a334e_31d_l3_d-ne.pdf

LufthansaTechnical Training

A330/340E Indicating/Recording Systems



3160 ELECTRONIC INSTRUMENT SYSTEM

INDICATING AND RECORDING SYSTEMS A330/340EENHANCED

3100

FRA US/T-2 FrM Nov 1, 2004

ATA 31 INDICATING AND RECORDINGSYSTEMS


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3160 ELECTRONIC INSTRUMENT SYSTEM

INDICATING AND RECORDING SYSTEMSELECTRONIC INSTRUMENT SYSTEM

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3160 ELECTRONIC INSTRUMENT SYSTEMGENERAL

EIS SYSTEM EVOLUTIONSThe principle evolutions of the new EIS System are:New system architecture i.e. a SMART architecture using an ARINC 629protocol between the DMC (Display Management Computer) and the DU(Display Units).New functions such as: Video on Display Units, Bitmap capability through Ethernet Bus connected to DMC, Ethernet interface for hardcopy function, Tele-loading through ARINC 6153 or ARINC 615A, Cross loading between the three DMCs.

New optical head for Display Unit using the first time LCD technology stripearrangement for pixels and a new concept of grahic generation which allowsthe implementation of an interactive human/machine interface (bitmapwindowing...). Useful area of 6,25 x 6,25 inch with the same external size of7,25 x 7,25 inch.

SYSTEM INTERFACESThe six Display Units are smart displays i.e. that each display contains its ownprocessing capability in order to compute and display the images required forPFD, ND, EWD and SD.The Display Units include the following interfaces: ARINC 629 buses for the DMCs, ARINC 453 bus for the WXR (Weather Radar) and EGPWS (Enhanced

Ground Proximity Warning System), Coaxial cables for video signals.


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DU#1

DU#6

DU#5

DU#4

DU#3

DU#2

A/CSYSTEMS

CAMERA/VIDEO RECORDER

DMCs

DISCRETES

ANALOGUES

VIDEO

ARIN

C 62

9 BU

S

ARIN

C 45

3 BU

S

DISPLAY UNITS


Page 3Figure 1 System Interfaces


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DISPLAY MANAGEMENT COMPUTERThe three Display Management Computers can be considered as DataConcentrators and receive data from aircraft sensors and systems in order tomerge and send them to the Display Units through ARINC 629 output buses.Moreover the DMCs insure: the interface between EIS and the other A/C computers and systems, the information exchange between the displays and the tele-loading of the Display Units software.


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DMC#1

DMC#2

DMC#3

DUs

ARIN

C 62

9 BU

S

ARINC 453 BUS

ARINC 429 BUS

DISCRETES

DISPLAY MANAGEMENT COMPUTERS

A/CSYS-TEMS


Page 5Figure 2 Display Management Computers


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EIS CONTROLS AND INDICATIONS INTRODUCTIONGENERALThe EIS (Electronic Instrument System) is an avionics system connected withmost of the aircraft system computers to perform the EFIS (Electronic FlightInstrument System) and ECAM (Electronic Centralized Aircraft Monitoring)functions.The EIS consists of 6 identical and interchangeable LCD units. The EFIS partcomprises a PFD (Primary Flight Display) and a ND (Navigation Display) perpilot. The ECAM part comprises an EWD (Engine and Warning Display) and anSD (System Display).Three control panels are provided for EFIS and ECAM.

DESCRIPTIONThe EIS comprises seven main computers allowing a great redundancy between systems to minimize the loss of information: three identical DMCs (Display Management Computers), two identical FWCs (Flight Warning Computers), two identical SDACs (System Data Acquisition Concentrators).

DMCs 1, 2 and 3 are divided in two independent parts, the EFIS and ECAMparts.Each of them decode and process data coming from the aircraft system computers.The two SDACs perform three main functions, such as, data acquisition fromthe A/C systems, data concentration and digitization to be sent to the DMCsECAM part.The Aircraft system malfunction data, wellknown as caution situations, arereceived and digitized by the SDACs and sent to the FWCs.The two FWCs perform three main functions, such as, data acquisition fromsome main A/C systems as well as SDACs, data warning computation corresponding to warning situations and flight phase computation. Then thedigitized 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) andAuto Call outs (synthetic voices) broadcast by two loudspeakers. There is novolume control for these audio signals.The EIS reconfiguration function is achieved by a set of switching devices andsome software implements within the DMCs. The switching or reconfigurationof the DMCs and DUs can be automatic or manual.


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FRA US/T-2 FrM Nov 1, 2004 LufthansaTechnical Training

Page 7Figure 3 Electronic Instrument System Overview


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EIS SWITCHING PANELS DESCRIPTIONGENERALPFDs and NDs are presented in front of each pilot. The PFD presents shortterm information necessary for the flight. The ND presents medium term flightinformation required for navigation.DMC 1 EFIS part is dedicated to the Captains PFD and ND, whilst DMC 2EFIS part is dedicated to the F/Os PFD and ND, the DMC 3 EFIS part being instandby.The EFIS control panels allow the Captain and F/O to control theircorresponding PFD/ND, through the DMCs.

PFD CONTROLThe PFD Control panel enables the display of the Loc and Glide scales anddeviation 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 ofthe measurement unit, hPa (hecto Pascal) or in Hg (Inches of Mercury). Aninner knob allows the selection of reference value by rotation, the selection ofthe standard value (1013 hPa) by pulling, and to display the QNH by pushing.The Baro reference window allows the display of the pressure reference valueand the reference used.

ND CONTROLFive pushbuttons enable additional data to be displayed on the ND.When pressed these pushbuttons respectively display: airports, ADF stations, VOR/DME stations, waypoints, 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 roseNAV, ARC and PLAN modes.

Two ADF/VOR selectors per control panel enable ADF or VOR bearingpointers to be selected on the associated ND as well as the correspondingnavigation station characteristics in any mode, except PLAN mode.

EFIS SWITCHINGThe EFIS switching panel located either side of the glareshield, enables: the switching from a failed Captain or F/O EFIS DMC to a valid one (DMC 3

first), thanks to the EFIS DMC selector, the switching from PFD to ND and viceversa with PFD/ND pushbutton.

The PFD OFF/BRT potentiometer controls the brightness in conjunction withthe automatic brightness control system, and is used to switch the display uniton or off.The ND OFF/BRT inner potentiometer controls the brightness and is used toswitch the display unit on or off. The outer potentiometer only adjusts thebrightness of the weather radar image.NOTE: In the OFF position, automatic and manual reconfigurations are

possible.


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EFIS CONTROL PANELSCAPT EFISSWITCHING

PANEL

F/O EFISSWITCHING

PANEL

PFD PFDND ND


Page 9Figure 4 EIS Switching


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DISPLAY UNIT COMPONENT DESCRIPTIONThe LCDU725 (Liquid Crystal Display Unit) is a color display using a 6,25 x6,25 inches AMLCD (Activ Matrix Liquid Crystal Display) with a 756 x 756 pixelresolution.The LCDU725 is a smart display i.e. it has embedded capabilities in order tocompute and to generate the symbols to be displayed from data sent by theDMC, 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: Video input processing and display function Printer output interface

The LCDU725 exchanges information with the DMCs through high speedmono directional buses of type ARINC629. The LCDU725 operational softwareeither graphic and/or calculation and the data base can be downloaded in theDU through DMCs. In addition the LCDU725 has a dedicated RS232 interfacefor 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 onboard 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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C I U

Taxi Aid Camera System

video recorder(optional)

(optional)

MDDU

Data loader(optional)

Hardcopy(optional)

Bitmap

Ethernet

Ethernet

Ethernet, ARINC 429


Page 11Figure 5 EIS External Interface


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DMC COMPONENT DESCRIPTIONThe DMC (Display Management Computer) is a computer which aquires andprocesses all the signals received from aircraft sensors and systems in order topresent 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, includingspares. The DMC is able to: load in its memory both DMC and DU software from a dedicated Data

Loader Interface realize cross loading operations (loading/transmitting both DMC and DU

software from/to other DMCs) realize DUs software tele-loading operation through ARINC 629 buses

interfaceMoreover the DMC receives and transmit to the displays: Display Units information returned on ARINC 629 buses bitmap information (wheather forecast, EPGWS) coming from Ethernet bus

The DMC is in charge of the selection of the wheather radar ARINC 453 outputdata buses. The DMC can receive the following A453 inputs: data bus 1 & 2 from the radar 1 T/R unit data bus 1 & 2 from the radar 2 T/R unit data bus from the DMC3 A453 output.

The DMC provides one ARINC 453 output bus which is the selection of oneamong the ARINC 453 input buses.


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Page 13Figure 6 EIS Internal Interface

INDICATING AND RECORDING SYSTEMSELECTRONIC INSTRUNMENT SYSTEM

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EIS FUNCTIONAL OPERATIONThe functioning of the EIS equipment software is characterized by two phases: a start up phase, dedicated to initialization, test and tele-loading activities,

activated after the power-on or reset of the processor. 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 aredefined: The POST Mode (Power-On Self Test) activated during the start-up phase,

dedicated to internal hardware and software tests. The TELE Mode (Tele-Loading), activated during the start-up phase,

dedicated to tele-load software into DU or DMC. The OPER Mode (Operational), activated during the processing phase,

dedicated to flight and navigation information management. 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 leastfor 300 ms before reading the ground/flight discrete transmitted by the LGCIUequipment. DU software stored in DMCs and DUs

Tele-loading fuction allows the new EIS software to be loaded in any DU orDMC. This function can be devided into three sub-functions Tele-loading from an external data loader (aircraft data loader or portable

data loader) into DMC. This operation is called uploading. Tele-loading from a DMC into DU is called cross loading Tele-loading from a DMC into DMC is called cross loading

NOTE: for LH only the Basic Function for Teleloading (from DMC 1) isavailable!

DMC and DU can activate two lists of POST: 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.

The complete POST which represents the whole POST mode activities andwhich 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 35seconds for the DMC.

During the post mode, or in case of interruption during POSTs, when the DUstarts again and if the results of the previous POST was OK, the messageSELF TEST IN PROGRESS (MAX 40 SECONDS) is displayed in greencharacter on two lines in the middle of the screen, when the required resourcesare available. This message is not displayed during the POST mode if a failuremessage is already being displayed or when POST error is detected.The new EIS software is divided into two parts: DMC software stored in DMCs, Du software stored in the DMCs.


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E

NOT WIRED INBASIC CONFIGURATION

PFD1(DU1)

ND1(DU2)

EWD(DU3)

SD(DU4)

ND2(DU5)

PFD2(DU6)

DMC1

ETH N1 A429 A629TELELOAD CROSSLOAD

DMC2

ETH N1 A429 A629

DMC3

ETH N1 A429 A629

DATALOADERA615A

DATALOADERA615-3

PDL(MDDU)/DLS/DLRB

A429HSETH

ERN

ET 1

0 BA

SET

LOAD ENABLE DISCRETE

(A629 8MHZ)A629 CROSSLOADING

LOAD ENABLE DISCRETEA429BS

A429

HS

LOAD

EN

ABLE

DU

TELE

LOAD

ING

A629

DU

TELE

LOAD

ING

A629A629


Page 15Figure 7 EIS System Layout


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FEEDBACK MONITORING FUNCTIONAL OPERATIONThe feedback monitoring function permits to detect and to confirm adiscrepancy between the value of a critical parameter which is displayed on aDU, called opposite value, and the value of this parameter aquired directly fromthe same sourced by another DU, called direct value.High criticality objectives are associated with the presentation in the cockpit ofthe following so called CRITICAL parameters: pitch and roll angles, engine primary indications, baroaltitude, heading,

The feedback monitoring can be on-side or off-side.Each image is monitored by two DUs as follows: DU1/PFD1: EWD, ND2 DU2/ND1: PFD2, EWD DU3/EWD: PFD1, PFD2 DU4/SD: ND1, ND2 DU5/ND2: PFD1, SD DU6/PFD2: ND1, SD

The feedback monitoring of the PFD, ND, SD and EWD images is executed ateach DU cycle.For these critical parameters, the data processed in the monitored DU are sentto two other DUs (the monitoring DUs) through the DMCs.The monitored DU includes two processing channels each one assigned to thegeneration of one image column over two. Just before sending a criticalparameter data to the final graphic memories both processors CP1 and CP2direct them to the interface processor for comparison of the two values. Sincethey are produced at the same time they should be equal.

A discrepancy stops the monitored DU, whereas in the other case the feedbackvalue 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 andtriggers a warning to be displayed by the FWC.The feedback signals are sent by the DU to the DMCs, then to the monitoringDUs via an ARINC 629 data link.The feedback is valid only if the feedback parameters are acquired from anoff-side DMC of the monitored DU, so that the feedback channel is segregatedfrom the monitored channel. If this is not possible, the feedback function is stillexecuted 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 MONITOREDWhen a DU triggers an order to display a feedback check message, a specificmessage is announced by the monitoring DU as follows: PFD CAPT discrepancy: CHECK CAPT PFD message ND CAPT discrepancy: CHECK CAPT ND message EWD discrepancy: CHECK EWD message SD discrepancy: CHECK SD message ND F/O discrepancy: CHECK F/O ND message PFD F/O discrepancy: CHECK F/O PFD message

If a feedback check message is triggered, a corresponding TSD (Class 1internal failure) is stored in the DU BITE zone which is not transmitted toDMCs.


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(DU1) (DU2) (DU3)

(DU4)

(DU5) (DU6)


Page 17Figure 8 Feedback Monitoring Function


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PRIMARY FLIGHT DISPLAY DESCRIPTIONThe PFD is divided into 7 zones.The ATTITUDE is indicated in the middle of the display unit, in the shape of acut 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 andtarget speeds.The HEADING scale displays the aircraft actual heading and track.The ALTITUDE scale presents the altitude according to a baro referencesetting.The VERTICAL/SPEED is displayed next to the altitude scale.For approach the TRAJECTORY DEVIATION is presented on the right, and atthe bottom of the attitude area. ILS and DME information appears below thespeed scale.The FMA (FLIGHT MODE ANNUNCIATOR) provides the pilot with the variousarmed and active AFS (Automatic Flight System) modes.


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Page 19Figure 9 Primary Flight Display


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NAVIGATION DISPLAY DESCRIPTION

Engine Standby ModeEngine standby mode is available for displaying engine primary parameters incase of complete ECAM DMC failure. The engine parameters are identical tothose presented on the EWD.Additional indications are: FOB (Fuel On Board) 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 isswitched on: Packs NAI system (Nacelle Anti Ice) WAI system (Wing Anti Ice)


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THREE MEMOSFOR SYSTEMS INOPERATION

SLATS / FLAPS POSITION

FUEL ON BOARD (FOB)

ND

A340 shown


Page 21Figure 10 ND Engine Stby Mode

INDICATING AND RECORDING SYSTEMSEFIS ECAM AND INSTRUMENTS

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E/WD INDICATION

GeneralThe E/WD (Engine and Warning Display), normally on the upper ECAM display,is divided into two areas: the upper area displaying, the engine primary parameters, the fuel quantity indication, and the slats and flaps position.

The lower area at the left is used for, warning and caution messages, as wellas memos.

The lower area at the right is used for normal memos and secondary failuremessages.


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INDICATING AND RECORDING SYSTEMSEFIS ECAM AND INSTRUMENTS

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ENGINE PRIMARYPARAMETERS

SLATS / FLAPSPOSITIONS

(FOB) FUEL ON BOARD

WARNING / CAUTIONMESSAGES

SECONDARYFAILURE ANDMEMO MESSAGES

EWD

A340 shown

MEMOS: PACK, NAI, WAI


Page 23Figure 11 Engine And Warning Display


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SD INDICATIONThe SD (System Display), normally on the lower ECAM display, is divided intotwo areas: 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,

two other modes are available: advisory mode which is an automaticpresentation due to a drifting parameter and flight phase mode, being anautomatic presentation due to the aircraft situation.

The lower area shows permanent data always displayed, whatever the systempage presented.A new Parameter is available in the Air Data Sector of the permanent areawhich is designated as ISA. This parameter is displayed in standard altitudemode (standard mode selected on the FCU and standard altitude valid) andwhen the SAT parameter is valid.


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UPPER AREA

LOWER AREA

SD

SYSTEM OR STATUS PAGES

PERMANENT DATA

NEW PARAMETER: ISAA340 shown


Page 25Figure 12 System Display


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TROUBLESHOOTING

Display Unit MessagesThe following tables summarize all messages displayed on a DU over a Blackscreen.


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Page 27Figure 13 Display Unit Messages Summary


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THIS PAGE INTENTIONALLY LEFT BLANK


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Page 29Figure 14 Display Unit Messages Summary Contd

INDICATING AND RECORDING SYSTEMEIS BITE

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EIS BITE

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


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INDICATING AND RECORDING SYSTEMEIS BITE

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Page 31Figure 15 EIS BITE


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DMC MCDU MAINTENANCE MENUS DESCRIPTIONFrom the DMC Main Menu the operator has access to several DMCSub-Menus.Once in the Maintenance Mode the operator can access the followingsub-menus.


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DMC MainMenu

BacklightingStatusDMU Load

DU BrightnessTest

SwitchingTest

Data BusTest

Fin Prog Status& Xload

SWTG/BUS/DU Test

GroundReport

System Test

Class &faults

TroublesShoot Data

GroundScanning

LRUIdentification

Last LegReport

PreviousLegs Report

DU Load

LCD Status Pin Prog

Hard Pin Soft Pin

1L

2L

4L

3L

5L

1R

2R

5R

4R

2L 3L 4L

6R

2L 3L 4L

5L 2R

2L 3L


Page 33Figure 16 DMC Sub Menus

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EIS MCDU MENU DESCRIPTION

FunctionalityThe SYSTEM REPORT/TEST page enables to select the ATA 31 INST DISPLAY function in order to interrogate the EIS SYSTEM for failure, reportdisplay and testing.The selection of one of the 3 DMCs will give access to the related DMC BITEpage. Each DMC is a type 1 computer with a BITE menu providing a GROUNDSCANNING 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: a DMC self test, a DMC/DUs A629 link test, a connected DUs self test, a display check.

NOTE: This test is used in service whenever a DMC or DU is replaced tocheck 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 theselected DMC and the other DMCs and DUs. It includes also a DUs brightnesstest.The PIN PROG/STATUS AND XLOAD function allows to check the hardwareand software pin program status of the selected DMC as well as the status ofthe light box bulbs and LCD screen of its related DUs. A X-LOAD function isalso available to update the software contents of the DMCs or DUs afterreplacement.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, theSWITCHING TEST, the GROUND SCANNING, the variousDISPLAY TEST, the DU teleloading of the function PINPROG/STATUS AND XLOAD.


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Page 35Figure 17 EIS MCDU Pages


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DMC BITESYSTEM TEST PROCEDUREDuring the SYSTEM TEST the DMC are in the INTERACTIVE mode.Throughout the duration of the test the DMC sends a page, held on the MCDUby the CMC, indicating TEST IN PROGRESS Xs. The length of time Xs isthe time in seconds required to execute all the abovedefined tests, taking intoaccount a reasonable maximum execution time for each test.DMC self test equivalent to: DMC POST DU POST A629 TEST

These tests are the same as those run after a power rise following a longpower cut on the ground.The fault messages and associated TSD concerning A629 and DU internalfaults are stored in zone 3 of the EEPROM (storage of internal faults on theground). The fault messages and associated TSD concerning external busfaults are stored in the RAM.

Test Procedure set initial conditions, start test color pattern display on the captain PFD and ND

The operator checks that the color pattern is actually displayed on the PFD andND. This operation is repeated three times as there are three different patternsavailable. first pattern: Color display second pattern: White/Black display third pattern: Black/White display

Test ReportNOTE: 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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DMC 1


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TELE-LOADING DESCRIPTIONA so-called Tele-Loading function provides the capability for software upgradesor initial software loading. All DMCs and DUs require Tele-Loading after anew component has been installed.The Tele-Loading function is achieved by crossloding a software from DMC toDMC or from DMC to DU, but it is possible to load a new software for thesystem 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-Loadingsubfunctions. For the Display Unit Cross-Loading subfunction, the maintenanceoperator has to configure the Display Units on the Emitter DMC by using theDMC reconfiguration switches.


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ARINC 629 FOR DUs CROSSLANDING

ARINC 629 FOR DMCs CROSSLANDING

ARIN

C 62

9


Page 41Figure 21 Tele-Loading Functions


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DMC X-LOADING DESCRIPTIONBy pressing the 6R key of the DMC menu the page DMCx PIN PROG/STATUSAND XLOAD on display (A) allows to select the DMC XLOAD page (key 2L) ondisplay (B) which allows to display: the software P/N of the DMC source 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: the DMC2 then DMC3

If the DMC2 is the DMC source, the DMCs targets are: the DMC1 then the DMC3

If the DMC3 is the DMC source, the DMCs targets are: the DMC1 then the DMC2

This order is repeated on all DMC XLOAD pages. The key 1R is then pressedwhich leads to the display XLOAD NOT AVAIL means the DMC target is notavailable for X-loading. EMPTY means the DMC target is available forX-loading.If all DMCs targets are followed by the message: XLOAD NOT AVAIL, or if allsoftware P/N of the DMCs targets are identical to the DMC source, then theamber message DMC XLOAD NOT ALLOWED is dsiplayed as on display.If the indication START XLOAD is displayed as on display, the operatorpresses the key 5L and gets access to the TRANSFER IN PROGRESS Page.


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DMC 1


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Description Contd

Figure AAfter the operator has pressed the key 5L he gets the display where thetransfers in progress are displayed by the message: DMC X TO DMC Y.

Figure BWhen the transfer is completed, an INTEGRITY CHECK is performed asmentioned on display which takes some time.Figure CWhen this check is completed the result is given as on display: XLOAD COMPLETED means the X-loading process is completed

successfully 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 (key6L) to the first XLOAD Page with the new software numbers available as ondisplay.


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DMC 1


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DU X-LOADING DESCRIPTIONBy pressing the 6R key of the DMC menu the page DMCx PIN PROG/STATUSAND XLOAD on display (A) allows to select the DU XLOAD page (key 3L) ondisplay (H) which allows to display: the software P/N of the DMC source the software P/N of the DUs targets 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 DUtargets have the same P/N, amber if they are different. The message XLOADNOT AVAIL is amber when the DMC does not receive data from the relevantDU. 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 isshown with the message: DU XLOAD NOT ALLOWEDIf at least one DU has a software P/N different from the DMC source, thedisplay is shown when the operator presses the key 1R. The operator is askedto perform some initial conditions.Where the DMC2 is concerned these initial conditions are: SET THE CAPT EFIS DMC SEL TO 2 SET THE FO EFIS DMC SEL TO NORM SET THE ECAM SWTG DMC SEL TO 2

Where the DMC3 is concerned these initial conditions are: SET THE CAPT EFIS DMC SEL TO 3 SET THE FO EFIS DMC SEL TO 3 SET THE ECAM SWTG DMC SEL TO 3

The key 5L (START XLOAD) is then pressed to show the display with themessage: TRANSFER IN PROGRESS and the DMC/DU concerned.


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DMC 1


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Description ContdAfter the key 5L (START XLOAD) of the previous page has been pressed, thefollowing message appears: TRANSFER IN PROGRESS and the DMC/DUconcerned.The next display is automatically shown for a while, when the integrity check isbeing performed. The message XLOAD COMPLETED means the X-loadingprocess has been performed successfully.The message XLOAD ABORTED in amber means the X-loading processs hasbeen failed.


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DMC 1

TABLE OF CONTENTS

Page i

ATA 31 INDICATING AND RECORDING SYSTEMS . . 1

3160 ELECTRONIC INSTRUMENT SYSTEM 2 . . . . . . . . . . . . . GENERAL 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EIS CONTROLS AND INDICATIONS INTRODUCTION 6 EIS SWITCHING PANELS DESCRIPTION 8 . . . . . . . . . . . DISPLAY UNIT COMPONENT DESCRIPTION 10 . . . . . . . DMC COMPONENT DESCRIPTION 12 . . . . . . . . . . . . . . . . EIS FUNCTIONAL OPERATION 14 . . . . . . . . . . . . . . . . . . . . FEEDBACK MONITORING FUNCTIONAL OPERATION 16 PRIMARY FLIGHT DISPLAY DESCRIPTION 18 . . . . . . . . . NAVIGATION DISPLAY DESCRIPTION 20 . . . . . . . . . . . . . . E/WD INDICATION 22 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SD INDICATION 24 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TROUBLESHOOTING 26 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EIS BITE 30 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DMC MCDU MAINTENANCE MENUS DESCRIPTION 32 . EIS MCDU MENU DESCRIPTION 34 . . . . . . . . . . . . . . . . . . DMC BITE 36 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TELE-LOADING DESCRIPTION 40 . . . . . . . . . . . . . . . . . . . . DMC X-LOADING DESCRIPTION 42 . . . . . . . . . . . . . . . . . . DU X-LOADING DESCRIPTION 46 . . . . . . . . . . . . . . . . . . . .

TABLE OF FIGURES

Page ii

Figure 1 System Interfaces 3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 2 Display Management Computers 5 . . . . . . . . . . . . . . . . . . . . . . . . . Figure 3 Electronic Instrument System Overview 7 . . . . . . . . . . . . . . . . . . . Figure 4 EIS Switching 9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 5 EIS External Interface 11 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 6 EIS Internal Interface 13 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 7 EIS System Layout 15 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 8 Feedback Monitoring Function 17 . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 9 Primary Flight Display 19 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 10 ND Engine Stby Mode 21 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 11 Engine And Warning Display 23 . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 12 System Display 25 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 13 Display Unit Messages Summary 27 . . . . . . . . . . . . . . . . . . . . . . . Figure 14 Display Unit Messages Summary Contd 29 . . . . . . . . . . . . . . . . . Figure 15 EIS BITE 31 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 16 DMC Sub Menus 33 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 17 EIS MCDU Pages 35 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 18 DMC System Test 1 37 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 19 DMC System Test 2 38 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 20 DMC Sytem Test 3 39 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 21 Tele-Loading Functions 41 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 22 DMC XLOAD 1 43 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 23 DMC XLOAD 2 45 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 24 DU XLOAD 1 47 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 25 DU XLOAD 2 49 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

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