For the video cabin surveillance, how many cameras is it possible to use? 1 3 4 2.
What is the goal of the vent door on the cargo door? It is used to dump the pressure in flight It evacuates the overpressure in flight It is used to ventilate the cargo compartment on ground It evacuates any residual pressurization before door opening.
On SURV format, which 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.
Opening the cargo door panel starts MFC modules self-test even with batteries switched OFF? Wrong, the MFC modules are self-tested only when batteries are turned ON True, all the MFC modules are self-tested even when batteries are switched OFF True, the MFC modules 1A and 2A are self-tested even when batteries are switched OFF Wrong, the MFC modules are self-tested only when batteries are turned on and cargo door panel must be opened.
How is the take off alert inhibition function activated? Manually by pressing TO inhibit push button Manually through the EFCPs Automatically by the MFCs Automatically by the FWA.
A procedure can be completed with missed items False, it is not possible to set the focus on the next item without validating the current one True, once validated, the number of skipped items will appear on the procedure window top right corner False, the “PROCEDURE COMPLETE” is only available once all items are done True, crew must be very careful when doing a check list. .
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 110V The AC STBY BUS voltage is lower than 19.5V The DC STBY BUS voltage is lower than 19.5V.
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 by opening the cabin entrance door With DC GPU available and online, by pressing the DC SVCE /UTLY 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 the HOT EMER BAT BUS DC STBY BUS and AC STBY BUS through INV 1 are supplied form the HOT EMER BAT BUS DC STBY BUS and AC STBY BUS are supplied form the DC BUS 2 DC STBY BUS and ACSTBY BUS are supplied form the DC BUS 1 or the DC BUS 2.
Aircraft ground, engines running, and AC EXT PWR connected and ON AC EXT PWR has priority over the 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.
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 diffusers On the ceiling of the AFT cargo compartment and includes two diffusers On the ceiling of the AFT cargo compartment and includes one diffuser.
To detect an engine fire, it is necessary to have: Only one loop activated and the nacelle overheat detector activated Both loops activated or only one providing the other one is deselected Only one loop activated Both loops activated.
Concerning the fuel temperature sensors, there is one in each engine fuel feeding line and: One in the left tank One in each tank One in the right tank There are not any other sensors.
When does the het pump’s “MOTIVE FLOW VALVE” open? Anytime the related “PUMP” P/B is set to “RUN” and pressure from the HMU is sufficient Anytime the “MOTIVE FLOW VALVE” P/B is in (depressed) Anytime the related “PUMP” P/B is in (depressed) Whenever the electric pump output is low.
What is the main engine parameter? Propeller RPM (Np) Torque (Tq) High pressure spool RPM (NH) Low pressure spool (NL).
The maximum ITT at starting is: Up to 950o C during 5 seconds 840o < ITT < 950o : record in log book Up to 840o C during 20 seconds All three answers are correct.
The reduction gear box drives: The ACW generator, the fuel HP pump, the propeller and the associated control accessories The propeller and the associated control accessories, the ACW generator 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 electric motor driving HP via: Engine Electronic Control Reduction gearbox Accessory gearbox Hydromechanical unit.
In the event of one PEC channel failure: FAULT amber light illuminates on the affected PEC pushbutton and it has to be switched off with CL on 100% OVRD position The back up channel is taking over automatically and “SGL CH” illuminates amber beside the affected propeller indicator on the EWD The relevant propeller NP is frozen and the CL must be set to 100% OVRD position to be modified The relevant propeller NP is frozen at 102.5%.
The two CAC (Core Avionic Cabinets): Control and authorize the operation of A/C avionic systems only Monitor aircraft operations only Control and authorize the operation of A/C avionic systems AND they monitor aircraft status and aircraft operations Monitor aircraft status only.
On pilot flying (PF) side and in NORMAL configuration, the lower part of the Primary Flight Display (PFD) displays: Radio nav data and veering pointers indications only FMS messages only Horizontal situation indication and selected heading only Horizontal situation indication and selected heading AND radio nav data and bearing pointers indications AND FMS messages.
After illumination of “OVHT” OR “LEAK” local light on the overhead panel and SD CABIN page, the related system may be recovered: Only after system cooling (“OVHT” OR “LEAK” local alarm disappeared following an OVHT or a LEAK) Never in any cases Following a LEAK, only after system cooling (“LEAK” local alarm disappeared) Following an OVHT, only after system cooling (“OVHT” local alarm disappeared).
In auto mode, what is the maximum cabin rate available with the descent rate pushbutton depressed (FAST)? 500 ft/min 450 ft/min 400 ft/min 550 ft/min.
After landing, the Cabin depressurization rate is: + 550 5ft/min + 400 ft/min + 300 ft/min + 500 ft/min.
In “MAN MODE”, what are the maximum cabin rates of descent and climb available? -2000 ft/min to + 2500 ft/min -1500 ft/min to + 2000 ft/min -5500 ft/min to + 2500 ft/min -1500 ft/min to + 2500 ft/min.
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 ONLY Turn the MAN RATE knob to GREEN SQUARE (AUTO) position and then deselected “MAN” on the CABIN PRESS pushbutton Deselected “MAN” on the CABIN PRESS pushbutton and then TURN the MAN RATE knob to GREEN SQUARE (AUTO) position.
In case of total DC electrical power loss AUTO PRESS mode is still available and MANUAL PRESS mode and CABIN PRESS IND are also still available AUTO PRESS mode is still available and MANUAL PRESS mode and CABIN PRESS IND are lost AUTO PRESS mode is lost and MANUAL PRESS mode and CABIN PRESS IND are still available AUTO PRESS mode is lost and MANULA PRESS mode and CABIN PRESS IND are also lost.
PACK VALVE FAULT means: Actual valve position in disagreement with the selected position only Actual valve position in disagreement with the selected position or overheat downstream the compressor (T>204o C) Actual valve position in disagreement with the selected position or overheat downstream the compressor (T>92o C) Overheat downstream the compressor (T>92o C) only .
TEMP SEL: <<OVHT>> is triggered when: CABIN TEMP EXCEEDS 35ºc DUCT TEMP EXCEEDS 92ºc FLIGHT COMPT TEMP EXCEEDS 35ºc COMPRESSOR TEMP EXCEEDS 204OC.
On ground BATTERIES ONLY, engine 1 & 2 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 FULL 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.
On ground or IN FLIGHT, engine 1 & running, OVBD valve guarded switch in AUTO position & EXHAUST mode P/B moved on OVBD position: The OVBD valve is FULL OPEN and the U/F is OPEN The OVBD valve is PARTIALLY OPEN in flight and FULL OPEN ON GROUND 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 is CLOSED.
What is the normal accumulator pre-charge pressure on the three gauges located in the left landing gear fairing? 1.500 PSI 3.000 PSI 800 PSI 1.000 PSI.
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.
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 in flight To energize the auxiliary pump, if BAT master switch ON position.
The “OVHT” alert on the HYD PWR panel indicates an: Overheat of the pump case drain line Overheat of the hydraulic fluid reservoir Overheat in the return line Overheat in the supply duct.
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.
How to reset the normal communication through the boom set and microphone after having used the flight crew oxygen mask? By depressing the EMERGENCY knob on the oxygen 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 oxygen mask.
Windshields are protected against ice building up by: An electrically heated system consisting of small wires embedded between two layers of glass Two electrically heated systems consisting of small wires embedded between three layers of glass Two electrically heated transparent films incorporated between three layers of glass An electrically heated transparent film incorporated between two layers of glass.
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%.
Can you use the pneumatic de-icing system with both engines bleed valves off and engine running? Yes No, except engine de-icing No Yes, except engine de-icing.
When both airframe and engine de-icing are selected ON, they are: Simultaneously de-iced Only de-iced if also anti-icing is selected ON Totally independent Sequentially de-iced.
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.
Roll trim is performed using: Both spoilers Only right aileron tab Only left aileron tab Both left and right aileron tabs.
The anti-skid test is inhibited for wheel speeds above: 10 kt The anti-skid test is never inhibited 35 kt 17 kt.
If anti-skid channel fails, the A-SKID test will show: No “F” displayed for that channel An amber “N” displayed for that channel A flashing green “F” for that channel An amber “F” remaining displayed after the test.
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 << VNAV>> key function These pages can be opened with the << PERF>> key function These pages can be opened with the << PROG>> key function.
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 function The discontinuity is cleared by inserting the proceeding waypoint 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 systems The VHF 1 system only Both VHF systems The VHF 2 system only.
What 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.
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