Hydraulics Flashcards
The hydraulic systems on the 737 are designated as ____.
a. System 1, System 2, and Alternate
b. main, alternate, and standby
c. System A, System B, and Standby
d. Left, Right, and Alternate
c. System A, System B, and Standby
Normal hydraulic system pressure is ____ psi.
a. 3000
b. 2900
c. 2800
d. 3500
a. 3000
Which of the following components are normally powered by Hydraulic System A?
a. Landing Gear Transfer Unit
b. Nosewheel steering (normal)
c. Yaw Damper
d. All of the above
b. Nosewheel steering (normal)
Which of the following components are normally powered by System B?
a. Alternate brakes
b. Trailing Edge Flaps
c. Landing Gear
d. All of the above
b. Trailing Edge Flaps
If either System A or System B is lost, the remaining system can power ____ with no decrease in airplane controllability.
a. the flaps/slats
b. the landing gear
c. the primary flight controls
d. all of the above
c. the primary flight controls
Turning Engine 1 or Engine 2 Hydraulic Pump Switches OFF ____.
a. disconnects the pump shaft from the engine accessory case
b. blocks fluid input to the pump
c. removes electrical power to the pump
d. blocks pump pressure output to the components
d. blocks pump pressure output to the components
Moving a FLT CONTROL switch to the STBY RUD position ____.
a. activates the Standby Pump
b. arms the ALTERNATE FLAPS Position Switch
c. extinguishes the Flight Control LOW PRESSURE light when the Standby Rudder Shutoff Valve opens
d. accomplishes both 1 and 3 above
d. accomplishes both 1 and 3 above
How are System A and B reservoirs pressurized?
a. Engine-driven pumps
b. Self-pressurizing AC electric pumps
c. Accumulators
d. Bleed air
d. Bleed air
Main Hydraulic System A or B pressure is generated by ____.
a. an AC electric motor-driven pump only
b. an engine-driven pump only
c. a pneumatic pump
d. both an AC electric motor-driven pump and an engine-driven pump
d. both an AC electric motor-driven pump and an engine-driven pump
An engine-driven hydraulic pump supplies approximately _____ times the fluid of an electric motor-driven pump.
a. 10
b. 2
c. 12
d. 6
d. 6
To block hydraulic fluid flow to the engine driven pump, ____.
a. turn the respective Engine Hydraulic Pump Switch to OFF
b. pull the respective engine Fire Handle
c. both A and B above are correct
d. none of the above are correct
b. pull the respective engine Fire Handle
Heat exchangers used for cooling hydraulic fluid are located ____.
a. in Main Fuel Tank #1 for System A
b. in Main Fuel Tank #2 for System B
c. in the center fuel tank for both systems
d. Both A and B are correct
d. Both A and B are correct
With System A fluid level at the top of the standpipe, the reservoir quantity displayed indicates approximately ____ % full.
a. 76
b. 20
c. 50
d. 72
b. 20
With fluid level at the top of the standpipe, fluid remaining in the System B reservoir is sufficient for operation of the ____.
a. landing gear transfer unit
b. Standby Hydraulic System
c. Power Transfer Unit
d. alternate flap extension
c. Power Transfer Unit
The purpose of the Power Transfer Unit (PTU) is to ____.
a. supply hydraulic fluid volume needed to operate autoslats and leading edge flaps and slats
b. operate the landing gear after loss of System A
c. operate the alternate brakes after loss of System B
d. operate the alternate nosewheel steering after loss of System B
a. supply hydraulic fluid volume needed to operate autoslats and leading edge flaps and slats
The Power Transfer Unit (PTU) operates automatically when ____.
a. System B engine-driven pump pressure drops below limits
b. airborne
c. flaps are less than 15 degrees but not up
d. all of the above occur
d. all of the above occur
The Landing Gear Transfer Unit operates when ____.
a. airborne and No. 1 engine RPM drops below a limit value
b. the landing gear lever is positioned UP and a main gear is not up and locked
c. both of the above occur
d. none of the above occur
c. both of the above occur
The automatic operation of the Standby Hydraulic System is initiated when all the following conditions exist:
a. Loss of system A or B pressure, flaps extended, airborne, or wheel speed greater than 60 knots.
b. Loss of system A and B pressure, flaps retracted airborne or wheel speed greater than 50 knots.
c. Loss of system A or B pressure, flaps extended, airborne, or wheel speed greater than 90 knots.
d. Loss of system A and B pressure, flaps retracted airborne, or wheel speed greater than 90 knots.
a. Loss of system A or B pressure, flaps extended, airborne, or wheel speed greater than 60 knots.
The Standby Hydraulic System LOW QUANTITY Light illuminates when the reservoir is ____.
a. empty
b. approximately 3/4 empty
c. approximately 1/4 empty
d. approximately 1/2 empty
d. approximately 1/2 empty
If a leak develops in Hydraulic System A engine-driven pump or its related lines, a ____ in the reservoir prevents a total system fluid loss.
a. standpipe
b. crossfeed valve
c. one-way check valve
d. scavenge pump
a. standpipe
What happens if this light illuminates on takeoff, prior to gear retraction without engine failure?
a. The landing gear should retract at a normal rate.
b. The landing gear should retract at a slower rate since the electric motor-driven pump’s fluid volume is ¼ of the engine-driven pump output.
c. The landing gear should retract normally through the Landing Gear Transfer Unit
d. The landing gear will not retract
b. The landing gear should retract at a slower rate since the electric motor-driven pump’s fluid volume is ¼ of the engine-driven pump output.
If the light is illuminated due to a leak in the #1 (System A) engine-driven pump, then System A quantity will \_\_\_\_ a. Drop to approximately 0%. b. Drop to approximately 20%. c. Show approximately 72%. d. show approximately 76%
b. Drop to approximately 20%.
Both engines are still operating. Turning OFF the #1 Engine Hydraulic Pump Switch
a. will shut off fluid to the pump
b. will deactivate the pump Low Pressure light
c. does not affect the rotation of the pump
d. will stop the pump from rotating
c. does not affect the rotation of the pump
Which of the following statements is true if the LOW PRESSURE light illuminates in flight?
a. There is a leak in Hydraulic System B.
b. It the light is intermittent, then there is a heavy demand on System B.
c. Output pressure of System B electric motor-driven pump is low.
d. Output pressure of System B engine driven pump is low.
d. Output pressure of System B engine driven pump is low
This light illuminates during takeoff, climbing through 1,000 feet AGL, and during flap retraction. Which statement below is most correct?
a. The leading edge devices will retract slowly because of the low volume output of the electric motor-driven pump.
b. The leading edge devices will retract at a normal rate through the PTU.
c. The leading edge devices will not retract.
d. The leading edge devices must be retracted using the Alternate Flap Switches
b. The leading edge devices will retract at a normal rate through the PTU.
How would this condition effect the flap operation prior to landing?
a. The PTU should automatically aid in extending the leading edge devices with the trailing edge flaps less than 15 degrees, but not up.
b. The PTU should aid in extending the leading edge flaps and slats, but the autoslats will be inoperative.
c. The PTU should not aid in extending the leading edge devices.
d. The PTU should automatically aid in extending the trailing edge devices
a. The PTU should automatically aid in extending the leading edge devices with the trailing edge flaps less than 15 degrees, but not up.
With Hydraulic System B quantity near 0, what do these lights indicate?
a. System B is lost with no fluid left in the reservoir.
b. System B is lost with some fluid trapped in the reservoir.
c. System B pressure is normal but the Standby Hydraulic System is lost.
d. System B and the Standby Hydraulic System are lost.
b. System B is lost with some fluid trapped in the reservoir.
When lowering the flaps with this condition, _____
a. the flaps will have to be lowered electrically with the aid of the PTU
b. the trailing edge flaps will be lowered electrically and the leading edge flaps and slats will be extended by the PTU
c. the trailing edge flaps and the leading edge devices will be extended using the Alternate Flap Extension method
d. Landing must be made with the flaps up
c. the trailing edge flaps and the leading edge devices will be extended using the Alternate Flap Extension method
In addition to both lights shown being illuminated, the airplane is airborne, flaps are extended, and the FLT CONTROL B Hydraulic System Switch is ON. Which of the following conditions is also true?
a. The Landing Gear Transfer Unit will operate.
b. Autopilot A will be inoperative.
c. Automatic operation of the Standby Hydraulic System will occur.
d. The Normal Brake System is available.
c. Automatic operation of the Standby Hydraulic System will occur.
With these lights illuminated’ and switches positioned as shown on the Hydraulic Panel, the pressure
in Hydraulic System A should read __ psi.
a. 1500
b. 3000
c. 0
d. 1000
c. 0
____ is/are not available with no pressure in Hydraulic System A.
a. All spoilers
b. The rudder
c. The elevator
d. Half of the flight spoilers and all of the ground spoilers
d. Half of the flight spoilers and all of the ground spoilers
If on descent, how would the landing gear be lowered with this condition?
a. The gear can be lowered using Hydraulic System B through the landing gear transfer unit.
b. The gear can be lowered by the Standby Hydraulic System.
c. The gear will have to be lowered manually.
d. The gear cannot be lowered
c. The gear will have to be lowered manually
In flight, what conditions could cause these two lights to illuminate?
a. The fluid used to cool and lubricate the Hydraulic System B electric-motor driven pump has overheated, or the pump itself has overheated.
b. The Hydraulic System B electric motor driven pump has overheated, but the fluid used to cool that pump is still below limits.
c. The fluid used to cool and lubricate the Hydraulic System B engine-driven pump has overheated, but the pump is still operating.
d. An overheat condition has been detected in Hydraulic System A.
a. The fluid used to cool and lubricate the Hydraulic System B electric-motor driven pump has overheated, or the pump itself has overheated.
When the overheat was detected in Hydraulic System B, what happens to the corresponding electric
motor driven pump?
a. The pump continues to operate with normal pressure.
b. The pump continues to operate at a reduced pressure.
c. The pump shuts off automatically.
d. The pump will eventually destruct if not shut down by the crew manually
c. The pump shuts off automatically
The QRH directs the crew to switch the Hydraulic System B electric motor driven pump OFF. How will this affect the operation of the Power Transfer Unit (PTU)?
a. While in flight, the PTU assists in the operation of the autoslats and leading edge flaps and slats at a reduced rate.
b. The PTU would automatically operate with flaps less than 15 but not up.
c. The PTU would automatically operate if you are airborne.
d. System B electric motor driven pump pressure does not determine operation of the PTU.
d. System B electric motor driven pump pressure does not determine operation of the PTU.
These four lights are illuminated at the same time. Choose the answer below that most accurately describes which hydraulic system(s) is/are lost?
a. Hydraulic System A only
b. Hydraulic System B only
c. Standby Hydraulic System only
d. Both Hydraulic System A and Hydraulic System B
d. Both Hydraulic System A and Hydraulic System B
Hydraulic Systems A and B are unavailable. How does this affect the Brake System?
a. Braking is not available
b. Braking is available via trapped hydraulic pressure in the brake accumulator.
c. Braking is available via the Normal Brake System pressure.
d. Braking is available via the Alternate Brake System pressure.
b. Braking is available via trapped hydraulic pressure in the brake accumulator
With the same conditions, which primary flight control(s) will still be pressurized?
a. The rudder using the Standby Hydraulic System.
b. The elevators using the Standby Hydraulic System.
c. The ailerons using the Standby Hydraulic System.
d. The rudder, elevators and ailerons using the Standby Hydraulic System.
a. The rudder using the Standby Hydraulic System
The crew suspects a leak in Hydraulic Systems B as indicated. How would the trailing edge (TE) flaps be extended in flight under these conditions?
a. The TE flaps can be extended normally via the Standby Hydraulic System.
b. The TE flaps can be extended hydraulically from System A via the ALTERNATE FLAPS Position Switch
c. The TE flaps cannot be extended when Hydraulic System B is lost.
d. The TE flaps can be extended electrically via the ALTERNATE FLAP Position Switch.
d. The TE flaps can be extended electrically via the ALTERNATE FLAP Position Switch.
After a few minutes, the crew notices that both Hydraulic Systems A and B are now unavailable as shown. How can the landing gear be extended prior to landing?
a. Only by using manual landing gear extension.
b. Normally via the Standby Hydraulic System.
c. Automatically via the Landing Gear Transfer Unit
d. The landing gear cannot be extended, and the QRH directs the crew to apply the Gear up Landing Procedure
a. Only by using manual landing gear extension.
Both Hydraulic Systems A and B are still unavailable after landing. Select the answer which best describes the operation of the nose wheel steering in this condition.
a. It does not work without pressure from Hydraulic Systems A or B.
b. It will work using the Alternate Nose Wheel Steering selection.
c. It will work via the Nose Wheel Steering accumulator.
d. It will work via the Landing Gear Transfer Unit but with limited displacement in either direction
a. It does not work without pressure from Hydraulic Systems A or B.
If the standby hydraulic low quantity light is illuminated, ______.
a. at least half of the standby fluid has been depleted
b. the B system has decreased to the 50% level
c. the PTU has lost hydraulic fluid
d. this light only arms with the standby pump operating and indicates normal operation
a. at least half of the standby fluid has been depleted
This light is armed ______.
a. only when the standby pump is running
b. only when system B is pressurized
c. any time there is power on the aircraft
d. only when the engines are running
c. any time there is power on the aircraft
With this light illuminated, Hydraulic System B quantity should read __ %.
a. 20
b. 76
b. 0
c. 72
c. 72
System A low pressure light is illuminated on the overhead panel. With this light on, how can the gear be extended?
a. Use the manual gear extension procedures.
b. Gear cannot be extended.
c. Normal gear extension
d. The landing gear transfer unit will deploy the gear when normally extended
c. Normal gear extension
With the A hydraulic system engine driven pump low pressure light on and indicating volume in the A
reservoir.
a. you must lower the landing gear manually
b. you cannot retract the gear
c. gear will retract at a slower rate
d. only two spoilers on each wing work normally
c. gear will retract at a slower rate
With this light on during gear retraction, the landing gear transfer unit will activate with ______.
a. Low RPM on the #2 engine.
b. loss of Hydraulic System B
c. the loss of System A electric pump
d. low RPM on the #1 Engine
d. low RPM on the #1 Engine
