Hydraulics

The hydraulic system engine pump switch controls ?
1. an electrically operated pump valve.
2. a solenoid activated blocking valve.
3. an electrically operated hydraulic valve.
4. an electrically operated pump valve opened by hydraulic pressure.
Under what condition is the engine hydraulic pump LOW PRESSURE warning light disarmed ?
1. When the related engine fire switch is pulled.
2. When the related engine pump switch is OFF.
3. When the related hydraulic reservoir is empty.
What condition(s) would cause the electric hydraulic pump OVERHEAT light to illuminate ?
1. The pump has overheated or the hydraulic fluid used to cool and lubricate the pump has overheated.
2. The hydraulic fluid being used by the pump from the respective reservoir has overheated.
3. The pump motor has overheated.
4. The hydraulic fluid cooler has failed.
How is the fluid used to cool and lubricate the electric hydraulic pump cooled ?
1. A heat exchanger located in the respective main fuel tank.
2. A heat exchanger located in the respective hydraulic reservoir.
3. A heat exchanger located in the number 1 main fuel tank.
4. A heat exchanger located in the standby hydraulic reservoir.
If a leak develops in the System A reservoir which associated pump(s) will have hydraulic fluid available from below the standpipe ?
1. The electric hydraulic pump.
2. The engine driven hydraulic pump.
3. Both the engine driven and electric hydraulic pump.
4. Neither pump will have hydraulic fluid available.
If a leak develops in the System B reservoir which associated pump(s) will have hydraulic fluid available from below the standpipe ?
1. The electric hydraulic pump.
2. The engine driven hydraulic pump.
3. Both the engine driven and electric hydraulic pump.
4. Neither pump will have hydraulic fluid available.
The Power Transfer Unit (PTU) powers which flight controls if hydraulic fluid is lost to the system B engine driven hydraulic pump ?
1. The trailing edge flaps.
2. The Autoslat system and leading edge flaps and slats.
3. The ailerons and elevator.
4. The trailing edge flaps and leading edge slats and flaps.
What is the source of fluid for operation of the Power Transfer Unit (PTU) if System B fluid is lost ?
1. System A
2. System B
3. Standby System
What is the source of fluid for the Power Transfer Unit (PTU) using systems if System B fluid is lost ?
1. System B
2. System A
3. Standby System
Which three conditions must exist before the PTU (Power Transfer Unit) will operate ?
1. System B pump pressure below limits.
  Airborne.
  Flaps less than 15 but not up.
2. System A pump pressure below limits.
  Airborne.
  Flaps less than 15 but not up.
3. System A pump pressure below limits.
  Airborne.
  Flaps less than 5 but not up.
4. System B pump pressure below limits.
  Airborne.
  Flaps less than 5 but not up.
Which statement is true regarding thrust reverser operation with a System A or B failure ?
1. The respective thrust reverser is inoperative.
2. The respective thrust reverser will operate normally from the operative hydraulic system. .
3. The respective thrust reverser will automatically operate using the Standby hydraulic system.
4. The respective thrust reverser will operate using the Standby hydraulic system if the Standby system has been manually or automatically activated.
Manual activation of the Standby hydraulic system may be accomplished by ?
1. Placing the Alternate Flaps switch to ARM and positioning both FLT CONTROL switches to SBY RUD.
2. Placing the Alternate Flaps switch to ARM or positioning both FLT CONTROL switches to SBY RUD.
3. Placing the Alternate Flaps switch to ARM and positioning either FLT CONTROL switch to SBY RUD.
4. Placing the Alternate Flaps switch to ARM or positioning either FLT CONTROL switch to SBY RUD.
Will the Standby hydraulic system automatically activate with a loss of System A or B pressure during take-off ?
1. No, the aircraft must be airborne.
2. Yes, if wheel speed is greater than 60 knots.
3. Only if both System A and B fail.
If either or both System A and System B loose pressure while airborne with flaps up, does the Standby hydraulic system automatically activate ?
1. Yes, if both System A and System B loose pressure.
2. No, automatic activation occurs only if the flaps are extended with a loss of pressure in System A or B.
3. Yes, failure of either System A or System B will cause automatic activation of the Standby system regardless of flap position.
Which primary flight control(s) will operate using standby hydraulic pressure if both System A and System B fail ?
1. The rudder.
2. The elevator.
3. The rudder and ailerons.
4. All primary flight controls.
The Landing Gear Transfer Unit will operate under what conditions ?
1. Anytime that the landing gear is retracted during a loss of pump volume in both hydraulic systems.
2. Anytime that the landing gear is retracted during a loss of pump volume in System A.
3. Anytime that the landing gear is retracted during a loss of pump volume in System B.
4. When retracting the landing gear using the Standby system.
A loss of power in which engine(s) will use the Landing Gear Transfer Unit to raise the landing gear at a normal rate ?
1. Number 1 engine.
2. Number 2 engine.
3. Either number 1 or number 2 engine.
How many Flight Spoilers will operate on each wing if either System A or System B fails ?
1. Two on each wing.
2. Four on each wing.
3. The Flight Spoilers are inoperative with a loss of System A or System B.
4. One on each wing.
Will Ground Spoilers be available with a loss of System A ?
1. No.
2. Yes.
3. One Ground Spoiler is available on each wing.
Which hydraulic system provides pressure for normal brakes ?
1. System A.
2. System B.
Which hydraulic system provides pressure for alternate brakes ?
1. System A.
2. System B.
The respective Autopilot will operate normally if either System A or System B is lost.
1. False
2. True
Which hydraulic system powers normal nosewheel steering ?
1. System A.
2. System B.
How is landing gear extension affected by loss of System A or System B.
1. The gear extends normally with a loss of either system.
2. Manual landing gear extension is required with a loss of System A.
3. Manual landing gear extension is required with a loss of System B.
May the landing gear be retracted if both System A and System B have failed ?
1. No
2. Yes
What is the crew's indication that a hydraulic reservoir must be serviced ?
1. The RF annunciation next to the fluid quantity on the HYDRAULIC indicator.
2. Low pressure on the hydraulic pressure indicator.
3. A low quantity indication on the respective hydraulic reservoir in the wheel well.
How may the crew determine that the Standby reservoir has sufficient hydraulic fluid ?
1. The RF annunciation next to the fluid quantity on the HYDRAULIC indicator.
2. A low quantity indication on the Standby hydraulic reservoir in the wheel well.
3. The LOW QUANTITY warning light on the Flight Control panel will illuminate.
How is the Standby reservoir pressurized ?
1. By the bleed air system through the System A reservoir.
2. By the bleed air system through the System B reservoir.
3. Directly by the bleed air system.

Hydraulic System