EIS 06 Identical & Interchangeable LCD Units. EFIS
ECAM
Primary flight display unit (PFD)
Navigation display unit (ND (ND))
Parameters necessary for short term aircraft control
Navigation & Radar information
EFIS
Engine & Warning Display ( EWD) EWD )
System & Status Display ( SD) SD)
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 Comp uters 2 Flight Warning Comp uters (generate all warning messages & activate attention getters) 2 System Data Acquisition Concentrato rs UPPER EACM Engine Primary Parameters - EPR - EGT - N1 - N2 - Fuel flow T/O or Landing Memo Normal Memo Primary Failure Message 13 system pages Cruise page automatic in flight
Status page summary of A/C operations
LOWER ECAM
FOB Slat/Flap indication
Normal Memo Secondary Failure Message
(identical & interchangeable) (-do-) (-do-)
System Page Or Status Display
TAT SAT
Time
Gross Weight
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. 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.
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, configuration, Captain (F/O) PFD & ND are affected by the failure of DMC 1 (2), a caution message appears on the EWD and the am ber message 'INVALID 'INVALID DATA' is displayed 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 not immediately (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 drives the 6 DUs, message 'EFIS SINGLE SOURCE 2' is displayed displayed on both PFDs (COPY mo de). DMC 1+2+3 FAILURE No more EFIS & ECAM information is presented, presented, the amber message INVALID DATA is displayed 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 encod ed Greenwich M ean Time (GMT) infor mation to the Cockpit Voice Reco rder 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 locate d 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 performa nce 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.
