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TEST BORRADO, QUIZÁS LE INTERESEATR 42/72 1

COMENTARIOS ESTADÍSTICAS RÉCORDS
REALIZAR TEST
Título del test:
ATR 42/72 1

Descripción:
Tema de estudio

Autor:
Meolac
(Otros tests del mismo autor)

Fecha de Creación:
09/04/2020

Categoría:
Otros

Número preguntas: 50
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Temario:
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 DC EXT GEN has priority over the DC GEN The first on line has priority DC EXT PWR has no priority over the DC GEN.
What is the maximum take-off weight? 18.770 Kg / 41.380 Lb 18.600 Kg / 41.005 Lb 16.700 Kg / 36.817 Lb 18.300 Kg / 40.344 Lb.
If you want to enter into the cockpit whilst the door is closed, you must press the call button on the Door Control Panel. Where is it located? On the left external door panel On the right external door panel On the flight attendant panel On the electrical rack bulkhead.
On NAV FORMAT, which page is displayed by default? VOR / ILS page with box on V / ILS 2 STBY frequency VOR / ILS page with box on V / ILS 1 STBY frequency VOR / ILS page with box on V / ILS 1 ACTIVE frequency VOR / ILS page with box on V / ILS 2 ACTIVE frequency.
What are the MFC functions? Monitoring, control and authorizing aircraft systems operations and manage system failures and flight envelope anomalies Monitoring, control and authorizing systems operations Managing the data displayed on the DUs Manage the Flight Warning System.
On the ATR 42-600, where is the FWS function implemented? In the MFC and the FWA In the MFC In the CAC and in the display units In the Flight Warning Application implemented in the CAC.
In the cockpit, when the buzzer sound 2 seconds, it's because: The cockpit toggle switch is set to ¨DENY¨ position The cockpit toggle switch is set to "OPEN" position A cabin crew member has called the cockpit A cabin crew member has depressed the EMER pushbutton on the Door Control Panel.
How are alert messages in the alert window of the EWD classified? According to alert level priorities According to order on detection Randomly by the CCAS Manually by the crew using EFCP.
The bank angle selection (High or Low Bank) is: Automatic and the selection of bank angle value is made by comparing aircraft speed with VmHB icing by default Automatic and the selection of bank angle value is made by comparing aircraft speed with 180 kts Automatic and the selection of bank angle value is made by comparing aircraft speed with VmHB icing according to flight conditions Manual through a BANK pushbutton.
The push to synchronize function exits: On the HDG button synchronize bug to the current A/C heading On the HDG button only to synchronize bug to the current A/C heading On the CRS 1 and 2 button to select the corresponding inbound course only On the ALT SEL button only to synchronize the altitude setting to the current A/C altitude only.
What is the normal voltage of the DC generators? 28 V 26 V 115 V 30 V.
What is the take-off power per engine? 2.750 shp RTO 2.750 shp / TO 2.160 shp 2.192 shp 2.132 shp.
What are the DC generators connected? To the respective accessory gear box connected to the HP compressor To the respective turbine shaft To the respective reduction gear box To the respective ram air turbine.
The GND HDLG BUS can be powered: On ground and flight On ground, even the BAT switch in OFF position but with any cargo, refueling or passenger door is open or on ground On ground, with BAT switch in ON position On ground, with GPU connected whatever the position of the BAT switch only.
On the MAIN ELEC PWR panel, what the illumination of the amber arrow means? The supply DC STBY BUS from DC ESS BUS or DC EMER BUS, according to one illuminated DC BUS 1 supplies the DC EMER BUS and DC BUS 2 supplies the DC ESS BUS 2 The supply of DC EMER BUS and DC ESS BUSS from DC BUSS 1 or DC BUS 2 Both batteries are discharging.
Where are the ACW generators connected? To the respective turbine shaft To the respective ram air turbine To the respective reduction gear box To the respective accessory gear box.
Each engine is equipped with: A continuous loop system monitoring overheat or fire A overhead nacelle detector Photoelectric sensing elements type Smoke detectors which trigger the warning for a certain amount of smoke.
Which of the following places is not protected by smoke detectors: The electrical panels in the cockpit The cargo compartments The lavatory The air conditioning compartment.
Jet pump is activated by: HP fuel from electrical pump + HP fuel return from engine hydromechanical unit + the jet pump pushbutton HP fuel from electrical pump HP fuel return from engine hydromechanical unit The jet pushbutton.
To feed engine nº 1 with tank nº 2, you must (with low pressure valve in line) open the crossfeed valve and: Select engine nº 1 fuel pump off and close the right LP valve Close the right LP valve Select engine nº 1 fuel pump OFF That is the only thing to do.
In normal operation, fuel electrical pumps are mainly used to: Pressurize the jet pump Start the engine Replace the jet pump in case of failure Provide the additional fuel flow required to take off.
The maximum asymmetrical fuel loading between wings is: 200 kg (440 lbs) 550 kg (1.212 lbs) No specified limit 160 kg (352 lbs).
Which kind of engine and/or propeller indications can be found on the MFD SD engine page? Torque, NP, fuel flow, oil pressure and temperature Torque, NP, fuel used, fuel temperature Torque, NP, ITT, whilst engine start rotatory selector is out of the OFF and Start Abort position, and fuel used NH, NL, ITT whilst the engine start rotatory selector is out of the OFF and Start Abort position, oil data and fuel data.
On which display units are engines and propeller data displayed? PFD and EWD MFD and PFD PFD, MFD and EWD EWD and MFD.
When selecting CRANK on the overhead ENG START panel, the igniter are energized: With **CL* at feather position With *CL* at fuel shut-off position With **CL* at AUTO position Never.
The EEC function is: To control, al low power level and low speed, a constant propeller All three answers are correct To provide the Uptrim in case of engine failure during take-off To ensure, at given engine rating, a constant PL position.
How do you shut off engine fuel supply? By the fuel 1/2 pump switch By the CL By the FUEL SO 1/2 switch By the PL.
The two altitude and heading reference systems (AHRS) provide the following data: Pitch, roll, heading, ground speed and time to go Pitch, roll, heading Altitude, airspeed and vertical speed Pitch, roll, heading and ground speed.
Where is the airspeed, altitudes and vertical speed information located? All are grouped on the PFD beside the ADI The ground speed is on the ND, the altitude on the IESI and the vertical speed on the VSI dial On the MFD, above the VCP On the EFIS.
The Pneumatic system supplies: Air conditioning / ventilation, pressurization and De Icing Pressurization, De Icing and engine cooling Air conditioning / ventilation, De Icing and engine crank Air conditioning / ventilation pressurization and engine cooling.
In normal operation, when does the ground crossfeed valve opens automatically? On ground, one engine running On ground, with both engines running and propeller brake "ON" or with one engine running In flight, with one engine running On ground, with both engines running and propeller brake "ON".
How is the constant frequency AC power obtained? From each ACW generator From each DC generator Directly from batteries From DC power through two inverters.
On air bleed panel: if packs pushbuttons are extinguished when depressed Packs valves are CLOSED and on SD cabin page, pack will be displayed in green in a green square Packs valves are CLOSED and on SD cabin page, nothing is displayed Packs valves are OPEN and on SD cabin page, pack will be display in green a green box Packs valves are OPEN and on SD cabin page, nothing displayed.
If no air pressure or if no electrical supply: The pack valve is spring loaded to CLOSED The pack valve is spring loaded to OPEN The pack valve returns to the previous position The pack valve remains in the last position.
Which pack(s) is (are) the supplier of the cabin? The pack 1 for 32% and pack 2 al 100% The pack 1 (left) only The pack 1 and pack 2 for 32% The pack 2 (right) only.
The selection of airflow "NORMAL / HIGH" from pack is: Automatic, depending of cabin air temperature Manual, with the flow pushbutton Automatic, depending of CL position Automatic, depending of PL position.
The COMPT TEMP setting knob: Control the TEMP CTL valve directly when TEMP SEL on AUTO and via the electronic controller when TEMP SEL on MANUAL Only control the temperature control valve through the electronic controller when the TEMP SEL in on AUTO position Controls the TEMP CTL valve directly when the TEMP SEL on MANUAL and via the electronic controller when TEMP SEL on AUTO Only controls directly temperature control valve when the TEMP SEL in on MAN position.
How many outflow valves are there? TWO: one electro-pneumatic outflow valve and one pneumatic outflow valve ONE: one electro-pneumatic outflow valve TWO: two electro-pneumatic outflow valve TWO: two pneumatic outflow valve.
In normal operation, without failure, the full automatic digital controller uses as reference the aircraft static air pressure generated by: ADC 1 and CAPT altimeter baro setting ADC 2 and CAPT altimeter baro setting ADC 1 and 1013.25 hpa ADC 2 and 1013.25 hpa.
If automatic pressurization control is desired, in which position should the CAB PRESS knob pointer be placed? At 9 o´clock with MOD SEL pushbutton depressed (extinguished) On the green squared with MOD SEL pushbutton in "MAN" position (MAN blue) On the green squared with MOD SEL pushbutton depressed (extinguished) At 9 o´clock with MOD SEL pushbutton in "MAN" position (MAN blue).
Above which airport elevation is the AUTOMATIC RETURN feature cancelled? 2500 ft above the departure airport elevation 3500 ft above the departure airport elevation 3500 ft above the destination airport elevation 2500 ft above the destination airport elevation .
The maximum cabin altitude (FL 250 DIFF PRESS 6psi)? 10.000 ft 20.000 ft 6.740 ft 9.500 ft.
In auto mode, what is the maximum cabin rate available with the descent rate pushbutton released (NORM): 550 ft/min 500 ft/min 400 ft/min 450 ft/min.
The recirculation fans: Are used recirculate a part of the cabin air, to increase fresh air supply Are used ti increase pack valve airflow when FLOW P/B in HIGH mode Are used recirculate a part of the FTL COMPT air, to increase fresh air supply Are used to improve cooling of heat exchanger on ground.
The auxiliary DC electrical motor driven pump is mounted: In both hydraulic systems In the green hydraulic system There is no DC electrical motor driven pump In the blue hydraulic system.
The hydraulic fluid is contained in: A single common pressurized tank located in the hydraulic bay (left landing gear fairing) A single common not pressurized tank located in the hydraulic bay (left landing gear fairing) A single common not pressurized tank located in the hydraulic bay (right landing gear fairing) Two separate tanks (blue in the left landing gear fairing. Green in the right landing gear fairing).
The IEP light diffuser ignition is controlled by: The ice detector panel The BEACON lights switch The STROBE lights switch The NAV lights Switch.
In flight, roll control is achieved by: Two ailerons each one with a spring tab and two spoilers Two ailerons each one with a spring tab Two ailerons each one with a spring tab and two speed-brakes Two ailerons only.
It is possible to access to either FMS 1 or FMS 2 from one MCDU Right, MCDU 1 can be linked with either FMS with the FGCP source selector Right, MCDU 1 can be linked with either FMS with the FGCP coupling selector Right, MCDU 1 can be linked with either FMS with the MCDU menu page Wrong, MCDU 1 is linked with FMS 1 and FMS 2 with FMS 2.
The landing gear position indications are controller by: Two isolated systems and two separate position indicators One system controlling one position indicator One system controlling two position indicators Two isolated system, SYSTEM 1 and SYSTEM 2 controlling one position indicator.
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