A330 B2 ATA31.3 INDICATING LEVEL3 VAECO_noted.pdf

A330 B2 PW4000 ATA 31 INSTRUMENT

LEVEL 3

ISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 1

INDICATING / RECORDING SYSTEMS A330200/300 A340200/300

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FRA US/T-2 KrB Sep 01, 2008

ATA 31 INDICATING/RECORDING SYSTEMS

LufthansaTechnical Training

Page 1


INDICATING / RECORDING SYSTEMSGENERAL

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OverheadPanel

Glareshield

Side Stick

Main InstrumentPanel

Side Stick

Pedestal

Maintenance Panel

Reset Circuit Breakers

A340 shown


Page 3Figure 1 CockpitISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 3


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Overhead PanelMost of the aircraft system controls are located on the Overhead panel. The main systems are located in the center of the overhead panel and the others on the side with the controls of each system grouped in a single place. There are no more circuit breakers in the cockpit. Most of them are located in the avionic compartement. However some computers can be reset from two panels.A maintenance panel is provided for onground maintenance operations on some systems (hyd, engines...).The overhead panel is scanned by using a standardized Airbus pattern.


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Computer Reset

ReadingLight

OxygenRecorder

Computer Reset

Cargo Smoke


Page 5Figure 2 Overhead PanelISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 5


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GlareshieldThe various rotary selector and attention getters are located on the glareshield. In the center is the Flight Control Unit (FCU), made up of an Auto Flight System (AFS) Control Panel and two Electronic Flight Instrument System (EFIS) Control Panels.


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Master Warning LightFCU

Chrono

Auto Land Light

EFIS DMCReconfiguration

PFD/ND Transfer

Master Caution LightSide Stick Priority

ND Control

PFD Control

Loudspeaker


Page 7Figure 3 GlareshieldISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 7


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Main Panel6 identical and interchangeable Cathode Ray Tubes are installed on the maininstrument panel.The Cathode Ray Tubes (CRT) are :- two Primary Flight Displays (PFD),- two Navigation Displays (ND),- an Engine/Warning Display (E/WD) and- a System Display (SD).The main panel is more of a rack with a cover plate than a panel.Note:the landing gear emergency extension is no longer mechanical but electrical.


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Horizon

ASI

SELCALCodeAltimeter

Ldg Gear/Autobrake/Antiskid

Brake Pressure

GPWS

MapLighting

Loudspeaker

Ldg Gear Emergency

Limit Speed PlacardClock

Ldg Gear SelectorECAM Switching

VOR/ADF DDRMI

Sliding Table

Console/Floor Lighting

Overhead Lighting True/Mag Selector


Page 9Figure 4 Main PanelISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 9


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PedestalThree identical and interchangeable Multipurpose Control and Display Units (MCDU) are installed on the pedestal.They provide an interface with theFMS,ACARS,Aircraft Condition Monitoring System (ACMS) andCentralized Maintenance System (CMS).The parking brake handle, thrust levers, flap control lever and speed brakelever control their respective systems electrically.Each pilot station is provided with a Radio Management Panel (RMP) and anAudio Control Panel (ACP) for communication and back up navigation.Usually, the two forward MCDUs are for pilot use and the rear one for maintenance use.

VU(S)All panels are identified by VU numbers, except those manufactured by vendors.


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Multipurpose Control Display Unit

Thrust and Thrust ReverserControl Levers

Speed Brake Control Lever

Parking Brake

Handset

Radio Management Panel

Pitch Trim Wheel

Audio Control Panel

Lighting and DFDR Event

Flap Control Lever

Engine Start Panel

A340 shown


Page 11Figure 5 PedestalISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 11


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COCKPIT PHILOSOPHY

Lights Out PhilosophyAll the aircraft and system controls are arranged to be within easy reach of thetwo crew members. The concentration of system controls on the overheadpanel is achieved by extensive use of illuminated pushbuttons directly installedon the system synoptic panel.In normal operation, no lights are illuminated in the cockpit.This is called the lights out philosophy .


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A340 shown


Page 13Figure 6 Electrical PanelISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 13


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Pushbutton PrincipleStatus and failure indications are integrated whenever possible into the relevantilluminated pushbuttons which must be operated for corrective action.

Pushbuttons with two stable positionsMost of the illuminated pushbuttons have two stable positions:pressed in andreleased out;each position corresponding to a control signal sent to a system.Pressed in (recessed): Normaly used system activation (AUTO or ON) Temporarily used system activation (ON) System activated for maintenance operation (ON) or override (OVRD).

Pushbuttons with one stable positionSome pushbuttons have only one stable position:released out.When pushed they send a control signal to the system.Released out (flush with the panel): System deactivation (OFF) Manual activation of a system (ON) Activation of an alternate system (ALTN).


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ADR1

ADR1

ADR1

Typical Pushbutton with two stable Positions

PRESSED INNO LIGHTSYSTEM ACTIVATED

CORRECT OPERATION

PRESSED INFAULT LIGHT ONSYSTEM ACTIVATED

FAULTY CONDITION

SYSTEM DEACTIVATED

RELEASED OUTOFF LIGHT ON

1. Pressed in

2. Released out


Page 15Figure 7 Pushbutton PrincipleISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 15


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Colour PhilosophyThe illuminated pushbutton and annunciator lights are of different colours according to their function.In normal operation, only green lights and sometimes blue lights areilluminated.


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RED IS USED FOR A FAILURE NEEDINGIMMEDIATE ACTION

AMBER IS USED FOR A FAILURE NEEDING AWARENESSBUT NO IMMEDIATE ACTION

WHITE IS USED TO INDICATE A PUSH BUTTON INAN ABNORMAL POSITION OR MAINTENANCE OPERATION

GREEN IS USED TO INDICATE NORMAL OPERATION OF A BACK UP SYSTEM

BLUE IS USED TO INDICATE NORMAL OPERATIONOF A TEMPORARILY USED SYSTEM


Page 17Figure 8 Colour PhilosophyISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 17

INDICATING / RECORDING SYSTEMSELECTRONIC INSTRUMENT SYSTEM

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EIS PRESENTATIONGeneralThe Electronic Instrument System ( EIS ) replaces conventional instruments bynew technology.It presents data to the pilots on six identical and interchangeable Cathode RayTubes ( CRT ).The Electronic Instrument System is divided into two parts : an Electronic Flight Instrument System ( EFIS ) comprising :

two Primary Flight Displays ( PFD ). two Navigation Displays ( ND ).

an Electronic Centralized Aircraft Monitoring ( ECAM ) comprising : an Engine and Warning Display ( E/WD ). a System Display ( SD ). attention getters.

Electronic Flight Instruments System ( EFIS )EFIS information is presented in front of each pilot on a Primary Flight Displayand a Navigation Display.The PFD displays the flight information required for short term flight.The ND displays the flight information required for navigation.

Electronic Centralized Aircraft Monitoring ( ECAM )ECAM information is presented on the center instrument panel on an Engineand Warning Display and a System Display.The E/WD displays the engine and fuel parameters, the check list and warningmessages, and certain information relevant to system operation. The SD displays synoptics giving the configuration of various A/C systems andsome permanent data.

Attention GettersAttention getters are visual and audio.Pilot attention is drawn by : two Master Warning lights. two Master Caution lights. two Autoland lights. Audio signals ( sounds ) and Auto Call out ( synthetic voices ) broadcast by

two loudspeakers.

EFIS ControlsEFIS controls are provided by independent controls for each pilot, for displayselection or reconfiguration.The EFIS controls are : 2 EFIS switching panels. 2 EFIS control panels.

ECAM ControlsECAM controls are provided by controls on center panel and pedestal for display selection and reconfiguration.The ECAM controls are : 1 ECAM switching panel. 1 ECAM control panel.


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Loudspeaker Loudspeaker

Master Warning, Master Caution andAutoland Lights

Master Warning, Master Caution andAutoland LightsCaptain FO

EFIS Control Panels

Captains EFISSwitching Panel

FOs EFISSwitching Panel

ECAM Switching Panel Engine/Warning DisplayECAM Control Panel System Display

Captains Navigation Display

Captains PrimaryFlight Display

FOs PFDFOs ND

AUTOLAND


Page 19Figure 9 EIS LRUs ( Cockpit )ISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 19


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3160 ELECTRONIC INSTRUMENT SYSTEM (EIS)EIS ARCHITECTUREGeneralThe Electronic Instrument System is an avionics system connected with mostof the aircraft systems to perform the EFIS (Electronic Flight InstrumentSystem) and ECAM ( Electronic Centralized Aircraft Monitoring) functions.The EFIS provides flight information and the ECAM provides system and warning information.The Electronic Instrument System comprises seven computers: three identical Display Management Computers ( DMCs ) two identical Flight Warning Computers ( FWCs ) two identical System Data Acquisition Concentrators ( SDACs ).

The DMCs comprise two independent parts:one for the EFIS function and one for the ECAM function.

Control PanelsThree Control Panels are provided for EFIS and ECAM controls.Control panels are physical interfaces between the crew members and the EIS.


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FRA US/T-2 KrB Sep 01, 2008 LufthansaTechnical Training

Page 21Figure 10 EIS Basic SchematicISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 21


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EFISThe EFIS part of the DMCs decodes and processes data from the aircraftsystems in such a way to generate images on PFDs and NDs.The three DMCs receive identical information, in normal operation DMC 3 isin standby.

ECAMDMC 3 ECAM part is used in normal configuration.The ECAM uses A/C system data which is processed in the System DataAcquisition Concentrators ( SDACs ), Flight Warning Computers ( FWCs )and DMCs before being presented on E/WD and SD.The SDACs digitalize aircraft system data and transmit it to the DMCs.The DMCs using the SDACs Outputs, generate aircraft system information fordisplay on the SD.

Note:the DMCs receive directly A/C system data for display on the upper part of theE/WD.The DMCs use the outputs of the FWCs to display aircraft information on thelower part of the E/WD ( messages ).The SDACs receive A/C system information concerning amber cautions andtransmit it to the FWCs.The FWCs receive A/C system data concerning red warnings and memos, theygenerate messages and activate attention getters ( audio signals through AudioManagement Unit ).

RedundancyA great redudancy between systems is used to minimize the loss of information.Loss of a SDAC, or a FWC, or one or two DMCs does not affect EIS operation.As shown on the drawing, the system still operates normally with one SDAC,one FWC and two DMCs inoperative.


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PFD2

DMC3

FWC1 FWC2

SDAC1 SDAC2

LOUDSPEAKERLOUDSPEAKER

MASTER WARNING/CAUTION LIGHTS

MASTER WARNING/CAUTION LIGHTS

PFD1 ND1 EWD

SD

ND2

DMC1 DMC2


Page 23Figure 11 EIS Basic SchematicISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 23

INDICATING / RECORDING SYSTEMSCENTRAL WARNING SYSTEMS

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EIS CONTROLSThe Flight Warning System and Electronic Instrument System (EIS) panels arelocated on the glareshield, on the main instrument panel and on the pedestal.The captain and first officer panels have the same functions.


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EFIS Control Panel EFIS Control Panel

Attention Getters Attention Getters

EFIS Switching Panel EFIS Switching Panel

ECAM Switching PanelECAM Control Panel

A340 shown


Page 25Figure 12 Control CabinISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 25


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EFIS CONTROL PANELThe EFIS control panels, which are part of the Flight Control Unit, are dividedinto PFD controls and ND controls.

PFD controls

LS P/B:enables the localizer and glide scales and deviation symbols to be displayed onthe associated PFD.

FD P/B:enables the Flight Diretor bars to be displayed or not on the associated PFD.

Baro reference selector knob:The outer knob enables the measurement unit to be selected, either HectoPascal (HPa) or Inches of Mercury (Hg), on the baro reference window.The inner knob is rotated to select the reference value, pulled to select thestandard value (1013 HPa) and pushed to display the QNH.

Baro reference window:used to display the pressure reference value and the reference used.

ND controls

Data base display P/Bs:these five P/Bs enable additional data to be displayed on the ND. Whenpressed these P/Bs respectively displayAirports,ADF stations,VOR/DME stations,Waypoints andConstraints.

Scale rotary selector:enables the scale to be selected in miles on the associated ND for the RoseNAV, ARC and PLAN modes.Mode rotary selector:enables the desired presentation of navigation information to be selected onthe associated ND.

Note: With the mode rotary selector in position ENG ( Engine ) the Engine Standby Page is displayed on the ND. It shows the same parameters like the E/WD, but no ECAM messages are displayed in the lower area.

ADF/VOR selector:enables ADF or VOR bearing pointers to be selected on the associated ND as well as the corresponding navigation stationcharacteristics in any mode except PLAN mode.


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FOs EFIS Control Panel


Page 27Figure 13 EFIS Control PanelISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 27


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EFIS SWITCHING PANELThe EFIS switching panel is located on either side of the glareshield.

EFIS DMC Rotary SelectorIt is used to select another Display Management Computer when EFIS DMC 2(or EFIS DMC 1 for captain) has failed. This selector has no effect on the ECAM display.

PFD/ND PushbuttonEach time the PFD/ND pushbutton is pressed, the images displayed on thePFD and ND are interchanged. The image previously displayed on the PFD isdisplayed on the ND and vice versa.

PFD PotentiometerThe PFD potentiometer switches the PFD display unit on or off and controls thebrightness in conjunction with the automatic brightness control system. In the OFF position, automatic and manual reconfigurations are possible.

ND PotentiometerThe ND inner potentiometer switches the ND Display Unit on or off and enablesgeneral adjustment of the ND brightness.The outer potentiometer only adjusts the brightness of the weather radarimage.


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FOs EFIS Switching Panel

EFIS DMC Rotary Selector

PFD/ND Pushbutton

PFD OFF/BRT Potentiometer

ND OFF/BRT Potentiometer


Page 29Figure 14 EFIS Switching PanelISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 29


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ECAM CONTROL PANELThe ECAM control panel located on the pedestal, includes the brightness potentiometers and the controls required for operation of the ECAM system.

E/WD and SD OFF/BRT potentiometersThe potentiometers switch the ECAM Display Unit on or off and control thebrigtness in conjunction with automatic brightness control system. In the OFFposition, automatic and manual reconfigurations are possible.

CLR (clear) P/BWhen the P/B light is on, the warning and caution messages displayed on thelower part of the E/WD can be cleared.

STS (status) P/BIt is used to call the Status page on the SD. If there are no status messages,the normal indication is displayed for 5 seconds on the SD.

RCL (recall) P/BIt is used to recall warning and caution messages inhibited by the CLR P/B or by the flight phase automatic inhibition. If there are no warning or cautionmessages, the normal indication is displayed for 5 seconds on the E/WD.

System page P/BThese 13 P/Bs allow the system synoptic diagrams to be manually selected onthe SD. When a P/B is pressed a second time, the system page is replaced bythe page corresponding to the current flight phase.

ALL P/BIt allows the 13 system pages to be successively displayed at 1 secondintervals. The ALL P/B remains active after a complete failure of the ECAMcontrol panel.

T.O. (take off) configuration P/BIt is used to check that the A/C is in the correct configuration before take off. If the configuration is correct, TO.CONFIG.NORMAL is displayed on the E/WD.

EMER CANCel (emergency cancel) P/BIt is used to cancel aural warnings and caution messages. Caution messagesmay be recalled by pressing the RCL P/B.


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Page 31Figure 15 ECAM Control PanelISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 31


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ECAM SWITCHING PANELThe ECAM switching panel is located on the main instrument panel on the leftside of the System Display.

ECAM DMC Rotary SelectorThe ECAM DMC rotary selector is used to select the ECAM DMC.In Auto position, only ECAM DMC3 is active. ECAM DMC1 automatically takesover in case of ECAM DMC3 failure.In position 1, 2, 3, the selected ECAM DMC is active and automatic transfer isnot possible.Note: this selector has no effect on the EFIS display.

ECAM/ND Rotary SelectorThe ECAM/ND rotary selector enables an ECAM image to be displayed on one of the ND Display Units. The NORMal position corresponds to a normaloperation.CPT or F/O positions enable ECAM images to be respectively displayed on theCPT or F/O ND Display Units.


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ECAM DMC Rotary Selector

ECAM/ND Rotary Selector


Page 33Figure 16 ECAM Switching PanelISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 33


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ATTENTION GETTERSA set of attention getters is installed in front of each pilot.It consists of a Master Warning light and a Master Caution light.

When a warning occurs, the Master Warning light flashes continuously.The crew may cancel it, in most cases, as well as the associated aural warningby pushing the Master Warning Light.When a caution occurs, the Master Caution light comes on and stays onassociated with a single chime.The Master Caution Light extinguishes when it is pushed.


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Master Warning Light

Master Caution Light


Page 35Figure 17 Attention GettersISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 35


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Note: Display Units shown in normal Configuration

LOCATION


Page 36Figure 18 Display Units LocationISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 36


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ECAM Control PanelECAM Switching Panel

Cpt EFIS Control Panel F/O EFIS Control Panel

Cpt EFIS Switching Panel F/O EFIS Switching Panel

Source Switching Panel

Attention Getters Attention Getters


Page 37Figure 19 Panel LocationISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 37


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1WT1DMC1

1WT3DMC3

1WT2DMC2

1WW1FWC1

1WV1SDAC1

1WV2SDAC21WW2FWC2

DMC


Page 38Figure 20 FWCs, SDACs, DMCs LocationISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 38


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EIS Switching Relays


Page 39Figure 21 EIS Switching Relays LocationISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 39

INDICATING / RECORDING SYSTEMSPRIMARY FLIGHT DISPLAY

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3164 PRIMARY FLIGHT DISPLAY

GeneralThe Primary Flight Display ( PFD ) is presented in front of each pilot, on theouter display unit.The PFD presents short term information necessary for the flight.It is divided into 7 zones.


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Page 41Figure 22 PFD ZonesISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 41


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AttitudeThe Attitude is indicated in the middle of the Display Unit, in the shape of a cutsphere window which looks like a conventional Attitude Direction Indicator.The Attitude area presents : A/C symbols Pitch and Roll indications Flight path drift angles...

GuidanceGuidance symbols may be superposed on the Attitude sphere.

SpeedThe Air Speed Scale contains all the Air Speed data displayed on aconventional Air Speed Indicator plus significant limits, protection and targetspeeds.

HeadingThe Heading Scale displays the aicraft actual Heading and Track.

AltitudeThe Altitude Scale presents the Altitude according to a baro reference setting.

Vertical SpeedNext to the Altitude, the Vertical Speed is displayed.

Trajectory DeviationFor approach, the Trajectory Deviation is presented on the right, and at thebottom of the Attitude area.ILS and DME information appear below the speed scale.

Flight Mode Annunciator ( FMA )The Flight Mode Annunciator provides the pilot with the various armed andactive Automatic Flight System modes.


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Page 43Figure 23 Primary Flight DisplayISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 43


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PFD CONTROLSBoth EFIS Control Panels have the same controls: Hg / hPa Selector Knob for QNH units ( in Hg or hPa ). BARO Setting Knob for QNH setting. FD Pushbutton Switch for switching of FD Bars resp. FPDSymbols. LS Pushbutton Switch for switching of LOC and GLIDE Scales on

the PFD.

ND CONTROLSFor the Navigation Display there are the following controls: Mode Selector Switch to use the ND in different modes.

In the Rose Modes the aircraft symbol is in the middle of the ND, in theARC Mode it is at the bottom of the DU.PLAN corresponds to a map displayed on the ND.ENG is a standby mode to display engine parameters on the ND.

Scale Selector Switch to select the range on the ND.for example, if 320 is selected the distance between aircraft sysmbol andcompass rose corresponds to a distance of 320 nautical miles.

ADF/VOR selector: enables ADF or VOR bearing pointers to be selectedon the associated ND as well as the corresponding navigation stationcharacteristics in any mode except PLAN mode.


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BARO Correction Display

Hg / hPa Selector

BARO SettingKnob

FD Pushbutton Switch LS Pushbutton Switch

Mode Selector Switch

Scale Selector Switch

ADF / VOR Selector Switches


Page 45Figure 24 EFIS Control Panel (Captain)ISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 45


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NAVIGATION DISPLAY MODESThe indication on the Navigation Display ( ND ) depends on the position of themode selector switch on the EFIS control panel.The different modes are shown on the following pages.

ROSE ILS ModeThis mode corresponds to the conventional HSI with Localizer and Glideslope Indication.

ROSE VOR ModeThis mode corresponds to the conventional HSI with VOR Course andVOR Deviation.

ROSE NAV ModeThis mode corresponds to the conventional HSI without VOR Course resp.VOR Deviation but with flight plan indications ( from the FMGES) and weatherradar Indication.

ARC ModeThis mode shows a sector of 90 degrees in front of the aircraft.The aircraft symbol is at the bottom of the DU. Flight plan information andweather radar are displayed like in the ROSE NAV mode.

PLAN ModeIn this mode a map is displayed with north up. In the middle of the display thereis a waypoint as a reference point.Depending on the selected range other waypoints and the planned flight pathare displayed. An aircraft symbol is displayed according to the presentposition.


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AMM 316500


Page 47Figure 25 ND ROSE ILS Mode and ROSE VOR ModeISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 47


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AMM 316500


Page 48Figure 26 ND ROSE NAV Mode and ARC ModeISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 48


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AMM 316500


Page 49Figure 27 ND PLAN ModeISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 49


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Engine Standby PageThrough the EFIS control panel, each pilot is able to display an engine standbypage on his ND DU instead of the navigation pages.This page is used after failure of all the ECAM parts of the DMCs of the EIS.This page is regarded as a simplified display of the primary engine indications,normally displayed on the EWD. This page is generated by the EFIS part of theDMCs and contains the same indications as the engine primary page, exceptthe following which are not included: N1 amber line N1 degraded mode N2 degraded mode Fuel flow degraded mode N2 grey background box during the starting sequence White box during the starting sequence

ECAM Messages will not be displayed.For more details, refer to AMM 316600: Engine/Warning Display.


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Page 51Figure 28 Engine Standby PageISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 51


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3150 CENTRAL WARNING SYSTEMSENGINE/WARNING DISPLAY PRESENTATIONGeneralThe Engine and Warning Display is normally on the upper ECAM Display Unit.It is divided into two areas: the upper area and the lower area.

The upper area displays: engine primary parameters fuel quantity slats and flaps position.

The lower area is used for: warning and caution messages memo messages.


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ENGINE PRIMARYPARAMETERS


Page 53Figure 29 Engine/Warning DisplayISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 53


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Upper AreaThe symbols of the upper area are permanently displayed.The parameters are provided in the form of analog and/or digital indications( refer to corresponding chapter for detailed description ).Note: this is the basic representation for CFM 56 engines.


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A 340-200 / 300A 330-200 / 300 GE


Page 55Figure 30 E/WD Upper AreaISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 55


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Left Memo AreaTake off or landing memo, normal memo, primary failure messages and actionsto be performed are displayed in the left memo area.As soon as a failure is detected, the memo messages are replaced bywarning/caution messages.

Right Memo AreaNormal memo and secondary failure messages are displayed in the rightmemo area.

For example when one Engine Anti Ice P/B is set to ON, ENG A.ICE appearson the right memo area.T.O. INHIBITDuring take off and landing, most of the warnings are inhibited to avoiddistraction of the crew.For example, at take off, when the second engine is set to take off power anduntil the A/C has reached 1500 ft, TO INHIB is displayed.

Advisory and Overflow StatusStatus, Advisory and Overflow indications are attention getters on the display.

ADV: Advisory appears pulsing in white to indicate that an A/C systemparameter has drifted out of its normal range.

STS: Status indicates that a status message is present on the ECAM page.

Overflow Arrow : only concerns the warning messages and indicatesthat the messages exceed the capacity of the display on the left memo area.In this case, the heading titles of the Warning Messages are displayed on theright memo area.


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AdministratorHighlight








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ENG A.ICE

TO INHIB


Page 57Figure 31 E/WD Memo AreaISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 57


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SYSTEM DISPLAY PRESENTATION

GeneralThe System Display is normally on the lower ECAM Display Unit. It is divided into two areas.The upper area displays system or status pages,the lower area permanent data.The system or status pages can be called automatically after a failure or manually upon the crew request by pressing the related P/B on the ECAMcontrol panel.

Permanent DataAt the bottom of the System Display, permanent data is always displayed whatever the page presented. Here temperature (TAT, SAT), time (UTC), gross weight (GW) and gross weight center of gravity (GWCG)

are always displayed.

Total air temperature (TAT) and static air temperature (SAT) are digital values.TAT: +19 C ( green ) when normal.

XX ( amber ) when data are not available.The same applies for Static Air Temperature ( SAT ).

Load factor (G LOAD) is displayed when the aircraft speed is over 80 kts.It is amber when its value is more than +1,4 G or less than 0.7 G during morethan 2 seconds. Information remains displayed 5 seconds after the excessivecondition has disappeared.

Universal Time Coordinated (UTC) indication is permanently displayed.It may be: 23 H 56 when normal XX when data are not available.

Gross Weight (GW) indication: 170000 KG when normal 170000== KG in case of degraded accuracy XX when data are not available

Gross Weight Center of Gravity (GWCG) indication: 28.1 % (green) when normal 28.1 % (amber) when Aft CG is detected by FE computer 28.1= in case of degraded accuracy XX when data are not available


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SYSTEM PAGE

STATUS PAGE

OR


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System Page13 system pages can be displayed manually or automatically. Refer to each chapter for detailed description of the pages.The 13 system pages are: ENG (Engine secondary parameters) BLEED (bleed air) PRESS (cabin pressurization) EL/AC (electrical power supply, AC) EL/DC (electrical power supply, DC) HYD (Hydraulic power) APU (Aux Power Unit) COND (air conditioning) DOOR (Doors and oxygen ) WHEEL (Landing gear, wheels, brakes) F/CTL(Flight controls) FUEL (Fuel) C/B (Circuit breaker status).

There is one page that can be called automatically only: CRUISE page (Combination of data used in flight)

System Page LogicThe ECAM operates in four modes for the system page presentation, with apriority order.The four selection modes of system page presentation are the: Manual mode: selection from ECAM Control panel Failure mode: automatic presentation due to a warning/caution Advisory mode: automatic presentation due to a drifting parameter Flight phase mode: automatic presentation due to the A/C situation.

Note: the manual mode is cancelled in case of failure or advisory.


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A340 shown A340 shown


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A340 shown A340 shown A340 shown

A340 shownA340 shown


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Cruise PageThe cruise page is only automatically called in flight.The cruise page displays main systems parameters to be monitored duringflight: Engine parameters such as

fuel used,oil quantity andvibrations

Cabin pressure parameters such aslanding field elevation,cabin vertical speed,cabin altitude andcabin differential pressurezone temperature.


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A340 shown


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Status PageThe status page is an operational summary of the aircraft condition. It can bedisplayed manually or automatically.The information is displayed at the end of an ECAM procedure or upon crewrequest. The status page includes:Left column: limitations approach procedures information cancelled cautions.

Right column inoperative systems maintenance information.


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STATUS


Page 67Figure 37 STATUS PageISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 67


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ECAM COLOUR PHILOSOPHYThe colour of the indications and messages shown on the Engine / WarningDisplay and on the System Display depends on their meaning: RED

Faults and flight situations which require action (Warning Messages). AMBER

Faults an flight situations which require attention, but no immediate action(Caution Messages).

GREENAircraft and system indications within normal range.

WHITETitles and remarks.

BLUE ( CYAN )Instructions and limitations.

MAGENTASpecial messages.


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APU FIREAPU FIRE P/B...............PUSHAGENT AFTER 10S.....DISCHMASTER SW....................OFF

LAND ASAPBlue

Red Red

Blue (Cyan)White

White

White

Amber

(Cyan)

Blue (Cyan)

Blue (Cyan)Green

White

Amber

Engine / Warning Display System Display ( Status Page )

s

AMM 316700

A340 shown


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ALERT LEVELSMessages have different levels. The level depends on the importance of themessage for flight safety.

Level 3: warnings ( highest priority )Level 2: cautionsLevel 1: cautionsStatus messages

Within each level a priority of warnings and caution messages is lain downin a list of warnings by priority order which can be found in the AMM,chapter 315100.

LEVEL 3Level 3 messages ( warnings ) have highest priority.Level 3 warnings are caused by real emergency situations which require actionby the crew.Typical causes for level 3 warnings are Aircraft in dangerous flight situation ( e. g. stall or overspeed ) System faults which concern safety ( e. g. excessive cabin altitude

or engine fire )Level 3 warnings are connected with an aural warning ( continous repetitivechime or special call out ) and the flashing master warning light.If there is a system page for the system concerned it will be displayed on thesystem display.

LEVEL 2A level 2 message is given when a system fault does not affect flight safetydirectly.It requires awareness of the crew, but no immediate action.A typical level 2 message is IDG 1 OIL LO PR.Level 2 messages are connected with a single chime and the mastercaution light.If there is a system page for the system concerned it will be displayed on thesystem display.

LEVEL 1Level 1 messages point to a system which is faulty but not directly necessaryfor the flight, e. g. PSCU 1 fault or EFIS DMC 3 fault.Level 1 messages appear on the E/WD without any chime.If there is a system page for the system concerned it will be displayed on thesystem display.


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Level 3 Level 2

Level 1

flashing


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FAILURES WITHOUT ECAM WARNINGSFaults which do not cause any warning or caution messages but which mustnot be postponed to the next maintenance check appear on the status page ofthe SD.As soon as a fault of this type occurs STS appears on the E/WD.For further information the crew has to call the status page manually.The faults are listed under the heading MAINTENANCE.After engine shut down the STS indication on the E/WD starts flashing.


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Status


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TYPES OF FAILURESThe ECAM indicates three types of failures. Independent Failure Primary Failure Secondary Failure

The failure type is indepedent of the alert level.

Independent FailureAn independent failure is a failure of a LRU or a system which does notconcern any other system.Example: Flight Warning Computer 1 failure.Independent failures are indicated on the left side of the E/WD with theirtitle underlined.

Primary FailureA primary failure is a failure of a LRU or a system which concerns other systems.Example: A failure of the blue hydraulic system has the consequence that some spoilers fail.Primary failures are indicated on the left side of the E/WD in a frame.

Secondary FailureA secondary failure is a consequence of a primary failure.Example:F/CTL ( some spoilers fail if the blue hydraulic system is lost ).Secondary failures are indicated on the right side of the E/WD.


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Engine/Warning Display Engine/Warning Display

Engine/Warning Display

Independent Failure (red or amber) Primary Failure (red or amber)

Secondary Failure (amber)corresponding System Pages


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AURAL WARNINGS GeneralThis is the list of the various audio signals generated by the Flight Warningcomputers and the manner of cancellation.

Warning and Callouts GenerationAll Aural Warnings and Synthtetic Voice Callouts are generated in both FWCs.By means of a discrete audio synchronization signal between the FWCs theaudio signals are synchronized, this means that the faster FWC suppressesthe other one.


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Instinctive disconnect P/B


Page 77Figure 42 List of Aural WarningsISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 77


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3150


FLIGHT PHASESA flight is divided into ten flight phases. The phases depend on parametersshown on the drawing below.The flight phases have influence on internal BITEs ECAM warning inhibits automatic selection of system pages.

The Correlation between Flight Phases and System PagesGenerally, some System Pages are selected according to the Flight Phase.

The Flight Phases are generated in each Flight Warning Computer ( FWC )and transmitted to the Display Management Computers ( DMCs ) which displaythe System Page according to the momentary Flight Phase.For example,when the aircraft is supplied with electrical power (Flight Phase 1) the DOOR /OXY Page is displayed. When Flight Phase 2 starts the WHEEL Page is displayed. (after engine startthe crew has to know if the aircraft is ready for taxiing , i. e. if the wheels areok).If the APU is switched on during flight phase 1 or 2 the APU page has higherpriority and will be displayed. These correlations are shown on the table belowtaken from the AMM.

This System Page selection mode is called Automatic Mode.In some documents it is also called Flight Phase Mode.


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AMM 316700on A330

on A340

LAST


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FLIGHT PHASES FUNCTIONAL OPERATION

GeneralWithout any aircraft system failure, the System Display automatically presentssystem pages in order to eliminate the need of frequent scanning of thesystem panels.In normal operation, the ECAM system pages are displayed according to thecurrent flight phase.

Flight PhasesA flight is divided into 10 phases corresponding to changes of aircraftconfiguration or flight conditions. The flight phases are generated by the FlightWarning Computer.These phases are used by the Display Management Computers (DMCs) toautomatically call up the system pages on the System Display and totemporarily inhibit some alerts : Phases 1 and 2 correspond to A/C power up and engine start Phases 3 and 4 correspond to take off Phases 5,6 and 7 correspond to flight Phases 8 and 9 correspond to landing and taxi Phase 10 corresponds to engine shutdown.

ECAM PagesIn this topic, by selecting the corresponding flight phases, you can see thedifferent ECAM system pages which are automatically displayed in normalmode. For detailled description of the system pages, refer to the correspondingchapter.

Flight Phase 1DOOR / OXY page.The APU or engine system pages are displayed in priority if the APU or theengines are started.The door page reappears 10 sec. after APU is available or at the end of enginestart.

Flight Phase 2The WHEEL page is displayed only when engine start has been completed.The flight control page replaces the wheel page for 20 sec. when eithersidestick is moved or when rudder deflection is above 22 degrees.

Flight Phases 35ENGINE page.During this phase, most warnings are inhibited. TO. INHIBIT is diplayed onthe E/WD.

Flight Phase 6The CRUISE page appears as soon as slats are in and the engines are nolonger at take off power, provided that the landing gear is retracted.The T.O. INHIBIT message disappears. The cruise page disappears when thelanding gear is selected down.

Flight Phases 7 and 8WHEEL page.During this phase, most warnings are inhibited.LDG. INHIBIT is displayed on the E/WD.

Flight Phase 9WHEEL page.LDG. INHIBIT message disappears.

Flight Phase 10DOOR / OXY page.Five minutes after the second engine shutdown, the Flight Warning Computersstart a new flight leg at phase 1.


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SYSTEM PAGEOR

STATUS PAGE

FWC Flight Phases


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FWC Flight Phases


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Page 83Figure 46 Flight Phases 2 and 35ISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 83


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FWC Flight PhasesA340 shown


Page 84Figure 47 Flight Phase 6ISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 84


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Page 85Figure 48 Flight Phases 79 and 10ISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 85


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FLIGHT PHASE INHIBITSSome warnings are suppressed during determined Flight Phases. The reasonis that during critical flight situations ( i. e. rotation during T. O. ) the crew is notconfronted with minor warnings which they can not handle in this situation.For example:If the inertial reference part of one ADIRU fails during Take-Off no MasterCaution Light and no ECAM Caution Message appears until Flight Phase 5 isfinished ( when altitude 1500 feet is reached ).Then the Master Caution Light and a Single Chime come on and an ECAMCaution Message is displayed on the E/WD. Additional, instructions are displayed in blue.On the following three pages there are excerpts from the AMM. Each tablecontains the Flight Phase Inhibits for a specific failure.

The Flight Phases concerning a faliure can be found by this means: AMM, chapter 3151XX.XX is for the ATAchapter of the affected system.


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315134

Page 2Jul 01/92


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315134Page 3

Oct 01/92




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315126 Page 4Oct 01/92




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ADVISORY MODEThe value of some critical system parameters is monitored by an advisorymode.When the value drifts from its normal range, the corresponding ECAM page isdisplayed automatically and the affected parameter pulses.The corresponding key light on the ECAM Control Panel is on.For example the PRESS page will be displayed if the cabin pressure increasesabove its normal value, but is still well below the threshold of the warning. In this case the crew may revert to manual pressure control and preventwarning activation.

Note: an advisory may or may not lead to a failure. They are totally independent onefrom the other.

A white ADV message pulses in dual or single display mode at the bottomof the Engine Warning Display to attract crew attention.

SINGLE DISPLAY UNIT OPERATIONIf only one ECAM DU is available the remaining one shows the E/WD.In single display mode ( one ECAM CRT remaining ), a white ADV messagepulses at the bottom of the Engine Warning Display to attract crew attention.In single display mode, as the corresponding system page cannot be displayedautomatically on the SD, the pilot has to fetch the information on the ECAMcontrol panel: the associated key light flashes to indicate which system isconcerned.The System Pages can be selected only manually by pressing and holdingthe concerned pushbutton.


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A340 shown

If a parameter drifts out of normal rangean advisory reminder is shown in the E/WD.The associated key light on the ECAM ControlPanel flashes.If only one ECAM Display Unit is available( Single Display Unit Operation ) the crewhas to call the adjacent system page manually.


Page 91Figure 52 System Display Example (Pressure Page)ISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 91


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FAILURE MODEIf a failure occurs which is important to be indicated the corresponding ECAMpage is displayed. In the case of two or more failures occuring the same timethe FWC decides which one is to be displayed first.A list of the priority orders can be found in the AMM, Chapter 315100. It iscalled List of the Warnings and Memos by Priority Order. One page of thislist is shown in this book.With the Failure Mode the pilots automatically get the indications they need inthe case of a failure.


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315100 Page 32Oct 01/92


Page 93Figure 53 List of Warnings by Priority OrderISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 93

INDICATING/RECORDING SYSTEMSCENTRAL WARNING SYSTEMS

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FAILURE PROCEDURE EXAMPLEOperation/Control and IndicatingThe FWS provides the crew with operational assistance for both normal andabnormal configurations of the aircraft systems. This operational assistance isgiven through visual and aural attention getters and through the two displayzones on the EWD and SD by means of messages and system synoptic diagrams.Without A/C system failure, the FWS improves crew comfort by eliminating theneed for frequent scanning of the various system panels for monitoring temporarily used systems or functions. For this purpose MEMO messages aredisplayed in the lower zone of the EWD.The typical MEMO messages are: APU AVAIL SEAT BELTS

Routine System MonitoringThe system synoptic diagrams are displayed in the upper zone of the SD. Theyare automatically displayed and adapted to the present flight phase and canalso be called manually (EIS function).If a system page is called manually, the DMC controls the illumination of therelated key light on the ECAM control panel.

System Parameters Monitoring (ADVISORY function)Some system parameters are monitored throughout the whole flight and automatically displayed on the relevant system page when their value drifts outof normal range but well before the warning level is reached. This is performedby the ADVISORY function of the EIS.In this case, the related key light comes on on the ECAM control panel.The relevant page is displayed as long as the advisory is present and no othersystem page is called (manually or automatically).

Status messagesIn normal operation, the SD can display status messages which are: an operational summary of the aircraft condition, an explanation of possible autoland capability downgrading, indications of the aircraft status following all the failures except those that do

not affect the flight, general contents, limitations (speed, altitude), peculiar or emergency

postponable procedures, information, etc....These STATUS messages appear once the crew has cleared all the pages corresponding to the current warning/caution, or upon manual call.

Warning and Caution Message PresentationWhenever a warning or a caution situation occurs, the FWCs send the text tobe written in the lower zone of the EWD in lieu of the MEMO information.These texts consist of messages written in plain English language, and providing the crew with: an A/C system failure analysis, with warning/caution identification and

corrective actions to be taken, operational assistance by minimizing the need to refer to paper checklist

or normal read out.As a matter of fact, an improved understanding of the aircraft and system configuration at the time of the failure and then during the execution of the corrective actions, is provided by the automatic display of the relevant systempage on the SD.


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Page 95Figure 54 Failure Example part 1ISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 95


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A/C System Primary or Independent FailureAs soon as a warning or a caution is detected by the FWC, the EWDautomatically shows the warning page, i.e. the messages giving the title of theprimary or independent failure, and the possible procedures/actions to betaken.These messages are displayed provided they are not inhibited in the presentflight phase.In addition, the relevant system page is called for by the FWC and is displayedon the SD. When a relevant system page does not exist for the warning, thesystem page which is displayed is the one related to the flight phase.By means of the RCL key, it is possible to reactivate the presentation of thewarning/caution messages inhibited by the CLR function or by flight phaserelated automatic inhibition.

Blue Hydraulic Reservoir has Low PressureAn aural warning, the single chime, and a visual warning, the Master Caution,attract attention.The Engine and Warning Display indicates the title of the failure in amber andthe actions to be taken in blue.On the Status and System Display, the Hydraulic Page is called automatically.The CLR pushbuttons come on and as long as the failure is not cleared, theystay on.On the Hydraulic Panel a FAULT light comes on, indicating the pushbutton torelease out.

ProcedureThe first action to be done is to press a Master Caution pushbutton. When apushbutton is pressed, the Master Caution Lights go out.Then the pilots have to perform the actions indicated on the Engine/WarningDisplay. The blue Engine 2 Pump has to be switched off.


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ATTENTION GETTERS: MASTER CAUTION LIGHTS ARE ONAND SINGLE CHIME SOUNDS

A340 shown





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On this picture, the corrective action has been taken: The blue Engine 2 Hydraulic Pump is switched off. The FAULT light on the System Control Panelis off. The OFF light illuminates.On the Engine / Warning Display, the messages associated with the correctiveaction have disappeared.On the left hand side of the Engine / Warning Display, the result of the failureappears indicating that it is a primary failure: B SYS LO PR.On the right hand side, the secondary failures are displayed.


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The next action to be done is to press a CLR pushbutton. By this means youget information about the first secondary failure.In this example, the Flight Control Page will be displayed.The system pages of the secondary failures appear in sequence as the crewpushes the CLR key on the ECAM control panel.In this example there is only one secondary failure.


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At the end, when there is no more A/C system page to be seen, the last actionon the CLR key makes the STATUS messages to appear on the SD, and thewarning/caution message to disappear on the EWD.The memo messages return.


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AMM 315100

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If the crew pushes a last time the CLR key, the STATUS page disappears and the A/C system page related to the present flight phase appears again on the SD.

Note1. As long as the CLR key light is on, each action on it changes the ECAM

displays.2. At any time, even during the actions related to an A/C system failure, the

crew can manually select any system synoptic diagram or the STATUSpage, by means of the related key on the ECAM control panel.The light of the key comes on only in the case of a manual selection, or inthe case of an advisory.

3. In case of overflow (more than 7 lines of text) a dedicated symbol (an arrow) is displayed at the bottom of the EWD.The scrolling of the message lines can be controlled only by the successiveCLR actions. The first lines disappear as the correspondingactions/procedures are made, thus enabling the presentation of the lineswhich were not displayed.


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AMM 315100

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ECAM ARCHITECTURE

GeneralHere you can see all the components of the Flight Warning System.

ECAM Control PanelThe ECAM Control Panel is connectied to the DMCs for system synoptic selection.The connection to the FWCs is used for the handling of messages: they can becancelled and recalled.

DMC InputsThe DMCs receive all engine data directly from the FADEC and data forsystem synoptics partly directly from the aircraft systems and partly via theSDACs.

ALERT LEVELS

Level 3Fail information which should result in a level 3 warning are directly fed into theFWCs (for example Smoke Detection Control Unit).The FWCs then generate the appropriate warning message for the Engine/Warning Display,trigger the Master Warning Lights and generate an aural warning.

Level 2Level 2 fail information from a system B (for example generator control unit fail)result in a caution message in the same manner.The FWCs additionally trigger the Master Caution Lights and generate a singlechime for the loud speakers.The FWCs receive not all fail information for level 2 cautions via the SDACs.Some systems, in the schematic below named systems A, are directlyconnected to the FWCs (for example ADIRUs).

Level 1When a SDAC receives a fail information from a system B (for example batterycharge limiter fail) which should result in a level 1 message, it is digitallypassed to the FWCs.The FWCs then generate the appropriate caution message for theEngine/Warning Display.


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AMM 315000

FWC 1 FWC 2

SDAC 1 SDAC 2

DMC 1 DMC 3 DMC 2ECAM Part ECAM Part ECAM Part

B

A

LEVEL 2/1

LEVEL3/2


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INDICATING / RECORDING SYSTEMSECAM CONTROL PANEL

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3156 ECAM CONTROL PANEL (ECP)DescriptionThe ECAM Control Panel works digitaly.However, some pushbuttons send a discrete signal, so they can be used in theevent of an ECP failure.The discrete outputs are: CLR ( Clear ) STS ( Status ) RCL ( Recall ) EMER CANC ( Emergency Cancel ) ALL.

InterfaceThe pushbuttons for the FWCs are: CLR STS RCL EMER CANC TO CONFIG ( Digital Bus ).

The pushbuttons for the DMCs are: Systempushbuttons ( Digital Bus ) ALL.

ECP Pushbutton Lights ControlThe Pushbutton Lights are controlled by DMC 3 via a digital bus.In the event of DMC 3 failure, they are controlled by the DMC 1 or the DMC 2.

FailuresIf the ECP power supply fails or the ECP is inoperative the analog connectedpushbuttons remain operative. The ECAMsystem can still be used.

SchematicThe ASM schematic shows the ECP interconnection.


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INDICATING / RECORDING SYSTEMSECAM CONTROL PANEL

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ASM 315600


Page 109Figure 61 ECAM Control Panel InterconnectionISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 109

INDICATING / RECORDING SYSTEMSSDAC

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3155 SYSTEM DATA ACQUISITION CONCENTRATOR (SDAC)DescriptionTwo interchangeable SDACs are installed in the aircraft.Each SDAC receives digital and analog data and descrete signals directly fromthe aircraft systems. These data are concentrated by each SDAC, i. e. the numerous analog and digital inputs are processed and offered to different receivers in ARINC 429 format.The SDACs send some data for the system pages to the DMCs via two databuses.When both SDACs are valid the receiving computers select which SDAC isused.Both SDACs also receive data about level 1 and level 2 malfuctions andfailures from the aircraft systems. These data ( amber cautions ) aretransmitted to the FWCs. The FWCs generate the corresponding CautionMessages and Procedure Messages for the Engine / Warning Display.The software is memorized on an OBRM ( On Board Replaceable Module ) sothat software modifications can be done quickly.


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AMM 315000

FWC 1 FWC 2

SDAC 1 SDAC 2


B

A

LEVEL 2/1

LEVEL3/2


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SDAC FAILURESBoth SDACs work independently from each other.If one SDAC fails the remaining SDAC covers all functions.

One SDAC faultyAll functions are preserved, on the E / WD the message FWS SDAC1 FAULT appears. ( If SDAC 2 fails accordingly reversed. )On the STATUS page the INOP SYS message SDAC1 will appear.

Both SDACs faultyOn some system pages some parameters can not be displayed any more,instead of numbers XX is displayed.Concerning aircraft systems which send their failure message to the SDACsonly, no Master Caution and no caution messages are available anymore. Local warning lights still are operative on the overhead panel.If both SDACs fail on the E/WD the following message appears:

FWS SDAC 1 + 2 Fault in amberMONITOR OVERHEAD PANEL in blueECAM SYS PAGES AVAIL : in blueENG, F/CTL, FUEL, WHEEL in bluePRESS, C/B. in blue


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FWS SDAC1 FAULT FWS SDAC1 +2 FAULTMONITOR OVERHEAD PANELECAM SYS PAGES AVAIL:ENG,F/CTL,FUEL,WHEELPRESS,CB


Page 113Figure 63 SDAC Fault Indications on the EWDISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 113

INDICATING / RECORDING SYSTEMSFWC

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3153 FLIGHT WARNING COMPUTER (FWC)DescriptionTwo interchangeable FWCs are installed in the aircraft.The FWCs cover the following functions: Triggering of Master Warning and Master Caution Lights Generating of Messages for the E/WD (Warnings and Cautions) Generating of Memo Messages Generating of the status function Generating of Aural Warnings and Callouts ( via the AMU ) Generating of Flight Phases ( by using input parameters) Triggering of the DMCs for the flight phase related system synoptic

selection Establishing of the interface to CMC 1 for FWCs and SDACs Comparison of Heading, Attitude and Altitude Indications Calculation of Overspeed Limits Calculation of Stall Limits.

Both FWCs receive all data about level 3 warnings ( and some data about level 1 and level 2 malfunctions ) directly from the aircraft systems in analog or digital form depending on the affected system.Most data about level 1 and level 2 malfunctions are received from bothSDACs.Normally, the FWCs use data from SDAC1. If this one fails SDAC 2 is used.Each FWC is connected with the opposite FWC via a data bus.The software is memorized on an OBRM ( On Board Replaceable Module ) sothat software modificatins can be done quickly.


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AMM 315000

FWC 1 FWC 2

SDAC 1 SDAC 2


B

A

LEVEL 1/2

LEVEL 2/3


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FWC FAULT

One FWC faultyBoth FWCs work independently from each other.If one FWC fails the other FWC covers all functions.. All functions arepreserved, on the E / WD the message FWS FWC 1 FAULT appears.On captains Master Warning and Master Caution Light the Master line, andon copilots side the Warning and Caution lines can not illuminate anymore because the upper and the lower bulb are triggered from different FWCs.( If FWC 2 fails accordingly reversed. )On the STATUS page the INOP SYS message FWC1 will appear.NOTE:A BITE test of the FWCs and the SDACs is not possible, when the FWC1 isfaulty.

Both FWCs faultyIf both FWCs fail the consequences are: no auto callouts no aural warnings no MEMO messages no STATUS page no Master Warning light no Master Caution light

On the E/WD the following message appears:FWS FWC 1 + 2 FAULT in AmberMONITOR SYS in BlueMONITOR OVERHEAD PANEL in BlueBoth FWCs fail triggers the DMCs to generate this message.No data are available on the ND, when the ENG page is selected.


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FWS FWC1 FAULT FWS FWC1 +2 FAULT NOT AVAILMONITOR SYSMONITOR OVERHEAD PANEL

ECAM WARNALTI ALERTSTATUSA/CALL OUTMEMO


Page 117Figure 65 FWC Fault Indications on the EWDISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 117


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Both FWCs faultyNormally the FWCs retransmit the ECU data to the EFIS DMC parts.When both FWCs are inoperative no data are available on the ND, when theENG page is selected.


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Page 119Figure 66 Engine Standby PageISS 01 REV 02 DATE 30MAR2010 FOR TRAINING PURPOSE ONLY ATA31 LVL3 PAGE 119


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COMPARISONGeneralEach FWC works as a comparetor. If it detects differences between the displayed parameters a message is generated.The monitored parameters are: Heading Attitude Altitude.

Note: Limits for Comparison Messages concerning the PFD are described in the AMM 316400 ( Primary Flight Display ).Limits for Comparison Messages concerning the ND are described in theAMM 316500 ( Navigation Display ).

Heading ComparisonIf the FWC detects a difference between the heading indications, the Message CHECK HDG appears on the heading scale of the PFD and on t

Documents

A330 B2 ATA31.3 INDICATING LEVEL3 VAECO_noted.pdf