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ATA 31

INDICATING AND RECORDING

SYSTEMS

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3160

ELECTRONIC INSTRUMENT SYSTEM

GENERAL
EIS SYSTEM EVOLUTIONS
The principle evolutions of the new EIS System are:
New system architecture i.e. a SMART architecture using an ARINC 629
protocol between the DMC (Display Management Computer) and the DU
(Display Units).
New functions such as:
S Video on Display Units,
S Bitmap capability through Ethernet Bus connected to DMC,
S Ethernet interface for hardcopy function,
S Tele-loading through ARINC 6153 or ARINC 615A,
S Cross loading between the three DMCs.
New optical head for Display Unit using the first time LCD technology stripe
arrangement for pixels and a new concept of grahic generation which allows
the implementation of an interactive human/machine interface (bitmap
windowing...). Useful area of 6,25 x 6,25 inch with the same external size of
7,25 x 7,25 inch.
SYSTEM INTERFACES
The six Display Units are smart displays i.e. that each display contains its own
processing capability in order to compute and display the images required for
PFD, ND, EWD and SD.
The Display Units include the following interfaces:
S ARINC 629 buses for the DMCs,
S ARINC 453 bus for the WXR (Weather Radar) and EGPWS (Enhanced
Ground Proximity Warning System),
S Coaxial cables for video signals.

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DISPLAY UNITS
DISCRETES

DU
#1

DU
#2

DU
#3

DU
#5

DU
#6

ANALOGUES

A/C
SYSTEMS

VIDEO

ARINC 453 BUS

CAMERA/
VIDEO RECORDER

ARINC 629 BUS

DU
#4

DMCs

Page 3
Figure
1 System
Interfaces
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DISPLAY MANAGEMENT COMPUTER
The three Display Management Computers can be considered as Data
Concentrators and receive data from aircraft sensors and systems in order to
merge and send them to the Display Units through ARINC 629 output buses.
Moreover the DMCs insure:
S the interface between EIS and the other A/C computers and systems,
S the information exchange between the displays and
S the tele-loading of the Display Units software.

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DISPLAY MANAGEMENT COMPUTERS

ARINC 629 BUS

DMC
#1

DUs

DMC
#3

DMC
#2

ARINC 453 BUS

ARINC 429 BUS

A/C
SYSTEMS

DISCRETES

Page 5
Figure
2 Display
Management
Computers
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EIS CONTROLS AND INDICATIONS INTRODUCTION
GENERAL
The EIS (Electronic Instrument System) is an avionics system connected with
most of the aircraft system computers to perform the EFIS (Electronic Flight
Instrument System) and ECAM (Electronic Centralized Aircraft Monitoring)
functions.
The EIS consists of 6 identical and interchangeable LCD units. The EFIS part
comprises a PFD (Primary Flight Display) and a ND (Navigation Display) per
pilot. The ECAM part comprises an EWD (Engine and Warning Display) and an
SD (System Display).
Three control panels are provided for EFIS and ECAM.

DESCRIPTION
The EIS comprises seven main computers allowing a great redundancy
between systems to minimize the loss of information:
S three identical DMCs (Display Management Computers),
S two identical FWCs (Flight Warning Computers),
S two identical SDACs (System Data Acquisition Concentrators).
DMCs 1, 2 and 3 are divided in two independent parts, the EFIS and ECAM
parts.
Each of them decode and process data coming from the aircraft system
computers.
The two SDACs perform three main functions, such as, data acquisition from
the A/C systems, data concentration and digitization to be sent to the DMCs
ECAM part.
The Aircraft system malfunction data, wellknown as caution situations, are
received and digitized by the SDACs and sent to the FWCs.
The two FWCs perform three main functions, such as, data acquisition from
some main A/C systems as well as SDACs, data warning computation
corresponding to warning situations and flight phase computation. Then the
digitized output is sent to the DMCs ECAM part.
The FWCs also generate attention getters composed of, Master Warning,
Master Caution, and Auto Land lights as well as Audio signals (sounds) and
Auto Call outs (synthetic voices) broadcast by two loudspeakers. There is no
volume control for these audio signals.
The EIS reconfiguration function is achieved by a set of switching devices and
some software implements within the DMCs. The switching or reconfiguration
of the DMCs and DUs can be automatic or manual.

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Figure
3 Electronic
Instrument
System Overview
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EIS SWITCHING PANELS DESCRIPTION
GENERAL
PFDs and NDs are presented in front of each pilot. The PFD presents short
term information necessary for the flight. The ND presents medium term flight
information required for navigation.
DMC 1 EFIS part is dedicated to the Captains PFD and ND, whilst DMC 2
EFIS part is dedicated to the F/Os PFD and ND, the DMC 3 EFIS part being in
standby.
The EFIS control panels allow the Captain and F/O to control their
corresponding PFD/ND, through the DMCs.
PFD CONTROL
The PFD Control panel enables the display of the Loc and Glide scales and
deviation symbols thanks to the LS pushbutton.
The FD pushbutton enables the display of the Flight Director bars.
The Baro reference selector knob, consists of an outer knob for the selection of
the measurement unit, hPa (hecto Pascal) or in Hg (Inches of Mercury). An
inner knob allows the selection of reference value by rotation, the selection of
the standard value (1013 hPa) by pulling, and to display the QNH by pushing.
The Baro reference window allows the display of the pressure reference value
and the reference used.

Two ADF/VOR selectors per control panel enable ADF or VOR bearing
pointers to be selected on the associated ND as well as the corresponding
navigation station characteristics in any mode, except PLAN mode.
EFIS SWITCHING
The EFIS switching panel located either side of the glareshield, enables:
S the switching from a failed Captain or F/O EFIS DMC to a valid one (DMC 3
first), thanks to the EFIS DMC selector,
S the switching from PFD to ND and viceversa with PFD/ND pushbutton.
The PFD OFF/BRT potentiometer controls the brightness in conjunction with
the automatic brightness control system, and is used to switch the display unit
on or off.
The ND OFF/BRT inner potentiometer controls the brightness and is used to
switch the display unit on or off. The outer potentiometer only adjusts the
brightness of the weather radar image.
NOTE:

In the OFF position, automatic and manual reconfigurations are

possible.

ND CONTROL
Five pushbuttons enable additional data to be displayed on the ND.
When pressed these pushbuttons respectively display:
S airports,
S ADF stations,
S VOR/DME stations,
S waypoints,
S and Constraints.
A mode rotary selector enables the desired presentation of navigation
information to be selected on the associated ND.
A scale rotary selector enables a value in miles to be selected for the rose
NAV, ARC and PLAN modes.

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CAPT EFIS
SWITCHING
PANEL

PFD

F/O EFIS
SWITCHING
PANEL

EFIS CONTROL PANELS

ND

ND

PFD

Page 9
Figure
4 EIS FrM
Switching
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DISPLAY UNIT COMPONENT DESCRIPTION
The LCDU725 (Liquid Crystal Display Unit) is a color display using a 6,25 x
6,25 inches AMLCD (Activ Matrix Liquid Crystal Display) with a 756 x 756 pixel
resolution.
The LCDU725 is a smart display i.e. it has embedded capabilities in order to
compute and to generate the symbols to be displayed from data sent by the
DMC, according to the selections given by its associated control panels.
In addition, the DU receives Wheather Radar or compressed bitmaps images,
via ARINC453 and displays them mixed with the symbology. As some options,
the DU is also able to implement the following capabilities:
S Video input processing and display function
S Printer output interface
The LCDU725 exchanges information with the DMCs through high speed
mono directional buses of type ARINC629. The LCDU725 operational software
either graphic and/or calculation and the data base can be downloaded in the
DU through DMCs. In addition the LCDU725 has a dedicated RS232 interface
for software tests.
The own operation of the DU is checked by an internal circuity called BITE
(Built-In-Test-Equipment). It provides fault isolation and reporting to the on
board maintenance system as well as to shop maintenance.
Moreover, the DU manages the feedback of critical parameters, via ARINC629,
such as attitude, heading and engine parameters.

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video recorder
(optional)
(optional)

CIU
Taxi Aid Camera System

Bitmap

Ethernet
Ethernet

Ethernet, ARINC 429

Hardcopy
(optional)
Data loader
(optional)

MDDU

Page 11
Figure
5 EIS FrM
ExternalNov
Interface
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DMC COMPONENT DESCRIPTION
The DMC (Display Management Computer) is a computer which aquires and
processes all the signals received from aircraft sensors and systems in order to
present information to the crew for safe flight, navigation, engine control,
system monitoring and warning information.
The DMC memory contains both DMC and Display Unit Software, including
spares. The DMC is able to:
S load in its memory both DMC and DU software from a dedicated Data
Loader Interface
S realize cross loading operations (loading/transmitting both DMC and DU
software from/to other DMCs)
S realize DUs software tele-loading operation through ARINC 629 buses
interface
Moreover the DMC receives and transmit to the displays:
S Display Units information returned on ARINC 629 buses
S bitmap information (wheather forecast, EPGWS) coming from Ethernet bus
The DMC is in charge of the selection of the wheather radar ARINC 453 output
data buses. The DMC can receive the following A453 inputs:
S data bus 1 & 2 from the radar 1 T/R unit
S data bus 1 & 2 from the radar 2 T/R unit
S data bus from the DMC3 A453 output.
The DMC provides one ARINC 453 output bus which is the selection of one
among the ARINC 453 input buses.

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Page 13
Figure
6 EIS FrM
InternalNov
Interface
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EIS FUNCTIONAL OPERATION
The functioning of the EIS equipment software is characterized by two phases:
S a start up phase, dedicated to initialization, test and tele-loading activities,
activated after the power-on or reset of the processor.
S a processing phase, dedicated to operational and maintenance activities,
activated cyclically, after the start-up phase.
Associated to these two phases of the software, four functioning modes are
defined:
S The POST Mode (Power-On Self Test) activated during the start-up phase,
dedicated to internal hardware and software tests.
S The TELE Mode (Tele-Loading), activated during the start-up phase,
dedicated to tele-load software into DU or DMC.
S The OPER Mode (Operational), activated during the processing phase,
dedicated to flight and navigation information management.
S The INTR Mode (Interactive), activated during the processing phase,
dedicated to maintenance activities.
After a long power cut or after many manual resets, DMC and DU wait at least
for 300 ms before reading the ground/flight discrete transmitted by the LGCIU
equipment.
S DU software stored in DMCs and DUs
Tele-loading fuction allows the new EIS software to be loaded in any DU or
DMC. This function can be devided into three sub-functions
S Tele-loading from an external data loader (aircraft data loader or portable
data loader) into DMC. This operation is called uploading.
S Tele-loading from a DMC into DU is called cross loading
S Tele-loading from a DMC into DMC is called cross loading
NOTE:

DMC and DU can activate two lists of POST:

S The light POST, which represents the minimum POST list to activate. This
minimum list is activated only after a fatal failure during the OPER mode.
The duration of these tests is as short as possible.
S The complete POST which represents the whole POST mode activities and
which is activated in all other conditions (see DU/DMC changing modes).
The duration of these tests is equal to 40 seconds for the LCDU and 35
seconds for the DMC.
During the post mode, or in case of interruption during POSTs, when the DU
starts again and if the results of the previous POST was OK, the message
SELF TEST IN PROGRESS (MAX 40 SECONDS) is displayed in green
character on two lines in the middle of the screen, when the required resources
are available. This message is not displayed during the POST mode if a failure
message is already being displayed or when POST error is detected.
The new EIS software is divided into two parts:
S DMC software stored in DMCs,
S Du software stored in the DMCs.

for LH only the Basic Function for Teleloading (from DMC 1) is

available!

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E

EWD
(DU3)
SD
(DU4)

A629

A629

DMC1
TELELOAD

ETHERNET 10 BASET

ETH N_1 A429

DATALOADER
A615A

ND2
(DU5)
DU TELELOADING

ND1
(DU2)

DMC3

PFD2
(DU6)

A629

DMC2

CROSSLOAD

A629

ETH N_1 A429

A629

ETH N_1 A429

A629

A629 CROSSLOADING
(A629 8MHZ)

LOAD ENABLE DISCRETE

A429HS

A429HS
LOAD ENABLE

DU TELELOADING

PFD1
(DU1)

DATALOADER
A615-3

A429BS
LOAD ENABLE DISCRETE

NOT WIRED IN
BASIC CONFIGURATION

PDL(MDDU)/DLS/DLRB

Page 15
Figure
7 EIS FrM
SystemNov
Layout
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FEEDBACK MONITORING FUNCTIONAL OPERATION
The feedback monitoring function permits to detect and to confirm a
discrepancy between the value of a critical parameter which is displayed on a
DU, called opposite value, and the value of this parameter aquired directly from
the same sourced by another DU, called direct value.
High criticality objectives are associated with the presentation in the cockpit of
the following so called CRITICAL parameters:
S pitch and roll angles,
S engine primary indications,
S baroaltitude,
S heading,
The feedback monitoring can be on-side or off-side.
Each image is monitored by two DUs as follows:
S DU1/PFD1: EWD, ND2
S DU2/ND1: PFD2, EWD
S DU3/EWD: PFD1, PFD2
S DU4/SD:
ND1, ND2
S DU5/ND2: PFD1, SD
S DU6/PFD2: ND1, SD
The feedback monitoring of the PFD, ND, SD and EWD images is executed at
each DU cycle.
For these critical parameters, the data processed in the monitored DU are sent
to two other DUs (the monitoring DUs) through the DMCs.
The monitored DU includes two processing channels each one assigned to the
generation of one image column over two. Just before sending a critical
parameter data to the final graphic memories both processors CP1 and CP2
direct them to the interface processor for comparison of the two values. Since
they are produced at the same time they should be equal.

A discrepancy stops the monitored DU, whereas in the other case the feedback
value is sent to the other DUs for comparison with the originating sensor value.
When the difference is too high, the monitoring DU displays a message and
triggers a warning to be displayed by the FWC.
The feedback signals are sent by the DU to the DMCs, then to the monitoring
DUs via an ARINC 629 data link.
The feedback is valid only if the feedback parameters are acquired from an
off-side DMC of the monitored DU, so that the feedback channel is segregated
from the monitored channel. If this is not possible, the feedback function is still
executed with feedback parameters acquisition from the on-side DMC.
NOTE:

If a DU is no more monitored by another DU, it displays the

amber message DU NOT MONITORED
When a DU triggers an order to display a feedback check message, a specific
message is announced by the monitoring DU as follows:
S PFD CAPT discrepancy: CHECK CAPT PFD message
S ND CAPT discrepancy: CHECK CAPT ND message
S EWD discrepancy: CHECK EWD message
S SD discrepancy: CHECK SD message
S ND F/O discrepancy: CHECK F/O ND message
S PFD F/O discrepancy: CHECK F/O PFD message
If a feedback check message is triggered, a corresponding TSD (Class 1
internal failure) is stored in the DU BITE zone which is not transmitted to
DMCs.

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(DU1)

(DU2)

(DU3)

(DU5)

(DU6)

(DU4)

Page 17
Figure
8 Feedback
Monitoring
Function
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PRIMARY FLIGHT DISPLAY DESCRIPTION
The PFD is divided into 7 zones.
The ATTITUDE is indicated in the middle of the display unit, in the shape of a
cut sphere window which looks like a conventional attitude direction indicator.
The attitude area presents, the aircraft symbol, the pitch and roll indications,
the flight path and drift angles.
The GUIDANCE symbols may be superimposed on the attitude sphere.
The AIR SPEED Scale contains all the air speed data displayed on a
conventional Air Speed Indicator plus significant limits such as protection and
target speeds.
The HEADING scale displays the aircraft actual heading and track.
The ALTITUDE scale presents the altitude according to a baro reference
setting.
The VERTICAL/SPEED is displayed next to the altitude scale.
For approach the TRAJECTORY DEVIATION is presented on the right, and at
the bottom of the attitude area. ILS and DME information appears below the
speed scale.
The FMA (FLIGHT MODE ANNUNCIATOR) provides the pilot with the various
armed and active AFS (Automatic Flight System) modes.

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Page 19
Figure
9 Primary
Flight
Display
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NAVIGATION DISPLAY DESCRIPTION
Engine Standby Mode
Engine standby mode is available for displaying engine primary parameters in
case of complete ECAM DMC failure. The engine parameters are identical to
those presented on the EWD.
Additional indications are:
S FOB (Fuel On Board)
S Slats/Flaps Position
This page is provided by the EFIS part of the DMC.
Three different additional memos may be displayed if the appropiate system is
switched on:
S Packs
S NAI system (Nacelle Anti Ice)
S WAI system (Wing Anti Ice)

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ND

FUEL ON BOARD
(FOB)

THREE MEMOS
FOR SYSTEMS IN
OPERATION

SLATS / FLAPS
POSITION

A340 shown
Page 21
Figure
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E/WD INDICATION
General
The E/WD (Engine and Warning Display), normally on the upper ECAM display,
is divided into two areas:
S the upper area displaying, the engine primary parameters,
S the fuel quantity indication,
S and the slats and flaps position.
The lower area at the left is used for, warning and caution messages, as well
as memos.
The lower area at the right is used for normal memos and secondary failure
messages.

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MEMOS: PACK, NAI, WAI

EWD
ENGINE PRIMARY
PARAMETERS

(FOB) FUEL ON BOARD

SLATS / FLAPS
POSITIONS
WARNING / CAUTION
MESSAGES

SECONDARY
FAILURE AND
MEMO MESSAGES
A340 shown

Page 23
Figure
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Engine
And
Warning Display
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SD INDICATION
The SD (System Display), normally on the lower ECAM display, is divided into
two areas:
S the upper area displays, system or status pages automatically after a
failure, called failure mode, or manually by the ECP (ECAM Control Panel)
pushbutton switches, called manual mode,
S two other modes are available: advisory mode which is an automatic
presentation due to a drifting parameter and flight phase mode, being an
automatic presentation due to the aircraft situation.
The lower area shows permanent data always displayed, whatever the system
page presented.
A new Parameter is available in the Air Data Sector of the permanent area
which is designated as ISA. This parameter is displayed in standard altitude
mode (standard mode selected on the FCU and standard altitude valid) and
when the SAT parameter is valid.

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SD

UPPER AREA

SYSTEM OR STATUS
PAGES

LOWER AREA

PERMANENT DATA
A340 shown

NEW PARAMETER: ISA

Page 25
Figure
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System
Display
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TROUBLESHOOTING
Display Unit Messages
The following tables summarize all messages displayed on a DU over a Black
screen.

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Page 27
Figure
13
FRA US/T-2

Display
Unit
Messages Summary
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THIS PAGE INTENTIONALLY LEFT BLANK

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Page 29
Figure
14
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Display
Unit
Messages Summary Contd
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EIS BITE

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EIS BITE
GENERAL
The Indicating system BITE is splitted into an EIS BITE and a Flight Warning
System (FWS) BITE.
The EIS BITE is ensured by each DMC (Display Management Computer) and
each DU (Display Unit). Each DMC provides an interface with the CMCs
(Central Maintenance Computers) and reports the failure information
associated with the DMCs, DUs and their related wiring.
The FWS BITE is ensured by each FWC (Flight Warning Computer), each
SDAC (System Data Acquisition Concentrator) and the ECP (ECAM Control
Panel), but only FWC1 provides the FWS interface with the CMCs. It reports
failures related to FWCs, SDACs, ECP, and their associated wiring.
The Indicating system BITE information is available through the MCDU
SYSTEM REPORT TEST page (ATA 31 INST).

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Page 31
Figure
15
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DMC MCDU MAINTENANCE MENUS DESCRIPTION
From the DMC Main Menu the operator has access to several DMC
Sub-Menus.
Once in the Maintenance Mode the operator can access the following
sub-menus.

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INDICATING AND RECORDING SYSTEMS

ELECTRONIC INSTRUNMENT SYSTEM

A330/340E
ENHANCED

3160

DMC Main
Menu

1L

Last Leg
Report

5L

2L

Previous
Legs Report

1R

Troubles
Shoot Data

4R

SWTG/BUS
/DU Test

2L

Class &
faults

6R

Fin Prog Status

& Xload

Data Bus
Test
2L

3L

LRU
Identification

2R

System Test

DMU Load

5L
4L

Ground
Scanning

5R

Ground
Report

LCD Status

3L

4L

Switching
Test
3L

DU Brightness
Test
4L

DU Load

Backlighting
Status

2R

Pin Prog

2L

3L

Hard Pin

Soft Pin

Page 33
Figure
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DMC
Sub Menus
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INDICATING AND RECORDING SYSTEMS

EIS BITE SYSTEM

A330/340E
ENHANCED

3160
EIS MCDU MENU DESCRIPTION
Functionality
The SYSTEM REPORT/TEST page enables to select the ATA 31 INST
DISPLAY function in order to interrogate the EIS SYSTEM for failure, report
display and testing.
The selection of one of the 3 DMCs will give access to the related DMC BITE
page. Each DMC is a type 1 computer with a BITE menu providing a GROUND
SCANNING and the following specific functions.
The SYSTEM TEST function allows an automatic test of the EIS and an
operator display visual check.
The system test performs in the following order:
S a DMC self test,
S a DMC/DUs A629 link test,
S a connected DUs self test,
S a display check.
NOTE:

This test is used in service whenever a DMC or DU is replaced to

check that it has not undergone any damage during installation.
The SWTG/BUS/DU TESTS function allows a manual check of the EIS
reconfiguration as well as an automatic test of the data bus links between the
selected DMC and the other DMCs and DUs. It includes also a DUs brightness
test.
The PIN PROG/STATUS AND XLOAD function allows to check the hardware
and software pin program status of the selected DMC as well as the status of
the light box bulbs and LCD screen of its related DUs. A X-LOAD function is
also available to update the software contents of the DMCs or DUs after
replacement.
NOTE:

If one of the three DMC is in interactive mode, a MAINTENANCE

MODE message is displayed on the DUs driven by the DMC.
This message is not displayed during execution of, the
SWITCHING TEST, the GROUND SCANNING, the various
DISPLAY TEST, the DU teleloading of the function PIN
PROG/STATUS AND XLOAD.

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INDICATING AND RECORDING SYSTEMS

EIS BITE SYSTEM

A330/340E
ENHANCED

3160

Page 35
Figure
17
FRA US/T-2

EISFrM
MCDUNov
Pages
1, 2004

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INDICATING AND RECORDING SYSTEMS

EIS BITE SYSTEM

A330/340E
ENHANCED

3160
DMC BITE
SYSTEM TEST PROCEDURE
During the SYSTEM TEST the DMC are in the INTERACTIVE mode.
Throughout the duration of the test the DMC sends a page, held on the MCDU
by the CMC, indicating TEST IN PROGRESS Xs. The length of time Xs is
the time in seconds required to execute all the abovedefined tests, taking into
account a reasonable maximum execution time for each test.
DMC self test equivalent to:
S DMC POST
S DU POST
S A629 TEST
These tests are the same as those run after a power rise following a long
power cut on the ground.
The fault messages and associated TSD concerning A629 and DU internal
faults are stored in zone 3 of the EEPROM (storage of internal faults on the
ground). The fault messages and associated TSD concerning external bus
faults are stored in the RAM.

Test Procedure
S set initial conditions,
S start test
S color pattern display on the captain PFD and ND
The operator checks that the color pattern is actually displayed on the PFD and
ND. This operation is repeated three times as there are three different patterns
available.
S first pattern: Color display
S second pattern: White/Black display
S third pattern: Black/White display
Test Report
NOTE:

NOTE: For maintenance messages and TSD associated with this

function, the date and time are not given.
When no failure is detected TEST OK is displayed in the middle of the screen.

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INDICATING AND RECORDING SYSTEMS

EIS BITE SYSTEM

A330/340E
ENHANCED

3160

DMC 1

DMC 1

TEST

LAST LEG

CLASS3

FAULTS>
SYSTEM
TEST>

<REPORT

PREVIOUS LEGS

<REPORT

<LRU IDENT
<GND SCANNING
TROUBLE SHOOT
<DATA
<RETURN

SWTG/BUS/DU

1/2

SYSTEM TEST
INITIAL CONDITONS:
-SET ADIRU 1+2+3 TO NAV
-ENTER PPOS IN OPP MCDU
WAIT FOR ALIGNMENT
-SELECT ALL FADEC GROUND
POWER ON

TEST>

GROUND

REPORT>

PIN PROG/STATUS

AND XLOAD>

DMC 1

SYSTEM TEST
INITIAL CONDITONS:
-MAKE SURE THAT ALL DU
ARE ON
-SET THE 2 EFIS DMC SEL
TO NORM
-SET THE 2 ECAM SWTG SEL
TO AUTO AND NORM

2/2

<START TEST

<RETURN

PRINT*

<RETURN

PRINT*

DMC 1

SYSTEM TEST

TEST IN PROGRESS 100S

<RETURN

PRINT*

Page 37
Figure
18
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DMC
System
Test 1
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INDICATING AND RECORDING SYSTEMS

EIS BITE SYSTEM

A330/340E
ENHANCED

3160

DMC 1

DMC 1

SYSTEM TEST

SYSTEM TEST

MAKE SURE THAT THE FIRST

TEST SCREEN (COLORS) IS
DISPLAYED ON PFD CAPT
AND ND CAPT DU

<BOTH OK
<NONE
<RETURN

P/N : C19366AF05
S/N : C19366000379
EIS SW
P/N : SXT47E2LR-031C

MAKE SURE THAT THE

SECOND TEST SCREEN (W/B)
IS DISPLAYED ON PFD CAPT
AND ND CAPT DU

ONLY PFD1>
ONLY ND1>

<BOTH OK
<NONE

PRINT*

<RETURN

ONLY PFD1>
ONLY ND1>
PRINT*

THALES AVIONICS

LCDU 725

Page 38
Figure
19
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DMC
System
Test 2
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INDICATING AND RECORDING SYSTEMS

EIS BITE SYSTEM

A330/340E
ENHANCED

3160
WITH FAULT
DMC 1

DMC 1

SYSTEM TEST

SYSTEM TEST

MAKE SURE THAT THE

SECOND TEST SCREEN (W/B)
IS DISPLAYED ON PFD CAPT
AND ND CAPT DU

<BOTH OK
<NONE
<RETURN

ATA

CLASS

316222
PFD CAPT (1WK1)

1>

ONLY PFD1>
ONLY ND1>
PRINT*

<RETURN

PRINT*

NO FAULT
DMC 1

SYSTEM TEST

TEST OK

<RETURN

PRINT*

Page 39
Figure
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DMC
Sytem
Test 3
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INDICATING AND RECORDING SYSTEMS

ELECTRONIC INSTRUNMENT SYSTEM

A330/340E
ENHANCED

3160
TELE-LOADING DESCRIPTION
A so-called Tele-Loading function provides the capability for software upgrades
or initial software loading. All DMCs and DUs require Tele-Loading after a
new component has been installed.
The Tele-Loading function is achieved by crossloding a software from DMC to
DMC or from DMC to DU, but it is possible to load a new software for the
system to DMC 1 only from the MDDU or a PDL.
NOTE:

Teleloading from MDDU to all dmcs is optional. Some operators

have only the basic function (Loading to DMC1 only)
The following figure gives examples of the three different Tele-Loading
subfunctions. For the Display Unit Cross-Loading subfunction, the maintenance
operator has to configure the Display Units on the Emitter DMC by using the
DMC reconfiguration switches.

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INDICATING AND RECORDING SYSTEMS

ELECTRONIC INSTRUNMENT SYSTEM

A330/340E
ENHANCED

3160

ARINC 629 FOR DUs CROSSLANDING

ARINC 629

ARINC 629 FOR DMCs CROSSLANDING

Page 41
Figure
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Tele-Loading
Functions
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INDICATING AND RECORDING SYSTEMS

EIS BITE SYSTEM

A330/340E
ENHANCED

3160
DMC X-LOADING DESCRIPTION
By pressing the 6R key of the DMC menu the page DMCx PIN PROG/STATUS
AND XLOAD on display (A) allows to select the DMC XLOAD page (key 2L) on
display (B) which allows to display:
S the software P/N of the DMC source
S the software P/N of the DMC target and to launch the X-load process (only
if the DMC source is not faulty).
If the DMC1 is the DMC source, the DMCs targets are:
S the DMC2 then DMC3
If the DMC2 is the DMC source, the DMCs targets are:
S the DMC1 then the DMC3
If the DMC3 is the DMC source, the DMCs targets are:
S the DMC1 then the DMC2
This order is repeated on all DMC XLOAD pages. The key 1R is then pressed
which leads to the display XLOAD NOT AVAIL means the DMC target is not
available for X-loading. EMPTY means the DMC target is available for
X-loading.
If all DMCs targets are followed by the message: XLOAD NOT AVAIL, or if all
software P/N of the DMCs targets are identical to the DMC source, then the
amber message DMC XLOAD NOT ALLOWED is dsiplayed as on display.
If the indication START XLOAD is displayed as on display, the operator
presses the key 5L and gets access to the TRANSFER IN PROGRESS Page.

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INDICATING AND RECORDING SYSTEMS

EIS BITE SYSTEM

A330/340E
ENHANCED

3160

XLOAD NOT POSSSIBLE

DMC 1
LAST LEG

CLASS3

FAULTS>
SYSTEM
TEST>

PREVIOUS LEGS

<REPORT

SWTG/BUS/DU

TEST>

GROUND

REPORT>

AND XLOAD>

LAST LEG

CLASS3

LAST LEG

<REPORT
PREVIOUS
DMC
1:
<REPORT

XLOAD TO

PIN PROG/STATUS

<RETURN

DMCTEST
XLOAD

DMCTEST
XLOAD

<REPORT

<LRU IDENT
<GND SCANNING
TROUBLE SHOOT
<DATA

DMC 1

DMC 1

TEST

LEGS

<REPORT
PREVIOUS
DMC
1:
<REPORT

ACCESSFAULTS>
XLOAD>
SYSTEMP/N
EIS SOFTWARE
SXT47/-E2LR-031C
TEST>

XLOAD TO

SXT47/-E2LR-031C
SWTG/BUS/DU
DMC 2:
TEST>
<GND
DMC
3: SCANNINGSXT47/-E2LR-031C
GROUND
TROUBLE SHOOT
<DATADMC XLOAD NOT ALLOWED
REPORT>
PIN PROG/STATUS

PIN PROG/STATUS

<RETURN

AND PRINT*
XLOAD>

XLOAD

DMC 1

PIN PROG/STATUS
TEST
AND XLOAD
LAST LEG
CLASS3

<REPORT
PREVIOUS LEGS
<REPORT
<DMC
XLOAD

FAULTS>
SYSTEM
PIN TEST>
PROG>

<DU XLOAD
<LRU
IDENT
DU BACKLIGHT
<STATUS
<GND SCANNING
TROUBLE SHOOT
<DATASTATUS
<LCD
<RETURN

SWTG/BUS/DU

TEST>

GROUND

REPORT>

PIN PROG/STATUS

AND PRINT*
XLOAD>

AND PRINT*
XLOAD>

POSSSIBLE

DMC 1

DMCTEST
XLOAD

SYSTEM TEST
LAST LEG

<REPORT

TEST IN PROGRESS 100S

LEGS

<LRU IDENT

<LRU IDENT
SWTG/BUS/DU
SXT47/-E2LR-031C
DMC 2:
TEST>
<GND
DMC
3: SCANNINGSXT47/-E2LR-031C
TROUBLE SHOOT
GROUND
<DATA
REPORT>
<RETURN

CLASS3

FAULTS>
EIS SOFTWARE
SYSTEMP/N
SXT47/-E2LR-031C
TEST>

PREVIOUS LEGS
DMC
1:
<REPORT
XLOAD TO

CLASS3

FAULTS>
SYSTEMP/N
EIS SOFTWARE
SXT47/-E2LR-031C
TEST>

<LRU IDENT

SXT47/-E2LR-031C
SWTG/BUS/DU
DMC 2:
TEST>
<GND
DMC
3: SCANNINGXXXXXXXXXXXXXXXX
GROUND
TROUBLE SHOOT

<DATA XLOAD
REPORT>
<START
PIN PROG/STATUS
AND PRINT*
XLOAD>
<RETURN

CONT. PAGE 45

Page 43
Figure
22
FRA US/T-2

DMC
XLOAD
1
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INDICATING AND RECORDING SYSTEMS

EIS BITE SYSTEM

A330/340E
ENHANCED

3160
Description Contd
Figure A
After the operator has pressed the key 5L he gets the display where the
transfers in progress are displayed by the message: DMC X TO DMC Y.
Figure B
When the transfer is completed, an INTEGRITY CHECK is performed as
mentioned on display which takes some time.
Figure C
When this check is completed the result is given as on display:
S XLOAD COMPLETED means the X-loading process is completed
successfully
S XLOAD ABORTED in amber means a X-load interrupt has occured or the
integrity check is not successful.
This leads to the DMC self test which is mentionned by the message:
DMC SELF TEST IN PROGRESS XXs.
After completion of this last test the page gives access by the RETURN (key
6L) to the first XLOAD Page with the new software numbers available as on
display.

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INDICATING AND RECORDING SYSTEMS

EIS BITE SYSTEM

A330/340E
ENHANCED

3160

From Page 43

Figure B

Figure A
DMC 1

Figure C

DMC 1

DMC 1

DMCTEST
XLOAD

DMCTEST
XLOAD

TRANSFER
<REPORT

CLASS3
IN PROGRESS
FAULTS>
PREVIOUS DMC1
LEGS TO DMC2 SYSTEM
<REPORT DMC1 TO DMC3 TEST>

<REPORTINTEGRITY CHECKFAULTS>
PREVIOUS LEGS DMC2
SYSTEM
TEST>
<REPORT
DMC3

<REPORT
FAULTS>
DMC
2 : XLOAD
PREVIOUS
LEGS COMPLETED SYSTEM
TEST>
<REPORT
DMC 3 : XLOAD ABORTED

<LRU IDENT
SWTG/BUS/DU
TEST>
<GND SCANNING
GROUND
TROUBLE SHOOT
<DATA MAX 10 MINUTESREPORT>

<LRU IDENT
SWTG/BUS/DU
TEST>
<GND SCANNING
TROUBLE SHOOT
GROUND
<DATA
MAX 40S REPORT>

<LRU IDENT
SWTG/BUS/DU
TEST>
<GND SCANNING
DMC SELF TEST GROUND
TROUBLE SHOOT
<DATA IN PROGRESS (40S)
REPORT>

LAST LEG

<RETURN

PIN PROG/STATUS
38% AND XLOAD>

LAST LEG

<RETURN

DMCTEST
XLOAD
CLASS3

PIN PROG/STATUS

AND XLOAD>

LAST LEG

<RETURN

CLASS3

PIN PROG/STATUS

AND XLOAD>

Page 45
Figure
23
FRA US/T-2

DMC
XLOAD
2
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INDICATING AND RECORDING SYSTEMS

EIS BITE SYSTEM

A330/340E
ENHANCED

3160
DU X-LOADING DESCRIPTION
By pressing the 6R key of the DMC menu the page DMCx PIN PROG/STATUS
AND XLOAD on display (A) allows to select the DU XLOAD page (key 3L) on
display (H) which allows to display:
S the software P/N of the DMC source
S the software P/N of the DUs targets
S to launch the X-loading function and to follow it
The software P/N: XXXXX of the DMC is green if the DMC source and the DU
targets have the same P/N, amber if they are different. The message XLOAD
NOT AVAIL is amber when the DMC does not receive data from the relevant
DU. The message EMPTY is amber when the relevant DU is not yet loaded.
If all DUs lines wear the mention: XLOAD NOT AVAIL then the display is
shown with the message: DU XLOAD NOT ALLOWED
If at least one DU has a software P/N different from the DMC source, the
display is shown when the operator presses the key 1R. The operator is asked
to perform some initial conditions.
Where the DMC2 is concerned these initial conditions are:
S SET THE CAPT EFIS DMC SEL TO 2
S SET THE FO EFIS DMC SEL TO NORM
S SET THE ECAM SWTG DMC SEL TO 2
Where the DMC3 is concerned these initial conditions are:
S SET THE CAPT EFIS DMC SEL TO 3
S SET THE FO EFIS DMC SEL TO 3
S SET THE ECAM SWTG DMC SEL TO 3
The key 5L (START XLOAD) is then pressed to show the display with the
message: TRANSFER IN PROGRESS and the DMC/DU concerned.

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INDICATING AND RECORDING SYSTEMS

EIS BITE SYSTEM

A330/340E
ENHANCED

3160

XLOAD NOT POSSSIBLE

DMC 1
LAST LEG

CLASS3

FAULTS>
SYSTEM
TEST>

PREVIOUS LEGS

<REPORT

SWTG/BUS/DU

TEST>

GROUND

REPORT>

PIN PROG/STATUS

AND XLOAD>

<RETURN

DU TEST
XLOAD

DU TEST
XLOAD

<REPORT

<LRU IDENT
<GND SCANNING
TROUBLE SHOOT
<DATA

DMC 1

DMC 1

TEST

LAST LEG

CLASS3

LAST LEG

<REPORT
PREVIOUS
DMC
1:
<REPORT

LEGS

<REPORT
PREVIOUS
<REPORT

ACCESSFAULTS>
XLOAD>
SYSTEMP/N
EIS SOFTWARE
SXT47/-E2LR-031C
TEST>

XLOAD TO
XLOAD NOT AVAIL
PFD
:
<LRUCAPTIDENT
XXXXXXXXXXXXXXX
SWTG/BUS/DU
ND CAPT :
XXXXXXXXXXXXXXX
TEST>
<GND
PFD
FO SCANNING
:
XXXXXXXXXXXXXXX
GROUND
NDTROUBLE
FO
:SHOOT
<DATA :
REPORT>
EMPTY
EWD
XLOAD
NOT AVAIL
SD
:
PIN
PROG/STATUS

<RETURN

DMC 1

<REPORT
PREVIOUS LEGS
<REPORT
<DMC
XLOAD

FAULTS>
SYSTEM
PIN TEST>
PROG>

<DU XLOAD
<LRU
IDENT
DU BACKLIGHT
<STATUS
<GND SCANNING
TROUBLE SHOOT
<DATASTATUS
<LCD
<RETURN

SWTG/BUS/DU

TEST>

GROUND

REPORT>

PIN PROG/STATUS

AND PRINT*
XLOAD>

LEGS

<LRU IDENT
DMC XLOAD NOT SWTG/BUS/DU
ALLOWED
TEST>
<GND SCANNING
GROUND
TROUBLE SHOOT
<DATA
REPORT>
<RETURN

AND PRINT*
XLOAD>

XLOAD

PIN PROG/STATUS
TEST
AND XLOAD
LAST LEG
CLASS3

CLASS3

FAULTS>
SYSTEM
TEST>

PIN PROG/STATUS

AND PRINT*
XLOAD>

POSSSIBLE

DMC 1

DU TEST
XLOAD

SYSTEM TEST
LAST LEG

<REPORT

TEST IN PROGRESS 100S

CLASS3

FAULTS>
SYSTEM
DMC
TEST>

INITIAL
PREVIOUSCONDITIONS
LEGS
-SET
THE CAPT EFIS
<REPORT
SEL TO NORM
-SET
FO EFIS DMC SEL
<LRUTHEIDENT
SWTG/BUS/DU
TO 1
TEST>
<GNDTHESCANNING
-SET
ECAM SWTG DMC
GROUND
TROUBLE
SEL
TO 1 SHOOT

<DATA XLOAD
REPORT>
<START
PIN PROG/STATUS
AND PRINT*
XLOAD>
<RETURN

CONT. PAGE 49
Page 47
Figure
24
FRA US/T-2

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XLOADNov
1 1, 2004

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Technical Training

INDICATING AND RECORDING SYSTEMS

EIS BITE SYSTEM

A330/340E
ENHANCED

3160
Description Contd
After the key 5L (START XLOAD) of the previous page has been pressed, the
following message appears: TRANSFER IN PROGRESS and the DMC/DU
concerned.
The next display is automatically shown for a while, when the integrity check is
being performed. The message XLOAD COMPLETED means the X-loading
process has been performed successfully.
The message XLOAD ABORTED in amber means the X-loading processs has
been failed.

Page 48
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INDICATING AND RECORDING SYSTEMS

EIS BITE SYSTEM

A330/340E
ENHANCED

3160

FROM PAGE 47

DMC 1

DMC 1

DMC 1

DU TEST
XLOAD

DMCTEST
XLOAD

TRANSFER
<REPORT

CLASS3
IN PROGRESS
FAULTS>
DMCLEGS
1 TO PFD CAPTSYSTEM
PREVIOUS
<REPORTDMC 1 TO ND CAPT TEST>

<REPORTINTEGRITY CHECKFAULTS>
PFD CAPT
PREVIOUS LEGS
SYSTEM
TEST>
<REPORT ND CAPT

<REPORT
FAULTS>
PFD
CAPT :LEGS
XLOAD COMPLETED
PREVIOUS
SYSTEM
<REPORT
ND CAPT : XLOAD ABORTED TEST>

<LRU IDENT
SWTG/BUS/DU
DMC 1 TO EWD
TEST>
<GND SCANNING
DMC 1 TO SD
GROUND
TROUBLE SHOOT
<DATA MAX 10 MINUTESREPORT>

<LRU IDENT
EWD SWTG/BUS/DU
TEST>
<GND SCANNINGSD
TROUBLE SHOOT
GROUND
<DATA
MAX 40S REPORT>

<LRU IDENT
EWD : XLOAD COMPLETED
SWTG/BUS/DU
TEST>
<GND
SD : SCANNING
XLOAD ABORTED
TROUBLE SHOOT
GROUND
<DATA DU SELF TEST REPORT>

LAST LEG

<RETURN

PIN PROG/STATUS
27% AND XLOAD>

LAST LEG

<RETURN

DMCTEST
XLOAD
CLASS3

PIN PROG/STATUS

AND XLOAD>

LAST LEG

CLASS3

IN PROGRESS
(40S)
PIN PROG/STATUS

<RETURN

AND XLOAD>

Page 49
Figure
25
FRA US/T-2

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XLOADNov
2 1, 2004

Lufthansa
Technical Training

TABLE OF CONTENTS
ATA 31 INDICATING AND RECORDING SYSTEMS . .
1
3160

ELECTRONIC INSTRUMENT SYSTEM . . . . . . . . . . . . .

GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
EIS CONTROLS AND INDICATIONS INTRODUCTION
EIS SWITCHING PANELS DESCRIPTION . . . . . . . . . . .
DISPLAY UNIT COMPONENT DESCRIPTION . . . . . . .
DMC COMPONENT DESCRIPTION . . . . . . . . . . . . . . . .
EIS FUNCTIONAL OPERATION . . . . . . . . . . . . . . . . . . . .
FEEDBACK MONITORING FUNCTIONAL OPERATION
PRIMARY FLIGHT DISPLAY DESCRIPTION . . . . . . . . .
NAVIGATION DISPLAY DESCRIPTION . . . . . . . . . . . . . .
E/WD INDICATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
SD INDICATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
TROUBLESHOOTING . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
EIS BITE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
DMC MCDU MAINTENANCE MENUS DESCRIPTION .
EIS MCDU MENU DESCRIPTION . . . . . . . . . . . . . . . . . .
DMC BITE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
TELE-LOADING DESCRIPTION . . . . . . . . . . . . . . . . . . . .
DMC X-LOADING DESCRIPTION . . . . . . . . . . . . . . . . . .
DU X-LOADING DESCRIPTION . . . . . . . . . . . . . . . . . . . .

2
2
6
8
10
12
14
16
18
20
22
24
26
30
32
34
36
40
42
46

Page i

TABLE OF FIGURES
Figure 1
Figure 2
Figure 3
Figure 4
Figure 5
Figure 6
Figure 7
Figure 8
Figure 9
Figure 10
Figure 11
Figure 12
Figure 13
Figure 14
Figure 15
Figure 16
Figure 17
Figure 18
Figure 19
Figure 20
Figure 21
Figure 22
Figure 23
Figure 24
Figure 25

System Interfaces . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Display Management Computers . . . . . . . . . . . . . . . . . . . . . . . . .
Electronic Instrument System Overview . . . . . . . . . . . . . . . . . . .
EIS Switching . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
EIS External Interface . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
EIS Internal Interface . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
EIS System Layout . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Feedback Monitoring Function . . . . . . . . . . . . . . . . . . . . . . . . . . .
Primary Flight Display . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
ND Engine Stby Mode . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Engine And Warning Display . . . . . . . . . . . . . . . . . . . . . . . . . . . .
System Display . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Display Unit Messages Summary . . . . . . . . . . . . . . . . . . . . . . .
Display Unit Messages Summary Contd . . . . . . . . . . . . . . . . .
EIS BITE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
DMC Sub Menus . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
EIS MCDU Pages . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
DMC System Test 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
DMC System Test 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
DMC Sytem Test 3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Tele-Loading Functions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
DMC XLOAD 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
DMC XLOAD 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
DU XLOAD 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
DU XLOAD 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3
5
7
9
11
13
15
17
19
21
23
25
27
29
31
33
35
37
38
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