Boeing 737NG - Hydraulics - SmartCockpit - Airline training guides, Aviation, Operations, Safety

The maximum hydraulic system A or B pressure is:

3250 psi.

3500 psi.

3000 psi.

Correct! Wrong!

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

System A Standby Rudder PCU.

Standby Rudder PCU

Main Rudder PCU.

System B Standby Rudder PCU.

Correct! Wrong!

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.

True.

False.

Correct! Wrong!

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.

False.

True.

Correct! Wrong!

The system A engine-driven pump is powered by the No. 1 engine and the system B engine-driven pump is powered by the No. 2 engine.

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

Electric motor driven pump has overheated or loss of hydraulic fluid.

Hydraulic fluid used to cool and lubricate the corresponding electric motor driven pump has overheated or the pump itself has overheated.

Electric motor driven pump has overheated

Electric motor driven pump has lost power and has therefore overheated

Correct! Wrong!

Selecting an engine driven hydraulic pump switch to OFF will:

Electrically close the fluid supply valve at the reservoir.

De-activate the solenoid-held blocking valve and isolate fluid from the using unit.

Activate the solenoid-held blocking valve and isolate fluid from the using unit.

Correct! Wrong!

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.

False.

True.

Correct! Wrong!

The flight control LOW PRESSURE light, Master Caution light, and the FLT CONT and HYD system annunciator lights also illuminate.

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.

False.

True

Correct! Wrong!

The heat exchanger for system A is located in main fuel tank No. 1 and for system B is in main fuel tank No. 2.

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 _____

60% full.

50% full.

20% full.

30% full.

Correct! Wrong!

System A hydraulic pressure is maintained by the electric motor-driven pump.

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

True.

False.

Correct! Wrong!

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

Approximately 25% full.

Approximately 40% full.

Approximately 50% full.

Approximately 72% full.

Correct! Wrong!

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

Has a quantity of fluid less or equal to 30% of the maximum level.

Has a quantity of fluid less or equal to 20% of the maximum level.

Has a quantity of fluid less or equal to 10% of the maximum level.

Is approximately half empty.

Correct! Wrong!

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

Partial thrust reversers, rudder, leading edge flaps and slats (extend only), standby yaw damper.

Thrust reversers, rudder, leading edge flaps and slats (extend only), standby yaw damper.

Rudder, leading edge flaps and slats (extend only), yaw damper.

Partial thrust reversers, standby rudder, leading edge flaps and slats (extend only), standby yaw damper.

Correct! Wrong!

The standby hydraulic pump only supplies pressure to the:

Standby rudder actuator, leading edge devices and thrust reversers.

Standby rudder and leading edge slats.

Standby rudder, leading edge devices and brakes.

Correct! Wrong!

The standby system LOW PRESSURE light is armed:

Only when the standby pump operation has been selected or automatic standby function is activated.

At all times.

Only when the standby pump operation has been selected or either Spoiler switch has been selected to OFF.

Correct! Wrong!

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 _____

20% full.

40% full.

72% full.

50% full.

Correct! Wrong!

System A hydraulic pressure is maintained by the electric motor-driven pump.

The Standby hydraulic fluid:

Is cooled by a heat exchanger located in NO. 2 tank.

Is cooled by a heat exchanger located in NO. 1 tank.

Is not cooled.

Correct! Wrong!

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

Mechanical indication on the reservoir.

LOW QUANTITY light on the centre instrument panel along with a Master Caution ENG annunciator light.

LOW QUANTITY light on the centre instrument panel.

Correct! Wrong!

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

It activates standby pump, and arms ALTERNATE FLAPS position switch.

It closes trailing edge flap bypass valve, activates standby pump, and arms ALTERNATE FLAPS position switch.

It closes Slats and trailing edge flap bypass valve, and arms ALTERNATE FLAPS position switch.

It arms ALTERNATE FLAPS position switch.

Correct! Wrong!

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

System B contents falling to 40%.

System B contents falling to zero.

System B contents falling to 20%.

Correct! Wrong!

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

Deployment time to decrease.

Deployment time not to be affected.

Deployment time to increase.

Correct! Wrong!

STANDBY HYDRAULIC LOW PRESSURE Light - When illuminated amber:

It indicates pressure of standby pump is below 20% It is armed only when automatic standby function is activated.

It indicates pressure of standby pump is below 20% It is armed only when standby pump operation has been selected.

It indicates output pressure of standby pump is low. It is armed only when standby pump operation has been selected.

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.

Correct! Wrong!

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

One standpipe.

One standpipe used for reservoir pressurisation of the standby reservoir.

Two standpipes.

Correct! Wrong!

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

Brake pressure from the PTU.

Brake pressure from standby hydraulic system.

Brake pressure from hydraulic system B if it is greater than 1000 psi.

Brake pressure from hydraulic system A if it is greater than 1000 psi.

Correct! Wrong!

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.

True.

False.

Correct! Wrong!

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

10 times

6 times

3 times

4 times

Correct! Wrong!

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

None.

Aileron and rudder.

Rudder only.

Correct! Wrong!

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:

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.

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.

System B engine-driven pump hydraulic pressure drops below limits, airborne,

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.

Correct! Wrong!

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

True.

False.

Correct! Wrong!

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

2500 to 3200psi.

3000 to 3750psi.

3000 to 3500psi.

Correct! Wrong!

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

20%.

10%.

Zero.

30%.

Correct! Wrong!

If one FLIGHT CONTROL switch is moved to STBY RUD:

It activates the standby rudder power control unit and deactivates the flight control shutoff valve isolating ailerons, elevators.

It activates standby pump and opens standby rudder shutoff valve to pressurize standby rudder power control unit.

It deactivates the standby rudder power control unit.

It activates the standby rudder power control unit.

Correct! Wrong!

In case of loss of system A:

Autopilot B is not available.

Autoslats are not available.

Nose wheel steering is not available.

Alternate nose wheel steering is not available.

Correct! Wrong!

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

Pressure fluctuations and the blinking of the related LOW PRESSURE lights. The MASTER CAUTION and HYD annunciator lights may also illuminate momentarily.

Pressure fluctuations and the MASTER CAUTION and HYD annunciator lights illumination.

Pressure fluctuations and the illumination of the related LOW PRESSURE lights.

Pressure fluctuations.

Correct! Wrong!

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

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.

Main yaw daper functions are available as long as hydraulic system A is providing normal pressure and the yaw damper switch is ON.

Main yaw damper functions are lost.

Normal yaw damper functions are available as long as hydraulic system A is providing normal pressure and the yaw damper switch is ON.

Correct! Wrong!

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

Select STBY RUD ON.

Start the ELEC pump

Monitor hydraulic System A pressure.

Position the pump switch to OFF.

Correct! Wrong!

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

False.

True.

Correct! Wrong!

A leak in system B does not affect the operation of the standby hydraulic system.

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

If Illuminated amber it indicates low quantity in standby hydraulic reservoir. It is only armed when in flight.

If Illuminated amber it indicates low quantity in standby hydraulic reservoir. It is always armed.

If Illuminated amber it indicates low quantity in standby hydraulic reservoir. It is only armed when on ground.

If Illuminated amber it indicates low quantity in standby hydraulic reservoir.

Correct! Wrong!

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.

True.

False.

Correct! Wrong!

The standby system can be activated manually or automatically.

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.

The autoslats and leading edge flaps and slats at the normal rate

The slats and the landing gear

The slats and flaps

The leading edge flaps and landing gear

Correct! Wrong!

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:

The quantity in the reservoir steadily decreases to 20% and system pressure is minimum.

The quantity in the reservoir steadily decreases to 15% and all system pressure partially lost.

The quantity in the reservoir steadily decreases to zero and all system pressure is lost.

the quantity in the reservoir steadily decreases to zero.

Correct! Wrong!

Complete loss of system 'B' pressure will deactivate:

The outboard flight spoilers.

The inboard flight spoilers.

The ground spoilers.

Correct! Wrong!

The RFF indication is displayed:

Valid only when airplane is on ground, with or without engines running and when quantity is below 76% in either system A or B

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.

Valid only when airplane is on ground and when quantity is below 88% in either system A or B

Automatically when the hydraulic quantity is below 88% in either system A or B.

Correct! Wrong!

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

420 kgs / 900 lbs.

760 kgs / 1700 lbs.

500 kgs / 1100 lbs.

600 kgs / 1300 lbs.

Correct! Wrong!

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

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.

Raising or lowering the landing gear, extending leading edge devices, during severe icing.

The system becomes pressurized after engine start, raising or lowering the landing gear

Raising or lowering the landing gear, extending leading edge devices

Correct! Wrong!

These variations have little effect on systems operation.

Boeing 737NG - Hydraulics

Boeing 737NG – Hydraulics

The maximum hydraulic system A or B pressure is:

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

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.

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.

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

Selecting an engine driven hydraulic pump switch to OFF will:

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.

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.

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 _____

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

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

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

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

The standby hydraulic pump only supplies pressure to the:

The standby system LOW PRESSURE light is armed:

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 _____

The Standby hydraulic fluid:

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

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

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

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

STANDBY HYDRAULIC LOW PRESSURE Light - When illuminated amber:

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

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

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.

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

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

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:

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

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

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

If one FLIGHT CONTROL switch is moved to STBY RUD:

In case of loss of system A:

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

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

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

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

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

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.

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.

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:

Complete loss of system 'B' pressure will deactivate:

The RFF indication is displayed:

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

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