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THIS IMAGE SHOWS arandelas. WASHERS. RIVETS. BOLTS.

THIS IMAGE SHOWS flaps. THE FLAPS. THE RUDDER. THE SLATS.

THIS IMAGE SHOWS tren de nariz. THE MLG. THE NLG. THE RAT.

THIS IMAGE SHOWS fap. THE FLIGHT ATTENDANT PANEL. THE ECAM. THE HEADS UP DISPLAY.

I CAN`T UNDERSTAND THIS ENGINEERING ORDER. WOULD YOU LIKE SOME HELP?. DON’T YOU KNOW?. I SUPPOSE YOU CAN.

WHAT SLIDE WILL YOU INSTALL FIRST?. I HOPE IT WAS RIGHT. WE CAN’T DECIDE. IS WASN’T VERY DIFFICULT.

WILL’D LIKE TWO TICKTEKS FOR TOMORROW’S EARLY MORNING FLIGHT. HOW MUCH DID YOU PAY?. AFTERNOON AND EVENING. I’LL JUST CHECK FOR YOU.

SHALL WE GO TO THE GYM AFTER WORK?. TOO. SO. VERY.

THE COMPANY NEEDS TO DECIDE ________ AND FOR ALL WHAT ITS SAFETY POLICY IS ON THIS ISSUE. ONCE. FIRST. FINALLY.

DON’T PUT THE LUBRICANT BOTTLE ON THE _________ OF THE BENCH -SOMEONE WIL KNOCK IT OFF. OFFSIDE. BOUNDARY. EDGE.

I’M SORRY- I DIDN’T _________ TO DISTRACT YOU. HOPE. THINK. MEAN.

________ TIRED MELISSA IS WHEN SHE GETS HOME FROM THE AIRPORT, SHE ALWAYS MAKES TIME TO CHANGE CLOTHES BEFORE ENTERING THE HOUSE. NO MATTER HOW. HOWEVER MUCH. ALTHOUGH.

IT WAS ONLY TEN DAYS AGO _______ SHE STARTED HER NEW JOB AT THE WAREHOUSE. THEN. THAT. AFTER.

THE WHEEL SHOP DIDN’T HAVE THE SPACERS I REQUIRED, BUT THEY’VE ________ SOME WITH AOG PRIORITY. BOOKED. ORDERED. COMMANDED.

HAVE YOU GOT TIME TO DISCUSS YOUR WORK NOW OR ARE YOU________ TO LEAVE?. THINKING. PLANNED. ABOUT.

SHE CAME TO WORK AS A SUPERVISOR HERE _________ A MONTH AGO. ALMOST. BEYOND. QUITE.

I LEFT MY LAST JOB BECAUSE I HAD NO _____ TO TRAVEL. PLACE. POSITION. OPPORTUNITY.

I’D RATHER YOU __________ TO HER WHY WE CAN’T DELIVER THIS TASK ON TIME. WOULD EXPLAIN. EXPLAINED. TO EXPLAIN.

BEFORE MAKING A DECISION, THE LEADER CONSIDERED ALL ___________ OF THE ARGUMENT. SIDES. FEATURES. SHADES.

THIS NEW PRINTER IS RECOMMENDED AS BEING ________ RELIABLE. GREATLY. HIGHLY. STRONGLY.

THIS IMAGE SHOWS pitot. A. VHF ANTENNA. B. PITOT TUBE. C. RAM AIR TURBINE.

THIS LOUD NOISE IS SOMEWHERE IN THE ___________ OF THE NORTH AIRPORT FACILITIES. QUARTER. VICINITY. DISTRICT.

THE NEW TOWBARLESS TRACTOR IS A ___________ VEHICLE. IT TURNS __________. FAST-FASTLY. FASTLY-FAST. FAST-FAST.

THE DISCREPANCY FORMS ___________. WHERE CHECKED ACCORDING WITH THE PROCEDURES. WHERE CHECKED IN ACCORDING WITH THE PROCEDURES. WHERE CHECKED ACCORDING TO THE PROCEDURES.

CHOOSE THE ONLY SENTENCE THAT IN WRITTEN CORRECTLY. ROLL ROYCE HAS DEVELOPED THE TRENT FAMILY TO MEET THE MARKET DEMAND. ROLL ROYCE HAS DEVELOPED THE TRENT FAMILY TO MEETING THE MARKET DEMAND. ROLL ROYCE HAS DEVELOPED THE TRENT FAMILY MEET THE MARKET DEMAND.

CHOOSE THE ONLY SENTENCE THAT IN WRITTEN CORRECTLY. EACH ENGINE TO HAVE ONE POWER PACK. EACH ENGINE HAVE ONE POWER PACK. EACH ENGINE HAS ONE POWER PACK.

CHOOSE THE ONLY SENTENCE THAT IN WRITTEN CORRECTLY. THE EEC HAS COMPLETE ITS POWER UP CHECKS (6% N2). THE EEC HAS COMPLETED ITS POWER UP CHECKS (6% N2). THE EEC HAS COMPLETING ITS POWER UP CHECKS (6% N2).

CHOOSE THE ONLY SENTENCE THAT IN WRITTEN CORRECTLY. THESE MEMBERS TO TRANSFER SHEAR LOADS FROM ONE COMPONENT TO ANOTHER. THESE MEMBERS TRANSFERS SHEAR LOADS FROM ONE COMPONENT TO ANOTHER. THESE MEMBERS TRANSFER SHEAR LOADS FROM ONE COMPONENT TO ANOTHER.

CHOOSE THE ONLY SENTENCE THAT IN WRITTEN CORRECTLY. DURING THE LAST NIGHT, THE LIGHTNING HIT THE RADOME FIRST. DURING THE LAST NIGHT, THE LIGHTNING HITTED THE RADOME FIRST. DURING THE LAST NIGHT, THE LIGHTNING HITS THE RADOME FIRST.

THE FMS DOES NAVIGATION AND PERFORMANCE CALCULATIONS FOR OPTIMUM FLIGHT PERFORMANCE. EL FMS REALIZA CALCULOS DE NAVEGACION Y ACTUACION PARA UN VUELO OPTIMO. EL FMS NO HACE CALCULOS DE NAVEGACION Y RENDIMIENTO PARA UN DESEMPEÑO OPTIMO DEL VUELO. EL FMS REALIZA CALCULOS DE NAVEGACION Y RENDIMIENTO PARA UN DESEMPEÑO OPTIMO DEL VUELO.

HYDRAULIC PRESSURE IS MONITORED IF THE AUTOPILOT SERVO NEEDS HYDRAULIC POWER. LA PRESION HIDRAULICA ES MONITOREADA SI EL SERVO DEL AUTOPILOT NECESITA PRESION HIDRAULICA. LA PRESION SERA MONITOREADA SI EL SERVO DEL AUTOPILOT NECESITARA PODER HIDRAULICO. LA PRESION HIDRAULICA ES MONITOREADA SI EL SERVO DEL AUTOPILOT NECESITA PODER HIDRAULICO.

AS THE ELVATOR ACCELERATES THERE IS AND ADDITIONAL FORCE WHICH INCREASES THE WEIGHT. A MEDIDA QUE EL ELEVADOR ACELERA HAY UNA FUERZA ADICIONAL QUE AUMENTA EL PESO. CUANDO EL ELEVADOR ACELERA HAY UNA FUERZA EXTRA QUE REDUCE EL PESO. A MEDIDA QUE EL ELVADOR ACELERA HAY UNA FUERZA ADICIONAL QUE DISMINUYE EL PESO.

ADDITIONAL FLIGHT INSTRUMENTS WHICH YOU WILL LEARN ABOUT IN THIS UNIT ARE THE VERTICAL SPEED INDICATOR, THE MACH METER AND THE TEMPERATURE INDICATORS. INSTRUMENTOS DE VUELO ADICIONALES QUE VAS APRENDER SOBRE ESTA UNIDAD SON EL INDICADOR DE VELOCIDAD VERTICAL, EL MEDIDOR DE MACH Y LOS INDICADORES DE PRESION. LOS INSTRUMENTOS DE VUELO ADICIONALES QUE APRENDISTE EN ESTA UNIDAD SON EL INDICADOR DE VELOCIDAD VERTICAL, EL MEDIDOR DE MACH Y LOS INDICADORES DE TEMPERATURA. LOS INSTRUMENTOS DE VUELO ADICIONAL QUE APRENDERAS EN ESTA UNIDAD SON EL INDICADOR DE VELOCIDAD VERTICAL, EL MEDIDOR DE MACH Y LOS INDICADORES DE TEMPERATURA.

READ THE TEXT TO ANSWER THE QUESTIONS THE FLIGHT CONTROL HYDRAULIC SUPPLY HER YOU CAN SEE HOW HYDRAULIC POWER FROM EACH OF THE THREE SYSTEMS IS DISTRIBUTED TO THE FLIGHT CONTROL CONSUMERS ON THE AIRBUS A320 HYDRAULIC POWER IS SUPPLIED VIA LEAK MEASUREMENT VALVES TO THE SURFACE WHICH CONTROL THE MOVEMENT OF THE AIRCRAFT AROUND THE THREE AXES AND VIA PRIORITY VALVES TO THE FLAPS AND THE LEADING EDGE DEVICES THE PRIORITY VALVES THE PRIORITY VALVES ARE PRESSURE OPERATE AND GIVE PRIORITY TO THE PRIMARY FLIGHTS CONTROLS. IN THIS EXAMPLE YOU CAN SEE THAT HYDRAULIC PRESSURE FROM THE GREEN SYSTEM FALLS. THE PRIORITY VALVE AUTOMATICALLY CLOSES AND CUTS OFF SUPPLY TO THE FLAPS AND THE LEADING EDGE DEVICES. CUTTING OF THESE LARGE CONSUMERS ALLOWS PRESSURE IN THE SYSTEM TO BUILD UP AGAIN AND PROVIDED ADEQUATE SUPPLY TO THE PRIMARY FLIGHT CONTROLS. WHEN THE PRESSURE IS RESTORED THE PRIORITY VALVE AUTOMATICALLY OPENS TO SUPPLY THE FLAPS AND THE LEADING EDGE DEVICES AGAIN. HOW IS HYDRAULIC POWER SUPPLIED TO THE SURFACES THAT CONTROL THE MOVEMENT OF THE AIRCRAFT AROUND THE THREE AXES?. VIA LEAK MEASUREMENT VALVES. THROUGH THE ELECTRICAL SYSTEM. THROUGH THE MAIN ENGINES.

WHAT HAPPENS TO THE PRIORITY VALVE WHEN THE HYDRAULIC PRESSURE FROM THE GREEN SYSTEM FALLS?. IT OPENS TO SUPPLY THE FLAPS AND LEADING EDGE DEVICES. IT AUTOMATICALLY CLOSES AND CUTS OFF SUPPLY TO THE FLAPS AND LEADING EDGE DEVICES. IT MAINTAINS THE CURRENT PRESSURE LEVELS. IT DEACTIVATES ALL PRIMARY FLIGHT CONTROLS.

WHEN ARE THE LEAK MEASUREMENT VALVES USED TO PERFORM CHECKS ?. WHEN THE AIRCRAFT IS ON THE GROUND. ONLY DURING EMERGENCIES. ONLY DURING ROUTINE MAINTENANCE. DURING FLIGHT.

WHY DOES THE PRIORITY VALVE CUT OFF SUPPLY TO THE FLAPS AND LEADING EDGE DEVICES WHEN THE HYDRAULIC PRESSURE FALLS?. TO ALLOW THE SYSTEM PRESSURE TO BUILD UP AGAIN AND PROVIDE ADEQUATED SUPPLY TO THE PRIMARY FLIGHT CONTROLS. TO REDUCE THE WEIGHT OF THE AIRCRAFT AND PROVIDE ADEQUATE SUPPLY TO THE PRIMARY FLIGHT CONTROLS. TO DEACTIVATE THE FLIGHT CONTROL SYSTEM. TO SAVE HYDRAULIC FLUID.

THE TEMPERATURE IN THE PNEUMATIC SYSTEM MUST NOT EXCEED ACCEPTABLE VALUES. A BUILT-IN PRECOOLER IS USED TO COOL THE ENGINE BLEED AIR TEMPERATURE. COOLING AIR IS TAKEN FROM THE ENGINE FAN DUCT. THE COOLING AIR IS SIMPLY FAN AIR. THE COOLING EFFECT DEPENDS ON THE MASS AND TEMPERATURE OF FAN AIR. YOY CAN PROBABLY GUESS THAT IN ORDER TO VARY THE COOLING EFFECT, THE MASS OF FAN AIR MUST ALSO BE VARIED. A FAN AIFR VALVE USED TO ALLOW MORE OR LESS FAN AIR TO PASS THE PRECOOLER. WHAT MECHANISM IS USED TO ADJUST THE COOLING EFFECT OF THE PRECOOLER, AND HOW DOES IT ACHIEVE THIS ADJUSTMENT ?. A TEMPERATURE SENSORS ADJUSTS THE COOLING EFFECT BY CHANGING THE TEMPERATURE OF THE ENGINE BLEED AIR. THE COOLING EFFECT IS ADJUSTED BY ALTERING THE SPEED OF THE ENGINE FAN. THE COOLING EFFECT IS CONTROLLED BY A PRESSURE REGULATOR THAT CHANGES THE PRESSURE OF THE FAN AIR. THE FAN AIR VALVE IS USED TO VARY THE MASS OF FAN AIR PASSING THROUGH THE PRECOOLER, THERE BY ADJUSTING THE COOLING EFFECT.

THE SKINS PANELS FORM THE EXTERIOR SURFACE OF THE WING. AND THEY ARE REINFORCED BY STRINGERS ON THE INNER SURFACE OF THE SKIN. THE THICKNESS OF THE WING SKIN PANEL IS TAPERED DEPENDING ON THE JOINTS AND OPENINGS. THE UPPER SKIN PANEL CARRIES MAINLY COMPRESSION LOADS TO THE FUSELAGE STRUCTURE AND IS MADE OF A ZINC ALUMINUM ALLOW THE LOWER SKIN PANEL CARRIES MAINLY TENSION LOADS TO THE FUSELAGE STRUCTURE AND IS MADE OF A COPPER ALUMINUM ALLOY. WHY IS IT SIGNIFICANT THAT DIFFERENT MATERIALS ARE USED FOR THE UPPER AND LOWER PANELS, AND HOW DOES THIS CHOICE RELATE TO THE TYPE OF LOADS EACH PANELCARIES?. THE UPPER SKIN PANEL IS MADE OF A ZINC ALUMINUM ALLOY BEACAUSE IT PRIMARILY CARRIES TENSION LOADS, WHICH REQUIREA MATERIAL CAPABLE OF STRETCHING WITHOUT BREAKING. THE LOWER SKIN PANEL IS MADE OF A COPPER ALUMINUM ALLOW BECAUSE IT MAINLY CARRIES COMPRESSION LOADS, WHICH NECESSITATE A MATERIAL THAT CAN WITHSTAND CRUSHING FORCES. BORN THE UPPER AND LOWER SKIN PANELS ARE MADE ON THE SAME ALLOY TO UNIFORMY DISTRIBUTE LOADS ACROSS THE WING STRUCTURE , BUT THE THICKNESS VANES TO MANAGE JOINTS AND OPENINGS EFFECTIVELY. THE MATERIAL CHOICE FOR THE UPPER AND LOWER SKIN PANELS IS ARBITRARY, AND THE PRIMARY CONCERN IS THE OVERALL WEIGHT REDUCTION OF THE WING STRUCTURE RATHER THAN LOAD MANAGEMENT. THE UPPER SKIN PANEL IS MADE OF A ZINC ALUMINUM ALLOW TO EFFICIENTLY CARRY COMPRESSION LOADS, WHICH ARE PREDOMINANT ON THE UPPER SURFACE DUE TO THE AERODYNAMIC FORCES DURING FLIGHT. THE LOWER SKIN PANEL IS MADE OF A COPPER ALUMINUM ALLOY TO HANDLE TENSION LOADS , AS THE LOWER SURFACE EXPERIENCES PULLING FORCES. THIS MATERIAL DIFFERENTIATION IS CRUCIAL FOR OPTIMIZING THE STRUCTURAL INTEGRITY AND PERFORMANCE OF THE WING.

THE OIL FILTER HAS AN INDICATOR BUTTOM TO MONITOR FOR FILTER CLOGS. WHEN THERE IS A PRESSURE DIFFERENCE OF MORE THAN 30 TO 40 PSI ACROSS THE FILTER AND THE OIL TEMPERATURE IS MORE THAN 21 DEGREES CELSIUS, THE INDICATOR BUTTON EXTENDS. UNDER WHAT CONDITIONS DOES THE INDICATOR BUTTON ON THE OIL FILTER EXTEND, AND WHY ARE THESE SPECIFIC CONDITIONS IMPORTANT FOR MONITORING FILTER CLOGS?. THE INDICATOR BUTTON EXTENDS WHEN THE OIL TEMPERATURE EXCEEDS 21 DEGREES CELSIUS TO ENSURE THE OIL REMAINS COOL. THE INDICATOR BUTTON EXTENDS WHEN THE PRESSURE DIFFERENCE ACROSS THE FILTER IS LESS THAN 30 TO 40 PSI, INDICATING LOW PRESSURE. THE INDICATOR BUTTON EXTEND WHEN THERE IS A PRESSURE DIFFERENCE OF MORE THAN 30 TO 40 PSI ACROSS THE FILTER AND THE OIL TEMPERATURE IS MORE THAN 21 DEGREES CELSIUS, INDICATING POTENTIAL FILTER CLOGS THAT COULD AFFECT ENGINE PERFORMANCE. THE INDICATOR BUTTON EXTENDS WHEN THE OIL TEMPERATURE IS LESS THAN 21 DEGREES CELSIUSTO PREVENT THE OIL FROM BECOMING TOO COLD.

WHEN YOU PUSH AND HOLD THE SYSTEM ANNUNCIATOR LIGHTS, THE RECALL SIGNAL GOES TO ALL THE COMPONENTS WHICH CAUSE THE LIGHTS ON THE SYSTEM ANNUNCIATORS TO COMO ON. THIS CAUSES ALL THE LIGHTS ON THE SYSTEM ANNUNCIATORS TO COMO ON. WHEN YOU REALEASE THE SYSTEM ANNUNCIATORS LIGHTS. THE SYSTEM ANNUNCIATOR LIGHTS SHOW ONLY THE SYSTEM WHICH HAVE FAULTS. WHAT IS THE PURPOSE OF PUSHING AND HOLDING THE SYSTEM ANNUNCIATOR LIGHTS?. PUSHING AND HOLDING THE SYSTEM ANNUNCIATOR LIGHTS SENDS A RECALL SIGNAL TO ALL COMPONENTS, CAUSING ALL ANNUNCIATOR LIGHTS TO COME ON. PUSHING AND HOLDING THE SYSTEM ANNUNCIATOR LIGHTS TURNS OFF ALL THE SYSTEM LIGHTS, HELPING TO CONSERVE POWER. PUSHING AND HOLDING THE SYSTEM ANNUNCIATOR LIGHTS RESETS ALL THE SYSTEM COMPONENTS TO THEIR DEFAULT STATE. PUSHING AND HOLDING THE SYSTEM ANNUNCIATOR LIGHTS ACTIVATES THE EMERGENCY LIGHTING SYSTEM FOR THE AIRCRAFT.

WHEN YOU PUSH THE FAULT/INOP TEST SWITCH, FAULTS ARE SIMULATED TO DO A CHECK OF THE CIRCUIT ABILITY TO DETECT A FAULT. IF THE CIRCUITS OPERATE CORRECTLY, ALL LIGHTS ON THE FRONT PANEL COME ON, IF A LIGHT DOES NOT COME ON, IT SHOWS A FAULTY CIRCUIT OPERATION. THE FAULT DISPLAY LIGHTS SHOW THE TYPE OF FAULT AND THE DETECTOR LOCATION. WHAT DOES IT INDICATE INDICATE IF A LIGHT DOES NOT COME ON WHEN WHEN YOU PUSH THE FAULT/INOP TEST SWITCH, AND HOW DOES THE SYSTEM PROVIDE INFORMATION ABOUT THE FAULT?. IT INDICATES THAT THE CIRCUIT IS FUNCTIONING CORRECTLY, AND THE FAULT DISPLAY LIGHTS SHOW THE SYSTEM STATUS. IT INDICATES A FAULTY CIRCUIT OPERATION, AND THE FAULT DISPLAY LIGTHS SHOW THE TYPE OF FAULT AND DETECTOR LOCATION. IT INDICATES THAT THE TEST SWITCH IS NOT WORKING PROPERLY, AND THE FAULT DISPLAY LIGHTS SHOW THE BATTERY STATUS. IT INDICATES NORMAL OPERATION, AND THE FAULT DISPLAY LIGHTS SHOW THE POWER LEVELS.

MLG IS LOCATED. BETWEEN FWD CARGO COMPT AND NWW. IN FRONT OF AFT E/E. AMONG AC BAY.

THE VALVE CONTROL UNIT _______________ THE RDC. RECEIVES DATA FROM. BYPASSES. FEED.

WHAT IS THE MAIN ADVANTAGE OF GE’S CONNECTED FLIGHT MANAGEMENT SYSTEM (FMS)?. GREATER GAINS IN EFFICIENCY AND ECONOMY FOR INDIVIDUAL FLIGHTS. ONBOARD HIGH BANDWIDTH CONNECTIVITY. POWERFUL FLEET MANAGEMENT SOLUTIONS IN EVERY PHASE ON FLIGHT.

GE AVIATION IS WORKING TO IMPROVE. FLIGHT DATA FOR ANALISYS DURING THE FLIGHT. FLIGHT DATA FOR ANALISYS IN ROUTE OR POST FLIGHT. FLIGHT DATA ONLY DURING THE FLIGHT.

HOW DOES THE CONNECTED FMS REDUCE PILOT WORKLOAD?. BY ENABLING PRE-FLIGHT TASK TO HAPPEN OFF AIRCRAFT. BY IMPROVING SITUATIONAL AWARENESS FOR THE PILOT AND DISPATCH. BY PROVIDING ACCESS TO ATC INFORMATION.

WHAT IS THE LARGEST POTENTIAL FOR GAINS AND OPERATIONAL EFFICIENCIES?. IMPROVED AIRCRAFT USAGE AND ROUTE OPTIMIZATION. FUEL SAVINGS AND IMPROVED FLEET OPERATIONS AND MAINTENANCE. REAL-TIME ANALYTICS.

WHAT DOES GE AVIATION PROVIDE TO APP DEVELOPERS TO LEVERAGE THE POWER OF DATA ACCESS?. FLIGHT MANAGEMENT SYSTEM SOFTWARE MODULES. ONBOARD HIGH BANDWIDTH CONNECTIVITY. CONNECTED FMS SOFTWARE DEVELOPMENT KIT.

Can I park the Genie telescopic boom lift here?. A. It’s the same place. B. Sorry, I did that. C. Only for haft an hour.

If the windows pane__broken, the cabin mechanics___it. A. Was - would replaced. B. Were not - not would replaced. C. Is - must to replace.

Figura: The ground strap is... A. Riveted to the bolt. B. Attached to the bolt. C. Built in the bolt.

If a false caution/warning is determined... A. Aircraft crew must check the system/components condition. B. Aircraft dispatch is not allowed. C. Aircraft dispatch is allowed.

Aircraft dispatch conditions are considered to be normal. A. If either the sliding window or the fixed window heating is faulty. The failure is shown amber on the EWD. B. On the EWD, the failure will appear amber when both sliding and fixed windows heating is faulty. C. On the EWD, the failure will appear amber when one window heating is faulty.

These are engine ( foto de motor palas). A. IDGs. B. Vanes. C. Blades.

Next generation aircraft will demand_________ 4 times more power than today. A. Up to. B. For. C. Until.

The APU page appears during the APU start sequence and it will be replaced by the DOOR/OXY page 10 seconds after de APU start sequence. The engine page appears during the engine start sequence and it will replaced by the WHEEL page after the engine start sequence. A. La página de APU aparece durante la secuencia de la partida del APU y será reemplazada por la página de DOOR/OXY 10 segundos después de la secuencia de la partida del APU. La página de ENG aparece durante la secuencia de partida del motor y será reemplazada por la página de WHEEL después de la secuencia de partida del motor. B. La página de APU aparece durante la partida de la secuencia de la APU y reemplazará la página de DOOR/OXY 10 segundos después de la partida de la secuencia de la APU la página de ENG aparece durante la partida de la secuencia del motor y reemplaza la página de WHEEL después del inicio de la secuencia del motor.

The passengers Walker over it (foto de pasillo de pasajeros) l. A. Sidewall Panel. B. Floor carpet. C. Arm rest.

The hydraulic braking operation is identical for automatic braking, manual braking and inflight braking. Note that during inflight braking, anti-skid function is inhibited by the BSCU. Normal braking and anti-skid regulation are electrically controlled by the Braking and Steering Control Unit. A. The BSCU controls normal braking hydraulically. B. The BSCU controls normal braking electrically. C. The BSCU inhibits inflight braking.

MEL section 1 can be used to identify A. The corresponding MEL ENTRY point. A. The TSM action. B. The inopertaive components. C. The alternative to TSM actions.

Video : In the begining of the video the passenger was upset for missing his flight connection to attend.... A. His daughter's wedding. B. A medical appointment. C. A business Meeting.

This is ( foto de avión con deslizador extendido). A. A floate. B. A slide. C. A raft.

Would you mind____these screens a wipe before installing them?. A. Gived. B. To giving. C. Giving. D. Gave.

If the elevators________the nose______. A. Goes down - Goes down. B. Go down - goes down. C. Will go down - go down.

Choose the correct alternative. A. The surface was cutted in accordance with EO. B. The surface was cut in accordance with EO. C. The surface was cuted in according to the EO.

the air fan modulating valve opens and closes in response to pressure signals from the air temperature sensor. A. El aire del fan está modulando la válvula para que se abra y cierre en respuesta a las señales de presión desde el sensor de temperatura del aire del fan. B. La válvula moduladora del aire del fan se abre y cierra en respuesta a las señales de presión desde el sensor de temperatura del aire del fan.

Once the plane is in the air, you can___ your seat belts ir you wish. A. Unfasten. B. Unlock. C. Untie. D. Undress.

It wasn’t a bad crash and___damage was done to the fork lift. A. Light. B. Mere. C. Little. D. Small.

I was loocking forward____engine 2 for test, but the whole operation was cancelled. A. Running. B. To run. C. To have run. D. To running.

False cautions/warnings can be determined by... A. Troubleshooting. B. MEL section 01. C. Abnormal/Emergency Procedure. D. ATA Chapter of section 01.

Dual precision resolvers sense thrust lever position and provide electrically isolated inputs. A. Thrust lever position is detected by dual precision resolvers. B. Electrically isolated inputs are sensed by dual precision resolvers. C. Thrust lever position is provided by dual precision resolvers.

When a caution/warning and "not applicable" dispatch condition column apperar together. A. MEL in not to be consulted. B. MEL item number is the MEL entry point. C. MEL is to be consulted. D. Aircraft dispatch is allowed.

An intelligent smart grid will be used to optimize... A. Electrical power supply and demand. B. Fuel cell and batteries. C. Auxiliary and emergency power.

GE expects to look after the aircraft's. A. Delays. B. Health and performance. C. Unscheduled maintenance.

GE Aviation is working to improve... A. Air traffic management. B. Engines and composite material. . Passenger and freight experiences.

These are (foto de tornillos con tuerca). A. Bolts. B. Rivets. C. Pins.

Electronic flight instrument system (EFIS) control panel. A. Instrumentos electrónicos del sistema de vuelo del panel de control. B. Panel de control electrónico de los instrumentos de vuelo del sistema. C. Panel de control del sistema electrónico de instrumentos de vuelo.

Choose the correct alternative. A. Prior the engine operation, make sure that the area is clear. B. Prior to the engine operation, making sure that the area is clear. C. Prior to the engine operation, to make sure that the area is clear.

The bigger logo is on ( foto de avión Latam). A. The elevator. B. The winglest. C. The rudder.

The plug furnishes the EEC with information identifying engine basic thrust rating. A. The EEC will set the engine basic thrust rating. B. The EEC is fed with information by the plug. C. The plug is provided wuth information by the EEC.

Choose the correct alternative. A. The toilet seat was removed according to the procedure. B. The toilet seat were removed according to the procedure. C. The toilet seat was removed in according with the procedure.

Figure: Packing position is__________________ the fuel distribution valve strainer and the adapter. A. In front of. B. Between. C. Among.

The engine fuel-feed system distributes fuel to the main engines (AMM 28-22-00-001) and the APU (AMM 28- 25-00/001). A. El sistema de alimentación de combustible del motor distribuye combustible a los motores principales (AMM 28-22-00-001) y a la APU (AMM 28-25-00/001). B. El combustible del motor que alimenta el sistema distribuye combustible a los motores principales (AMM 28-22-00-001) y a la APU (AMM 28-25-00/001).

The air conditioning system____ conditioned air to the control cabin. A. Provides. B. Did no provided. C. Does not provided.

Choose the correct alternative. A. The wires were splitted according to figure 1. B. The wires were split according to figure 1. C. The wires were splited according to figure 1.

When I realised o has dropped a magnetic tip of my screwdriver, I decided to___my steps. A. Retrace. B. Return. C. Regress. D. Resume.

Choose the correct alternative. A. The engine indications were seted to normal configurations. B. The engine indications were setted to normal configuration. C. The engine indications were set to normal configuration.

The technician ended the rigging__ her torque wrench. A. With. B. In. C. As. D. By.

When ALL the landing gear is up and locked, the LGCIU signals the doors to close while maintaining landing gear UP signal to keep the "raise" line pressurized. Door uplock proximity detectors signal the LGCIU that the doors are uplocked. As soon as the last door closes and locks, the LGCIU cancels the landing gear " raise" signal and maintanins the door close signaal as long as the safety valve is open (LGCIU, Landing gear control interface unit). A. The LGCIU cancel the landing gear "raise" signal after the last door closes and locks. B. The LGCIU cancel the landing gear " raise" signal when the safety valve is open. C. The LGCIU cancel the landing gear " raise" signal when the landing gear is up.

The Electrical Flight Control System (EFCS) * computers, including both ELACs and SECs, are designed with a pair of internal processors: one for controlling (COM) and one for monitoring (MON). What is the direct consequence of a detected discrepancy between these two internal processor channels within an ELAC or SEC unit?. The monitoring processor automatically overrides the controlling processor to ensure continued safe operation. Output to the relevant flight control actuator will be inhibited, preventing potentially erroneous commands. A fault message is immediately transmitted to the ECAM, but control output continues without interruption.

Beyond their primary role in acquiring data from the ELACs and SECs, what are the two main destinations for this data and the additional crucial function that the Flight Control Data Concentrators (FCDC) provide within the Electrical Flight Control System (EFCS)?. FCDCs transmit data exclusively to the ECAM for pilot display and manage the automatic "power-up" tests of the EFCS. FCDCs send data to the Centralized Fault Display System (CFDS) for maintenance reporting and directly control the elevators and THS during alternate law. FCDCs transmit collected data to both the ECAM and the CFDS, and they also facilitate access to the EFCS specifically for CFDS tests.

For an A319/320/321 aircraft to operate in * its most advanced control mode, NORMAL LAW, with all projections active, what specific set of conditions must be simultaneously fulfilled according to the Electrical Flight Control System (EFCS) design?. The EFCS must be in a downgraded configuration, and only electrical power must be available to the control surfaces. The EFCS must be normal, and both electrical power and hydraulic pressure must be available. Only the SECs are required to be fully functional, and at least one hydraulic system must be operational, regardless of electrical power status.

The wiring for the Electrical Flight Control System (EFCS) is strategically routed throughout the aircraft. Considering the specific control surfaces, where are the wire runs from the computers to the general surface actuators primarily located, and how are the Aileron and Spoiler signals specifically routed within the wings?. General wire runs are under the cabin floor beams (left and right side) and under the cabin ceiling; within the wings, Aileron signals are routed in the leading edge and Spoiler signals in the trailing edge. All EFCS wiring is routed exclusively under the cabin floor beams, with both Aileron and Spoiler signals running in the wing trailing edge. EFCS wire runs are only located in the cabin ceiling, and within the wings, Aileron signals are in the trailing edge while Spoiler signals are in the leading edge.

Within the Electrical Flight Control System (EFCS), the ELACs and SECs have distinct primary control responsibilities but also provide backup functions. Which statement accurately describes their primary control outputs and the backup relationship for specific control surfaces?. ELACs primarily control Spoilers, and SECs provide backup for the Ailerons. ELACs primarily provide output to control the Elevators, Ailerons, and THS, while SECs primarily control the Spoilers and serve as a backup for the Elevators and THS. SECs are solely responsible for all elevator and THS control, with ELACs providing backup for spoilers.

Once resources become limited, only a - of components can be available. division. section. fraction.

He did not, however, propose a correct mechanism for _ _ parts can be interchangeable. all. how. Once.

There are…. ( pines). Pins. Rivets. Bolita.

If RUDDER _______, THE NOSE _____. DEFECT LEFT ,DEFLECT LEFT. DEFLECTS LEFT,DEFLECTS LEFTS. TO DEFLECTS,TO DEFLECTS.

These are leading edge (slats). Flaps. Slats. Spoiler.

The surface is ( panel remachado). Riveted. Attached with bolts. Welded.

THIS imagen ( antena VHF). Pitot. VHF antena. AOA.

The pilot command sends inputs. _ the Flight Control Computer *. Up to. From. To.

Shall we go to the gym after work?. I’m to tired. It’s very good. Not at all.