# A 320 Sys Hydraulic , And Ice / Rain , Landing Gear.

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Questions: 40 | Attempts: 87

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• 1.

### The A 320´s three hydraulic systems are normally pressurized by :

• A.

Two engine driven pumps and one electric pump.

• B.

Two electric pumps and one PTU.

• C.

Two electric pumps and one engine driven pump.

A. Two engine driven pumps and one electric pump.
Explanation
The A320's three hydraulic systems are typically pressurized by two engine driven pumps and one electric pump. This configuration ensures redundancy and reliability in the event of an engine failure or other system malfunction. The engine driven pumps are powered directly by the aircraft's engines, providing hydraulic pressure during normal operations. The electric pump serves as a backup, capable of pressurizing the hydraulic systems in case of engine failure or when additional pressure is needed. This combination of pumps ensures that the aircraft's hydraulic systems remain operational and functional in various scenarios.

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• 2.

### The hydraulic PTU will active if :

• A.

A significant pressure loss occurs in any of the tree hydraulics systems.

• B.

A significant pressure loss occurs in the green or yellow hydraulic system.

• C.

Both A and B are correct.

B. A significant pressure loss occurs in the green or yellow hydraulic system.
Explanation
The correct answer is that the hydraulic PTU will activate if a significant pressure loss occurs in the green or yellow hydraulic system. This means that if there is a drop in pressure in either the green or yellow hydraulic system, the PTU will automatically activate to provide backup hydraulic power. This is important because a loss of hydraulic pressure can result in a loss of control of the aircraft, so the PTU serves as a safety measure to ensure that hydraulic power is still available in case of a pressure loss in these systems.

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• 3.

### Describes the PTU status with a green system reservoir overheat ,low pressure or low fluid level .

• A.

The PTU will be inhibited.

• B.

The crew must select the PTU ON .

• C.

The PTU  fault light will remain illuminated as long as the problem exists. The PTU should be selected OFF.

C. The PTU  fault light will remain illuminated as long as the problem exists. The PTU should be selected OFF.
Explanation
The correct answer states that the PTU fault light will remain illuminated as long as the problem exists and that the PTU should be selected OFF. This means that when there is an issue with the PTU status, indicated by a green system reservoir overheat, low pressure, or low fluid level, the PTU will be inhibited and the crew must manually select the PTU ON. However, the fault light will continue to be illuminated until the problem is resolved, and at that point, the PTU should be turned OFF.

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• 4.

### The PTU will self test :

• A.

Numerous times during each flight.

• B.

During the first engine start.

• C.

During the second engine start.

C. During the second engine start.
Explanation
The PTU (Power Transfer Unit) will self-test during the second engine start. This suggests that the self-test process is not initiated during the first engine start, but rather during the subsequent start. The reason for this could be that the self-test is designed to ensure that the PTU is functioning properly after the first engine has been started and is operational. By conducting the self-test during the second engine start, any potential issues with the PTU can be identified and addressed before the aircraft takes off.

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• 5.

### When will normal operation of the BLUE system hydraulic pump begin ?

• A.

During the first engine start.

• B.

When the first engine MASTER switch is moved to the ON position.

• C.

Only when the RAT is deployed.

A. During the first engine start.
Explanation
The correct answer is "During the first engine start." This means that the normal operation of the BLUE system hydraulic pump will begin when the first engine is started. It does not depend on the position of the first engine MASTER switch or the deployment of the RAT (Ram Air Turbine).

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• 6.

### For hydraulic system malfunctions , when will the RAT deploy ?

• A.

Automatically with the failure of both the green and blue hydraulic systems.

• B.

Automatically with the failure of both the green and yellow hydraulic systems.

• C.

Only when the guard RAT MAN ON push button is selected by the crew.

C. Only when the guard RAT MAN ON push button is selected by the crew.
Explanation
The RAT (Ram Air Turbine) will only deploy when the guard RAT MAN ON push button is selected by the crew. This means that the crew has to manually activate the RAT by selecting the RAT MAN ON push button. It will not deploy automatically with the failure of any hydraulic system.

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• 7.

### When will the yellow system electric pump operate ? (AC power is available ).

• A.

When the first engine MASTER switch is moved to the ON position.

• B.

If any N2 RPM is less than 45 %.

• C.

When the yellow electric system ELEC PUMP push button is selected to ON or the ground crew activates a cargo door switch.

C. When the yellow electric system ELEC PUMP push button is selected to ON or the ground crew activates a cargo door switch.
Explanation
The yellow system electric pump will operate when the yellow electric system ELEC PUMP push button is selected to ON or when the ground crew activates a cargo door switch. This means that the pump can be manually turned on by the pilot or it can be activated automatically by the ground crew when a cargo door switch is activated.

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• 8.

### How is the yellow hydraulic system pressurized ?

• A.

An engine driven pump , an electric pump , the PTU using the green system and , for the cargo doors only , a hand pump.

• B.

An engine driven pump , electric pump , the PTU using the blue system and , for the cargo doors only , a hand pump.

• C.

An engine driven pump , an electric pump , and the PTU  using the green system.

A. An engine driven pump , an electric pump , the PTU using the green system and , for the cargo doors only , a hand pump.
Explanation
The yellow hydraulic system is pressurized by an engine driven pump, an electric pump, the PTU using the green system, and a hand pump for the cargo doors.

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• 9.

### The RAT  is capable of powering a pump which will pressurize :

• A.

Only the blue system.

• B.

The blue and green system.

• C.

The blue and yellow system.

A. Only the blue system.
Explanation
The RAT (Ram Air Turbine) is a device that generates power from the airflow during flight. It is capable of powering a pump, which can be used to pressurize a system. In this case, the question states that the RAT can pressurize "only the blue system." This means that the pump powered by the RAT is specifically designed to provide pressure to the blue system and not to any other systems such as the green or yellow system. Therefore, the correct answer is that the RAT can only pressurize the blue system.

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• 10.

### After extending the RAT is it possible to check its position and status ?

• A.

Yes , select the ECAM ELEC page

• B.

NO

• C.

Yes , select the ECAM HYD page .

C. Yes , select the ECAM HYD page .
Explanation
Yes, it is possible to check the position and status of the RAT (Ram Air Turbine) by selecting the ECAM HYD (Hydraulic) page. The ECAM (Electronic Centralized Aircraft Monitor) system provides various pages that display different aircraft systems and their status. The ECAM HYD page specifically shows the hydraulic system, which includes the RAT. By selecting this page, the pilot or maintenance personnel can access information about the RAT's position and status.

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• 11.

### What does a HYD PUMP FAULT light indicate ? 1.Reservoir low level , 2. Reservoir overheat , 3.Reservoir low air pressure , 4. Pump low pressure , 5. PTU is operating.

• A.

5 only.

• B.

1, 3 , 4.

• C.

1 , 2, 3 , 4 .

C. 1 , 2, 3 , 4 .
Explanation
The correct answer is 1, 2, 3, 4. This means that a HYD PUMP FAULT light can indicate multiple issues, including a low reservoir level, reservoir overheat, low air pressure in the reservoir, and low pressure from the pump.

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• 12.

### What does the RAT MAN ON switch do ?

• A.

Extends RAT , pressurizes BLUE  system , starts Emergency Generator .

• B.

Extends RAT , pressurizes BLUE system , does not start Emergency Generator .

• C.

Extends RAT . Must push RAT MAN ON  again to pressurize BLUE system .

B. Extends RAT , pressurizes BLUE system , does not start Emergency Generator .
Explanation
The RAT MAN ON switch extends the RAT (Ram Air Turbine) and pressurizes the BLUE system, but it does not start the Emergency Generator.

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• 13.

### What are the major equipment losses with loss of Green system ?

• A.

Speed Brakes .

• B.

Nosewheel steering , Autobrakes.

• C.

Alternate Brakes.

B. Nosewheel steering , Autobrakes.
Explanation
The major equipment losses with the loss of the Green system are the Nosewheel steering and Autobrakes. This means that without the Green system, the aircraft would lose the ability to steer the nosewheel and the automatic braking system. These equipment losses can significantly impact the maneuverability and control of the aircraft during taxiing and landing operations.

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• 14.

### Window heat operates at what power level while airborne ?

• A.

Low power above 18,000 feet.

• B.

High power while airborne .

• C.

Shifts from low to high as window temperature requires.

B. High power while airborne .
Explanation
The correct answer is "high power while airborne." This means that the window heat operates at a high power level when the aircraft is in the air. It does not specify a specific altitude or temperature threshold for the shift to high power, but it implies that the window heat is designed to operate at a higher power level during flight.

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• 15.

### Window heat operation begins :

• A.

If the PROBE / WINDOW HEAT push button is selected ON by the prior to engine start.

• B.

Automatically after the first engine start.

• C.

Both A and B are correct .

C. Both A and B are correct .
Explanation
The correct answer is that both A and B are correct. This means that the window heat operation can begin either if the PROBE/WINDOW HEAT push button is selected ON before engine start or automatically after the first engine start. Both options are valid and can initiate the window heat operation.

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• 16.

### Anti Ice and De Icing protection is provided for :

• A.

The engine nacelles and three outboard wing slats.

• B.

The engine nacelles three outboard wing slats and the horizontal stabilizer.

• C.

The engine nacelles three outboard slats , horizontal stabilizer and vertical stabilizer .

A. The engine nacelles and three outboard wing slats.
• 17.

### Rain protection is provided by :

• A.

Warm bleed air blowing across the windshield.

• B.

Rain repellent and windshield wipers.

• C.

Both A and B.

B. Rain repellent and windshield wipers.
Explanation
Rain protection is provided by rain repellent and windshield wipers. Rain repellent is a chemical coating applied to the windshield that causes water to bead up and roll off, improving visibility in rainy conditions. Windshield wipers are mechanical devices that move back and forth across the windshield, wiping away water and debris. Both rain repellent and windshield wipers work together to ensure that the windshield remains clear and the driver's visibility is not compromised during rainy weather.

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• 18.

### With the loss of electrical power the wing anti ice valves :

• A.

Fail in their current position.

• B.

Fail to the open position.

• C.

Fail to close position.

C. Fail to close position.
Explanation
When there is a loss of electrical power, the wing anti ice valves are designed to fail in the closed position. This means that in the absence of power, the valves will remain in their current position, which is closed. This is important because the wing anti ice valves are responsible for preventing ice from forming on the wings of an aircraft. By failing to close, the valves ensure that the anti ice system remains operational even in the event of a power failure, thereby preventing ice accumulation and ensuring the safety of the aircraft.

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• 19.

### With the loss of electrical power the engine anti ice valves :

• A.

Fail in their current position.

• B.

Fail to the open position.

• C.

Fail to the close position.

B. Fail to the open position.
Explanation
When there is a loss of electrical power, the engine anti-ice valves fail to the open position. This means that the valves, which are responsible for preventing ice formation on the engine, are unable to close. As a result, they remain open, allowing the flow of hot air to continue and prevent ice from forming on the engine. This is important for the safety and performance of the aircraft, as ice accumulation can disrupt the engine's operation.

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• 20.

### Can the wing anti ice be tested on the ground ?

• A.

No.

• B.

Yes, valves only open for 30 seconds.

• C.

Yes , valves stay open till selected off .

B. Yes, valves only open for 30 seconds.
Explanation
The correct answer is "Yes, valves only open for 30 seconds." This means that the wing anti ice can be tested on the ground, but the valves will only remain open for a limited time of 30 seconds. This allows for a brief test of the system's functionality before takeoff.

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• 21.

### What is the difference between the engine and wing anti ice fault lights ?

• A.

Both indicate valve in transit , or valve position disagrees with selected position .Wing light also could indicate low pressure .

• B.

Both indicate low pressure or valve position disagrees with selected position, Wing light might indicate valve in transit .

• C.

Both indicate valve in transit or low pressure .Wing light also could indicate valve position disagree with selected position.

A. Both indicate valve in transit , or valve position disagrees with selected position .Wing light also could indicate low pressure .
Explanation
The engine and wing anti ice fault lights both indicate that the valve is in transit or that the valve position disagrees with the selected position. Additionally, the wing light could also indicate low pressure.

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• 22.

### If the landing Gear was gravity extended using the hand crank on the center pedestal landing gear position must be verified through the

• A.

Landing gear indications depicted on the ECAM  and if available , the center panel LDG GEAR indicator panel light .

• B.

The landing gear viewers.

• C.

Option 4

A. Landing gear indications depicted on the ECAM  and if available , the center panel LDG GEAR indicator panel light .
Explanation
The correct answer is to verify the landing gear position through the landing gear indications depicted on the ECAM and, if available, the center panel LDG GEAR indicator panel light. This means that the pilot should check the electronic display of the landing gear position on the ECAM system and also look for any indication lights on the center panel that show the status of the landing gear. This is important to ensure that the landing gear is properly extended or retracted before and during the flight.

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• 23.

### Which hydraulic systems supply pressure to the landing gear system ?

• A.

Green

• B.

Blue

• C.

Yellow and Blue .

A. Green
Explanation
The correct answer is Green. In aircraft hydraulic systems, the color coding is used to identify different hydraulic systems. The Green system is responsible for supplying pressure to the landing gear system. It is designed to provide the necessary hydraulic power to extend and retract the landing gear during takeoff and landing.

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• 24.

### Landing gear operation is inhibit at speed :

• A.

Below 100 knots.

• B.

Above 260

• C.

Below 100 knots and above 260 Knots.

B. Above 260
Explanation
The correct answer is "Above 260". This means that the landing gear operation is inhibited or disabled when the aircraft's speed exceeds 260 knots. This could be due to safety reasons, as the landing gear may not be designed to handle high speeds and could cause damage or instability if deployed at such velocities. Therefore, the system is programmed to prevent the landing gear from being activated when the speed is above 260 knots.

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• 25.

### How many turns are required on the gravity extension hand crank to extend the landing gear ?

• A.

3

• B.

5

• C.

2

A. 3
Explanation
The correct answer is 3. This suggests that it takes three turns on the gravity extension hand crank to extend the landing gear.

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• 26.

### When the landing gear is Gravity extended will nose wheel steering be available ?

• A.

No.

• B.

Only if the A/SKID AND N/W STRG switch is selected ON.

• C.

Limited nose wheel steering is available only through the captain's rudder pedals.

A. No.
Explanation
When the landing gear is gravity extended, nose wheel steering will not be available unless the A/SKID AND N/W STRG switch is selected ON. Even then, the nose wheel steering will be limited and can only be controlled through the captain's rudder pedals.

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• 27.

### Can normal landing gear operation be restored after a gravity extension if green hydraulic pressure available ?

• A.

Restoration is always possible .

• B.

It may be possible if the gravity extension was not caused by a failure of the landing gear mechanism.

• C.

No , only maintenance can restore normal operation.

B. It may be possible if the gravity extension was not caused by a failure of the landing gear mechanism.
Explanation
If the gravity extension of the landing gear was not caused by a failure of the mechanism, then it may be possible to restore normal landing gear operation. This suggests that if the gravity extension was due to some other reason, such as a temporary loss of power or a manual release, then the landing gear can be restored to its normal operation. However, if the gravity extension was caused by a failure of the landing gear mechanism itself, then normal operation cannot be restored without maintenance.

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• 28.

### If the Landing Gear was gravity extended using the hand crank on the center pedestal , what other systems will be inoperative ?

• A.

Nose wheel steering .

• B.

Anti skid and auto braking .

• C.

Nose wheel steering and anti skid .

• D.

Option 4

A. Nose wheel steering .
Explanation
If the landing gear was gravity extended using the hand crank on the center pedestal, the nose wheel steering system will be inoperative. This is because when the landing gear is extended manually, there is no hydraulic pressure available to operate the nose wheel steering mechanism. The nose wheel steering system relies on hydraulic power to turn the nose wheel, so without it, the steering functionality will not work.

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• 29.

### Which hydraulic system supplies pressure to the nose wheel steering ?

• A.

Green

• B.

Blue

• C.

Yellow

A. Green
Explanation
The green hydraulic system supplies pressure to the nose wheel steering.

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• 30.

### If the brake system automatically transitions to alternate brakes with the A/SKID AND NW STRG switch in the ON position , which of the following will be available ?

• A.

Auto brakes and Anti skid.

• B.

Only Auto brakes.

• C.

Anti skid.

C. Anti skid.
Explanation
When the A/SKID AND NW STRG switch is in the ON position, the brake system will automatically transition to alternate brakes. In this scenario, only the Anti skid feature will be available. The Auto brakes feature will not be available.

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• 31.

### If the accumulator on the alternate brake system is your only source pressure , which of the following will be available .

• A.

Auto brakes and Anti skid .

• B.

Anti skid .

• C.

Seven applications of the brake pedals .

C. Seven applications of the brake pedals .
Explanation
If the accumulator on the alternate brake system is the only source of pressure, then the only thing that will be available is seven applications of the brake pedals. This means that the brakes can be applied seven times before the pressure runs out. Auto brakes and anti-skid will not be available in this situation.

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• 32.

### What is indicated by the auto brake DECEL lights ?

• A.

Airplane deceleration is 50 % of selected rate .

• B.

Airplane deceleration is 100% of selected rate .

• C.

Airplane deceleration 80% of selected rate .

C. Airplane deceleration 80% of selected rate .
Explanation
The auto brake DECEL lights indicate that the airplane's deceleration is at 80% of the selected rate.

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• 33.

### What system pressure does the ACCU PRESS and BRAKES pressure indicator indicate ?

• A.

Yellow brake accumulator  and yellow brake system pressure to the left and right brakes.

• B.

Yellow brake accumulator and green brake system pressure to the left and right brakes.

• C.

Yellow brake accumulator and green or yellow brake system pressure to the left and right brakes.

A. Yellow brake accumulator  and yellow brake system pressure to the left and right brakes.
Explanation
The ACCU PRESS and BRAKES pressure indicator indicates the yellow brake accumulator and yellow brake system pressure to the left and right brakes.

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• 34.

### What does each turn of the gravity gear extension handle do ?

• A.

Open gear doors , drop gear shut doors.

• B.

Open gear doors , unlock gear ,drop gear.

• C.

Shutoff hydraulic pressure ,open doors , unlock gear.

C. Shutoff hydraulic pressure ,open doors , unlock gear.
Explanation
Each turn of the gravity gear extension handle performs three actions in sequence: shutting off hydraulic pressure, opening the gear doors, and unlocking the gear. This suggests that the handle is responsible for initiating the process of extending the gravity gear, by first stopping the hydraulic pressure, then opening the doors, and finally unlocking the gear mechanism.

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• 35.

### The normal brake system uses.......... hydraulic pressure and the alternate brake system uses ....... hydraulic pressure backed up by the hydraulic brake accumulator.

• A.

Green , Blue.

• B.

Yellow , Green.

• C.

Green , Yellow

C. Green , Yellow
Explanation
The normal brake system uses green hydraulic pressure, while the alternate brake system uses yellow hydraulic pressure backed up by the hydraulic brake accumulator.

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• 36.

### What is required to arm the auto brake ?

• A.

Green hydraulic pressure available , anti skid , no failures in the braking system.

• B.

Landing gear lever selected down and selection of an auto breaking rate.

• C.

Both A and B are required.

A. Green hydraulic pressure available , anti skid , no failures in the braking system.
Explanation
To arm the auto brake, it is necessary to have green hydraulic pressure available, anti-skid functionality, and no failures in the braking system. Both options A (green hydraulic pressure available, anti-skid, no failures in the braking system) and B (landing gear lever selected down and selection of an auto braking rate) are required. However, option B alone is not sufficient as it does not include the necessary conditions related to the braking system.

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• 37.

### Auto brakes , if selected , will only be activated by :

• A.

The struts being compressed.

• B.

The brake pedals being depressed.

• C.

The ground spoiler extension command.

C. The ground spoiler extension command.
Explanation
Auto brakes are a feature in some aircraft that automatically apply the brakes when certain conditions are met. In this case, the correct answer is the ground spoiler extension command. When the ground spoiler, which is a device on the wings that disrupts the airflow and creates drag, is extended, it signals the auto brakes to activate. This allows the auto brakes to engage and assist in slowing down the aircraft during landing. The other options, such as the struts being compressed or the brake pedals being depressed, are not the correct triggers for the auto brakes.

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• 38.

### If the BSCU detects a brake system malfunction in flight with the A/SKID and NW STRG switch in the ON position :

• A.

The crew will be notified with an ECAM message .

• B.

The crew will be notified with an ECAM message after touchdown if the brake system does malfunction.

• C.

The crew must manually select alternate brakes.

A. The crew will be notified with an ECAM message .
Explanation
If the BSCU (Brake and Steering Control Unit) detects a brake system malfunction in flight with the A/SKID (Anti-Skid) and NW STRG (Nose Wheel Steering) switch in the ON position, the crew will be notified with an ECAM (Electronic Centralized Aircraft Monitor) message. This message serves as an alert to the crew about the malfunction and allows them to take appropriate action. The ECAM system provides real-time monitoring and notification of various aircraft systems, helping the crew to effectively manage any issues that may arise during the flight.

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• 39.

### On the ECAM WHEEL page , which of the following will NOT be displayed ?

• A.

Bake system pressure.

• B.

Brake accumulator pressure .

• C.

Neither A or B .

C. Neither A or B .
Explanation
On the ECAM WHEEL page, both the brake system pressure and the brake accumulator pressure will be displayed. Therefore, the correct answer is "Neither A or B" because both options A and B will be displayed on the ECAM WHEEL page.

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• 40.

### How can the brake accumulator be re pressurized ?

• A.

With the Yellow electrical pump.

• B.

Whit the blue electrical pump.

• C.

A and B.

A. With the Yellow electrical pump.
Explanation
The brake accumulator can be repressurized using the Yellow electrical pump.

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• Current Version
• Apr 21, 2023
Quiz Edited by
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• Jun 02, 2020
Quiz Created by
GECAVA

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