Cuestionario Airbus A320 P.5

What is the purpose of the High-Pressure Bleed Valve (HPV)?. To maintain high pressure in the pneumatic system. To supply air when engines are at low power. To regulate the temperature of the bleed air. To monitor system pressure.

Where is the Pressure Regulating Valve (PRV) installed in the pneumatic system?. Upstream of the IP bleed valve. Downstream of the HP bleed valve. Downstream of the IP and HP bleed valves. Upstream of the High Pressure Bleed Valve (HPV).

Which components of the pneumatic system are primarily installed on the engines and in the pylons?. Pressure regulation components. Temperature regulation components. Leak detection components. Crossbleed valve components.

What happens if one Bleed Monitoring Computer (BMC) fails?. The associated FAULT light is lost. The associated bleed valve closes automatically. The overpressure warning is activated. Both BMCs exchange data via ARINC bus.

The temperature of the engine bleed air is regulated by passing it through an air-to-air heat exchanger called the ____(?)_____. precooler. fan discharge. crossbleed. APU supply.

Both Bleed Monitoring Computers (BMCs) receive signals from the leak detection loops. They exchange data via an ARINC bus for wing double loop detection. The wing loops A are connected to BMC 1, and wing loops B are connected to BMC 2. The crosstalk bus allows wing leak warnings to be activated through an _____(?)______. OR logic. XOR logic. AND logic. NOT logic.

How is the engine air bleed pressure pneumatically regulated in the Airbus A320 family of aircraft?. High Pressure (HP) Valve (VLV), Pressure Regulating Valve (PRV). Bleed Monitoring Computers (BMCs), Wing Anti-Ice (WAI). Pressure Regulating Valve (PRV), High Pressure (HP) Valve (VLV). Wing Anti-Ice (WAI), Bleed Monitoring Computers (BMCs).

When does the HP VLV pneumatically regulate the air supply, and within what pressure range does it operate?. At low engine speed, 8 to 36 psi. At high engine speed, 44 to 85 psi. At idle, 110 to 240 psi. At high altitude, 15,000 ft to 35,000 ft.

What is the primary function of the IP check valve, and when does it come into play?. Protects the IP stage from reverse flow when HP VLV is open. Regulates the pressure downstream from the PRV. Monitors engine fire at 450°C. Controls bleed pressure at high altitude.

Describe the two operating modes of the PRV control solenoid and the conditions under which each is used. Pneumatic mode for reverse flow protection, electrical mode for ENGine BLEED P/B OFF. Pneumatic mode for overpressure, electrical mode for engine fire. Pneumatic mode for engine fire, electrical mode for altitude > 15,000 ft. Pneumatic mode for delta pressure, electrical mode for precooler temperature.

The engine air bleed pressure is pneumatically regulated by the ___(?)____ when air is supplied by the HP stage, or by the ____(?)____ when the air is supplied by the Intermediate Pressure (IP) stage. High Pressure (HP) Valve (VLV), Pressure Regulating Valve (PRV). Bleed Monitoring Computers (BMCs), Wing Anti-Ice (WAI). Pressure Regulating Valve (PRV), High Pressure (HP) Valve (VLV). Wing Anti-Ice (WAI), Bleed Monitoring Computers (BMCs).

When does the HP VLV pneumatically regulate the air supply, and within what pressure range does it operate??. At low engine speed, 8 to 36 psi. At high engine speed, 44 to 85 psi. At idle, 110 to 240 psi. At high altitude, 15,000 ft to 35,000 ft.

What is the primary function of the IP check valve, and when does it come into play??. Protects the IP stage from reverse flow when HP VLV is open. Regulates the pressure downstream from the PRV. Monitors engine fire at 450°C. Controls bleed pressure at high altitude.

A ground cart may supply the pneumatic system, and the supply duct is located on the left-hand side of the cross bleed valve. Only the LH bleed system is supplied when the X-BLEED selector is in the ____(?)____ position for ground air supply. OFF. AUTO. OPEN. SHUT.

When the X-BLEED selector is in the SHUT position, the ground air supply will be available to supply the LH and RH systems ____(?)_____. simultaneously. independently. alternately. occasionally.

The leak detection system is used to detect leaks in the vicinity of the packs, wings, pylons, and APU hot air ducts. Each wing is monitored by a double loop, and the pylon and APU hot air ducts are monitored by a ____(?)____ loop. dual. redundant. single. triple.

The APU bleed air supplies the pneumatic system through the APU bleed valve if the APU is ____(?)_____. operational. running. stopped. in standby mode.

What are the three subsystems that make up the water and waste system on Airbus A320 Family aircraft?. Fuel system, electrical system, hydraulic system. Potable water system, waste water system, toilet system. Navigation system, communication system, entertainment system. Landing gear system, engine system, avionics system.

Where is the potable water tank located in the A318, A319, and A321 aircraft?. In the galleys. In the forward cargo compartment. In the aft cargo compartment. In the lavatories.

Where is the potable water tank located in the A320 aircraft?. In the forward cargo compartment. In the aft cargo compartment. In the aft bulk cargo. In the galleys zone.

Which aircraft in the Airbus A320 Family has a different location for the potable water tank compared to the others?. A318. A319. A320. A321.

What controls the potable water service panel heating, especially in winter conditions?. A thermostat. The Flight Attendant Panel (FAP). The vacuum toilet system. The water tank.

Where are the water and waste indications displayed for the flight attendants?. On the cockpit display. On the passenger seats. On the Flight Attendant Panel (FAP). On the aircraft's exterior.

How is used water from the lavatory washbasins and galley sinks discarded in the waste water system?. Stored in a separate tank. Discharged overboard outside. Stored in the cargo compartment. Converted into drinking water.

What feature is integrated into the drain masts of the waste water system to prevent ice formation?. Heated tapes. Compressed air. Vacuum generator. Electric heating elements.

What type of system does the toilet system on Airbus A320 Family aircraft use for flushing?. Hydraulic system. Electrical system. Potable water system. Differential pressure toilet system.

What happens when the waste holding tank is full in the toilet system?. The waste is automatically ejected. The toilet system shuts down. The waste is recycled. The waste is diverted to the potable water tank.

What provides the necessary differential pressure in the waste system to move waste from the toilet bowl to the tank at low altitude or on the ground?. The cabin air pressure. A vacuum generator. The waste holding tank. The toilet bowl.

Which system controls the flushing system operation and stops it when the waste servicing panel is open?. The Flight Attendant Panel (FAP). The potable water system. The Vacuum System Controller Function (VSCF). The waste holding tank.

Where is the waste holding tank located in the aircraft?. In the lavatories. In the forward cargo compartment. Behind the bulk cargo compartment. In the galleys.

What components are included in the waste holding tank?. A vacuum generator, a liquid level sensor, and a flush control unit. A water separator, a liquid level transmitter, and an ice prevention system. A waste drain valve, two rinse line connections, and a liquid level sensor. A potable water tank, a vacuum system controller, and a heating element.

What can be insulated in the waste holding tank system as an option?. The vacuum generator. The toilet bowl. The potable water tank. The lines between the tank and the service panel.

Why are the lines between the waste holding tank and the service panel insulated and heated?. To keep the waste warm. To prevent freezing and ice formation. To improve waste disposal efficiency. To save energy.

What controls and monitors the system functions and related electric components in the vacuum toilet system?. The Flight Attendant Panel (FAP). The waste holding tank. The Flush Control Unit (FCU). The Cabin Intercommunication Data System (CIDS).

What happens when the waste holding tank is full in the toilet system??. The waste is automatically ejected. The toilet system shuts down. The waste is recycled. The waste is diverted to the potable water tank.

The water and waste indications are displayed automatically as soon as the service panel is open. True. False.

On the Flight Attendant Panel (FAP), the filling quantity cannot be selected as an option. True. False.

There is only one control handle on the water service panel. True. False.

On the A320, the overflow valve opens mechanically when the fill/drain control handle is set to the drain position. True. False.

When does the "Overflow Valve Light" come on, and what does it indicate when the valve is in the open position?. The "Overflow Valve Light" comes on during draining, indicating that the valve is closed. The "Overflow Valve Light" comes on during filling, indicating that the valve is open. The "Overflow Valve Light" comes on when the air compressor is activated. The "Overflow Valve Light" comes on when the tank is empty.

The Fill/Drain control handle is initially positioned to "drain" when filling the water tank. True. False.

The "Green Tank Full Light" comes on when the tank is empty. True. False.

What happens when the toilet service panel door is open on the ground?. All toilet operations are stopped through DEU B. Flush signals are inhibited. The vacuum generator starts automatically. The waste holding tank is drained.

What is the primary purpose of the drain control handle located at the service panel?. Initiating the vacuum generator. Controlling cabin pressurization. Initiating waste holding tank draining. Activating the DEU B.

When is the drain control handle used during ground service?. To activate the vacuum generator valve. To stop all toilet operations. To initiate cabin pressurization. To operate the vacuum generator motor.

What is the purpose of opening the cap of the waste drain connection during the servicing process?. To check for leaks from the waste drain connection. To connect the toilet service vehicle drain hose. To flush the waste tank with disinfectant solution. To activate the vacuum system.

The Fuel Tank Inerting System (FTIS) includes two sub-systems: The Fuel Tank Ventilation System (FTVS). The Air Conditioning System (ACS). The Engine Bleed Air System (EBAS). The Airplane Mode Selector (AMS).

The CSAS gets hot air from the Engine bleed air system and decreases its temperature to a level compatible with the IGGS sub-system. The CSAS Inert Gas Generation System (IGGS). The CSAS Conditioned Service Air System (CSAS). The CSAS Engine Bleed Air System (EBAS). The CSAS Air Conditioning System (ACS).

Engine 1 is the primary bleed source and Eng 2, through the X Bleed valve, is the secondary bleed source. Engine 1 is the secondary bleed source. Engine 2 is the primary bleed source. Engine 2 is the secondary bleed source. Engine 1 is the primary bleed source.

The bypass valve is installed in the heat exchanger bypass duct and is controlled by the CSAS. The bypass valve adds cold air downstream of the heat exchanger. The bypass valve adds hot air downstream of the heat exchanger. The bypass valve controls the ozone converter. The bypass valve is not used in the CSAS.

If there is over-pressure or over-temperature, the CSAS isolation valve closes to stop the system. The CSAS isolation valve opens to release pressure. The CSAS isolation valve remains unaffected by temperature changes. The CSAS isolation valve closes in normal operation. The CSAS isolation valve has no impact on pressure.

In normal operation, the CSAS isolation valve is open to let the air go through the ozone converter. The CSAS isolation valve remains closed. The CSAS isolation valve opens after the ozone converter. The CSAS isolation valve opens after the heat exchanger. The CSAS isolation valve is not used in normal operation.

If a failure of the CSAS system occurs, the status message "INERT FAULT" will come into view only in flight phase 1 and 10, for maintenance. The status message appears in all flight phases. The status message appears only in flight phase 2. The status message appears only in flight phase 1 and 10. The status message never appears.

The MEL tells that the A/C can be dispatched with the system unserviceable for 10 days with no maintenance procedure. The MEL allows dispatch with unlimited unserviceable days. The MEL requires maintenance immediately. The MEL allows a 10-day dispatch without maintenance. The MEL does not mention dispatch conditions.

In normal operation, the bleed air is filtered by the. CSAS and D-ULPA filter. HPGC door and ASM. ICU and DFSOV. ASM and HPGC door.

Downstream of the D-ULPA filter, air parameters are sent to. DFSOV and ASM. ICU and ASM. Oxygen sensor and ASM. HPGC door and DFSOV.

In abnormal operation, if there is overpressure or overtemperature, the ICU de-energizes the. IGGS Isolation Gate Valve solenoid and the DFSOV solenoid. HPGC door and ASM. DFSOV solenoid and the oxygen sensor. Oxygen sensor and the ASM.

If the oxygen sensor senses an oxygen rate higher than 12% during abnormal operation, the ICU de-energizes the. DFSOV solenoid and the IGGS Isolation Gate Valve solenoid. ASM and HPGC door. HPGC door and the DFSOV solenoid. IGGS Isolation Gate Valve solenoid and the oxygen sensor.

The ASM is the core of the Inert Gas Generation System, and it removes oxygen to produce. Oxygen Enriched Air (OEA) and Nitrogen Enriched Air (NEA). Hydrocarbons and dust. Oxygen and hydrocarbons. OEA and HPGC door.

An ASM is a semi-permeable hollow-fiber membrane bundle contained in a. Pressure containment canister. D-ULPA filter. CSAS. HPGC door.

In normal operation, the DFSOV is __________ and isolates the IGGS from the center fuel tank. open. closed. partially open. malfunctioning.

The ICU supplies the two solenoids of the DFSOV to control the DFSOV position (OPEN/CLOSE) and to control the NEA flow __(?)__. LOW. HIGH. MI. LOW/MI/HIGH.

What is the primary function of the Auxiliary Power Unit (APU)?. Electrical power generation. Engine thrust. Fuel storage. Wing anti-ice.

Besides electrical power, what else does the APU provide?. Engine cooling. Air conditioning in-flight, bleed air for various functions. Navigation assistance. Oxygen supply.

When does the air intake flap open and close?. Opens when APU is ON, closes when OFF. Opens during landing, closes during takeoff. Opens during takeoff, closes during landing. Opens when the main engines are running.

What is the purpose of the air intake flap?. Engine cooling. Reducing noise. Pneumatic supply, combustion air supply. Preventing fires.

Where is the APU installed on the aircraft?. In the cockpit. In the wing. In the fuselage tail cone. In the landing gear.

How is vibration transmission reduced between the APU and the aircraft structure?. Through tie rods,Through isolators. Through fuselage. Through exhaust muffler. Through air intake.

How is the APU attached to the structure brackets in the APU compartment ceiling?. Through tie rods. Through bolts. Through welding. Through adhesive.

What is the purpose of the vibration isolators in the APU mounting system?. To increase vibration. To reduce noise, prevent transmission of vibrations. To transfer vibrations to the aircraft structure. To connect to the APU three-point mounting system.

What is the primary purpose of the drain system in the APU compartment?. To collect fluids for reuse. To prevent fluid accumulation. To supply water for aircraft cleaning. To collect APU exhaust gases.

How are fluids collected and removed from the APU compartment?. Through a drain mast. Through an APU exhaust pipe. Through an APU cooling system. Through an APU fuel line.

The Auxiliary Power Unit (APU) is a constant-speed ___(?)___ engine. electric. jet. gas turbine. propeller.

The APU provides electrical power for the aircraft systems, bleed air for various functions, and bleed air cutoff above the specified ___(?)___ limit. altitude. temperature. manufacturer. speed.

The air intake flap opens when the APU MASTER SWITCH is set to ON and closes when the MASTER SWITCH is set to OFF and the APU ___(?)___. When open, it supplies air to the APU inlet for combustion and pneumatic supply. starts. stalls. accelerates. stops.

In case of failure, the air intake flap can be opened or closed manually by a manual ___(?)___ device. override. control. lever. switch.

The APU is installed in a fireproof compartment located in the fuselage ___(?)___ cone. wing. tail. nose. cockpit.

Vibration isolators are installed between the APU mount brackets and the tie rods to reduce the transmission of A/C vibrations and shocks to the APU. The isolators also prevent the transmission of vibrations from the APU to the A/C ___(?)___. wings. engines. structure. cockpit.

The air intake system ducts ambient air to the APU plenum chamber. An air intake flap cuts off the air supply when the APU does not operate. In case of failure, the air intake flap can be opened or closed manually by a manual ___(?)___ device. override. control. lever. switch.

The air intake duct, which is composed of a diffuser and elbow, provides correct airflow to the APU plenum. The air intake duct is attached to the ___(?)___ access door. left. right. top. rear.

The exhaust system lets the APU exhaust gas flow into the atmosphere and muffles the ___(?)___ from the exhaust. The exhaust muffler thermal insulation protects the A/C structure. smoke. noise. heat. vibration.

The exhaust muffler thermal insulation protects the A/C ___(?)___. wings. engines. structure. cockpit.

Two access doors allow access to the APU compartment. The access doors on the bottom of the tail cone open ___(?)___ to allow the APU to be inspected, lifted, and lowered. inward. outward. upward. downward.

Two access doors allow access to the APU compartment. The access doors on the bottom of the tail cone open outward to allow the APU to be inspected, lifted, and ___(?)___. secured. fixed. raised. lowered.

A drain system prevents the collection of fluids in the APU compartment. Any fluid that may accumulate in the APU compartment is delivered to a ___(?)___ mast. Some of the fluids are collected in a drain tank in the APU compartment, which is emptied through the drain mast when the A/C is above 200 kt. fuel. drain. water. hydraulic.

The Structure Repair Manual is a customized document exclusive to specific airlines. True. False.

The introduction chapter of the SRM provides airplane information such as Weight Variant and Airplane Allocation List. True. False.

The weight variant given in the Airplane allocation list always represents the current status of the aircraft. True. False.

For permanent repairs with inspection program, inspections are not quoted along with the repair. True. False.

Each subject within the SRM uses a four-element numbering system. True. False.

What is the first document to use to assess damage on the aircraft structure?. Aircraft Operation Manual. Pilot's Handbook. Structure Repair Manual. Maintenance Manual.

Where is general information or information applicable to more than one chapter included in the SRM?. Chapter 50. Chapter 51. Chapter 52. Chapter 53.

In the "MOD/Definition Comparison" service, what does the "Aircraft status" criterion allow you to filter by?. The family of the aircraft. The type of aircraft. The status of the aircraft (e.g. delivered or to be delivered). The owner ICAO code of the aircraft.

What is the primary purpose of the Structure Repair Manual (SRM)?. To provide a list of all Airbus aircraft models. To provide guidelines on how to repair aircraft. To provide a history of Airbus. To provide a list of all aircraft manufacturers.

How is the SRM organized?. By aircraft model. By type of damage. By ATA specification. By date of publication.

What is the significance of 'Allowable Damage'?. It indicates damage that requires immediate repair. It indicates damage that can be ignored. It indicates damage that can be temporarily tolerated without immediate repair. It indicates damage that has been repaired previously.

What does a 'gouge' refer to?. A line of damage. A damage area resulting in a cross-sectional change. A mark caused by a sharp object. A series of scratches.

What causes 'corrosion'?. Physical impact. Chemical or electro-chemical effect. Exposure to high temperatures. Regular wear and tear.

Which factors determine the type of surface protection for components?. Material and Function. Material, Function, and Location. Function and Location. Only Material.

Which of the following is NOT an exception to external areas having surface protection?. Leading edges of slats. APU exhaust. Wing flaps. Cabin Pressurization Control System Outflow Valve.