Airbus A320 ATA 31 EIS Presentation

EIS (DMC & DU) - Page 1

TITLE

The A320 aircraft family can be fitted with two different EIS (Electronic Instrument System)

1 – EIS "1" This system is fitted with three DMC (Display Management Computers) located in the avionics compartment and six DU (display units, CRT (Cathode Ray Tube)) type fitted in the cockpit. DMC manages the various images to be displayed on the DU (Display Units)

2 – EIS "2" This system is fitted with three DMC (Display Management Computers) located in the avionics compartment and six DU (display units, LCD (Liquid Crystal Display)) type fitted in the cockpit. DMC manages the various images to be displayed on the DU (Display Units)

For both systems, Thales Avionics provide the 3 DMC and the 6 DU.

Basic functions are the same between EIS1 and EIS2.

This presentation is related to EIS2.


EIS – Presentation

The Electronic Instrument System ( EIS ) is an avionics system connected with most of the aircraft systems to carry out the two main functions:- EFIS ( Electronic Flight Information System )- ECAM ( Electronic Maintenance Aircraft Monitoring ).

The system is mainly composed of:

Six identical display units ( DU ) including integrated graphics generator are located in the cockpit:- two Primary Flight Displays ( PFD ) + two Navigation Displays ( ND ) for EFIS ( Electronic Flight Instrument System ) - one engine warning display + one system display for ECAM ( Electronic Centralized Aircraft Monitoring )

Three Display Management Computers ( DMC ) located in he avionics compartment;- images generation to be displayed on PFD, ND and ECAM Dus.- digital data links to display units.- DMC 3 may replaced either No 1 or No 2 DMC by switching in the cockpit.

Two System Data Acquisition Concentrators ( SDAC ):- acquiring systems data for transmission of caution to FWCs and systems condition to DMCs.

Two Flight Warning Computers ( FWC )- generating alert messages, aural alerts and procedural messages for display on ECAM.

Thales Avionics provides the three DMC and six DU.


EIS – Presentation – Display Units location

FLIGH CONTROL UNITCAPT EFIS Control UnitAttention Getters Attention GettersF/O EFIS Control Unit

PFDPFD PFDPFDNDNDNDND

PFD / ND transfer push-button

Control and Brightness Knobs for ND and PFD DUs

ECAM

Upper display

ECAM

Upper display

ECAM

Lower display

ECAM

Lower display

PFD / ND transfer push-button

Control and Brightness Knobs for ND and PFD DUs


EIS – System description (1)

PFD1

ND1

PFD2

ND2

EFIS

CTL

EFISCTL

FCU

ECAM CP

DMC 1

FWC 1

DMC 3

SDAC 1

DMC 2

SDAC 2

FWC 2

WARNING WARNING

CAUTION CAUTION

ECAM1

ECAM2

ENGINEWARNING

SYSTEMSTATUS

ATTENTIONGETTERS

A/C SYSTEMS SENSORS / COMPUTERS INPUT FOR :

-RED WARNINGS-FLT PHASE COMPUTATION-A/C SYSTEMS SYNOPTICS

A/C SYSTEMS SENSORS / COMPUTERS INPUTS FOR :-AMBER CAUTIONS

-A/C SYSTEMS SYNOPTICS

FWC 2SDAC 2

SENSORS / COMPUTERS-NAVIGATION & AFS -ENGINE FADEC SYSTEM -FUEL QTY

FWC 1SDAC 1

ATTENTIONGETTERS

This figure is the general system architecture of the EIS ( Electronic Instruments System ). This system provide all the necessary flight information and flight warning and alarms to the crew thanks to avionics computers such as the DMCs ( Display Management Computers ), the FWCs (Flight Warning Computers), the SDACs (System Data Acquisition Concentrators ) and the 6 Dus (Display Units) fitted in the cockpit,


EIS – System description (2)

EIS general - Main equipment

The Electronic Instrument System ( EIS ) is an avionics system connected with most of the aircraft systems to carry out the two main functions, EFIS ( Electronic Flight Information System ) and ECAM ( Electronic Maintenance Aircraft Monitoring ).

The system is mainly composed of:

Six identical display units ( DU ) including integrated graphics generator are located in the cockpit:- two Primary Flight Displays ( PFD ) + two Navigation Displays ( ND ) for EFIS ( Electronic Flight Instrument System ) - one engine warning display + one system display for ECAM ( Electronic Centralized Aircraft Monitoring )

Three Display Management Computers ( DMC ) located in he avionics compartment;- images generation to be displayed on PFD, ND and ECAM Dus.- digital data links to display units.- DMC 3 may replaced either No 1 or No 2 DMC by switching in the cockpit.

Two System Data Acquisition Concentrators ( SDAC ):- acquiring systems data for transmission of caution to FWCs and systems condition to DMCs.

Two Flight Warning Computers ( FWC )- generating alert messages, aural alerts and procedural messages for display on ECAM.

* both EFIS and ECAM will be presented in the next slides.


EIS – System description - EFIS Electronic Flight Instrument System (1)

ADC 3IRS 3

TCAS 1

FAC 1 AND 2FMGC: 1 AND 2

FM: 1 AND 2

VOR 1 AND 2ILS 1 AND 2MLS 1 AND 2

R/A 1 AND 2DME 1 AND 2ADF 1 AND 2

EFIS 2EFIS 1

FCUPFD

1ND 1

ECAMDU 2

ECAMDU 1

ND2

PFD2

DMC 1 DMC 3 DMC 2

WXR

WX

R

WX

R

WXR 1 AND 2

ADC 1IRS 1FCU 1

ADC 2IRS 2FCU 2

EFIS SIDE 1 EFIS SIDE 2

EFIS system centralizes and displays the necessary flight information and is therefore connected to major avionics equipment.



The EFIS ( Electronic Flight Instrument System ) provides the necessary displays of the flight and navigation information thanks to the PFD ( Primary Flight Displays ) and the ND ( Navigation Displays ).

FLIGH CONTROL UNITCAPT EFIS Control UnitAttention Getters Attention GettersF/O EFIS Control Unit

PFDPFD PFDPFDNDNDNDND

INSTRUMENT PANELPFD / ND transfer push-button PFD / ND transfer push-button

Control and Brightness Knobs for ND DUs

Control and Brightness Knobs for PFD DUs



Refer to the two following pages to see the functions of the selector a,d push-buttons.



ND control part

A set of selectors and pushbuttons enable the display different ND pages. Selector ILS to PLAN ) change the layout of the display, selector 10 to 320 NM modifies the scale of the navigation display while the set of pushbuttons ( CSTR to ARPT ) are used to add additional flight information such as navaids, airport or constraint data .

ADF or/and VOR information can be added to the ND page using the switches ADF/VOR 1 and 2.

- CSTR = CONSTRAINT

- WPT = WAYPOINT

- VORD = VOR/DME

- NDB = NON DIRECTIONAL BEACON

- ARPT = AIRPORT



PFD control

The switch enables to control the barometric setting in inches of mercury ( In Hg) or in hecto Pascal (hPa).The baro-setting knob can be pulled or pushed in order to set the barometric setting to either STD (standard) or QNH or QFE (1).The FD pushbutton is used to engage/disengage the Flight Director (2), while the LS pushbutton is used to display LS information on the PFD (3).

(1) The QFE setting is optional (pin programming)

(2) When the FD push-button is lighted the FD bars are in view on the PFD (assuming active modes are negaged in the corresponding AP/FD system. When the FD push-button is pressed to set the FD off, the FD bars are out of view. Basically at power on, after the initialization process of the corresponding FMGC, the FD are automatically engaged and the push-buttons are lighted on.

(3) When LS push-button is used the corresponding PFD displays Localizer and Glide/Slope deviation scales whatever is the used landing system, ILS (Instrument Landing System) or MLS (Microvawe Landing System)


EIS – System description - PFD Primary Flight Display (1)

Typical PFD displays - Attitude, Airspeed, Altitude and Heading information

The PFD displays the main flight information necessary for the control of the A/C, arranged in the basic T configuration :

A/C symbol, pitch and roll indications, flight path angle and drift angle, guidance symbols (Flight or Flight Path Director).

Airspeed scale provides the pilot with the A/C actual indicated Air Speed, and with all the characteristic airspeed limitations. Characteristic airspeed limitations are computed by the FACs. Refer to chapter FE ( Flight Envelope ) of the ATA 22 chapter for more information.

An altitude scale and vertical speed scale provide the pilot with the A/C actual baro altitude and baro/inertial vertical speed, plus the altitude and flight level selections.

Baro setting reference indication

A heading scale provides the pilot with the A/C actual heading, actual track, and relative selections.


EIS – System description - PFD Primary Flight Display (2)

A full Flight Mode Annunciation ( FMA ) provides the pilot with the engaged modes, the various armed/active longitudinal and lateral modes,and the AP/FD/A-THR engagement status.

A vertical and lateral deviation scales give GLIDE/SLOPE - LOCALIZER or V/DEV -L/DEV (for further references other than LS) raw data.These deviation scales and indexes are only activated once the LS pushbutton on the FCU has been pressed in.

FD ( Flight Director ) barsFD tendency bars are displayed once the FD is engaged ( FD pushbutton pressed in and lighted on the FCU ).FD bars are composed of three bars: for pitch, roll and yaw .( for more information about FD, please refer to Flight Director chapter in the ATA 22 section ).

Additional flight information can be added on the PFD image, such as the radio altitude which will be displayed in digital form below the horizon line during landing, etc.


EIS – System description - ND Navigation Display

ROSE_ILS MODE ROSE_VOR MODE ROSE_NAV MODE

ARC MODE PLAN MODE

Depending of the EFIS control panel switch and selector setting it is possible to display the navigation data in different display types such as the one below:


EIS – System description - ECAM Electronic Centralized Aircraft Monitoring (1)

ECAM centralizes and displays the information related to various aircraft systems.

DMC 1 DMC 3 DMC 2

ECAM CP

PFD1

ND1 ECAM

1

ECAM2

ND2

PFD2

LGCIU 1 AND 2FWC 1 AND 2SDAC 1 AND 2ECU 1 AND 2ECAM CTL PANEL

FQI 1 AND 2LGCIU 1 AND 2EEC 1 AND 2FCDC 1 AND 2



The ECAM ( Electronic Centralised Aircraft Monitoring ) provides the information related to various aircraft systems.

UPPER ECAM

LOWER ECAMECAM CONTROL PANEL



SWITCHING PANEL

ECAM CONTROL PANEL

The ECAM control panel enables the display of different system pages ( ENG to F/CTL pushbuttons ) or to display a status page ( STS pushbutton ). See some samples in the following pages.



Engine primary indicationsFor the two engines, primary indications (N1, N2,EGT, FF) as well as engine management parameters(N1 LIM and actual operating mode, N1 CMD with A/THR engaged, will constantly be display on theECAM upper Display Unit in normal configuration.At landing, a “REV” indication will appear in theN1 indicators thrust reverser cowls unlocked,or fully deployed.

Fuel quantity indicationsThe numeric value of the total fuel weight on board(F.O.B.) will be permanently presented.

Slats/Flaps indicationsSlats and flaps position (selected position and actualposition, plus indications and messages for abnormal configurations)are also permanently presented.

Upper ECAM display

The lower zone will present various kinds of messages :-MEMO and A/C configurations item,-Warning/caution messages,-Title of A/C system pages in relation with warnings or cautions.


EIS (Electronic Instrument System) – System description - ECAM Electronic Centralized Aircraft Monitoring (5)

ENGINE PAGE

ELECTRICAL

Several system pages can be displayed using the ECAM control panel push-buttons. Here two examples: engine & electrical pages.Lower ECAM display

FUEL PAGE

FLIGHT CONTROL



This page displays status information of the aircraft system and configuration.

Lower ECAM display: STATUS page


EIS – System description - System reconfiguration – Normal operation

• In normal operation, each DMC, with respect to sensor and computer inputs, acquires data/parameters through its ONSIDE sources to gather all necessary data in order for the display unit driven by the DMC to generate all graphic symbologies related to a particular image.

•• In normal operation, each DMC drives two display units as follows:

• - The DMC 1 drives the CAPT PFD DU , CAPT ND DU, EWD, and SD.•• - The DMC 2 drives the F/O PFD DU and the F/O ND DU,•• - The DMC 3 is used in case of reconfigurations ( see chapter 5.7 System Reconfiguration ).

• In order to ensure the greatest availability of the displayed data, the fully redundancy architecture of the system enables three types of reconfiguration in case of any component failure:

• - In case of single or multiple DU failures,• - In case of single or multiple DMC failures,• - In case of external (sensor/computer) information source failures.


EIS – System description - System reconfiguration – Normal operation (2)

(*)


EIS – System description - System reconfiguration – DMC 1 failure

(*)

INVALID DATA

INVALID DATA EWDND PFD

DMC1

DMC3

DMC2

EF

IS2

DM

CM

DM

CM

PFD ND ND PFD

SD

DMC1

DMC3

DMC2

EF

IS2

DM

CM

DM

CM

EF

IS1

DM

CM

DM

CM

1) Loss of EFIS CAPT images 2) DMC2 takes over automatically for ECAM images

3) EIS DMC switch set to CAPT 34) CAPT EFIS images recovery

DM

CA

1

DM

CA

1

ND

DM

CA

1

EC

AM

3

EC

AM

M (

*)

DMCM

DMCM

EF

IS3/

1

EF

IS3/

1

EWD

SD

EC

AM

M

DMCM

DMCM

DMCA1

DMCA1

EC

AM

A

(*) assuming relay#2 is still powered



PFD ND EWD INVALID DATA

INVALID DATA

SD

DMC1

DMC3

DMC2

EF

IS2

DM

CM

DM

CM

PFD ND EWD ND PFD

SD

DMC1

DMC3

DMC2

DM

CA

1

DM

CA

1

EF

IS1

DM

CM

DM

CM

1) Loss of EFIS F/O images 2) EIS DMC switch set to F/O 33) F/O EFIS images recovery

EC

AM

M

DMCM

DMCM

EF

IS1

DM

CM

DM

CM

EC

AM

M

DMCM

DMCM

EF

IS3/

2

EF

IS3/

2



PFD ND EWD ND PFD

SD

DMC1

DMC3

DMC2

EF

IS1

DM

CM

DM

CM

EF

IS2

DM

CM

DM

CM

EC

AM

M

DMCM

DMCM

No change


EIS – System description - System reconfiguration – DMC 1 and 2 failure

INVALID DATA

INVALID DATA

INVALID DATA

INVALID DATA

INVALID DATA

INVALID DATA

DMC1

DMC3

DMC2

EF

IS2

DM

CM

DM

CM

PFD ND EWD INVALID DATA

INVALID DATA

SD

DMC1

DMC3

DMC2

EF

IS1

DM

CM

DM

CM

1) Loss of all images 2) EIS DMC switch set to CAPT 33) CAPT EFIS & ECAM images recovery

DM

CA

1

DM

CA

1

EC

AM

M

DMCM

DMCM

EC

AM

3

EC

AM

M (

*)

DMCM

DMCM

EF

IS3/

1

EF

IS3/

1

ECAM images can be transmitted by DMC2

(*) assuming relay#2 is still powered



1) Loss of EFIS CAPT images 2) DMC2 takes over automatically for ECAM images

INVALID DATA INVALID DATA EWD ND PFD

SD

DMC1

DMC3

DMC2

EF

IS1

DM

CM

DM

CM

EF

IS2

DM

CM

DM

CM

EC

AM

M

DMCM

DMCM

DMCA1

DMCA1

EC

AM

A



Loss of F/O images

PFD ND EWD INVALID DATA INVALID DATA

SD

DMC1

DMC3

DMC2

EF

IS1

DM

CM

DM

CM

EF

IS2

DM

CM

DM

CM

EC

AM

M

DMCM

DMCM


EIS – System description - System reconfiguration – DU normal operation

ND PFD EWD ND PFD

SD

DMC1

DMC3

DMC2

EF

IS1

DM

CM

DM

CM

EF

IS2

DM

CM

DM

CM

EC

AM

M

DMCM

DMCM

The CAPT PFD/ND pushbutton switch and the F/O PFD/ND pushbutton switch enable to exchange the PFD and the ND. This is a manual way to recover one missing EFIS display.PFD/ND transfer also works with DMC3 active


EIS – System description - System reconfiguration – DU 1 or DU 6 failure

INVALID DISPLAY

UNITPFD EWD

SD

DMC1

DMC3

INVALID DISPLAY

UNIT

PFDorND

EWD ND PFD

SD

DMC1

DMC3

DMC2

EF

IS2

DM

CM

DM

CM

EF

IS1

DM

CM

1) ND DU automatically displays the PFD image 2) Action on PFD/ND transfer pushbutton switch to recover ND image on ND DU

EC

AM

M

DMCM

DMCM

EF

IS1

DM

CM

EC

AM

M

DMCM

DMCM

ND PFD

DMC2

EF

IS2

DM

CM

DM

CM

DM

CM


EIS – System description - System reconfiguration – DU 2 or DU 5 failure

INVALID DISPLAY

UNITPFD

INVALID DISPLAY

UNITEWD

SD

DMC1

DMC3

PFDorND

EWD ND PFD

SD

DMC1

DMC3

DMC2

EF

IS2

DM

CM

DM

CM

EF

IS1

DM

CM

DM

CM

EC

AM

M

DMCM

DMCM

EF

IS1

DM

CM

EC

AM

M

DMCM

DMCM

ND PFD

DMC2

EF

IS2

DM

CM

DM

CM

1) No change on PFD DU 2) Action on PFD/ND transfer pushbutton switch to display ND image on PFD DU


EIS – System description - System reconfiguration – DU 1 + 2 failure or DU 5 + 6 failure

INVALID DISPLAY UNIT

INVALID DISPLAY UNIT EWD ND PFD

SD

DMC1

DMC3

DMC2

EF

IS1

DM

CM

DM

CM

EF

IS2

DM

CM

DM

CM

EC

AM

M

DMCM

DMCM

Loss of EFIS images on CAPT side


EIS – System description - System reconfiguration – DU 3 failure (CAPT reconfiguration)

PFD NDINVALID DISPLAY

UNIT

EWDorSD

DMC1

DMC3

PFDorND

SDINVALID DISPLAY

UNITND PFD

EWD

DMC1

DMC3

DMC2

EF

IS2

DM

CM

DM

CM

EF

IS1

DM

CM

DM

CM

EC

AM

M

DMCM

DMCM

EF

IS1

DM

CM

DM

CM

ND PFD

DMC2

EF

IS2

DM

CM

DM

CM

EC

AM

M

DMCM

1) DU 4 automatically displays the EWD image2) SD pages can still be displayed on the DU4 by momentary action on the ECAM control panel

3) ECAM/ND XFR switch set to CAPT4) SD image recovery on DU25) Action on PFD/ND XFR pushbutton switch to have PFD changed into ND


EIS – System description - System reconfiguration – DU 3 failure (F/O reconfiguration)


UNIT

EWDorSD

DMC1

DMC3


UNITSD

PFDorND

EWD

DMC1

DMC3

DMC2

EF

IS2

DM

CM

DM

CM

EF

IS1

DM

CM

DM

CM

EC

AM

M

DMCM

DMCM

EF

IS1

DM

CM

DM

CM

EC

AM

M

DMCM

ND PFD

DMC2

EF

IS2

DM

CM

DM

CM

DMCA1

EC

AM

A

1) DU4 automatically displays the EWD image2) SD pages can still be displayed on the DU4 by momentary action on the ECAM control panel

3) ECAM/ND XFR switch set to F/O4) SD image recovery on DU55) Action on PFD/ND XFR pushbutton switch to have PFD changed into ND


EIS – System description - System reconfiguration – DU 4 failure (CAPT reconfiguration)

PFD NDEWD

orSD

INVALID DISPLAY

UNIT

DMC1

DMC3

PFDorND

SD EWD ND PFD

INVALID DISPLAY

UNIT

DMC1

DMC3

DMC2

EF

IS2

DM

CM

DM

CM

EF

IS1

DM

CM

DM

CM

EC

AM

M

DMCM

DMCM

EF

IS1

DM

CM

DM

CM

EC

AM

M

DMCMND PFD

DMC2

EF

IS2

DM

CM

DM

CM

1) Loss of SD image2) SD pages can still be displayed on the DU3 by momentary action on the ECAM control panel

3) ECAM/ND XFR switch set to CAPT4) SD image recovery on DU25) Action on PFD/ND XFR pushbutton switch to have PFD changed into ND


EIS – System description - System reconfiguration – DU 4 failure (F/O reconfiguration)

PFD NDEWD

orSD

INVALID DISPLAY

UNIT

DMC1

DMC3

PFD ND EWD SDPFDorND

INVALID DISPLAY

UNIT

DMC1

DMC3

DMC2

EF

IS2

DM

CM

DM

CM

EF

IS1

DM

CM

DM

CM

EC

AM

M

DMCM

DMCM

EF

IS1

DM

CM

DM

CM

EC

AM

M

DMCMND PFD

DMC2

EF

IS2

DM

CM

DM

CM

EC

AM

A

DMCA1

1) Loss of SD image2) SD pages can still be displayed on the DU3 by momentary action on the ECAM control panel

3) ECAM/ND XFR switch set to F/O4) SD image recovery on DU55) Action on PFD/ND XFR pushbutton switch to have PFD changed into ND


EIS – System description - System reconfiguration – DU 3 + 4 failure (CAPT reconfiguration)


UNIT

INVALID DISPLAY

UNIT

DMC1

DMC3

PFDorND

EWDorSD

INVALID DISPLAY

UNIT

INVALID DISPLAY

UNIT

DMC1

DMC3

EF

IS1

DM

CM

DM

CM

EC

AM

M

DMCM

DMCM

EF

IS1

DM

CM

DM

CM

ND PFD

DMC2

EF

IS2

DM

CM

DM

CM

ND PFD

DMC2

EF

IS2

DM

CM

DM

CM

1) Loss of ECAM image 2) ECAM/ND XFR switch set to CAPT3) EWD image recovery on DU22) SD pages can still be displayed on the DU2 by momentary action on the ECAM control panel4) Action on PFD/ND XFR pushbutton switch to have PFD changed into ND


EIS – System description - System reconfiguration – DU 3 + 4 failure (F/O reconfiguration)


UNIT

INVALID DISPLAY

UNIT

DMC1

DMC3


UNIT

EWDorSD

PFDorND

INVALID DISPLAY

UNIT

DMC1

DMC3

DMC2

EF

IS2

DM

CM

DM

CM

EF

IS1

DM

CM

DM

CM

EC

AM

M

DMCM

DMCM

EF

IS1

DM

CM

DM

CM

ND PFD

DMC2

EF

IS2

DM

CM

DM

CM

1) Loss of ECAM image2) ECAM/ND XFR switch set to F/O3) EWD image recovery on DU52) SD pages can still be displayed on the DU5 by momentary action on the ECAM control panel4) Action on PFD/ND XFR pushbutton switch to have PFD changed into ND


EIS – System description - System reconfiguration – Input buses reconfiguration 1/3)

Pilots are provided with a Source Select Panel (SSP) which is used to select the information from the incoming sensors to be used by the EIS system. This selection includes:

- Attitude / Heading Computer Selection,

- Air Data Unit Selection.

- EIS DMC Selection.

The following tables show which sensors and computers are connected to each DMC and indicates those DMC inputs used in normal operation (N) or after source reconfiguration (R), according to the validity of these sensors/computers and the switching possibly made by the crew (ATT/ HDG, AIR DATA and EIS DMC).

Wired to DMCnumber

Processed byDMC number

Processed by DMC3when transferLRU Name

Input BusName

1 2 3 1 2 3 3/1 3/2Remarks

FAC1 X X X N R N N RFAC

FAC2 X X X R N R R NAutomatic selection, according to FAC validity andAIR DATA switching

FGC1 X X X X X X X XFGC2 X X X X X X X XFM1 X X X N R N N R

FMGC

FM2 X X X R N R R NR, if onside FMGC FM part has failed

EFIS1-1 X X X X XEFIS1-2 X X X X XEFIS2-1 X X X X

FCU

EFIS2-2 X X X X

Selection of FCU processor 2 in case of failure ofprocessor 1


EIS – System description - System reconfiguration – Input buses reconfiguration (2/3)

Wired to DMCnumber



Input BusName

1 2 3 1 2 3 3/1 3/2Remarks

IRS1 X X X N F N NIRS2 X X X F N NIRS3 X X X R R R R R

R, if CAPT (F/O) selects ATT/HDG CAPT/3 (F/O/3)F for feedback

ADC1 X X X N F N NADC2 X X X F N N

ADIRU

ADC3 X X X R R R R R

R, if CAPT (F/O) selects ATT/HDG CAPT/3 (F/O/3)F for feedback

VOR1 X X X X X X X XVOR

VOR2 X X X X X X X XILS1 X X X X X X X X

ILSILS2 X X X X X X X X

ILS1 -> PFD1 & ND2ILS2 -> PFD2 & ND1

RA1 X X X X X X X XRA

RA2 X X X X X X X XDME1 X X X X X X X X

DMEDME2 X X X X X X X XADF1 X X X X X X X X

ADFADF2 X X X X X X X X

(ADF2 optional)

ECAM CTLPNL

X X X X X X X X

FQIU1-1 X X X X X XFQIU1-2 X XFQIU2-1 X X

FQIU

FQIU2-2 X X X X X X

R, when the channel superiority signal controls thechange over to the other bus or when the normalbus becomes faulty

CFDIU X X X X X X X X


EIS – System description - System reconfiguration – Input buses reconfiguration (3/3)

Wired to DMCnumber



Input BusName

1 2 3 1 2 3 3/1 3/2Remarks

WXR1-1 X X X N N N NWXR1-2 X X X N N N RWXR2-1 X X X R R R N

WXR(A453)

WXR2-2 X X X R R R RFWC1-1 X XFWC1-2 X XFWC1-3 X X X XFWC2-1 X XFWC2-2 X X

FWC(A429)

FWC2-3 X X X XFWC1-1 X NFWC1-2 X NFWC1-3 X N N NFWC2-1 X RFWC2-2 X R

FWC(RS422)

FWC2-3 X R R R

R, when FWC1-X bus is seen faulty

SDAC1 X X X X X X X XSDAC

SDAC2 X X X X X X X X(ADF2 optional)

1-A1 X X X X X X1-A2 X X1-B1 X X X X1-B2 X X X X2-A1 X X X X X X2-A2 X X2-B1 X X X X

ECUorEEC

2-B2 X X X X


EIS – System description - Monitoring of displayed parameters (1/2)

• The following parameters, displayed on the PFD image, are monitored :• - Pitch indication,• - Roll indication,• - Heading indication,• - Altitude indication.

• The following parameter, displayed on the ND image, are monitored :• - Heading indication.

• The following parameters, displayed on the E/WD image, are monitored :• - N1 indications (digital and analog readouts), for all the engines.• - N2 indications (digital readout), for all the engines.• - N3 indications (digital readout), for all the engines.• - EGT indications (digital and analog readouts), for all the engines.• - Fuel flow indications (digital readout), for all the engines.• - EPR indications (digital and analog readouts), for all the engines.

• The following parameter, displayed on the SD image, are monitored :• - UTC indication (digital readout, minutes only).

• The discrepancy between direct and opposite values for every critical parameter is compared with a corresponding threshold, so that if this discrepancy exceeds this threshold during the confirmation time, the monitoring DU will trigger the order to display a feedback CHECK message.


EIS – System description - Monitoring of displayed parameters (2/2)

When a DU triggers an order to display a feedback CHECK message, a specific message is announced by the monitoring DU as described hereafter :

- 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 Trouble Shooting Data (class 1 internal failure) is stored in the DU BITE zone.


EIS – System description - ECAM warnings DMC 1 FAULT

DMC 1 FAULT detected by FWC

Local warning UPPPER ECAM DU LOWER ECAM DU STATUS

EIS DMC 1 FAULT (a)- EIS DMC SWITCH………..CAPT (c)

INOP SYS (w) DMC 1 (a)

Inhibition: during flight phases 4, 5, 7, 8 Flight phases ?

MASTER CAUTION

SINGLE CHIME




Local warning UPPPER ECAM DU LOWER ECAM DU STATUS

EIS DMC 2 FAULT (a)- EIS DMC SWITCH………….F/O (c)



MASTER CAUTION

SINGLE CHIME




Local warningUPPPER ECAM DU LOWER ECAM DU STATUS

EIS DMC 3 FAULT (a)



MASTER CAUTION

SINGLE CHIME


EIS – System description - DU power supply

The 3 DMCs, the 6 DUs are supplied with 115 VAC / 400 Hz single phase and also receive 28 VDC for on/off switching control signals.


EIS – System description - DMC power supply

• DMC Power Supply:

• In NORMAL electrical configuration, DMC3 is supplied with 115 VAC BUS1.

• In case of 115 VAC BUS1 loss and if EIS DMC selector is on CAPT 3 position, power supply switching is applied automatically and DMC3 is supplied with 115 VAC ESS BUS.

• Note 1: On schematic, 20XN relay is shown energized (AC BUS1 is active) and 26WT relay is not energized.


EIS – System description - Circuit breaker

Circuit Breakers fitted on 49VU (Overhead Panel)Designation Identifier Location

EIS/ND CAPT/SPLY 12WT1 E01EIS/ND CAPT/SWTG 23WT1 E02EIS/PFD CAPT/SPLY 11WT1 E03EIS/PFD CAPT/SWTG 22WT1 E04EIS/ECAM DU/UPPER/SPLY 13WT1 E05EIS/ECAM DU/UPPER/SWTG 24WT1 E06EIS/DMC3/SWTG 21WT3 E07EIS/DMC1/SWTG 21WT1 E09EIS/DMC3/STBY/SPLY 14WT1 E10EIS/DMC1/SPLY 10WT1 E11EIS/ECAM/CTL/PNL 15WT E12

Circuit Breakers fitted on 121VU (behind F/O seat)Designation Identifier Location

EIS/DMC2/SPLY 10WT2 Q08EIS/DMC3/SPLY 10WT3 Q09EIS/PFD/F/O 11WT2 R03EIS/ND/F/O 12WT2 R04EIS/PFD/F/O/SWTG 22WT2 R05EIS/ND/F/O/SWTG 23WT2 R06EIS/DMC2/SWTG 21WT2 R08EIS/ECAM DU/LOWER/SWTG 24WT2 R10EIS/ECAM DU/LOWER/SPLY 13WT2 R11


EIS – On Board maintenance

ON BOARD MAINTENANCE & BITE


EIS – On Board maintenance – BITE (DMC and DU) General

There are 3 types of Built-In Test:

- Power-On Self Test ( POST ): this includes software and hardware testing activated at power on. The objective of the POST is to ensure of the validity of the equipment

- Continuous Built-In Test ( CBIT ): the CBIT includes recurrent tests. The objective is to detect internal or external, to memorize the abnormal event, to analyze it and then to transmit the failure report to the centralized maintenance system i.e. the CFDIU (Centralized Fault Interface Unit

- Initiated Test ( IBIT ): interactive test called IBIT are activated while the aircraft is on ground, the CFDS (Centralized Fault Display Display System) switched to MENU mode, the INST (Instrument) page selected and finally the EIS 1 (2) or (3) page has been selected by the MCDU operator.


EIS – On Board maintenance – BITE (DMC and DU) – Power On (1/4)

1 : after power-on, DMC and DU acquire flight/ground information during 300 ms and pin-programming.

2 : after 300 ms, DMC and DU activate the POST mode. DUs display the SELF TEST IN PROGRESS green message.

3 : DMC, after correct completion of the POST mode, activates the OPER mode and sends operational data to DUs. DUs, because of their internal hardware tests duration, are always activating the POST mode tests and displaying the SELF TEST IN PROGRESS green message.



5 : after correct completion of theses checks, DUs display an operational image.

4 : DUs, after correct completion of the POST mode, activate the OPER mode. During this phase, DUs send software version and link check wordstring and activate the software version check process and the A629 inputs validity check process. During this phase (short test), nothing is displayed on DUs. DMC is always sending operational data to DUs.

The duration of these tests is equal to 40 seconds for the LCDU and 35 seconds for the DMC.



SELF TEST IN PROGRESS

(MAX 40 SECONDS)

During the POST mode, or in case of interruption during the POSTs, when the DU starts again and if the results of the previous POST was OK, the SELF TEST IN PROGRESS (MAX 40 SECONDS) green message is displayed, when the required resources are available.

INVALID DISPLAY

UNIT

If the required resources are available, the INVALID DISPLAY UNIT amber message is displayed when:- a fatal failure is detected during the DU POST,- or in case of interruption during the POSTs, when the DU starts again and if the results of the previous POST was KO.

FIf the hardware resources to display a failure message, are not available, the hardware pattern F is displayed in amber. If any failure is detected during the start-up phase (for instance if one of the two graphic channels is out of order), the software orders directly to the hardware the display of the hardware pattern F.

Notes: message displayed are largely blow-up and does not correspond to the actual text size



Notes: message displayed are largely blow-up and does not correspond to the actual text size

The POST mode activities and their sequence for DMC are:1) hardware P/N compatibility check (complete),2) pin program parity check (complete),3) equipment location check (complete),4) engine type validity check (complete),5) internal hardware tests (complete/light).

The POST mode activities and their sequence for DU are:1) hardware P/N compatibility check (complete),2) pin program parity check (complete),3) equipment location check (complete),4) internal hardware tests (complete/light).

INVALID DATAIn case of DMC POST activity n° 1, 2, 3, or 5 failure the DU displays the INVALID DATA amber message.

DMC VERSION INCONSISTENCY

In case of DMC POST activity n° 4 failure the DU displays the DMC VERSION INCONSISTENCY amber message.


EIS – On Board maintenance (1)

Tele-loading from an external data-loader (aircraft data loader or portable data loader) into a DMC. This operation is called DMC Uploading.

Tele-loading from a DMC into DUs is called DU Cross-loading,

Tele-loading from a DMC into another DMCs is called DMC Cross-loading.

DMC

Data-loader Active DMC

DMC

another DMC

DU

The DMC or DU delivered to you (as spare equipment or after a repair) does not content any software or may content a software which is not the latest one.

As a consequence, once a DMC or a DU is installed on board the aircraft it is necessary to load the software into it

You can do this software loading in three manner/



The following figure gives examples of the 3 different tele-loading sub-functions. For the DU cross-loading sub-function, the maintenance operator has to configure the DUs on the Emitter DMC by using the DMC reconfiguration

• Note: The cross-load of the 6 DUs in one operation is not possible. To load the 6 DUs, 2 cross-loading operations from 2 different DMCs are needed. These 2 operations have to be done one after the other (2 DMCs can not be in cross-loading mode at the same time).





Up-loading DMC from the data loader (block diagram of the connections between DMCs and Data Loader)


EIS – On Board maintenance (5) – Tele Loading

Tele-loading Description :

During a tele-loading (Uploading or Cross-loading), the loaded LRU:• - manages the dialogue with the loader,• - manages its FPROM (erase, write on the FPROM), • - behaves as if it was not powered regard to the other computer, it does not emitting on the output buses

(except the bus used for tele-loading) and sets discrete signals in the open state.

When the transfer of the software to the LRU is completed, the LRU checks the integrity of the tele-loaded software. If the integrity checks of the tele-loaded software are false, the LRU:

• - sends its part number hardware, a part number software corresponding to a LRU without operational software and its serial number every 50 ms on the A629 bus,

• - stays in TELE mode and waits for a new tele-loading request.

L E

• Note: During the tele-loading, a DU displays the large L cyan letter.• Before tele-loading the DU without software displays the large E white letter.


EIS – On Board maintenance (6) - Tele Loading

• The duration of the uploading depends on the protocol used (A615-3 or A615A) and on the internal behavior of the data-loader.

• The total duration of any kind of cross-loading (1 to 2 DMCs or 1 to 6 DUs) is less than 10 minutes. The cross-loading duration includes the time needed for data transfer on A629 buses, data writing on FPROM and integrity checks of tele-loaded software (any manual operation by the operator is not part of the cross-loading duration).

When a DMC cross-loads several LRUs at the same time, if the cross-load of one LRU is aborted, the DMC considers as aborted only the cross-loading of this LRU and the DMC continues the cross-loading of the other LRUs.

• Note: There is no requirement on uploading duration for the EIS. Cross-loading duration is given for a 16 Mbits software and if the FPROM writing or erasing time is typical, i.e. the FPROM is used in normal conditions (temperature, voltage, wearing state of the FPROM).



General• The (OMS) On board Maintenance System through MCDUs, installed in the cockpit, provides maintenance

operator with the possibility to consult A/C systems status and to activate a set of tests.

• This function is accessible when the OMS is in MENU Mode. Note that this mode correspond to the INTR mode of the new EIS system. Note this mode is available on ground only.

• During the INTR mode and if no other image is requested, each DU, that is connected to a DMC which is in maintenance mode, displays the MAINTENANCE MODE green message.

1L

2L

3L

4L

5L

6L

1R

2R

3R

4R

5R

6R

D M C 1

L A S T L E G C L A S S 3

< R E P O R T F A U L T >

P R E V I O U S L E G S S Y S T E M

< R E P O R T T E S T >

< L R U I D E N T

S W T G / B U S / D U

< G N D S C A N N I N G T E S T S >

T R O U B L E S H O O T G R O U N D

< D A T A R E P O R T >

P I N P R O G / S T A T U S

< R E T U R N A N D X L O A D >

MCDU Display

MAINTENANCE MODE


Once in the DMC Main Menu, the operator can access the following sub-menus:

DMC Main Menu

Last Leg Report

Previous Legs

Report

LRU Identification

Ground Scanning

Trouble Shoot Data

Class 3 faults

System Test

Ground Report

SWTG/BUS/DU

Test

Pin Prog Status &

Xload

Data Bus Test

Switching Test

DMC Load

DU Load Backlighting Status

LCD Status

Pin Prog

1L

2L

3L

4L 5R

2R

1R

5L

6R

4R

2L 3L

2L 3L 4L

5L

DU Brightness

Test

4L

Engines

2R 3R


Have a look on the MCDU simulator


D M C 1

P I N P R O G / S T A T U S

A N D X L O A D

< D M C X L O A D P I N P R O G >

< D U X L O A D E N G I N E S >

D U B A C K L I G H T

< S T A T U S

< L C D S T A T U S

< R E T U R N P R I N T *

The Pin Prog/Status and Xload menu, accessed by key 6R of the DMC main menu, allows:

• - to activate the cross-loading between DMCs or between DMC and DU,• - to consult EIS system pin programming,• - to activate specific tests in order to supervise some characteristics of the EIS system,• - to consult engines parameters.



The DMC Cross-Load function, activated by key 2L of the Pin Prog/Status and Xload menu, allows:

- to display the software part number of all the DMCs,- to activate and follow the cross-loading progress of a target DMC by the origin DMC.

If the software part number of a target DMC is the same as the software part number of the origin DMC, it is displayed in green characters, otherwise it is in amber characters.

If a target DMC does not transmit its software part number or does not have any software, specific messages are displayed in amber characters.

D M C 1

D M C X L O A D

A C C E S S X L O A D >

E I S S W P N R

D M C 1 : S X T 3 E - E 2 S A - 0 4 0 0

X L O A D T O

D M C 2 : S X T 3 E - E 2 S A - 0 4 0 0

D M C 3 : S X T 3 8 - E 2 S A - 0 3 0 1


D M C 1

D M C X L O A D


E I S S W P N R

D M C 1 : S X T 3 E - E 2 S A - 0 4 0 0

X L O A D T O

D M C 2 : X L O A D N O T A V A I L

D M C 3 : E M P T Y




By pressing the 1R key (ACCESS XLOAD) of the previous page and according to EIS system status, the following pages can be displayed:

D M C 1

D M C X L O A D

E I S S W P N R

D M C 1 : S X T 3 E - E 2 S A - 0 4 0 0

X L O A D T O

D M C 2 : S X T 3 E - E 2 S A - 0 4 0 0

D M C 3 : X L O A D N O T A V A I L

D M C X L O A D N O T A L L O W E D


If software part numbers of a target DMCs are identical or not available the Xload function is not allowed.

D M C 1

D M C X L O A D

E I S S W P N R

D M C 1 : S X T 3 E - E 2 S A - 0 4 0 0

X L O A D T O

D M C 2 : E M P T Y

D M C 3 : S X T 3 8 - E 2 S A - 0 3 0 1

< S T A R T X L OA D


If a least one target DMC does not have any software or a different part number, the operator can start the Xload function.



By pressing the 5L key (START XLOAD) of the previous page, the following pages are sequentially displayed:

If a target DMC does not need to be cross-loaded, the corresponding message "DMC1 to DMCx" is not displayed.

D M C 1

D M C X L O A D

T R A N S F E R I N P R O G R E S S

D M C 1 T O D M C 2

D M C 1 T O D M C 3

M A X 1 0 M I N U T E S

0 0 %

D M C 1

D M C X L O A D

I N T E G R I T Y C H E C K

D M C 2

D M C 3

M A X 1 5 S



According to the integrity check result, a green or amber message is displayed beside each DMC, to indicate integrity check result.

Each successfully downloaded DMC automatically performs self-test.

D M C 1

D M C X L O A D

D M C 2 : X L O A D C O M P L E T E D

D M C 3 : X L O A D A B O R T E D


D M C 1

D M C X L O A D

D M C 2 : X L O A D C O M P L E T E D

D M C 3 : X L O A D A B O R T E D

D M C S E L F T E S T

I N P R O G R E S S ( 3 5 s )

R E T U R N P R I N T *



The DU Cross-Load function, activated by key 3L of the Pin Prog/Status and Xload menu, allows:

- to display the software part number of the origin DMC and all the DUs,- to activate and follow the cross-loading progress of a target DU by the origin DMC.

If the software part number of a target DU is the same as the software part number of the origin DMC, it is displayed in green characters, otherwise it is in amber characters.

If a target DU does not transmit its software part number or does not have any software, specific messages are displayed in amber characters.

D M C 1

D U X L O A D


E I S S W P N R

D M C 1 : S X T 3 E - E 2 S A - 0 4 0 0

X L O A D T O

P F D C A P T : S X T 3 E - E 2 S A - 0 4 0 0

N D C A P T : S X T 3 E - E 2 S A - 0 4 0 0

P F D F / O : X L O A D N O T A V A I L

N D F / O : E M P T Y

E W D : S X T 3 E - E 2 S A - 0 4 0 0

S D : S X T 3 8 - E 2 S A - 0 3 0 1




By pressing the 1R key (ACCESS XLOAD) of the previous page and according to EIS system status, the following pages can be displayed:

The following page is displayed, for all DMCs, if no target DU needs to be cross-loaded (the DU software part number is the same than the origin DMC or the DU is not available).

The following "initial conditions" page for DMC1 or DMC2 is displayed if at least one target DU needs to be cross-loaded (the DU software part number is different than the origin DMC or the DU is without software).

D M C 1

D U X L O A D

D U X L O A D N O T A L L O W E D


D M C 1

D U X L O A D

I N I T I A L C O N D I T I O N S :

- S E T T H E E I S D M C S E L

T O N O R M

< S T A R T X L O A D




For DMC3, a menu is displayed to select DUs to be cross-loaded, then the following described initial conditions (1 page) are displayed:

1L

2L

3L

4L

5L

6L

1R

2R

3R

4R

5R

6R

D M C 3

D U X L O A D



T O C A P T 3



1L

2L

3L

4L

5L

6L

1R

2R

3R

4R

5R

6R

D M C 3

D U X L O A D

X L O A D T O

< E F I S C A P T A N D E C A M D U

X L O A D T O

< E F I S F O D U


1L

2L

3L

4L

5L

6L

1R

2R

3R

4R

5R

6R

D M C 3

D U X L O A D



T O F O 3





By pressing the 5L key (START XLOAD) of the previous page, the following pages are sequentially displayed:

If a target DU does not need to be cross-loaded or cannot be cross-loaded (not connected), the corresponding message "DMC1 to DUx” is not displayed.

1L

2L

3L

4L

5L

6L

1R

2R

3R

4R

5R

6R

D M C 1

D U X L O A D

T R A N S F E R I N P R O G R E S S

D M C 1 T O P F D C A P T

D M C 1 T O N D C A P T

D M C 1 T O E W D

D M C 1 T O S D

M A X 1 0 M I N U T E S

0 0 %

1L

2L

3L

4L

5L

6L

D M C 1

D U X L O A D

I N T E G R I T Y C H E C K

P F D C A P T

N D C A P T

E W D

S D

M A X 1 5 S



According to the integrity check result, a green or amber message is displayed beside each DU, to indicate integrity check result. Each successfully downloaded DU automatically performs self-test.

1L

2L

3L

4L

5L

6L

1R

2R

3R

4R

5R

6R

D M C 1

D U X L O A D

P F D C A P T : X L O A D C O M P L E T E D

N D C A P T : X L O A D A B O R T E D

E W D : X L O A D C O M P L E T E D

S D : X L O A D C O M P L E T E D


1L

2L

3L

4L

5L

6L

1R

2R

3R

4R

5R

6R

D M C 1

D U X L O A D

P F D C A P T : X L O A D C O M P L E T E D

N D C A P T : X L O A D A B O R T E D

E W D : X L O A D C O M P L E T E D

S D : X L O A D C O M P L E T E D

D U S E L F T E S T

I N P R O G R E S S ( 4 0 s )

R E T U R N P R I N T *



For DMC3, by pressing the RETURN key from the previous page, the following page is displayed:

D M C 3

D U X L O A D

C L O S E U P


T O N O R M




The Backlight Status page, activated by key 4L of the Pin Prog/Status and Xload menu, allows to display parameters of the Back Lighting Module (BLM) of the active DUs.

•DU Back-lighting Test Activation:•On BACKLIGHT STATUS command reception from the active DMC, the DU, if its position corresponds to the DU selected in the BACKLIGHT STATUS page:- generates the calibrated maximum luminance,- activates the BLM lamp tests,- acquires the BLM characteristics from BLM interface,- sends on A629 link the BLM characteristics and BLM lamp test.


Before starting the test on DMC1 & DMC2, the following described initial conditions (1 page) are displayed (aircraft avionics must be powered).

1L

2L

3L

4L

5L

6L

1R

2R

3R

4R

5R

6R

D M C 1

D U B A C K L I G H T S T A T U S


- M A K E S U R E T H A T A L L D U

A R E O N


T O N O R M

< A C C E S S T E S T


1L

2L

3L

4L

5L

6L

1R

2R

3R

4R

5R

6R

D M C 2




A R E O N


T O N O R M



DMC1 DMC2


Before starting the test on DMC3, a menu is displayed to select tested DUs, then the following described initial conditions (1 page) are displayed (aircraft avionics must be powered).

1L

2L

3L

4L

5L

6L

1R

2R

3R

4R

5R

6R

D M C 3




A R E O N


T O C A P T 3



1L

2L

3L

4L

5L

6L

1R

2R

3R

4R

5R

6R

D M C 3


< E F I S C A P T A N D E C A M D U

< E F I S F O D U


1L

2L

3L

4L

5L

6L

1R

2R

3R

4R

5R

6R

D M C 3




A R E O N


T O F O 3





By pressing the 5L key (ACCESS TEST) of the previous page, the following menu is displayed and allows operator to consult status of each DU.•Note: only linked DU are accessible and displayed with a prompt.

D M C 1


< P F D C A P T P F D F / O

< N D C A P T N D F / O

< E / WD S D >




From the previous menu, by selection of the DU, the following pages may be displayed:

If selected DU is not associated to the active DMC

If selected DU is failed

1L

2L

3L

4L

5L

6L

1R

2R

3R

4R

5R

6R

D M C 1


P F D F O

S T A T U S N O T P O S S I B L E

F R O M D M C 1


1L

2L

3L

4L

5L

6L

1R

2R

3R

4R

5R

6R

D M C 1


P F D C A P T

S T A T U S N O T A V A I L A B L E

( P F D C A P T U N S E R V I C E A B L E )


1L

2L

3L

4L

5L

6L

1R

2R

3R

4R

5R

6R

D M C 1


P F D C A P T

T E S T I N P R O G R E S S 5 s


If selected DU is associated to the active DMC and is not failed



When the test is launched, i.e. TEST IN PROGRESS message is displayed, the following pages gives the status of the lamps of both stages of the Back Lighting Module (BLM) of the current DU are displayed.

Lamps failed are indicated by the FAIL amber message and lamps good condition are indicated by the OK green message.• For DMC1 & DMC2, Backlight Status consultation is completed after the display of one of these pages.

1L

2L

3L

4L

5L

6L

1R

2R

3R

4R

5R

6R

D M C 1 1 / 2


P F D C A P T

L A M P 1 : O K L A M P 6 : O K

L A M P 2 : O K L A M P 7 : O K

L A M P 3 : O K L A M P 8 : O K

L A M P 4 : O K L A M P 9 : O K

L A M P 5 : O K L A M P 1 0 : O K


1L

2L

3L

4L

5L

6L

1R

2R

3R

4R

5R

6R

D M C 1 2 / 2


P F D C A P T

L A M P 1 1 : O K L A M P 1 6 : O K

L A M P 1 2 : O K L A M P 1 7 : O K

L A M P 1 3 : O K L A M P 1 8 : O K

L A M P 1 4 : O K L A M P 1 9 : O K

L A M P 1 5 : O K L A M P 2 0 : F A I L


Next Page



For DMC3, by pressing the RETURN key on one of the previous page the following page is displayed:

D M C 3


C L O S E U P


T O N O R M




The LCD Status page, activated by key 5L of the Pin Prog/Status and Xload menu, allows to verify the wear level of the LCD displays. Three test patterns could be displayed on the LCDU.

• LCD Status Activation:- On LCDU STATUS command reception from the active DMC, the DU:- displays the test image corresponding to the selected key.

D M C 1

L C D S T A T U S

D I S P L A Y T E S T 1




D M C 1

L C D S T A T U S

T E S T N O T A V A I L A B L E


If test can not be initiated, the following page is displayed



The Display Test 1 is used during on-board maintenance step, in order to evaluate the graphic drawing capability of the LCDU725. A specific pattern is used which is composed of:

- a color palette which presents the 8 basis colors,- a gray scale from Black to White in order to check the addressing chain of the LCD panel,- the LCDU725 Part and Serial Number,- the EIS Software Part Number.

D M C 1

L C D S T A T U S


I N P R O G R E S S


PNR: C19298AF05 THALES AVIONICS

SER: C19298000234

EIS SW

PNR: SXT3E-E2SA-0400 LCDU 725


Have a look on the MCDU simulator


The Display Test 2 is used to check the Pixels defect OFF and ON by a visual control of a dedicated checkerboard gray and white colored.

D M C 1

L C D S T A T U S


I N P R O G R E S S




The Display Test 3 is used to check the Pixels defect OFF and ON by a visual control of a dedicated checkerboard gray and white colored.

D M C 1

L C D S T A T U S


I N P R O G R E S S




The PIN PROG pages, activated by key 2R of the Pin Prog/Status and Xload menu, enables access to Hardware and Software program pins as shown hereafter.

•Pin Programming Activation:• On PIN PROG command reception from the active DMC, the DU:• restores the hardware program pin configuration from the EEPROM,• restores the software program pin configuration from the EEPROM,• sends the two configurations on the A629 link.

D M C 1

P I N P R O G

< H A R D P I N P R O G

< S O F T P I N P R O G




From Hard Pin Prog menu, activated by key 2L of the previous menu, operator can consult for the current DMC and each DUs, the Hard pin programming configuration displayed in a list form with the name of the hard PP and the its value.• Note: Use Next/Previous page keys to scroll Hard PP list. There are 17 hard PP for DU and 48 for DMC.

D M C 1

D U N D F / O H A R D P P

D U P O S I 1 0

D U P O S I 1 1

D U P O S I 1 0

D U F T E 0

D U D E V -

D U P A R I T Y 0

D U S H O P 0

D U A C P T E S T 0


D M C 1

H A R D P I N P R O G

< D M C 1

< D U P F D C A P T D U N D F / O

< D U N D C A P T D U E / W D

< D U P F D F / O D U S D >


When a PP status is unknown a dash is displayed.



The Soft Pin Prog pages, activated by key 2L of the previous menu, operator can consult for the current DMC the Boolean and Numeric software pin programming configuration displayed in a list form with the name of the soft PP and the its value.

• Note: Use Next/Previous page keys to scroll Soft PP list. There are 99 Boolean PP and 96 Numeric PP.

D M C 1 1 / 1 4

S O F T P I N P R O G

G L S O P T I O N 0 S T A I R S D O O R 1

M L S O P T I O N 1 B U L K D O O R 1

M M R I N S T 0 C T R T A N K 0

A P P T Y P E 1 P R E D W S 0

M O R A 1 G N D C O O L 0

F W D C G O H E A T 1 0

A F T C G O H E A T 1 0

F W D C G O V E N T 1 0

A F T C G O V E N T 0 1


Boolean software program pins

D M C 1 7 / 1 4

S O F T P I N P R O G

N 1 R L 1 1 1 1

N 1 R L 2 1 1 1

N 2 R L 1 1 1 1

N 2 R L 2 1 1 1

E G T R L 1 2 0 4 8

E G T R L 2 2 0 4 8


Numeric software program pins



The Engines page, activated by key 3R of the Pin Prog/Status and Xload menu, allows to display the engine parameters recorded by the current DMC.

D M C 1

E N G I N E S O V E R S P E E D / T E M P

< N 1 E 1 N 1 E 2 >

< N 2 E 1 N 2 E 2 >

< E G T E 1 E G T E 2 >

< G E N E R A L R E S E T




D M C 1


N 1 R E D L I N E = 1 0 4 . 0 %

N 1 E 1 M A X R E A C H E D = 1 0 7 . 5 %


If the maximum speed reached is over the red line value

D M C 1


N 1 R E D L I N E = 1 0 4 . 0 %

N 1 E 1 = N O O V E R S P E E D


If the maximum speed reached is not over the red line value

D M C 1


E G T 1 R E D L I N E = 9 1 0 . 0 ° C

E G T 1 M A X R E A C H E D =

9 3 0 . 0 ° C


If the maximum temperature reached is over the red line value

DMC 1


E G T 1 R E D L I N E = 9 1 0 . 0 ° C

E G T 1 = NO O V E R T EM P


If the maximum temperature reached is not over the red line value



An error code corresponds to a message sent to the OMS. The list of external error code with the associated message sent to the OMS is given hereafter:

ErrorCode

ATANumber

Message

1 345331 ADF1(2RP1)/DMCx(1WTx)

2 341234ADIRU1(1FP1)BUSx ADR/

DMCx(1WTx)

3 341234ADIRU1(1FP1)BUSx IR/

DMCx(1WTx)4 341234 ADIRU1(1FP1)

ADIRU2(1FP2)BUS2 ADR/DMC1(1WT1) (note 5)ADIRU2(1FP2)BUS1 ADR/DMC2(1WT2) (note 6)

5 341234

ADIRU2(1FP2)BUS3 ADR/DMC3(1WT3) (note 7)ADIRU2(1FP2)BUS2 IR/DMC1(1WT1) (note 5)ADIRU2(1FP2)BUS1 IR/DMC2(1WT2) (note 6)

6 341234

ADIRU2(1FP2)BUS3 IR/DMC3(1WT3) (note 7)

7 341234 ADIRU2(1FP2)ADIRU3(1FP3)BUS3 ADR/DMC1(1WT1) (note 5)ADIRU3(1FP3)BUS2 ADR/DMC2(1WT2) (note 6)

8 341234

ADIRU3(1FP3)BUS1 ADR/DMC3(1WT3) (note 7)

ErrorCode

ATANumber

Message

ADIRU3(1FP3)BUS3 IR/DMC1(1WT1) (note 5)ADIRU3(1FP3)BUS2 IR/DMC2(1WT2) (note 6)

9 341234

ADIRU3(1FP3)BUS1 IR/DMC3(1WT3) (note 7)

10 341234 ADIRU3(1FP3)11 313234 CFDIU(1TW1)/DMCx(1WTx)12 345133 DME1(2SD1)/DMCx(1WTx)13 345133 DME2(2SD2)/DMCx(1WTx)14 316112 ECP (6WT)/DMCx(1WTx)

15 732160ECU(E1-4000KS)BUS ECU1A/DMCx(1WTx) (note 1)

16 732160ECU(E1-4000KS)BUS ECU1B/DMCx(1WTx) (note 1)

17 732160ECU(E2-4000KS)BUS ECU2A/DMCx(1WTx) (note 1)

18 732160ECU(E2-4000KS)BUS ECU2B/DMCx(1WTx) (note 1)

19 732160 ECU(E1-4000KS) (note 1)20 732160 ECU(E2-4000KS) (note 1)

21 732234EEC(E1-4000KS)BUS EEC1A/DMCx(1WTx) (note 2)

22 732234EEC(E1-4000KS)BUS EEC1B/DMCx(1WTx) (note 2)



ErrorCode

ATANumber

Message

23 732234EEC(E2-4000KS)BUS EEC2A/DMCx(1WTx) (note 2)

24 732234EEC(E2-4000KS)BUS EEC2B/DMCx(1WTx) (note 2)

25 732234 EEC(E1-4000KS) (note 2)26 732234 EEC(E2-4000KS) (note 2)27 279534 FCDC1(3CE1)/DMCx(1WTx)28 279534 FCDC2(3CE2)/DMCx(1WTx)

29 228112FCU1(2CA)BUS FCU1A/DMCx(1WTx)

30 228112FCU1(2CA)BUS FCU1B/DMCx(1WTx)

31 228112 FCU1(2CA)/DMCx(1WTx)

32 228112FCU2(2CA)BUS FCU2A/DMCx(1WTx)

33 228112FCU2(2CA)BUS FCU2B/DMCx(1WTx)

34 228112 FCU2(2CA)/DMCx(1WTx)

35 228334FMGC1(1CA1)BUS FM1 TOEIS/DMCx(1WTx)

36 228334FMGC1(1CA1)BUS1 FG1/DMCx(1WTx)

37 228334 FMGC1(1CA1)

38 228334FMGC2(1CA2)BUS FM2 TOEIS/DMCx(1WTx)

39 228334FMGC2(1CA2)BUS1 FG2/DMCx(1WTx)

40 228334 FMGC2(1CA2)41 226634 FAC1(1CC1)/DMCx(1WTx)42 226634 FAC2(1CC2)/DMCx(1WTx)

43 315334FWC1(1WW1)BUSx DATA/DMCx(1WTx)

ErrorCode

ATANumber

Message

44 315334FWC1(1WW1)BUS MESSAGEx/DMCx(1WTx)

45 315334 FWC1(1WW1)FWC2(1WW2)BUS3 DATA/DMC3(1WT3) (note 7)FWC2(1WW2)BUS2 DATA/DMC1(1WT1) (note 5)

46 315334

FWC2(1WW2)BUS1 DATA/DMC2(1WT2) (note 6)

47 315334FWC2(1WW2)BUSMESSAGEx/DMCx(1WTx)

48 315334 FWC2(1WW2)49 343631 ILS1(40RT1)/DMCx(1WTx) (note 3)50 343631 MMR1(40RT1)/DMCx(1WTx) (note 4)51 343631 ILS2(40RT2)/DMCx(1WTx) (note 3)52 343631 MMR2(40RT2)/DMCx(1WTx) (note 4)53 323171 LGCIU1(5GA1)/DMCx(1WTx)54 323171 LGCIU2(5GA2)/DMCx(1WTx)55 344233 RA1(2SA1)/DMCx(1WTx)56 344233 RA2(2SA2)/DMCx(1WTx)57 315534 SDAC1(1WV1)/DMCx(1WTx)58 315534 SDAC2(1WV2)/DMCx(1WTx)59 345531 VOR1(3RS1)/DMCx(1WTx)60 345531 VOR2(3RS2)/DMCx(1WTx)

61 344133WXR1(1SQ1)/DU PFDCAPT(2WT1)/DMCx(1WTx)

62 344133WXR1(1SQ1)/DU PFDFO(2WT2)/DMCx(1WTx)

63 344133WXR1(1SQ1)/DU NDCAPT(3WT1)/DMCx(1WTx)

64 344133WXR1(1SQ1)/ DU NDFO(3WT2)/DMCx(1WTx)



ErrorCode

ATANumber

Message

65 240000 POWER SUPPLY INTERRUPT

66 316322DU PFD CAPT(2WT1)/PFD CAPT POT(7WT1)

67 316322DU ND CAPT(3WT1)/ND CAPT POT(8WT1)

68 316322DU PFD FO(2WT2)/PFD FO POT(7WT2)

69 316322DU ND FO(3WT2)/ND FO POT(8WT2)

70 316322DU EWD(4WT1)/ECP(6WT)

71 316322DU SD (4WT2)/ECP(6WT)

72 284234 FQI(3QT)BUS1/DMCx(1WTx)73 284234 FQI(3QT)74 284234 FQI(3QT)BUS2/DMCx(1WTx)

75 323171LGCIU1 FLIGHTDISCRETE (5GA1)/ DMCx(1WTx)

76 323171LGCIU2 FLIGHTDISCRETE (5GA2)/ DMCx(1WTx)

80 345331 ADF2(2RP2)/DMCx(1WTx)81 344334 TCAS(1SG)/DMCx(1WTx)

82 344133WXR1(1SQ1)/WXR2(1SQ2)/PFDCAPT(2WT1)/DMCx(1WTx)

83 344133WXR1(1SQ1)/WXR2(1SQ2)/PFD FO(2WT2)/DMCx(1WTx)

84 344133WXR1(1SQ1)/WXR2(1SQ2)/ND CAPT(3WT1)/DMCx(1WTx)

85 344133WXR1(1SQ1)/WXR2(1SQ2)/ND FO(3WT2)/DMCx(1WTx)

100 237534CIU(1RM)/DU PFD CAPT(2WT1)

ErrorCode

ATANumber

Message

101 237534CIU(1RM)/DU PFD FO(2WT2)

102 237534CIU(1RM)/DU SD(4WT2)

x =1, 2 or 3 according to DMC1, 2 or 3.

(note 1) : for CFM engines(note 2) : for IAE + PW engines(note 3) : if MMR is not installed, ILS messages take place(note 4) : if MMR is installed, MMR messages take place(note 5) : Message to be transmitted by DMC1(note 6) : Message to be transmitted by DMC2(note 7) : Message to be transmitted by DMC3



An error code corresponds to a message sent to the OMS. The list of internal error code with the associated message sent to the OMS is given hereafter:

•Software Incompatibility:

ErrorCode

ATANumber

Message Comment

201 316334 INVALID LRU IDENTLRUs have different EISsoftware part number.

202 316300MICRODISK(1WT MD1)/DMCx(1WTx)

SW A/C & HW/SWincompatibility

x =1, 2 or 3 according to DMC1, 2 or 3.



Feedback Failure:

The feedback failure message are defined as follows:

DMCx/DUx/DUy

• DMCx: DMC which transmits the feedback failure message• DUx: DU in failure• DUy: DU which detects the feedback discrepancy

• Example:• Particular Cases:

ErrorCode

ATANumber

Message Comment

316334 DMC1(1WT1)/DU ND CAPT(3WT1) DU2 checks SD image and displays at the same time the SD image204

316334 DMC1(1WT1)/DU ND FO(3WT2) DU5 checks SD image and displays at the same time the SD image

ErrorCode

ATANumber

Message

204 316334DMC1(1WT1)/DU PFD CAPT(2WT1)/DU ND FO(3WT2)



Bus Failure:• Maintenance Messages associated to a bus failure are• defined according to the following schematic:

ErrorCode

ATANumber

Message

247 316322DU PFD CAPT(2WT1)/WRG:DMCx BUS DATA TO PFDCAPT

248 316322DU ND CAPT(3WT1)/WRG:DMCx BUS DATA TO ND CAPT

249 316322DU EWD(4WT1)/WRG:DMCx BUS DATA TO EWD

250 316322DU SD(4WT2)/WRG:DMCx BUS DATA TO SD

251 316322DU PFD FO(2WT2)/WRG:DMCx BUS DATA TO PFD FO

252 316322DU ND FO(3WT2)/WRG:DMCx BUS DATA TO ND FO

x =1, 2 or 3 according to DMC1, 2 or 3

ErrorCode

ATANumber

Message

205 316234 DMC1(1WT1)/DMCy(1WTy)206 316234 DMC2(1WT2)/DMCy(1WTy)207 316234 DMC3(1WT3)/DMCy(1WTy)

235 316322DU PFD CAPT(2WT1)/DMCx(1WTx)

236 316322DU ND CAPT(3WT1)/DMCx(1WTx)

237 316322DU EWD(4WT1)/DMCx(1WTx)

238 316322DU SD(4WT2)/DMCx(1WTx)

239 316322DU ND FO(3WT2)/DMCx(1WTx)

240 316322DU PFD FO(2WT2)/DMCx(1WTx)

241 316334DMCx(1WTx)/WRG:DMCxBUS DATA TO PFD CAPT

242 316334DMCx(1WTx)/WRG:DMCx BUS DATA TO ND CAPT

243 316334DMCx(1WTx)/WRG:DMCx BUS DATA TO EWD

244 316334DMCx(1WTx)/WRG:DMCx BUS DATA TO SD

245 316334DMCx(1WTx)/WRG:DMCx BUS DATA TO ND FO

246 316334DMCx(1WTx)/WRG:DMCx BUS DATA TO PFD FO

DUx

DMCx

DUy



• Hardware Pin Programming Failure:

ErrorCode

ATANumber

Message

213 316300WRG : PIN PROG/DU EWD(2WK1)

214 316300WRG : PIN PROG/DU SD(2WK2)

215 316300WRG : PIN PROG/DU ND FO(3WK2)

216 316300WRG : PIN PROG/DU PFD FO(1WK2)

ErrorCode

ATANumber

Message

316322DU PFD CAPT(2WT1)/COOLING

316322DU ND CAPT(3WT1)/COOLING

316322DU EWD(4WT1)/COOLING

316322DU SD(4WT2)/COOLING

316322DU ND FO(3WT2)/COOLING

316322DU PFD FO(2WT2)/COOLING

316334 DMC1(1WT1)/COOLING316334 DMC2(1WT2)/COOLING

229

316334 DMC3(1WT3)/COOLING

ErrorCode

ATANumber

Message

316334 DMC1(1WT1) (note 1)316334 DMC2(1WT2) (note 1)316334 DMC3(1WT3) (note 1)316322 DU PFD CAPT(2WT1) (note 1)316322 DU ND CAPT(3WT1) (note 1)316322 DU EWD(4WT1) (note 1)316322 DU SD(4WT2) (note 1)316322 DU ND FO(3WT2) (note 1)

228

316322 DU PFD FO(2WT2) (note 1)

(note 1) : These messages mean a hardware/software incompatibility.

ErrorCode

ATANumber

Message

208 316200 WRG : PIN PROG/DMC1(1WT1)209 316200 WRG : PIN PROG/DMC2(1WT2)210 316200 WRG : PIN PROG/DMC3(1WT3)

211 316300WRG : PIN PROG/DU PFD CAPT(1WK1)

212 316300WRG : PIN PROG/DU ND CAPT(3WK1)


Hardware failure


The following table summarizes all message displayed by DU over a black screen:

Message Details Meaning

Blank screen /

- DU in OFF position- DU failure cases where the integrity of the display can no

longer be warranted- DU not powered

DISPLAY SYSTEMVERSION INCONSISTENCY

Amber messagecentered on the screen

- If an operational image and the message are displayed, the DUand an inactive DMC have different EIS software version

- If only the message is displayed, the DU and its active DMChave different EIS software version

DMC VERSION INCONSISTENCY Amber messagecentered on the screen

EIS loaded software inside the active DMC is not compatible withA/C type (DMC pin prog)

E Large white lettercentered on the screen

None operational software stored in the DU

ECAM ON ND Green messagecentered on the screen

ECAM image is displayed on ND and both ECAM DUs are valid

F Large amber lettercentered on the screen

DU is unserviceable

INVALID DATA Amber messagecentered on the screen

DU does not receive any data from a DMC

INVALID DISPLAY UNIT Amber messagecentered on the screen

- POST results not OK- DU compatibility check not OK



Message Details Meaning

L Large cyan lettercentered on the screen

DU is tele-loaded

MAINTENANCE MODE Green messagecentered on the screen

EIS system is in maintenance mode

PLEASE WAIT Green messagecentered on the screen

Displayed for 1 seconds during operational image/Video transition

SELF TEST IN PROGRESS(MAX 40 SECONDS)

Green messagecentered on the screen

DU is in power-up test (POST)

VIDEO NOT AVAIL Amber messagecentered on the screen

Video not available

WAITING FOR DATA(MAX 35 SECONDS)

Green messagecentered on the screen

DMC ARINC 629 communication is to be established



EIS– Description of THALES equipment – LCDU 725 (1)

1: Housing Assembly Module

2: Cover

A1: PPM board

A2: GPM board

A3: BLM

A4: LAM

A5: PSM board

A6: VPM board

A7: ICM

C 19268 A F 05

part number type (C for hardware part number). ordering

number

version status hardware modification status

software modification status of the resident software

PART NUMBER


EIS– Description of THALES equipment – LCDU 725 (2)

Pin Type Signal Name Pin Type Signal Name Pin Type Signal Name

1 I A453_R1_HI 29 I A629_WA_LO (spare) 52 I DSI_SPARE16

3 I VIDEO_IN 30 I PP_INE (not used) 54 I STR_GND-2 (not used)

4 O VIDEO_OUT 31 I PP_SPARE1 55 I A429_R1_HI (spare)

5 VIDEO (spare) 32 I PP_SPARE2 56 I A429_R1_LO (spare)

6 O A629_T1_HI (DU return) 33 I PP_SPARE3 57 I RS232_GND (shop test)

7 I A629_R1_shield 34 I CELL_LO 58 I A429_R2_HI (spare)

8 0 A629_T1_LO (DU return) 35 I CELL_HI 59 I A429_R2_LO (spare)

9 I A629_T1_shield 36 O BRT_REF_HI 60 I SHOP/LINE

10 I A453_R1_LO 37 I BACKGND_BRT 61 I ACCPT_TEST (shop test)

12 I A629_R1_HI (DMCM) 38 I BITMAP_BRT 62 O PSM_VAL (not used)

13 I A629_R1_LO (DMCM) 39 I GENERAL_BRT 67 I STR_GND_1 (mech gnd)

14 I A629_WA_shield (spare) 40 O BRT_REF_LO 68 O A429_DUEV_HI (not used)

17 I A629_R4_shield (spare) 41 I GND/FLIGHT 69 O A429_DUEV_LO (not used)

18 I A629_R4_HI (spare) 42 I DSI_SPARE6 70 I RS232_RX (shop test)

19 I A629_R4_LO (spare) 43 I DSI_SPARE7 71 O RS232_TX (shop test)

20 I A453_R1_shield 44 I PP_FTE (not used) 72 O DUINV (DU GO/NOGO)

22 I A629_R2_HI (DMCA1) 45 I PP0_POSI1 73 O DSO_SPARE2

23 I A629_R2_LO (DMCA1) 46 I PP1_POSI2 74 O DSO_SPARE3

24 I A629_R2_shield 47 I PP2_POSI3 75 I DUOFF

25 I A629_R3_HI (not used) 48 I PP_PARITY 77 I 115VAC_LO

26 I A629_R3_LO (not used) 49 I PP_DEV (not used) 79 I 115VAC_HI

27 I A629_R3_shield (not used) 50 I DSI_SPARE14 81 I 28VDC

28 I A629_WA_HI (spare) 51 I DSI_SPARE15

Connector pin assigment


EIS – Description of THALES equipment – DMC

DISPLAY MANAGEMENT COMPUTER

DMC were developed and are manufactured by Diehl Avionik System (formerly VDO).

1 98 266 0 10 9

part number type (1 for hardware part number).

type of unit (98 for DMC).

program number (266 for New EIS).

compatibility index between HW and SW

hardware modification status including BOOT and ADL software

checksum of the 9 first digits


EIS – Description of THALES equipment – Component location - DMC

82 VU

84 VU

86 VU

88VU

81 VU

85 VU

87 VU

DMC2

DMC3

DMC 1

A : AFT ELECTRONICS RACK 80 VU

Documents

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