electronic instrument systems in modern aircraft.ppt

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AIRBUS A318/ A319 / A320 /A321AIRBUS A318/ A319 / A320 /A321
ELECTRONIC INSTRUMENTATION ELECTRONIC INSTRUMENTATION
SYSTEMSYSTEM

2
Housekeeping Rules
No smoking
PunctualityParticipation
References follow up
Silent Phones
Notes taking
Test to earn
Certificate

3
AIMAIM
At the end of the training, the participants will be able to At the end of the training, the participants will be able to
understand the installation, interconnection, operation and understand the installation, interconnection, operation and
maintenance principles of ELECTRONIC INSTRUMENTATION maintenance principles of ELECTRONIC INSTRUMENTATION
SYSTEM fitted in Airbus 320 Family aircraft and perform the SYSTEM fitted in Airbus 320 Family aircraft and perform the
maintenance activities.maintenance activities.

4

ELECTRONIC INSTRUMENTATION ELECTRONIC INSTRUMENTATION
SYSTEM (GENERAL)SYSTEM (GENERAL)

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ELECTRONIC INSTRUMENTATION SYSTEMELECTRONIC INSTRUMENTATION SYSTEM

THE ELECTRONIC INSTRUMENTATION SYSTEM PRESENTS COCKPIT DATA THE ELECTRONIC INSTRUMENTATION SYSTEM PRESENTS COCKPIT DATA
ON DISPLAY UNITS (CRT OR LCD DISPLAY UNITS)ON DISPLAY UNITS (CRT OR LCD DISPLAY UNITS)

THE THE GLASS COCKPITGLASS COCKPIT TECHNOLOGY ENSURES: TECHNOLOGY ENSURES:

SIMPLICITY, SIMPLICITY,

REDUNDANCY, REDUNDANCY,

AUTOMATION AND AUTOMATION AND

CENTRALISED DISPLAY.CENTRALISED DISPLAY.

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/USPR/ - ETS, HYDERABAD/USPR/ - ETS, HYDERABAD 66

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/USPR/ - ETS, HYDERABAD/USPR/ - ETS, HYDERABAD 77

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E I S CLASSIFICATIONE I S CLASSIFICATION
E I SE I S
EFISEFISECAMECAM
PFDPFDNDND E / WD E / WD SD SD
(UECAM) (LECAM)(UECAM) (LECAM)
EIS IS PRESENTED IN SIX IDENTICAL DISPLAY UNITS

9

THE ELECTRONIC FLIGHT INSTRUMENTATION SYSTEM PRESENTS THE ELECTRONIC FLIGHT INSTRUMENTATION SYSTEM PRESENTS

FLIGHT PARAMETERS IN THE FLIGHT PARAMETERS IN THE PRIMARY FLIGHT DISPLAY (PFD)PRIMARY FLIGHT DISPLAY (PFD) AND THE AND THE
NAVIGATION PARAMETERES IN THE NAVIGATION PARAMETERES IN THE NAVIGATIONNAVIGATION DISPLAY (ND)DISPLAY (ND) and and

THE THE ELECTRONIC CENTRALISED AIRCRAFT MONITOR (ECAM)ELECTRONIC CENTRALISED AIRCRAFT MONITOR (ECAM) PRESENTS PRESENTS

ENGINE PARAMETERS IN E/W DISPLAY ENGINE PARAMETERS IN E/W DISPLAY (UECAM)(UECAM) AND SYSTEM PAGES AND AND SYSTEM PAGES AND
STATUS INFORMATION IN SD STATUS INFORMATION IN SD (LECAM).(LECAM).
ELECTRONIC INSTRUMENTATION SYSTEMELECTRONIC INSTRUMENTATION SYSTEM

11

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PFD1PFD1 PFD2PFD2 ND1ND1 ND2ND2
ELECTRONIC FLIGHT INSTRUMENT SYSTEMELECTRONIC FLIGHT INSTRUMENT SYSTEM

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EELECTRONICLECTRONIC CCENTRALIZEDENTRALIZED AAIRCRAFTIRCRAFT MMONITORONITOR

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Engine/WarningEngine/Warning
DisplayDisplay
System System
DisplayDisplay
EELECTRONICLECTRONIC CCENTRALIZEDENTRALIZED AAIRCRAFTIRCRAFT MMONITORONITOR

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/USPR/ - ETS, HYDERABAD/USPR/ - ETS, HYDERABAD 1515
PFD / ND ON / OFF AND TRANSFER PFD / ND ON / OFF AND TRANSFER
PANELS ( 301 VU AND 500 VU)PANELS ( 301 VU AND 500 VU)

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PFD / ND ON / OFF AND TRANSFER PFD / ND ON / OFF AND TRANSFER
PANELS ( 301 VU AND 500 VU)PANELS ( 301 VU AND 500 VU)

18 FLIGHT CONTROL UNIT (13 VU)FLIGHT CONTROL UNIT (13 VU)

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ECAM CONTROL UNIT (8 VU)ECAM CONTROL UNIT (8 VU)

20 SWITCHING PANEL (8 VU)SWITCHING PANEL (8 VU)

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2 VU2 VU
6 VU6 VU
131 VU131 VU 130 VU130 VU

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/USPR/ - ETS, HYDERABAD/USPR/ - ETS, HYDERABAD 2222
COMPUTERS IN COMPUTERS IN
THE AVIONICS THE AVIONICS
COMPARTMENTCOMPARTMENT
80 VU80 VU
8
0
V
U
8
0
V
U
103 VU103 VU

DESCRIPTION
OF
COMPONENTS

24
AIRCRAFT SYSTEM SENSORS ANDAIRCRAFT SYSTEM SENSORS AND
COMPUTERSCOMPUTERS
FWC1FWC1
SDAC2SDAC2SDAC1SDAC1
DMC1DMC1 DMC3DMC3 DMC2DMC2
FWC2FWC2

DISPLAY MANAGEMENT COMPUTERSDISPLAY MANAGEMENT COMPUTERS

THREE IDENTICAL DISPLAY MANAGEMENT COMPUTERES THREE IDENTICAL DISPLAY MANAGEMENT COMPUTERES
(DMCs) ACQUIRE AND PROCESS ALL THE SIGNALS RECEIVED (DMCs) ACQUIRE AND PROCESS ALL THE SIGNALS RECEIVED
FROM SENSORS AND OTHER COMPUTERS TO FROM SENSORS AND OTHER COMPUTERS TO GENERATE THE GENERATE THE
GRAPHIC CODES FOR THE IMAGESGRAPHIC CODES FOR THE IMAGES TO BE DISPLAYED IN THE TO BE DISPLAYED IN THE
DISPLAY UNITS. (PFDs, NDs AND ECAMs)DISPLAY UNITS. (PFDs, NDs AND ECAMs)

EACH DMC HAS EACH DMC HAS FOUR INDEPENDENT CHANNELSFOUR INDEPENDENT CHANNELS , ,
ACQUISITION CHANNEL, PFD CHANNEL, ND CHANNEL AND ACQUISITION CHANNEL, PFD CHANNEL, ND CHANNEL AND
ECAM CHANNEL.ECAM CHANNEL.

THERE IS A BOARD TO PROCESS WEATHER RADAR THERE IS A BOARD TO PROCESS WEATHER RADAR
INFORMATION TOO.INFORMATION TOO.

ALL THE CHANNELS ARE INDEPENDENT IN OPERATION.ALL THE CHANNELS ARE INDEPENDENT IN OPERATION.

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•EACH DMC IS CAPABLE OF DRIVING EACH DMC IS CAPABLE OF DRIVING
SIMULTANEOUSLY ONE PFD, ONE ND AND EITHER OF SIMULTANEOUSLY ONE PFD, ONE ND AND EITHER OF
THE ECAMsTHE ECAMs
•DURING NORMAL OPERATION, DMC 1 FEEDS PFD 1, DURING NORMAL OPERATION, DMC 1 FEEDS PFD 1,
ND1 AND UECAM AND DMC 2 FEEDS PFD 2, ND2 AND ND1 AND UECAM AND DMC 2 FEEDS PFD 2, ND2 AND
LECAM. DMC 3 IS STANDBY.LECAM. DMC 3 IS STANDBY.
•IN CASE DMC 1 OR 2 IS FAULTY, THEN DMC 3 CAN BE IN CASE DMC 1 OR 2 IS FAULTY, THEN DMC 3 CAN BE
MANUALLYMANUALLY SELECTED FROM THE SWITCHING PANEL. SELECTED FROM THE SWITCHING PANEL.
•IF DMC FAILS, THE CORRESPONDING DISPLAY UNITS IF DMC FAILS, THE CORRESPONDING DISPLAY UNITS
SHOW DIAGONAL LINE.SHOW DIAGONAL LINE.

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DMC1DMC1 DMC3DMC3 DMC2DMC2
BACKUPBACKUP

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DMC1 DMC3DMC3 DMC2DMC2
BACKUPBACKUP
I N
O
P
I N
O
P

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DMC1 DMC3DMC3 DMC2DMC2
BACKUPBACKUPI N
O
P
I N
O
P

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
THERE ARE TEN BOARDS INSIDE EACH DMC THERE ARE TEN BOARDS INSIDE EACH DMC
INCLUDING THREE POWER SUPPLY BOARDS.INCLUDING THREE POWER SUPPLY BOARDS.

IF ANY ONE OF THE DMCs FAILS, IF ANY ONE OF THE DMCs FAILS, DMC 1 (2) OR 3 DMC 1 (2) OR 3
FAULTFAULT MESSAGE IS PRESENTED IN THE E/ WD. MESSAGE IS PRESENTED IN THE E/ WD.

ALONG WITH THE MESSAGE, MASTER CAUTION ALONG WITH THE MESSAGE, MASTER CAUTION
AND SINGLE CHIME ARE ALSO AVAILABLE IN ALL AND SINGLE CHIME ARE ALSO AVAILABLE IN ALL
FLIGHT PHASES EXCEPT 4, 5, 7 AND 8 FLIGHT PHASES EXCEPT 4, 5, 7 AND 8 (NOT (NOT
AVAILABLE DURING TAKE OFF AND LANDING)AVAILABLE DURING TAKE OFF AND LANDING)

IF ANY TWO DMCs FAIL, ONLY ONE DISPLAY IF ANY TWO DMCs FAIL, ONLY ONE DISPLAY
CHANNEL CAN BE MADE AVAILABLE.CHANNEL CAN BE MADE AVAILABLE.

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EIS (CLASSIC) EIS (CLASSIC)

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EIS (ENHANCED)EIS (ENHANCED)

FLIGHT WARNING COMPUTERSFLIGHT WARNING COMPUTERS

TWO IDENTICAL FWCs GENERATE WARNING AND TWO IDENTICAL FWCs GENERATE WARNING AND
CAUTION MESSAGES, MEMOS, AURAL ALERTS AND CAUTION MESSAGES, MEMOS, AURAL ALERTS AND
SYNTHETIC VOICE MESSAGES.SYNTHETIC VOICE MESSAGES.

FOR THIS PURPOSE, THEY ACQUIRE DATA:FOR THIS PURPOSE, THEY ACQUIRE DATA:

DIRECTLY FROM AIRCRAFT SENSORS OR SYSTEMS TO DIRECTLY FROM AIRCRAFT SENSORS OR SYSTEMS TO GENERATE GENERATE
RED WARNING MESSAGESRED WARNING MESSAGES and and

TRHROUGH THE SDACs TO TRHROUGH THE SDACs TO GENERATE AMBER CAUTION GENERATE AMBER CAUTION
MESSASGES.MESSASGES.

ALSO, FLIGHT WARNING COMPUTERS GENERATEALSO, FLIGHT WARNING COMPUTERS GENERATE

ATTENTION GETTERS, AUDIO WARNINGS AND AUTO LAND ATTENTION GETTERS, AUDIO WARNINGS AND AUTO LAND
LIGHTSLIGHTS

RADIO ALTITUDE AND DECISION HEIGHT CALL OUTS andRADIO ALTITUDE AND DECISION HEIGHT CALL OUTS and

10 FLIGHT PHASES10 FLIGHT PHASES

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FLIGHT PHASES BY FWCFLIGHT PHASES BY FWC

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
FWCs GENERATE ALPHANUMERIC CODES FWCs GENERATE ALPHANUMERIC CODES
CORRESPONDING TO TEXT MESSAGES TO BE CORRESPONDING TO TEXT MESSAGES TO BE
DISPLAYED IN ECAM. (ASCII AND OTHER DISPLAYED IN ECAM. (ASCII AND OTHER
SPECIFIC CODES)SPECIFIC CODES)

ALL ACQUISITIONS OF THE INFORMATION ALL ACQUISITIONS OF THE INFORMATION
FROM SENSORS AND OTHER COMPUTERS ARE FROM SENSORS AND OTHER COMPUTERS ARE
DUPLICATED.DUPLICATED.

BOTH FWCs ARE SYNCHRONIZED FOR BOTH FWCs ARE SYNCHRONIZED FOR
GENERATION OF AUDIO WARNINGS AND GENERATION OF AUDIO WARNINGS AND
AURAL MESSAGES.AURAL MESSAGES.

EACH FWC CONSISTS OF 9 CIRCUIT BOARDS, 2 EACH FWC CONSISTS OF 9 CIRCUIT BOARDS, 2
MEMORY MODULES AND 1 POWER SUPPLY MEMORY MODULES AND 1 POWER SUPPLY
MODULE.MODULE.

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
IF ANY ONE OF THE FWCs FAILS THERE IS NO IF ANY ONE OF THE FWCs FAILS THERE IS NO
OPERATIONAL CONSEQUENCE AND THE OPERATIONAL CONSEQUENCE AND THE
MESSAGE MESSAGE FWC 1 (2) FAULTFWC 1 (2) FAULT APPEARS. APPEARS. (INHIBITED (INHIBITED
IN FLIGHT PHASES 3,4,5,7 AND 8)IN FLIGHT PHASES 3,4,5,7 AND 8)

IF BOTH FWCs FAIL, THEN THERE IS LOSS OF IF BOTH FWCs FAIL, THEN THERE IS LOSS OF
AURAL WARNINGS, SYNTHETIC VOICES, AURAL WARNINGS, SYNTHETIC VOICES,
ATTENTION GETTERS AND COLOURED TEXT ATTENTION GETTERS AND COLOURED TEXT
MESSAGES IN THE DISPLAY UNITS.MESSAGES IN THE DISPLAY UNITS.

DMCDMC DISPLAYS THE MESSAGE DISPLAYS THE MESSAGE FWC 1+2FWC 1+2 FAULTFAULT IN IN
THE E/WD. THERE IS NO MASTER CAUTION AND THE E/WD. THERE IS NO MASTER CAUTION AND
THIS IS NOT INHIBITED IN ANY FLIGHT PHASE.THIS IS NOT INHIBITED IN ANY FLIGHT PHASE.

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THE LOSS OF BOTH FWCs WILL REMOVE THE AUTOMATIC MONITORING OF THE LOSS OF BOTH FWCs WILL REMOVE THE AUTOMATIC MONITORING OF
THE AIRCRAFT SYSTEMS. THE AIRCRAFT SYSTEMS.
A MESSAGE AND INFORMATION, GENERATED BY DMC, IS DISPLAYED AT A MESSAGE AND INFORMATION, GENERATED BY DMC, IS DISPLAYED AT
THE BOTTOM OF THE E/WD. THE BOTTOM OF THE E/WD.
THERE WILL BE NO FURTHER ECAM CAUTIONS OR WARNINGS, AURAL THERE WILL BE NO FURTHER ECAM CAUTIONS OR WARNINGS, AURAL
WARNINGS, MASTER CAUTION OR MASTER WARNING LIGHTS. WARNINGS, MASTER CAUTION OR MASTER WARNING LIGHTS.
I N
O
P
I N
O
P
AUTO FLT AP OFF
ANTI ICE CAPT AOA
I N
O
P

38
THE OVERHEAD PANEL SHOULD BE THE OVERHEAD PANEL SHOULD BE
CHECKED FOR ANY LOCAL CHECKED FOR ANY LOCAL
WARNINGS. WARNINGS.
THE SYSTEM PAGES CAN BE THE SYSTEM PAGES CAN BE
CHECKED FOR ABNORMAL CHECKED FOR ABNORMAL
INDICATIONS EITHER BY INDIVIDUAL INDICATIONS EITHER BY INDIVIDUAL
SELECTION OF THE PAGES OR BY SELECTION OF THE PAGES OR BY
USING THE ALL PB TO SEQUENCE USING THE ALL PB TO SEQUENCE
THROUGH THE PAGES. THROUGH THE PAGES.

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SYSTEM DATA ACQUISITION SYSTEM DATA ACQUISITION
CONCENTRATOR (SDAC)CONCENTRATOR (SDAC)

TWO IDENTICAL SDACs ACQUIRE DATA FROM TWO IDENTICAL SDACs ACQUIRE DATA FROM
VARIOUS SENSORS AND SYSTEMS AND VARIOUS SENSORS AND SYSTEMS AND
GENERATE VARIOUS SIGNALS.GENERATE VARIOUS SIGNALS.

SOME OF THESE SIGNALS ARE USED FOR THE SOME OF THESE SIGNALS ARE USED FOR THE
GENERATION OF GENERATION OF SYSTEM PAGES AND ENGINE SYSTEM PAGES AND ENGINE
PARAMETERS.PARAMETERS.

OTHER SIGNALS GO TO FLIGHT WARNING OTHER SIGNALS GO TO FLIGHT WARNING
COMPUTERS, WHICH USE THEM TO GENERATE COMPUTERS, WHICH USE THEM TO GENERATE
AMBER CAUTIONAMBER CAUTION MESSAGES. MESSAGES.

40


IF ANY ONE OF THE SDACs FAILS, THERE IS NO IF ANY ONE OF THE SDACs FAILS, THERE IS NO
OPERATIONAL CONSEQUENCES.OPERATIONAL CONSEQUENCES.

THE THE SDAC 1 (2) FAULTSDAC 1 (2) FAULT MESSAGE APPEARS IN THE E / WD MESSAGE APPEARS IN THE E / WD
AND IT IS INHIBITED IN FLIGHT PHASES 3,4,5,7 AND 8AND IT IS INHIBITED IN FLIGHT PHASES 3,4,5,7 AND 8

IF BOTH SDACs FAIL, THEN IF BOTH SDACs FAIL, THEN SDAC 1+2 FAULTSDAC 1+2 FAULT MESSAGE MESSAGE
APPEARS TOGETHER WITH MASTER CAUTION AND SINGLE APPEARS TOGETHER WITH MASTER CAUTION AND SINGLE
CHIME. IT IS INHIBITED IN THE FLIGHT PHASES IN 4,5,7 CHIME. IT IS INHIBITED IN THE FLIGHT PHASES IN 4,5,7
AND 8 AND 8

IF BOTH SDACs FAIL, THEN THERE IS NO AMBER IF BOTH SDACs FAIL, THEN THERE IS NO AMBER
CAUTIONS DISPLAYED AND THE SYSTEM PAGES, CAUTIONS DISPLAYED AND THE SYSTEM PAGES, FLT.CTL, FLT.CTL,
WHEEL, FUEL AND ENGINE WHEEL, FUEL AND ENGINE CAN ONLY BE DISPLAYED. CAN ONLY BE DISPLAYED.
(WITH LIMITED DISPLAY). (WITH LIMITED DISPLAY). THE OVERHEAD PANEL IS TO BE THE OVERHEAD PANEL IS TO BE
MONITORED FOR CAUTIONS.MONITORED FOR CAUTIONS.

EACH SDAC HAS 11 BOARDS, ONE POWER SUPPLY EACH SDAC HAS 11 BOARDS, ONE POWER SUPPLY
MODULE AND 1 MEMORY MODULE.MODULE AND 1 MEMORY MODULE.

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THE DISPLAY UNITSTHE DISPLAY UNITS

THE DISPLAY UNITS ARE FULL COLOUR, HIGH RESOLUTION THE DISPLAY UNITS ARE FULL COLOUR, HIGH RESOLUTION
CRTs.CRTs.

ALL THE DISPLAY UNITS ARE SIMILAR AND HAS THE DIMENSION ALL THE DISPLAY UNITS ARE SIMILAR AND HAS THE DIMENSION
OF 7.25 X 7.25 INCHES.OF 7.25 X 7.25 INCHES.

IF THE COOLING IS LOST, THE GREY BACKGROUND IN SOME OF IF THE COOLING IS LOST, THE GREY BACKGROUND IN SOME OF
THE DISPLAYS IS LOST. (SPEED, ALTITUDE, HDG SCALE etc.)THE DISPLAYS IS LOST. (SPEED, ALTITUDE, HDG SCALE etc.)

THE DISPLAY UNITS ARE SIGNALED FROM DMCs THROUGH THE DISPLAY UNITS ARE SIGNALED FROM DMCs THROUGH
DIGITAL SERIAL DATA LINK (DSDL) - HI SPEED ARINC 429.DIGITAL SERIAL DATA LINK (DSDL) - HI SPEED ARINC 429.

THE DISPLAY UNIT HOUSES, CONNECTION BOARD, SYMBOL THE DISPLAY UNIT HOUSES, CONNECTION BOARD, SYMBOL
GENERATOR BOARD, ANALOG BOARD, CRT AND POWER SUPPLY GENERATOR BOARD, ANALOG BOARD, CRT AND POWER SUPPLY
BOARD.BOARD.

THE BRIGHTNESS CONTROL OF THE CRT CAN BE ADJUSTED THE BRIGHTNESS CONTROL OF THE CRT CAN BE ADJUSTED
AUTOMATICALLY (PHOTO CELL) AND MANUALLY (CONTROLS)AUTOMATICALLY (PHOTO CELL) AND MANUALLY (CONTROLS)

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VERSION 1.0
On ENHANCED A/C, the Display Units (DU) are now
full color Liquid Crystal Displays (LCD).
ENHANCED ELECTRONIC ENHANCED ELECTRONIC
INSTRUMENTATION SYSTEMINSTRUMENTATION SYSTEM

43
VERSION 1.0
CLASSIC A/C ENHANCED A/C
On E/WD,
given
information
remain
unchanged,
only the layout
is modified.

44
VERSION 1.0
Here are
the CFM
ENGINE SD
pages.
Note that
a delta ISA
is displayed
in flight
when
standard
baro
reference is
selected.
CLASSIC A/C ENHANCED A/C

45
MULTIPURPOSE DISK DRIVE UNIT MULTIPURPOSE DISK DRIVE UNIT
(MDDU)(MDDU)

46
/USPR/ - ETS, HYDERABAD/USPR/ - ETS, HYDERABAD 4646

47
THE EFIS CONTROL PANELS ARE DIVIDED INTO TWO SECTIONS, THE EFIS CONTROL PANELS ARE DIVIDED INTO TWO SECTIONS,
ONE SECTION IS ASSOCIATED WITH THE PFD AND THE OTHER ONE SECTION IS ASSOCIATED WITH THE PFD AND THE OTHER
WITH THE ND.WITH THE ND.

48

49
= NORMAL AND NORMAL AND
LONG TERMLONG TERM

50
= ABNORMAL= ABNORMAL
AWARENESSAWARENESS
NOTNOT IMMEDIATE ACTION IMMEDIATE ACTION

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= WARNING= WARNING
IMMEDIATE CREW ACTIONIMMEDIATE CREW ACTION

52
COLOUR DEFINITIONCOLOUR DEFINITION

REDRED

CONFIGURATION OR FAILURE REQUIRING IMMEDIATE CONFIGURATION OR FAILURE REQUIRING IMMEDIATE
ACTION.ACTION.

AMBERAMBER

CONFIGURATION OR FAILURE REQUIRING IMMEDIATE CONFIGURATION OR FAILURE REQUIRING IMMEDIATE
ATTENTION BUT NO IMMEDIATE ACTION IS REQUIRED.ATTENTION BUT NO IMMEDIATE ACTION IS REQUIRED.

GREENGREEN

NORMAL AND LONG TREM OPERATION. NO ACTION IS NORMAL AND LONG TREM OPERATION. NO ACTION IS
REQUIRED.REQUIRED.

CYANCYAN

NORMAL BUT SHORT TERM OPERATIONNORMAL BUT SHORT TERM OPERATION

53
/USPR/ - ETS, HYDERABAD/USPR/ - ETS, HYDERABAD 5353

54
THE INDICATORS THE INDICATORS
ARE LAID OUT IN A ARE LAID OUT IN A
CLASSIC CLASSIC
INSTRUMENT INSTRUMENT “T”“T”
CONFIGURATION.CONFIGURATION.

55
AIRSPEED INDICATIONSAIRSPEED INDICATIONS
FLIGHT MODE FLIGHT MODE
ANNUNCIATORANNUNCIATOR
HEADING HEADING
INDICATIONSINDICATIONS
VERTICAL SPEED VERTICAL SPEED
INDICATIONSINDICATIONS
ALTITUDE ALTITUDE
INDICATIONSINDICATIONS
ATTITUDE ATTITUDE
INDICATIONSINDICATIONS
PRIMARY FLIGHT PRIMARY FLIGHT
DISPLAYDISPLAY

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ATTITUDE INDICATIONSATTITUDE INDICATIONS

57
ATTITUDE ATTITUDE
INFORMATION IS SHOWN INFORMATION IS SHOWN
AT THE CENTER OF THE AT THE CENTER OF THE
DISPLAY.DISPLAY.
ATTITUDE INDICATIONATTITUDE INDICATION

58
THE AIRCRAFT IS THE AIRCRAFT IS
REPRESENTED BY 3 BLACK REPRESENTED BY 3 BLACK
AND YELLOW SYMBOLS AND YELLOW SYMBOLS
WHICH REMAIN FIXED. WHICH REMAIN FIXED.
REFERENCE AIRCRAFTREFERENCE AIRCRAFT

59
THERE IS A GRADUATED THERE IS A GRADUATED
SCALE FOR PITCH ANGLE SCALE FOR PITCH ANGLE
ABOVE AND BELOW THE ABOVE AND BELOW THE
HORIZONHORIZON..
PITCH SCALEPITCH SCALE

60
BANK ANGLE IS DISPLAYED BANK ANGLE IS DISPLAYED
AT THE TOP OF THE AT THE TOP OF THE
INDICATOR, EACH INDICATOR, EACH
GRADUATION REPRESENTS 10 GRADUATION REPRESENTS 10
DEGREES ANGLE OF BANK.DEGREES ANGLE OF BANK.
BANK ANGLE INDICATIONBANK ANGLE INDICATION

61
THE ROLL INDEX TRIANGLE THE ROLL INDEX TRIANGLE
MOVES AGAINST A FIXED MOVES AGAINST A FIXED
SCALE TO SHOW ANGLE OF SCALE TO SHOW ANGLE OF
BANK.BANK.
ROLL INDEXROLL INDEX
ROLL ANGLE INDICATIONROLL ANGLE INDICATION

62
IN THIS EXAMPLE THE AIRCRAFT IN THIS EXAMPLE THE AIRCRAFT
IS IN A 20 DEGREE BANKED TURN IS IN A 20 DEGREE BANKED TURN
TO THE LEFT WITH A NOSE UPTO THE LEFT WITH A NOSE UP
PITCH ATTITUDE OF 10 DEGREES.PITCH ATTITUDE OF 10 DEGREES.
20 DEGREES OF LEFT BANK20 DEGREES OF LEFT BANK
10 DEGREES OF NOSE UP PITCH10 DEGREES OF NOSE UP PITCH
ATTITUDE INDICATIONATTITUDE INDICATION

63
BELOW THE ROLL INDEX IS BELOW THE ROLL INDEX IS
THE SIDE SLIP INDEX. THIS THE SIDE SLIP INDEX. THIS
INDEX MOVES TO INDICATE INDEX MOVES TO INDICATE
SIDE SLIP AND REPLACES THE SIDE SLIP AND REPLACES THE
OLD FASHIONED SLIP BALL.OLD FASHIONED SLIP BALL.
SIDE SLIP SIDE SLIP
INDEXINDEX

64
AIR SPEED INDICATIONSAIR SPEED INDICATIONS

65
ALTITUDE INDICATIONSALTITUDE INDICATIONS

66
VERTICAL SPEED INDICATIONSVERTICAL SPEED INDICATIONS
NORMALLY INERTIAL NORMALLY INERTIAL
AND DEGRADED MODE AND DEGRADED MODE
BAROBARO

67
HEADING HEADING
INDICATIONSINDICATIONS

68
HEADING HEADING
INDICATIONSINDICATIONS
TRACKTRACK
DIAMONDDIAMOND
YELLOW YELLOW
LINELINE

69
THE COMPASS DISPLAY IS THE COMPASS DISPLAY IS
VERY CONVENTIONAL. VERY CONVENTIONAL.

THE GRAY SCALE MOVES THE GRAY SCALE MOVES
AGAINST A FIXED YELLOW LINE AGAINST A FIXED YELLOW LINE
WHICH REPRESENTS THE WHICH REPRESENTS THE
CENTERLINE OF THE AIRCRAFT. CENTERLINE OF THE AIRCRAFT.

IN THE EXAMPLE SHOWN THE IN THE EXAMPLE SHOWN THE
AIRCRAFT IS HEADING 091 AIRCRAFT IS HEADING 091
DEGREES.DEGREES.
HEADING 091HEADING 091

70
THE SMALL GREEN THE SMALL GREEN
DIAMOND REPRESENTS THE DIAMOND REPRESENTS THE
AIRCRAFT TRACK, AND IT IS AIRCRAFT TRACK, AND IT IS
NORMALLY REFERRED TO AS NORMALLY REFERRED TO AS
THE TRACK DIAMOND.THE TRACK DIAMOND.
IN THE EXAMPLE SHOWN IN THE EXAMPLE SHOWN
THE TRACK IS 094 DEGREES THE TRACK IS 094 DEGREES
WHICH MEANS THAT THE WHICH MEANS THAT THE
AIRCRAFT HAS 3 DEGREES OF AIRCRAFT HAS 3 DEGREES OF
DRIFT TO THE RIGHT.DRIFT TO THE RIGHT.
TRACK 094TRACK 094
TRACKTRACK
DIAMONDDIAMOND

71
FLIGHT MODE ANNUNCIATORFLIGHT MODE ANNUNCIATOR
(FMA)(FMA)

72
FLIGHT DIRECTOR (FD) INDICATIONSFLIGHT DIRECTOR (FD) INDICATIONS

73
THE VERTICAL LINE IS THE THE VERTICAL LINE IS THE
FLIGHT DIRECTOR ROLL BAR, FLIGHT DIRECTOR ROLL BAR,
WHILE THE HORIZONTAL WHILE THE HORIZONTAL
LINE IS THE PITCH BAR. LINE IS THE PITCH BAR.
FLIGHT DIRECTOR ROLL BAR FLIGHT DIRECTOR ROLL BAR
FLIGHT DIRECTOR PITCH BARFLIGHT DIRECTOR PITCH BAR
FLIGHT DIRECTOR ROLL BAR AND PITCH BARFLIGHT DIRECTOR ROLL BAR AND PITCH BAR

74
IN THIS EXAMPLE THE FLIGHT IN THIS EXAMPLE THE FLIGHT
DIRECTOR IS DIRECTING A PITCH DIRECTOR IS DIRECTING A PITCH
UP AND ROLL TO THE RIGHT.UP AND ROLL TO THE RIGHT.
ONCE THE AIRCRAFT HAS ONCE THE AIRCRAFT HAS
ACHIEVED THE REQUIRED PITCH ACHIEVED THE REQUIRED PITCH
AND BANK THE FLIGHT AND BANK THE FLIGHT
DIRECTOR BARS WILL ONCE DIRECTOR BARS WILL ONCE
AGAIN BE CENTRALIZEDAGAIN BE CENTRALIZED.
ROLL TO THE RIGHT DIRECTED ROLL TO THE RIGHT DIRECTED
PITCH UP DIRECTEDPITCH UP DIRECTED
FLIGHT DIRECTOR ROLL BAR AND PITCH BARFLIGHT DIRECTOR ROLL BAR AND PITCH BAR

75
WHEN BELOW 2500 WHEN BELOW 2500
FEET A DIGITAL RADIO FEET A DIGITAL RADIO
ALTIMETER IS ALTIMETER IS
DISPLAYED. DISPLAYED.
RADIO RADIO
ALTIMETER ALTIMETER
INDICATIONINDICATION

76
7676
THE ILS PB ON THE EFIS THE ILS PB ON THE EFIS
CONTROL PANEL ENABLES CONTROL PANEL ENABLES
THE PILOTS TO SWITCH ON THE PILOTS TO SWITCH ON
AN ILS DISPLAYAN ILS DISPLAY.

ILS INDICATIONSILS INDICATIONS

77
THE ILS DISPLAY THE ILS DISPLAY
INCLUDES INDICATIONS INCLUDES INDICATIONS
FOR:FOR:
•LOCALIZER,LOCALIZER,
•FRONT COURSE,FRONT COURSE,
•GLIDE SLOPE,GLIDE SLOPE,
•INFORMATION.INFORMATION.

ILS INDICATIONSILS INDICATIONS
ILS 1 INFORMATION ILS 1 INFORMATION
ARE DISPLAYED IN ARE DISPLAYED IN
PFD1 AND ILS 2 PFD1 AND ILS 2
INFORMATION ARE INFORMATION ARE
DISPLAYED IN PFD 2DISPLAYED IN PFD 2

78
THE FLIGHT PATH VECTOR CAN BE THE FLIGHT PATH VECTOR CAN BE
DISPLAYED ON THE PFD TO SHOW DISPLAYED ON THE PFD TO SHOW
WHAT THE AIRCRAFT IS DOING IN WHAT THE AIRCRAFT IS DOING IN
RELATION TO THE WORLD. RELATION TO THE WORLD.
IT IS AN INDICATION OF THE IT IS AN INDICATION OF THE
AIRCRAFT FLIGHT PATH. IT IS NOT AIRCRAFT FLIGHT PATH. IT IS NOT
A DIRECTOR.A DIRECTOR.
THE GREEN SYMBOL, SOMETIMES THE GREEN SYMBOL, SOMETIMES
CALLED “THE BIRD”, REPRESENTS CALLED “THE BIRD”, REPRESENTS
THE AIRCRAFT. THE ATTITUDE THE AIRCRAFT. THE ATTITUDE
INDICATOR REPRESENTS THE INDICATOR REPRESENTS THE
WORLD.WORLD.
FLIGHT PATH VECTORFLIGHT PATH VECTOR

79
THE AIRCRAFT HEADING AND THE AIRCRAFT HEADING AND
TRACK ARE THE SAME SO THE TRACK ARE THE SAME SO THE
FPV AND THE TRACK DIAMOND FPV AND THE TRACK DIAMOND
ARE IN LINE WITH THE HEADING ARE IN LINE WITH THE HEADING
MARKER. MARKER.
THESE INDICATIONS MEAN THESE INDICATIONS MEAN
THAT THE AIRCRAFT IS NOT THAT THE AIRCRAFT IS NOT
DRIFTING.DRIFTING.
FLIGHT PATH VECTORFLIGHT PATH VECTOR

80
THE AIRCRAFT IS FLYING LEVEL WITH A PITCH THE AIRCRAFT IS FLYING LEVEL WITH A PITCH
ATTITUDE OF 9 DEGREES. ATTITUDE OF 9 DEGREES.
THE FPV IS ON THE HORIZON LINE SO AT THE FPV IS ON THE HORIZON LINE SO AT
PRESENT THE FLIGHT PATH ANGLE IS ZERO, PRESENT THE FLIGHT PATH ANGLE IS ZERO,
THE AIRCRAFT IS IN LEVEL FLIGHT.THE AIRCRAFT IS IN LEVEL FLIGHT.
NOW LET’S ENTER A DESCENT AND SEE WHAT NOW LET’S ENTER A DESCENT AND SEE WHAT
HAPPENS TO THE FPV.HAPPENS TO THE FPV.
PITCH ATTITUDEPITCH ATTITUDE
FLIGHT PATH VECTORFLIGHT PATH VECTOR

81
THE FPV WILL MOVE DOWN TO INDICATE THE THE FPV WILL MOVE DOWN TO INDICATE THE
ANGLE AT WHICH THE AIRCRAFT IS DESCENDING ANGLE AT WHICH THE AIRCRAFT IS DESCENDING
THROUGH THE AIR. THROUGH THE AIR.
THIS IS KNOWN AS THE FLIGHT PATH ANGLE.THIS IS KNOWN AS THE FLIGHT PATH ANGLE.
NOW LETS INTRODUCE SOME DRIFT TO THE LEFT.NOW LETS INTRODUCE SOME DRIFT TO THE LEFT.
PITCH ATTITUDEPITCH ATTITUDE
FLIGHT PATH ANGLEFLIGHT PATH ANGLE
FLIGHT PATH VECTORFLIGHT PATH VECTOR

82
AS A RESULT OF WIND AS A RESULT OF WIND
FROM THE RIGHT THE FROM THE RIGHT THE
AIRCRAFT IS DRIFTING AIRCRAFT IS DRIFTING
TO THE LEFT.TO THE LEFT.
PITCH ATTITUDEPITCH ATTITUDE
FLIGHT PATH ANGLEFLIGHT PATH ANGLE
FLIGHT PATH VECTORFLIGHT PATH VECTOR

83

2424

84
/USPR/ - ETS, HYDERABAD/USPR/ - ETS, HYDERABAD 8484

85
THERE ARE 5 DISPLAY THERE ARE 5 DISPLAY
MODES AVAILABLE ON THE MODES AVAILABLE ON THE
ND INCLUDING SUB MODES..ND INCLUDING SUB MODES..
THEY ARE SELECTED BY THE THEY ARE SELECTED BY THE
MODE SELECTOR ON THE EFIS MODE SELECTOR ON THE EFIS
CONTROL PANEL.CONTROL PANEL.
THE MODES ARE ROSE, ARC THE MODES ARE ROSE, ARC
AND PLAN AND THE ROSE AND PLAN AND THE ROSE
SUB MODESSUB MODES
MODES OF DISPLAY OF NDMODES OF DISPLAY OF ND

86
MODES OF NDMODES OF ND

IN ROSE MODE, FULL HEADING DIAL IS PRESENTED ORIENTED TO THE IN ROSE MODE, FULL HEADING DIAL IS PRESENTED ORIENTED TO THE
AIRCRAFT’S PRESENT HEADING.AIRCRAFT’S PRESENT HEADING.

ROSE MODE HAS THREE SUB MODES. THEY ARE:ROSE MODE HAS THREE SUB MODES. THEY ARE:

ROSE ILSROSE ILS

ROSE VOR and ROSE VOR and

ROSE NAV.ROSE NAV.

ROSE ILS ROSE ILS GIVES CLASSICAL HSI DISPLAY WITH LOCALISER DEVIATION WITH GIVES CLASSICAL HSI DISPLAY WITH LOCALISER DEVIATION WITH
RESPECT TO SELECTED ILS COURSE.RESPECT TO SELECTED ILS COURSE.

ROSE VOR ROSE VOR GIVES CLSSICAL HSI WITH VOR DEVIATION WITH RESPECT TO GIVES CLSSICAL HSI WITH VOR DEVIATION WITH RESPECT TO
SELECTED VOR COURSESELECTED VOR COURSE

ROSE NAV ROSE NAV PRESENTS FLIGHT PLAN WITH AIRCRAFT POSITIONED IN IT AND PRESENTS FLIGHT PLAN WITH AIRCRAFT POSITIONED IN IT AND
THE POSITION OF NAVIGATIONAL AIDS.THE POSITION OF NAVIGATIONAL AIDS.

87
ROSE MODESROSE MODES

88
LOCALIZER DEVIATION LOCALIZER DEVIATION
BARBAR
GROUND SPEED AND GROUND SPEED AND
TRUE AIR SPEEDTRUE AIR SPEED
ILS COURSE POINTERILS COURSE POINTER
ND ROSE ILS MODEND ROSE ILS MODE
WIND DIRECTION / WIND DIRECTION /
SPEEDSPEED
SELECTED ILS SELECTED ILS
INFORMATIONINFORMATION
GLIDE DEVIAITONGLIDE DEVIAITON

89
LATERAL DEVIATION LATERAL DEVIATION
BARBAR
VOR COURSE POINTERVOR COURSE POINTER
VOR INFORMATIONVOR INFORMATION
ND ROSE VOR MODEND ROSE VOR MODE

90
TO WAYPOINTTO WAYPOINT
WAYPOINTWAYPOINT
RANGE MARKS AND RANGE MARKS AND
VALUESVALUES
ND ROSE NAV MODEND ROSE NAV MODE

91
THIS IS THE NEXT THIS IS THE NEXT
WAYPOINT TO BE WAYPOINT TO BE
OVERFLOWN. OVERFLOWN.
INFORMATION INFORMATION
SHOWN ARE :SHOWN ARE :
-WAYPOINT ID-WAYPOINT ID
-TRACK TO GO-TRACK TO GO
-DISTANCE TO GO-DISTANCE TO GO
-ESTIMATED TIME -ESTIMATED TIME
OF ARRIVALOF ARRIVAL.
TO WAYPOINTTO WAYPOINT
IF 40 NM RANGE IS SELECTED, THEN THE DIAMETER OF DISPLAY IS 40 NM AND IF 40 NM RANGE IS SELECTED, THEN THE DIAMETER OF DISPLAY IS 40 NM AND
THE DISTANCE AHEAD OF AIRCRAFT IS 20NM.THE DISTANCE AHEAD OF AIRCRAFT IS 20NM.
ND ROSE NAV MODEND ROSE NAV MODE

92
ND MODESND MODES

IN THE ARC MODEIN THE ARC MODE , THE HEADING AHEAD OF THE , THE HEADING AHEAD OF THE
AIRCRAFT IS ONLY SHOWN.AIRCRAFT IS ONLY SHOWN.

IN ADDITION TO THIS, THE FLIGHT PLAN, IN ADDITION TO THIS, THE FLIGHT PLAN,
AIRCRAFT POSITION AND NAVIGATIONAL AIDS AIRCRAFT POSITION AND NAVIGATIONAL AIDS
ARE SHOWN.ARE SHOWN.

IN THE PLAN MODEIN THE PLAN MODE , FULL HEADING DIAL IS , FULL HEADING DIAL IS
PRESENTED, BUT ORIENTED TOWARDS PRESENTED, BUT ORIENTED TOWARDS
GEOGRAPHICAL(TRUE) NORTH.GEOGRAPHICAL(TRUE) NORTH.

IN THIS MODE, THE WEATHER RADAR IMAGES AND IN THIS MODE, THE WEATHER RADAR IMAGES AND
TCAS TRAFFIC SYMBOLS ARE NOT DISPLAYED.TCAS TRAFFIC SYMBOLS ARE NOT DISPLAYED.

93
•ARC, A 90 DEGREE ARC, A 90 DEGREE
SEGMENT.SEGMENT.
•IT IS SIMILAR TO IT IS SIMILAR TO
ROSE MODEROSE MODE
ARC MODEARC MODE
IF 40 NM RANGE IS SELECTED, THEN IF 40 NM RANGE IS SELECTED, THEN
THE DISTANCE AHEAD OF AIRCRAFT THE DISTANCE AHEAD OF AIRCRAFT
IS 40 NMIS 40 NM

94
•PLAN, A MAP WITH TRUE PLAN, A MAP WITH TRUE
NORTH AT THE TOP.NORTH AT THE TOP.
PLAN MODEPLAN MODE

95
GROUND SPEEDGROUND SPEED
TRUE AIR SPEEDTRUE AIR SPEED
BELOW THE SPEED INDICATIONS, THE WIND BELOW THE SPEED INDICATIONS, THE WIND
DATA ARE PRESENTED; WIND DIRECTION (TRUE DATA ARE PRESENTED; WIND DIRECTION (TRUE
NORTH), WIND SPEED AND AN ARROW TO NORTH), WIND SPEED AND AN ARROW TO
INDICATE THE WIND DIRECTION WITH RESPECT INDICATE THE WIND DIRECTION WITH RESPECT
TO MAGNETIC NORTH. TO MAGNETIC NORTH.
HERE, WIND FROM 60 DEGREES AT 52 KT.HERE, WIND FROM 60 DEGREES AT 52 KT.
GS, TAS AND WIND GS, TAS AND WIND
INFORMATION DISPLAYINFORMATION DISPLAY

96
AIRCRAFT MAGNETIC HEADING AIRCRAFT MAGNETIC HEADING
IS GIVEN BY A FIXED YELLOW IS GIVEN BY A FIXED YELLOW
LUBBER LINE AGAINST THE LUBBER LINE AGAINST THE
MOVING COMPASS ROSE. MOVING COMPASS ROSE.
AIRCRAFT HEADINGAIRCRAFT HEADING
AIRCRAFT HEADINGAIRCRAFT HEADING
AIRCRAFT HEADING DISPLAYAIRCRAFT HEADING DISPLAY

97
THE ADF 1 AND 2 BEARING THE ADF 1 AND 2 BEARING
POINTERS ARES NOW POINTERS ARES NOW
DISPLAYED REPRESENTED BY DISPLAYED REPRESENTED BY
A SINGLE AND DOUBLE A SINGLE AND DOUBLE
LINED ARROWS.LINED ARROWS.

AT THE BOTTOM OF THE AT THE BOTTOM OF THE
DISPLAY THERE IS DISPLAY THERE IS
INFORMATION ON THE INFORMATION ON THE
SELECTED NAV AIDS. SELECTED NAV AIDS.
ADF 2 BEARING POINTERADF 2 BEARING POINTER
ONE TWO
ONEONE TWOTWO
ADF 1 BEARING POINTERADF 1 BEARING POINTER
ADF POINTERS DISPLAYADF POINTERS DISPLAY

98
WEATHER RADAR WEATHER RADAR
DISPLAYDISPLAY
DISPLAYS ONLY IN DISPLAYS ONLY IN
ROSE AND ARC ROSE AND ARC
MODESMODES
NO IMAGE DURING NO IMAGE DURING
AVIONIC AVIONIC
VENTILLATION VENTILLATION
FALIUREFALIURE

99

FLAGS IN ND
1111

100
/USPR/ - ETS, HYDERABAD/USPR/ - ETS, HYDERABAD 100100

101
FWC FLIGHT PHASESFWC FLIGHT PHASES

FWC DIVIDES ITS FUNCTIONS FWC DIVIDES ITS FUNCTIONS
ACCORDING TO TEN FLIGHT PHASES.ACCORDING TO TEN FLIGHT PHASES.

TO IMPROVE ITS OPERATIONAL EFFICACY TO IMPROVE ITS OPERATIONAL EFFICACY
THE COMPUTER INHIBITS SOME OF THE THE COMPUTER INHIBITS SOME OF THE
WARNINGS AND CAUTIONS IN CERTAIN WARNINGS AND CAUTIONS IN CERTAIN
FLIGHT PHASES.FLIGHT PHASES.

IT DOES SO, TO AVOID ALERTING THE IT DOES SO, TO AVOID ALERTING THE
PILOTS UNNECESSARILY AT TIMES, THEY PILOTS UNNECESSARILY AT TIMES, THEY
HAVE HIGH WORKLOADS, SUCH AS TAKE HAVE HIGH WORKLOADS, SUCH AS TAKE
OFF AND LANDING.OFF AND LANDING.

102
Electrical
power up
After
shut down
Take Off Landing

103
FLIGHT PHASES BY FWCFLIGHT PHASES BY FWC

104
DETECTION SEQUENCE OF AN ALERTDETECTION SEQUENCE OF AN ALERT

THERE ARE THREE DISTINCT PHASES IN THERE ARE THREE DISTINCT PHASES IN
ALERTING SYSTEM.ALERTING SYSTEM.

ALERTALERT

AURAL AND VISUAL ATTENTION IS DRAWNAURAL AND VISUAL ATTENTION IS DRAWN

IDENTIFICATIONIDENTIFICATION

SPECIFIC SOUNDS AND GENERAL DISPLAY IN UECAMSPECIFIC SOUNDS AND GENERAL DISPLAY IN UECAM

ISOLATIONISOLATION

DETAILED DISPLAY IN BOTH ECAMS AND LOCAL DETAILED DISPLAY IN BOTH ECAMS AND LOCAL
WARNING / CAUTION.WARNING / CAUTION.

105
TYPES OF FAILURESTYPES OF FAILURES

FAILURES ARE CLASSIFIED INTO FAILURES ARE CLASSIFIED INTO THREE THREE TYPES.TYPES.

INDEPENDENT FAILURESINDEPENDENT FAILURES

A FAILURE THAT AFFECETS AN ISOLATED SYSTEM OR ITEM OF EQUIPMENT WITHOUT A FAILURE THAT AFFECETS AN ISOLATED SYSTEM OR ITEM OF EQUIPMENT WITHOUT
DEGRADING THE PERFORMANCE OF OTHER EQUIPMENT OR SYSTEMS.DEGRADING THE PERFORMANCE OF OTHER EQUIPMENT OR SYSTEMS.

PRIMARY FAILURESPRIMARY FAILURES

A FAILURE OF A SYSTEM OR AN ITEM OF EQUIPMENT THAT CAUSES MALFUNCTION OR A FAILURE OF A SYSTEM OR AN ITEM OF EQUIPMENT THAT CAUSES MALFUNCTION OR
LOSS OF OTHER AIRCRAFT SYSTEMS OR ITEMS OF EQUIPMENT WHICH DEPEND UPON IT.LOSS OF OTHER AIRCRAFT SYSTEMS OR ITEMS OF EQUIPMENT WHICH DEPEND UPON IT.

DISPLAYED WITHIN A BOX.DISPLAYED WITHIN A BOX.

SECONDARY FAILURESSECONDARY FAILURES

THE LOSS OF A SYSTEM OR AN ITEM OF EQUIPMENT RESULTING FROM A PRIMARY THE LOSS OF A SYSTEM OR AN ITEM OF EQUIPMENT RESULTING FROM A PRIMARY
FAILURE.FAILURE.

DISPLAYED WITH A STAR MARK BEFORE THE FAULTY SYSTEMDISPLAYED WITH A STAR MARK BEFORE THE FAULTY SYSTEM ..

106
/USPR/ - ETS, HYDERABAD/USPR/ - ETS, HYDERABAD 106106

SECONDARY FAILURESSECONDARY FAILURES
INDEPENDENT FAILURESINDEPENDENT FAILURES
PRIMARY PRIMARY
FAILURESFAILURES
ACTION LINEACTION LINE

107
CLASSIFICATION OF FAULTS IN THE CLASSIFICATION OF FAULTS IN THE
AIRCRAFT SYSTEMSAIRCRAFT SYSTEMS

FAULTS ARE CLASSIFIED INTO FAULTS ARE CLASSIFIED INTO THREETHREE TYPES ACCORDING TYPES ACCORDING
TO THE SEVERITY. THEY ARE:TO THE SEVERITY. THEY ARE:

CLASS 1 FAULTSCLASS 1 FAULTS

CLASS 2 FAULTS andCLASS 2 FAULTS and

CLASS 3 FAULTS.CLASS 3 FAULTS.

CALSS 1 FAULTS:CALSS 1 FAULTS:

CLASS 1 FAULTS ARE DIVIDED INTO CLASS 1 FAULTS ARE DIVIDED INTO THREE TYPES. THREE TYPES.
THEY ARE:THEY ARE:

LEVEL 1 FAULTSLEVEL 1 FAULTS

LEVEL 2 FAULTS andLEVEL 2 FAULTS and

LEVEL 3 FAULTSLEVEL 3 FAULTS

108


LEVEL 3 FAULTSLEVEL 3 FAULTS

THIS LEVEL CORRESPONDS TO WARNINGS THIS LEVEL CORRESPONDS TO WARNINGS
NEEDING IMMEDIATE CREW ACTION.NEEDING IMMEDIATE CREW ACTION.

THE WARNINGS ARE ASSOCIATED WITH THE WARNINGS ARE ASSOCIATED WITH
REPETITIVE CHIME OR SPECIFIC SOUND, RED REPETITIVE CHIME OR SPECIFIC SOUND, RED
WARNING MESSAGE IN EIS AND MASTER WARNING MESSAGE IN EIS AND MASTER
WARNING LIGHT FLASHING RED.WARNING LIGHT FLASHING RED.

LEVEL 2 FAULTSLEVEL 2 FAULTS

THIS LEVEL CORRESPONDS TO ABNORMAL THIS LEVEL CORRESPONDS TO ABNORMAL
SITUATIONS NEEDING IMMEDIATE CREW SITUATIONS NEEDING IMMEDIATE CREW
ATTENTION BUT NOT IMMEDIATE ACTION.ATTENTION BUT NOT IMMEDIATE ACTION.

LEVEL 2 WARNINGS ARE ASSOCIATED WITH LEVEL 2 WARNINGS ARE ASSOCIATED WITH
SINGLE CHIME, MASTER CAUTION STEADY SINGLE CHIME, MASTER CAUTION STEADY
AMBER LIGHT AND AMBER COLOUR CAUTION AMBER LIGHT AND AMBER COLOUR CAUTION
MEASSGES IN EIS.MEASSGES IN EIS.

109


LEVEL 1LEVEL 1

THIS LEVEL CORRESPONDS TO CAUTIONS.THIS LEVEL CORRESPONDS TO CAUTIONS.

IT IS ASSOCIATED WITH ONLY IT IS ASSOCIATED WITH ONLY CAUTION CAUTION
MESSAGES.MESSAGES. NORMALLY IT IS USED FOR FAILURES NORMALLY IT IS USED FOR FAILURES
LEADING TO LOSS OF REDUNDANCY OR SYSTEM LEADING TO LOSS OF REDUNDANCY OR SYSTEM
DEGRADATION.DEGRADATION.
______________________________________________________________________

CLASS 2CLASS 2

THESE FAILURES ARE INDICATED ON THE THESE FAILURES ARE INDICATED ON THE STATUS STATUS
PAGEPAGE, UNDER THE ITEM “MAINTENANCE”. THEY , UNDER THE ITEM “MAINTENANCE”. THEY
ARE ALSO ACCESSIBLE THROUGH CFDS.ARE ALSO ACCESSIBLE THROUGH CFDS.

CLASS 3CLASS 3

THESE FAILURES ARE NOT INDICATED, BUT CAN THESE FAILURES ARE NOT INDICATED, BUT CAN
BE ACCESSED THROUGH CFDS.BE ACCESSED THROUGH CFDS.

110
/USPR/ - ETS, HYDERABAD/USPR/ - ETS, HYDERABAD 110110

111
THE E/WD IS DIVIDED INTO TWO MAIN THE E/WD IS DIVIDED INTO TWO MAIN
PARTS. THE UPPER AREA IS USED FOR THE PARTS. THE UPPER AREA IS USED FOR THE
MAIN ENGINE PARAMETERS, FUEL ON MAIN ENGINE PARAMETERS, FUEL ON
BOARD, AND SLAT/FLAP POSITION. BOARD, AND SLAT/FLAP POSITION.
ENGINE / ENGINE /
WARNING WARNING
DISPLAYDISPLAY
(UECAM)(UECAM)

112
UNDER NORMAL CONDITIONS, THE LOWER PART OF THE E/WD IS USED TO DISPLAY UNDER NORMAL CONDITIONS, THE LOWER PART OF THE E/WD IS USED TO DISPLAY
MEMO. MEMO.
IN THE EXAMPLE SHOWN THE MEMOS INDICATE THAT THE SEAT BELT AND NO IN THE EXAMPLE SHOWN THE MEMOS INDICATE THAT THE SEAT BELT AND NO
SMOKING SIGNS ARE SWITCHED ON AND THAT THE APU IS AVAILABLE FOR USE.SMOKING SIGNS ARE SWITCHED ON AND THAT THE APU IS AVAILABLE FOR USE.
MEMO MESSAGESMEMO MESSAGES
ENGINE / ENGINE /
WARNING WARNING
DISPLAYDISPLAY
(UECAM)(UECAM)

113
IF FAILURES OCCUR WARNING/CAUTION MESSAGES ARE DISPLAYED IN PLACE IF FAILURES OCCUR WARNING/CAUTION MESSAGES ARE DISPLAYED IN PLACE
OF THE MEMOS. OF THE MEMOS.
IN THE EXAMPLE SHOWN THERE IS AN AMBER CAUTION MESSAGE WITH A IN THE EXAMPLE SHOWN THERE IS AN AMBER CAUTION MESSAGE WITH A
SERIES OF BLUE ACTION ITEMS. THESE ACTION ITEMS ARE ELECTRONIC SERIES OF BLUE ACTION ITEMS. THESE ACTION ITEMS ARE ELECTRONIC
CHECKLIST TO RESPOND TO THE PARTICULAR ABNORMAL SITUATIONCHECKLIST TO RESPOND TO THE PARTICULAR ABNORMAL SITUATION
WARNINGS/CAUTION MESSAGESWARNINGS/CAUTION MESSAGES
ENGINE / ENGINE /
WARNING WARNING
DISPLAYDISPLAY
(UECAM)(UECAM)

114
THE SD IS USED TO DISPLAY PARTICULAR SYSTEM INFORMATION. IN THE EXAMPLE THE SD IS USED TO DISPLAY PARTICULAR SYSTEM INFORMATION. IN THE EXAMPLE
SHOWN THE CRUISE PAGE IS DISPLAYED. SHOWN THE CRUISE PAGE IS DISPLAYED.
THIS IS THE PAGE NORMALLY SEEN FOR THE MAJORITY OF THE TIME THAT THE THIS IS THE PAGE NORMALLY SEEN FOR THE MAJORITY OF THE TIME THAT THE
AIRCRAFT IS AIRBORNE. AIRCRAFT IS AIRBORNE.
INFORMATION, THAT IS USEFUL DURING FLIGHT, FROM SEVERAL SYSTEMS IS INFORMATION, THAT IS USEFUL DURING FLIGHT, FROM SEVERAL SYSTEMS IS
DISPLAYED. . DISPLAYED. .
CRUISE CRUISE
PagePage
SYSTEM / SYSTEM /
STATUS STATUS
DISPLAYDISPLAY
(LECAM)(LECAM)

115
THE SD CAN ALSO BE USED TO DISPLAY THE SD CAN ALSO BE USED TO DISPLAY
SYNOPTIC DIAGRAMS OF THE AIRCRAFT SYNOPTIC DIAGRAMS OF THE AIRCRAFT
SYSTEMS, SYSTEM PAGES. IN THE EXAMPLE SYSTEMS, SYSTEM PAGES. IN THE EXAMPLE
SHOWN THE HYDRAULICS SYSTEM PAGE HAS SHOWN THE HYDRAULICS SYSTEM PAGE HAS
BEEN CALLED. BEEN CALLED.
SYSTEM / SYSTEM /
STATUS STATUS
DISPLAYDISPLAY
(LECAM)(LECAM)

116
THE SYSEM PAGES DISPLAYEDTHE SYSEM PAGES DISPLAYED

ENGINE ENGINE (SECONDARY ENGINE PARAMETERS)(SECONDARY ENGINE PARAMETERS)

BLEEDBLEED

CABIN PRESSCABIN PRESS

ELECTRICALELECTRICAL

HYDRAULICHYDRAULIC

FUELFUEL

APUAPU

AIR CONDITIONINGAIR CONDITIONING

DOOR / OXYGENDOOR / OXYGEN

WHEELWHEEL

FLIGHT CONTROLFLIGHT CONTROL

CRUISE CRUISE (CANNOT BE SELECTED FROM ECAM CONTROL (CANNOT BE SELECTED FROM ECAM CONTROL
PANEL)PANEL)

117
/USPR/ - ETS, HYDERABAD/USPR/ - ETS, HYDERABAD
AN AIRCRAFT STATUS PAGE MAY BE DISPLAYED ON THE SD TO AN AIRCRAFT STATUS PAGE MAY BE DISPLAYED ON THE SD TO
CHECK THE STATE OF THE AIRCRAFT. CHECK THE STATE OF THE AIRCRAFT.
A NORMAL MESSAGE IS DISPLAYED TO INDICATE THAT THE A NORMAL MESSAGE IS DISPLAYED TO INDICATE THAT THE
AIRCRAFT STATE IS NORMAL AND THAT THERE ARE NO INOPERATIVE AIRCRAFT STATE IS NORMAL AND THAT THERE ARE NO INOPERATIVE
SYSTEMS.SYSTEMS.
(PAGE IS SELECTED FROM ECAM CONTROL PANEL)(PAGE IS SELECTED FROM ECAM CONTROL PANEL)
SYSTEM / SYSTEM /
STATUS STATUS
DISPLAYDISPLAY
(LECAM)(LECAM)

118
LIMITATIONSLIMITATIONS
STATUS PAGESTATUS PAGE

119
LIMITATIONSLIMITATIONS
APPROACHAPPROACH
PROCEDURESPROCEDURES
STATUS PAGESTATUS PAGE

120
LIMITATIONSLIMITATIONS
APPROACHAPPROACH
PROCEDURESPROCEDURES
INFORMATIONINFORMATION
STATUS PAGESTATUS PAGE

121
THE INFORMATION DISPLAYED ON THE STATUS PAGE WILL VARY THE INFORMATION DISPLAYED ON THE STATUS PAGE WILL VARY
DEPENDING ON THE FAILURE BUT AS AN EXAMPLE CAN INCLUDE:DEPENDING ON THE FAILURE BUT AS AN EXAMPLE CAN INCLUDE:
•LIMITATIONS,LIMITATIONS,
•APPROACH PROCEDURES INCLUDING ACTIONS AND CORRECTIONS,APPROACH PROCEDURES INCLUDING ACTIONS AND CORRECTIONS,
•INFORMATION,INFORMATION,
•INOPERATIVE SYSTEMS.INOPERATIVE SYSTEMS.
LIMITATIONS
APPROACH
PROCEDURES
INFORMATION
INOPERATIVE SYSTEMSINOPERATIVE SYSTEMS

122
THE AREA AT THE BOTTOM OF ANY SD CONTAINS THE AREA AT THE BOTTOM OF ANY SD CONTAINS
PERMANENT DATA:PERMANENT DATA:
•TOTAL AIR TEMPERATURE (TAT),TOTAL AIR TEMPERATURE (TAT),
•STATIC AIR TEMPERATURE (SAT),STATIC AIR TEMPERATURE (SAT),
•TIME, TIME,
•GROSS WEIGHT.GROSS WEIGHT.
PERMANENT PERMANENT
DATADATA

123
IF A SYSTEM PARAMETER, FOR EXAMPLE IF A SYSTEM PARAMETER, FOR EXAMPLE
AN ENGINE VIBRATION LEVEL, AN ENGINE VIBRATION LEVEL,
APPROACHES A LIMIT THE ECAM SYSTEM APPROACHES A LIMIT THE ECAM SYSTEM
WILL ADVISE OF THIS BY DISPLAYING THE WILL ADVISE OF THIS BY DISPLAYING THE
RELEVANT SYSTEM PAGE ON THE SD. RELEVANT SYSTEM PAGE ON THE SD.
THE AFFECTED PARAMETER WILL PULSE. THE AFFECTED PARAMETER WILL PULSE.
NOTICE THAT AT THIS STAGE, THE NOTICE THAT AT THIS STAGE, THE
PARAMETER IS STILL SHOWN IN GREEN PARAMETER IS STILL SHOWN IN GREEN
SINCE IT IS STILL WITHIN NORMAL LIMITS.SINCE IT IS STILL WITHIN NORMAL LIMITS.
THIS IS KNOWN AS AN ECAM ADVISORY.THIS IS KNOWN AS AN ECAM ADVISORY.
ADVISORYADVISORY

124
/USPR/ - ETS, HYDERABAD/USPR/ - ETS, HYDERABAD 124124

125
ECAM SYSTEM PAGES LOGICECAM SYSTEM PAGES LOGIC

THE ECAM SYSTEM PAGES ARE DISPLAYED WITH THE FOLLOWING THE ECAM SYSTEM PAGES ARE DISPLAYED WITH THE FOLLOWING
PRIORITIESPRIORITIES

AUTOMATIC MODE RELATED TO A FAILUREAUTOMATIC MODE RELATED TO A FAILURE

AN ECAM SYSTEM PAGE CALL IS ASSOCIATED WITH MOST OF AN ECAM SYSTEM PAGE CALL IS ASSOCIATED WITH MOST OF
THE WARNINGS. THE PARTICULAR PAGE IS THEN THE WARNINGS. THE PARTICULAR PAGE IS THEN
AUTOMATICALLY CALLED AND HAS PRIORITY OVER THE PAGE AUTOMATICALLY CALLED AND HAS PRIORITY OVER THE PAGE
DISPLAY MODES.DISPLAY MODES.

126


AUTOMATIC ADVISORY PAGEAUTOMATIC ADVISORY PAGE

THE ADVISORY MODE INDICATES A PARAMETER WHICH THE ADVISORY MODE INDICATES A PARAMETER WHICH
DRIFTS OUT OF ITS NORMAL RANGE BEFORE TRIGGERING A DRIFTS OUT OF ITS NORMAL RANGE BEFORE TRIGGERING A
WARNING.WARNING.

THE PARAMETER AND THE TITLE OF THE SYSTEM PAGE ARE THE PARAMETER AND THE TITLE OF THE SYSTEM PAGE ARE
DISPLAYED PULSING IN GREEN.DISPLAYED PULSING IN GREEN.

THE CORRESPONDING PUSHBUTTON ON THE ECAM THE CORRESPONDING PUSHBUTTON ON THE ECAM
CONTROL PANEL ALSO ILLUMINATES.CONTROL PANEL ALSO ILLUMINATES.

MANUAL MODEMANUAL MODE

WHEN PRESSED IN, AN ECAM CONTROL PANEL WHEN PRESSED IN, AN ECAM CONTROL PANEL
PUSHBUTTON WILL ILLUMINATE AND DISPLAY THE PUSHBUTTON WILL ILLUMINATE AND DISPLAY THE
CORRESPONDING SYSTEM PAGE IN NORMAL MODE.CORRESPONDING SYSTEM PAGE IN NORMAL MODE.

PRESSING TWICE WILL RETURN TO THE PREVIOUS PAGEPRESSING TWICE WILL RETURN TO THE PREVIOUS PAGE

127
AUTOMATIC MODE RELATED TO FLIGHT AUTOMATIC MODE RELATED TO FLIGHT
PHASEPHASE

IF NO OTHER MODE IS SELECTED, THE ECAM SYSTEM PAGES ARE IF NO OTHER MODE IS SELECTED, THE ECAM SYSTEM PAGES ARE
AUTOMATICALLY DISPLAYED ACCORDING TO THE FLIGHT PHASE.AUTOMATICALLY DISPLAYED ACCORDING TO THE FLIGHT PHASE.

THE SYSTEM PAGES SYNOPTIC COLOUR CODING ISTHE SYSTEM PAGES SYNOPTIC COLOUR CODING IS

O K O K GREENGREEN

NOT IN USE NOT IN USE NOT DISPLAYEDNOT DISPLAYED

OFFOFF WHITEWHITE

ABNORMAL ABNORMAL RED OR AMBERRED OR AMBER

FAILED PARAMETERFAILED PARAMETER XX (AMBER)XX (AMBER)

128
FLIGHT PHASE RELATED PAGESFLIGHT PHASE RELATED PAGES

129
THE FAULT IS AN OVERHEAT OF THE BLUE THE FAULT IS AN OVERHEAT OF THE BLUE
HYDRAULIC SYSTEM RESERVOIR. HYDRAULIC SYSTEM RESERVOIR.

130
WHEN THE FAULT OCCURS THE ECAM SYSTEM ALERTS THE CREW WHEN THE FAULT OCCURS THE ECAM SYSTEM ALERTS THE CREW
AURALLY AND VISUALLY. AURALLY AND VISUALLY.
A SINGLE CHIME IS HEARD AND THE MASTER CAUTION LIGHTS A SINGLE CHIME IS HEARD AND THE MASTER CAUTION LIGHTS
ARE ON. ARE ON.
TO CANCEL THE MASTER CAUTION LIGHTS, AND RESET THE TO CANCEL THE MASTER CAUTION LIGHTS, AND RESET THE
ALERTING SYSTEM, ONE OF THE MASTER CAUTION PB MUST BE ALERTING SYSTEM, ONE OF THE MASTER CAUTION PB MUST BE
PRESSED.PRESSED.

131
THE MASTER CAUTION IS EXTINGUISHED THE MASTER CAUTION IS EXTINGUISHED
AND THE ALERTING SYSTEM IS RESET.AND THE ALERTING SYSTEM IS RESET.

132
THE FIRST PRIORITY IS ALWAYS TO ENSURE THE SAFE THE FIRST PRIORITY IS ALWAYS TO ENSURE THE SAFE
FLIGHT PATH OF THE AIRCRAFT BEFORE DEALING WITH FLIGHT PATH OF THE AIRCRAFT BEFORE DEALING WITH
THE FAULT. THE FAULT.
THE MASTER CAUTION MEANS THAT THE ABNORMAL THE MASTER CAUTION MEANS THAT THE ABNORMAL
SITUATION NEEDS CREW AWARENESS BUT NOT SITUATION NEEDS CREW AWARENESS BUT NOT
IMMEDIATE ACTION.IMMEDIATE ACTION.
= ABNORMAL= ABNORMAL
AWARENESSAWARENESS
NOTNOT IMMEDIATE ACTION IMMEDIATE ACTION

133
THE INDICATIONS ARE:THE INDICATIONS ARE:
•A FAILURE MESSAGE ON THE E/WD,A FAILURE MESSAGE ON THE E/WD,
•THE SYSTEM SYNOPTIC ASSOCIATED THE SYSTEM SYNOPTIC ASSOCIATED
WITH THE FAULT IS AUTOMATICALLY WITH THE FAULT IS AUTOMATICALLY
DISPLAYED ON THE SD,DISPLAYED ON THE SD,
• THE CLEAR KEYS ON THE ECAM THE CLEAR KEYS ON THE ECAM
CONTROL PANEL LIGHT UP.CONTROL PANEL LIGHT UP.

134
THE SYSTEM TITLE IS THE SYSTEM TITLE IS
UNDERLINED, IN THIS CASE UNDERLINED, IN THIS CASE
HYDHYDRAULICS, AND THE FAULT RAULICS, AND THE FAULT
IS SHOWN ALONGSIDE, BLUE IS SHOWN ALONGSIDE, BLUE
RESERVOIR OVERHEAT. RESERVOIR OVERHEAT.
NOTICE THAT NOTICE THAT
ABBREVIATIONS ARE USED. ABBREVIATIONS ARE USED.

135
AT THE HYDRAULIC AT THE HYDRAULIC
SYSTEM DISPLAY SYSTEM DISPLAY
AMBER OVHT MESSAGE AMBER OVHT MESSAGE
IS DISPLAYED. IS DISPLAYED.

136
ON THE OVERHEAD PANEL AN ON THE OVERHEAD PANEL AN
AMBER FAULT LIGHT HAS AMBER FAULT LIGHT HAS
ILLUMINATED ON THE HYDRAULIC ILLUMINATED ON THE HYDRAULIC
CONTROL PANEL.CONTROL PANEL.

137
THE FAULT LIGHT ON THE THE FAULT LIGHT ON THE
HYD PANEL HELPS TO LOCATE HYD PANEL HELPS TO LOCATE
THE SWITCH TO BE OPERATED. THE SWITCH TO BE OPERATED.

138

139
WHEN THE PUMP IS SWITCHED OFF WHEN THE PUMP IS SWITCHED OFF
THE ACTION LINE IS REMOVED. THE THE ACTION LINE IS REMOVED. THE
BLUE HYDRAULIC SYSTEM BLUE HYDRAULIC SYSTEM
DEPRESSURIZES, AS SHOWN ON THE DEPRESSURIZES, AS SHOWN ON THE
HYD PAGE BY THE AMBER HYD PAGE BY THE AMBER
INDICATIONS. THE ECAM SYSTEM INDICATIONS. THE ECAM SYSTEM
DETECTS THE DROP IN PRESSURE AND DETECTS THE DROP IN PRESSURE AND
GENERATES A FURTHER ALERT. GENERATES A FURTHER ALERT.

140
THE SINGLE CHIME IS HEARD AND THE MASTER THE SINGLE CHIME IS HEARD AND THE MASTER
CAUTION LIGHTS ARE ON.CAUTION LIGHTS ARE ON.

141
THE MASTER CAUTION CAN BE PUT TO OFFTHE MASTER CAUTION CAN BE PUT TO OFF

142
THERE IS NOW A NEW ABNORMAL THERE IS NOW A NEW ABNORMAL
MESSAGE ON THE E/WD B SYS LO PR.MESSAGE ON THE E/WD B SYS LO PR.
THE MESSAGE IS BOXED TO THE MESSAGE IS BOXED TO
INDICATE THAT THE LOSS OF THE BLUE INDICATE THAT THE LOSS OF THE BLUE
HYDRAULIC SYSTEM IS CLASSED AS A HYDRAULIC SYSTEM IS CLASSED AS A
PRIMARY FAILURE THAT WILL AFFECT PRIMARY FAILURE THAT WILL AFFECT
OTHER SYSTEMS.OTHER SYSTEMS.

143
THE SYSTEMS AFFECTED ARE THE SYSTEMS AFFECTED ARE
SHOWN ON THE RIGHT OF THE SHOWN ON THE RIGHT OF THE
E/WD AS STARRED ITEMS CALLED E/WD AS STARRED ITEMS CALLED
SECONDARY FAILURES. SECONDARY FAILURES.
IN THIS EXAMPLE THE PRIMARY IN THIS EXAMPLE THE PRIMARY
FAILURE OF THE BLUE HYDRAULIC FAILURE OF THE BLUE HYDRAULIC
SYSTEM HAS CAUSED A SYSTEM HAS CAUSED A
SECONDARY FAILURE OF FLIGHT SECONDARY FAILURE OF FLIGHT
CONTROLSCONTROLS.

144
AFTER CLR ACTION ON THE PUSH AFTER CLR ACTION ON THE PUSH
BUTTON ON ECAM CONTROL PANEL, BUTTON ON ECAM CONTROL PANEL,
NORMAL MEMOS HAVE RETURNED NORMAL MEMOS HAVE RETURNED
ON THE LEFT SIDE OF THE E/WD.ON THE LEFT SIDE OF THE E/WD.
THE ECAM F/CTL SYSTEM PAGE IS THE ECAM F/CTL SYSTEM PAGE IS
DISPLAYED ON THE SD WHICH DISPLAYED ON THE SD WHICH
CORRESPONDS TO THE SECONDARY CORRESPONDS TO THE SECONDARY
FAILURE ITEM ON THE E/WD .FAILURE ITEM ON THE E/WD .

145
ON THE ECAM F/CTL PAGE, ON THE ECAM F/CTL PAGE,
NOTICE THAT THE NOTICE THAT THE
CONTROLS AFFECTED BY CONTROLS AFFECTED BY
THE LOSS OF BLUE THE LOSS OF BLUE
HYDRAULICS HAVE AMBER HYDRAULICS HAVE AMBER
INDICATIONS. INDICATIONS.

146
THE FLT CTL PAGE CAN BE THE FLT CTL PAGE CAN BE
CLEARED BY PRESSING THE CLEARED BY PRESSING THE
CLR PUSHBUTTON ON THE CLR PUSHBUTTON ON THE
ECAM CONTROL PANEL.ECAM CONTROL PANEL.

147
147147
NOTICE THAT THE SECONDARY FAILURE NOTICE THAT THE SECONDARY FAILURE
INDICATION ON THE E/WD IS REMOVED.INDICATION ON THE E/WD IS REMOVED.
THE STATUS PAGE IS NOW DISPLAYED THE STATUS PAGE IS NOW DISPLAYED
CONTAINING SEVERAL PIECES OF CONTAINING SEVERAL PIECES OF
INFORMATION.INFORMATION.
THE FIRST AREA GIVES PROCEDURES TO THE FIRST AREA GIVES PROCEDURES TO
BE APPLIED FOR APPROACH, LANDING BE APPLIED FOR APPROACH, LANDING
DISTANCE FACTORS, AND OTHER DISTANCE FACTORS, AND OTHER
INFORMATION. INFORMATION.

148
148148
IN THIS EXAMPLE THE INOPERATIVE IN THIS EXAMPLE THE INOPERATIVE
SYSTEMS ARE:SYSTEMS ARE:
•CAT 3, WHICH MEANS THAT CATEGORY 3 CAT 3, WHICH MEANS THAT CATEGORY 3
AUTOLAND IS NOT AVAILABLE,AUTOLAND IS NOT AVAILABLE,
•BLUE HYD, THE SYSTEM WAS SWITCHED BLUE HYD, THE SYSTEM WAS SWITCHED
OFF DURING THE ECAM PROCEDURE,OFF DURING THE ECAM PROCEDURE,
•SPLR 3, THE SPOILERS THAT ARE SPLR 3, THE SPOILERS THAT ARE
INOPERATIVE BECAUSE THERE IS NO BLUE INOPERATIVE BECAUSE THERE IS NO BLUE
HYDRAULIC PRESSURE.HYDRAULIC PRESSURE.

149
TO CLEAR THE STATUS TO CLEAR THE STATUS
PAGE, THE CLR PAGE, THE CLR
PUSHBUTTON ON THE PUSHBUTTON ON THE
ECAM CONTROL PANEL ECAM CONTROL PANEL
IS TO BE PRESSED.IS TO BE PRESSED.

150
THE ECAM ACTIONS FOR A BLUE THE ECAM ACTIONS FOR A BLUE
HYDRAULIC RESERVOIR OVERHEAT ARE HYDRAULIC RESERVOIR OVERHEAT ARE
COMPLETE. COMPLETE.
NOTICE THAT THE STATUS REMINDER IS NOTICE THAT THE STATUS REMINDER IS
DISPLAYED AT THE BOTTOM OF THE E/WD DISPLAYED AT THE BOTTOM OF THE E/WD
REMINDING THAT THERE IS REMINDING THAT THERE IS
INFORMATION ON THE STATUS PAGE. INFORMATION ON THE STATUS PAGE.
THIS IS IMPORTANT SINCE THERE WERE THIS IS IMPORTANT SINCE THERE WERE
APPROACH PROCEDURES TO BE APPLIED.APPROACH PROCEDURES TO BE APPLIED.
NOW THE CRUISE PAGE IS DISPLAYED.NOW THE CRUISE PAGE IS DISPLAYED.

151
THERE IS AN OVERFLOW THERE IS AN OVERFLOW
ARROW TO INDICATE ARROW TO INDICATE
THAT IF THERE IS MORE THAT IF THERE IS MORE
INFORMATION TO BE INFORMATION TO BE
SEEN. SEEN.
THE CLR KEY IN THE THE CLR KEY IN THE
ECAM CONTROL PANEL IS ECAM CONTROL PANEL IS
PRESSED FOR SCROLLING.PRESSED FOR SCROLLING.

152
/USPR/ - ETS, HYDERABAD/USPR/ - ETS, HYDERABAD 152152

153
ECAM CONTROLSECAM CONTROLS
PanelPanel
OFF / BRT KNOBSOFF / BRT KNOBS
EMER CANC KEYEMER CANC KEY
ALL KEYALL KEY
SYSTEM PAGES KEYSSYSTEM PAGES KEYS
T.O. CONFIG KEYT.O. CONFIG KEY
CLR KEYSCLR KEYS
STS KEYSTS KEY
RCL KEYRCL KEY
NO INTEGRAL LIGHTS IN TO NO INTEGRAL LIGHTS IN TO
CONFIG, EMER CANC, RCL CONFIG, EMER CANC, RCL
AND ALLAND ALL

154
SWITCHING SWITCHING
PanelPanel
EIS DMC SELECTOREIS DMC SELECTOR
ECAM / ND SYSTEM ECAM / ND SYSTEM
SELECTORSELECTOR

155
MISCELLANEOUSMISCELLANEOUS
PanelPanel
PFD BRIGHTNESS CONTROL PFD BRIGHTNESS CONTROL
KNOBKNOB
PFD/ND XFR PBPFD/ND XFR PB
ND BRIGHTNESS CONTROL ND BRIGHTNESS CONTROL
KNOBKNOB

156
CONTROLS THE CONTROLS THE
ON/OFF AND ON/OFF AND
BRIGHTNESS FOR BRIGHTNESS FOR
THE ASSOCIATED THE ASSOCIATED
PFD.PFD.
PFD BRIGHTNESS CONTROL PFD BRIGHTNESS CONTROL
KNOBKNOB
MISCELLANEOUSMISCELLANEOUS
PanelPanel

157
USED TO INTERCHANGE THE USED TO INTERCHANGE THE
PFD AND THE ND.PFD AND THE ND.
IF THE PFD UNIT FAILS, THE IF THE PFD UNIT FAILS, THE
PFD IS AUTOMATICALLY PFD IS AUTOMATICALLY
TRANSFERRED TO THE ND UNIT. TRANSFERRED TO THE ND UNIT.
IF THE ND UNIT FAILS, THERE IF THE ND UNIT FAILS, THERE
IS NO AUTOMATIC TRANSFER OF IS NO AUTOMATIC TRANSFER OF
THE ND IMAGE TO PFD.THE ND IMAGE TO PFD.
PFD/ND XFR pbPFD/ND XFR pb
MISCELLANEOUSMISCELLANEOUS
PanelPanel

158
- INNER KNOB : CONTROLS THE INNER KNOB : CONTROLS THE
ON/OFF AND BRIGHTNESS FOR THE ON/OFF AND BRIGHTNESS FOR THE
ASSOCIATED ND.ASSOCIATED ND.
- OUTER KNOB : CONTROLS THE - OUTER KNOB : CONTROLS THE
BRIGHTNESS OF THE WEATHER BRIGHTNESS OF THE WEATHER
RADAR IMAGE ONLY.RADAR IMAGE ONLY.
ND BRIGHTNESS CONTROL ND BRIGHTNESS CONTROL
KNOBKNOB
MISCELLANEOUSMISCELLANEOUS
PanelPanel

159
/USPR/ - ETS, HYDERABAD/USPR/ - ETS, HYDERABAD 159159

160
ATTENTION GETTERSATTENTION GETTERS

THE FWCs DRIVE THE ATTENTION GETTERS. THE FWCs DRIVE THE ATTENTION GETTERS.

EACH PILOT HAS A SET OF THESE IN THE GLARESHIELD EACH PILOT HAS A SET OF THESE IN THE GLARESHIELD
PANELPANEL

A MASTER WARNING LIGHT A MASTER WARNING LIGHT FLSHINGFLSHING IN IN REDRED FOR FOR
WARNINGS andWARNINGS and

A MASTER CAUTION LIGHT STEADY IN A MASTER CAUTION LIGHT STEADY IN AMBER AMBER FOR FOR
CAUTIONS.CAUTIONS.



MASTER WARNINGMASTER WARNING (LEVEL 3 WARNING)(LEVEL 3 WARNING) LIGHTS ARE LIGHTS ARE
ACCOMPANIED BY AN AURAL WARNING (CONTINOUS ACCOMPANIED BY AN AURAL WARNING (CONTINOUS
REPETITIVE CHIME, SPECIFIC SOUNDS OR SYNTHETIC REPETITIVE CHIME, SPECIFIC SOUNDS OR SYNTHETIC
VOICE)VOICE)

MASTER CAUTIONMASTER CAUTION (LEVEL 2 CAUTION)(LEVEL 2 CAUTION) LIGHTS ARE LIGHTS ARE
ASSOCIATED WITH SINGLE CHIME.ASSOCIATED WITH SINGLE CHIME.

161
ATTENTION ATTENTION
GETTERSGETTERS
MASTER WARN LIGHTMASTER WARN LIGHT
MASTER CAUT LIGHTMASTER CAUT LIGHT

162
THE LIGHT EXTINGUISHES THE LIGHT EXTINGUISHES
AND THE AURAL WARNING AND THE AURAL WARNING
STOPS WHEN :STOPS WHEN :
- THE MASTER WARN PB SW IS - THE MASTER WARN PB SW IS
PRESSED,PRESSED,
- OR THE WARNING - OR THE WARNING
SITUATION IS OVER,SITUATION IS OVER,
- OR THE EMER CANC KEY IS - OR THE EMER CANC KEY IS
PRESSED.PRESSED.
MASTER WARN lightMASTER WARN light
ATTENTION ATTENTION
GETTERSGETTERS

163
THE LIGHT EXTINGUISHES THE LIGHT EXTINGUISHES
WHEN :WHEN :
-THE MASTER CAUT THE MASTER CAUT PB SW PB SW
IS PRESSED,IS PRESSED,
- OR THE CAUTION - OR THE CAUTION
SITUATION IS OVER,SITUATION IS OVER,
- OR THE EMER CANC KEY IS - OR THE EMER CANC KEY IS
PRESSED.PRESSED.
MASTER CAUT lightMASTER CAUT light
ATTENTION ATTENTION
GETTERSGETTERS

164
/USPR/ - ETS, HYDERABAD/USPR/ - ETS, HYDERABAD 164164

165
/USPR/ - ETS, HYDERABAD/USPR/ - ETS, HYDERABAD 165165
IF A SINGLE DISPLAY UNIT FAILS THERE ARE IF A SINGLE DISPLAY UNIT FAILS THERE ARE
SEVERAL WAYS THAT THE EIS CAN BE RECONFIGURED SEVERAL WAYS THAT THE EIS CAN BE RECONFIGURED
TO ENSURE THAT THE PILOTS HAVE ALL THE TO ENSURE THAT THE PILOTS HAVE ALL THE
INFORMATION THAT THEY NEEDINFORMATION THAT THEY NEED .

166
PFD / ND RECONFIGURATIONPFD / ND RECONFIGURATION

IF A PFD FAILS, THE SYSTEM AUTOMATICALLY TRANSFERS IF A PFD FAILS, THE SYSTEM AUTOMATICALLY TRANSFERS
THE PFD IMAGES TO THE ND.THE PFD IMAGES TO THE ND.

THIS TRANSFER CAN BE MADE MANUALLY BY:THIS TRANSFER CAN BE MADE MANUALLY BY:

TURNING THE PFD ON / OFF SWITCH TO OFF orTURNING THE PFD ON / OFF SWITCH TO OFF or

PUSHING THE PFD / ND XFR PUSH BUTTON, WHICH CROSS PUSHING THE PFD / ND XFR PUSH BUTTON, WHICH CROSS
CHANGES THE IMAGES BETWEEN THE PFD AND ND.CHANGES THE IMAGES BETWEEN THE PFD AND ND.

IF THE ND FAILS, THE PFD / ND XFR PUSHBUTTON CAN BE IF THE ND FAILS, THE PFD / ND XFR PUSHBUTTON CAN BE
USED TO TRANSFER THE ND IMAGES TO PFD.USED TO TRANSFER THE ND IMAGES TO PFD.

167
IF A PRIMARY FLIGHT DISPLAY SCREEN FAILS, THE SCREEN WILL IF A PRIMARY FLIGHT DISPLAY SCREEN FAILS, THE SCREEN WILL
BLANK.BLANK.
THERE IS NO WHITE DIAGONAL LINE SINCE THIS IS A SCREEN THERE IS NO WHITE DIAGONAL LINE SINCE THIS IS A SCREEN
FAILURE NOT A LOSS OF DATA.FAILURE NOT A LOSS OF DATA.
BECAUSE THE PRIMARY FLIGHT DISPLAY HAS PRIORITY, THE EIS BECAUSE THE PRIMARY FLIGHT DISPLAY HAS PRIORITY, THE EIS
WILL AUTOMATICALLY TRANSFER THE PFD TO THE ND SCREEN.WILL AUTOMATICALLY TRANSFER THE PFD TO THE ND SCREEN.

168
/USPR/ - ETS, HYDERABAD/USPR/ - ETS, HYDERABAD 168168
IF A NAVIGATION DISPLAY FAILS NO AUTOMATIC IF A NAVIGATION DISPLAY FAILS NO AUTOMATIC
TRANSFER TAKES PLACE. TRANSFER TAKES PLACE.
IF REQUIRED THE PFD / ND TRANSFER SWITCH CAN BE IF REQUIRED THE PFD / ND TRANSFER SWITCH CAN BE
USED TO MANUALLY TRANSFER NAVIGATION USED TO MANUALLY TRANSFER NAVIGATION
INFORMATION TO THE PFD SCREEN.INFORMATION TO THE PFD SCREEN.

169
UPPER ECAM FAILS OR UPPER ECAM FAILS OR
IT IS PUT TO OFF IT IS PUT TO OFF

IF THE UECAM DU FAILS OR SWITCHED OFF:IF THE UECAM DU FAILS OR SWITCHED OFF:

THE E / WD PAGE AUTOMATICALLY REPLACES THE SD PAGE THE E / WD PAGE AUTOMATICALLY REPLACES THE SD PAGE
IN THE LECAM.IN THE LECAM.

THE SD PAGE CAN BE DISPLAYED BY:THE SD PAGE CAN BE DISPLAYED BY:

USING THE ECAM / ND TRANSFER SWITCH ON THE USING THE ECAM / ND TRANSFER SWITCH ON THE
SWITCHING PANEL, SD CAN BE DISPLAYED IN ANY ND orSWITCHING PANEL, SD CAN BE DISPLAYED IN ANY ND or

PUSHING AND HOLDING (FOR A MAXIMUM OF 3 MINUTES -PUSHING AND HOLDING (FOR A MAXIMUM OF 3 MINUTES -
REVISED), THE RELATED SYSTEM PAGE PUSHBUTTON IN REVISED), THE RELATED SYSTEM PAGE PUSHBUTTON IN
ECAM CONTROL PANEL TO DISPLAY THE SD TEMPORORILY ECAM CONTROL PANEL TO DISPLAY THE SD TEMPORORILY
ON LECAM ( IN THE PLACE OF E / WD)ON LECAM ( IN THE PLACE OF E / WD)

170
SHOULD A FAILURE OF THE UPPER ECAM DISPLAY SCREEN SHOULD A FAILURE OF THE UPPER ECAM DISPLAY SCREEN
OCCUR AN AUTOMATIC TRANSFER OF THE E/WD TO THE OCCUR AN AUTOMATIC TRANSFER OF THE E/WD TO THE
LOWER ECAM SCREEN TAKES PLACE.LOWER ECAM SCREEN TAKES PLACE.
LIKE THE PFD THE E/WD HAS PRIORITY OVER THE SD.LIKE THE PFD THE E/WD HAS PRIORITY OVER THE SD.

171
SYSTEM PAGES CAN BE DISPLAYED BY USING THE SYSTEM PAGES CAN BE DISPLAYED BY USING THE
SYSTEM PB SWITCHES ON THE ECAM CONTROL PANEL.SYSTEM PB SWITCHES ON THE ECAM CONTROL PANEL.

172
A PARTICULAR PAGE PUSHBUTTON IN ECAM CONTROL PANEL IS PUSHED AND A PARTICULAR PAGE PUSHBUTTON IN ECAM CONTROL PANEL IS PUSHED AND
HELD TO TEMPORARILY DISPLAY A SYSTEM PAGE. WHILE THE SYSTEM PAGE IS HELD TO TEMPORARILY DISPLAY A SYSTEM PAGE. WHILE THE SYSTEM PAGE IS
DISPLAYED A WHITE LIGHT ILLUMINATES ON THE PB.DISPLAYED A WHITE LIGHT ILLUMINATES ON THE PB.
NOTE; IF A PB IS HELD DOWN FOR MORE THAN 30 SECONDS THE E/WD SCREEN NOTE; IF A PB IS HELD DOWN FOR MORE THAN 30 SECONDS THE E/WD SCREEN
WILL BE RECALLED AUTOMATICALLY. THIS HAPPENS BECAUSE THE ECAM SYSTEM WILL BE RECALLED AUTOMATICALLY. THIS HAPPENS BECAUSE THE ECAM SYSTEM
ASSIGNS PRIORITY TO THE E/WD.ASSIGNS PRIORITY TO THE E/WD.

173
AS SOON AS THE PB IS RELEASED THE LIGHT GOES AS SOON AS THE PB IS RELEASED THE LIGHT GOES
OUT AND THE E/WD REAPPEARS ON THE LOWER OUT AND THE E/WD REAPPEARS ON THE LOWER
ECAM SCREEN.ECAM SCREEN.

174
IF A PARTICULAR SYSTEM IS NEEDED THE SYSTEM SCREEN CAN BE IF A PARTICULAR SYSTEM IS NEEDED THE SYSTEM SCREEN CAN BE
TRANSFERED TO ONE OF THE ND SCREENS USING THE ECAM / ND TRANSFERED TO ONE OF THE ND SCREENS USING THE ECAM / ND
TRANSFER SWITCH ON THE SWITCHING PANEL.TRANSFER SWITCH ON THE SWITCHING PANEL.

175
BY SELECTING THE ECAM/ND TRANSFER SWITCH TO F/O THE BY SELECTING THE ECAM/ND TRANSFER SWITCH TO F/O THE
SD HAS BEEN TRANSFERRED TO THE FIRST OFFICERS SD HAS BEEN TRANSFERRED TO THE FIRST OFFICERS
NAVIGATION DISPLAY SCREEN. NOTICE THAT THE ND IS NAVIGATION DISPLAY SCREEN. NOTICE THAT THE ND IS
REPLACED BY THE SD, IT IS NOT TRANSFERREDREPLACED BY THE SD, IT IS NOT TRANSFERRED ..

176
NORMAL SELECTION OF SYSTEM NORMAL SELECTION OF SYSTEM
PAGES IS THEN AVAILABLE VIA THE PAGES IS THEN AVAILABLE VIA THE
ECAM CONTROL PANEL.ECAM CONTROL PANEL.

177
LOWER ECAM FAILS ORLOWER ECAM FAILS OR
IT IS PUT TO OFFIT IS PUT TO OFF

IF THE LECAM FAILS OR SWITCHED OFF, THERE IS NO AUTOMATIC IF THE LECAM FAILS OR SWITCHED OFF, THERE IS NO AUTOMATIC
TRANSFER OF SD.TRANSFER OF SD.

THE SD CAN BE DISPLAYED BYTHE SD CAN BE DISPLAYED BY

USING THE ECAM / ND XFR SWITCH ON THE SWITCHING PANEL TO DISPLAY THE USING THE ECAM / ND XFR SWITCH ON THE SWITCHING PANEL TO DISPLAY THE
SD IN ANY ND orSD IN ANY ND or

PUSHING AND HOLDING (FOR A MAXIMUM OF 3 MINUTES - REVISED) THE PUSHING AND HOLDING (FOR A MAXIMUM OF 3 MINUTES - REVISED) THE
RELATED SD PAGE PUSH BUTTON ON ECAM CONTROL PANEL TO DISPLAY IT RELATED SD PAGE PUSH BUTTON ON ECAM CONTROL PANEL TO DISPLAY IT
TEMPORORILY ON UECAM (IN THE PLACE OF E / WD PAGE)TEMPORORILY ON UECAM (IN THE PLACE OF E / WD PAGE)

178
FAILURE OF BOTH ECAMsFAILURE OF BOTH ECAMs

IF BOTH ECAMs FAIL:IF BOTH ECAMs FAIL:

THE ECAM / ND XFR SWITCH ON THE SWITCHING PANEL CAN BE THE ECAM / ND XFR SWITCH ON THE SWITCHING PANEL CAN BE
USED TO DISPLAY THE E /WD PAGE IN THE ND orUSED TO DISPLAY THE E /WD PAGE IN THE ND or

THE RELATED SYSTEM PAGE PUSH BUTTON IN THE ECAM CONTROL THE RELATED SYSTEM PAGE PUSH BUTTON IN THE ECAM CONTROL
PANEL CAN BE PUSHED AND HOLD (FOR A MAXIMUM OF 3 PANEL CAN BE PUSHED AND HOLD (FOR A MAXIMUM OF 3
MINUTES - REVISED) TO DISPLAY THE SD IN THE ND.MINUTES - REVISED) TO DISPLAY THE SD IN THE ND.

179
IN THE UNLIKELY EVENT THAT BOTH ECAM DISPLAYS FAIL THE ECAM / IN THE UNLIKELY EVENT THAT BOTH ECAM DISPLAYS FAIL THE ECAM /
ND TRANSFER SWITCH CAN BE USED TO DISPLAY THE E/WD ON ONE OF ND TRANSFER SWITCH CAN BE USED TO DISPLAY THE E/WD ON ONE OF
THE NAVIGATION DISPLAY UNITS. THE NAVIGATION DISPLAY UNITS.

180
THE FIRST OFFICER NOW HAS THE THE FIRST OFFICER NOW HAS THE
E/WD ON HIS ND SCREEN. E/WD ON HIS ND SCREEN.

181
IF IT IS NEEDED TO LOOK AT A SYSTEM IF IT IS NEEDED TO LOOK AT A SYSTEM
PAGE THIS CAN BE DONE BY PRESSING PAGE THIS CAN BE DONE BY PRESSING
AND HOLDING THE RELATED SYSTEM AND HOLDING THE RELATED SYSTEM
PAGE PUSHBUTTON ON THE ECAM PAGE PUSHBUTTON ON THE ECAM
CONTROL PANEL, FOR A MAXIMUM OF CONTROL PANEL, FOR A MAXIMUM OF
3 MINUTES.3 MINUTES.

182
AS SOON AS THE SYSTEM PB AS SOON AS THE SYSTEM PB
IS RELEASED THE E/WD IS RELEASED THE E/WD
RETURNS AND THE LIGHT ON RETURNS AND THE LIGHT ON
THE ECAM CONTROL PANEL IS THE ECAM CONTROL PANEL IS
EXTINGUISHED.EXTINGUISHED.

183
IF ONLY ONE ECAM SCREEN IS IF ONLY ONE ECAM SCREEN IS
AVAILABLE AND IF AN ADVISORY AVAILABLE AND IF AN ADVISORY
CONDITION ARISES, THE CONDITION ARISES, THE
RELEVANT SYSTEM PAGE IS NOT RELEVANT SYSTEM PAGE IS NOT
AUTOMATICALLY DISPLAYED. AUTOMATICALLY DISPLAYED.
INSTEAD THE LIGHT ON THE PB INSTEAD THE LIGHT ON THE PB
SWITCH FOR THE SYSTEM AND A SWITCH FOR THE SYSTEM AND A
BOXED ADV MESSAGE ON THE BOXED ADV MESSAGE ON THE
E/WD WILL FLASH.E/WD WILL FLASH.

184
WHEN ONLY ONE ECAM IS AVAILABLE AND WHEN ONLY ONE ECAM IS AVAILABLE AND
IF AN ECAM WARNING OR CAUTION IS IF AN ECAM WARNING OR CAUTION IS
TRIGGERED THEN THERE WILL BE NO TRIGGERED THEN THERE WILL BE NO
AUTOMATIC DISPLAY OF THE RELEVANT AUTOMATIC DISPLAY OF THE RELEVANT
SYSTEM PAGE. OR LIGHTING ON PB SW IN SYSTEM PAGE. OR LIGHTING ON PB SW IN
ECAM CONTROL PANEL.ECAM CONTROL PANEL.
SYSTEM PAGES SHOULD BE CALLED BY SYSTEM PAGES SHOULD BE CALLED BY
MANUAL SELECTION ON THE ECAM CONTROL MANUAL SELECTION ON THE ECAM CONTROL
PANEL. (THE TITLE OF THE FAULTY SYSTEM IS PANEL. (THE TITLE OF THE FAULTY SYSTEM IS
DISPLAYED IN E /WD)DISPLAYED IN E /WD)

185
WHEN A FAILURE IS WHEN A FAILURE IS
DETECTED ECAM WILL GIVE DETECTED ECAM WILL GIVE
THE NORMAL AURAL AND THE NORMAL AURAL AND
VISUAL INDICATIONS. ON VISUAL INDICATIONS. ON
THE E/WD THE FAILURE THE E/WD THE FAILURE
MESSAGE WILL BE DISPLAYED MESSAGE WILL BE DISPLAYED
AND ON THE ECAM CONTROL AND ON THE ECAM CONTROL
PANEL THE TWO CLR KEYS PANEL THE TWO CLR KEYS
WILL BE ILLUMINATED. WILL BE ILLUMINATED.
F/O ND SCREEN F/O PFD SCREEN

186
BY LOOKING AT THE UNDERLINED BY LOOKING AT THE UNDERLINED
SYSTEM TITLE ,SYSTEM PAGE NEEDS TO SYSTEM TITLE ,SYSTEM PAGE NEEDS TO
BE VIEWED CAN BE IDENTIFIED. BE VIEWED CAN BE IDENTIFIED.
IN THIS EXAMPLE THE FUEL PAGE PB IN THIS EXAMPLE THE FUEL PAGE PB
SHOULD BE SELECTED AND HELD ON SHOULD BE SELECTED AND HELD ON
THE ECAM CONTROL PANEL. THE ECAM CONTROL PANEL.
THE SYSTEM PAGE CAN BE STUDIED THE SYSTEM PAGE CAN BE STUDIED
TO PROVIDE MORE INFORMATION TO PROVIDE MORE INFORMATION
ABOUT THE FAILURE AND THEN THE PB ABOUT THE FAILURE AND THEN THE PB
RELEASED.RELEASED.

187
THE E/WD RETURNS AND THE E/WD RETURNS AND
THE ECAM ACTIONS CAN BE THE ECAM ACTIONS CAN BE
CARRIED OUT. CARRIED OUT.

188
/USPR/ - ETS, HYDERABAD/USPR/ - ETS, HYDERABAD 188188

189
AURAL WARNINGSAURAL WARNINGS

VARIOUS TYPES OF AURAL WARNINGS ARE GENERATED BY VARIOUS TYPES OF AURAL WARNINGS ARE GENERATED BY
THE FWCs TO DRAW THE ATTENTION OF CREW DURING THE FWCs TO DRAW THE ATTENTION OF CREW DURING
FAILURES.FAILURES.

THE AURAL WARNINGS ARE SINGLE CHIME, REPETITIVE THE AURAL WARNINGS ARE SINGLE CHIME, REPETITIVE
CHIME, SYNTHETIC VOICES AND SPECIFIC SOUNDS.CHIME, SYNTHETIC VOICES AND SPECIFIC SOUNDS.

THE AURAL WARNINGS CAN BE CANCELLED BY “THE AURAL WARNINGS CAN BE CANCELLED BY “ EMEREMER CANCCANC” ”
PUSH BUTTON ON PUSH BUTTON ON THE ECAM CONTROL PANELTHE ECAM CONTROL PANEL OR OR

THE MASTER WARNING PUSH BUTTON EXCEPT FOR THE MASTER WARNING PUSH BUTTON EXCEPT FOR
OVERSPEED OR L/G NOT DOWN WARNNGS.OVERSPEED OR L/G NOT DOWN WARNNGS.

SOME OF THE AUDIO WARNINGS HAVE MAXIMUM TIME SOME OF THE AUDIO WARNINGS HAVE MAXIMUM TIME
DURATION AND SOME WARNINGS SOUND TILL CORRECTIVE DURATION AND SOME WARNINGS SOUND TILL CORRECTIVE
ACTION IS TAKEN.ACTION IS TAKEN.

190
VERSION 1.0
STANDBY INSTRUMENTSSTANDBY INSTRUMENTS

191
VERSION 1.0
INTEGRATED STANDBY INTEGRATED STANDBY
INSTRUMENT SYSTEM (ISIS)INSTRUMENT SYSTEM (ISIS)

192
VERSION 1.0
HORIZON AIRSPEED
INDICATOR
ALTIMETER
In A 321, the standby instruments (horizon, airspeed
and altimeter) are replaced by one Integrated Standby
Instrument System called ISIS.
ISIS
CLASSIC A/C ENHANCED A/C

193
VERSION 1.0
• Reduction in weight and volume
• Enhanced ergonomic design
symbology similar to the PFD (LCD technology)
• All electronic (no moving parts)
• Maintenance costs decreased
increased MTBF
reduction of LRU spares (High MTBF & 1 LRU)
reduction of repair time (efficient BITE)
ISIS ADVANTAGESISIS ADVANTAGES

194
VERSION 1.0
INTEGRATED STANDBY INTEGRATED STANDBY
INSTRUMENT SYSTEM (ISIS)INSTRUMENT SYSTEM (ISIS)

195
VERSION 1.0
INTEGRATED STANDBY INTEGRATED STANDBY
INSTRUMENT SYSTEM (ISIS)INSTRUMENT SYSTEM (ISIS)

196
VERSION 1.0
INTEGRATED STANDBY INTEGRATED STANDBY
INSTRUMENT SYSTEM (ISIS)INSTRUMENT SYSTEM (ISIS)

197
VERSION 1.0
INTEGRATED STANDBY INTEGRATED STANDBY
INSTRUMENT SYSTEM (ISIS)INSTRUMENT SYSTEM (ISIS)

198
VERSION 1.0
INTEGRATED STANDBY INTEGRATED STANDBY
INSTRUMENT SYSTEM (ISIS)INSTRUMENT SYSTEM (ISIS)

199
VERSION 1.0
ATTITUDE RESET
ROLL SCALE
FIXED AIRCRAFT
SYMBOL
ROLL INDEX
LATERAL
ACCELERATION
PITCH SCALE
ATTITUDE
INTEGRATED STANDBY INTEGRATED STANDBY
INSTRUMENT SYSTEM (ISIS)INSTRUMENT SYSTEM (ISIS)

200
VERSION 1.0
INTEGRATED STANDBY INTEGRATED STANDBY
INSTRUMENT SYSTEM (ISIS)INSTRUMENT SYSTEM (ISIS)

201
VERSION 1.0
ATTITUDE DISPLAYATTITUDE DISPLAY

202
VERSION 1.0
SIDE SLIPSIDE SLIP

203
VERSION 1.0
On ISIS, the pitch attitude scale is identical to the one displayed on PFD.
The ATT RST pb is used for resetting the attitude indication by pressing it for at
least 2 seconds. During this period “ATT 10s” is displayed on the screen.
Note: the flight must be stabilized (without pitch and roll angles and with
stabilized speed).
ATTITUDE RESET
ATTITUDE

204
VERSION 1.0

205
VERSION 1.0
INTEGRATED STANDBY INTEGRATED STANDBY
INSTRUMENT SYSTEM (ISIS)INSTRUMENT SYSTEM (ISIS)

206
VERSION 1.0
CAUTION
The Airbus SOP do not recommend to set bugs during a flight.
BUGS

207
VERSION 1.0
The BUGS pb sw is used to display or inhibit the bugs function.
The BUGS page has two columns positioned vertically:
•the speed bug column where four speed values (in knots) can be selected
•and the altitude bug column where two altitude values (X 100) can be selected
BUGS pb sw
BUGS

208
VERSION 1.0
BUGS VALUE
SELECTION KNOB
The BUGS value selection knob allows the bug to be set in the active box by rotating
the BARO knob.
Movement from one box to another is made by the “+ or -” pushbuttons. The active
box flashes.
Pressing the BARO setting knob once the bug value box is activated, will deselect the
bug value. The OFF label comes on close to the activated box.
The entered values are memorized by the system when exiting the screen by pressing
the BUGS pb sw or after 15 s without any action.
BOX ACTIVATION
PUSHBUTTONS
BUGS pb sw
BUGS

209
VERSION 1.0
Once a value is entered and activated, a cyan dash is displayed on the
corresponding scale, representing the bug. Here, two examples are given: a
speed bug and an altitude bug.
BUGS

210
VERSION 1.0
BUGSBUGS

211
VERSION 1.0
INTEGRATED STANDBY INTEGRATED STANDBY
INSTRUMENT SYSTEM (ISIS)INSTRUMENT SYSTEM (ISIS)

212
VERSION 1.0
ENGINEERING DATAENGINEERING DATA

213
VERSION 1.0
INTEGRATED STANDBY INTEGRATED STANDBY
INSTRUMENT SYSTEM (ISIS)INSTRUMENT SYSTEM (ISIS)

214
VERSION 1.0
TESTSTESTS

215
VERSION 1.0
FUNCTIONAL TESTFUNCTIONAL TEST

216
VERSION 1.0
DISPLAY TESTDISPLAY TEST

217
VERSION 1.0
INTEGRATED STANDBY INTEGRATED STANDBY
INSTRUMENT SYSTEM (ISIS)INSTRUMENT SYSTEM (ISIS)

218
VERSION 1.0
ISIS ARCHITECTUREISIS ARCHITECTURE

219
VERSION 1.0
INTERNAL ARCHITECTUREINTERNAL ARCHITECTURE

220
VERSION 1.0
INTEGRATED STANDBY INTEGRATED STANDBY
INSTRUMENT SYSTEM (ISIS)INSTRUMENT SYSTEM (ISIS)

221
VERSION 1.0
INTEGRATED STANDBY INTEGRATED STANDBY
INSTRUMENT SYSTEM (ISIS)INSTRUMENT SYSTEM (ISIS)

•

electronic instrument systems in modern aircraft.ppt

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