electronic instrument systems in modern aircraft.ppt

1
AIRBUS A318/ A319 / A320 /A321
AIRBUS A318/ A319 / A320 /A321
ELECTRONIC INSTRUMENTATION
SYSTEM
SYSTEM

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

3
AIM
AIM
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
SYSTEM (GENERAL)
SYSTEM (GENERAL)

5
ELECTRONIC 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 COCKPIT
GLASS COCKPIT TECHNOLOGY ENSURES:
TECHNOLOGY ENSURES:
 SIMPLICITY,
SIMPLICITY,
 REDUNDANCY,
REDUNDANCY,
 AUTOMATION AND
AUTOMATION AND
 CENTRALISED DISPLAY.
CENTRALISED DISPLAY.

6
/USPR/ - ETS, HYDERABAD
/USPR/ - ETS, HYDERABAD 6
6

7
7

8
E I S CLASSIFICATION
E I S CLASSIFICATION
E I S
E I S
EFIS
EFIS ECAM
ECAM
PFD
PFD ND
ND 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 NAVIGATION
NAVIGATION 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).

12
PFD1
PFD1 PFD2
PFD2
ND1
ND1 ND2
ND2
ELECTRONIC FLIGHT INSTRUMENT SYSTEM
ELECTRONIC FLIGHT INSTRUMENT SYSTEM

13
E
ELECTRONIC
LECTRONIC C
CENTRALIZED
ENTRALIZED A
AIRCRAFT
IRCRAFT M
MONITOR
ONITOR

14
Engine/Warning
Engine/Warning
Display
Display
System
System
Display
Display
E
ELECTRONIC
LECTRONIC C
CENTRALIZED
ENTRALIZED A
AIRCRAFT
IRCRAFT M
MONITOR
ONITOR

15
15
PFD / ND ON / OFF AND TRANSFER
PANELS ( 301 VU AND 500 VU)

16

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

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

21
2 VU
2 VU 6 VU
6 VU
131 VU
131 VU 130 VU
130 VU

22
22
COMPUTERS IN
COMPUTERS IN
THE AVIONICS
THE AVIONICS
COMPARTMENT
COMPARTMENT
80 VU
80 VU
80 VU
80 VU
103 VU
103 VU

24
AIRCRAFT SYSTEM SENSORS AND
AIRCRAFT SYSTEM SENSORS AND
COMPUTERS
COMPUTERS
FWC1
FWC1 SDAC2
SDAC2
SDAC1
SDAC1
DMC1
DMC1 DMC3
DMC3 DMC2
DMC2
FWC2
FWC2

DISPLAY MANAGEMENT COMPUTERS
DISPLAY 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 IMAGES
GRAPHIC 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 CHANNELS
FOUR 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.

26
•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 ECAMs
THE 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
MANUALLY
MANUALLY 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.

27
DMC1
DMC1 DMC3
DMC3 DMC2
DMC2
BACKUP
BACKUP

28
DMC1 DMC3
DMC3 DMC2
DMC2
BACKUP
BACKUP
IN
O
P
IN
O
P

29
DMC1 DMC3
DMC3 DMC2
DMC2
BACKUP
BACKUP
IN
O
P
IN
O
P

30
 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
FAULT
FAULT 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.

31
EIS (CLASSIC)
EIS (CLASSIC)

32
EIS (ENHANCED)
EIS (ENHANCED)

FLIGHT WARNING COMPUTERS
FLIGHT 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 MESSAGES
RED WARNING MESSAGES and
and
 TRHROUGH THE SDACs TO
TRHROUGH THE SDACs TO GENERATE AMBER CAUTION
GENERATE AMBER CAUTION
MESSASGES.
MESSASGES.
 ALSO, FLIGHT WARNING COMPUTERS GENERATE
ALSO, FLIGHT WARNING COMPUTERS GENERATE
 ATTENTION GETTERS, AUDIO WARNINGS AND AUTO LAND
ATTENTION GETTERS, AUDIO WARNINGS AND AUTO LAND
LIGHTS
LIGHTS
 RADIO ALTITUDE AND DECISION HEIGHT CALL OUTS and
RADIO ALTITUDE AND DECISION HEIGHT CALL OUTS and
 10 FLIGHT PHASES
10 FLIGHT PHASES

34
FLIGHT PHASES BY FWC

35
 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.

36
 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) FAULT
FWC 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.
 DMC
DMC DISPLAYS THE MESSAGE
DISPLAYS THE MESSAGE FWC 1+2
FWC 1+2 FAULT
FAULT 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.

37
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.
IN
O
P
IN
O
P
AUTO FLT AP OFF
ANTI ICE CAPT AOA
IN
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.

39
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 CAUTION
AMBER 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) FAULT
SDAC 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 8
AND 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 FAULT
SDAC 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.

41
THE DISPLAY UNITS
THE 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)

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

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

46
46

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.

49
= NORMAL AND
NORMAL AND
LONG TERM
LONG TERM

50
= ABNORMAL
= ABNORMAL
AWARENESS
AWARENESS
NOT
NOT IMMEDIATE ACTION
IMMEDIATE ACTION

51
= WARNING
= WARNING
IMMEDIATE CREW ACTION
IMMEDIATE CREW ACTION

52
COLOUR DEFINITION
COLOUR DEFINITION
 RED
RED
 CONFIGURATION OR FAILURE REQUIRING IMMEDIATE
CONFIGURATION OR FAILURE REQUIRING IMMEDIATE
ACTION.
ACTION.
 AMBER
AMBER
 CONFIGURATION OR FAILURE REQUIRING IMMEDIATE
CONFIGURATION OR FAILURE REQUIRING IMMEDIATE
ATTENTION BUT NO IMMEDIATE ACTION IS REQUIRED.
ATTENTION BUT NO IMMEDIATE ACTION IS REQUIRED.
 GREEN
GREEN
 NORMAL AND LONG TREM OPERATION. NO ACTION IS
NORMAL AND LONG TREM OPERATION. NO ACTION IS
REQUIRED.
REQUIRED.
 CYAN
CYAN
 NORMAL BUT SHORT TERM OPERATION
NORMAL BUT SHORT TERM OPERATION

53
53

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 INDICATIONS
AIRSPEED INDICATIONS
FLIGHT MODE
FLIGHT MODE
ANNUNCIATOR
ANNUNCIATOR
HEADING
HEADING
INDICATIONS
INDICATIONS
VERTICAL SPEED
VERTICAL SPEED
INDICATIONS
INDICATIONS
ALTITUDE
ALTITUDE
INDICATIONS
INDICATIONS
ATTITUDE
ATTITUDE
INDICATIONS
INDICATIONS
PRIMARY FLIGHT
PRIMARY FLIGHT
DISPLAY
DISPLAY

56
ATTITUDE INDICATIONS
ATTITUDE INDICATIONS

57
ATTITUDE
ATTITUDE
INFORMATION IS SHOWN
INFORMATION IS SHOWN
AT THE CENTER OF THE
AT THE CENTER OF THE
DISPLAY.
DISPLAY.
ATTITUDE INDICATION
ATTITUDE 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 AIRCRAFT
REFERENCE 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
HORIZON
HORIZON.
.
PITCH SCALE
PITCH 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 INDICATION
BANK 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 INDEX
ROLL INDEX
ROLL ANGLE INDICATION
ROLL 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 UP
TO THE LEFT WITH A NOSE UP
PITCH ATTITUDE OF 10 DEGREES.
PITCH ATTITUDE OF 10 DEGREES.
20 DEGREES OF LEFT BANK
20 DEGREES OF LEFT BANK
10 DEGREES OF NOSE UP PITCH
10 DEGREES OF NOSE UP PITCH
ATTITUDE INDICATION
ATTITUDE 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
INDEX
INDEX

64
AIR SPEED INDICATIONS
AIR SPEED INDICATIONS

65
ALTITUDE INDICATIONS
ALTITUDE INDICATIONS

66
VERTICAL SPEED INDICATIONS
VERTICAL SPEED INDICATIONS
NORMALLY INERTIAL
NORMALLY INERTIAL
AND DEGRADED MODE
AND DEGRADED MODE
BARO
BARO

67
HEADING
HEADING
INDICATIONS
INDICATIONS

68
HEADING
HEADING
INDICATIONS
INDICATIONS
TRACK
TRACK
DIAMOND
DIAMOND
YELLOW
YELLOW
LINE
LINE

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 091
HEADING 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 094
TRACK 094
TRACK
TRACK
DIAMOND
DIAMOND

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

72
FLIGHT DIRECTOR (FD) INDICATIONS
FLIGHT 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 BAR
FLIGHT DIRECTOR PITCH BAR
FLIGHT 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 CENTRALIZED
AGAIN BE CENTRALIZED.
ROLL TO THE RIGHT DIRECTED
ROLL TO THE RIGHT DIRECTED
PITCH UP DIRECTED
PITCH UP DIRECTED

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
INDICATION
INDICATION

76
76
76
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 DISPLAY
AN ILS DISPLAY.
ILS INDICATIONS
ILS 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 INDICATIONS
ILS 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 2
DISPLAYED 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 VECTOR
FLIGHT 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 VECTOR
FLIGHT 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 ATTITUDE
PITCH ATTITUDE
FLIGHT PATH VECTOR
FLIGHT 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 ATTITUDE
PITCH ATTITUDE
FLIGHT PATH ANGLE
FLIGHT PATH ANGLE
FLIGHT PATH VECTOR
FLIGHT 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 ATTITUDE
PITCH ATTITUDE
FLIGHT PATH ANGLE
FLIGHT PATH ANGLE
FLIGHT PATH VECTOR
FLIGHT PATH VECTOR

84
84

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 MODES
SUB MODES
MODES OF DISPLAY OF ND
MODES OF DISPLAY OF ND

86
MODES OF ND
MODES 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 ILS
ROSE 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 COURSE
SELECTED 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.

88
LOCALIZER DEVIATION
LOCALIZER DEVIATION
BAR
BAR
GROUND SPEED AND
GROUND SPEED AND
TRUE AIR SPEED
TRUE AIR SPEED
ILS COURSE POINTER
ILS COURSE POINTER
ND ROSE ILS MODE
ND ROSE ILS MODE
WIND DIRECTION /
WIND DIRECTION /
SPEED
SPEED
SELECTED ILS
SELECTED ILS
INFORMATION
INFORMATION
GLIDE DEVIAITON
GLIDE DEVIAITON

89
LATERAL DEVIATION
LATERAL DEVIATION
BAR
BAR
VOR COURSE POINTER
VOR COURSE POINTER
VOR INFORMATION
VOR INFORMATION
ND ROSE VOR MODE
ND ROSE VOR MODE

90
TO WAYPOINT
TO WAYPOINT
WAYPOINT
WAYPOINT
RANGE MARKS AND
RANGE MARKS AND
VALUES
VALUES
ND ROSE NAV MODE
ND 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 ARRIVAL
OF ARRIVAL.
TO WAYPOINT
TO 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 MODE
ND ROSE NAV MODE

92
ND MODES
ND MODES
 IN THE ARC MODE
IN 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 MODE
IN 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 MODE
ROSE MODE
ARC MODE
ARC 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 NM
IS 40 NM

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

95
GROUND SPEED
GROUND SPEED
TRUE AIR SPEED
TRUE 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 DISPLAY
INFORMATION 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 HEADING
AIRCRAFT HEADING AIRCRAFT HEADING
AIRCRAFT HEADING
AIRCRAFT HEADING DISPLAY
AIRCRAFT 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 POINTER
ONE TWO
ONE
ONE TWO
TWO
ADF POINTERS DISPLAY
ADF POINTERS DISPLAY

98
WEATHER RADAR
WEATHER RADAR
DISPLAY
DISPLAY
DISPLAYS ONLY IN
DISPLAYS ONLY IN
ROSE AND ARC
ROSE AND ARC
MODES
MODES
NO IMAGE DURING
NO IMAGE DURING
AVIONIC
AVIONIC
VENTILLATION
VENTILLATION
FALIURE
FALIURE

100
100

101
FWC FLIGHT PHASES
FWC 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

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

105
TYPES OF FAILURES
TYPES OF FAILURES
 FAILURES ARE CLASSIFIED INTO
FAILURES ARE CLASSIFIED INTO THREE
THREE TYPES.
TYPES.
 INDEPENDENT FAILURES
INDEPENDENT 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 FAILURES
PRIMARY 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 FAILURES
SECONDARY 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 SYSTEM
DISPLAYED WITH A STAR MARK BEFORE THE FAULTY SYSTEM.
.

106
106
SECONDARY FAILURES
SECONDARY FAILURES
PRIMARY
PRIMARY
FAILURES
FAILURES
ACTION LINE
ACTION LINE

107
CLASSIFICATION OF FAULTS IN THE
CLASSIFICATION OF FAULTS IN THE
AIRCRAFT SYSTEMS
AIRCRAFT SYSTEMS
 FAULTS ARE CLASSIFIED INTO
FAULTS ARE CLASSIFIED INTO THREE
THREE TYPES ACCORDING
TYPES ACCORDING
TO THE SEVERITY. THEY ARE:
TO THE SEVERITY. THEY ARE:
 CLASS 1 FAULTS
CLASS 1 FAULTS
 CLASS 2 FAULTS and
CLASS 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 FAULTS
LEVEL 1 FAULTS
 LEVEL 2 FAULTS and
LEVEL 2 FAULTS and
 LEVEL 3 FAULTS
LEVEL 3 FAULTS

108
 LEVEL 3 FAULTS
LEVEL 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 FAULTS
LEVEL 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 1
LEVEL 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 2
CLASS 2
 THESE FAILURES ARE INDICATED ON THE
THESE FAILURES ARE INDICATED ON THE STATUS
STATUS
PAGE
PAGE, UNDER THE ITEM “MAINTENANCE”. THEY
, UNDER THE ITEM “MAINTENANCE”. THEY
ARE ALSO ACCESSIBLE THROUGH CFDS.
ARE ALSO ACCESSIBLE THROUGH CFDS.
 CLASS 3
CLASS 3
 THESE FAILURES ARE NOT INDICATED, BUT CAN
THESE FAILURES ARE NOT INDICATED, BUT CAN
BE ACCESSED THROUGH CFDS.
BE ACCESSED THROUGH CFDS.

110
110

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
DISPLAY
DISPLAY
(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 MESSAGES
MEMO MESSAGES
ENGINE /
ENGINE /
WARNING
WARNING
DISPLAY
DISPLAY
(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 SITUATION
CHECKLIST TO RESPOND TO THE PARTICULAR ABNORMAL SITUATION
WARNINGS/CAUTION MESSAGES
WARNINGS/CAUTION MESSAGES
ENGINE /
ENGINE /
WARNING
WARNING
DISPLAY
DISPLAY
(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
Page
Page
SYSTEM /
SYSTEM /
STATUS
STATUS
DISPLAY
DISPLAY
(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
DISPLAY
DISPLAY
(LECAM)
(LECAM)

116
THE SYSEM PAGES DISPLAYED
THE SYSEM PAGES DISPLAYED
 ENGINE
ENGINE (SECONDARY ENGINE PARAMETERS)
(SECONDARY ENGINE PARAMETERS)
 BLEED
BLEED
 CABIN PRESS
CABIN PRESS
 ELECTRICAL
ELECTRICAL
 HYDRAULIC
HYDRAULIC
 FUEL
FUEL
 APU
APU
 AIR CONDITIONING
AIR CONDITIONING
 DOOR / OXYGEN
DOOR / OXYGEN
 WHEEL
WHEEL
 FLIGHT CONTROL
FLIGHT CONTROL
 CRUISE
CRUISE (CANNOT BE SELECTED FROM ECAM CONTROL
(CANNOT BE SELECTED FROM ECAM CONTROL
PANEL)
PANEL)

117
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
DISPLAY
DISPLAY
(LECAM)
(LECAM)

118
LIMITATIONS
LIMITATIONS
STATUS PAGE
STATUS PAGE

119
LIMITATIONS
LIMITATIONS
APPROACH
APPROACH
PROCEDURES
PROCEDURES
STATUS PAGE
STATUS PAGE

120
LIMITATIONS
LIMITATIONS
APPROACH
APPROACH
PROCEDURES
PROCEDURES
INFORMATION
INFORMATION
STATUS PAGE
STATUS 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 SYSTEMS
INOPERATIVE 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
DATA
DATA

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.
ADVISORY
ADVISORY

124
124

125
ECAM SYSTEM PAGES LOGIC
ECAM SYSTEM PAGES LOGIC
 THE ECAM SYSTEM PAGES ARE DISPLAYED WITH THE FOLLOWING
THE ECAM SYSTEM PAGES ARE DISPLAYED WITH THE FOLLOWING
PRIORITIES
PRIORITIES
 AUTOMATIC MODE RELATED TO A FAILURE
AUTOMATIC 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 PAGE
AUTOMATIC 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 MODE
MANUAL 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 PAGE
PRESSING TWICE WILL RETURN TO THE PREVIOUS PAGE

127
AUTOMATIC MODE RELATED TO FLIGHT
AUTOMATIC MODE RELATED TO FLIGHT
PHASE
PHASE
 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 IS
THE SYSTEM PAGES SYNOPTIC COLOUR CODING IS
 O K
O K GREEN
GREEN
 NOT IN USE
NOT IN USE NOT DISPLAYED
NOT DISPLAYED
 OFF
OFF WHITE
WHITE
 ABNORMAL
ABNORMAL RED OR AMBER
RED OR AMBER
 FAILED PARAMETER
FAILED PARAMETER XX (AMBER)
XX (AMBER)

128
FLIGHT PHASE RELATED PAGES
FLIGHT 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
AWARENESS
AWARENESS
NOT
NOT 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
HYD
HYDRAULICS, 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.

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 OFF
THE 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
CONTROLS
CONTROLS.

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
147
147
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
148
148
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
152

153
ECAM CONTROLS
ECAM CONTROLS
Panel
Panel
OFF / BRT KNOBS
OFF / BRT KNOBS
EMER CANC KEY
EMER CANC KEY
ALL KEY
ALL KEY
SYSTEM PAGES KEYS
SYSTEM PAGES KEYS
T.O. CONFIG KEY
T.O. CONFIG KEY
CLR KEYS
CLR KEYS
STS KEY
STS KEY
RCL KEY
RCL KEY
NO INTEGRAL LIGHTS IN TO
NO INTEGRAL LIGHTS IN TO
CONFIG, EMER CANC, RCL
CONFIG, EMER CANC, RCL
AND ALL
AND ALL

154
SWITCHING
SWITCHING
Panel
Panel
EIS DMC SELECTOR
EIS DMC SELECTOR
ECAM / ND SYSTEM
ECAM / ND SYSTEM
SELECTOR
SELECTOR

155
MISCELLANEOUS
MISCELLANEOUS
Panel
Panel
PFD BRIGHTNESS CONTROL
KNOB
KNOB
PFD/ND XFR PB
PFD/ND XFR PB
ND BRIGHTNESS CONTROL
KNOB
KNOB

156
CONTROLS THE
CONTROLS THE
ON/OFF AND
ON/OFF AND
BRIGHTNESS FOR
BRIGHTNESS FOR
THE ASSOCIATED
THE ASSOCIATED
PFD.
PFD.
KNOB
KNOB
MISCELLANEOUS
MISCELLANEOUS
Panel
Panel

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 pb
PFD/ND XFR pb
MISCELLANEOUS
MISCELLANEOUS
Panel
Panel

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.
KNOB
KNOB
MISCELLANEOUS
MISCELLANEOUS
Panel
Panel

159
159

160
ATTENTION GETTERS
ATTENTION 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
PANEL
PANEL
 A MASTER WARNING LIGHT
A MASTER WARNING LIGHT FLSHING
FLSHING IN
IN RED
RED FOR
FOR
WARNINGS and
WARNINGS and
 A MASTER CAUTION LIGHT STEADY IN
A MASTER CAUTION LIGHT STEADY IN AMBER
AMBER FOR
FOR
CAUTIONS.
CAUTIONS.

 MASTER WARNING
MASTER 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 CAUTION
MASTER CAUTION (LEVEL 2 CAUTION)
(LEVEL 2 CAUTION) LIGHTS ARE
LIGHTS ARE
ASSOCIATED WITH SINGLE CHIME.
ASSOCIATED WITH SINGLE CHIME.

161
ATTENTION
ATTENTION
GETTERS
GETTERS
MASTER WARN LIGHT
MASTER WARN LIGHT
MASTER CAUT LIGHT
MASTER CAUT LIGHT

162
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
PRESSED.
PRESSED.
MASTER WARN light
MASTER WARN light
ATTENTION
ATTENTION
GETTERS
GETTERS

163
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,
PRESSED.
PRESSED.
MASTER CAUT light
MASTER CAUT light
ATTENTION
ATTENTION
GETTERS
GETTERS

164
164

165
165
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 NEED
INFORMATION THAT THEY NEED.

166
PFD / ND RECONFIGURATION
PFD / 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 or
TURNING 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
168
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 or
SWITCHING 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 TRANSFERRED
REPLACED 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 OR
LOWER ECAM FAILS OR
IT IS PUT TO OFF
IT 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 BY
THE 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 or
SD 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 ECAMs
FAILURE 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 or
USED 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
188

189
AURAL WARNINGS
AURAL 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 “EMER
EMER CANC
CANC”
”
PUSH BUTTON ON
PUSH BUTTON ON THE ECAM CONTROL PANEL
THE 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 INSTRUMENTS
STANDBY INSTRUMENTS

191 VERSION 1.0
INTEGRATED STANDBY
INTEGRATED STANDBY
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

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 ADVANTAGES
ISIS ADVANTAGES

194 VERSION 1.0
INTEGRATED STANDBY
INTEGRATED STANDBY

195 VERSION 1.0
INTEGRATED STANDBY
INTEGRATED STANDBY

196 VERSION 1.0
INTEGRATED STANDBY
INTEGRATED STANDBY

197 VERSION 1.0
INTEGRATED STANDBY
INTEGRATED STANDBY

198 VERSION 1.0
INTEGRATED STANDBY
INTEGRATED STANDBY

199 VERSION 1.0
ATTITUDE RESET
ROLL SCALE
FIXED AIRCRAFT
SYMBOL
ROLL INDEX
LATERAL
ACCELERATION
PITCH SCALE
ATTITUDE
INTEGRATED STANDBY
INTEGRATED STANDBY

200 VERSION 1.0
INTEGRATED STANDBY
INTEGRATED STANDBY

201 VERSION 1.0
ATTITUDE DISPLAY
ATTITUDE DISPLAY

202 VERSION 1.0
SIDE SLIP
SIDE 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

205 VERSION 1.0
INTEGRATED STANDBY
INTEGRATED STANDBY

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

211 VERSION 1.0
INTEGRATED STANDBY
INTEGRATED STANDBY

212 VERSION 1.0
ENGINEERING DATA
ENGINEERING DATA

213 VERSION 1.0
INTEGRATED STANDBY
INTEGRATED STANDBY

215 VERSION 1.0
FUNCTIONAL TEST
FUNCTIONAL TEST

216 VERSION 1.0
DISPLAY TEST
DISPLAY TEST

217 VERSION 1.0
INTEGRATED STANDBY
INTEGRATED STANDBY

218 VERSION 1.0
ISIS ARCHITECTURE
ISIS ARCHITECTURE

219 VERSION 1.0
INTERNAL ARCHITECTURE
INTERNAL ARCHITECTURE

220 VERSION 1.0
INTEGRATED STANDBY
INTEGRATED STANDBY

221 VERSION 1.0
INTEGRATED STANDBY
INTEGRATED STANDBY

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