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TEST BORRADO, QUIZÁS LE INTERESEATR 72-6 AE

COMENTARIOS ESTADÍSTICAS RÉCORDS
REALIZAR TEST
Título del test:
ATR 72-6 AE

Descripción:
Examen licencia ATR

Autor:
AVATAR
Juan P. Rodriguez
(Otros tests del mismo autor)


Fecha de Creación:
09/09/2020

Categoría:
Personal

Número preguntas: 233
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Temario:
On the ATR600, the IESI (Integrated Electronic Stand-by Instrument) The VHF1 system only VOR/ILS page with Edit Box on V/ILS 1 STBY Frequency Combines the Stand-By Horizon, the Stand-By Airspeed Indicator, the Stand-By altimeter and the Stand-By Compass.
The two CAC (Core Avionic Cabinet) To control, at low power level and low speed, a constant propeller speed (for instance on ground) Control and authorize the operation of A/C avionic systems only Manage the ACMS function, the APM, Data Broadcast to CAC, Communicate with ACARS and MCDU.
The Yellow Arrow on the Speed Scale indicates The current Aircraft Speed IAS selection only Yes, 170Kt can be manually targeted by pressing the 'activate' function on the APPROACH page.
The Altitude Selection Bug is set Using the ALT SEL rotary selector on the FGCP Pitch, roll, heading and ground speed IAS selection only.
Where is the Airspeed, Altitude and Vertical Speed information located On the EFIS The ND key on the EFIS CONTROL PANEL (EFCP) On the Primary Flight Display.
The two Attitude and Heading Reference Systems (AHRS) provide the following data There are not any other sensors Pitch, roll, heading and ground speed Right , MCDU1 can be linked with either FMS with the FGCP source selector.
PROP BRK blue light is illuminated on the engine start panel and is displayed on the EWD when As long as the TEST push-button is depressed On ground, with the BAT switch in ON position only Engagement or disengagement conditions are met.
Each DC starter/generator during engine start acts as an electric motor driving HP via Hydraulic blue pressure Reduction Gearbox By the PL.
Is the fuel heated to prevent icing No, it is not necessary When Bleed Valve must be closed manually When Both Outflow Valves remain in the last position.
The Reduction GearBox drives The ACW generator, the fuel HP pump, the propeller and the associated control accessories Hydraulic blue pressure From each ACW generator.
What is the important thing that you need to do before opening the Cockpit Emergency Hatch Activates the Cockpit Door Locking System It is important to disconnect the electrical connector and the water drain A cabin Crew member has called the Cockpit.
During landing, when does the idle-gate move rearward to the Ground Idle position At take-off as soon as both main landing gears absorbers are released Slower than normal engine deceleration and faster than normal engine acceleration accompanies any forward or rearward movement of the power lever Only after all gear shock absorber are compressed.
"A" "GATE" "prevents PL angle reduction below FI" At take-off as soon as both main landing gears absorbers are released Only after all gear shock absorber are compressed Arms auto-feather system durin take-off.
The propeller brake is powered by Hydraulic blue pressure By the PL Reduction Gearbox.
What happens if you use the Power Lever with one EEC off Slower than normal engine deceleration and faster than normal engine acceleration accompanies any forward or rearward movement of the power lever Arms auto-feather system durin take-off Both loops activated.
How do you shut off engine fuel supply By the PL Start sw OFF By the key.
FAULT on START 2 pushbutton illuminates when On RH engine, engine start selector is on start, porpeller brake is on, but gust lock is not engaged, or a GCU failure is detected during starting, or starter remains engaged after 45% Slower than normal engine deceleration and faster than normal engine acceleration accompanies any forward or rearward movement of the power lever With CL at AUTO position.
During start sequence, the cross start system Makes use of the main battery until 10% NH then uses main battery assisted by the opposite DC GEN until 45% NH Bleed Valve must be closed manually NH=61.5%.
The EEC function is To control, at low power level and low speed, a constant propeller speed (for instance on ground) Control and authorize the operation of A/C avionic systems only On the EFIS.
The Engine Electronic Control (EEC) Arms auto-feather system durin take-off Control and authorize the operation of A/C avionic systems only Provide the additional fuel flow required for take off.
When selecting CRANK on the overhead ENG START panel, the igniters are energized With CL at AUTO position Automatic, depending of PL position Below 36%.
In the cockpit, on the Doors Control Panel, if you depress the SW TEST pushbutton It test Cabin and Service doors microswitches The refueling panel, the cargo door control panel, the cabin door Cockpit door only.
Which ATPCS functions are available when it has been armed for take-off Autofeather only There are not any other functions Torque, Np, ITT and Fuel Used.
Which kind of engine and/or propeller indications can be found on the MFD SD engine page Torque, Np, Fuel flow, Oil pressures and temperatures Fuel quantity is displayed on Weight page of the MFD In the MFC and in the FWA.
Which kind of engine and/or propeller indications can be found on the EWD Torque, Np, ITT and Fuel Used Airspeed, Altitude and Vertical Speed information The current Aircraft Speed.
On which display units are engines and propeller data displayed EWD and MFD FGCP MPC.
Where is the Fuel Used Reset button located On the VCP associated with the PERF page On the VCP associated with the WEIGHT page On the VCP associated with the NAV page.
Where can you read the fuel quantity Fuel quantity is displayed on Weight page of the MCDU On EWD On PFD.
"During a cross feed operation, a blue ""FUEL XFEED"" flashing message on memo panel means" Either both fuel pumps are ON or OFF or fuel pump is OFF in the tank with the most fuel quantity Fuel quantity is lower than 160kg (352lbs) A leak in the fuel circuit.
Concerning the fuel temperature sensors, there is one in each engine fuel feeding line and There are not any other sensors False Provide the additional fuel flow required for take off.
Each electrical pump can supply one engine throughout the whole aircraft envelope False Fuel quantity is lower than 160kg (352lbs) Provide the additional fuel flow required for take off.
The maximum asymmetrical fuel loading between wings is 200kg (440lbs) 220kg (485lbs) 240kg (530lbs).
For the video cabin surveillance, how many cameras is it possible to use 3 2 4.
LO LVL amber light and FWS activation mean that Fuel quantity is lower than 160kg (352lbs) The Fuel is enought to complete the fly The Fuel Tank is empty.
In normal operation, fuel electrical pumps are mainly used to Provide the additional fuel flow required for take off Cross Feed Heating Fuel.
"Engine running, ""FEED LO PR"" associated with FWS activation means" A leak in the fuel circuit The fuel pump is fault The fuel tank is empty.
"When ""FUEL PUMP"" pushbutton is released out" "Electrical pump is de-activated and ""OFF"" white light illuminates on pushbutton" Fuel quantity is lower than 160kg (352lbs) Fuel mass remaining on board.
Fuel quantity indicators display Fuel mass remaining on board On EWD ON PFD.
Jet pump is activated by The Jet Pump Pushbutton Start Engine Pushbutton Condition Lever in Auto Position.
Following an angine 2 fire under control and affected fire bottle discharged, you can read AGENT 1 DISCH illuminated on engine 2 and AGENT 1 DISCH illuminated on engine 1 Both AGENT illuminated Neither AGENT illuminated.
To detect an engine fire, it is necessary to have Both loops activated One loops activated Neither loops activated.
The DISCH amber light indicates The right P/B to discharge a bottle Both loops activated Validate the percussion of the single bottle.
The fire extinguishing system of the AFT cargo compartment is installed On the ceiling of the AFT cargo compartment and includes two diffusers The lavatory Four extinguisher bottles, two per engine.
In the cockpit, when the buzzer sounds for 2 seconds, it´s because A cabin Crew member has called the Cockpit A cabin Crew member has called the Passangers A cabin Crew member has called the other Cabin crew.
Pulling the fire handle enable to Validate the percussion of the single bottle A continuous loop system monitoring overheat or fire Auto extinguishing in case of engine fire.
Which of the following places is not protected by smoke detectors The lavatory The Stairs The luggage rack .
Engine fire extinguishing system includes Four extinguisher bottles, two per engine Two extinguisher bottles, one per engine One extinguisher bottle, one for both engines.
Each engine is equipped with A continuous loop system monitoring overheat or fire A smoke detector A lineal circuit.
The ATR Fire Protection system provides Auto extinguishing in case of engine fire Validate the percussion of the single bottle Portable extiguishers.
One ACW generator off-line ACW SVCE BUS only is shed AC EXT PWR supplies the busses which are not supplied by the ACW GEN Hydraulic system operates normally.
Aircraft on ground, engines running and AC EXT PWR connected and ON AC EXT PWR supplies the busses which are not supplied by the ACW GEN ACW SVCE BUS only is shed All DC buses operates normally.
Where are the ACW generators connected To the respective accesory gear box To the respective reduction gear box Primary Governor.
How is the ACW power obtained From each DC generator converted in ACW by TRU ACW SVCE BUS only is shed From Reduction gear box.
The DC generator comes on line at NH=61.5% NH=72.8% NH=65%.
What is the goal of the Cockpit Door Locking System control switch Activates the Cockpit Door Locking System A cabin Crew member has called the Cockpit Call the cockpit for emergency.
Assuming normal operation in flight, when are the DC EMER BUS and thenDC ESS BUS connected to the DC BUS 1 and/or the DC BUS 2 Always through respective battery charge contactor and its respective HOT BAT BUS DC STBY BUS and AC STBY BUS are supplied from the DC BUS 1 or the DC BUS 2 At the pilot's discretion.
The inverter 1 normal supplies The AC BUS 1 and the AC STBY BUS Always through respective battery charge contactor and its respective HOT BAT BUS The AC BUS 2 .
Depressing the STBY BUS OVRD P/B DC STBY BUS and AC STBY BUS are supplied from the DC BUS 1 or the DC BUS 2 The AC BUS 1 and the AC STBY BUS Supplied fromDC BUS 2.
With no external power, no engine running and the battery switch OFF, which items does the GND HDLG BUS power The refueling panel, the cargo door control panel, the cabin door The lavatory The service door.
No engine running, how can the DC SVCE BUS be powered With DC GPU available and on-line, by pressing the DC SVCE/UTLY BUS P/B in the cockpit AC EXT PWR supplies the busses which are not supplied by the ACW GEN DC Generators.
What means the illumination of the UNDV amber light on the STBY BUS P/B on the MAIN ELEC PWR panel The DC STBY BUS voltage is lower than 24V The AC STBY BUS voltage is lower than 115V The ACW STBY BUS voltage is lower than 28V.
On the MAIN ELEC PWR panel, what the illumination of the amber arrows means Both batteries are discharging One Bat is discharging EMER bat is discharging only.
BAT switch on the MAIN ELEC PWR panel on OVRD position means Allows to be sure that DC EMER BUS is supplied by the HOT EMER BAT BUS and the DC ESS/SBY BUS are supplied by the HOT MAIN BAT BUS Both batteries are discharging DC electrical power is converted to AC.
The GND HDLG BUS can be powered On ground, with the BAT switch in ON position only In flight, with the EXT Power switch in ON position only On ground, with the AC EXT Power switch in ON position only.
DC SVCE/UTLY BUS shed amber light on the MAN ELECT PWR panel illuminates when The DC SVCE BUS is shed ACW SVCE BUS only is shed With DC GPU available and on-line, by pressing the DC SVCE/UTLY BUS P/B in the cockpit.
A visual seat position gage can be used for seat adjustment. The pilot aligns The colored balls to ensure proper sitting position With the airplane nose With the deck.
Aircraft on ground, engines running and DC EXT PWR connected and ON DC EXT PWR supplies the busses which are not supplied by the DC GEN AC EXT PWR supplies the busses which are not supplied by the ACW GEN All Buses are OFF.
What is the nominal frequency of the AC constant frequency power 400Hz 300HZ 115HZ.
What are the capacities of the batteries Main Battery: 28.5V 43Ah / Emergency Battery: 28.5V 17Ah Main Battery: 28V 43Ah / Emergency Battery: 28.5V 15Ah Main Battery: 27.5V 43Ah / Emergency Battery: 28.5V 17Ah.
What is the nominal voltage of the DC generators 115V 120V 110V.
How is the constant frequency AC power obtained From each ACW generator From each DC generator From Essencial BUS.
Which pushbutton must be pressed on the FGCP to intercept and track a VOR course BC IAS VS.
In GO AROUND The AFCS provides FD commands only to manually acquire and maintain predetermined safe pitch altitude and present heading The FGCP maintain Inop The pilot must do the maneuver in manual mode.
The ALT SEL mode is automatically armed when the aircraft climbs (or descends) towards the selected altitude This asseertion is correct This asseertion is incorrect You don't know what to do.
The Push to Synchronize function exists On the HDG button only to synchronize the Heading bug to the current A/C Heading On the NAV button only On the BC button only.
The Pitch Wheel of the FGCP is used for IAS selection only COM selection only The function does not exist.
What is the take-off power per engine 2.475 HP 2.525 HP 2.415 HP.
The Bank Angle selection (High or Low Bank) is Automatic and the selection of bank angle value is made by comparing aircraft speed with 180 Kts Manual, the pilot can change the angle as required When the Pilot turn more than 15°.
Following a failure detection Postponed actions and limitations are automatically embodied in pending list´s stored status. Inoperative equipment list has to be read in the QRH Continue the flight and after landing take emergency actions Call COM company.
Concerning the main failure detection phases, we can say that Four main phases are available: 1-Isolation, 2-Detection, 3-Identification, 4-Confirmation Four main phases are available: 1-Detection, 1-Isolation,3-Identification, 4-Confirmation Four main phases are available: 1-Confirmation 2-Isolation, 3-Detection, 4-Identification .
Concerning the normal check lists They are always automatically popped-up according to the different flight phases The pilot has to select it manually The plane doesn't have a list.
How is the take-off alert inhibition function activated Automatically by the FWA Automatically by the PFD Automatically by the EWD.
What are the conditions to activate the take-off alert inhibition function A/C on ground, PWR MGT in TO position, both PL below TO position, both NH above 60%, no oil low pressure alarm on engines A/C on air On the TakeOff.
Intruder flight information data are available on the tag associated to its symbol on the ND If the intruder is equipped with a mode C o S transponder If the intruder is equipped with a mode A transponder If the intruder is equipped with a mode S transponder only.
TCAS is controlled through the MCDU In the TCAS page available in the COMMUNICATION page In the NAV page In the COM page.
Which statement is correct A mode A equipped intruder can in the worst case cause a Resolution Advisory A mode S equipped intruder can in the worst case cause a Resolution Advisory All mode equipped intruder can in the worst case cause a Resolution Advisory.
How are Alert messages in the Alert window of the EWD classified Manually by the crew using EFCP Only if you have an emergency Automatically in the the PFD.
When does TCAS system begin the tracking phase When the intruder reaches the detection limit When the TCAS is Off When the intruder reaches the visual limit of the pilot.
TCAS is controlled through the VCP via The TCAS tab in the NAV page for the modes selection and in the ND OVLY tab of the SURV page for the modes display In the WEIGHT page In the COM page.
TCAS information is displayed On the PFD - HSI for traffic background On the EWD- Aletrt window for traffic background On the Passager Cam.
Through the IESI, the pilot can tune The VHF1 system only The VHF2 system only The VHF1, VHF2 system.
VHF1 and VHF2 transceivers are respectively supplied by The DC EMER BUS and the DC ESS BUS The AC GEN BAR The ACW GEN BAR.
When the dual HF option is installed, the HF antenna enables The reception of two frequencies and transmission of only one frequency at the same time The reception of one frequencie and transmission of only one frequency at the same time The reception of two frequencies and transmission of only two frequencies at the same time.
Each Radio Management Application (RMA) is A computer located in the avionic rack Its a software It doesn´t exist on the plane.
After using the oxygen mask in order to reset the communication system to boomset mike, it is necessary to Pack away the oxygen mask in the containers Select Oxigen sw to 100% Select Oxigen sw to Emergency.
Use of the Audio 1 sel P/B When ALTN illuminates on the P/B when released, the captain station is connected directly to the VHF1. VHF2, interphone and passenger address are not affected When ALTN illuminates on the P/B when released, the captain station is connected directly to the VHF2 only and the interphone. When ALTN illuminates on the P/B when released, the captain station is connected directly to the VHF1 only and passenger address are not affected.
The Audio Integrated system is connected to The Cockpit Voice Recorder, the Passenger Address and the VHF and HF system The Passengers speakers The communication frequency.
On the ATR-600s where are the Alert messages generated by the FWS displayed On the Primary Flight Display On the Flight Management System On the Video Screen.
How many radio PTT exist in the cockpit 8 (one on each ACP, one on each control column, one on the nose wheel steering handle, one near the observer seat, one on each power lever) 6 10.
When is the Passenger Address volume increased As soon as the PA selection key on the ACP is selected On the FGCP On the FMS.
The default flight path angle is 3 degrees, is it possible to change this angle No, the default flight path angle is 3 degrees according to certification Yes, it´s possible Depends to App charts.
Where can you select the alternate airport and the flight level to alternate It is selected through the 'PROG' page opened by pressing PROG function key two times and selecting PERF INIT Lsk It is selected through the 'NAV' page opened by pressing PROG function key two times and selecting PERF INIT Lsk It is selected through the 'WEIGHT' page opened by pressing PROG function key two times and selecting PERF INIT Lsk.
In flight, where can you check the Actual Navigation Performance (ANP) It is possible to check the ANP It is not possible It is automatically .
You are 10NM to the Final Approach Fix, with speed auto selected and 240Kt, is it possible to target 170Kt earlier than 2NM to FAF Yes, 170Kt can be manually targeted by pressing the 'activate' function on the APPROACH page No, because only the co-pilot do Never.
During your flight preparation, you must insert an Airway, how is it possible The only method of Airway insertion is via the vertical revision page at each waypoint It is not possible Automatically.
How to insert a HOLD The HOLD is inserted via the lateral revision keys, via the next waypoint only When the airplane is on ground conditions only The plane doesn't have that button.
How can you clear a discontinuity in a flight plan The discontinuity is cleared by inserting a CLEAR in place of the discontinuity The HOLD is inserted via the lateral revision keys, via the next waypoint only Push Direct To sw.
For prediction computation, an accurate and a simplified wind model is available. What are the ways to insert the two types of wind profiles What is the way to insert the one type of wind profile The plane does not have this option.
The simplified wind model is inserted through each waypoints Lateral revision page and the accurate one through each waypoints vertical revision page Check PFD It is not relevant to the operation.
On the ATR-600s where is the FWS function implemented In the MFC and in the FWA In the CAC and in the FMS Only in the PFD.
How can the Take-off, Cruise and Approach page be opened These pages can be opened with the DATA key function These pages can be opened with the COM key function These pages can be opened with the WEIGHT key function.
How many flight plan types can be used by the pilot It is possible to create two flight plans, a primary one and a secondary Three flight plans, a primary one and a secondary and third One, only the one that is active.
It is possible to access to either FMS1 or FMS2 from one MCDU Right , MCDU1 can be linked with either FMS with the FGCP source selector Wrong Right , MCDU2 can be linked with either FMS with the FGCP source selector.
In the FMS Operational Domain, what is the maximum Ground Speed (GS) 820Kt 900Kt 750KT.
The anti-skid system also provides Touchdown protection preventing inadvertent brake application for 5 seconds after touchdown or until wheels speed is above 35kt Touchdown protection preventing inadvertent brake application for 3 seconds after touchdown or until wheels speed is above 30kt Touchdown protection preventing inadvertent brake application immediately after touchdown or until wheels speed is above 10kt.
The landing gear wheels are braked after take off Only the MLG wheels brake automatically when the Landing Gear Control Lever is set to the UP position Only when the pilot applies the brakes The wheels remain braked.
In case of total hydraulic failure, the parking and emergency brake accumulator allows Six complete braking applications without ANTI-SKID protection Eight complete braking applications with ANTI-SKID protection Five complete braking applications without ANTI-SKID protection.
The anti-skid is available for wheels speeds greater than 10 kt 20 kt 19 kt.
The anti-skid test is inhibited for wheel speeds above 35 Kts 30 kts 33 kts.
"For how long are the amber ""F"" displayed during the A-SKID test" As long as the TEST push-button is depressed 5 seconds Automatic.
What is the purpose of the FDAU part of the MPC Manage the ACMS function, the APM, Data Broadcast to CAC, Communicate with ACARS and MCDU Manage the ACMS function, the APM Manage the Communicate with ACARS and MCDU.
What is the maximum passengers configuration on ATR 72-600 74 68 72.
The Nose Wheel Steering is available "As soon as the Landing Gear control Lever is placed on ""DOWN""" When the pilot use the nose wheel steering lever When the main landing wheels are on ground.
The Nose Wheel Steering switch Is a guarded switch to turn OFF to de-energize the Steering Solenoid Valve during towing Prevents from being used in flight Use only in flight.
"The system triggers the master warning alarm: ""LDG GEAR NOT DN"" and the red light of the LDG GEAR control lever illuminates if any landing gear is seen as not down and locked and" At least one PL is at FI and Radio altitude is below 500 ft The Landing Gear Lever is UP The airplane is on Ground.
"On the LDG GEAR indicators, the ""UNLK"" light illuminates to indicate that" An uplock box has failed The wheels are flat The main and nose landing gear are up.
The LDG GEAR is considered down when 3 green triangles are illuminated on The central instrument panel LDG GEAR indicator ONLY The central and over head instrument panel LDG GEAR indicator The over head instrument panel LDG GEAR indicator ONLY.
LDG GEAR normal operations In the connecting lines, hydraulic pressure is released when the gear is locked in the commanded position (UP or DOWN) The plane does it automatically As recommended by the manufacturer.
Concerning the LDG GEAR selector valve There is only one valve, located en the LH Main Landing Gear Fairing There are two valve, located en the LH and RH Main Landing Gear Fairing There is only one valve, located en the RH Main Landing Gear Fairing.
"The anti retraction latch of the landing gear control lever prevents selecting ""UP"" if" At least one gear shock abosrber senses weight on wheels All gears shock abosrber senses weight on wheels At two gears shock abosrber senses weight on wheels.
The LDG GEAR not down alarm is generated by MFC 2 associated to SYSTEM 2 CAC MPC.
If the aircraft is on battery power Only the primary LDG GEAR indicator is operative (SYSTEM 1) Only the secondary LDG GEAR indicator is operative (SYSTEM 2) The system is not operational.
How is the MPC made up It is composed of a SSFDR / SSCVR part and an ACARS associated with its MCDU CAC MFD.
The landing gear position indications are controlled by Two isolated systems, SYSTEM 1 and SYSTEM 2 controlling one position indicator One isolated systems, SYSTEM 1 controlling one position indicator One isolated systems, SYSTEM 2 controlling one position indicator.
The flaps position indicator becomes red when An uncommanded flaps retraction of more than 4 degrees Flaps Unlocked Discrepancy between flaps position and indication.
What is the VFE of the flap settings VFE flaps 15 degrees = 190Kt and VFE flaps 30 degrees = 150Kt VFE flaps 15 degrees = 185Kt and VFE flaps 30 degrees = 150Kt VFE flaps 15 degrees = 190Kt and VFE flaps 30 degrees = 155Kt.
What is the meaning of the cyan flaps position display on the flaps position indicator The difference between the flaps position and the flaps command is less than 1 degree The difference between the flaps position and the flaps command is less than 2 degree The difference between the flaps position and the flaps command is less than 3 degree.
The stick pusher actuator is attached to The CAPT control column The F.O control column Both.
The stick shaker is generated by Two stick shaker actuators, one on each control column Four stick shaker actuators, two on each control column One stick shaker actuators, one on CAPT control column.
What protects the rudder from excessive travel speed caused by wind gusts when on ground A hydraulic damper Tops in the rudder Line cable.
The gust lock acts on Roll controls, pitch controls, and rudder controls Ailerons, pitch controls, and rudder controls Roll controls, ailerons, and rudder controls.
The TLU LO SPEED indication is displayed In green when rudder travel is limited In magenta when rudder travel is limited In white when rudder travel is limited.
In normal operation, the Travel Limitation Unit (TLU) Limits rudder travel and rudder clearance (umlimited up to 185Kt in acceleration and limited above 180Kt in deceleration) The operation is according to the flight path the pilot can operate it according to criteria.
What are the MFC functions Monitoring, control and authorizing aircraft systems operations and manage system failures and flight envelope anomalies Synchronize, monitoring, control and authorizing aircraft systems operations All the answers are correct.
The Releasable Centering Unit (RCU) Enables stabilization of the rudder position, when no action is applied on the pedals and disengages to allow trim setting when the yaw trim is actuated Actuate TLU The plane does not have this system.
How could both elevators be reconnected in case of elevators declutch Through the Elevator Clutch P/B on the right maintenance panel if A/C is on ground and gust-lock is ON Only be reconnected in fly The plane does not have this option.
An aural whooler alert is generated when 1 degree movement or more on the yaw trim indicator scale 3 degree movement or more on the yaw trim indicator scale 5 degree movement or more on the yaw trim indicator scale.
If one control column is jammed The pitch uncoupling procedure allows the other control column to operate both elevators Both control columns will be inoperative Both answer are correct.
What does the green band on the pitch trim scale mean It corresponds to the take-off pitch trim range Flaps Selection 8°Degrees.
Pitch control is achieved by One mechanically driven elevator Two mechanically driven elevator Four mechanically driven elevator.
What does it mean when the aileron trim indicator becomes white on the EWD The autopilot is disengaged and the aileron trim is not inhibited The autopilot continue engaged and the aileron trim is not inhibited The autopilot continue engaged and the aileron trim is inhibited.
Each spoiler has a hydraulic actuator which is controlled Mechanically by the associated aileron linkage Automatically by the associated aileron linkage The ailerons do not have actuators.
The spoilers cyan triangle light illuminate to indicate that The associated spoiler is in retracted position The associated spoiler is armed The associated spoiler is operating.
Roll trim is performed using Only left aileron tab Only right aileron tab Both aileron tab.
What happens in the AFCS when the BAT selector is set to ON The software is upgraded The computer remain shutdown The computer will start.
Roll control is achieved by actuating Mechanically the ailerons and hydraulically the spoilers Hydraulically the ailerons and mechanically the spoilers Mechanically the ailerons and mechanically the spoilers.
In flight, roll control is achieved by Two ailerons each one with a spring tab and two spoilers Two ailerons Two spoilers.
When should airframe and engine de-icing be used It should be turned ON as soon as ice accretion is noted and left until no more ice accretion has been whatever the flight conditions Wait for the ice light to go out on the EWD Wait for weather conditions to change.
What is the last part of the airframe to become clear of ice when leaving ice accretion and icing conditions Ice Evidence Probe Wait for the ice light to go out on the EWD Wait for weather conditions to change.
Aircraft is in flight, anti-icing and de-icing are switched OFF and the ice detector detects ice accretion. You will have The yellow ICING message illuminates steady on the FMA Ice formed on the wings Loss of speed.
Aircraft in flight, anti-icing and de-icing selected ON, the ice detector detects ice accretion The AIRFRAME message is flashing on the Temporary Selection Window IEP message in EWD Ice over the wings.
What the MODE SEL AUTO P/B Fault amber light illumination means MODE SEL AUTO P/B must be set to MAN and the anti-icing and de-icing MODE SEL P/B must be selected according to the SAT Ice over the wings IEP fault.
The pneumatic de-icing system is supplied by air, bled from External air directly RAM air Recirculation Fan.
Can you use the pneumatic de-icing system with both engines bleed valves off and engine running Yes No Discretion.
It is possible to supply the airframe de-icing boots when the AFR AIR BLEED P/B is OFF Yes if a fire handle is not pulled No Discretion.
ATC Transponder can be tuned through MCP and MCDU only FGCP and MCP ICP and MCDU.
To prevent overheating, propellers anti-icing is inhibited when Np is Below 36% Above 36% Below 30%.
Where are located the anti-icing and de-icing systems status information On the Temporary Selection Window of each MFD only On the Temporary Selection Window of each PFD only On the Temporary Selection Window of each EWD only.
At least one horn is ON Icing AOA illuminates on FMA only De-Icing system ON Anti-Icing system ON.
How are the horns anti-iced Electrically and pneumatically Electrically Pneumatically.
To prevent icing on air data sensors, the probes are heated On ground and in flight, except TAT sensors which are heated only in flight On ground only In flight only.
The IEP light diffuser ignition is controlled by The STROBE lights switch The LANDING lights switch The TAXi light switch.
Ice Evidence Probe (IEP) is located On the lower frame of the right side window In front of the nose The tail .
About emergency lights, assuming that toggle switch is in ARM position, when did they illuminate They illuminate when emergency battery voltage is below 18V or when one DC generator is lost They illuminate when emergency battery voltage is below 19V or when one DC generator is lost They illuminate when emergency battery voltage is below 18V or when one AC generator is lost.
How many emergency exits are there in the cabin There are four emergency exits in the cabin: two foreward and the passenger door and the cockpit hatch There are five emergency exits in the cabin: two foreward and the passenger door and the cockpit hatch and service door There are two emergency exits in the cabin: two foreward and the passenger door .
How is the oxygen delivered to the passengers By the mean of portable oxygen bottle for 10% of passengers From ram air From packs.
On SURV FORMAT, wich page is displayed by default XPDR page with Edit Box on FLT ID NAV page WEIGHT page.
How many portable oxygen bottle are fitted in the ATR72 4 located in the cockpit and in the cabin 6 located in the cockpit and in the cabin 3 located in the cockpit and in the cabin.
How to reset the normal communication through the boomset and microphone after having used the flight crew oxygen mask By selecting the N/100% rocker in the N position on the oxygen mask By selecting the N/100% rocker in the 100% position on the oxygen mask Store the oxygen mask.
What is the purpose of the N/100% rocker on the Flight Crew oxygen mask It is to choose the level of oxygen pressurization in the mask For emergency Only So that passengers more oxygen.
Who is supplied by the fixed oxygen system The Flight Crew members and the passengers The Flight Crew members only The passengers only.
With the aircraft on ground, the right engine is running and the Condition Lever is set in AUTO position (NP>66%) , the following main pumps are electrically supplied Green only Blue only Green and Blue.
On ground, pressing the HYD AUX PUMP switch on the pedestal, can be used To energize the auxiliary pump, regardless of BAT master switch position and to pressurize the Green hydraulic system To energize the auxiliary pump, regardless of BAT master switch position and to pressurize the Green hydraulic system To energize the auxiliary pump, regardless of BAT master switch position and to pressurize the Green and Blue hydraulic system.
On ground without electrical power (no ACW GPU & BAT SW ON), at the first flight of the day, we should read 1.500PSI on gas pressure gauges in the hydraulic bay and 0PSI of hydraulic pressure in the cockpit 1.500PSI on gas pressure gauges in the hydraulic bay and 1500PSI of hydraulic pressure in the cockpit 0PSI on gas pressure gauges in the hydraulic bay and 1500PSI of hydraulic pressure in the cockpit.
Which systems are supplied by the Green hydraulic circuit Landing gear, Normal brake Emergency Brakes, Flasps, Wippers L/G, Flaps, Spoliers.
Which systems are supplied by the Blue hydraulic circuit Nose wheel steering, Flaps, Spoilers, Propeller brake, Normal brake Landing gear, Normal brake Flaps, Landing Gear.
The normal accumulator pre-charge pressure on the three gauges located in the left landing gear fairing 8.00PSI 7.00PSI 9.00PSI.
On NAV FORMAT, wich page is displayed by default VOR/ILS page with Edit Box on V/ILS 1 STBY Frequency WEIGHT PERF.
The nominal hydraulic pressure of Blue and Green systems is 3.000PSI 4.000PSI 3.500PSI.
Each hydraulic system is normally pressurized by means of A DC electric motor driven pump A AC electric motor driven pump A ACW electric motor driven pump.
Selecting the DITCH MODE with the DITCH pushbutton The electrical motors maintain both Outflow Valves in CLOSE position, regardless of AUTO or MANUAL PRESS mode use and ON is written in white on the Push-button BUT no FWS ALARM Activate the OUT FLOW VALVE in OPEN position The Fire Extinguisher bottles discharged.
How many Outflow Valves are opened in DUMP function Zero Two One.
When is the DUMP function available Only in AUTO PRESS mode regardless of differential pressure Only in a mergency in flight Only in MANUAL PRESS mode regardless of differential pressure.
What happens in case of loss of electrical supply to the DIGITAL CONTROLLER in automatic mode Both Outflow Valves remain in the last position Both Outflow Valves will open Both Outflow Valves remain mantain close.
"What is the correct way to switch the auto press system from ""manual"" to ""auto"" mode" Turno the MAN RATE knob to GREEN SQUARE (AUTO) position and then deselect MAN on the CABIN PRESS Pushbutton MAN RATE Off, AUTO On AT THE PILOT'S DISCRETION.
In MAN MODE, what are the maximum Cabin rates of descent and climb available -1500ft/min to +2.500ft/mi -1500ft/min to +2.000ft/mi -1000ft/min to +2.500ft/mi.
In case of ADC 1 failure, the Fully Automatic Digital Controller uses the Aircraft static air pressure generated by ADC 2 and CM1 altimeter baro setting ADC 1 and CM1 altimeter baro setting ADC 1 and CM2 altimeter baro setting.
In auto mode, what is the maximum Cabin rate available with the descent rate pushbutton depressed (FAST) +500ft/min +1500ft/min +1000ft/min.
On COM FORMAT, wich page is displayed by default VHF page with Edit Box on VHF 1 STBY Frequency PERF page VHF page with Edit Box on VHF 2 STBY Frequency.
In auto mode, what is the maximum Cabin rate available with the descent rate pushbutton released (NORM) +500ft/min +700ft/min +1000ft/min.
The maximum Cabin rate of climb, up to 20.000 Ft in auto mode is +500ft/min +700ft/min +100ft/min.
Which data is set on the AUTO PRESS panel before each flight The PRESSURE ALTITUDE (Using 1013.25) of the DEPARTURE airport QFE QNH.
What are the correct indications during a ground pressurisation system test Only, the Landing Elevation Indicator displays alternately 8800 and -8.800 Only, the Landing Elevation Indicator displays alternately 9800 and -8.800 Only, the Landing Elevation Indicator displays alternately 8800 and -9.800.
How many Outflow Valves are there TWO: Two pneumatic Outflow Valves ONE pneumatic Outflow Valve TWO: Two electrical Outflow Valves.
What is the MAX difference press allowed to select the OVBD VALVE switch to FULL OPEN position 0.35 PSI 0.50 PSI 0.75 PSI.
With the OVBD VALVE switch on AUTO position, The OVBD VALVE position is function of The exhaust mode Push Button position and the aircraft situation (On Ground with Engine 1 running or not or in Flight) The plane does not have this function The OVBD VALVE position, mantain Open.
When Engine 1 or Engine 2 start sequence is initiated "Extract fan stops during 120"" to avoid pressure shocks. During this period, the EXHAUST MODE P/B FAULT WILL NOT ILLUMINATE. The Ground Mechanic Call sounds" "Extract fan stops during 60"" to avoid pressure shocks. During this period, the EXHAUST MODE P/B FAULT WILL ILLUMINATE. The plane does not have this function.
The Overhead Valve position can be manually set in FULL OPEN or FULL CLOSE position with the OVBD VALVE control switch In case of AUTO MODE failure or for cold days (on ground) in order to expedite cabin heating by setting it in FULL CLOSE only In case of MANUAL MODE failure or for cold days (on ground) in order to expedite cabin heating by setting it in FULL CLOSE only In case of AUTO MODE failure or for cold days (in flight) in order to expedite cabin heating by setting it in FULL CLOSE only.
ON Ground or IN Flight, Engine 1 & 2 running , OVBD valve guarded switch in AUTO position & EXHAUST mode P/B moved on OVBD position The OVBD Valve is PARTIALLY OPEN in Flight and FULL OPEN ON GROUND and the U/F is OPEN The OVBD Valve is FULL CLOSE in Flight and PARTIALLY OPEN ON GROUND and the U/F is OPEN The OVBD Valve is PARTIALLY OPEN in Flight and FULL OPEN ON GROUND and the U/F is CLOSE.
When the EMER EXIT LT have been automatically illuminated, under what condition(s) will they be extinguished When DC STBY BUS voltage reach 20V or when at least one generator operating When DC STBY BUS voltage reach 18V or when at least one generator operating When DC STBY BUS voltage reach 19.5V or when at least one generator operating.
ON Ground or IN Flight, Engine 1 & 2 running , OVBD valve guarded switch in AUTO position & EXHAUST mode P/B Pressed IN (extinguished) The OVBD Valve is PARTIALLY OPEN and the U/F is OPEN The OVBD Valve is CLOSE and the U/F is PARTIALLY OPEN The OVBD Valve is CLOSE and the U/F is CLOSE.
ON Ground, Engine 2 running (Hotel mode or not) Engine 1 shut down, OVBD valve guarded switch in AUTO position & EXHAUST mode P/B Pressed IN (extinguished) The OVBD Valve is PARTIALLY OPEN and the U/F is OPEN The OVBD Valve is PARTIALLY OPEN and the U/F is CLOSE The OVBD Valve is PARTIALLY CLOSE and the U/F is OPEN.
TEMP SEL: OVHT is triggered when FLIGHT COMPT TEMP EXCEEDS 35 Celsius FLIGHT COMPT TEMP EXCEEDS 45 Celsius FLIGHT COMPT TEMP EXCEEDS 50 Celsius.
If a Pack Valve is CLOSED or inoperative Hot air is still available from that pack via the Temperature Control Valve when TEMP SEL is in AUTO mode only Hot air is still available from that pack via the Temperature Control Valve when TEMP SEL is in MANUAL mode only The plane does not have that function.
PACK VALVE FAULT means Overheat downstream the Compressor (T > 92 Celsius) only Overheat downstream the Compressor (T > 90 Celsius) only Overheat downstream the Compressor (T > 88 Celsius) only.
On ground, the air supplied to the Air Conditioing System may come from Engines or air Ground Conditioning Unit RAM air From PACK´s.
The COMPT TEMP indicator displays The compartment and the duct temperature of the selected side The compartment only The duct temperature only.
The COMPT TEMP setting knob Controls the TEMP CTL Valve directly when the TEMP SEL on MANUAL and via the Electronic Controller when the TEMP SEL on AUTO At the pilot's discretion The plane does not have this option.
"The selection of airflow ""NORMAL / HIGH"" from Packs is" Automatic, depending of PL position Manual At the pilot's discretion.
Pack Valves are Electrically operated and pneumatically controlled Electrically operated and electrically controlled Pneumatically operated and electrically controlled.
What is the maximum crosswind component to operate the cargo door 45kt 35kt 43kt.
Which Pack(s) is (are) the supplier of the cabin The Pack 1 (LEFT) only The Pack 1 (RIGHT) only The Pack 1 and Pack 2.
The Ground Cooling Turbo Fan is running When the Landing Gear is down or retracted for less than 10 minutes only When the Landing Gear is down or retracted for less than 12 minutes only When the Landing Gear is down or retracted for less than 8 minutes only.
On Air Bleed Panel: IF Packs pushbutton are extinguished when depressed Packs Valves are CLOSED and on SD Cabin page, PACK will be display in green in a green square Packs Valves are OPEN and on SD Cabin page, PACK will be display in green in a green square Packs Valves are CLOSED and on SD Cabin page, PACK will be display in blue in a green square.
What are Pack Valves functions The Pack Valves function is to SHUT OFF the PACK, CONTROL the PRESSURE and ENHANCE FLOW CONTROL Supply fresh air to the passagers cabin Airplane Pressurization.
Where is located the Packs The Packs are located under the Cabin floor The Packs are located in the Engines The Packs are on the wings.
The Pneumatic System is Always supplied by Engine LP stage Always supplied by Engine HP stage Always supplied by Engine P3.
In which case does the Bleed Air Shut-off Valve close automatically OVHT, LEAK, Absence of air pressure Electrical failure Engine shut down in flight.
"What happens, without air pressure and when ""WNG 1 or 2 BLEED"" pushbutton are depressed" Bleed Valve must be closed manually Bleed Valve must be closed automatically At the pilot's discretion.
The Pneumatic System supplies Pressurization, De icing and Engine Cooling De Icing Only Pressurization only.
SD CABIN, SD ENGINE SECONDARY, SD ELEC, SD ACW/HYD pages can be displayed using The ND key on the EFIS CONTROL PANEL (EFCP) ICP FGCP.
On the cockpit signs panel, the NO DEVICE switch illuminates the associated sign on the Passenger Service Units (PSU) in the cabin. It illuminates also The cyan NO DEVICE memo in the Temporary Selection Window on the MFD The red FASTEN SEAT BELT memo in the Temporary Selection Window on the MFD The red NO SMKG memo in the Temporary Selection Window on the MFD.
What is the maximum take-off weight 23.000kg / 50.705lb 21.000kg / 48.501lb 22.300kg / 49163lb.
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