1EFF : 001-049, 051-099, 101-105, 151-199, 1 31-68-00Page 50 1201-299, 301-302, 1Config-1 May 01/05 1 1 1CES 1
W/R Transceiver - DMCs Interface
Figure 015
1EFF : 001-049, 101-105, 151-199, 201-299, 1 31-68-00Page 51/52 1301-302, 1Config-1 May 01/05 1 1 1CES R W/R Transceivers - DMCs Interface R Figure 015A
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R **ON A/C 001-049, 051-099, 101-105, 151-199, 201-299, 301-302,
In this case, the DMC 1 (or DMC 3 if the EIS DMC selector switch is set to CAPT/3) processes the DATA 2 bus from the W/R XCVR in operation. The range markers and the mode on the Captain ND are then those corresponding to the F/O selection, which is indicated on the Captain ND by an amber message : SELECT OFFSIDE RANGE & MODE. This message may disappear sooner, if the Captain selects the same range as the First Officer. The same applies for the DMCs working on side 2, which normally use the D2 buses, but which use the D1 buses in case of FMGC 2 failure.
NOTE : The W/R equipment has different buses, D1 being associated to the
____ CAPT range, and D2 to the F/O range.
NOTE : If there is a discrepancy between the range selection from the FCU
____ and the range selection sent on the corresponding W/R data bus, no W/R image is displayed and the W/R RANGE red message is displayed.
1EFF : 001-049, 051-099, 101-105, 151-199, 1 31-68-00Page 55 1201-299, 301-302, 1Config-1 May 01/05 1 1 1CES 1 EIS - SWITCHING - DESCRIPTION AND OPERATION
___________________________________________
1. General
_______
The EIS reconfiguration function is part of the Electronic Instrument System
(EIS) which is described in 316000.
This function is necessary to cope with availability objectives.
This reconfiguration function is mainly aimed at changing the six displays
of the main instrument panel whenever necessary. These displays are:
(Ref. 316000 for further definition)
-
the Primary Flight Display (PFD): all information related to the behavior of the aircraft with respect to pitch and roll axes.
-
the Navigation Display (ND): all information related to the behavior of the aircraft with respect to yaw axis describing the aircraft horizontal situation.
-
the Engine/Warning Display (EWD):
. ENGINE area: engine parameters
fuel on board
slat and flap position indication.
. WARNING area: all equipment failures together with their consequences on the flight.
-the System/Status Display (SD): a sketch of the main aircraft systems with a symbology relating the behavior of most of the items of equipment concerned by the system.
Redundancy together with weight saving objectives have led to the design of the EIS which enables to draw all these displays on six display units (DUs).
Three Display Management Computers (DMCs) drive the displays.
The EIS reconfiguration function is achieved by means of a set of switching devices plus some software implements within the DMC to enable reconfiguration of these system parts which include a failed component.
Various reconfiguration possibilities are provided in the EIS in order to cope with the operational requirements in case of failure of:
-
a bus input
-
a DMC
-
a DU
-
a control panel (EFIS control panel of the Flight Control Unit (FCU) or ECAM control panel).
(Ref. Fig. 001)
R 1EFF : 401-499, 1 31-68-00Page 1 1 1 Config-2 Aug 01/05 1 1 1CES 1
EIS Switching - Reconfiguration principles
Figure 001
R 1EFF : 401-499, 1 31-68-00Page 2 1 1 Config-2 Aug 01/05 1 1 1CES 1 A set of switching devices and some automatic processes are provided to the crew. They are:
-One EIS DMC selector switch, to provide the change over DMC1 to DMC3 or DMC2 to DMC3.
-Two PFD/ND pushbutton switches, one on the Captain side, the other on the First Officer side
-One ECAM/ND selector switch for ECAM/CAPT ND or ECAM/F/O ND transfer.
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