(d)
 In case of SD DU failure or if the LOWER DISPLAY potentiometer is turned to OFF, no automatic reconfiguration is done. At that time, the ECAM works in the ECAM SINGLE DISPLAY mode. Each crew member has also the possibility to permanently present the SD on his ND DU by rotating the ECAM/ND XFR selector switch on the SWITCHING panel.

 (3) Reconfiguration in case of multiple DU failures
 (a) In case of EWD DU and SD DU failure, each crew member has the possibility to permanently present the EWD on his ND DU by rotating the ECAM/ND XFR selector switch on the SWITCHING panel. The PFD DU presents the PFD or ND, depending on action on the PFD/ND transfer pushbutton switch.
 NOTE : In case of PFD DU and ND DU failure (on the same side), no
____
 reconfiguration is available.

 (4)
 Reconfiguration in case of single DMC failure

 (a) In case of DMC1 failure, the CAPT has to switch on the DMC 3 by rotating the EIS DMC selector switch on the SWITCHING panel. Same operation in case of DMC2 failure: the F/O has to switch on the DMC 3.

 (5)
 Reconfiguration in case of double DMC failures

 (a) In case of 2 DMC failure, either the CAPT or the F/O may select the remaining DMC3.
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 EFIS/ECAM Reconfiguration capability Figure 015 (SHEET 1)
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 EFIS/ECAM Reconfiguration capability Figure 015 (SHEET 2)
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 (b) In case of 3 DMC failure, the crew can only use the standby instruments of the instrument panel.
 (6) Reconfiguration in case of external source failures
 (a) In case of external (sensor/computer) source failure(s), it is possible to perform a source reconfiguration either manually
 (e.g. Flight Management) or automatically (e.g Flight Guidance). The SWITCHING panel enables manual source reconfiguration for ATT HDG, AIR DATA.
 E. Description of Display Symbologies
 (1) Description of EFIS symbology (Ref. Fig. 016)
 (a) Primary Flight Display (PFD) (For further details, Ref. to 31-64-00). The PFD presents the main information necessary for the control of the aircraft arranged in the basic T configuration. Only one page is available. The PFD is shared in the following main areas:
 1_ The ATTITUDE area which gives:
 - A/C symbol, Pitch and Roll indications, Flight Path, drift
 angles and Guidance symbols (Flight Director or Flight Path
 Director).
 2_ The AIRSPEED area which gives:
 - The Airspeed scale with A/C actual and target indicated
 speed and with all the airspeed limitations and protections.
 3_ The ALTITUDE area which gives:
 - The Altitude scale associated with a vertical speed scale
 with the A/C actual baro-altitude and inertial vertical
 speed
 - The Altitude and flight level selection associated with an
 altitude alert indication below the altitude scale
 - The baro reference setting with the reference mode i.e. QNH
 and STD
 - The TCAS resolution commands on the vertical speed scale.
 4_ The HEADING/TRACK area which gives:
 - The Heading scale with the A/C actual heading and track
 - The relative selections and the ILS/MLS course (Runway
 heading). 

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 PFD - General principle
 Figure 016

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 5_ The AUTO FLIGHT SYSTEM area which gives:
 - The full flight mode annunciator with the various armed and
 active AFS modes (longitudinal, lateral and thrust modes)
 - The AFS engagement status.
 6_ The ILS/MLS area which gives:
 - The vertical ILS/MLS deviation scale close to the right of
 the attitude area
 - The lateral ILS/MLS deviation scale close to the bottom of
 the attitude area.

 (b) Navigation Display (ND) (Ref. Fig. 017) (For further details, Ref. to 31-65-00). The ND provides the crew with 5 different pages according to the selected mode. This mode selection is done on the EFIS control panel and enables the display of one of the following images:
 -ROSE-ILS/MLS,
 -ROSE-VOR,
 -ROSE-NAV,
 -ARC,
 -PLAN,
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 ND - Flight Plan/waypoint symbology
 Figure 017

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