Airbus A320 ATA 31 EIS Presentation

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 (DMC & DU) - Page 1 

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 Attention Getters

CAPT EFIS Control Unit

FLIGH CONTROL UNIT

F/O EFIS Control Unit

Attention Getters

ECAM PFD

ND

Upper display

ND

PFD

PFD / ND transfer push-button

ECAM


Control and Brightness Knobs for ND and PFD DUs

Lower display

Control and Brightness Knobs for ND and PFD DUs


EIS – System description (1)

EFIS

EFIS

FCU

CTL

PFD 1

ECAM 1

ND 1

ECAM 2

WARNING

CTL ENGINE WARNING ND 2

PFD 2

SYSTEM STATUS

WARNING

ECAM CP

CAUTION

CAUTION DMC 1

DMC 3

DMC 2 ATTENTION GETTERS

ATTENTION GETTERS

FWC 1

FWC 1 SDAC 1

FWC 2 SDAC 2 SDAC 1

A/C SYSTEMS SENSORS / COMPUTERS INPUT FOR : -RED WARNINGS -FLT PHASE COMPUTATION -A/C SYSTEMS SYNOPTICS

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

FWC 2

SDAC 2

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

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 (DMC & DU) - Page 4 

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)

EFIS 1

EFIS 2 FCU

PFD 1

ND 1

PFD 2

ND 2

ECAM DU 2

WXR

WXR

ECAM DU 1

WXR

DMC 1

DMC 3

DMC 2 ADC 2 IRS 2 FCU 2

ADC 1 IRS 1 FCU 1 ADC 3 IRS 3 TCAS 1

VOR 1 AND 2 FAC 1 AND 2 R/A 1 AND 2 WXR 1 AND 2 EFIS SIDE 2 ILS 1 AND 2 FMGC: 1 AND 2 DME 1 AND 2 MLS 1 AND 2 FM: 1 AND 2 ADF 1 AND 2 EFIS system centralizes and displays the necessary flight information and is therefore connected to major avionics equipment. EFIS SIDE 1


EIS – System description - EFIS Electronic Flight Instrument System (2) Attention Getters

CAPT EFIS Control Unit


PFD

FLIGH CONTROL UNIT

F/O EFIS Control Unit


INSTRUMENT PANEL

ND

Attention Getters

ND

PFD

Control and Brightness Knobs for ND DUs

Control and Brightness Knobs for PFD DUs

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 ).  EIS (DMC & DU) - Page 7 


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


EIS – System description - EFIS Electronic Flight Instrument System (5) 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). 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.

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.

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 ) bars FD 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 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:

ROSE_ILS MODE

ROSE_VOR MODE

ROSE_NAV MODE

PLAN MODE

ARC MODE  EIS (DMC & DU) - Page 13 

EIS – System description - ECAM Electronic Centralized Aircraft Monitoring (1) ECAM centralizes and displays the information related to various aircraft systems.

PFD 1

ND 1

ND 2

ECAM 1

ECAM 2

ECAM CP

DMC 1

DMC 3

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

DMC 2

FQI LGCIU EEC FCDC

1 AND 1 AND 1 AND 1 AND

2 2 2 2


PFD 2

EIS – System description - ECAM Electronic Centralized Aircraft Monitoring (2) The ECAM ( Electronic Centralised Aircraft Monitoring ) provides the information related to various aircraft systems.

UPPER ECAM

LOWER ECAM

ECAM CONTROL PANEL


EIS – System description - ECAM Electronic Centralized Aircraft Monitoring (3) 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.

SWITCHING PANEL

ECAM CONTROL PANEL


EIS – System description - ECAM Electronic Centralized Aircraft Monitoring (4)

Upper ECAM display Fuel quantity indications The numeric value of the total fuel weight on board (F.O.B.) will be permanently presented. Engine primary indications For 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 the ECAM upper Display Unit in normal configuration. At landing, a “REV” indication will appear in the N1 indicators thrust reverser cowls unlocked, or fully deployed. 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.

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


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

Lower ECAM display

Several system pages can be displayed using the ECAM control panel pushbuttons. Here two examples: engine & electrical pages.

ELECTRICAL ENGINE

PAGE

FLIGHT CONTROL

FUEL PAGE  EIS (DMC & DU) - Page 18 

EIS – System description - ECAM Electronic Centralized Aircraft Monitoring (6)

Lower ECAM display: STATUS page

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


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

DMCM

ND

EWD

DMCM

ND

PFD

SD

DMCM

DMCA1

PFD

DMCA1

SD

PFD

DMCA1

DMCM

ND

DMCM

DMCA1

EWD

DMCM

DMCM

DMCM

INVALID DATA

DMCM

DMCM

INVALID DATA

DMC 3

DMC 2

(*) assuming relay#2 is still powered

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

EFIS2

ECAM3

ECAMM (*)

EFIS3/1

DMC 1

DMC 3

DMC 2 EFIS3/1

DMC 1

EFIS2

EFIS1

ECAMM

ECAMA

(*)

3) EIS DMC switch set to CAPT 3 4) CAPT EFIS images recovery



DMC 1

DMC 3

1) Loss of EFIS F/O images

DMC 2

DMCM

DMC 1

DMC 3

DMCA1

SD

2) EIS DMC switch set to F/O 3 3) F/O EFIS images recovery


PFD

EFIS3/2

ECAMM

DMCM

ND

DMCA1

EWD

EFIS3/2

ND

DMCM

DMCM

PFD

EFIS1

SD

INVALID DATA

ECAMM

DMCM

INVALID DATA

DMCM

EWD

EFIS2

DMCM

EFIS1

DMCM

ND

DMCM

DMCM

PFD

DMC 2


DMCM

SD

PFD

DMC 1

EFIS2

ECAMM

DMCM

ND

DMCM

EWD

DMCM

DMCM

ND

EFIS1

DMCM

PFD

DMC 3

No change


DMC 2

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

INVALID DATA

DMCM

PFD

ND

DMCA1

INVALID DATA

INVALID DATA

DMCA1

DMCM

INVALID DATA

DMCM

DMCM

DMCM

INVALID DATA

DMCM

DMCM

INVALID DATA

INVALID DATA

EWD

DMCM

INVALID DATA

SD

DMC 3

DMC 2

(*) assuming relay#2 is still powered

1) Loss of all images

ECAM3

ECAMM (*)

EFIS3/1

DMC 1

DMC 3

DMC 2 EFIS3/1

DMC 1

EFIS2

EFIS1

ECAMM

ECAM images can be transmitted by DMC2

2) EIS DMC switch set to CAPT 3 3) CAPT EFIS & ECAM images recovery



SD

DMC 3

EFIS2

ECAMM

DMC 1

DMCA1

PFD

ECAMA

DMCM

ND

DMCM

DMCM

EFIS1

DMCM

DMCA1

EWD

INVALID DATA

DMCM

DMCM INVALID DATA

DMC 2

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



DMCM

SD

DMC 1

INVALID DATA

EFIS2

ECAMM

DMCM

INVALID DATA

DMCM

EWD

DMCM

DMCM

ND

EFIS1

DMCM

PFD

DMC 3

Loss of F/O images


DMC 2

EIS – System description - System reconfiguration – DU normal operation

DMCM

SD

PFD

DMC 1

EFIS2

ECAMM

DMCM

ND

DMCM

EWD

DMCM

DMCM

PFD

EFIS1

DMCM

ND

DMC 3

DMC 2

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 (DMC & DU) - Page 28 

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

DMC 1

DMC 2

1) ND DU automatically displays the PFD image

DMCM

SD

PFD

DMCM

DMCM

ND

DMCM

EWD

DMC 1

EFIS2

ECAMM

EFIS2

DMC 3

PFD or ND

INVALID DISPLAY UNIT

EFIS1

SD

PFD

ECAMM

DMCM

ND

DMCM

EWD

DMCM

DMCM

EFIS1

DMCM

PFD

DMCM

DMCM


DMC 3

DMC 2

2) Action on PFD/ND transfer pushbutton switch to recover ND image on ND DU


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

DMC 1

DMC 3

1) No change on PFD DU

DMC 2

DMCM

EWD

SD

PFD

DMCM

DMCM

ND

DMCM


DMC 1

EFIS2

ECAMM

DMCM

PFD or ND

EFIS1

SD

PFD

ECAMM

DMCM

ND

DMCM

EWD

EFIS2

DMCM

EFIS1

DMCM

DMCM

DMCM


PFD

DMC 3

DMC 2

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

DMCM

EWD

DMCM

SD

PFD

DMC 1

EFIS2

ECAMM

DMCM

ND

DMCM

DMCM


EFIS1

DMCM


DMC 3

Loss of EFIS images on CAPT side


DMC 2

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

DMC 1

DMC 3

DMC 2

1) DU 4 automatically displays the EWD image 2) SD pages can still be displayed on the DU4 by momentary action on the ECAM control panel


DMCM

EWD

PFD

DMC 1

EFIS2

ECAMM

DMCM

ND

DMCM

SD

DMCM

DMCM

PFD or ND

EFIS1

PFD

DMCM

EWD or SD

ND

ECAMM

DMCM


EFIS2

DMCM

EFIS1

DMCM

ND

DMCM

DMCM

PFD

DMC 3

DMC 2

3) ECAM/ND XFR switch set to CAPT 4) SD image recovery on DU2 5) Action on PFD/ND XFR pushbutton switch to have PFD changed into ND


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

DMC 1

DMC 3

DMC 2

1) DU4 automatically displays the EWD image 2) SD pages can still be displayed on the DU4 by momentary action on the ECAM control panel


DMC 1

DMCA1

DMCM

EWD

DMCM

DMC 3

EFIS2

DMCM

PFD or ND

SD

ECAMA

DMCM

ND

ECAMM

DMCM

PFD

EFIS1

PFD

DMCM

EWD or SD

ND

ECAMM

DMCM


EFIS2

DMCM

EFIS1

DMCM

ND

DMCM

DMCM

PFD

DMC 2

3) ECAM/ND XFR switch set to F/O 4) SD image recovery on DU5 5) Action on PFD/ND XFR pushbutton switch to have PFD changed into ND


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

DMC 1

DMC 3

1) Loss of SD image 2) SD pages can still be displayed on the DU3 by momentary action on the ECAM control panel

DMC 2

DMCM


ND

PFD

DMCM

EWD

DMCM

DMCM

SD

DMC 1

EFIS2

ECAMM

DMCM

PFD or ND

EFIS1

PFD

DMCM


ND

ECAMM

DMCM

EWD or SD

EFIS2

DMCM

EFIS1

DMCM

ND

DMCM

DMCM

PFD

DMC 3

3) ECAM/ND XFR switch set to CAPT 4) SD image recovery on DU2 5) Action on PFD/ND XFR pushbutton switch to have PFD changed into ND


DMC 2

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

DMC 1

DMC 3

1) Loss of SD image 2) SD pages can still be displayed on the DU3 by momentary action on the ECAM control panel

DMC 2

DMCM EFIS2

ECAMM

DMC 3

3) ECAM/ND XFR switch set to F/O 4) SD image recovery on DU5 5) Action on PFD/ND XFR pushbutton switch to have PFD changed into ND


SD

ECAMA


DMC 1

PFD or ND

DMCA1

EWD

DMCM

ND

DMCM

DMCM

PFD

EFIS1

PFD

DMCM


DMCM

ND

ECAMM

DMCM

EWD or SD

EFIS2

DMCM

EFIS1

DMCM

ND

DMCM

DMCM

PFD

DMC 2

DMC 1

DMC 3

1) Loss of ECAM image

DMC 2

DMCM


ND

PFD

DMCM

DMCM


EFIS2

EWD or SD

PFD

DMCM

PFD or ND

EFIS1


ND

ECAMM

DMCM


DMCM

DMCM

EFIS1

DMCM

ND

DMCM

DMCM

PFD

EFIS2

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

DMC 1

DMC 3

2) ECAM/ND XFR switch set to CAPT 3) EWD image recovery on DU2 2) SD pages can still be displayed on the DU2 by momentary action on the ECAM control panel 4) Action on PFD/ND XFR pushbutton switch to have PFD changed into ND  EIS (DMC & DU) - Page 36 

DMC 2

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

DMC 1

DMC 3

1) Loss of ECAM image

DMC 2

PFD or ND

EFIS2


EWD or SD

DMCM


DMCM

ND

DMCM

DMCM

PFD

EFIS1

PFD

DMCM


ND

ECAMM

DMCM


EFIS2

DMCM

EFIS1

DMCM

ND

DMCM

DMCM

PFD

DMC 1

DMC 3

DMC 2

2) ECAM/ND XFR switch set to F/O 3) EWD image recovery on DU5 2) SD pages can still be displayed on the DU5 by momentary action on the ECAM control panel 4) Action on PFD/ND XFR pushbutton switch to have PFD changed into ND  EIS (DMC & DU) - Page 37 

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).

LRU Name

FAC

FMGC

FCU

Input Bus Name FAC1 FAC2 FGC1 FGC2 FM1 FM2 EFIS1-1 EFIS1-2 EFIS2-1 EFIS2-2

Wired to DMC number

Processed by DMC number

1

2

3

1

2

3

3/1

3/2

X X X X X X X X

X X X X X X

X X X X X X X X X X

N R X X N R X X

R N X X R N

N R X X N R X X

N R X X N R X X

R N X X R N

X X

X X

Processed by DMC3 when transfer

X X

Remarks Automatic selection, according to FAC validity and AIR DATA switching

R, if onside FMGC FM part has failed Selection of FCU processor 2 in case of failure of processor 1


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

LRU Name

ADIRU

VOR ILS RA DME ADF

Input Bus Name IRS1 IRS2 IRS3 ADC1 ADC2 ADC3 VOR1 VOR2 ILS1 ILS2 RA1 RA2 DME1 DME2 ADF1 ADF2

ECAM CTL PNL FQIU CFDIU

FQIU1-1 FQIU1-2 FQIU2-1 FQIU2-2

Wired to DMC number


1

2

3

1

2

3

3/1

X X X X X X X X X X X X X X X X



N F R N F R X X X X X X X X X X

F N R F N R X X X X X X X X X X

N

N

R X X X X X X X X X X

R X X X X X X X X X X

N R X X X X X X X X X X

X

X

X

X

X

X

X

X

X

X

X

X

X

X X

X X

X X

X X

R N

N R

X X X

X X

X

X X

Remarks

3/2

X

X X

R N


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

ILS1 -> PFD1 & ND2 ILS2 -> PFD2 & ND1

(ADF2 optional)

R, when the channel superiority signal controls the change over to the other bus or when the normal bus becomes faulty


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

LRU Name

WXR (A453)

FWC (A429)

FWC (RS422)

SDAC

ECU or EEC

Input Bus Name WXR1-1 WXR1-2 WXR2-1 WXR2-2 FWC1-1 FWC1-2 FWC1-3 FWC2-1 FWC2-2 FWC2-3 FWC1-1 FWC1-2 FWC1-3 FWC2-1 FWC2-2 FWC2-3 SDAC1 SDAC2 1-A1 1-A2 1-B1 1-B2 2-A1 2-A2 2-B1 2-B2

Wired to DMC number


1

2

3

1

2

3

3/1

X X X X X

X X X X

X X X X

N N R R X

N N R R

N N R R

N

X

X

X

X

X

X

N

N

N

R X X X

R X X X

R X X X

X X

X X

X X

X

X

X

X X

R N R

X X

X

N X

N X

X

R X X X

R, when FWC1-X bus is seen faulty

R X X X X

X X

X X X X

X X

X X

3/2

X X

X

Remarks

X X

X X X


X X

(ADF2 optional)

X X

X X

X

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 (DMC & DU) - Page 41 

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 MASTER CAUTION SINGLE CHIME

UPPPER ECAM DU EIS DMC 1 FAULT - EIS DMC SWITCH………..CAPT

LOWER ECAM DU STATUS (a) (c)

INOP SYS DMC 1

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

Flight phases ? 


(w) (a)

EIS – System description - ECAM warnings DMC 2 FAULT DMC 2 FAULT detected by FWC Local warning MASTER CAUTION

UPPPER ECAM DU

LOWER ECAM DU STATUS

SINGLE CHIME EIS DMC 2 FAULT - EIS DMC SWITCH………….F/O

(a) (c)

INOP SYS DMC 2


Flight phases ? 


(w) (a)

EIS – System description - ECAM warnings DMC 3 FAULT DMC 3 FAULT detected by FWC Local warning MASTER CAUTION SINGLE CHIME

UPPPER ECAM DU EIS DMC 3 FAULT

LOWER ECAM DU STATUS (a)

INOP SYS DMC 3


Flight phases ? 


(w) (a)

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 (DMC & DU) - Page 46 

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 EIS/ND CAPT/SPLY 12WT1 EIS/ND CAPT/SWTG 23WT1 EIS/PFD CAPT/SPLY 11WT1 EIS/PFD CAPT/SWTG 22WT1 EIS/ECAM DU/UPPER/SPLY 13WT1 EIS/ECAM DU/UPPER/SWTG 24WT1 EIS/DMC3/SWTG 21WT3 EIS/DMC1/SWTG 21WT1 EIS/DMC3/STBY/SPLY 14WT1 EIS/DMC1/SPLY 10WT1 EIS/ECAM/CTL/PNL 15WT Circuit Breakers fitted on 121VU (behind F/O seat) Designation Identifier EIS/DMC2/SPLY 10WT2 EIS/DMC3/SPLY 10WT3 EIS/PFD/F/O 11WT2 EIS/ND/F/O 12WT2 EIS/PFD/F/O/SWTG 22WT2 EIS/ND/F/O/SWTG 23WT2 EIS/DMC2/SWTG 21WT2 EIS/ECAM DU/LOWER/SWTG 24WT2 EIS/ECAM DU/LOWER/SPLY 13WT2


Location E01 E02 E03 E04 E05 E06 E07 E09 E10 E11 E12 Location Q08 Q09 R03 R04 R05 R06 R08 R10 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.



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. 5 : after correct completion of theses checks, DUs display an operational image. The duration of these tests is equal to 40 seconds for the LCDU and 35 seconds for the DMC.


EIS – On Board maintenance – BITE (DMC and DU) – Power On (3/4) 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.


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.

F

If 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



INVALID DATA

In 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.

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).


EIS – On Board maintenance (1) 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/

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

DMC

Data-loader

another DMC


DU

Active DMC

EIS – On Board maintenance (2) The following figure gives examples of the 3 different tele-loading sub-functions. For the DU cross-loading subfunction, 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).


EIS – On Board maintenance (3)


EIS – On Board maintenance (4) 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 crossloading 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).


EIS – On Board maintenance (7) 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.

DMC L A S T

1L

L E G

C L A S S

< R E POR T P R E V I O U S

MAINTENANCE MODE

1

2L

< R E POR T

3L

< L RU

3

FAUL T > L E G S

1R

S Y S T E M

TEST >

2R 3R

I DENT SW T G / B U S / D U

4L

< GND

S C A NN I NG

T R O U B L E

5L

< DATA

6L

< RE T URN

TESTS >

S H OO T

G R O U N D

RE POR T > P I N

5R

P R OG / S T A T U S

AND

MCDU Display  EIS (DMC & DU) - Page 61 

4R

X LOAD >

6R

EIS – On Board maintenance (8) Once in the DMC Main Menu, the operator can access the following sub-menus: DMC Main Menu

Have a look on the MCDU simulator 

1L

2L

Last Leg Report Previous Legs Report

5L

Trouble Shoot Data

4R

2L 1R

Class 3 faults

Data Bus Test 6R

3L

4L

LRU Identification

Ground Scanning

SWTG/B US/DU Test

2R

5R

System Test

Ground Report

3L Switching Test

Pin Prog Status & Xload 2L DMC Load 5L LCD Status


3L DU Load

2R Pin Prog

4L DU Brightness Test

4L Backlighting Status 3R Engines

EIS – On Board maintenance (9) 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.


EIS – On Board maintenance (10) 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.

DMC

DMC

1

DMC DMC

ACCESS

X LOAD >

E I S

P N R

SW

SXT 3E - E2SA - 0 4 0 0

D MC 1 : X L O A D

X L O A D

D MC 2 : D MC 3 :

< RE T URN

X L O A D

ACCESS

X LOAD >

E I S

P N R

T O

SXT 3E - E2SA - 0 4 0 0

D MC 2 :

X L O A D

SXT 3 8 - E2SA - 0 3 0 1

D MC 3 :

E M P T Y

PR I NT *

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.

SW

SXT 3E - E2SA - 0 4 0 0

D MC 1 : X L O A D

T O

1

< RE T URN

N O T

A V A I

L

PR I NT *

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



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

DMC

X L O A D

E I S

SW

D MC 2 :

SXT 3E - E2SA - 0 4 0 0

D MC 3 :

X L O A D

DMC

X L O A D

< RE T URN

N O T

X L O A D

A V A I

L

A L L OW E D

PR I NT *

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

SW

P N R

SXT 3E - E2SA - 0 4 0 0

D MC 1 : X L O A D

T O

N O T

1

E I S

P N R

SXT 3E - E2SA - 0 4 0 0

D MC 1 : X L O A D

DMC

1

T O

D MC 2 :

E M P T Y

D MC 3 :

SXT 3 8 - E2SA - 0 3 0 1

< ST ART

X L OAD

< RE T URN

PR I NT *

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


EIS – On Board maintenance (12) 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.

DMC DMC

1

X L O A D

T R A N S F E R

I N

P R OG R E S S

DMC 1

T O

DMC 2

DMC 1

T O

DMC 3

DMC DMC

1

X L O A D

I N T E G R I T Y MA X

10

M I N U T E S

C H E C K

DMC 2 DMC 3

0 0%

M A X


15

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.

DMC DMC

1

DMC

X L O A D

DMC

D MC 2 :

X L O A D

C OM P L E T E D

D MC 3 :

X L O A D

A B O R T E D

DMC I N

S E L F

P R OG R E S S

RE T URN

1

X L O A D

D MC 2 :

X L O A D

C OMP L E T E D

D MC 3 :

X L O A D

A B O R T E D

T E S T ( 3 5 s )

PR I NT *

< RE T URN


PR I NT *

EIS – On Board maintenance (14) 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. DMC D U

P F D N D

N D

ACCESS

X LOAD >

E I S

P N R

SW

T O

C A P T : C A P T

P F D

X L O A D

SXT 3E - E2SA - 0 4 0 0

D MC 1 : X L O A D

1

F / O F / O

:

SXT 3E - E2SA - 0 4 0 0 SXT 3E - E2SA - 0 4 0 0

: X L O A D

N O T

A V A I

L

: E M P T Y

E WD

:

SXT 3E - E2SA - 0 4 0 0

S D

:

SXT 3 8 - E2SA - 0 3 0 1

< RE T URN

PR I NT *

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.


EIS – On Board maintenance (15) By pressing the 1R key (ACCESS XLOAD) of the previous page and according to EIS system status, the following pages can be displayed:

DMC D U

DMC

1

D U

X L O A D

I N I T I A L - S E T D U

X L O A D

N O T

T O

A L L OW E D

PR I NT *

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).

X L O A D

C O N D I T I O N S :

T H E

E I S

DMC

S E L

NO RM

< START < RE T URN

1

< RE T URN

X LOAD PR I NT *

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).


EIS – On Board maintenance (16) For DMC3, a menu is displayed to select DUs to be cross-loaded, then the following described initial conditions (1 page) are displayed: DMC DU

3

X L OA D

1L

DMC DU

3

2L

1R

- S E T T O

CA P T

E I S

DMC

S E L

4L

4R

< RE T URN

X L OA D

T O

3L

< EF I S

FO DU

AND

E CAM DU

2R 3R

4L

4R

5L

5R

6L

< RE T URN

3

3R

6L

CAPT

2R

3L

< START

T O

< EF I S

COND I T I ONS :

T HE

5L

X L OA D

2L

X L OA D

1L I N I T I A L

1R

5R

X LOAD PR I NT *

6R DMC DU

3

X L OA D

1L

1R I N I T I A L

2L

- S E T T O

COND I T I ONS :

T HE F O

E I S

DMC

S E L

2R

3

3L

3R

4L

4R

5L

< START

6L

< RE T URN

5R

X LOAD PR I NT *


6R

PR I NT *

6R

EIS – On Board maintenance (17) 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.

DMC DU

1L

DMC

X L OA D

T R A NS F E R

2L

1

I N

1R

DMC 1

T O

P F D

DMC 1

T O

ND

CA P T

5L

6L

DMC 1

T O

EWD

DMC 1

T O

S D

MA X

10

M I NU T E S

0 0%

DU

X L OA D

I N T EGR I T Y

2R

2L

C A P T

3L

4L

1L

P ROGRE S S

1

P F D ND

3R

3L

4R

4L

5R

5L

6R

6L

CH E C K

C A P T C A P T

EWD


S D

MA 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.

DMC DU

1L

2L

P F D N D

1

X L OAD

CA P T : X L OAD CAP T

DMC

: X L OAD

COMP L E T E D

E WD

: X L OAD

COMP L E T E D

S D

: X L OAD

COMP L E T E D

DU

5L

6L

I N

S E L F

PROGRE S S

RE T URN

1L

2R

2L

A BORT ED

3L

4L

1R

DU

P F D N D

3R

3L

4R

4L

5R

5L

6R

6L

1

X L OAD

CA P T : X L OAD CAP T

: X L OAD

1R

COMP L E T E D

2R

A BORT ED

3R E WD

: X L OAD

COMP L E T E D

S D

: X L OAD

COMP L E T E D

4R

T E S T ( 4 0 s )

PR I NT *


5R

< RE T URN

PR I NT *

6R

EIS – On Board maintenance (19) For DMC3, by pressing the RETURN key from the previous page, the following page is displayed:

DMC D U

X L O A D

C L O S E

- S E T T O

T H E

3

E I S

U P

DMC

S E L

N O RM

< RE T URN

PR I NT *


EIS – On Board maintenance (20) 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). DMC DU

1L

I N I T I A L

2L

- MA K E ARE

3L

- S E T TO

1

DMC

B ACK L I GHT

S T A T US

6L

1L

2R

2L

3R

3L

4R

4L

5R

5L

6R

6L

COND I T I ONS :

SURE

T HA T

A L L

ON T HE

ARE E I S

DMC

S E L

NORM

< ACCESS < RE T URN

- MA K E

- S E T TO

TEST PR I NT *

DMC1

2

B ACK L I GHT

I N I T I A L DU

4L

5L

1R

DU

S T A T US

COND I T I ONS :

SURE

T HA T

A L L

DU

2R

ON T HE

E I S

DMC

S E L

3R

NORM

4R

< ACCESS < RE T URN

5R

TEST PR I NT *

DMC2  EIS (DMC & DU) - Page 74 

1R

6R

EIS – On Board maintenance (21) 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). DMC DU

3

B A C K L I GH T

S T A T U S

1L

DMC DU

3

B A C K L I GH T

2L

1R

- MA K E A R E

3L

- S E T T O

2L

< EF I S

CAPT

3L

< EF I S

FO

T H A T

CA P T

E I S

DMC

A L L

DU

S E L

5R

6L

< RE T URN

2R 3R 4R

< ACCESS

6L

< RE T URN

3R

DU

5L

3

4L 5L

2R

4R

ON T H E

E CAM DU

4L

COND I T I ONS :

S UR E

AND

S T A T U S

1L I N I T I A L

1R

5R

TEST PR I NT *

6R DMC DU

3

B A C K L I GH T

S T A T U S

1L

1R I N I T I A L

2L

- MA K E A R E

3L

- S E T T O

COND I T I ONS :

S UR E

T H A T

A L L

DU

2R

ON T H E F O

E I S

DMC

S E L

3R

3

4L

4R

5L

< ACCESS

6L

< RE T URN

5R

TEST PR I NT *


6R

PR I NT *

6R

EIS – On Board maintenance (22) 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.

DMC D U

< PFD < ND

1

B A C K L I G H T

CAPT CAPT

< E / WD

< RE T URN

S T A T U S

PFD

F /O

ND

F /O SD >

PR I NT *


EIS – On Board maintenance (23) From the previous menu, by selection of the DU, the following pages may be displayed: DMC D U

1

B A C K L I G H T

1L

DMC S T A T U S

D U

1

B A C K L I G H T

S T A T U S

1R

1L

2R

2L

3R

3L

4L

4R

4L

4R

5L

5R

5L

5R

6R

6L

P F D

F O

NO T

P O S S I B L E

2L S T A T U S

3L

6L

F ROM

< RE T URN

DMC 1

PR I NT *

P F D

S T A T U S

( P F D

< RE T URN

If selected DU is not associated to the active DMC

DMC

1

B A C K L I G H T

1L

P F D

T E S T

I N

S T A T U S

1R

C A P T

P R OG R E S S

5 s

2R

3L

3R

4L

4R

5L

5R

6L

N O T

A V A I L A B L E

U N S E R V I C E A B L E )

PR I NT *

If selected DU is failed

D U

2L

C A P T

1R

C A P T

< RE T URN

PR I NT *

6R

If selected DU is associated to the active DMC and is not failed  EIS (DMC & DU) - Page 77 

2R 3R

6R

EIS – On Board maintenance (24) 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.

DMC 1L

DU

1

B ACK L I GH T P F D

1 / 2 S T A T US

1L

DU

2R L AMP

1 : OK

L AMP

6 : OK

L AMP

2 : OK

L AMP

7 : OK

L AMP

3 : OK

L AMP

8 : OK

L AMP

4 : OK

L AMP

9 : OK

L AMP

5 : OK

L AMP 1 0 : OK

3R

5L

< RE T URN

PR I NT *

1

B ACK L I GH T P F D

3L

6L

1R

CA P T

2L

4L

DMC

2 / 2 S T A T US

2L

2R L AMP 1 1 : OK

L AMP 1 6 : OK

L AMP 1 2 : OK

L AMP 1 7 : OK

L AMP 1 3 : OK

L AMP 1 8 : OK

L AMP 1 4 : OK

L AMP 1 9 : OK

L AMP 1 5 : OK

L AMP 2 0 : F A I L

3L

4R

4L

5R

5L

6R

6L

Next Page


1R

CA P T

3R

4R

5R

< RE T URN

PR I NT *

6R

EIS – On Board maintenance (25) For DMC3, by pressing the RETURN key on one of the previous page the following page is displayed:

DMC DU

B A C K L I GH T C L OS E

- S E T T O

3

T H E

E I S

S T A T U S U P

DMC

S E L

NORM

< RE T URN

PR I NT *


EIS – On Board maintenance (26) 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.

DMC L C D

1

DMC

S T A T U S

D I S P L A Y

T E S T

1

D I S P L A Y

T E S T

2

L CD

T E S T D I S P L A Y

< RE T URN

T E S T

NOT

1

S T A T US

A V A I L A B L E

3

PR I NT *

< RE T URN

PR I NT *

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


EIS – On Board maintenance (27) 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. Have a look on the MCDU simulator 

DMC L C D

D I S P L A Y I N

1

S T A T U S

T E S T

1

P ROGR E S S

PNR: C19298AF05 SER: C19298000234 EIS SW PNR: SXT3E-E2SA-0400

< RE T URN

PR I NT *


THALES AVIONICS

LCDU 725

EIS – On Board maintenance (28) 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.

DMC L CD

S T A T U S

D I S P L A Y I N

< RE T URN

1

T E S T

2

P ROGR E S S

PR I NT *


EIS – On Board maintenance (29) 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.

DMC L C D

S T A T U S

D I S P L A Y I N

< RE T URN

1

T E S T

3

P ROGR E S S

PR I NT *


EIS – On Board maintenance (30) 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.

DMC P I N

1 P ROG

< HARD

P I N

P ROG

< SOF T

P I N

P ROG

< RE T URN

PR I NT *


EIS – On Board maintenance (31) 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. DMC H A R D

P I N

1 P R OG

< DMC 1

< D U

P F D

< D U

N D

< D U

P F D

< RE T URN

C A P T

C A P T

F / O

D U

N D

D U

F / O

E / WD

D U

S D >

PR I NT *

D U

N D

DMC

1

F / O

H A R D

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

< RE T URN

P P

PR I NT *

When a PP status is unknown a dash is displayed.  EIS (DMC & DU) - Page 85 

EIS – On Board maintenance (32) 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.

DMC S O F T

P I N

1

S O F T

P ROG

G L S O P T I O N

0

S T A I R S DOO R 1

M L S O P T I O N

1

B U L K DOOR

M MR I N S T

0

C T R T A N K

1 0

A P P T Y P E

1

P R E DWS

0

M OR A

1

GN D COO L

0

F WD CGOH E A T 1

0

A F T CGOH E A T 1

0

F WD CGO V E N T 1

0

A F T CGO V E N T 0

1

< RE T URN

DMC

1 / 1 4

Boolean software program pins

1

7 / 1 4 P ROG

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

< RE T URN

PR I NT *

P I N

PR I NT *

Numeric software program pins


EIS – On Board maintenance (33) 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.

DMC E N G I N E S

O V E R

1 S P E E D / T E M P

N1E2 >

N2E2 >

< EGT E 1 < GENERA L

< RE T URN

EGT E 2 > RESET

PR I NT *



DMC E NG I N E S

N1 N1E1

O V E R

RED MA X

1

DMC

S P E E D / T E MP

L I NE = 1 0 4 . 0% REACHED =

< RE T URN

107 . 5 %

PR I NT *

If the maximum speed reached is over the red line value

DMC E NG I N E S

EGT 1

RED

EGT 1

O V E R

N1

RED

N1E1

=

OVERSPEED

< RE T URN

PR I NT *

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

DM C

S P E E D / T E MP

L I NE

S P E E D / T E MP

L I NE = 1 0 4 . 0% NO

1

O V E R

MA X

E NG I N E S

1

=

910 . 0 °C

REACHED

=

E N G I N E S

E GT 1

O V E R

RED

EGT 1

L I NE

=

1 S P E E D / T E M P

=

910 . 0 °C

NO O V E R T EMP

930 . 0 °C

< RE T URN

PR I NT *

If the maximum temperature reached is over the red line value

< RE T URN

PR I NT *

If the maximum temperature reached is not over the red line value  EIS (DMC & DU) - Page 88 

EIS – On Board maintenance (35) 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: Error Code 1

ATA Number 345331

2

341234

3

341234

4

341234

5

6

7

8

341234

341234

341234

341234

Error Code

Message ADF1(2RP1)/DMCx(1WTx) ADIRU1(1FP1) BUSx ADR/ DMCx(1WTx) ADIRU1(1FP1) BUSx IR/ DMCx(1WTx) ADIRU1(1FP1) ADIRU2(1FP2)BUS2 ADR/ DMC1(1WT1) (note 5) ADIRU2(1FP2)BUS1 ADR/ DMC2(1WT2) (note 6) ADIRU2(1FP2)BUS3 ADR/ DMC3(1WT3) (note 7) ADIRU2(1FP2)BUS2 IR/ DMC1(1WT1) (note 5) ADIRU2(1FP2)BUS1 IR/ DMC2(1WT2) (note 6) ADIRU2(1FP2)BUS3 IR/ DMC3(1WT3) (note 7) ADIRU2(1FP2) ADIRU3(1FP3)BUS3 ADR/ DMC1(1WT1) (note 5) ADIRU3(1FP3)BUS2 ADR/ DMC2(1WT2) (note 6) ADIRU3(1FP3)BUS1 ADR/ DMC3(1WT3) (note 7)

ATA Number

9

341234

10 11 12 13 14

341234 313234 345133 345133 316112

15

732160

16

732160

17

732160

18

732160

19 20

732160 732160

21

732234

22

732234

Message ADIRU3(1FP3)BUS3 IR/ DMC1(1WT1) (note 5) ADIRU3(1FP3)BUS2 IR/ DMC2(1WT2) (note 6) ADIRU3(1FP3)BUS1 IR/ DMC3(1WT3) (note 7) ADIRU3(1FP3) CFDIU(1TW1)/DMCx(1WTx) DME1(2SD1)/DMCx(1WTx) DME2(2SD2)/DMCx(1WTx) ECP (6WT)/DMCx(1WTx) ECU(E1-4000KS)BUS ECU1A/ DMCx(1WTx) (note 1) ECU(E1-4000KS)BUS ECU1B/ DMCx(1WTx) (note 1) ECU(E2-4000KS)BUS ECU2A/ DMCx(1WTx) (note 1) ECU(E2-4000KS)BUS ECU2B/ DMCx(1WTx) (note 1) ECU(E1-4000KS) (note 1) ECU(E2-4000KS) (note 1) EEC(E1-4000KS)BUS EEC1A/ DMCx(1WTx) (note 2) EEC(E1-4000KS)BUS EEC1B/ DMCx(1WTx) (note 2)


EIS – On Board maintenance (36) Error Code

ATA Number

23

732234

24

732234

25 26 27 28

732234 732234 279534 279534

29

228112

30

228112

31

228112

32

228112

33

228112

34

228112

35

228334

36

228334

37

228334

38

228334

39

228334

40 41 42

228334 226634 226634

43

315334

Message EEC(E2-4000KS)BUS EEC2A/ DMCx(1WTx) (note 2) EEC(E2-4000KS)BUS EEC2B/ DMCx(1WTx) (note 2) EEC(E1-4000KS) (note 2) EEC(E2-4000KS) (note 2) FCDC1(3CE1)/DMCx(1WTx) FCDC2(3CE2)/DMCx(1WTx) FCU1(2CA)BUS FCU1A/ DMCx(1WTx) FCU1(2CA)BUS FCU1B/ DMCx(1WTx) FCU1(2CA)/DMCx(1WTx) FCU2(2CA)BUS FCU2A/ DMCx(1WTx) FCU2(2CA)BUS FCU2B/ DMCx(1WTx) FCU2(2CA)/DMCx(1WTx) FMGC1(1CA1)BUS FM1 TO EIS/DMCx(1WTx) FMGC1(1CA1)BUS1 FG1/ DMCx(1WTx) FMGC1(1CA1) FMGC2(1CA2)BUS FM2 TO EIS/DMCx(1WTx) FMGC2(1CA2)BUS1 FG2/ DMCx(1WTx) FMGC2(1CA2) FAC1(1CC1)/DMCx(1WTx) FAC2(1CC2)/DMCx(1WTx) FWC1(1WW1)BUSx DATA/ DMCx(1WTx)

Error Code

ATA Number

44

315334

45

315334

46

315334

47

315334

48 49 50 51 52 53 54 55 56 57 58 59 60

315334 343631 343631 343631 343631 323171 323171 344233 344233 315534 315534 345531 345531

61

344133

62

344133

63

344133

64

344133


Message FWC1(1WW1)BUS MESSAGEx/ DMCx(1WTx) FWC1(1WW1) FWC2(1WW2)BUS3 DATA/ DMC3(1WT3) (note 7) FWC2(1WW2)BUS2 DATA/ DMC1(1WT1) (note 5) FWC2(1WW2)BUS1 DATA/ DMC2(1WT2) (note 6) FWC2(1WW2)BUS MESSAGEx/DMCx(1WTx) FWC2(1WW2) ILS1(40RT1)/DMCx(1WTx) (note 3) MMR1(40RT1)/DMCx(1WTx) (note 4) ILS2(40RT2)/DMCx(1WTx) (note 3) MMR2(40RT2)/DMCx(1WTx) (note 4) LGCIU1(5GA1)/DMCx(1WTx) LGCIU2(5GA2)/DMCx(1WTx) RA1(2SA1)/DMCx(1WTx) RA2(2SA2)/DMCx(1WTx) SDAC1(1WV1)/DMCx(1WTx) SDAC2(1WV2)/DMCx(1WTx) VOR1(3RS1)/DMCx(1WTx) VOR2(3RS2)/DMCx(1WTx) WXR1(1SQ1)/DU PFD CAPT(2WT1)/DMCx(1WTx) WXR1(1SQ1)/DU PFD FO(2WT2)/DMCx(1WTx) WXR1(1SQ1)/DU ND CAPT(3WT1)/DMCx(1WTx) WXR1(1SQ1)/ DU ND FO(3WT2)/DMCx(1WTx)

EIS – On Board maintenance (37) Error Code 65

ATA Number 240000

66

316322

67

316322

68

316322

69

316322

70

316322

71

316322

72 73 74

284234 284234 284234

75

323171

76

323171

80 81

345331 344334

82

344133

83

344133

84

344133

85

344133

100

237534

Message POWER SUPPLY INTERRUPT DU PFD CAPT(2WT1)/ PFD CAPT POT(7WT1) DU ND CAPT(3WT1)/ ND CAPT POT(8WT1) DU PFD FO(2WT2)/ PFD FO POT(7WT2) DU ND FO(3WT2)/ ND FO POT(8WT2) DU EWD(4WT1)/ ECP(6WT) DU SD (4WT2)/ ECP(6WT) FQI(3QT)BUS1/DMCx(1WTx) FQI(3QT) FQI(3QT)BUS2/DMCx(1WTx) LGCIU1 FLIGHT DISCRETE (5GA1)/ DMCx(1WTx) LGCIU2 FLIGHT DISCRETE (5GA2)/ DMCx(1WTx) ADF2(2RP2)/DMCx(1WTx) TCAS(1SG)/DMCx(1WTx) WXR1(1SQ1)/WXR2(1SQ2)/ PFDCAPT(2WT1)/DMCx(1WTx) WXR1(1SQ1)/WXR2(1SQ2)/ PFD FO(2WT2)/DMCx(1WTx) WXR1(1SQ1)/WXR2(1SQ2)/ ND CAPT(3WT1)/DMCx(1WTx) WXR1(1SQ1)/WXR2(1SQ2)/ ND FO(3WT2)/DMCx(1WTx) CIU(1RM)/ DU PFD CAPT(2WT1)

Error Code

ATA Number

101

237534

102

237534

Message CIU(1RM)/ DU PFD FO(2WT2) CIU(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


EIS – On Board maintenance (38) 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:

Error Code

ATA Number

Message

Comment

201

316334

INVALID LRU IDENT

LRUs have different EIS software part number.

202

316300

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

SW A/C & HW/SW incompatibility

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:

Error Code 204

ATA Number 316334 316334

Error Code

ATA Number

Message

204

316334

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

Message

Comment

DMC1(1WT1)/DU ND CAPT(3WT1) DMC1(1WT1)/DU ND FO(3WT2)

DU2 checks SD image and displays at the same time the SD image DU5 checks SD image and displays at the same time the SD image


EIS – On Board maintenance (40) Bus Failure: • Maintenance Messages associated to a bus failure are • defined according to the following schematic: Error Code 205 206 207

ATA Number 316234 316234 316234

235

316322

236

316322

237

316322

238

316322

239

316322

240

316322

241

316334

242

316334

243

316334

244

316334

245

316334

246

316334

DUx

DUy

Message DMC1(1WT1)/DMCy(1WTy) DMC2(1WT2)/DMCy(1WTy) DMC3(1WT3)/DMCy(1WTy) DU PFD CAPT(2WT1)/ DMCx(1WTx) DU ND CAPT(3WT1)/ DMCx(1WTx) DU EWD(4WT1)/ DMCx(1WTx) DU SD(4WT2)/ DMCx(1WTx) DU ND FO(3WT2)/ DMCx(1WTx) DU PFD FO(2WT2)/ DMCx(1WTx) DMCx(1WTx)/WRG:DMCx BUS DATA TO PFD CAPT DMCx(1WTx)/WRG: DMCx BUS DATA TO ND CAPT DMCx(1WTx)/WRG: DMCx BUS DATA TO EWD DMCx(1WTx)/WRG: DMCx BUS DATA TO SD DMCx(1WTx)/WRG: DMCx BUS DATA TO ND FO DMCx(1WTx)/WRG: DMCx BUS DATA TO PFD FO

DMCx Error Code

ATA Number

247

316322

248

316322

249

316322

250

316322

251

316322

252

316322

Message DU PFD CAPT(2WT1)/WRG: DMCx BUS DATA TO PFDCAPT DU ND CAPT(3WT1)/WRG: DMCx BUS DATA TO ND CAPT DU EWD(4WT1)/WRG: DMCx BUS DATA TO EWD DU SD(4WT2)/WRG: DMCx BUS DATA TO SD DU PFD FO(2WT2)/WRG: DMCx BUS DATA TO PFD FO DU ND FO(3WT2)/WRG: DMCx BUS DATA TO ND FO

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



•

Hardware Pin Programming Failure:

Error Code 208 209 210

ATA Number 316200 316200 316200

211

316300

212

316300

Message WRG : PIN PROG/DMC1(1WT1) WRG : PIN PROG/DMC2(1WT2) WRG : PIN PROG/DMC3(1WT3) WRG : PIN PROG/ DU PFD CAPT(1WK1) WRG : PIN PROG/ DU ND CAPT(3WK1)

Hardware failure Error Code

228

ATA Number 316334 316334 316334 316322 316322 316322 316322 316322 316322

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

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

Error Code

ATA Number

213

316300

214

316300

215

316300

216

316300

Error Code

ATA Number 316322 316322 316322

229

316322 316322 316322 316334 316334 316334


Message WRG : PIN PROG/ DU EWD(2WK1) WRG : PIN PROG/ DU SD(2WK2) WRG : PIN PROG/ DU ND FO(3WK2) WRG : PIN PROG/ DU PFD FO(1WK2)

Message DU PFD CAPT(2WT1)/ COOLING DU ND CAPT(3WT1)/ COOLING DU EWD(4WT1)/ COOLING DU SD(4WT2)/ COOLING DU ND FO(3WT2)/ COOLING DU PFD FO(2WT2)/ COOLING DMC1(1WT1)/COOLING DMC2(1WT2)/COOLING DMC3(1WT3)/COOLING

EIS – On Board maintenance (42) The following table summarizes all message displayed by DU over a black screen: Message

Blank screen

Details

/

Meaning -

DISPLAY SYSTEM VERSION INCONSISTENCY

DMC VERSION INCONSISTENCY E ECAM ON ND F INVALID DATA INVALID DISPLAY UNIT

Amber message centered on the screen -

DU in OFF position DU failure cases where the integrity of the display can no longer be warranted DU not powered If an operational image and the message are displayed, the DU and an inactive DMC have different EIS software version If only the message is displayed, the DU and its active DMC have different EIS software version

Amber message EIS loaded software inside the active DMC is not compatible with centered on the screen A/C type (DMC pin prog) Large white letter None operational software stored in the DU centered on the screen Green message ECAM image is displayed on ND and both ECAM DUs are valid centered on the screen Large amber letter DU is unserviceable centered on the screen Amber message DU does not receive any data from a DMC centered on the screen Amber message centered on the screen -

POST results not OK DU compatibility check not OK



Message L MAINTENANCE MODE PLEASE WAIT SELF TEST IN PROGRESS (MAX 40 SECONDS) VIDEO NOT AVAIL WAITING FOR DATA (MAX 35 SECONDS)

Details

Meaning

Large cyan letter DU is tele-loaded centered on the screen Green message EIS system is in maintenance mode centered on the screen Green message Displayed for 1 seconds during operational image/Video transition centered on the screen Green message DU is in power-up test (POST) centered on the screen Amber message Video not available centered on the screen Green message DMC ARINC 629 communication is to be established centered on the screen


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 PART NUMBER part number type (C for hardware part number).

C

ordering number

19268

A

F

version status

05

software modification status of the resident software

hardware modification status


EIS– Description of THALES equipment – LCDU 725 (2) Connector pin assigment


EIS – Description of THALES equipment – DMC

DISPLAY MANAGEMENT COMPUTER

1

98

266

0

part number type (1 for hardware part number). type of unit (98 for DMC).

10

9

checksum of the 9 first digits hardware modification status including BOOT and ADL software

program number (266 for New EIS).

compatibility index between HW and SW

DMC were developed and are manufactured by Diehl Avionik System (formerly VDO).  EIS (DMC & DU) - Page 100 

EIS – Description of THALES equipment – Component location - DMC

DMC2

DMC 1 DMC3

82 VU

81 VU

84 VU

86 VU

88VU

A : AFT ELECTRONICS RACK 80 VU


85 VU

87 VU

Airbus A320 ATA 31 EIS Presentation

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