A380-LEVEL I - ATA 31 Indicating_Recording Systems

A380TECHNICAL TRAINING MANUAL

MAINTENANCE COURSE - T1 & T2 (RR / Metric)LEVEL I - ATA 31 Indicating/Recording Systems

This document must be used for training purposes only

Under no circumstances should this document be used as a reference

It will not be updated.

All rights reservedNo part of this manual may be reproduced in any form,

by photostat, microfilm, retrieval system, or any other means,without the prior written permission of AIRBUS S.A.S.

LEVEL I - ATA 31 INDICATING/RECORDING SYSTEMSIndicating & Recording System Introduction . . . . . . . . . . . . . . . . . . . 2Control & Display System Presentation . . . . . . . . . . . . . . . . . . . . . . . 4Flight Warning System Presentation . . . . . . . . . . . . . . . . . . . . . . . . . 22Flight Data Recording System Presentation . . . . . . . . . . . . . . . . . . . 48Electrical Clock System Presentation . . . . . . . . . . . . . . . . . . . . . . . . 52Tail Strike Indication System Presentation . . . . . . . . . . . . . . . . . . . . 56Interface for Video System Presentation . . . . . . . . . . . . . . . . . . . . . . 60


TABLE OF CONTENTS Mar 21, 2006Page 1

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INDICATING & RECORDING SYSTEM INTRODUCTIONGeneral

The Indicating and Recording system is composed of six sub systems:- The Control and Display System (CDS)- The Flight Warning System (FWS)- The Flight Data Recording System (FDRS)- The Electrical Clock System- The Tail Strike Indication (TSI) system- The Interface for Video


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GENERAL


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CONTROL & DISPLAY SYSTEM PRESENTATIONGeneral

The Control and Display System (CDS) is an avionics world systemconnected with most of the other aircraft systems in order to display flightinformation, to allow systems monitoring and aircraft environment videomonitoring, through eight identical and interchangeable Display Units(DUs).Some novelties regarding the DUs have been introduced on the A380.The Cathode Ray Tubes (CRTs) have been replaced by eight identicaland interchangeable enlarged (8 inch by 6 inch) Smart Liquid CrystalDisplay Units (LCDUs), which support the following conventionaldisplay, formats:- 2 Primary Flight Displays (PFDs)- 2 Navigation Displays (NDs)- 1 Engine Warning Display (EWD)- 1 System Display (SD)- 2 Multi-Function Displays (MFDs)The two Multi-Function Displays support several remote user applicationsand among other things, ensure part of the control and display capabilitiescarried out on the previous Airbus programs by the Multipurpose Controland Display Units (MCDUs).These LCDUs are equipped with more interactive capability through theuse of cursors or focus, controlled by the Keyboard and Cursor ControlUnits (KCCUs). The KCCU is a new display control mean installed inthe A380 cockpit. It is composed of two functionally redundant parts:the Cursor and Control Device (CCD), based on trackball technology,and the keyboard. There are two KCCUs, one dedicated to each pilot,located on the pedestal.The CDS incorporates the Electronic Flight Instrument System (EFIS)and the Electronic Centralized Aircraft Monitoring (ECAM) system.It also supplies display capabilities dedicated to remote user applicationsperforming basic avionics functions.

Finally, incorporates video capability, and supports various videomonitoring functions.


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CONTROL & DISPLAY SYSTEM PRESENTATIONEFIS Function

General LayoutThe EFIS displays information related to the aircraft guidance andnavigation.This information is presented in front of each pilot on a PFD MainZone and on the ND. The PFD Main Zone displays, on the outerdisplay unit, the flight information required for short-term flight. TheND displays, on the inner display unit, the information required fornavigation. The EFIS architecture is based on LCD smart DUs. EachEFIS LCDU acquires data from A/C systems via the Avionics DataCommunication Network (ADCN). Then it elaborates the appropriatedisplayed pages. In order to overcome a complete ADCN failure, theLCDUs can also acquire data through a backup connection, directlyfrom the Air Data Inertial References (ADIRS).Interactivity with EFIS is given independently to each pilot, for displayselection and reconfiguration, through:- The CAPT and F/O KCCUs, which enable to control cursor or focusin order to select interactive functions on their dedicated DUs,- The CAPT and F/O EFIS control panels which provide selection ofthe display modes,- The CAPT and F/O CDS Reconfiguration control panels, whichenable DUs reconfigurations.




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EFIS FUNCTION - GENERAL LAYOUT




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CONTROL & DISPLAY SYSTEM PRESENTATIONEFIS Function (continued)

EFIS DisplaysThe EFIS information is presented on the PFDs Main Zone and onthe NDs.PFDEach PFD displays short-term flight information and is divided intotwo zones.The PFD Main Zone shows conventional Primary Flight Display datasuch as speed, altitude, heading and attitude.The lower zone, which is not part of the EFIS, is associated to theECAM system.NDEach ND displays medium/long term flight information dedicated tonavigation and is also divided into two different zones: the upper partcalled ND Main Zone and the lower part called Vertical Display (VD)Zone.




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EFIS FUNCTION - EFIS DISPLAYS




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CONTROL & DISPLAY SYSTEM PRESENTATIONECAM Function

General LayoutThe ECAM system displays A/C system information for monitoringpurposes and provides a display support to the Flight Warning System(FWS) as well.This information is presented to both pilots on:- A single Engine Warning Display (EWD) located in normalconfiguration on the upper ECAM DU.- The main zone of a single System Display (SD) located normallyon the lower ECAM DU.- Both PFDs lower zone located in normal configuration on the outerDUs.The ECAM architecture is based on LCD smart DUs.Each ECAM LCDU acquires data from A/C systems to elaborate theEngine Primary display on the EWD and the A/C systems synopticspages on the SD. It also acquires and displays data from the FWS.Note that these data acquisitions are done via the ADCN. In order toovercome a complete ADCN failure, the LCDUs can also acquiredata through a backup connection, directly from FWS.Interactivity with ECAM is given to both pilots, for display selectionand reconfiguration:- Through a single ECAM Control Panel (ECP) for pages control andselection.- The CAPT and F/O CDS Reconfiguration control panels, whichenable DUs reconfigurations.Note that the ECP controls the ECAM and the FWS via the ADCNor directly through backup connections.




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ECAM FUNCTION - GENERAL LAYOUT




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CONTROL & DISPLAY SYSTEM PRESENTATIONECAM Function (continued)

ECAM DisplaysThe ECAM information is presented on several display units:- The EWD- The SD- The PFDs A/C Configuration and Flight Limitation ZoneEWDThe Engine Warning Display is presented to both pilots and dividedinto two zones:- The Engine Display (ED), which displays all engine primaryparameters. These data are driven by the ECAM itself.- The Warning Display (WD), which supplies Warning/Cautionmessages and corresponding procedures, Memos, general Limitations,normal checklists and abnormal procedures. These data are driven bythe FWS.SDThe SD image is presented to both pilots and is divided into threezones:

- An upper zone called SD Main Zone displays the A/C systemssynoptic pages driven by the ECAM itself or the Status page drivenby the FWS.- A middle zone dedicated to permanent data related to temperature,time, weight and fuel, driven by the ECAM as well.- A lower zone called Air Traffic Control (ATC) Mail Box, which isnot driven by the ECAM.PFDThe A/C Configuration and Flight Limitation Zone located on thelower part of the PFDs gives slats, flaps and trim position, memosand limitations. Note that all memos and limitations generated by the

FWS are displayed on the WD while PFDs display only Memos andLimitations related to short-term flight.




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ECAM FUNCTION - ECAM DISPLAYS




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CONTROL & DISPLAY SYSTEM PRESENTATIONECAM Function (continued)

ECAM ModesThe ECAM operates according to four modes related to the A/C systemsynoptic pages presentation on the SD. These modes are:- The Normal mode- The Manual mode- The Advisory mode- The Failure related modeNormal ModeIn Normal mode, without any A/C system failure, the SD presentsautomatically A/C system synoptic pages according to the currentflight phase computed by the FWS.Manual ModeIn Manual mode, without any A/C system failure, the SD presentsA/C system synoptic pages selected by the crew via the ECAM ControlPanel (ECP). Note that the manual mode can override all other modes.Advisory ModeThe ECAM permanently monitors the value of some critical systemparameters. When a value drifts from its normal range, the Advisorymode is triggered and the ECAM displays automatically thecorresponding SD page, with the affected parameter pulsing.Failure Related ModeWhen an A/C system failure occurs the ECAM displays on the EWDthe warning and caution messages generated by the FWS. In this casethe failure related mode displays automatically on the SD thecorresponding A/C system synoptic page.Note: An advisory may or may not lead to a failure. Advisory andFailure related modes are totally independent one from the other andwhen triggered they cancel the other modes.




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CONTROL & DISPLAY SYSTEM PRESENTATIONRemote User Applications Display Support

General LayoutIn addition to the EFIS and ECAM functions, the CDS also givesinteractive display resources for the following systems:- The Flight Warning System (FWS)- The Concentrator and Multiplexor for Video (CMV)- The Flight Management System (FMS)- The Aircraft Environment Surveillance System (AESS)- The Air Traffic Control System (ATCS)- The Flight Control Unit (FCU) BackupThese systems are not hosted in the CDS. The CDS acquiresparameters from them through the ADCN, except for the Concentratorand Multiplexer for Video (CMV), which is directly connected. Theseparameters are used to build the corresponding pages on the DUs.The CDS gives to most of these systems a dedicated Human-MachineInterface (HMI) called Multi-Function Display (MFD).




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REMOTE USER APPLICATIONS DISPLAY SUPPORT - GENERAL LAYOUT




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CONTROL & DISPLAY SYSTEM PRESENTATIONRemote User Applications Display Support (continued)

MFDThe MFD is an interactive display resource, which allows the crewto control the following remote user applications:- FMS- The ATCS- The AESS- The FCU Back-up functionsIn addition it lets these systems to display computed data.The MFD human-machine interface is based on KCCU interactivity,which enables pages selection via different menus, and data insertion.There is one MFD for each pilot, and each MFD is divided into twodifferent zones:- The upper MFD zone specific to each system, is used for the pagesselection- The MFD Main Display, which is dedicated to the display of remoteuser application functions.




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CONTROL & DISPLAY SYSTEM PRESENTATIONCDS Functions Allocation Review and Interactivity

The A380 cockpit CDS functions allocation philosophy is based on theAirbus family T: PFD-ND Capt, EWD-SD, ND-PFD F/O.These functions are shared out in the cockpit on the LCDUs and controlledby different interactive control means.The KCCU is a new display control mean installed in the A380 cockpit:it introduces more interactivity between the DUs and the crew throughthe use of cursors/focus. There are two KCCUs, one dedicated to eachpilot, located on the pedestal.Each KCCU controls:- The onside ND, for medium/long term lateral navigation- The onside MFD, for Flight Management System (FMS), Air TrafficControl Communication (ATC-COM) system , Aircraft EnvironmentSurveillance system (AESS) and Flight Control Unit (FCU) backupfunctions.- The SD lower part, which displays the ATC Mail BoxThe ECP controls the WD part of the EWD for the management and thedisplay of Warning and Cautions, Normal Checklist, and abnormalprocedures. It controls also the SD Main Zone for the selection of A/Csystems synoptics and Status pages.Each EFIS CP controls:- The onside PFD Main Zone for short-term guidance- The onside ND Main Zone and Vertical Display for Medium/Long termnavigation pages selection and display range




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CDS FUNCTIONS ALLOCATION REVIEW AND INTERACTIVITY




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FLIGHT WARNING SYSTEM PRESENTATIONGeneral

The Flight Warning System (FWS) is a centralized system improvingthe crew situation awareness in normal and abnormal A/C systemoperation. In case of aircraft systems failure or A/C dangerousconfiguration, the FWS: Alerts the crew in real time about the seriousness level of the failure Gives failure identification and categorization through caution andwarning messages Helps pilots to isolate the failure through an associated procedure Provides failure consequences on A/C status and flight operations(limitations)For that the FWS monitors all the A/C system, identifies and classifiesfailures, and activates aural and visual alert indications thanks to cockpitperipherals. It gives abnormal procedures related to systems undetectableevents as well. In normal operations, the FWS provides also an operationalassistance to the crew via Normal Checklist, memos and auralannouncements in approach.


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FLIGHT WARNING SYSTEM PRESENTATIONFWS Architecture

The FWS is mainly composed of two FWS Applications hosted in theCPIOMs-C1 and C2 acquiring data from A/C systems (LRMs, LRUs).This data acquisition is done either via the Aircraft Data CommunicationNetwork (ADCN) or directly for some systems through a backupconnection. Then if an A/C system failure or configuration change isdetected, or in case of A/C abnormal configuration, the FWS generatesalert signals controlling directly the loudspeakers and the visual AttentionGetters, and warning and cautions messages displayed through the Controland Display System (CDS). This is the alert processing.The crew interfaces with the FWS through the ECAM Control Panel(ECP). Regarding the FWS, the ECP mainly:- Manages caution and warning related procedures- Calls the Status page on the System Display (SD)- calls and handles the normal checklists and abnormal proceduresThe ECP is connected to the FWS applications via IOMs and the ADCN.Note that in case of ADCN loss, a backup connection keeps all itsfunctions operational.In addition, the FWS sends its own BITE messages, and data such asalerts and flight phases to the Central Maintenance System (CMS) formaintenance data consolidation.




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FLIGHT WARNING SYSTEM PRESENTATIONFlight Phases Computation

Normal aircraft flight is divided by the FWS into 12 phases. Each flightphase corresponds either to an A/C or a flight configuration change.These flight phases are then used by the CDS to compute the ECAMnormal mode or by the FWS itself to inhibit during critical flight phasesalerts related to non-critical flight failures. Moreover, the flight phaseswill provide contextual information about failures to the CMS.




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FLIGHT PHASES COMPUTATION




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FLIGHT WARNING SYSTEM PRESENTATIONFWS Functions in A/C and System Normal Configuration

Normal ChecklistsOn the A380, the normal checklists, which can be carried out by thecrew at different phases of the flight, have been implemented into theFWS. The crew has the capability to choose the correspondingchecklist and their associated procedures on the EWD. For non-senseditems, actions are confirmed manually through the ECP.An automatic feedback is provided for sensed items.




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FWS FUNCTIONS IN A/C AND SYSTEM NORMAL CONFIGURATION - NORMAL CHECKLISTS




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FLIGHT WARNING SYSTEM PRESENTATIONFWS Functions in A/C and System Normal Configuration(continued)

MemosThe FWS generates all memos indications, which inform the crewabout the A/C configuration following routine crew action. Memosare displayed on the PFDs Lower Zone and on the EWD. All memosgenerated by the FWS are displayed on the EWD. In addition thememos directly related to the flight are also displayed on the PFDslower zone (ex: ENG A. ICE)




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FLIGHT WARNING SYSTEM PRESENTATIONFWS Functions in A/C or System Abnormal Configuration

Failures CategorizationThere are three types of failures: An Independent failure A Primary failure A Secondary failureAn Independent failure is a failure, which affects an isolated systemor item of equipment without affecting another one (ex: i.e. fuel pump).A Primary failure is a failure of a system or of an item of equipment,which causes the loss of other systems, or equipments (ex: Greenhydraulic system).A secondary failure is the loss of a system or of an item of equipmentresulting from a Primary failure (ex: Spoilers 2, 4, 6, 8).




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FLIGHT WARNING SYSTEM PRESENTATIONFWS Functions in A/C or System Abnormal Configuration(continued)

Alerts ClassificationAlerts are classified in three levels, depending on the importance andthe urgency of the crew corrective actions required.Level 3Level 3 alert corresponds to an emergency situation requiring animmediate reaction of the crew. The following warnings fall into thiscategory:- A/C in dangerous configuration or limit flight conditions (e.g.:OVERSPEED)- System failure (e.g.: ENGINE/APU FIRE, EXCESS CABIN ALT)Level 2Level 2 alert corresponds to an abnormal situation of the aircraft,where immediate crew awareness is required, but not immediate crewcorrective action. The crew must decide how soon action has to betaken.Level 1Level 1alerts corresponds to a configuration requiring crew monitoring.This level mainly comprises the failures leading to a loss ofredundancy or performance degradation of a system (e.g.: loss ofFUEL TANK PUMP LH or RH but not both).




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Level 3 Alert ActivationWhen activated, a level 3 alert leads to the following cockpitrepercussions: An aural alert performed either by the Continuous Repetitive Chime(CRC) or a specific sound or a synthetic voice broadcast through thecockpit loudspeakers A visual alert shown by both Master Warning red-flashing lights A red warning message generally on the EWD When existing, the automatic display of the affected system synopticECAM page on the SD.




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Level 2 Alert ActivationWhen activated, a level 2 alert leads to the following cockpitrepercussions: An aural alert performed by a single chime broadcast through thecockpit loudspeakers A visual alert shown by both Master Caution amber steady lights An amber caution message generally on the EWD When existing, the automatic display of the affected system synopticECAM page on the SD.




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Level 1 Alert ActivationWhen activated, a level 1 alert does not trigger any visual or auralattention getters and leads to the following cockpit repercussions: An amber caution message displayed on the EWD When existing, the automatic display of the affected system synopticECAM page on the SD.




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StatusThe Status Page is an operational status of the A/C after systemfailures. It draws crew attention to limitations and deferred procedures(part of the normal checklist). It presents inoperative systems andgeneral information. Note that when the MORE indication is displayed,deeper information is available within the Status More Info Page.




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LimitationsThe FWS also generates all limitations indications which inform thecrew about the A/C flight capabilities. Limitations are displayed onthe EWD and on the PFDs Lower Zone. All limitations generated bythe FWS are displayed on the EWD. In addition, the limitations relatedto the flight are also displayed on the PFDs Lower zones (ex: Speedlimitation).




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Abnormal ProceduresThe Abnormal Procedure Page presents to the crew the non-sensedabnormal procedures (ex: bomb inboard, broken windows etc). Ithelps the crew to face critical situations and to minimize the risk ofjeopardizing the flight. The procedures are classified by type of eventsor by affected system.




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FLIGHT DATA RECORDING SYSTEM PRESENTATIONGeneral

The Flight Data Recording System (FDRS) is designed to meet theAirworthiness Authorities recording requirements for crash and incidentinvestigations.Thus, the FDRS acquires, processes and records the required criticalflight parameters delivered by the A/C systems.


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FLIGHT DATA RECORDING SYSTEM PRESENTATIONFDRS Architecture

The FDRS architecture is mainly based on an application dedicated toacquisition and processing called Flight Data Interface Function (FDIF)and on different recording devices.The FDIF application is hosted by the Central Data Acquisition Module(CDAM). This application acquires critical flight data from the A/Csystems either through the Avionics Data Communication Network(ADCN) or directly from a linear accelerometer dedicated to the FDRSand from the Integrated Standby Instrument System (ISIS).Note that the Linear Accelerometer is installed at the A/C center of gravityposition to provide the FDIF with the 3 axes acceleration data.Then, the FDIF formats the critical flight data by processing and sendsit directly to the following recording devices:- The Flight Data recorder (FDR) which is mandatory and crash resistant.The FDR is able to record the critical flight parameters received duringthe last 25 hours.- The Quick Access Recorder (QAR), which is an optional equipment.The QAR can give an easier access to the recorded data. The recordingcapability of the QAR depends on the airlines internal needs.- The Virtual QAR (VQAR), if installed, is hosted in the Network ServerSystem (NSS). It takes up a part of the Aircraft Network Server Unit(ANSU) memory. Note that QAR and VQAR record the same data thanthe FDR. The VQAR is able to record data related to the last four flightswith a maximum duration of 16 hours each.Moreover, the crew has the capability to control the FDRS through twodifferent control means:- The Ground Control Switch which enables to supply the FDRS onground for test and maintenance purposes, or forpreflight check.- The EVENT pushbutton, which is used to record an event mark in eachFDRS recording device.




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ELECTRICAL CLOCK SYSTEM PRESENTATIONGeneral

The Electrical Clock is located on the main instrument panel and givesUniversal Time Coordinated (UTC) and associated date, Elapsed Time(ET) and Chronometer (CHR). This data is used for flight management,maintenance and recording purposes and crew information.


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ELECTRICAL CLOCK SYSTEM PRESENTATIONElectrical Clock System Architecture

The Electrical Clock displays and outputs UTC and date synchronizedeither on an external time reference or on an internal time reference. Innormal configuration the Electrical Clock display and outputs aresynchronized on an external time reference received from the Multi-ModeReceiver 1 (MMR 1)(Global Positioning System 1 (GPS1)). This is theexternal mode.Time and date display and outputs can also be synchronized on theElectrical Clock internal time base. This internal time reference is basedeither on the last valid data received from the GPS or on the time setmanually by the crew.In this case, the clock increments time and date. This is the internal mode.The Internal mode can be activated in two cases:- Manually, when the time given by the MMR 1 (GPS 1) is detectederroneous or inaccurate by the crew.- Automatically in a degraded mode of operation, when the externalsource is not available.In external or internal mode the Electrical Clock time and date areavailable through two IOMs on the Avionics Data CommunicationNetwork (ADCN), and transmitted to the clock users both in the Avionicsand Open Worlds.When the clock data is not available, the users which need a time referenceuse the output data of the three Air Data and Inertial Reference Unit(ADIRUs). Note that the ADIRUs use both MMR1 and MMR2 data tocompute the time reference.




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ELECTRICAL CLOCK SYSTEM ARCHITECTURE




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TAIL STRIKE INDICATION SYSTEM PRESENTATIONGeneral

The Tail Strike Indication System detects ground contacts of the tailfuselage, occurred during take-off (Phases 5 and 6) or landing phases(Phases 9 and 10). In case of Tail Strike event during these phases, thisdetection allows to generate a cockpit indication in order to prevent thecrew from continuing the flight and to ensure proper maintenance action.In order not to disturb the crew during critical phases, this alert will onlybe displayed in phases 7 and 11, and inhibited during all other flightphases.


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TAIL STRIKE INDICATION SYSTEM PRESENTATIONTail Strike Indication System Architecture

The TSI System is made up of two Tail Strike Indicators, located on therear fuselage, one on the right side and the other one on the left side.These Tail Strike indicators ensure the detection of rear fuselage chafesor loads on the ground during takeoff or landing.The two TSIs transmit Tail strike detection data through IOMs, via theAvionics Data Communication Network (ADCN) to the Flight WarningSystem (FWS). Then the FWS computes the Tail Strike alert anddepending on the flight phase, sends it via the ADCN to the Control andDisplay System (CDS). This alert indication is displayed on ElectronicCentralized Aircraft Monitoring (ECAM) Engine Warning Display (EWD)and on the PFDs Lower zone.




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INTERFACE FOR VIDEO SYSTEM PRESENTATIONGeneral

On the A380, the video monitoring functions have been increased inorder to provide the crew with additional aircraft status information, toimprove both A/C operations and passengers safety. The Concentratorand Multiplexer for Video (CMV) offers an interface to several aircraftvideo monitoring sources, to make them compatible with the Control andDisplay System (CDS) specific video protocol. The video sourcesmanaged by the CMV allow the crew to perform the monitoring of:- The Aircraft external environment- The Airport traffic- The Cockpit Door environment- The cabin environment


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INTERFACE FOR VIDEO SYSTEM PRESENTATIONCMV Architecture

The CMV is the core unit, which is used to concentrate video signalscoming from several A/C video sources. These video sources are theExternal and Taxing Camera System (ETACS), and the optional:- Cockpit Door Surveillance System (CDSS),- Cabin Video Monitoring System (CVMS),- Onboard Airport Navigation System (OANS)Different control means offer to the crew the capability to perform thevideo source selection. This selection is transmitted in parallel to theControl and Display System (CDS) and to the CMV, which sends it tothe different video sources available.The CMV treats the video sources signals in order to make themcompatible with the CDS specific video protocol and transmits them fordisplay to the CDS via direct links.




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INTERFACE FOR VIDEO SYSTEM PRESENTATIONCMV Video Sources Allocation on CDS

All video signals acquired by the CMV from video sources are displayedon cockpit display units depending on the crew video selection. In normaloperation, the video sources allocation is organized in the following way.Each EFIS Control Panel (EFIS-CP) controls:- The onside Primary Flight Display (PFD) for the selection and displayof the ETACS video signal- The onside Navigation Display (ND) for the selection and display ofthe OANS video signalThe ECAM Control Panel (ECP) controls the System Display (SD) forthe selection and display of:- The CDSS video signal- The CVMS video signal- The ETACS video signal also




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AIRBUS S.A.S.31707 BLAGNAC cedex, FRANCE

STMREFERENCE L0Y06082

MARCH 2006PRINTED IN FRANCEAIRBUS S.A.S. 2006

ALL RIGHTS RESERVED

AN EADS JOINT COMPANYWITH BAE SYSTEMS

Table of ContentsIndicating & Recording System IntroductionGeneral

Control & Display System PresentationGeneralEFIS FunctionGeneral LayoutEFIS Displays

ECAM FunctionGeneral LayoutECAM DisplaysECAM Modes

Remote User Applications Display SupportGeneral LayoutMFD

CDS Functions Allocation Review and Interactivity

Flight Warning System PresentationGeneralFWS ArchitectureFlight Phases ComputationFWS Functions in A/C and System Normal ConfigurationNormal ChecklistsMemos

FWS Functions in A/C or System Abnormal ConfigurationFailures CategorizationAlerts ClassificationLevel 3 Alert ActivationLevel 2 Alert ActivationLevel 1 Alert ActivationStatusLimitationsAbnormal Procedures

Flight Data Recording System PresentationGeneralFDRS Architecture

Electrical Clock System PresentationGeneralElectrical Clock System Architecture

Tail Strike Indication System PresentationGeneralTail Strike Indication System Architecture

Interface for Video System PresentationGeneralCMV ArchitectureCMV Video Sources Allocation on CDS

A380-LEVEL I - ATA 31 Indicating_Recording Systems

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