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A 330 Ind Record Summary

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EIS 06 Identical & Interchangeable LCD Units. EFIS Primary flight display unit (PFD) Parameters necessary for short term aircraft control EFIS Navigation display unit (ND) Navigation & Radar information Engine & Warning Display (EWD) ECAM System & Status Display (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
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    EIS 06 Identical &InterchangeableLCD Units.  EFIS ECAM Primary flightdisplay unit (PFD)  Parametersnecessary for shortterm aircraft controlNavigation displayunit ( ND )Navigation & RadarinformationEngine &Warning Display( EWD )System &Status Display( SD )EFIS  2 Primary Flight Displays & 2 Navigation DisplaysDMC 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 DisplayDMC 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 landWarning Light3 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 flowFOBSlat/Flap indicationSystem PageOrStatus DisplayT/O or Landing MemoNormal MemoPrimary Failure MessageNormal MemoSecondary Failure MessageTATSATTime 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 ECAMFailure Mode  Automatic due to warningAdvisory Mode  Automatic due to drifting parameterFlight Phase Mode  Automatic presentation due to A/C Situation Maintenance Post Flight Report Can be printed only on ground, contains ECAM messages & failure messagesThe advisory (ADV), appears by pulsing in white to indicate that an aircraft system parameter has drifted out of its normaloperating range. In ECAM single display mode, the related page pushbutton will also flash on the ECAM Control Panel toindicate 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 NDimage by pushing the PFD/ND transfer pushbutton . When the ND fails or is switched off, the ND image can be manuallyrecovered 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 isavailable 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 SINGLEDISPLAY 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/NDtransfer 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 FAILUREDMC 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 theEWD 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 not   immediately (a message is displayed on both EWD and SD for 1 second: INVALIDDATA ). The crew is then asked to switch the ECAM SWITCHING/DMC selector switch to the position 1 to confirm this DMC 1selection. 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 CAPTmust switch the EFIS DMC SELECTOR and the ECAM DMC SWITCHING to the position 2. In this case a caution messageappears 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 hasto 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 wantsto 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 forincident/accident investigations by the airworthy authorities. The main functions of the FDIU are to collect all critical flightparameters from various aircraft systems and to send them to the Digital Flight Data Recorder. At the same time the FDIUsends an audio signal with encoded Greenwich Mean Time (GMT) information to the Cockpit Voice Recorder forsynchronization with the DFDR. The DMU section is dedicated to the Aircraft Condition Monitoring System monitoringaircraft 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 theDFDR 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 theperformance or condition monitoring tasks be carried out through the Ground Support Equipment. The QAR is installed inthe 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.
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