ATR 72-600

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. 23.000kg / 50.705 Lb.

On NAV FORMAT, wich page is displayed by default. VOR /ILS page with Edit box on V /ILS 2 STBY frequency. VOR /ILS page with Edit Box on V/ILS 1 STBY frequency. VOR /ILS page with Edit box on V /ILS 1 ACTIVE frequency. VOR /ILS page with Edit 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.

In the cockpit, when the buzzer sounds for 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 exists. On the HDG button synchronize bug to the current A/C heading. On the HDG button only to synchronize the Heading 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 take-off power per engine. 2.750 SHP. RTO 2.750 SHP / TO 2.160 SHP. 2.192 SHP. 2.475 SHP.

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 only. 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 Pump Pushbutton.

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 for 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 speed (for instance on ground). 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 attitude 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, altitude 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.

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.

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 auto mode, what is the maximum cabin rate available with the descent rate pushbutton depressed (FAST). 550 ft/min. 500 ft/min. 400 ft/min. 450 ft/min.

The IEP light diffuser ignition is controlled by. The ice detector panel. The BEACON lights switch. The STROBE lights switch. The NAV lights Switch.

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. Right, MCDU1 can be linked with either FMS with the FGCP coupling selector. Right, MCDU1 can be linked with either FMS with the MCDU menu page. Wrong, MCDU1 is linked with FMS 1 and FMS 2 with FMS 2.

The landing gear position indications are controlled 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.

A visual seat position gage can be used for seat adjustment. The pilot aligns. The white balls to ensure proper sitting position. The colored balls to ensure proper sitting position. The red ball with the nose plane. The red balls to ensure proper sitting position.

What is the goal of the Cockpit door locking system control switch. Activates the buzzer. Activates the status light of the cockpit control panel. Activate the door control panel. Activate the cockpit door locking system.

On COM FORMAT, which page is displayed by default. VHF page with Edit Box on VHF 2 STBY frecuency. VHF page with Edit Box on VHF 1 STBY frecuency. VHF page with Edit Box on VHF 2 ACTIVE frecuency. VHF page with Edit Box on VHF 1 ACTIVE frecuency.

How is the MPC made up. It is composed of an AMP and a DMU part. It is composed of a FDAU and a DMU part. It is composed only of maintenance fuctions. Its composed pf a SSFDR/SSCVR part and an ACARS associated with its MCDU.

On the ATR-600s where are the Alert messages generated by the FWS displayed. On the crew alerting panel. On the engine warning display. On the primary flight display. On the multi-fuction display.

What are the conditions to activate the take-off alert inhibition fuction. A/C on ground, PWR MGT in TO position, both PL below TO position, both NH above 60% no oil low pressure alarm on engies. A/C on ground, PWR MGT in TO position, both PL at or above TO position, both NH above 60% no oil low pressure alarm on engies. A/C on ground, PWR MGT in TO position. A/C on ground, PWR MGT in TO position, both PL at or above TO position, landing gear lever up position.

The Pitch wheel of the FGCP is used for. Vertical speed (VS) only. IAS selection only. Vertical speed (VS), Pitch and IAS selection. Vertical speed (VS) and Pitch selection only.

What are the capacities of the batteries. Main battery: 26v / 43Ah Emergency battery: 26v / 17Ah. Both batteries: 24v/ 43Ah. Main battery: 28.5v /43Ah Emergency battery: 28.5v /17Ah. Main battery: 24v / 43Ah Emergency battery: 24v / 17Ah.

What is the nominal frequency of the AC constant frequency power. 50Hz. 488Hz. 400Hz. 341Hz.

DC SVCE/UTLY BUS shed amber light on the MAIN ELEC PWR panel illuminates when. The DC SVCE BUS is shed. At least one DC UTLY BUS or the DC SVCE BUS is shed. DC UTLY BUS 1 and DC UTLY BUS 2 are shed. The corresponding DC SVCE BUS and DC UTLY BUS P/B is switched off.

How is the ACW power obtained. From each DC generator converted in ACW by TRU, from ACW GPU and from batteries. From each ACW generator, from ACW GPU. From each ACW generator, from ACW GPU and from batteries. From each DC generator converted in ACW by TRU.

The ATR fire protection system provides. Auto extinguishing in case of engine fire. Detection, alerts and extinguishing for each engine, nacelles and cabin. Fire for electric compartments and battery only on ground. Fire alarm in the passenger compartment.

Engine fire extinguishing system includes. One main extinguisher bottle identified as A, one emergency bottle identified as B. Two extinguisher bottles which may be used for either engine 1 or engine 2. One extinguisher bottle, the precussion of which is controlled from flight compartment to be selected to one of two extinguishing ramp. Four extinguisher bottles, two per engine.

Pulling the fire handle enable to. Discharge the corresponding bottle. Set the corresponding AGENT switch to FIRE position. Arm the squibs enabling the discharge of the fire bottles. Validate the precussion of the single bottle.

Fuel quantity indicators display. Fuel volume remaining on board. Total consumption since engine start (expressed as volume). Fuel mass remaining on board. Total consumption since engine start (expressed as mass).

“Engine running "FEED LO PR" associated with FWS activation means”. Double pump failure (jet pump + electrical pump). Jet pump failure. Double pump failure (jet pump + electrical pump) or a leak in the fuel circuit. A leak in the fuel circuit.

LO LVL amber light and FWS activation mean that. Fuel quantity is lower than 160Kg (352Lbs. Fuel quantity is lower than 50Kg (110Lbs). Fuel pump is not delivering the correct pressure. Fuel quantity is lower that 100Kg (220Lbs).

Each electrical pump can supply one engine throughout the whole aircraft envelope. True, but only with crossfeed. True, each electric pump can even supply both engines throughout the aircraft flight. True. False.

Which kind of engine and/or propeller indications can be found on the EWD. Torque, Np, ITT and fuel used. Torque, Np, fuel flow, oil pressure and temperatures. Torque, Np, fuel used, fuel temperatures. NH, NL, ITT fuel flow, Oil pressures and temperatures and fuel temperatures.

Which ATPCS functions are available when it has been armed for take-off. Uptrim only. Autofeather only. Uptrim and autofather. None.

The engine electronic control (EEC). Arms auto-feather system during take-off. Acts on "HMU richness" program. Control the fuel shut-off function. Control auto feathering system during take-off.

During start sequence, the cross start system. Make use of EMER battery until 10% NH. Makes use of the main battery until 10% NH then uses main battery assisted by the opposite DC GEN until 45% NH. Makes use of the main battery and the opposite DC GEN. Makes use only opposite DC GEN to start.

What happens if you use the Power Lever with one EEC off. Faster that normal engine deceleration and accelereation acoompanies any forward or rearward movement of the power lever. Slower that normal engine acceleration and faster that normal engine deceleration accompanies any forward or rearward movement of the power level. Slower that normal engine deceleration and faster that normal engine acceleration accompanies any forward or rearward movement of the power level. Slower that normal engine deceleration and acceleartion accompanies any forward or rearward movement of the power level.

The altitude selection Bug is set. Using the ALT SEL rotary selector on the FGCP. On the multifuctional control display unit (MCDU). On the index Control Panel (ICP). With the pitch wheel of the flight guidance and control panel (FGCP).

What are pack valves functions. The pack valves functions is to SHUT OFF the PACK, CONTROL the PRESSURE and ENHANCE FLOW CONTROL. The pack valves function is to SHUR OFF the PACK only. The pack valves functions is to CONTROL the PRESSURE only. The pack valves functions is to SHUR OFF the PACK, CONTROL the PRESSURE and CONTROL the TEMPERATURE.

The ground cooling turbo fan is running. When the ground cooling turbo fan valve is open only. When the ground cooling turbo fan valve is open, and the landing gear is down or retracted for less that 7 minutes and speed 140KTS. When the ground cooling turbo fan valve is open, and the landing gear is down or retracted for less than 10 minutes KTS. When the landing gear is down or retracted for less than 10 minutes only.

Pack valves are. Electrically operated and pneumatically controlled. Pneumatically operated and electrically controlled. Electrically operated and electrically controlled. Pneumatic operated and pneumatically controlled.

What are the correct indications during a ground pressurization system test. Only, the landing elevation indicator displays alternately 8800 and -8800. The amber "FAULT" light in the MAN pushbutton and the landing elevation indicator displays alternately +8800 and -8800. The amber "FAULT" light in the MAN pushbutton an the landing elevation indicator displays alternately 18800 and -8800. The amber "FAULT" light in the MAN pushbutton only.

Which data is set on the AUTO PRESS panel before each flight. The PRESSURE ALTITUDE (Using 1013.25) of the DESTINATION airport. The PRESSURE ALTITUDE (Using 1013.25) of the DEPARTURE airport. The ALTITUDE (Using QNH on CM1 Altimeter) OR ZERO (Using QFE on CM1 Altimeter) of the DEPARTURE airport. The ALTITUDE (Using QNH on CM1 Altimeter) OR ZERO (Using QFE on CM1 Altimeter) of the DESTINATION airport.

The maximum cabin rate of climb, up to 20.000 ft in auto mode is. +550ft/min. +450ft/min. +500ft/min. +400ft/min.

The COMPT TEMP indicator displays. Only the compartment temperature of selected side. The compartment and the duct temperature of the selected side. The pack and the duct temperature of the selected side. The compartment and the pack temperature of the selected side.

Each hydraulic system is normally pressurized by means of. ADC electric motor driven pump. An engine driven pump. An ACW electrical motor driven pump. An alternate pump.

Ice Evidence Probe (IEP) is located. On the lower frame of the left side window. On the lower frame of the right side window. In front of the captain's windshield. Below the left wing leading edge.

To prevent icing on air data sensors, the probes are heated. On ground and flight, exept TAR sensors which are heated only on ground. On ground and in flight, except TAT sensors which are heated only in flight. On ground and flight. In flight only.

For the video cabin surveillance, how many cameras is it possible to use. 1. 3. 4. 2.

On SURV format, wich page is displayed by default. XPDR page, with Edit box on ALT OFF. XPDR page, with Edit box on FLT ID. XPDR page, with Edit box on ATC code. XPDR page, with Edit box on XPDR.

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 that 24V. The AC STBY BUS voltage is lower that 110V. The AC STBY BUS voltage is lower that 19.5V. The DC STBY BUS voltage is lower that 19.5V.

Aircraft on ground, engines running and AC EXT PWR connected and ON. AC EXT PWR has priority over ACW GEN. The first online has priority AC EXT PWR has no priority over the. ACW GEN. AC EXT PWR supplies the busses which are not supplied by the ACW GEN.

To detect an engine fire, it is necessary to have. Only one loop actived and the nacelle overheat detector activated. Both loops activated or only the one providing the other one is deselected. Only one loop activated. Both loops activated.

The reduction GearBox drives. The ACW generator the fuel HP pump the propeller an the associeted control accessories. The propeller and the associated control accessories, the ACW. The DC start / generator the HP fuel pump the oil pumps. The propeller and the associated control accessories.

Each DC starter/generator during engine start acts as an electrical motor driving HP via. Engine electronic control. Reduction gearbox. Accessory gearbox. Hydromechanical unit.

How to reset the normal communication throught the boomset and microphone after having used the flight crew oxigen mask. By depressing the emergency knob on the oxigen mask. By selecting INT position on the INT/RAD switch on the audio control panel. By depressing the PRESS TO TEST AND RESET P/B on the oxygen mask compartment. By selecting the N/100% rocker in the N position on the oxigen mask.

Roll trim is performed using. Both spoilers. Only right aileron tab. Only left aileron tab. Both left and right aileron tabs.

How can the take-off, cruise and approach page be opened. These pages can be opened with the DATA key fuctions. These pages can be opened with the VNAV key fuctions. These pages can be opened with the PERF key fuctions. These pages can be opened with the PROG key fuctions.

When does TCAS system begin the tracking phase. When the intruder reaches the RA limit. When the intruder reaches the detection limit. When the intruder reaches the detection limit and is equipped also with TCAS system. When the intruder reaches the TA limit.

What is the important thing that you need to do before opening the cockpit emergency hatch. It is important to disconnect the electrical connector and the water drain. It is important to open the vent door on the cargo door. It is important to switch off the door locking system. It is important to open the side window in the cockpit.

In the cockpit, on the doors control panel, if you depress the SW TEST pushbutton. It tests cabin a service doors microswitches. It tests all cargo door microswitches. It tests emer doors. It tests the service door and cargo door only.

What is the purpose of the FDAU part of the MPC. The flight data recording, the APM, time and aircraft configuration management. Manage the ACMS function, the APM, data broadcast to CAC, communicates with ACARS and MCDU. The flight data recording, the APM, data broadcast to CAC, communicates with ACARS and MCDU. Reports management The flight data recording, the APM, data broadcast to CAC, time and aircraft configuration management.

Concerning the normal check lists. They are always automatically popped-up according to the different flight phases. They are always automatically called according to the different flight phases. They can only be called up manually form the EFCP left. They are always automatically popped up according to the different flight phases or can be manually called.

One ACW generator off-line. ACW SVCE BUS only is shed. The ACW BUS 2 is lost. The associated ACW BUS is lost. All ACW busses remain supplied by the remaining generator.

The DISCH amber light indicates. The fire bottle is empty. The fire bottle is discharging. The right P/B to discharge a bottle. A successful discharge head test.

The propeller brake is powered by. A separate accumulator. Hydraulic blue pressure. Hydraulic green pressure. Either hydraulic blue or green pressure.

During landing, when does the idle-gate move reward to the Ground Idle position. Only after all gear shock absorbers are compressed. Only after manual action from the pilot. Only after both main gear shock struts are compressed. As soon as one main landing gear absorber is compressed.

Is the fuel heated to prevent icing. Yes, by a heating resistor installed at the filter outlet. No, it is not necessary. Yes, by mean of self-monitoring EEC. Yes, by a fuel heater installed at the filter outlet, heated by engine oil.

PROP BRK blue light is illuminated on the engine start panel and is displayed on the EWD when. Propeller brake is fully locked. The propeller brake is not locked in fully locked or the fully released position. Engagement of disengagement conditions are met. Propeller brake is not released.

The yellow arrow on the speed scale indicates. The current aircraft speed. The aircraft speed prediction 10 seconds ahead. If the aircraft is climbing or descending. The never to exceed speed.

On the ATR600, the IESI (Integrated Electronic Stand-by Instrument). Combines the Stand-By Horizon, the Stand-By Airspeed Indicator, the Stand-By altimeter and the Stand-By Compass. Combines the stand by horizon, the stand by airspeed indicator and the stand by altimeter and stand by compass Is ONLY a stand by horizon. Combines the stand by horizon and the stand by altimeter.

The pneumatic system is. Generally supplied by engine HP stage. if the air is not sufficient, air surge is switched to the Engine LP stage (descent, flight idle, ground operation). Always supplied by Engine LP stage. Always supplied by engine HP stage Generally supplied by engine LP stage. if the air is not sufficient, air surge is switched to the Engine HP stage (descent, flight idle, ground operation).

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 2 and CM2 altimeter baro setting. ADC 2 and 1013.25 Hpa ADC 2 and IESI altimeter baro setting.

What happens in case of loss of electrical supply to the "DIGITAL CONTROLLER" in automatic mode. Both outflow valves go to "FULL CLOSE". Both outflow valves remain in the last position. Both outflow valves go to "FULL OPEN". The electro-pneumatic valves goes to "FULL CLOSE" and the pneumatic valve remains in the last position.

On ground, the air supplied to the Air Conditioning System may come from. Engine 2 in hotel mode only or air ground conditioning unit. Engines or air ground conditioning unit. Engine 2 in hotel mode only. Engines only.

What is the purpose of the N/100% rocker on the flight crew oxygen mask. It enables to reset the hot mike communication. It is to choose between diluted or pure oxygen delivery. It is to choose the level of oxygen pressurization in the mask. It allows to shut off the oxygen delivery or not.

At least one horn is ON. Icing AOA illuminate of FMA only. Icing AOA illuminate of FMA and on ICE detector control panel. Icing amber message illuminetes on the EWD. Icing yellow message start flashing on the FMA.

What the MODE SEL AUTO P/B fault amber light illumination means. The de-icing and anti-icing MODE SEL P/B are operative and the low power cycle is automatically activated. 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. The de-icing and anti-icing MODE SEL P/B are inoperative and the normal mode is automatically activated. The de-icing and anti-icing MODE SEL P/B are operative and the slow mode is automatically for the de-icing.

In case of total hydraulic failure, the parking and emergency brake accumulator allows. Six complete braking application with ANTI-SKID protection. Differential braking for aircraft control. One brake application with full braking pressure. Six complete braking application without ANTI-SKID protection.

For prediction computation, an accurate and a simplified wind model is available. what are the ways to insert the two types of wind profiles. The simplified wind model is inserted through the CRUISE page and the accurate one through each waypoint s vertical revision. The simplified or accurate wind models are inserted through the CRUISE page. The simplified or accurate wind models are inserted through the PROG page.

How to insert a HOLD. The HOLD is inserted via the vertical revision keys via the next waypoint only. The HOLD is inserted via the lateral revision keys, via the next waypoint only. The HOLD is inserted via the lateral revision keys whichever the waypoint. The HOLD is inserted via the vertical revision keys whichever the waypoint.

TCAS is controlled through the MCDU. In the TCAS page available in the MENU. In the TCAS page available in the NAVIGATION page. In the TCAS page available in the COMMUNICATION page. In the TCAS page available in the SURV page.

ATC transponder can be tuned through. MCP and MCDU only. MCP only. MCP and IESI only MCP. MCDU and IESI.

The ALT SEL mode is automatically armed when the aircraft climbs (or descends) towards the selected altitude Incorrect. There is no arming phase in the ALT SEL mode. This assertation is correct. Incorrect: the STBY mode must be depressed to enable the new altitude to be selected. Incorrect: the ALT SEL mode must be armed them engaged before selecting a new altitude.

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 refueling panel, the cargo door control panel, the cabin door, the HYD AUX PUMP P/B. The refueling panel, the cargo door control panel, the cabin door, the HYD AUX PUMP P/B, the hydraulic access panel. The refueling panel, the cargo door control panel, the cabin door, the cabin and cockpit entrance light, the HYD AUX PUMP P/B.

The inverter 1 normal supplies. The AC BUS 1 and the AC STBY BUS. The AC BUS 1 and the AC BUS 2. The AC BUS 2 and the AC STBY BUS. The AC BUS 1.

“A” “GATE” prevents PL angle reduction below FI. At take off as soon as landing gears are up and locked. At take off as soon as the landing gears lever is selected up. At take off as soon as one main landing gear absorbers released. At take off as soon as both main landing gears absorbers are released.

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. The other pack supplies both compartments (flight compt and cabin) via the pneumatic cross feed. Hot air is still available from that pack via the temperature control valve when TEMP SEL is in MAN mode only. The other pack supplies both compartments (flight compt and cabin) through the mixing chamber.

It is possible to supply the airframe de-icing boots when the AFR AIR BLEED P/B is OFF. Yes. Not. Yes, is the DE-ICING MODE SEL is OVRD position. Yes, if a fire handle is not pulled.

The pneumatic de-icing system is supplied by air, bleed from. External air directly. The engine High- and low-pressure compressors. The engine low pressure compressors. The engine high pressure compressors.

What protects the rudder from excessive travel speed caused by wind gusts when on ground. No protection is necessary. A hydraulic damper. The RCU. The TLU.

The anti-skid is available for wheels speeds greater than. 10 kt. 35 kt. 40 kt. 25 kt.

How is the take-off alert inhibition function actived. Manually by pressing. TO inhibit push button. Manually through the EFCP's Automatically by the MFC's. Automatically by the FWA.

No engine running, how can the DC SVCE BUS be powered. With battery by pressing the DC GND SVCE BUS switch on the cabin attendant panel and the DC SVCE / UTLY BUS P/B in the cockpit. With DC GPU connected and confirming GND SVCE BUS on ON position on the cabin attendant panel. With battery bay opening the cabin entrance door. With DC GPU available and on-line, by pressing the DC SVCE/ ULTY BUS P/B in the cockpit.

Depressing the STBY BUS OVRD P/B. DC STBY BUS is supplied by the HOT MAIN BAT BUS and AC STBY BUS through INV 1 by te HOT EMER BAT BUS. DC STBY BUS and AC STBY BUS through INV 1 are supplied from the HOT EMER BAT BUS. DC STBY BUS and AC STBY BUS are supplied from the DC BUS 2. DC STBY BUS and AC STBY BUS are supplied from the DC BUS 1 or the DC BUS 2.

The fire extinguishing system of the AFT cargo compartment is installed. On the side walls of the AFT cargo compartment and includes one diffuser. On the floor of the AFT cargo compartment and includes two diffuser. On the ceiling of the AFT cargo compartment and includes two diffuser. On the ceiling of the AFT cargo compartment and includes one diffuser.

Concerning the fuel temperature sensors, ther is one in each engine fuel fedding line and. One in the left tank. One in each tank one in the right tank. There is not any oather sensors. There are not any other sensors.

The two CAC (Core Avionic Cabinets). Control and authorize the operation of A/C avionic systems only. Monitor aircraft operations only. Control and the authorize the operation of A/C system AND they monitor aircraft status and aircraft operations. Monitor aircraft status only.

“What is the correct way to switch the auto press system from "manual" to "auto" “mode”. Deselected "MAN" on the CABIN PRESS pushbutton ONLY. Turn the MAN RATE knob to GREEN SQUEARE (AUTO) position. Turn the MAN RATE knob to GREEN SQUEARE (AUTO) position and deselected "MAN" on the CABIN PRESS pushbutton. Deselected "MAN" on the CABIN PRESS pushbutton and then Turn the MAN RATE knob to GREEN SQUEARE (AUTO) position.

PACK VALVE FAULT means. Actual position in disagreement with the selected position only. Actual position in disagreement with the selected position or overheat downstream the compressor (T>204°C). Actual position in disagreement with the selected position or overheat downstream the compressor (T>92°C). Overheat downstream the compressor (T > 92 Celsius) only.

TEMP SEL: OVHT is triggered when. CABIN TEMP EXCEEDS 35°Celsius. DUCT TEMP EXCEEDS 92°Celsius. FLIGHT COMPT TEMP EXCEEDS 35°Celsius. COMPRESSOR TEMP EXCEEDS 204°Celsius.

Who is supplied by the fixed oxygen system. The flight crew members only. The cabin crew members and the passengers. The flight crew members and the passengers. The flight crew members and the cabin crew members.

Where are located the anti-icing and de-icing systems status information. On the FMA of each PFD. On the EWD. On the temporary selection window of each MFD and on the overhead panel. On the temporary selection window of each MFD only.

To prevent overheating, propellers anti-icing is inhibited when Np is. Bellow 63%. Above 36%. Bellow 36%. Above 63%.

The anti-skid test is inhibited for wheel speeds above. 10 kt. The anti-skid test is never inhibited. 35 kt. 17 kt.

How can you clear a discontinuity in a flight plan. The discontinuity is cleared by inserting the next waypoint in place of the discontinuity. The discontinuity is cleared by pressing the cleaner "MRK" key functions. The discontinuity is cleared by inserting the proceeding in place of the discontinuity. The discontinuity is cleared by inserting a CLEAR in place of the discontinuity.

Through the IESI, the pilot can tune. The VHF 1 and the HF 1 system. The VHF 1 system only. Both VHF systems. The VHF 2 system only.

What is the nominal voltage of the DC generators. 26V. 28V. 30V. 115V.

BAT switch on the MAIN ELEC PWR panel on OVDR position means. Allow to be sure that DC EMER/STBY BUS are supplied by the HOT EMER BAT BUS and the DC ESS BUS is supplied by the HOT MAIN BAT BUS. Each battery continues to be charged by its respective DC BUS. Allow to be sure that DC EMER BUS is supplied by the HOT EMER BAT BUS and the DC ESS/STBY BUS are supplied by the HOT MAIN BAT BUS. DC/AC STBY BUSses are transferred from the DC ESS BUS to the DC EMER BUS.

The DC generator comes on line at. NH = 45%. NH = 66%. NH = 70%. NH = 61.5%.

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 least fuel quantity. Either both fuel pumps are ON or OFF Fuel pump is OFF in the tank with the least fuel quantity. Either both fuel pumps are ON or OFF or fuel pump is OFF in the tank with the most fuel quantity.

Where can you read the fuel quantity. Fuel quantity is displayed on the FMA. Fuel quantity is displayed on the MFD secondary engine display page. Fuel quantity is displayed on weight page of the MCDU. Fuel quantity is displayed on the EWD beside FOB (fuel on board).

Where is the fuel used reset button located. On the VCP associated with the secondary engine system page. On the MCDU associated with the primary engine system page. On the MCDU associated with the WEIGHT page. On the VCP associated with the PERF page.

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%. On RH engine, engine start selector is on start, porpeller brake is on, but gust lock is not engaged. Not engine start selector.

"When ""FUEL PUMP"" pushbutton is released out". Electrical pump is de-activated and “OFF”. Motive flow valve closes and jet pump stop to operate. Electrical pump is de-activated and ""OFF"" white light illuminates on pushbutton.

Following an engine 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. AGENT 1 DISCH illuminated on engine 2. Engine 2 and AGENT 1 DISCH illuminated on engine 1.

Assuming normal operation in fliht, when are the DC EMER BUS and then DC 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. Always directly Only when the respective battery needs charging. When the BAT switch is set to OVRD position.

Which pushbutton must be pressed on the FGCP to intercept and track a VOR course. BC. APP. NAV.

In GO AROUND. The AFCS provides FD commands only to manually acquire and maintain predetermined safe pitch altitude and present heading. Disengage AP and FD bars disappear. The GA PB when depressed, automatically moves the PL to the require power setting, but the pilot should manually maintain the speed.

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. Postponed actions and limitations are automatically embodied in pending list´s stored status. Are automatically embodied in pending.

Concerning the main failure detection phases, we can say that. Four main phases are available: 1-Isolation, 2-Detection, 3-Identification, 4-Confirmation. Phases are available: 1-Isolation, 2-Detection,. Four main phases are available.

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. It is not equipment. Only mode C.

Which statement is correct. A mode A equipped intruder can in the worst case cause a Resolution Advisory. Each pilot who deviates from an ATC clearance in response to a TCAS II. Resolution advisory (RA) is expected to "maintain the course and altitude resulting from the deviation.

TCAS information is displayed. On the PFD - HSI for traffic background. All are grouped on the PFD beside the ADI. On the MFD, above the VCP.

VHF1 and VHF2 transceivers are respectively supplied by. The DC EMER BUS and the DC ESS BUS. The DC EMER BUS and the DC BUS 2. The DC ESS BUS and the DC EMER BUS. The DC ESS BUS and the DC BUS 2.

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 two frequencies only. only one frequency at the same time.

Each Radio Management Application (RMA) is. A computer located in the avionic rack. A computer located in the comparment. In the CAC.

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. Do not pack the oxygen mask. Just wear the oxygen mask.

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 VHF1. VHF2. The captain station is connected directly.

The Audio Integrated system is connected to. The Cockpit Voice Recorder, the Passenger Address and the VHF and HF system. VHF 2 automatically. ADF 1 automatically and VHF 1 automatically.

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). 2 (one on each ACP). 6 (one on each ACP, one on each control column, one on the nose wheel steering handle, one near the observer seat).

When is the Passenger Address volume increased. As soon as the PA selection key on the ACP is selected. Only selectioning one PA. Speaking for the microfhone.

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 is posible. Not.

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 PERF. It is selected through the COM.

In flight, where can you check the Actual Navigation Performance (ANP). It is possible to check the ANP. It is not possible to verify it. According to the performance of the plane.

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. Not, It is not possible. Yes, verify function on the PERF.

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. The only method of airway insertion is through the lateral revision page at each landmark. Through any point.

On the ATR-600s where is the FWS function implemented. In the MFC and in the FWA. In the MFC In the CAC and in the display units. In the Flight Warning Application implemented in the CAC.

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. It is only possible to create a flight plan. Many flight plans can be created at the same time.

In the FMS Operational Domain, what is the maximum Ground Speed (GS). 820Kt. 170 Kt. 620 Kt.

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 15kt. Touchdown protection preventing inadvertent brake application for 6 seconds after touchdown or until wheels speed is above 30kt.

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. No, the wheels never stop. They are always braked after takeoff.

“ For how long are the amber” "F" displayed during the A-SKID test". As long as the TEST push-button is depressed. Always displayed. Shows for 20 seconds.

What is the maximum passengers configuration on ATR 72-600. 74. 72. 68. 76.

The Nose Wheel Steering is available. As soon as the Landing Gear control Lever is placed on ""DOWN""". At the moment the train control lever is selected. Only when the indication is shown in green.

The Nose Wheel Steering switch. The Nose Wheel Steering switch. It is a switch that never turns off. This switch helps to de-energize the nose wheel.

“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. At least one PL is at FI and Radio altitude is above 500. The two PL are at FI.

The LDG GEAR is considered down when 3 green triangles are illuminated on. The central instrument panel LDG GEAR indicator ONLY. Both, overhead and central instrument panels. Either, overhead or central instrument panel.

Concerning the LDG GEAR selector valve. There is only one valve, located in the LH Main Landing Gear Fairing. There are two valves. In each landing gear are valves.

The anti retraction latch of the landing gear control lever prevents selecting ""UP"" if". At least one gear shock absorber senses weight on wheels. The first leg of landing gear unlocks before retraction. Gear is locked up.

The LDG GEAR not down alarm is generated by. MFC 2 associated to SYSTEM 2. MFC 1 y 2 associated to SYSTEM 2. MFC 1 associated to SYSTEM 2.

If the aircraft is on battery power. Only the primary LDG GEAR indicator is operative (SYSTEM 1). The indicator does not work when inoperative. Only the primary indicator LDG GEAR is operational (SYSTEM 2).

The flaps position indicator becomes red whe. An uncommanded flaps retraction of more than 4 degrees. An uncommanded flaps retraction of more than 3. An uncommanded flaps retraction of more than 2.

What is the VFE of the flap settings. VFE flaps 15 degrees = 190Kt and VFE flaps 30 degrees = 150Kt. VFE flaps 15 degrees = 170Kt and VFE flaps 30 degrees = 150Kt. VFE flaps 15 degrees = 160Kt and VFE flaps 30 degrees = 150Kt.

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. Flap valve is hydraulically commanding flaps extensión. With flaps extended, it indicates a hydraulic leak.

The stick pusher actuator is attached to. The CAPT control column. F/O control column. CPT's and F/O's control columns.

The stick shaker is generated by. Two stick shaker actuators, one on each control column. One stick shaker actuator. Only the actuators.

The gust lock acts on. Roll controls, pitch controls, and rudder controls. Roll control and pitch control. Roll control and rudder control.

The TLU LO SPEED indication is displayed. In green when rudder travel is limited. In cyan when rudder not travel. TLU not indication.

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). 190kts during acceleration and deceleration. 180kts during acceleration and deceleration.

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. Do not allow stabilization of the rudder. Adjusts according to the indication.

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 with the maintenance action. Through the P / B clutch lift on the right maintenance panel if the air conditioner is on the ground and the burst lock is disabled.

An aural whooler alert is generated when. 1 degree movement or more on the yaw trim indicator scale. Pitch trim rocker use for more than 1 second. Movement on pitch trim position indicator.

If one control column is jammed. The pitch uncoupling procedure allows the other control column to operate both elevators. The Pitch uncoupling procedure allows the other channel to operate one elevator. An automatic pitch uncoupling allows the other channel to operate the two elevators.

What does the green band on the pitch trim scale mean. It corresponds to the take-off pitch trim range. Pitch trim rocker use for more than 1 second. Movement on pitch trim position indicator.

Pitch control is achieved by. One mechanically driven elevator. One Hidraullically driven. Mechanically and Hidraullically.

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 is disengaged and the aileron trim is inhibited. The autopilot is engaged.

Each spoiler has a hydraulic actuator which is controlled. Mechanically by the associated aileron linkage. Mechanically by the related fire handle. Electrically by the related condition lever.

The spoilers cyan triangle light illuminate to indicate that. The associated spoiler is in retracted position. The spoiler has not indication. Associated spoiler is in extended position.

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. Only lights up if flight conditions require it. It should not light at any stage of the flight.

What is the last part of the airframe to become clear of ice when leaving ice accretion and icing conditions. Ice Evidence Probe. In front of the captain's windshield. Below the left wing leading edge.

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. The Cyan ICING message illuminates on the PFD. Message illuminates on the EWD and PFD.

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. AIRFRAME message blinks on PFD and EWD. No message appears.

Can you use the pneumatic de-icing system with both engines bleed valves off and engine running. Yes. No, except engine de-icing. Yes, except engine de-icing.

How are the horns anti-iced. Electrically and pneumatically. Only electrically. Pneumatically and hydraulically.

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 light up when the emergency battery voltage is less than 24 V. Only when a DC 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 three emergency exits in the cabin: one in front and the passenger door and the hatch of the cabin. There are two emergency exits in the cabin: one in front and the passenger door.

How is the oxygen delivered to the passengers. By the mean of portable oxygen bottle for 10% of passengers. By means of oxygen masks. Oxygen is found in each of the passenger seats.

How many portable oxygen bottle are fitted in the ATR72. 4 located in the cockpit and in the cabin. 2 one in each cabin. 5 located throughout the cabin.

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 blue hydraulic system. Only operates flight To energize the auxiliary pump, if BAT master switch ON position.

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. 1500 PSI on gas pressure gauges in the hydraulic bay only 1500 PSI on gas pressure gauges in the hydraulic. 0 PSI in the cockpit and 0 PSI on the pressure gauges in the hydraulic bay 0 PSI of hydraulic pressure in the cockpit only.

The nominal hydraulic pressure of Blue and Green systems is. 3.000 PSI. 1.500 PSI. 800 PSI. 1.000 PSI.

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. Electric motors keep both outlet flow valves in the OPEN position, regardless of using MANUAL or AUTO PRESS mode, and the message ON is written in white on the button BUT there is no FWS ALARM. Electric motors connected to the other outlet flow valves in position, open and the other closed.

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. On ground only, MAN or AUTO PRESS mode. It only works in AUTO PRESS mode.

What is the MAX difference press allowed to select the OVBD VALVE switch to FULL OPEN position. 0.35 PSI. 0.55 PSI. 1 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 OVBD valve is PARTIALLY OPEN and the U/F is OPEN The OVBD valve is FULL OPEN and the U/F is OPEN. The OVBD valve is FULL CLOSE and the U/F is OPEN The OVBD valve is FULL OPEN and the U/F is CLOSED.

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 NOT ILLUMINATE. The Ground Mechanic Call sounds". "Extract fan stops during 120"" to avoid pressure shocks. During this period, the EXHAUST MODE P/B FAULT WILL NOT ILLUMINATE.

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 AUTO MODE failure or for cold days (on ground) in order to expedite cabin heating by setting it in FULL OPEN. For cold days (on ground) in order to expedite cabin heating by setting it in FULL CLOSE only In case of AUTO MODE failure 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 OPEN and the U/F is OPEN. The OVBD valve is FULL CLOSED and the U/F is OPEN The OVBD valve is PARTIALLY OPEN in flight and FULL OPEN ON GROUND and the U/F CLOSED.

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 17V or when at least one generator operating. When DC STBY BUS voltage reach 24V or when at least two generators 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 FULL CLOSED and the U/F is OPEN. The OVBD valve is FULL OPEN and the U/F is CLOSED. The OVBD valve is FULL OPEN and the U/F is OPEN.

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. OVBD valve is FULL CLOSED and the U/F is OPEN. The OVBD valve is FULL OPEN and the U/F is CLOSED. The OVBD valve is FULL OPEN and the U/F is OPEN.

What is the maximum crosswind component to operate the cargo door. 45 kt. 70 kt. 35 kt.

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 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.

Where is located the Packs. The Packs are located under the Cabin floor. The packages are between the compartments. The packages are in the cargo comparment.

In which case does the Bleed Air Shut-off Valve close automatically. OVHT, LEAK, Absence of air pressure. OVHT, LEAK, LACK of air pressure or loss of electrical supply. Fire handle pulled, PROP break On (for left bleed Valve only) and during starting sequence A+B.

"What happens, without air pressure and when ""WNG 1 or 2 BLEED"" pushbutton are depressed". Bleed Valve must be closed manually. Bleed valve stays open. Bleed valve closed automatically.

SD CABIN, SD ENGINE SECONDARY, SD ELEC, SD ACW/HYD pages can be displayed using. The ND key on the EFIS CONTROL PANEL (EFCP). The MODE key on the control panel. The key on the VCP.

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 green memo WITH DEVICE in the temporary selection window in the MFD. Cyan memo WITH DEVICE in temporary selection window on PFD.

Which systems are supplied by the blue hydraulic circuit. Nose wheel steering, flaps, spoilers, propeller brake, normal brake. Landing gear, emergency & normal brake. Nose wheel steering, flaps, spoilers, propeller brake, emergency & parking brake. Landing gear, normal brake.

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. Blue only. Green only. Both. Neither.

Roll control is achieved by actuating. Mechanically the spoilers and the ailerons. Mechanically the ailerons and hydraulically the spoilers. Hydraulically the ailerons and the spoilers. Mechanically the spoilers and hydraulically the ailerons.

TCAS is controlled through the VCP via. In the TCAS page available in the MENU In the TCAS page available in the NAVIGATION page. In the TCAS page available in the COMMUNICATION page. 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.

Which systems are supplied by the green hydraulic circuit. Landing gear, emergency & normal brake. Landing gear, normal brake. Nose wheel steering, flaps, spoilers, propeller brake, normal brake. Nose wheel steering, flaps, spoilers, propeller brake, emergency & parking brake.

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.

On the LDG GEAR indicators, the “UNLK” light illuminates to indicate that. An uplock box has failed. Down-lock device has failed. Respective gear not seen locked in lever selected position, or on ground up-lock box not in the right position.

LDG GEAR normal operations. The main gear wheels are braked automatically as soon as the lever is selected up. In the connecting lines, hydraulic pressure is released when the gear is locked in the commanded position (UP or DOWN). All of the above is correct.

The simplified wind model is inserted through each waypoints. Lateral revision page and the accurate one through each waypoints vertical revision page. The vertical review page and the precise one through each vertical waypoint review page. Lateral revision page and the accurate one through each waypoints lateral revision page.

What happens in the AFCS when the BAT selector is set to on. They are only powered. All data is erased. The software is upgraded. An auto-test of the MFC's occurs.

The normal accumulator pre-charge pressure on the three gauges located in the left landing gear fairing. 1.500 PSI. 3.000 PSI. 8.00 PSI. 1.000 PSI.

In MAN MODE, what are the maximum Cabin rates of descent and climb available. -1500ft/min to +2.500ft/min. -1600ft/min to +2.000ft/min. -1500ft/min to +2.000ft/min.

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.