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After an ECAM caution occurs, the crew reports that no MASTER CAUT light illuminated and no audio alert was heard, although the message appeared on the EWD. Which elements should be considered as part of the pilot attention alerting system?. Only the SD synoptic page. MASTER CAUT, MASTER WARN, AUTOLAND warning lights only. MASTER CAUT, MASTER WARN, AUTOLAND warning lights, and associated audio signals via AMU to loudspeakers. Only the ECP brightness control.

During cruise, both the EWD and SD go blank. CAPT and F/O PFD/ND remain fully operational. MASTER WARN lights and audio alerts still function. Based strictly on system architecture, which failure is most consistent?. External computer information source failure. FWC failure. SDAC dual failure. DMC 3 failure.

How are red warning failure data acquired by the system?. Through ARINC 453 radar data bus. Directly by the FWCs from aircraft systems, without involving the SDACs.

A maintenance engineer needs to perform short-term troubleshooting immediately after arrival for a reported malfunction. Which systems and tools are primarily involved according to the defined maintenance grouping?. FDRS recorder data only. ACMS and FDRS through downloaded data. ECAM and CMS through MCDUs and printed or ATSU down-linked reports. Only CMS BITE data stored internally.

During cruise, an amber message appears on the EWD. No MASTER CAUT or MASTER WARN lights illuminate, and no audio signal is heard. A related system synoptic page is automatically displayed on the SD. Based strictly on alert classification logic, which level is consistent with this situation?. Level 1 – Advisory. Level 3 – Warning. Level 3 – Inhibited Warning. Level 2 – Caution.

After engine shutdown, the DFDR stops recording five minutes later as expected. During ground maintenance, a technician needs to power the DFDR without starting an engine. What action must be taken?. Power the FDIU through pin programming. Press the RCDR GND CTL pushbutton switch on the overhead panel. Select ECAM DMC switching to position 1. Rotate to crank the rotary selector on center pedestal.

After clearing a failure using the CLR key sequence, the crew observes a white boxed STS reminder on the EWD. Later, after engine shutdown, the STS reminder begins flashing. What does this indicate?. A primary failure has not been cleared. A Level 3 warning is still active. The SDAC has failed and display redundancy is degraded. A class 2 fault requiring maintenance action is reported under MAINTENANCE.

What is the primary difference in display format between an Alpha Call-Up and a Label Call-Up?. Alpha Call-Up requires SD entry, Label Call-Up does not. Alpha Call-Up displays data in engineering units, while Label Call-Up displays data in binary form. Both display data only in engineering units. Alpha Call-Up displays binary data, Label Call-Up displays engineering units.

What is the correct description of the functions combined within the FDIUM?. It records flight parameters only for crash investigation purposes. It provides aircraft identification data directly to the DFDR. It combines the FDIU for FDRS data collection and the DMU for ACMS data collection. It combines the ACMS for flight parameter recording and the DFDR for ACMS data collection.

After landing, maintenance retrieves a fault that occurred three flights ago from a specific aircraft system. The system supports interactive on-ground testing through ARINC 429 communication with the CMC. Based strictly on system architecture, which system type is most consistent?. Type-3 system. Type-2 system. Type-1 system.

In normal operation, how do the Central Maintenance Computers (CMCs) validate clock information?. The CMCs receive and validate date and time from the SD every second. The FWCs validate time and transmit it to the CMCs. The CMCs cyclically check and validate date and time from the main clock every second. The SDACs digitize the clock signal before transmission.

Which statement correctly describes the CMS normal mode?. It allows initiation of system tests from the MCDU. It is available only on ground. It records fault messages from system BITE and warnings from the FWCs. It enables LRU replacement procedures automatically.

Under CMS normal mode, when do Type-2 systems memorize failure messages?. Only when the aircraft is airborne (landing gear not compressed). From the start of each flight leg until 80 kts + 180 seconds after touchdown. Only during ground operation in interactive mode. Continuously, regardless of flight phase.

In flight, DMC 3 fails. A one-second “INVALID DATA” message appears simultaneously on both EWD and SD, then disappears. Based strictly on system logic, what automatic and crew actions are expected?. DMC 1 automatically takes over, and the crew must confirm selection by switching the ECAM DMC selector to position 1. All DUs revert to copy mode from DMC 2. DMC 2 automatically takes over, no crew action required.

According to the EIS redundancy architecture, which failure combination still allows EFIS and ECAM information to be displayed on the LCD units?. Single FWC failure and single DMC failure. Single DMC failure only. Dual SDAC failure and single FWC failure. Single SDAC failure associated with a single FWC and two DMC failures.

During cruise flight, a pilot selects a system page manually via the ECP. Shortly after, an amber caution is triggered due to a system failure. What should occur on the SD?. The SD blanks momentarily before returning to manual mode. The CRUISE page remains displayed because of flight phase priority. The manually selected page remains displayed until deselected. The system automatically switches to failure mode, cancelling manual mode.

A technician restores main electrical power after a temporary aircraft power interruption. The clock display is blank, but aircraft battery power had remained available during the interruption. What should be expected?. The time must be manually reset before display returns. The clock will display GPS time automatically. The clock will show CHECK DATA BASE CYCLE on the display. The updated time will be displayed once main power is restored.

Where can ACMS collected data be stored?. Only on the PCMCIA card. In the internal DMU memory, on the PCMCIA card, and/or in the WDAR (if installed). Only in the internal DMU memory. Only in the WDAR.

A crew reports that amber caution messages are not displayed on the SD, although red warnings and associated MASTER WARN indications operate normally. Based on the ECAM architecture, which component should be investigated first?. DMC 3. SDAC. EFIS switching panel. FWCs.

During maintenance troubleshooting, it is found that DFDR recordings do not contain valid aircraft identification data (tail number and fleet ID), although flight parameters are properly recorded. Based strictly on system architecture, which component should be investigated first?. SDACs. Linear Accelerometer. FWCs. FDRS Coding Panel.

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What information is included in the maintenance Post Flight Report (PFR), which can be printed only on ground? *. ECAM warnings and fault messages from the last 64 flights, with time, flight phase and ATA reference. ECAM warnings and fault messages from the last flight, with time, flight phase and ATA reference. Only real-time system warnings without time reference. System test results performed during ground maintenance.

In flight, a GREEN HYD failure occurs. The crew observes a boxed amber failure message on the EWD. Additionally, spoiler loss is indicated on the lower right part of the EWD with an amber title and an asterisk. Based strictly on ECAM failure logic, how are these failures classified?. Both are independent failures. GREEN HYD failure is primary; spoiler loss is secondary. GREEN HYD failure is secondary; spoiler loss is primary. Both are secondary failures.

In flight, the aircraft is operating in ECAM single display mode due to loss of one LCD unit. A system parameter drifts outside its normal range. The crew observes a pulsing white ADV at the bottom of the EWD, but no system page change occurs. What must the crew do to monitor the affected system?. Push the associated flashing system key on the ECP. Push and hold the associated flashing system key on the ECP. Select the STS page to view parameter details. Wait for automatic failure mode activation.

According to the EFIS architecture, what is the normal role of the Display Management Computers (DMCs)? *. To acquire and process data from aircraft systems and send it to the display units. To generate warning messages and audio alerts. To provide flight control laws to the FMGES. To digitize system data and transmit it directly to the ECAM SD.

What is the primary role of the Central Maintenance Computers (CMCs) on the A330?. To provide navigation and guidance data to the flight crew. To generate flight warnings and control ECAM displays. To record flight parameters for crash investigation. To centralize, memorize and report failure messages and warnings from system BITE and FWCS.