The center hydraulic system has an isolation function which:
A. Ensures the pilots can lower the landing gear.
B. Allows nose gear steering to be operational for landing, rollout and taxi.
C. Ensures hydraulic operation of the flap and slats.
D. A and B are correct.
D. A and B are correct.
Normal brakes are powered:
A. Hydraulically by the right system.
B. Hydraulically by the center system.
C. Electrically.
D. By the PMGs.
C. Electrically.
The 28 VDC bus system is the primary power source and the main battery provides the backup power source.
The Center Demand pump operates:
A. On the ground for the first three minutes after the second engine is started.
B. During takeoff roll and gear retraction.
C. When flaps and slats are in motion.
D. All the above.
D. All the above.
The center demand pump operates under any of the following conditions:
System low pressure.
On the ground for the first 3 minutes after the second engine is started.
From takeoff thrust set until radio altitude exceeds 2000 feet.
Flaps or slats in motion.
During descent from when the gear handle is down and radio altitude is less than 2000 feet until groundspeed is less than 60 knots.
The left hydraulic system powers which systems?
A. Alternate & Reserve brake system.
B. Flaps and Slats.
C. Some flight controls and left engine thrust reverser.
D. Stabilizer Trim.
C. Some flight controls and left engine thrust reverser.
The left hydraulic system powers:
Flight controls
The left engine thrust reverser
Right and left wing spoilers
One hydraulic system provides adequate airplane control.
A. True.
B. False.
A. True.
With the left or right hydraulic demand pump selectors in the AUTO position, which of the following is true?
A. Pumps operate from takeoff thrust set to flaps retracted.
B. Pumps operate for three minutes after second engine is started.
C. Pumps operate during thrust reverser operation.
D. All the above.
D. All the above.
In the AUTO position, the L and R demand pumps operate under any of the following conditions:
System low pressure.
On the ground for the first 3 minutes after the second engine is started.
From takeoff thrust set to flaps retracted.
During descent from when the gear handle is down or radio altitude is less than 1000 feet until groundspeed is less than 40 knots.
Thrust reverser operation.
Which hydraulic pump(s) may be shed to allow the electrical system to provide power to other systems?
A. Center Demand Pump.
B. Left Demand Pump.
C. Right Demand Pump.
D. All of the above.
D. All of the above.
The hydraulic isolation system ensures:
A. Stabilizer trim operation.
B. Pressure to the Reserve Brakes.
C. Landing gear can be lowered and nose wheel steering operates.
D. Pressure to the Normal Brakes.
C. Landing gear can be lowered and nose wheel steering operates.
Which of the following will cause the RAT to deploy automatically in flight?
A. Loss of two electric motor pumps (EMP).
B. Loss of electrical power to the FOs flight instrument bus.
C. Loss of any two engine starter generators.
D. Left, Center, and Right Hydraulic pressure low.
D. Left, Center, and Right Hydraulic pressure low.
Inflight, the RAT deploys automatically if any of the following occur:
Both engines have failed.
All three hydraulic system pressures are low.
Loss of all electrical power to Captain’s and First Officer’s flight instruments.
Loss of all four EMPs and faults in the flight control system occur on approach.
Loss of all four EMPs and an engine fail on takeoff or landing.
What component(s) does the RAT hydraulically power?
A. Alternate gear extension system.
B. Normal brakes (after landing and airspeed below 60 knots).
C. Primary flight control components normally powered by the center hydraulic system.
D. Flaps and Slats.
C. Primary flight control components normally powered by the center hydraulic system.
All 3 hydraulic systems will provide up to 4000 psi per system: L, C, R.?
A. True.
B. False.
B. False.
The airplane has three independent 5000 psi hydraulic systems: L, C, R.
What happens if both the C1 and C2 Pump selectors are positioned to ON at the same time?
A. Both pumps will run continuously.
B. Only the C2 pump will operate.
C. Only the C1 pump will operate.
D. Both the C1 and C2 pumps will operate only if the gear is extended.
A. Both pumps will run continuously.
Which of the following components are powered by the right hydraulic system?
A. The Ram Air Turbine.
B. Some flight controls.
C. Right engine thrust reverser.
D. Both B and C are correct.
D. Both B and C are correct.
The right hydraulic system powers:
Flight controls.
The right engine thrust reverser.
Right and left wing spoilers.
The Ram Air Turbine (RAT) must be manually deployed?
A. True.
B. False.
B. False.
Inflight, the RAT deploys automatically if any of the following occur: Both engines have failed, All three hydraulic system pressures are low, Loss of all electrical power to Captain’s and First Officer’s flight instruments, Loss of all four EMPs and faults in the flight control system occur on approach, Loss of all four EMPs and an engine fail on takeoff or landing.
The RAT can be deployed manually by pushing the RAM AIR TURBINE switch on the hydraulic panel.
The primary hydraulic pump FAULT lights illuminate (amber) when the following occurs:
A. Low primary pump pressure.
B. Excessive primary pump fluid temperature.
C. Pump Selector to OFF.
D. All the above.
D. All the above.
In the AUTO position, the right hydraulic system demand pump:
A. Operates from takeoff thrust set to flaps retracted.
B. Operates when system, or primary pump pressure is low.
C. Operates with right thrust reverser deployment.
D. All of the above.
D. All of the above.
In the AUTO position, the L and R demand pumps operate under any of the following conditions:
System low pressure.
On the ground for the first 3 minutes after the second engine is started.
From takeoff thrust set to flaps retracted.
During descent from when the gear handle is down or radio altitude is less than1000 feet until groundspeed is less than 40 knots.
Thrust reverser operation.
Where would you find hydraulic quantity indications?
A. Secondary Engine Instruments.
B. Status Display.
C. Hydraulic Synoptic.
D. Both B and C.
D. Both B and C.
Flight control system components are distributed so that any two hydraulic systems can provide adequate airplane controllability.
A. True
B. False
B. False
Any ONE hydraulic system can provide adequate airplane controllability.
The left and right primary pumps are _______ driven by the related _______.
A. Electrically-driven by the related starter/generator.
B. Electrically-driven by the 115 VAC power system.
C. Engine-driven by the related left and right engines.
C. Engine-driven by the related left and right engines.
The ram air turbine (RAT) only provides hydraulic power to the _______ hydraulic system primary flight controls.
A. Left
B. Right
C. Center
C. Center
Once deployed, the RAT can be stowed in flight using center hydraulic system pressure.
A. True
B. False
B. False
The RAT cannot be stowed in flight.
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Airplane General33
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Air Systems43
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Anti-Ice and Rain21
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Autoflight41
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Communications20
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Electrical38
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Engines and APU39
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Fire Protection32
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Flight Controls61
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Flight Management and Navigation41
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Flight Instruments and Displays42
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Fuel26
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Hydraulics21
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Landing Gear20
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Warning Systems27
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Limitations79
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Immediate Action Items8
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ORCA Operations64
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Exterior Inspection25
