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always driven by the master FMGC. When 2 APs are engaged or neither AP/FD, A/THR 1 has priority. Setting the THR levers to the idle detent,
disconnects the A/THR. If you press and hold the instinctive disconnect pb on the thrust levers for 15secs, you disarm the A/THR until the aircraft
is totally powered down.
FMA The 5 columns are: A/THR, Vertical, Lateral, Approach and AP/FD/A/THR status. The engaged modes are displayed in GRN on the first
line. Armed messages are displayed in BLU/MAG on the second line. Special messages are displayed on the third line with first priority to flight
control messages then lower priority messages relating to the FMGS.
Wt & CG The FMGC uses the weight and CG from the Fuel Computer when available. The GW and CG computed by the FE are used as a back-up
in case of dual FCMC failure and to trigger the aft CG caution/warning signals.
EIS
The EIS presents data to 6 identical DU: 4 EFIs and the ECAMs. The EFIs are 2 PFDs and 2 NDs. The ECAM presents data to the E/WD and SD.
The 3 identical DMC acquire and process all input signals for display on the EFIs/ECAM. The DMCs have separate channels for EFIs and ECAM
displays. 2 FWC acquire data directly and through the SDAC for alert messages, memo info, aural alerts, voice info and flight phase calculations
which is fed to the DMCs. Normally #1 DMC drives Capt's PFD/ND, #2 DMC drives F/O's PFD/ND and #3 DMC drives the ECAM. A DMC failure is
indicated by a green diagonal line across the screen. DMC 1/2 can replace DMC 3 and the ECAM SD can be transferred to either Capt's or F/O's ND.
The Capt's PFD & the E/WD is always available even after an electrical emergency.
If the upper ECAM DU fails, info is auto transferred to the lower ECAM DU. The system/status page may be recovered either by ECAM/ND
switching to an ND or on the lower ND by holding depressed the SYS button. If the lower DU fails, info may be recovered as for the upper DU. If
the PFD display fails, the ND display is auto replaced by the PFD. PFD and ND can then be toggled by the PFD/ND pb. If after PFD failure, the PFD
display comes back on line, the PFD is latched so disallow irritation switching of display. All switching for EFIs re-configuration after assoc DMC
failure is manual. ECAM reconfiguration from DMC #3 to #1 is automatic although manual follow-up is required. Further re-configuration is
manual. After a dual E/WD and SD failure, the ECAM page can be transferred to the ND by the ECAM/ND NORM rotary switch. After total ECAM
DMC failure, the ENG page is available via the EFIs half of the DMC on the ND through the ND selector. If the ECAM Control Panel failure, The CLR,
RCL, STS, ALL and EMER CANC pb remain operative as they are hard-wired to the FWC/DMC. Access to individual pages is then via the ALL pb
which cycles pages at 2sec intervals.
ECAM
The ECAM warning/cautions have priority rules such that a level 3 warning has priority over level 2 caution which has priority over a level 1 caution.
Same levels are sorted by the FWC. Types of failure:
Independent affects an isolated system or system which consequences for other systems.
Primary causes collateral failures.
Secondary resultant loss from primary failure.
Level 3 Level 2 Level 1
Action? YES Amber caution Amber caution
Optical warning? Master Warning flashes
E/WD message
Relevant systems page
Master caution On
E/WD caution message
Relevant systems page
No
E/WD caution message
Aural warning? CRC Single chime No
The STS page appears automatically once the crew have cleared all the pages corresponding to the current failure and, reappears during descent
when baro ref is selected on the FCU or when slats are extended, whichever occurs first.
Irritation warnings may be long term cancelled with the ECAM EMER CANC pb (1.31.30 p3). This cancels the present aural warning as long as the
failure is present, the master warning lights go out but ECAM message display is not affected by the selection. Any present caution is cancelled for
the remainder of the flight, the STS page is auto-called and "CANCELLED CAUTION" displayed. The inhibition is suppressed when the aircraft is
next powered up or when the RCL button is pressed for more than 3secs.
Cockpit Overhead Circuit Breakers
ACP/AMU Audio Control Panel / Audio Management Unit 1.23.10 FWC Flight Warning Computer 1.31.05
CIDS Cabin Intercom Data System 1.23.20 LGCIU Landing Gear Control Interface Unit 1.32.10
CPC Cabin Pressure Controller 1.21.20 PACK CONT Pack Controller 1.21.10
DMC Display Management Computer 1.31.05 PHC Probes Heat Computer 1.30.50
EIVMU Engine Interface & Vibration Monitoring Unit 1.70.80 PSCU Proximity Switch Control Unit 1.52.10 p10
FCDC Flight Control Data Concentrator 1.27.10 SDAC System Data Acquisition Concentrator 1.31.05
　
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