NOTE : At any time, even during actions related to an A/C system
____ failure, the crew can manually select any system synoptic diagram or the STATUS page, by means of the corresponding ECAM CP key. The A/C system page key comes on only in the case of a manual selection, or in the case of an advisory.
 NOTE : In case of overflow (more than 7 lines of text) a special
____ symbol (an arrow) is displayed at the bottom of the DU. The scrolling of the message lines can be controlled only by the successive CLR actions. The first lines disappear as the corresponding actions/procedures are made, thus enabling the presentation of the lines which were not displayed. (Ref. Fig. 027)
 NOTE : The following figure gives an example of caution/warning
____
 messages presentation in case of double A/C system
 failure.
 (Ref. Fig. 028)

 1EFF : ALL 1 31-50-00Page 49 1 1 Feb 01/01R 1 1 1CES 1

 Corrective Action Carried by the Crew Figure 023
 1EFF : 1 1R 1CES  ALL  1 11 1 31-50-00 Page 50 Feb 01/01

 Action on Either CLR and Result Figure 024
 1EFF : 1 1R 1CES  ALL  1 11 1 31-50-00 Page 51 Feb 01/01

 2nd Action on Either CLR and Result Figure 025
 1EFF : 1 1R 1CES  ALL  1 11 1 31-50-00 Page 52 Feb 01/01

 3rd Action on Either CLR and Result Figure 026
 1EFF : 1 1R 1CES  ALL  1 11 1 31-50-00 Page 53 Feb 01/01

 Example of Message Overflow Figure 027
 1EFF : 1 1R 1CES  ALL  1 11 1 31-50-00 Page 54 Feb 01/01

 ECAM Message - Double A/C System Failure Figure 028
 1EFF : 1 1R 1CES  ALL  1 11 1 31-50-00 Page 55 Feb 01/01

 (g) A/C STATUS page (Ref. Fig. 029) The STATUS mode is selected:
 -automatically after a warning message, as soon as all corrective actions have been performed, by pressing the CLR key (if there is no STATUS, MEMO is directly displayed)
 -manually by pressing the STS key.
 In this case the CLR key comes on.
 (if there is no STATUS, NORMAL is directly displayed)

 This mode is suppressed automatically when a warning message
 occurs or manually when the CLR key is pressed.
 The STATUS page of the aircraft gives:
 - on the left part of the display an operational summary of the

 aircraft condition, listing all the failures having consequences upon operational aspects: Emergency procedure (LAND ASAP) landing capability and procedures Limitation (speed, altitude) Postponable procedures not displayed on first page Lost system or function Information
 - on the right part of the display the so called secondary failures or losses of system/equipment resulting from the origin or primary failure.
 The status messages are generated by the FWCs in the same way as the warning/caution messages.
 NOTE : A STATUS reminder message is displayed on the upper ECAM
____ DU whenever the STATUS page is not empty. Pressing the STS key on the ECAM control panel causes the STATUS page to appear on the lower ECAM DU.
 1EFF : ALL 1 31-50-00Page 56 1 1 Feb 01/01R 1 1 1CES 1

 STATUS Page Example Figure 029
 1EFF : 1 1R 1CES  ALL  1 11 1 31-50-00 Page 57 Feb 01/01

 5. Power Supply
____________ (Ref. Fig. 030) The 3 DMCs, 2 DUs, 2 FWCs and 2 SDACs are supplied with 115VAC/400 Hz single phase. The ECAM control panel is supplied with 28VDC. The table below gives the main electrical power sources for each component.
 NOTE : The DMCs and DUs are also supplied with 28VDC for switching purpose
____
 (mentioned in table 1-2)

 TABLE 1-1
 -------------------------------------------------------------------------------| AC BUS1 | AC BUS2 | AC ESS | DC BUS 1 | DC BUS 2 | DC ESS BUS | |----------|------------|-----------|------------|------------|---------------| | DMC3 | DMC2 | DMC1 | | | | | | | (DMC3) | | | | |----------|------------|-----------|------------|------------|---------------| | | Lower | Upper | | | | | | ECAM DU | ECAM DU | | | | |----------|------------|-----------|------------|------------|---------------| | | | | | | ECAM CP | |----------|------------|-----------|------------|------------|---------------| | | FWC2 | FWC1 | | | | |----------|------------|-----------|------------|------------|---------------| | | SDAC2 | SDAC1 | | | | -------------------------------------------------------------------------------
TABLE 1-2
 -------------------------------------------------------------------------------| AC BUS1 | AC BUS2 | AC ESS | DC BUS 1 | DC BUS 2 | DC ESS BUS | |----------|------------|-----------|------------|------------|---------------| | | | | | DMC2 | DMC1&3 | |----------|------------|-----------|------------|------------|---------------| | | | | | Lower | Upper | | | | | | ECAM DU | ECAM DU | -------------------------------------------------------------------------------
　
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