psi.
正确答案：3000 to 3500psi.　·　NG　·　来源 smartcockpit.com

112.Using the Standby Hydraulic power for thrust reverser deployment will cause:

  1. Deployment time not to be affected.
  2. Deployment time to increase. ✓
  3. Deployment time to decrease.
正确答案：Deployment time to increase.　·　NG　·　来源 smartcockpit.com

113.The maximum hydraulic system A or B pressure is:

  1. 3000 psi.
  2. 3250 psi.
  3. 3500 psi. ✓
正确答案：3500 psi.　·　NG　·　来源 smartcockpit.com

114.Low fluid quantity in the A system reservoir can be indicated by one of the following:

  1. Mechanical indication on the reservoir. ✓
  2. LOW QUANTITY light on the centre instrument panel.
  3. LOW QUANTITY light on the centre instrument panel along with a Master Caution ENG annunciator light.
正确答案：Mechanical indication on the reservoir.　·　NG　·　来源 smartcockpit.com

115.Which hydraulic system operates the parking brake?

  1. Hydraulic system A
  2. Brake accumulator
  3. Hydraulic system B
  4. All options are correct ✓
正确答案：All options are correct　·　NG　·　来源 Chair Flight B737 Question Bank

116.The engine hydraulic pump (ENG 1 and ENG 2) switches are switch ON:

  1. They de-energize the blocking valve to allow pump pressure to enter the system. The switches should remain ON at shutdown to prolong solenoid life. ✓
  2. They de-energize the blocking valve to allow pump pressure to enter the system. The switches should remain OFF at shutdown to prolong solenoid life.
  3. They energize the blocking valve to allow pump pressure to enter the system. The switches should remain OFF at shutdown to prolong solenoid life.
  4. They energize the blocking valve to allow pump pressure to enter the system. The switches should remain ON at shutdown to prolong solenoid life.
正确答案：They de-energize the blocking valve to allow pump pressure to enter the system. The switches should remain ON at shutdown to prolong solenoid life.　·　NG　·　来源 Chair Flight B737 Question Bank

117.Hydraulic System A powers which hydraulic system components?

  1. Landing gear, normal nose wheel steering and the power transfer unit (PTU) ✓
  2. Ground spoilers, normal nose wheel steering and the Landing Gear Transfer Unit
  3. Ground spoilers, trailing edge flaps and the power transfer unit (PTU)
  4. Alternate nose wheel steering, Alternate brakes and ground spoilers
正确答案：Landing gear, normal nose wheel steering and the power transfer unit (PTU)　·　NG　·　来源 Chair Flight B737 Question Bank

118.Which statement is true regarding thrust reverser operation with a failure of hydraulic System A?

  1. The No.1 thrust reverser will automatically operate using the Standby System.
  2. The No.1 thrust reverser will operate normally from System B via the PTU.
  3. The No.1 thrust reverser will operate using the Standby System if the Standby System has been manually or automatically activated. ✓
  4. The No.1 thrust reverser will be inoperative.
正确答案：The No.1 thrust reverser will operate using the Standby System if the Standby System has been manually or automatically activated.　·　NG　·　来源 Chair Flight B737 Question Bank

119.If a leak develops in the hydraulic System A reservoir, which associated pump(s) will have hydraulic fluid available from below the standpipe?

  1. Both the the engine driven pump (EDP) and the AC electric motor-driven pump
  2. Neither pump
  3. The AC electric motor-driven pump ✓
  4. The engine driven pump
正确答案：The AC electric motor-driven pump　·　NG　·　来源 Chair Flight B737 Question Bank

120.What is the maximum hydraulic system pressure.

  1. 4,500 psi
  2. 3,500 psi ✓
  3. 3,000 psi
  4. 4,000 psi
正确答案：3,500 psi　·　NG　·　来源 Chair Flight B737 Question Bank

121.The purpose of the Power Transfer Unit (PTU) is to supply system A with the volume of hydraulic fluid from system B to raise the landing gear at the normal rate when system A Engine Driven Pump volume is lost.

  1. True
  2. False ✓
正确答案：False　·　NG　·　来源 Chair Flight B737 Question Bank

122.Which systems are powered by the hydraulic system?

  1. Flight controls, autothrottles, wheel brakes, leading and trailing edge flaps, leading edge slats, nose wheel steering, landing gear, thrust reversers.
  2. Yaw damper, autopilot and autothrottle, flight controls, brakes, landing gear, trailing edge flaps and slats, nose wheel steering, tiller, power transfer unit, landing gear transfer unit.
  3. Flight controls, Anti-skid, trailing edge flaps and slats, nose wheel steering, landing gear, thrust reversers, autopilots.
  4. Flight controls, wheel brakes, leading and trailing edge flaps, leading edge slats, nose wheel steering, landing gear, thrust reversers, autopilots. ✓
正确答案：Flight controls, wheel brakes, leading and trailing edge flaps, leading edge slats, nose wheel steering, landing gear, thrust reversers, autopilots.　·　NG　·　来源 Chair Flight B737 Question Bank

123.If hydraulic system A develops a leak the engine driven pump (EDP) in system A is starved of oil before the electrical motor driven pump. If system B develops a leak, the electrical motor driven pump in system B is the first to be starved of oil?

  1. True
  2. False ✓
正确答案：False　·　NG　·　来源 Chair Flight B737 Question Bank

124.The electric motor driven hydraulic pumps are cooled and lubricated by hydraulic oil passing through them - this oil is then cooled by passing through a fuel cooled oil cooler located in each main tank. What quantity of fuel must there be in each main tank to operate the electric driven pumps on the ground?

  1. 726 kg
  2. 363 kg
  3. 760 kg ✓
  4. 453 kg
正确答案：760 kg　·　NG　·　来源 Chair Flight B737 Question Bank

125.How is hydraulic oil pressure stopped from entering the system when the Engine Driven Pumps (EDPs) are switched to OFF?

  1. A blocking valve in the pump is energised allowing it to close and stop pressure entering the system. ✓
  2. A blocking valve in the pump is de-energised allowing it to close and stop pressure entering the system.
  3. The EDPs are mechanically disengaged from the engine external gearbox by means of a Sprag clutch.
  4. The EDPs are mechanically disengaged from the engine external gearbox by means of a electronic clutch.
正确答案：A blocking valve in the pump is energised allowing it to close and stop pressure entering the system.　·　NG　·　来源 Chair Flight B737 Question Bank

126.What is the effect on the Standby Hydraulic System, if there is a leak in system B?

  1. No effect as the standby system is supplied from system A.
  2. The standby system will decrease but only a limited amount due to the standpipe in system B reservoir.
  3. No effect as the standby system has its own accumulator. ✓
  4. The level in the standby system will also decrease as it is linked to system B.
正确答案：No effect as the standby system has its own accumulator.　·　NG　·　来源 Chair Flight B737 Question Bank

127.While airborne and with flaps retracted, if hydraulic System A or System B loose pressure does the Standby hydraulic system automatically activate?

  1. Yes, but only if both System A and System B loose pressure.
  2. No, automatic activation only occurs if either System A or System B loose pressure and flaps are extended. ✓
  3. No, automatic activation only occurs if both System A and System B loose pressure and flaps are extended.
  4. Yes, failure of either System A or System B will cause automatic activation of the Standby hydraulic system.
正确答案：No, automatic activation only occurs if either System A or System B loose pressure and flaps are extended.　·　NG　·　来源 Chair Flight B737 Question Bank

128.What effect will a leak in system B downstream of the EDP have on the Power Transfer Unit (PTU)?

  1. It will function as normal as it is part of the standby system and powered by system A oil pressure.
  2. A leak in system B has no effect as the PTU only uses oil from system A to operate.
  3. It will cease to function as it requires oil from system B to operate.
  4. It will continue to function if required due to oil in the system B reservoir below the standpipe level. ✓
正确答案：It will continue to function if required due to oil in the system B reservoir below the standpipe level.　·　NG　·　来源 Chair Flight B737 Question Bank

129.The Power Transfer Unit (PTU) supplies pressure to which flight controls if the System B Engine Driven Pump (EDP) pressure drops below limits?

  1. Trailing Edge (TE) flaps and Leading Edge (LE) flaps
  2. Trailing Edge (TE) flaps
  3. The Autoslat system and all leading edge devices ✓
  4. The landing gear
正确答案：The Autoslat system and all leading edge devices　·　NG　·　来源 Chair Flight B737 Question Bank

130.Which statement is true regarding Hydraulic System A failure? The Standby hydraulic system, powered by a single electric-motor driven pump, has been manually activated.

  1. Ground spoiler are inoperative, increasing landing distance. Half of the flight spoilers on each wing are inoperative, reducing roll rate. Engine 1 thrust reverser will deploy and retract at a slower rate and some asymmetry can be anticipated during thrust reverser deployment. ✓
  2. Ground spoiler are inoperative, increasing landing distance. Half of the flight spoilers on each wing are inop, reducing roll rate. Both thrust reversers are powered by the Standby system to avoid asymmetry during thrust reverser deployment.
  3. Ground spoiler are inoperative, increasing landing distance. Half of the flight spoilers on each wing are powered by the Standby hydraulic system. Engine 1 thrust reverser will deploy and retract at a slower rate and some asymmetry can be anticipated during thrust reverser deployment.
  4. Ground spoilers are powered by the Standby system and are operative. Half of the flight spoilers on each wing are inoperative, reducing roll rate. Engine 1 thrust reverser will deploy and retract at a slower rate and some asymmetry can be anticipated during thrust reverser deployment.
正确答案：Ground spoiler are inoperative, increasing landing distance. Half of the flight spoilers on each wing are inoperative, reducing roll rate. Engine 1 thrust reverser will deploy and retract at a slower rate and some asymmetry can be anticipated during thrust reverser deployment.　·　NG　·　来源 Chair Flight B737 Question Bank

131.The hydraulic system quantity is displayed on the upper DU by digital indication from 0 to 106%.

  1. True
  2. False ✓
正确答案：False　·　NG　·　来源 Chair Flight B737 Question Bank

132.The hydraulic system quantity is displayed on the lower DU by digital indication from 0 to 106%.

  1. True ✓
  2. False
正确答案：True　·　NG　·　来源 Chair Flight B737 Question Bank

133.After the Centre Tank has emptied the auto shutoff logic stops the pumps, how do the pumps then function?

  1. There is no shutoff logic, the pumps continue to run with the amber LOW PRESSURE light illuminated until the Flight Crew switch the pumps to OFF.
  2. Switching the pumps to OFF and then back to ON recycles the auto shutoff logic and the pumps will again activate. ✓
  3. The pumps will not funtion again until the Centre tank has been refueled above 453 kg.
  4. The pumps can be activated if necessary by tripping the auto shutoff circuit breaker on Panel P6-1 behind the First Officer.
正确答案：Switching the pumps to OFF and then back to ON recycles the auto shutoff logic and the pumps will again activate.　·　NG　·　来源 Chair Flight B737 Question Bank

134.Where is the fuel temperature sensor located?

  1. In each engine Hydro-Mechanical fuel control unit.
  2. 1 in the inboard rear of each main tank
  3. In each engine supply line adjacent to the Fuel Flow Meter
  4. In the No1 main tank. ✓
正确答案：In the No1 main tank.　·　NG　·　来源 Chair Flight B737 Question Bank

135.If all Temperature Selectors are positioned OFF, the pack controls will cause the packs to produce which fixed temperatures?

  1. Left Pack, 24 degrees Centigrade. Right Pack, 18 degrees Centigrade. ✓
  2. Left Pack, 20 degrees Centigrade. Right Pack, 22 degrees Centigrade.
  3. Left Pack, 18 degrees Centigrade. Right Pack, 24 degrees Centigrade.
  4. Left Pack, 22 degrees Centigrade. Right Pack, 20 degrees Centigrade.
正确答案：Left Pack, 24 degrees Centigrade. Right Pack, 18 degrees Centigrade.　·　NG　·　来源 Chair Flight B737 Question Bank

136.What is the result if all temperature zone selectors are positioned to OFF?

  1. The right pack will produce a fixed temperature of 75 degrees Fahrenheit, and the left pack will produce a fixed temperature of 65 degrees Fahrenheit.
  2. Left pack will produce 24 degrees centigrade and right pack will produce 18 degrees centigrade. ✓
  3. The packs will attempt to maintain an average temperature across all zones.
  4. ----
正确答案：Left pack will produce 24 degrees centigrade and right pack will produce 18 degrees centigrade.　·　NG　·　来源 Chair Flight B737 Question Bank
王牌左座 Ace Left Seat · 公开层程序练习器，非批准训练设备，不计入训练记录 · 返回首页 · 题库总览