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EIS

06 Identical &

Interchangeable

LCD Units.

EFIS ECAM

Primary flight

display unit (PFD)

Parametersnecessary for short

term aircraft control

Navigation display

unit (ND)

Navigation & Radarinformation

Engine &

Warning Display

(EWD)

System &

Status Display

(SD)

EFIS 2 Primary Flight Displays & 2 Navigation Displays

DMC 1 normally drives CAPT PFD & ND, DMC 2 normally drives F/O PFD & ND, DMC 3 is in standby

ECAM 1 Engine/Warning Display & 1 System Display

DMC 3 normally drives EWD & SD, DMC 1 & DMC 2 are in standby

Attention getters (in front of each pilot) Red Master Warning Light, Amber Master Caution Light, Aural Warning, Auto land

Warning Light

3 Display Management Computers (identical & interchangeable)2 Flight Warning Computers (generate all warning messages & activate attention getters) (-do-)

2 System Data Acquisition Concentrators (-do-)

UPPER EACM LOWER ECAM

Engine Primary Parameters

- EPR- EGT- N1- N2- Fuel flow

FOB

Slat/Flap indication

System Page

Or

Status Display

T/O or Landing Memo

Normal Memo

Primary Failure Message

Normal Memo

Secondary Failure Message

TAT

SAT

Time Gross Weight

13 system pages

Cruise page

automatic in flight

Status page

summary of

A/C operations

System Page Logic

Manual Mode Overrides others Selection from ECAM

Failure Mode Automatic due to warning

Advisory Mode Automatic due to drifting parameter

Flight Phase Mode Automatic presentation due to A/C Situation

Maintenance Post Flight Report

Can be printed only on ground, contains ECAM messages & failure messages

The advisory (ADV), appears by pulsing in white to indicate that an aircraft system parameter has drifted out of its normal

operating range. In ECAM single display mode, the related page pushbutton will also flash on the ECAM Control Panel to

indicate to the crew which system page is affected by an advisory.

The status (STS) indicates that a status message is on the ECAM status page.

The overflow arrow indicates that the warning messages exceed the capacity of the display on the left memo area (7 lines).

In this case, the heading titles of the warning messages are displayed on the right memo area.

PFD or ND FAILURE

When PFD fails or is switched off, the PFD image is transferred automatically on the ND. It is possible to recover the ND

image by pushing the PFD/ND transfer pushbutton. When the ND fails or is switched off, the ND image can be manually

recovered on the PFD by using the PFD/ND transfer pushbutton.

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EWD or SD FAILURE

When EWD fails or is switched off, the EWD image is automatically transferred to the SD. In this case only one DU is

available to show the ECAM displays, this is called the ECAM SINGLE DISPLAY mode. A system page can be displayed

momentarily by pressing & holding one of the system keys.

If the failure happens on the lower display, the EWD is presented on the upper display and this is also in ECAM SINGLE

DISPLAY mode.

In these failure cases, the pilots may use the ECAM/ND transfer selection to recover a second ECAM display on the ND.

EWD & SD FAILURE

If both ECAM DUs fail or are switched off, the crew can display the EWD image on the ND by switching the ECAM/ND

transfer selector to CAPT or F/O. This is then an ECAM SINGLE DISPLAY mode, but in this case ECAM is presented on the ND.

DMC FAILURE

DMC 1 (2) FAILURE

In normal configuration, Captain (F/O) PFD & ND are affected by the failure of DMC 1(2), a caution message appears on the

EWD and the amber message 'INVALID DATA' is displayed in the center of the PFD and ND. So the Captain (F/O) must switch

to DMC3 to recover the PFD and ND information.

DMC 3 FAILURE

DMC1 takes over automatically but notimmediately (a message is displayed on both EWD and SD for 1 second: "INVALID

DATA"). The crew is then asked to switch the ECAM SWITCHING/DMC selector switch to the position 1 to confirm this DMC 1

selection.

DMC 1+3 FAILURE

On the CAPT PFD, ND, EWD & SD, the amber message 'INVALID DATA' is displayed in the center of the displays. The CAPT

must switch the EFIS DMC SELECTOR and the ECAM DMC SWITCHING to the position 2. In this case a caution message

appears on the EWD. DMC 2 drives the 6 DUs, message 'EFIS SINGLE SOURCE 2' is displayed on both PFDs (COPY mode).

DMC 1+2+3 FAILURE

No more EFIS & ECAM information is presented, the amber message INVALID DATA is displayed on the 6 DUs. The crew has

to use the Integrated Standby Instrument System (ISIS).

SOME EFIS SWITCHING NOT ALLOWED

Some EFIS switching are not allowed because they can cause unusual configurations of the system. In case of the crew wants

to switch some of these configurations, an amber message comes into view on the PFD.

RECORDING SYSTEM

FDIMU = Flight Data Interface Unit (DFDRS function) & Data Management Unit (ACMS function) with PCMCIA interface.

The FDIU section is dedicated to the Digital Flight Data Recording System, acquiring mandatory parameters to record for

incident/accident investigations by the airworthy authorities. The main functions of the FDIU are to collect all critical flight

parameters from various aircraft systems and to send them to the Digital Flight Data Recorder. At the same time the FDIU

sends an audio signal with encoded Greenwich Mean Time (GMT) information to the Cockpit Voice Recorder for

synchronization with the DFDR. The DMU section is dedicated to the Aircraft Condition Monitoring System monitoring

aircraft systems condition, mainly engines and APU systems, as well as aircraft performance.

DFDR is a recorder located in the aft part of the aircraft, which stores, in a solid state memory, the data of the last twenty -

five hours collected by the FDIU. The front face of the DFDR includes an Underwater Locator Beacon..

An EVENT P/B is located on the cockpit center pedestal. When pushed, the EVENT P/B is used to record an event mark in the

DFDR memory. This enables the technician to quickly find the event out of the 25 hours of data.

The DFDR parameters can be optionally recorded on an optical disk located in the Quick Access Recorder (QAR). This lets the

performance or condition monitoring tasks be carried out through the Ground Support Equipment. The QAR is installed in

the avionics compartment.

A Linear Accelerometer is installed in the aircraft center of gravity to give to the FDIU the data of three axis of acceleration.

The FDIU receives the LA information via the System Data Acquisition Concentrators.