1. What happens when FQIS (fuel quantity indicating system) detects high level condition in any of the aircraft tanks during the refueling operation. a. A warning for excess fuel is triggered. b. The refueling operation is stopped automatically. c. The corresponding Refuel valve is closed to avoid overfilling of the tank. d. The transfer valve is open to fill the inner cell.
2. What is the state of the wing tank boost pumps when center tank boost pumps feed the engines: a. Running, because they work all the time. b. Running, because they also feed the engines when the center tank does it. c. Not Running, because the center tank boost pumps have priority to feed the engines. d. Not running, because they only run when the center tank is empty.
3. On ECAM fuel page, when is the FUEL USED indication for the engines re-initialized to Zero: a. When the system is de-energized shutdown. b. At next aircraft Refueling. c. At next engine start. d. After engine shutdown.
4. With the following configuration: aircraft on ground, slats extended, MODE SEL PB in fuel control panel in AUTO mode; which source feeds the engines 3 minutes after engine start? a. The center tank. b. The wing tank inner cells. c. The wing tanks outer cells. d. All of the above.
5. Which is the function of the intercell transfer valves when they are operated: a. Allow the fuel to flow from center tank to the inner cells. b. Allow the fuel to flow from inner cells to the outer cells. c. Allow the fuel to flow from outer cells to the vent surge tanks. d. Allow the fuel to flow from outer cells to the inner cells.
6. On the fuel tanks vent system, the overpressure protector normally releases an overpressure in the wing tank outer cells to: a. The inner cell. b. The center tank. c. The vent surge tank. d. Atmosphere (overboard).
7. What function is performed by the wing and center tank boost pump pressure switches. a. Control the automatic running and shutdown for the boost pumps. b. Sense a specific value of differential pressure between cells to open the transfer valves. c. Send a LOW PRESSURE signal to trigger an ECAM Warning when the boost pump fails.
8. Which component from the Refuel/Defuel system allows the connection of the boost pump pressure outputs (fuel feed system) to the refueling gallery, when performing defueling/fuel transfer operations between aircraft tanks on ground. a. Refuel valve. b. Diffusers. c. Defuel/Transfer valve. d. Air inlet valve. e. Drain valve.
9. When the wing tanks are feeding the engines, what happens when the low level sensor senses that a value of 1650 lbs of fuel in any of the wing tank inner cells has been reached. a. The transfer valve of the wing tank with low level opens. b. The transfer valve of the wing tank with low level closes. c. The transfer valves of both wing tanks close simultaneously. d. The transfer valves of both wing tanks open simultaneously.
10. Which component from the aircraft tanks allows the gravity feeding of the engines when there are no pressure sources (boost pumps) available: a. LP Valve. b. By-pass suction valves. c. Sequence valves. d. Crossfeed valve.
11. What function is performed by the APU boost pump pressure switch. a. Control the automatic running/shutdown of the APU boost pump. b. Sense a specific value of differential pressure to open the transfer valves. c. Send a LOW PRESSURE signal to trigger an ECAM Warning when the boost pump fails. d. None of the above.
12. Which component from the aircraft fuel system allows the feeding of any engine from any fuel tank: a. LP Valve. b. By-pass suction valves. c. Sequence valves. d. Crossfeed valve.
13. Which component from the Refuel/Defuel system minimizes the formation of turbulence and electrostatic buildup when the fuel is discharged into the aircraft tanks during fueling operations. a. Refuel valve. b. Diffusers. c. Defuel/Transfer valve. d. Air inlet valve. e. Drain valve.
14. Which component from the Refuel/Defuel system releases the remaining pressure in the refueling gallery allowing the drainage of the fuel trapped in the line and its recovery into the inner cell of the tanks, after the refuel operation of the aircraft. a. Refuel valve. b. Diffusers. c. Defuel/Transfer valve. d. Air inlet valve. e. Drain valve.
15. Which component from the fuel system allows the cutoff of fuel flow to the engines or APU during normal or emergency shutdown: a. LP Valve. b. By-pass suction valves. c. Sequence valves. d. Crossfeed valve.
16. After a normal flight, when are the intercell transfer valves going to close automatically again: a. At system shutdown. b. At next aircraft refueling. c. At next engine start. d. After engine shutdown.
17. What happens in the fuel quantity indicating system when one of the FQIC (fuel quantity indicating computer) channels is inoperative. a. Half of the fuel quantity data on ECAM is not available. b. All fuel quantity data on ECAM is not available. c. A warning in the fuel system is triggered and also a report on CFDS. d. The system operates normally and the failure is reported on request through CFDS.
18. What happens with the center tank boost pumps in flight, when the slats are extended (MODE SEL PB in fuel control panel on AUTO mode): a. The center tank boost pumps run automatically. b. The center tank boost pumps must be stopped manually. c. The center tank pumps stop automatically. d. Nothing happens.
19. Which component from the Refuel/Defuel system allows the manual or automatic interconnection of the refueling gallery with the corresponding aircraft tank to supply it with fuel during fueling operations, and also cuts off the fuel supply when the fuel inside the tank has reached a specific level. a. Refuel valve. b. Diffusers. c. Defuel/Transfer valve. d. Air inlet valve. e. Drain valve.
20. Which component from the fuel system limits the pressure output of wing tanks boost pumps to give priority to center tank boost pumps: a. LP Valve. b. By-pass suction valves. c. Sequence valves. d. Crossfeed valve.
21. On ECAM fuel page, what does it mean if the fuel quantity indication of any tank is boxed amber. a. Failure in one of the channels of FQIC (fuel quantity indicating computer). b. Failure on both channels of FQIC (fuel quantity indicating computer). c. The fuel quantity inside the tank is USABLE FUEL. d. The fuel quantity inside the tank is UNUSABLE FUEL.
22. Only the center tank allows the gravity feeding of the engines when there is a complete failure of all aircraft boost pumps. a. True. b. False.
23. On the fuel tanks vent system, the overpressure protector normally releases an overpressure in the wing tank inner cells: a. To the inner cell. b. To the center tank. c. To the vent surge tank. d. To atmosphere (overboard).
24. What should be the position of the different controls in the Refuel/Defuel panel to accomplish a fuel transfer from the right wing tank to the left. a. MODE SELECT SW: DEFUEL/XFR; REFUEL VALVE RIGHT WING: OPEN; CROSFEED VALVE: OPEN; LEFT WING BOOST PUMP PB: ON. b. MODE SELECT SW: DEFUEL/XFR; REFUEL VALVE LEFT WING: OPEN; CROSFEED VALVE: OPEN; RIGHT WING BOOST PUMP PB: ON. c. MODE SELECT SW: DEFUEL/XFR; REFUEL VALVE RIGHT WING: OPEN; CROSFEED VALVE: CLOSED; LEFT WING BOOST PUMP PB: ON. d. MODE SELECT SW: DEFUEL/XFR; REFUEL VALVE LEFT WING: OPEN; CROSFEED VALVE: OPEN; LEFT WING BOOST PUMP PB: ON.
25. When pressing the TEST PB in fire protection panel (overhead), which of the following lights is ON but only as a lamp test. a. FIRE PB (RED). b. SQUIB (WHITE). c. DISCH (AMBER). d. MASTER WARNING (RED).
26. In the event of a fire in any engine or APU, how is the extinguisher bottle discharged in the corresponding engine or APU. a. Releasing the FIRE PB after pressing the AGENT PB. b. Pressing the AGENT PB after releasing the FIRE PB. c. Just by pressing the corresponding FIRE PB. d. Just by pressing the corresponding AGENT PB.
27. What is indicated if the SQUIB white light in the fire protection panel (FIRE PB released out) is ON. a. Automatic discharge of the corresponding extinguisher bottle. b. Manual discharge of the corresponding extinguisher bottle. c. The arming and continuity of the bottle explosive charge circuit. d. None of the above.
28. During a smoke condition in the avionics compartment, what happens when the EXTRACT FAN PB (ventilation panel) is set in OVRD (override) position. a. The blower fan continues to run and the air conditioning system is used as air source to ventilate the avionics compartment. b. The blower fan is stopped and the air conditioning is used as air source to ventilate avionics compartment. c. The extract fan is stopped and the air in the avionics compartment is dumped through the extract valve. d. The extract fan continues to run and the air in avionics compartment is dumped through the extract valve.
29. Which component monitors the smoke detectors installed in the lavatories air extraction duct. a. FDU (fire detection unit). b. SDCU (smoke detection control unit). c. AEVC (avionics equipment ventilation computer). d. All of the above.
30. Which component from the fire extinguishing system detects when any of the fire extinguisher bottles has been manually or thermally discharged (amber DISCH light ON). a. Loop A/Loop B. b. Pressure switch. c. Squib. d. FDU.
31. In the event of an APU fire in flight, the autoextinguishing system will initiate the emergency shutdown sequence and automatically discharge the APU fire extinguisher bottle. a. True. b. False.
32. What kind of test is performed when the TEST PB in the fire protection panel is pressed. a. Fire detection system loop circuits continuity and FDU integrity. b. Explosive charge circuits integrity in the fire extinguisher bottles. c. Fire warnings and indications in the cockpit. d. All of the above.
33. Which one of the responder switches in the fire loop detectors (normally closed) has the function of sensing an internal pressure loss in the sensor and trigger a fault condition for the loop in the cockpit. a. Alarm switch. b. Integrity switch.
34. What result is obtained if any of the FDU (engines or APU) senses a Loop A & Loop B FAULT condition (failure of both loops) with the failures of the loops occurring within a time frame of less than 5 seconds. a. Fire warnings (Fire PB ON, Master warning, Continuos repetitive chime, ECAM warning, etc.). b. Loop fault (only ECAM amber message). c. Fire Det fault (ECAM amber message, Master caution, single chime, etc.). d. There is no consequences in the cockpit.
1. Which is the main function of the FDU (fire detection unit) for the engines and APU: e. To control the fire extinguishing system. f. To control the fire detection system. g. To control the fire detection and fire extinguishing system. h. None of the above.
1. En la página de Fuel de ECAM cuando se inicializa la indicación de FUEL USED de los motores nuevamente a Cero: a. Al apagar completamente el sistema. b. Al siguiente Refueling del avión. c. Al siguiente arranque de motores (engine start). d. Después del apagado de los motores (engine shutdown).
2. Con la siguiente configuración: avión en tierra, slats extendidos, MODE SEL PB en fuel control panel en AUTO mode; que fuente alimenta los motores 1minuto después del engine start? a. El center tank. b. Los wing tank inner cells. c. Los wing tanks outer cells. d. Todos los anteriores.
3. Cual es la función de las intercell transfer valves cuando éstas se accionan: a. Permitir el flujo de combustible del center tank hacia los inner cells. b. Permitir el flujo de combustible de los inner cells hacia los outer cells. c. Permitir el flujo de combustible de los outer cells hacia los vent surge tanks. d. Permitir el flujo de combustible de los outer cells hacia los inner cells.
4. Cual es la función de los pressure switches de las boost pumps de los wing tanks y center tank. a. Controlar el encendido y apagado automático de las boost pumps. b. Determinar cuando existe una diferencia de presión suficiente para abrir las transfer valves. c. Enviar la señal de LOW PRESSURE Warning a ECAM cuando la bosst pump falla.
5. Cual es el estado de las fuel boost pumps de los wing tanks cuando las boost pumps del center tank alimentan a los motores: a. Encendidas, ya que funcionan todo el tiempo. b. Encendidas, ya que ellas tambien alimentan a los motores mientras el center tank lo hace. c. Apagadas, ya que las boost pumps del center tank tienen prioridad. d. Apagadas, ya que solo funcionan cuando el center tank está vacío.
6. Que componente del sistema de combustible permite alimentar cualquier motor desde cualquier tanque: a. LP Valve. b. By-pass suction valves. c. Sequence valves. d. Crossfeed valve.
7. Que componente del sistema de combustible permite interrumpir la alimentación de los motores durante el shutdown, ya sea normal o por condiciones de fuego en los motores o APU (emergency shutdown): a. LP Valve. b. By-pass suction valves. c. Sequence valves. d. Crossfeed valve.
8. Cual es la función del pressure switch de la boost pump del APU. a. Controlar el encendido y apagado automático de la APU boost pump. b. Determinar cuando existe una diferencia de presión suficiente para abrir las transfer valves. c. Enviar la señal de LOW PRESSURE Warning a ECAM. d. Ninguna de las anteriores.
9. Que componente del sistema de combustible permite limitar la salida de presión de las boost pumps de los wing tanks para dar prioridad a las boost pumps del center tank: a. LP Valve. b. By-pass suction valves. c. Sequence valves. d. Crossfeed valve.
10. Que componente del sistema de Refuel/Defuel permite evitar la formación de turbulencia y electricidad estática cuando el combustible es descargado dentro de los tanques al dar servicio de combustible al avión. a. Refuel valve. b. Diffusers. c. Defuel/Transfer valve. d. Air inlet valve. e. Drain valve.
5. Que componente del sistema de combustible permite alimentar los motores por gravedad cuando no tenemos fuentes de presión (boost pumps) disponibles: a. LP Valve. b. By-pass suction valves. c. Sequence valves. d. Crossfeed valve.
10. Que fuente del sistema de combustible permite alimentar los motores por gravedad cuando no tenemos fuentes de presión (boost pumps) disponibles: a. El center tank. b. Los wing tank inner cells. c. Los wing tanks outer cells. d. Todos los anteriores.
1. Cuando los sistemas están operando normal y se da una situación de baja presión en el sistema verde: a. El sistema amarillo transfiere fluido a 3000 PSI por medio de la PTU para presurizar el sistema verde. b. La electric pump del sistema azul transfiere fluido a 3000 PSI por medio de la PTU para presurizar el sistema verde. c. La electric pump del sistema azul transfiere mecánicamente solo potencia hidráulica por medio de la PTU para presurizar el sistema verde, no hay transferencia de fluido. d. El sistema amarillo transfiere mecánicamente solo potencia hidráulica por medio de la PTU para presurizar el sistema verde, no hay transferencia de fluido.
2. Si falla la electric pump del sistema Azul en vuelo, el sistema hidráulico Azul: a. Se pierde durante del resto del vuelo. b. Puede ser recobrado extendiendo la RAT. c. Puede ser recobrado por medio de la PTU. d. (b) y (c) son correctas.
3. Que componente de los sistemas hidráulicos se encarga de enviar el valor de la presión de operación del sistema al ECAM a través de los SDAC’s. a. La pressure relief valve. b. El pressure transducer. c. La leak measurement valve. d. El hydraulic accumulator.
4. Bajo condiciones normales de operación y el PTU PB en posición AUTO, la power transfer unit funciona automáticamente: a. Al perderse el sistema Azul. b. Cuando la diferencia de presión entre los sistemas Azul y Amarillo es de 500 PSI. c. Cuando la diferencia de presión entre los sistemas Verde y Amarillo es de 500 PSI. d. Manualmente colocando el PTU PB en la posición ON.
5. Cuando se extenderá automáticamente la RAT en tierra: a. Cuando se da una pérdida completa de los sistemas hidráulicos. b. Cuando la presión de salida de la electric pump del sistema azul se encuentre abajo de 1450 PSI. c. Cuando se da la pérdida de los generadores eléctricos principales (Engines & APU). d. Ninguno de las anteriores.
6. Cual es el propósito de la hand pump del sistema amarillo: a. Permitir presurizar el sistema amarillo si la engine driven pump & electric pump fallan. b. Permitir presurizar el sistema verde a través de la PTU en tierra. c. Permitir la operación de las cargo doors en tierra. d. Ninguna de las anteriores.
7. En tierra (Blue elect pump PB en posición AUTO), que condición provocará que el sistema azul se encuentre presurizado (blue electric pump energizada y funcionando): a. La red eléctrica del avión energizada por al menos un Engine generator. b. La red eléctrica del avión energizada por el APU generator. c. La red eléctrica del avión energizada por el EXT PWR. d. La red eléctrica del avión con EXT PWR Available.
8. Cual es el propósito de las engine fire valves de los sistemas hidráulicos del avión. a. Interrumpir el paso de fluido hidráulico hacia las electric pumps de los sistemas azul/amarillo al liberar el Fire PB correspondiente. b. Interrumpir el paso de fluido hidráulico hacia las engine driven pumps de los sistemas azul/amarillo al liberar el Fire PB correspondiente. c. Interrumpir el paso de fluido hidráulico hacia las electric pumps de los sistemas verde/amarillo al liberar el Fire PB correspondiente. d. Interrumpir el paso de fluido hidráulico hacia las engine driven pumps de los sistemas verde/amarillo al liberar el Fire PB correspondiente.
9. Durante el arranque del primer motor (engine start) y operación de las cargo doors, la PTU: a. Funciona automáticamente para transferir potencia hidráulica entre los sistemas amarillo y verde. b. Es chequeada automáticamente. c. No opera, ya que su funcionamiento se encuentra inhibido (no hay transferencia de potencia hidráulica). d. Ninguna de las anteriores.
10. Cual es el propósito de las priority valves de los sistemas hidráulicos: a. Mantener la alimentación de presión hacia los usuarios esenciales cuando la presión del sistema es baja. b. Mantener la alimentación de presión hacia los usuarios de alta demanda cuando la presión del sistema es baja. c. Regulan la alimentación de presión hacia todos los usuarios cuando la presión del sistema es baja. d. Aislan a los usuarios esenciales del sistema correspondiente.
11. Que componente de los sistemas hidráulicos se encarga de cubrir demandas transitorias de presión y amortiguar pequeños cambios de presión y caudal. a. La pressure relief valve. b. El pressure transducer. c. La leak measurement valve. d. El hydraulic accumulator.
12. Con el avión en tierra (BLUE ELECT PUMP PB en posición AUTO, motores apagados) y con la red eléctrica energizada con EXT PWR, como podemos presurizar el sistema azul: a. Colocando el BLUE ELECT PUMP PB (hidraulic control panel) en la posición ON. b. Colocando el BLUE PUMP OVRD PB (maintenance panel) en la posición ON. c. Extendiendo la RAT. d. A través de la electric pump del sistema amarillo y la PTU.
13. La RAT (ram air turbine) se extiende automáticamente en el aire para presurizar el sistema azul, cuando se pierden totalmente todos los sistemas hidráulicos (Blue, green & yellow). a. Verdadero. b. Falso.
14. Cual es el propósito principal de mantener presurizados los reservorios a 50 PSI nominales: a. Mantener los reservorios siempre llenos de fluido. b. Evitar que el fluido se mueva dentro del reservorio durante maniobras del avión. c. Permitir drenar los reservorios más rápidamente. d. Mantener una alimentación positiva del reservorio a las bombas y evitar cavitación de éstas.
15. Cual es el panel que permite dar servicio de fluido hidráulico a todos los reservorios (blue, green & yellow): a. Yellow ground service panel. b. Green ground service panel. c. Blue ground service panel.
16. Cual es la fuente normal de bleed air del sistema de presurización de reservorios hidráulicos. a. La 8th etapa de HPC del motor 1. b. El sistema neumático a la salida del precooler. c. El APU. d. Carro externo a través de un ground connector.
17. Cuando los motores se encuentran apagados (no hay fuentes de presión disponibles en el sistema), como se encuentran los reservorios hidráulicos. a. Sin presurizar. b. Presurizados a 50 PSI nominales. c. Presurizados a 3000 PSI nominales (presión del sistema). d. Ninguna de las anteriores.
18. Que componente de los sistemas hidráulicos se encarga de proteger el sistema contra sobrepresiones, enviando la salida de presión directamente al retorno cuando la presión del sistema alcanza 3436 PSI. a. La pressure relief valve. b. El pressure transducer. c. La leak measurement valve. d. El hydraulic accumulator.
19. Que fluido de los tres sistemas hidráulicos se monitorea su para dar el ECAM warning (reservoir overheat) cuando su temperatura alcanza los 95°C. a. El fluido de enfriamiento y lubricación de las bombas (case drain). b. El fluido de suministro hacia las bombas. c. El fluido de suministro hacia la PTU. d. El fluido de retorno.
20. Que componente de los sistemas hidráulicos permite interrumpir el paso de fluido a la salida de la bomba y así aislar los usuarios principales de los sistemas hidráulicos durante operaciones de mantenimiento para encontrar componentes defectuosos (con fugas). a. La pressure relief valve. b. El pressure transducer. c. La leak measurement valve. d. El hydraulic accumulator.
1. Under normal operating conditions and with a low pressure condition in the green system: a. Yellow system transfers fluid at 3000 PSI through the PTU to pressurize the green system. b. The blue electric pump transfers fluid at 3000 PSI through the PTU to pressurize the green system. c. The blue electric pump mechanically transfers hydraulic power through the PTU to pressurize the green system, there is no fluid transfer. d. Yellow system mechanically transfers hydraulic power through the PTU to pressurize the green system, there is no fluid transfer.
2. If the blue electric pump fails during a flight, the blue hydraulic system: a. Is lost for the rest of the flight. b. Can be recovered by extending the RAT. c. Can be recovered by means of the PTU. d. (b) y (c) are correct.
3. Which component from the hydraulic systems sends the value of system operating pressure to ECAM through the SDAC’s. a. Pressure relief valve. b. Pressure transducer. c. Leak measurement valve. d. Hydraulic accumulator.
4. Under normal operating conditions and the PTU PB in AUTO position, la power transfer unit works automatically: a. When blue hydraulic system is lost. b. When the pressure difference between blua and yellow system is 500 PSI. c. When the pressure difference between green and yellow is 500 PSI. d. Only manually setting the PTU PB in ON position. .
5. When will the RAT be extended automatically on ground: a. With a complete lost of all hydraulic systems. b. When the pressure output from blue electric pump is below 1450 PSI. c. With a complete lost of main electrical generators (Engines & APU). d. None of the above.
6. What is the main purpose of yellow system hand pump: a. Allow the pressurization of the yellow system if the engine driven pump & electric pump fail. b. Allow the pressurization of green system through the PTU on ground. c. Allow the operation of cargo doors on ground. d. None of the above.
7. On ground (Blue elect pump PB in AUTO position), what condition will cause the blue system to be pressurized (blue electric pump energized and running): a. Aircraft electrical network energized by at least one engine generator. b. Aircraft electrical network energized by APU generator. c. Aircraft electrical network by EXT PWR. d. Aircraft electrical network with EXT PWR Available.
8. What is the main purpose if the engine fire valves in the aircraft hydraulic systems. a. Shut off the flow of hydraulic fluid to the blue/yellow electric pumps when the corresponding Fire PB is released. b. Shut off the flow of hydraulic fluid to the blue/yellow engine driven pumps the corresponding Fire PB is released. c. Shut off the flow of hydraulic fluid to the green/yellow electric pumps when the corresponding Fire PB is released. d. Shut off the flow of hydraulic fluid to the green/yellow engine driven pumps when the corresponding Fire PB is released.
9. During the first engine start and cargo doors operation, the PTU: a. Runs automatically to transfer hydraulic power between green and yellow system. b. Is automatically tested. c. Is inhibited (Does not run). d. None of the above.
10. Which is the main purpose of the priority valves in the hydraulic systems: a. Cuts off hydraulic power to heavy load users under low hydraulic pressure conditions. b. Maintain hydraulic power to heavy load users under low hydraulic pressure conditions. c. Regulate the hydraulic power to all users under low hydraulic pressure conditions. d. Cuts off hydraulic power to essential users under low hydraulic pressure conditions.
11. Which component from the hydraulic systems covers transient pressure demands and dampens small pressure and flow changes. a. Pressure relief valve. b. Pressure transducer. c. Leak measurement valve. d. Hydraulic accumulator.
12. With the aircraft on ground (BLUE ELECT PUMP PB in AUTO position, engines not running) and the electrical network powered by EXT PWR, how is it possible to pressurize the blue hydraulic system: a. Setting the BLUE ELECT PUMP PB (hydraulic control panel) in ON position. b. Setting the BLUE PUMP OVRD PB (maintenance panel) in ON position. c. Extending the RAT. d. Through the yellow electric pump and the PTU.
13. The RAT (ram air turbine) is extended automatically in flight to pressurize the blue hydraulic system, when all hydraulic systems are lost (Blue, green & yellow). a. True. b. False.
14. What is the purpose of keeping the reservoirs pressurized at nominal 50 PSI: a. Keep the reservoirs always full of fluid. b. Prevent the movement of fluid inside the reservoirs during aircraft maneuvers. c. Allow the drainage of the reservoirs more easily. d. Keep a positive supply of fluid from the reservoir to the pumps to prevent cavitation.
15. Which panel allows the hydraulic fluid service to all reservoir (blue, green & yellow): a. Yellow ground service panel. b. Green ground service panel. c. Blue ground service panel.
16. Which is the normal source of bleed air for the hydraulic reservoir pressurization system. a. 8th stage from HPC of engine 1. b. The pneumatic system downstream of the precooler. c. APU. d. External cart.
17. When the engines are not running (no pressure sources available), which is the state of the hydraulic reservoirs. a. Not pressurized. b. Pressurized at nominal 50 PSI. c. Pressurized at nominal 3000 PSI (system pressure). d. None of the above.
18. Which component from the hydraulic systems protects the system against overpressures, sending the excess pressure directly to return when system pressure reaches 3436 PSI. a. Pressure relief valve. b. Pressure transducer. c. Leak measurement valve. d. Hydraulic accumulator.
19. Which hydraulic fluid is monitored to trigger an ECAM warning (reservoir overheat) when its temperature reaches 95°C. a. Pumps cooling and lubrication fluid (case drain). b. Pump supply fluid. c. PTU supply fluid . d. Return fluid.
20. Which component from the hydraulic systems shuts down the flow of hydraulic fluid downstream of the pump pressure output, to isolate the main users of the hydraulic systems and troubleshoot defective components. a. Pressure relief valve. b. Pressure transducer. c. Leak measurement valve. d. Hydraulic accumulator.
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