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

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.

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.

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.

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.

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.

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.

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

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.

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).

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.

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

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.

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.

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.

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

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.

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.

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.

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.

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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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.

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.

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.

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.

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.

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.

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

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.

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.

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.

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.

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.

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

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.

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.

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.

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

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

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.