Test 2.0

How many type computers has the auto flight system (AFS) installed on the aircraft?. 3. 2. 4.

2. The Flight Management and Guidance Computer (FMGC) is part of. The Flight Augmentation Computer (FAC). The Auto Flight System (AFS). The Multipurpose Control and Display Unit (MCDU).

The autopilot (AP), flight director (FD), automatic thrust control (A/THR) and flight management are functions of: The Flight Augmentation Computer. The Flight Management and Guidance Computer. The Multipurpose Control and Display Unit.

The Flight Control Unit (FCU) is used to the engagement of the AP/FD and A/THR systems the selection of flight parameters (altitude, speed/Mach, vertical speed/flight path angle, heading/track) the selection of AP/FD modes. True. False.

The ACARS management unit allows the management of the data entered by: The crews and transmitted to the ground. The ground station and transmitted to the crew. The crew and transmitted to the other airplane.

What is the system that integrates and manages all audio signals supplied and sent to the radio communication and radio navigation systems?. The Interphone system. The Audio Integrating System. Voice privacy system.

The Very High Frequency (VHF) system is used for?. All short-range voice. All range voice. All large-range voice.

How many service interphone jacks are installed at different locations on the aircraft?. 10. 8. 5.

What is the function of static dichargers?. To decrease the effect of the interference cused by static electricity. to increase the effect of the interference caused by static electricity. to decrease the effect very low radio-frequency.

the cockpit voice recorder (CVR) is designed to record crew conversation and communications: in flight and on the ground. on the ground only. in flight only.

when the CVR can to record crew conversation and communication?. at least one engine is running or to five minutes after the second engine is shut down. two engine is running. at least one engine is running or to thirly minutes after the second engine is shut down.

what is the function of the cabin intercommunication data system (CIDS) ?. is used to operate, control, monitor and test various cabin function. is used to operate, control, monitor and test engine functions. is used to operated, control, monitor APU function.

Who are the responsible of supply with alternating current to the distribution network of the aircraft in. Transformer rectifier. Generator. Static inverter.

Who is the responsible to supply to the distribution network with direct current, in normal configuration?. Battery. Transformer Rectifiers. Generator.

When the static inverter is automatically activated?. If AC BUS I and AC BUS 2 no are lost and the CSM/G is available. If AC BUS 1 and AC BUS 2 are lost and the CSM/G is unavailable. If AC BUS I and AC BUS 2 are lost and the CSM/G is available.

Which are the power sources of direct current?. Two identical transformer rectifiers and two identical batteries. Three identical transformer rectifiers and two identical batteries. Three identical transformer rectifiers and one identical battery.

One of main functions of the GCU is: To regulate the generator voltage by the field current,. To protect transformer rectifier. To protect the batteries.

The batteries are mainly to start the APU. in flight only. in flight and on ground. grond dy.

What is the Unit which the main function is in convert various critical flight parameters into a Recordable form. Digital Flight Data Recording System DFDRS. System Data Acquisition Concentrator SDAC. Display Management Computer DMC.

What is the display unit of Electronic Instrument System that shown essential engine parameters flap/slat position indication, fuel on board and Memo/Warning display?. upper ECAM. lower ECAM. multifunction control and display units.

What is the display unit of Electronic Instrument System that shown System/Status display. Digital Flight-Data Recording System DFDRS. upper ECAM. Lower ECAM.

What is the Purpose of the Aircraft Integrated Data System?. Process condition monitoring for various A/C systems. Process condition all A/C systems. Process the inputs from the flight control system.

What is the computer that acquires all data necessary for generation of alert messages associated to relevant A/C system failures?. FWC(Flight Warning Computer). SDAC (System Data Acquisition Computer). DMC (Display Management Computers).

What is the computer that generates the aural alerts, as well as synthetic voice messages for radio-height automatic call-out?. FWC(Flight Warning Computer). SDAC. DMC.

What is the electrical power source for emergency lights?. Batteries. Generator 1. External power.

What is the function of Taxi and Takeoff Lights?. Provide illumination of the runway and the taxiway during the taxi and the take off phase. They illuminate of the lateral areas of the runway. They illuminate the engine air intakes and the wing leading edges.

Runway Turnoff lights. Provide illumination of the lateral areas of the runway. The landing light system provides lighting to illuminate the runway. Provide illumination of the runway and the taxiway.

Wing and Engine Scan Lights. They illuminate the engine air intakes and the wing leading edges. The landing light system provides lighting to illuminate the runway. Provide illumination of the runway and the taxiway.

Landing Lights. Provides lighting to illuminate the runway. Provide illemination of the runway and the taxiway. Provide illumination of the lateral areas of the runway.

What is the function of the Navigation Light system. They illuminate the engine air intakes and the wing leading edges. Gives an external, visual indication of the position of the aircraft and its direction of flight. Provide illumination of the lateral areas of the runway.

Where is the location of strobe light. One light is installed in each wing tip facing forward and one is installed in the tailcone, below the APU exhaust facing rearwards. On the top and on the bottom of the aircraft fuselage. On the horizontal stabilizer in the zones 334 and 344.

What is the instrument that indicates the barometric altitude of the aircraft?. Standby Altimeter. Standby Airspeed Indicator. standby air data system.

What is the function of the ILS?. Provide the crew and airborne system users with lateral (LOC) und vertical (G/S) deviation signals. Receive and process Global Positioning System signals. Receive from the crew and airborne system users with lateral and vertical deviation signals.

Where is the location of Localizer antenna?. Forward lower fuselage area. Radome area. Forward upper fuselage area.

If exist a failure in ADIRU's 1, 2 &3, what is the stand by instrument that shown the magnetic heading information?. Standby Horizon. Standby airspeed indicator. Standby compass.

What instruments have shown the information from ILS receiver 2 through DMC respect?. PFD2 & ND2. PFD1 & ND2. PFD2 & ND1.

where is the GPWS function?. Warning. provide the crew and airborne system whit located (LOC) and (GPS) desviation signals. Receive and process Global Positioning system signals.

How many VOR systems have the aircraft?. 1. 2. 3.

Where is the location of the VOR antenna?. Forward upper fuselage. forward lower fuselage. vertical stabilizer.

Witch part of the ILS system ( instrument landing system provides to the crew the correct angle of descent toward the runway. The Localizer LOC. The glideslope G/S. The VOR system.

Under Normal operating conditione, with the engines shutdows (GEN 1 & GEN 2 PB in AUTO Position) APU GEN PB GEN PB in AUTO position and external power available (EXT PWR PB in ON potion, which source has the priority in feed aircraft electrical network busses. GEN 1. APU GEN. External power.

in normal operating conditions which of the following components converts the 115 VAC voltage, 400 He from the AC BUS 1 & 2 into 28 VDC to feed the DC BUS 1 & 2. The CSM/G (Constant Speed MotuifGenerators. The TR (Transformer Rectifier. The static inverter.

In the cabin pressurization system, what happens if the outflow valve begins to close?. Cabin altitude increases and its differential pressure decreases. Cubin altitude decreases and its differential pressure decreases. Cabin altitude decreases and its differential pressure increases.

Which of the following computers generates (produces) the information displayed on EFIS (Electronic Flight Instrument System) and ECAM screens: SDAC (System Data Acquisition Concentrator). DMC (Display Management Computer). FWC (Flight Warning Computer).

In ease of fullure of the 28VDC essential bushur, batteries in each EPSU continue to supply the emergency lighting system for at least... 6 minutes. 8 minutes. 12 minutes.

With the Emergency Ligher armed. When do the EPSUs integrated Batteries supply the emergency linghting system. When the EMER EXIT LT selector selector is in the ON position. When the 28 VDC ESS BUS is lost. When Main Lighting System has failed.

What are the fractions of the FACs?. Yaw damper, rudder trim, rudder travel limitation, and flight envelope protection. Yaw damper, piach trim, rudder trim, and flight envelope protection. Yan damper, rudder trim, pitch trim.

Which RM? can control the VHF 1 transceiver?. RMP 1. RMP 1 and RMP 2. RMP 1, RMP 2 and RMP 3.

What information is displayed on the airspeed scale?. CAS from ADR. CAS from ADR mixed with inertial speed. CAS from ADR, Inertial speed if ADR failure.

What happens if there is a fault on the AC BUS 1. The AC ESS BUS is lost and cannot be energized. The AC ESS BUS can be re-energized setting the AC ESS FEED PB in ALT position. The AC ESS BUS is lost momentarily, but can be re-energized starting the APU GEN.