ATA 31- INDICATING / RECORDING A330

How many Display Management Computers (DMCs) are part of the EIS?. 2. 3. 4. 5.

What function do the Flight Warning Computers (FWCs) fulfill within the EIS?. Display generation. Flight data acquisition. Flight warning and alerting. System monitoring.

How can the clock display be switched between time and date?. By using the UTC selector. By pushing the SET button. By using the navigation panel. By turning off the display.

What does the UTC selector enable on the clock?. Switching to local time. Synchronization with GPS signal. Manual time adjustment. Switching to system time.

How many LCD units are capable of generating and displaying symbols in the EIS?. 4. 5. 6. 7.

What additional capability is available on the A340-500 and A340-600 aircraft regarding the LCD units?. Touchscreen functionality. Display of weather data. Video image display. Night vision display.

Which component sends data to the LCD units for symbol generation and display?. FWCs. SDACs. GPS. DMCs.

How many DMCs are installed in the EIS?. 2. 3. 4. 5.

What type of data do the DMCs primarily process for the EIS?. Navigation data. System alerts. Symbol generation data. Engine performance data.

What does the PFD display on the EFIS provide?. Navigation information. Basic flight information for short-term flight. Engine parameters. Weather radar information.

What is the primary function of the ND on the EFIS?. Displaying system warnings. Displaying navigation information. Displaying engine performance. Displaying communication status.

What is the purpose of the EFIS control panel for each pilot?. To control aircraft lighting. To select the display modes. To communicate with ATC. To monitor cabin pressure.

What is displayed on the EWD in the ECAM system?. Synoptic of various systems. Engine parameters and warning messages. Navigation data. Weather radar images.

Where is the SD located in the ECAM system?. In front of each pilot. On the center instrument panel. On the overhead panel. In the aft of the cockpit.

What controls the ECAM displays and operation?. EFIS control panel. ECAM Control Panel (ECP). Flight Warning Computer (FWC). System Data Acquisition Concentrator (SDAC).

What types of messages are shown in the lower area of the EWD?. Navigation data. Weather updates. Warning and caution messages. Engine parameters.

How can pilots control the brightness and operation of the EWD?. Using the EFIS control panel. Using the ECAM Control Panel (ECP). Using the autopilot system. Using the flight management computer.

What is displayed in the upper area of the SD?. Permanent data. Navigation data. System or status pages. Weather information.

Which DMC normally drives the Captain's PFD and ND?. DMC 1. DMC 2. DMC 3. DMC 4.

How is the EFIS reconfiguration achieved?. Automatically only. Manually only. Both automatically and manually. By the Flight Warning Computer.

What triggers the activation of attention getters in the ECAM system?. Data from the GPS system. External weather alerts. Data from the Flight Warning Computers (FWCs). Manual input from the pilot.

How does the redundancy in the EIS architecture affect system display in the event of multiple failures?. Loss of all EFIS and ECAM information. Partial display of EFIS information only. Continued display of EFIS and ECAM information on the LCD units. Display of only ECAM information.

What is the impact of a single SDAC failure combined with a single FWC failure on the ECAM system?. Complete shutdown of the ECAM system. Loss of all warning messages. ECAM system continues to operate. Display of only primary engine parameters.

How does the FWS architecture handle a single internal failure?. It becomes inoperative. It loses some data temporarily. It remains fully operational. It requires manual reset.

What type of data is displayed in the upper area of the EWD?. Warning messages. Engine primary parameters, fuel on board, slat/flap position. Navigation data. System configuration.

Where are advisory indications shown on the EWD?. Right memo area. Lower area. Upper area. Left memo area.

Which mode does the ECAM operate in automatically when a parameter is drifting?. Normal mode. Failure mode. Advisory mode. Manual mode.

In which flight phase does the CRUISE page appear on the ECAM?. Phase 1. Phase 6. Phase 10. Phase 3.

Which pages are displayed in priority during the DOOR phase if the APU or engines are started?. APU or Engine pages. Flight Control page. Landing Gear page. Brake page.

When does the WHEEL page appear during the flight phases 7, 8, and 9?. After engine start. After landing. During takeoff. During cruise.

What message appears on the EWD during flight phases 3, 4, and 5?. "TO INHIBIT". "LDG INHIBIT". "WHEEL INHIBIT". "CRUISE INHIBIT".

How are system pages displayed in manual mode when a system key is pressed?. Automatically. Sequentially. Randomly. Individually.

What type of alert is mainly associated with a Single Chime and a MASTER CAUT amber light?. Level 1. Level 2. Level 3. Status Messages.

What is the highest priority level of alert that requires immediate crew corrective action?. Level 1. Level 2. Level 3. Status Messages.

What type of failures correspond to Level 1 alerts?. Immediate corrective actions. Loss of redundancy. Safety concerns. Audio and visual alerts.

How are Level 2 cautions typically indicated to the crew?. MASTER WARN flashing lights. Single Chime and amber light. Red lights and warning message. Audio alerts only.

In what scenario would a Level 3 warning be triggered?. Routine system checks. Emergency configurations. Maintenance tasks. Crew monitoring.

How is a primary failure distinguished on the ECAM display?. Green box around the failure. Red or amber box around the failure. Flashing lights. Audio alerts.

Which type of failure affects other systems or equipment?. Independent failure. Secondary failure. Primary failure. Routine failure.

What is a secondary failure?. Loss of a system due to a primary failure. Loss of redundancy in a system. Loss of multiple systems simultaneously. Loss of critical equipment.

How is the advisory mode distinguished in dual display mode?. Green box around the failure. Red or amber box around the failure. Pulsing value for the parameter. Flashing lights.

What happens in single display mode on the ECAM?. All systems are displayed automatically. A white ADV message pulses at the bottom. The system pages are displayed on the SD. Audio alerts are triggered.

What are the main functions of the SDACs?. A) Data acquisition. B) Data concentration. C) Data digitization. D) Data transmission.

What type of data format is used by SDACs to send signals to DMCs?. A) ARINC 629. B) ARINC 453. C) ARINC 429. D) RS 232.

How are the failures categorized in the context of SDACs?. A) Primary failures. B) Independent failures. C) Secondary failures. D) Tertiary failures.

What is the primary function of the Digital Flight Data Recording System (DFDRS)?. To monitor real-time flight parameters for pilot reference. To fulfill the mandatory requirements of crash recording. To transmit data to air traffic control for monitoring purposes. To provide entertainment options for passengers during flight.

What components are included in the DFDRS architecture?. Flight Data Interface Unit (FDIU), Linear Accelerometer (LA), Event P/B, Recorder Ground Control P/BSW, Quick Access Recorder (QAR). Flight Data Recorder (DFDR), Cockpit Voice Recorder (CVR), Flight Data Interface Management Unit (FDIMU), Linear Accelerometer (LA). Flight Data Interface Unit (FDIU), Quick Access Recorder (QAR), Recorder Ground Control P/BSW, Event P/B, DFDR. Flight Data Recorder (DFDR), Linear Accelerometer (LA), Aircraft Tail Number, Fleet Identification.

What is the function of the Flight Data Interface Unit (FDIU)?. To collect various basic aircraft system parameters and convert them for recording. To control the aircraft's flight path and altitude. To collect various aircraft system parameters and recording. To communicate with air traffic control towers.

Where is the FDIU typically located?. In the cockpit center pedestal. In the aircraft center of gravity. In the avionics bay. In the passenger cabin.

What information does the DFDRS Coding Panel provide to the FDIU?. Aircraft tail number, airline identification, fleet identification. Pilot's name, flight route, departure time. Engine temperature, fuel level, cabin pressure. Air traffic control frequency, weather updates, navigation waypoints.

What is the purpose of the Linear Accelerometer (LA) in the DFDRS?. To measure the aircraft's speed. To provide data on three axes of acceleration to the FDIU. To monitor engine performance. To control cabin temperature.

How does the FDIU receive information from the Linear Accelerometer (LA)?. Via the System Data Acquisition Concentrators (SDACs). Via direct cable connection to the DFDR. Through wireless transmission. By manual input from the pilot.

What is the function of the EVENT P/B in the cockpit?. To initiate emergency procedures. To record an event mark in the DFDR memory. To activate the autopilot system. To control cabin lighting.

How many hours of data can the DFDR store?. 10 hours. 25 hours. 48 hours. 100 hours.

How does the EVENT P/B assist technicians in identifying specific events?. By marking events with a timestamp. By highlighting events on the cockpit display. By generating a notification to maintenance personnel. By triggering an alarm in the cockpit.

Where is the Quick Access Recorder (QAR) typically installed?. In the cockpit center pedestal. In the passenger cabin. In the avionics compartment. In the aircraft center of gravity.

How is the power supply to the DFDR and QAR controlled?. It is controlled manually by the flight crew. It is controlled automatically based on engine activity. It is controlled by a separate power management system. It is controlled by the cockpit voice recorder.

When does the DFDR power up automatically?. When the aircraft is taxiing. When one engine is started. When the aircraft is in cruise mode. When the aircraft is descending.

How long does the DFDR remain powered after the last engine shutdown?. It remains powered until manually switched off by the flight crew. It remains powered indefinitely. It remains powered for five minutes after the last engine shutdown. It remains powered forTten minutes after the last engine shutdown.

Where is the Linear Accelerometer (LA) installed in the aircraft?. In the avionics bay. In the cockpit center pedestal. In the aircraft center of gravity. In the passenger cabin.