More generally, the consequences of FWS/EIS component failures on the availability of information displayed on the DUs given on table 5, hereafter.
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 TABLE 5

 -------------------------------------------------------------------------------| FAILURE | OPERATIONAL CONSEQUENCE | |---------------|-------------------------------------------------------------| | 1 DMC | NO | |---------------|-------------------------------------------------------------| | 2 DMCs | - Loss of PFD and ND images on either CAPT or F/O | | | instrument panel | | | - Loss of ECAM system image (possibility to get it back | | | temporarily). | |---------------|-------------------------------------------------------------| | 1 EFIS DU | Loss of ND image on the corresponding pilot's intrument | | | panel. Possibility to get the ND image back by means of | | | the PFD/ND XFR pushbutton switch. | |---------------|-------------------------------------------------------------| | UPPER ECAM DU | Automatic transfer of the Engine/Warning (E/W) image on | | | the lower ECAM DU, and subsequent loss of the System/Status| | | image : | | | - possibility to display the S image temporarily instead | | | of the E/W image if ECAM CP keys are pressed | | | - possibility to display the S image permanently on either | | | ND instead of the ND image by means of the ECAM/ND | | | XFR switch. | |---------------|-------------------------------------------------------------| | LOWER ECAM DU | Loss of the S image. | | | Possibility to get it back temporarily or permanently | | | (same as above). | |---------------|-------------------------------------------------------------| | BOTH ECAM DUs | Loss of Engine/Warning and System images. | | | Possibility to have the Engine/Warning image displayed on | | | either ND by means of the ECAM/ND XFR selector switch. | | | Possibility to display momentarily the S image instead of | | | the E/W image. | |---------------|-------------------------------------------------------------| | NOTE : When there is only one DU left for the ECAM display, priority is | | given to the E/W image display. However, if any monitored parameter | | exceeds its corresponding ADVISORY threshold: | - on the lower part of the E/W image, the ADV white message flashes | | - on the ECAM CP, the key of the affected A/C system flashes. This | | enables the pilot to find it easily and to consult the | | corresponding system image temporarily as he presses on the key. | -------------------------------------------------------------------------------
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 7. Test
____
 A. Maintenance and Test The EIS includes Hard-oriented and Soft-oriented Built-In-Test (BITE) functions. The CFDS (Centralized Fault Data System) facilitates the interface of these BITE resident routines for maintenance and test implemented in the various computers.
 (1)
 Failure Detection Functions The BITE of a computer is able to detect the internal failures as well as failures which affect the I/P parameters. The BITE is designed so as to minimize the undetected failures, and to make the maintenance of the system easier. To that end, the events detected by the BITE (anomaly, abnormal disengagement, failure...) are coded and stored in non-volatile memories called BITE memories, under the form of messages in alphanumeric characters. The GMT at the time of each failure is recorded and stored with the associated event. The BITE memories store information concerning several flights. To help the flight crew and the maintenance personnel, the CFDS provides the capability to display the above messages, as well as system maintenance data and procedures, through the interactive multipurpose Control and Display Units (MCDUs), located on the center pedestal.

 (2)
 Operation The CFDIU addresses through its common O/P bus line the DMCs. (Ref. Fig. 047) The CFDIU common bus line conveys the following information:

 -GMT, flight number, date... to number and mark the events stored in the BITE (system disconnection, failures...)
 -control words to address the A/C computer.
 In return, the addressed A/C computer sends on its O/P bus line
 (ARINC 429) to the CFDIU the following information:
 - one word for identification of the A/C computer, so that the CFDIU

 recognizes where the maintenance message comes from
 -several words of characters, encoded per ISO alphabet No. 5, and which form messages in plain English language. These messages are a translation of the BITE memory stored events. They will give the faults at the LRU level in flight, and at a deeper level on the ground (complete BITE memory dump available through menus).
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 CFDIU to EFIS/ECAM Interface
　
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