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

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 10% of the maximum level.

Is approximately half empty.

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

Correct! Wrong!

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

LOW QUANTITY light on the centre instrument panel.

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

Mechanical indication on the reservoir.

Correct! Wrong!

The Standby hydraulic fluid:

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

Is not cooled.

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

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!

Complete loss of system 'B' pressure will deactivate:

The inboard flight spoilers.

The ground spoilers.

The outboard flight spoilers.

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 40% full.

Approximately 25% full.

Approximately 72% full.

Approximately 50% full.

Correct! Wrong!

In case of loss of system A:

Autoslats are not available.

Nose wheel steering is not available.

Alternate nose wheel steering is not available.

Autopilot B is not available.

Correct! Wrong!

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

Raising or lowering the landing gear, extending leading edge devices

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.

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

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

Correct! Wrong!

These variations have little effect on systems operation.

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

30%.

20%.

10%.

Zero.

Correct! Wrong!

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

Brake pressure from standby hydraulic system.

Brake pressure from the PTU.

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!

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 zero.

System B contents falling to 40%.

System B contents falling to 20%.

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.

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

6 times

3 times

4 times

10 times

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:

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

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.

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.

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.

Correct! Wrong!

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

Main yaw damper functions are lost.

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

Normal yaw damper 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 available if the FLT CTL B switch is placed to STBY RUD and the yaw damper switch is reset to ON.

Correct! Wrong!

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

Deployment time to increase.

Deployment time to decrease.

Deployment time not to be affected.

Correct! Wrong!

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 slats and flaps

The leading edge flaps and landing gear

The slats and the landing gear

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

Correct! Wrong!

The maximum hydraulic system A or B pressure is:

3250 psi.

3000 psi.

3500 psi.

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 _____

50% full.

40% full.

72% full.

20% full.

Correct! Wrong!

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

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

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 in flight.

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

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

Correct! Wrong!

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

Pressure fluctuations.

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

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

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

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.

False.

True.

Correct! Wrong!

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

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

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

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.

Correct! Wrong!

Selecting an engine driven hydraulic pump switch to OFF will:

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

Electrically close the fluid supply valve at the reservoir.

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

Correct! Wrong!

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

Main Rudder PCU.

Standby Rudder PCU

System B Standby Rudder PCU.

System A Standby Rudder PCU.

Correct! Wrong!

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

One standpipe.

Two standpipes.

One standpipe used for reservoir pressurisation of the standby reservoir.

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

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

Valid only when airplane is on ground and when quantity is below 88% 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.

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.

False.

True.

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.

False.

True.

Correct! Wrong!

The standby system can be activated manually or automatically.

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.

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.

True

False.

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.

STANDBY HYDRAULIC LOW PRESSURE Light - When illuminated amber:

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.

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.

Correct! Wrong!

The standby hydraulic pump only supplies pressure to the:

Standby rudder and leading edge slats.

Standby rudder actuator, leading edge devices and thrust reversers.

Standby rudder, leading edge devices and brakes.

Correct! Wrong!

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

False.

True.

Correct! Wrong!

The standby system LOW PRESSURE light is armed:

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

At all times.

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

Correct! Wrong!

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 lost power and has therefore overheated

Electric motor driven pump has overheated

Correct! Wrong!

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

Rudder only.

None.

Aileron and rudder.

Correct! Wrong!

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

True.

False.

Correct! Wrong!

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

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

500 kgs / 1100 lbs.

760 kgs / 1700 lbs.

420 kgs / 900 lbs.

600 kgs / 1300 lbs.

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 zero and all system pressure is lost.

the quantity in the reservoir steadily decreases to zero.

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.

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 _____

30% full.

50% full.

20% full.

60% full.

Correct! Wrong!

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

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

Monitor hydraulic System A pressure.

Position the pump switch to OFF.

Select STBY RUD ON.

Start the ELEC pump

Correct! Wrong!

If one FLIGHT CONTROL switch is moved to STBY RUD:

It activates the standby rudder power control unit.

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

It deactivates the standby rudder power control unit.

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

Correct! Wrong!

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

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

It arms ALTERNATE FLAPS position switch.

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

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

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!

Boeing 737NG - Hydraulics

Boeing 737NG – Hydraulics

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

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

The Standby hydraulic fluid:

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.

Complete loss of system 'B' pressure will deactivate:

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

In case of loss of system A:

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

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

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

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

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.

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

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:

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

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

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 maximum hydraulic system A or B pressure is:

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 _____

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

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

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.

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

Selecting an engine driven hydraulic pump switch to OFF will:

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

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

The RFF indication is displayed:

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

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.

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.

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.

STANDBY HYDRAULIC LOW PRESSURE Light - When illuminated amber:

The standby hydraulic pump only supplies pressure to the:

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

The standby system LOW PRESSURE light is armed:

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

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

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

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

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:

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

If one FLIGHT CONTROL switch is moved to STBY RUD:

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

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