The Digital Flight Data Acquisition Unit detects a failure in processing mandatory data for the Flight Data Recorder System, while its Airplane Condition and Monitoring System functions remain available. Which indication set should result?, The Digital Flight Data Acquisition Unit FAULT light only, because Airplane Condition and Monitoring System data is still available., The Digital Flight Data Acquisition Unit FAULT light, Flight Recorder OFF light, both MASTER CAUTION lights and the OVERHEAD annunciator., The Flight Recorder Built-In Test Equipment light and Flight Recorder OFF light only., The Flight Data Recorder is operating normally, but the Digital Flight Data Acquisition Unit stops detecting valid playback synchronization words from the recorder. Why is this significant to system monitoring?, Playback data is used by the Digital Flight Data Acquisition Unit to verify that the Flight Data Recorder is actually receiving and processing the transmitted data., Playback synchronization is used only to determine whether the Underwater Locating Device is operating., Loss of synchronization causes the Digital Flight Data Acquisition Unit to transfer mandatory recording to the Quick Access Recorder., The Digital Flight Data Acquisition Unit receives an Aeronautical Radio Incorporated 429 digital input containing an invalid parity or status condition. At what stage is that validity checked before mandatory data is sent to the recorder?, The Solid-State Flight Data Recorder checks the signal after Harvard biphase conversion., The Digital Flight Data Acquisition Unit master controller checks parity and status bits before sending the data toward the Solid-State Flight Data Recorder., The Data Management Unit checks the signal only if the parameter has been selected for Airplane Condition and Monitoring System recording., An Initiated Built-In Test is requested on the Digital Flight Data Acquisition Unit. Which aircraft condition is required before the test can be performed?, The aircraft must be on the ground with both engines off., The aircraft may be airborne provided the Flight Recorder TEST/NORMAL switch is selected TEST., At least one engine must be operating so that the Flight Data Recorder System remains automatically powered., The aircraft is on the ground with the thrust levers advanced toward takeoff power. The horizontal stabilizer is correctly positioned, but the speedbrake lever is not DOWN. What warning should be generated?, A continuous horn generated by the cabin-pressure warning circuit., A wailer generated by the Master Caution system., An intermittent horn generated by the takeoff-warning function., A Display Processing Computer suffers a complete failure while the Display Source switch remains in AUTO. What design feature allows the MAX Display System to retain display information?, Each Display Unit independently calculates all flight and engine formats if it loses its normal Display Processing Computer., Either Display Processing Computer is capable of providing display data to all four Display Units, and automatic routing changes attempt to preserve the available formats., The Flight Management Computer automatically becomes the graphics source for the affected side., Within a Display Processing Computer, why are two isolated processors used on each processor card?, They independently generate left-side and right-side Display Unit graphics., They compare instructions and read/write operations while using isolated power and clock monitoring to improve integrity., One processor operates normally while the second remains unpowered until the first processor fails., Software must be loaded into an aircraft Line Replaceable Unit using the Loadable Software Airplane Parts process. What correctly distinguishes stage one from stage two?, Stage one transfers software from the Portable Maintenance Device to aircraft mass storage; stage two transfers it from aircraft storage to the target Line Replaceable Unit., Stage one verifies software only; stage two transfers software directly from the Portable Maintenance Device to the Line Replaceable Unit., Stage one loads mandatory avionics software and stage two loads only navigation databases., A technician reviewing Maintenance Awareness System data sees a SHOW LIST prompt instead of DISPLAY beside a particular system’s manual-event entry. What does this indicate?, The system has more than five manual snapshots and older events must be erased before they can be displayed., Between two and five manual snapshots are stored for that system and a list must be opened to select an individual event., The system has both a manual and automatic event recorded at exactly the same time., A Category 2 fault remains recorded after maintenance review. Why can it exist without illuminating the MAINT light or generating a normal status message?, Category 2 faults are Scheduled Maintenance Task messages rather than normal status-message faults and may remain for specified operating intervals., Category 2 faults are automatically downgraded to advisory information whenever both engines are running., Category 2 faults are stored only in the Digital Flight Data Acquisition Unit and are not available to the MAX Display System.

ATA 31

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