-
ENGINE (Running Mode) page indications (Ref. Fig. 044) 1 - Nacelle temperature 2 - Engine oil temperature 3 - Engine oil pressure (analog, digital) 4 - Engine oil quantity (analog, digital) 5 - Fuel used indication 6 - Engine vibrations N1, N2 7 - Engine oil filter clog 8 - Engine fuel filter clog

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 AIR BLEED Page Figure 041
 1EFF : 1 1 1CES  106-149, 303-399,  1 111 Page 7831-60-00 Config-3 Aug 01/05

 APU Page Figure 042
 1EFF : 1 1 1CES  106-149, 303-399,  1 111 Page 7931-60-00 Config-3 Aug 01/05

 ENGINE Page - Starting Mode
 Figure 043

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 ENGINE Page - Running Mode
 Figure 044

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 6. Operation in Case of Failure-Reconfiguration
____________________________________________
 A. General Due to the highly integrated design of the EIS system, the schematics and certain switching cases concern both the ECAM and the EFIS parts.
 B. Configuration of Input Sources
 (1)
 Normal operation The information displayed for the Captain and First Officer must be as independent from each other as possible (split concept). So, they are computed by independent computers from distinct sources using their onside sources (E.G.) ADIRU1 for DMC1 and ADIRU2 for DMC2:

 -DMC1 supplies data to the CAPT EFIS DUs (PFD and ND) and the upper ECAM DU.
 -DMC2 supplies data to the F/O EFIS DUs (PFD and ND) and to the lower ECAM DU.
 -DMC3 is then in standby, (HOT SPARE) and does not control any display, but nevertheless computes all data necessary for display on the Captain's EFIS DUs and upper ECAM DU. Thus it is prepared to replace DMC1. DMC3 receives data from sides 1 and 2 sensors but in this case, it only utilizes data from side 1 sensors.

 (2)
 Source reconfiguration Table 3 shows which sensors and computers are connected to each DMC. It also indicates those DMC inputs used in normal operation (N) or after source reconfiguration (A), according to the validity of these sensors/computers and the switching possibly made by the crew (ATT/ HDG, AIR DATA and EIS DMC). Table 3 gives an exhaustive list of all the DMC input buses. Bus "processed" by a DMC means: the parameters of the bus are acquired by the DMC and stored in its memory for possible use by the EFIS or ECAM processors. The sensors/computers I/P buses fall into different classes according to the nature of the possible reconfigurations, manual or automatic:

 -Manual reconfigurations A few sensor reconfigurations are left at the crew's disposal: ATT/ HDG, AIR DATA and of course, the reconfigurations concerning the EIS DMC (DMC3 globally replacing the DMC1 or 2).
 -Automatic reconfigurations For those systems, of which only the onside sensor/computer is processed by the DMC, the DMC uses the parameters of its onside sensor/computer if it operates properly, normal case (N). And it switches as a whole to the offside sensor/computer if the onside one fails, alternate case (A), i.e if the onside bus no longer
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 signal. Such is the case for the FACs, FMGC EFIS buses.
 The DMC switches back to the onside sensor/computer if it works
 properly again, and under certain conditions.
 For those systems of which the side 1 and 2 sensor/computer buses are
 processed simultaneously, the DMC can take parameters on either side
 (in any case, each DMC preferably works with the parameters of its
 onside sensor/computer bus).
 Such is the case for the FMGC (FGC) buses, FADEC & ECU, FWCs and
 SDACs data buses.
 -------------------------------------------------------------------------------| | SPEED | WIRED | PROCES| PROCES-| | | | (HIGH | TO | SED BY| SED BY | | | INPUT BUS | SPEED | DMC | DMC | DMC 3 | | | | LOW | No. | No. | WHEN | | | | SPEED) | | | TRANSFER | | | | | 1 2 3 | 1 2 3 | 3/1 3/2 | | |------------------|--------|-------|-------|----------|----------------------| | ADIRU = IRS bus1 | HS | X X | N N | N |A, if CAPT (F/O) | | 2 | " | X X | N | N |selects ATT/HDG CAPT | | 3 | " | X X X | A A A | A A |(F/O)/3 on the | | | | | | |SWITCHING panel | |------------------|--------|-------|-------|----------|----------------------| | ADIRU = ADC bus1 | LS | X X | N N | N |A, if CAPT (F/O) | | 2 | " | X X | N | N |selects AIR DATA CAPT | | 3 | " | X X X | A A A | A A |(F/O)/3 on the | | | | | | |SWITCHING panel | |------------------|--------|-------|-------|----------|----------------------| | FAC 1 | HS | X X X | N A N | N A |Automatic selection, | | 2 | " | X X X | A N A | A N |according to FAC | | | | | | |validity and AIR DATA | | | | | | |switching | |------------------|--------|-------|-------|----------|----------------------| | FMGC = FGC bus 1 | " | X X X | X X X | X X | | | 2 | " | X X X | X X X | X X | | |------------------|--------|-------|-------|----------|----------------------| | FMGC = FM bus 1 | HS | X X X | N A N | N A |A, if onside FMGC FM | | 2 | " | X X X | A N A | A N |part has failed | |------------------|--------|-------|-------|----------|----------------------| | FCU(FCU/EFIS)1-1 | LS | X X | X X | X |Selection of FCU | | CP 1-2 | " | X X | X X | X |processor 2 in case | | 2-1 | " | X X | X | X |of failure of | | 2-1 | " | X X | X | X |processor 1 | |------------------|--------|-------|-------|----------|----------------------| | VOR 1 | " | X X X | X X X | X X | | | 2 | " | X X X | X X X | X X | |
　
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