Cuestionario Airbus A320 P.3

How does the crossfeed valve operate in the aircraft's fuel system?. It electrically connects the left and right tanks. It isolates the engine fuel feed supply. It controls fuel temperature. It supplies fuel to the APU.

What happens when the center tank pumps run in the aircraft's fuel system?. The center tank supplies fuel to the engines. The LP valve closes. The cross feed valve opens. The APU LP valve opens.

Where is the air release valve installed in the fuel system?. At the highest point between the pump and the LP fuel valve. In the center tank. In the wing tank. Inside the fuel pump.

When does the LP fuel valve isolate the engine fuel feed supply?. At engine shutdown and in case of an emergency. During refueling. When the LP valve is manually closed. During crossfeed operations.

In the A318/A319/A320, when is fuel supplied to the engines from the wing inner cells? When the center tank is ___(?)___. full. empty. overfilled. pressurized.

Two engine Low Pressure (LP) valves in the A318/A319/A320 close when their related engine ____(?)____. is running. is refuled. stops. overheats.

The cross feed valve in the A318/A319/A320 divides the main fuel pump system into two parts, one for each ___(?)___. fuel tank. wing. engine. pump.

The wing fuel feed pumps in the A318/A319/A320 are replaced from the ____(?)____. cockpit. belly fairing. wing upper surface. wing lower surface.

The manual Magnetic Level Indicators are used to calculate tank fuel quantities if a failure affects the Fuel Quantity Indicating System, such as an ____(?)____. electrical failure. engine malfunction. APU failure. overheating issue.

The LP fuel valve in the A318/A319/A320 isolates the engine fuel feed supply during engine shutdown or in case of an ____(?)____. APU malfunction. LP valve failure. engine fire emergency. overheating situation.

The scavenge jet pump in the fuel system has a jet pump body, a jet adaptor assembly, and a non-return valve (NRV) that prevents fuel from entering a fuel pump that is ____(?)____. running. inoperative. oversized. overheated.

In what situation will the FAULT light on the MODE SEL P/BSW and the MASTER CAUT come on in flight?. Failure of the center tank transfer valves. Failure of wing tank transfer valves. When more than 5000 kg of fuel is left in either wing tank. When there is no fuel in the center tank.

What triggers the display of the FUEL page on the ECAM?. Failure of the main fuel pumps. Wing tank overflow. Failure of the center tank transfer valves. Low fuel level in the center tank.

In MANUAL MODE, what should be done when the FAULT light appears in the CTR TK P/BSW?. Leave the P/B switch in the OFF position. Set the MODE SEL P/BSW to AUTO mode. Push the FAULT light to reset it. Set the related CTR TK L XFR or R XFR P/B switch to OFF.

How can you test the operation of the high-level protection system during refueling?. By setting the Pre-selector to maximum fuel load. By draining at least one liter of fuel. By performing the Lights (LTS) and High Level (HI. LVL) test. By turning on the external ground power.

Before entering a fuel tank for maintenance, it is essential to complete the Pre-Entry Checklist. True. False.

When refueling is complete, the END light will not illuminate, indicating that the refuel valve is still open. True. False.

What is the normal source of pressure for the green hydraulic system?. Engine Driven Pump (EDP). Power Transfer Unit (PTU). Electrical pump (E-Pump). Ram Air Turbine (RAT).

Which hydraulic system can the blue electric pump be used as an auxiliary power source for on the ground?. Green. Blue. Yellow. None.

What is the purpose of the Power Transfer Unit (PTU)?. It transfers fluid between the green and yellow hydraulic systems. It provides auxiliary pressure supply to the blue system. It is used for cargo door operation on the yellow system. It is auxiliary pressure supply for either the green or yellow systems.

How is the RAT deployed for auxiliary pressure supply?. Automatically. Manually. Both automatically and manually. It is always extended.

What prevents the RAT from stowing when extended?. Interlock mechanism. Hydraulic pressure. Spring force. Solenoid operation.

Which system uses the Constant Speed Motor/Generator (CSM/G) to provide emergency electrical power?. Green. Yellow. Blue. All systems.

What is the role of priority valves in the hydraulic system?. They cut off hydraulic power to essential systems. They transfer fluid between hydraulic systems. They cut off hydraulic power to Heavy Load Users. They supply hydraulic power to heavy load users.

The PTU is an auxiliary pressure supply for either the green or yellow systems without the transfer of fluid between the two systems. It operates automatically if there is a delta pressure of ____(?)____ between the green/yellow or yellow/green hydraulic systems. 100psi. 250psi. 500psi. 750psi.

The RAT is an auxiliary pressure supply for the blue system and for the emergency electrical power Constant Speed Motor/Generator (CSM / G). It can be deployed ____(?)____ or manually depending on the failure conditions. automatically. manually. both automatically and manually. neither automatically nor manually.

The interlock mechanism on the RAT will only permit RAT stowage if the blades are properly aligned. It also prevents rotation when stowed. The interlock will release at approximately ___(?)____ degrees from the full extension position. 10 degrees. 45 degrees. 90 degrees. 5 degrees.

In the event of low hydraulic pressure, the priority valves maintain the operation of essential systems by cutting off hydraulic power to ____(?)____. heavy load users. all systems. the PTU. the RAT.

What is the auxiliary source of pressure for the blue hydraulic system?. EDP. PTU. E-Pump. RAT.

Where are hydraulic pipes located within the aircraft?. Passenger cabin and flight compartment. Only in the flight compartment. Only in the passenger cabin. In the aircraft except in Passenger cabin and flight compartment.

What is the nitrogen pressure set to during the pressurization of the reservoir?. 30 PSI. 40 PSI. 50 PSI. 60 PSI.

Before starting the filling procedure, what must be the position of the flight control surfaces and cargo doors?. Neutral retracted position. Fully extended position. Open position. Any position.

What should the triple indicator show when the yellow electric pump is selected to OFF?. Hydraulic system pressure. Brake accumulator pressure. Nitrogen pressure. Green hydraulic pressure.

Why should a warning notice be placed before operating the hydraulic system?. To indicate the system is depressurized. To prevent others from operating the system. To remind the operator to wear gloves. To indicate the cargo doors are closed.

What is done with the hand pump lever from the yellow panel during the filling operation?. It is removed and assembled for use on the green panel. It is left in place. It is disconnected and stored in a toolbox. It is used to depressurize the system.

What precautions should be taken before removing the flexible hose from its housing?. Wear proper protection gloves and goggles. Disconnect the hydraulic system. Depressurize the nitrogen pressure. Ensure the cargo doors are open.

How is the selection of the hydraulic system to be filled confirmed?. A colored LED on the indication panel. A sound alert. A pressure gauge reading. An audible beep.

Where should the system reservoir be filled to during the filling operation?. To the end of the scale. To the last white line in the related colored band. To the top of the reservoir. To the halfway mark.

The triple indicator should show the brake accumulator as being fully pressurized to 5000 PSI when the electric pump is turned OFF. True. False.

Warning notices are placed to remind the operator to wear gloves and goggles during the hydraulic filling operation. True. False.

The hand pump lever is disconnected and stored in a toolbox during the filling operation. True. False.

The flexible hose is inserted into a new canister of hydraulic fluid after connecting it to the hand pump. True. False.

The filling operation is initiated by selecting the hydraulic system that needs to be filled. True. False.

The system reservoir should be filled to the end of the scale during the filling operation. True. False.

Which subsystems are part of the ice and rain protection system on the Airbus A320 family aircraft?. Wing ice protection. Engine air intake ice protection, rain mast ice protection. Probe ice protection, Windshield ice and rain protection. All.

How is wing anti-ice supply controlled for both wings?. By a single pushbutton switch on the overhead ANTI ICE panel. By separate switches for each wing. By the engine's bleed air automatically. By manual control in the cockpit.

When is engine air intake anti-ice protection available?. Only in flight. Only on the ground. In flight or on the ground with the engine running. Automatically when the aircraft is powered.

What is used to protect the Angle Of Attack (AOA) sensors, pitot probes, static ports, and Total Air Temperature (TAT) probes from ice?. Electrical heating. Hot air from the pneumatic system. Manual insulation covers. Engine bleed air.

How is windshield anti-icing provided on the Airbus A320 family aircraft?. By manual control in the cockpit. By hot air from the pneumatic system. Automatically when at least one engine is running. By electrical heating.

Under what conditions is the drain mast heating switched ON?. When the electrical system is powered. When the aircraft is in heavy rain. When the temperature is above a specific value. It is always in operation.

The front windshields and side windows are heated ____(?)_____ when at least one engine is running. automatically. manually. with wipers. during takeoff.

The Drain Mast Heating is switched ON when the temperature is ____(?)____ a specific value. above. below. exactly at. not related to.

What subsystem protects the engine air intake from ice?. Probe ice protection. Windshield ice and rain protection. Engine air intake ice protection. Drain mast ice protection.

Which part of the aircraft's electrical system heats the water and waste system for ice protection?. Visual lighted ice detection. Electronic ice detection system. Engine bleed air. Hot air from the pneumatic system.

How is the operation of the rain repellent system controlled on the CAPT and F/O sides?. Independently. Simultaneously. Manually. Automatically.

What is used to initiate a new cycle of rain repellent fluid spray?. Press the P/B once. Press and hold the P/B. Release and press the P/B again. It starts automatically.

The wing anti-ice supply to both wings is controlled by a single pushbutton switch on the overhead ANTI ICE panel. True. False.

Engine anti-ice is only available in flight and not on the ground with the engine running. True. False.

The PROBE/WINDOW HEAT pushbutton switch is used to select windshield anti-icing when the engines are shut down. True. False.

Each Control Unit (CU) regulates the heating temperature of the associated drain mast tube between ____(?)_____. 0°C (32°F) to 6°C (43°F). 6°C (43°F) to 10°C (50°F). 10°C (50°F) to 15°C (59°F). 15°C (59°F) to 20°C (68°F).

The system status is sent to the Cabin Intercommunication Data System (CIDS) for indication on the ____(?)_____. pilot's display. maintenance logbook. Flight Attendant Panel (FAP). Centralized Fault Display Interface Unit (CFDIU).

If there is a failure of the Heater (HTR) or CU, a ____(?)_____ light is illuminated on the Flight Attendant Panel (FAP). green. red. caution. maintenance.

The drain mast data is stored in the ____(?)_____. aircraft's central server. maintenance logbook. Centralized Fault Display Interface Unit (CFDIU). Flight Attendant Panel (FAP).

To perform a complete test of the drain mast system, two tests must be carried out, one from the MCDU, and the second one on each ____(?)____. flight attendant. maintenance technician. control unit. aircraft.

The thermal switch in the AC power supply line within the drain mast opens at 120°C (250°F). True. False.

The system status is sent to the Centralized Fault Display Interface Unit (CFDIU) for indication. True. False.

If there is a failure of the Heater (HTR) or CU, a green light is illuminated on the Flight Attendant Panel (FAP). True. False.

What is the purpose of the Electronic Centralized Aircraft Monitoring (ECAM) system?. Monitoring engine parameters. Displaying weather information. Controlling navigation systems. Managing cabin lighting.

Which Display Management Computer (DMC) drives the Captain's Primary Flight Display (PFD) in normal operation?. DMC 1. DMC 2. DMC 3. DMC 4.

When does the ADV symbol pulsate on the Engine/Warning Display (EWD)?. When there's an advisory on another SD page. During takeoff and landing. When a failure is detected by the FWC. When the CAPT PFD and ND fail.

What does the overflow arrow on the EWD indicate?. Engine failures. Excessive warning messages. Cabin temperature issues. Navigation system problems.

What is the role of the System Data Acquisition Concentrators (SDACs) in the aircraft system?. Generate warning messages. Compute engine parameters. Receive signals from aircraft systems. Provide navigation guidance.

In which situations does the Engine/Warning Display (EWD) display the title of a failure and the associated actions to take?. During takeoff and landing only. When there's an advisory on another SD page. When an aural warning is triggered. In case of aircraft system failure.

How are the CLeaR P/Bs used in response to a system failure?. They turn off the power to the Display Units (DUs). They release the Fault lights on the hydraulic panel. They indicate the phase of the flight. They clear the warnings and cautions.

What are the primary parameters displayed in the upper area of the Engine/Warning Display (EWD)?. Engine Pressure Ratio (EPR). Slat/flap position. Fuel On Board (FOB). All.

The Electronic Centralized Aircraft Monitoring (ECAM) system displays weather information. True. False.

In normal operation, DMC 1 drives the Captain's Primary Flight Display (PFD), while DMC 2 drives the First Officer's PFD. True. False.

The CLeaR P/Bs are used to activate the warnings and cautions. True. False.

The STATUS REMINDER and RECALL FUNCTION reminds the crew of cleared warnings. True. False.

The System Data Acquisition Concentrators (SDACs) send data to the Electronic Flight Instrument System (EFIS) displays. True. False.

Level 3 alerts correspond to an emergency configuration where corrective or palliative action must be taken by the crew ____(?)____. immediately. without any action. after a crew meeting. during routine maintenance.

A primary failure is a failure of an equipment or system causing the loss of ___(?)___ equipment. secondary. other. independent. advisory.

In ECAM Normal Dual Display mode, the flashing ADV symbol indicates multiple advisories on different pages or a failure ____(?)____. on the currently displayed page. detected by the FWC. requiring immediate action. in the ECP.

In ECAM MONO Display mode, when a value drifts from its normal range, a white ADV message flashes in the center of the EWD to attract crew ____(?)____. monitoring. attention. routine maintenance. emergency response.

Level 3 warnings are associated with a Continuous Repetitive Chime (CRC), warning messages on Liquid Crystal Display (LCD), and a flashing __________. caution light. advisory light. caution message. master warining lighh.

Level 2 alerts require immediate crew awareness but not immediate ____(?)____ action. emergency. corrective. advisory. monitoring.

What happens when the PFD unit is switched off by its potentiometer?. ND is automatically displayed on the PFD unit. The PFD image remains on the PFD unit. The ND image is automatically displayed on the ND unit. The ECAM single display mode is activated.

How is the PFD/ND transfer (XFR) performed?. Physically swapping the PFD and ND units. Manually switching the PFD/ND outputs inside the DMC. Automatically by the ECAM Control Panel. Through the use of SDAC.

What happens when the upper EWD display fails?. Upper display is automatically transferred to the lower display. ECAM single display mode is activated. The ECAM/ND transfer selector is activated. Both PFD and ND units fail.

What reconfiguration options are available in case of lower DU failure?. No automatic reconfiguration is possible. The ECAM works in dual display mode. PFD automatically takes over the lower DU. ND image is displayed on the PFD.

In case of lower DU failure or if the lower display is turned to off, no automatic reconfiguration is possible, and the ECAM works in ____(?)____ display mode. single display mode. dual. triple. full.

In case of EWD unit and SD unit failure, each crew member can permanently present the EWD on the ND unit by rotating the ECAM/ND transfer selector switch on the switching panel. True. False.

It is still possible to recover a system page by pushing and holding a system key on the ECP. True. False.

How should the annunciator light switch be set to test the clock?. On. Off. Test. Reset.

What is the operational consequence of Class 1 failures?. Affects flight. No operational consequence. Only affects the cockpit. Requires maintenance.

What does the crew report in the logbook after a malfunction?. Cockpit effect. Flight time. Weather conditions. Maintenance procedures.

What are the two primary functions of the Flight Data Interface and Management Unit (FDIMU)?. Flight Data Interface Unit (FDIU) and Data Management Unit (DMU). Data Loading Selector (DLS) and Multipurpose Disk Drive Unit (MDDU). Digital Flight Data Recorder (DFDR) and Quick Access Recorder (QAR). Linear Accelerometer (LA) and System Data Acquisition Concentrator (SDAC).

What does the FDIU-part of the FDIMU do with the input parameters?. Transmits them to the Digital AIDS Recorder (DAR). Converts, compares, and checks them. Records them in data frames. Routes them to the Data Loading Routing Box (DLRB).

When does the FDIU-part check the integrity of the mandatory parameters during a flight?. Continuously throughout the flight. After the engines are shut down. Before engine start. Only during maintenance checks.

What is the purpose of the underwater locator beacon on the DFDR?. To activate the DFDR. To provide the location of the recorder in water after an accident. To transmit data to the CFDIU. To control the power interlock circuit.