ECAM SYSTEM/STATUS DISPLAY - DESCRIPTION AND OPERATION

** ON A/C NOT FOR ALL

1. General
The System Display (SD) is normally presented on the lower ECAM display unit, on the center instrument panel: the System Display Display Unit (SD DU).
It provides 11 system pages, a cruise page and a status page.
These pages are displayed one at a time.
They can be called automatically or manually. The SD can be presented on the upper ECAM display unit (Engine/Warning Display Display Unit - EWD DU) or on a Navigation Display Display Unit (ND DU) after a DU failure
(Ref. AMM D/O 31-68-00-00).

** ON A/C NOT FOR ALL

2. Component Location

SD - Component Location ** ON A/C NOT FOR ALL

FIN	FUNCTIONAL DESIGNATION	PANEL	ZONE	ATA REF
** ON A/C ALL
1WT1	DMC-1	85VU	127	31-63-34
1WT2	DMC-2	86VU	128	31-63-34
1WT3	DMC-3	85VU	127	31-63-34
4WT2	DU-ECAM, LOWER	4VU	210	31-63-22
6WT	CTL PNL-ECAM	11VU	210	31-61-12

** ON A/C NOT FOR ALL

3. System Description

A. General

(1) Areas on the SD

SD - Display Areas ** ON A/C NOT FOR ALL

The System Display is divided in two areas:

one large area at the top, to display the system pages
one small area at the bottom, to display permanent data.
The permanent data area is always displayed, whatever the page presented.
It consists of:
total air temperature
static air temperature
G load if excessive
identification of the active DMC during the switching test
Universal Coordinated Time
gross weight

NOTE: (a) The display indications given in this note are for description purpose only and do not represent an operational configuration.

NOTE: (b) The separating lines and the drawing background are grey; the units are cyan, the page title is white.

NOTE: (c) Data are said not available when there is no normal operation upon ARINC transmission status or when there is no refresh on data.

(2) Areas on the System Display (SD)

SD - Display Areas ** ON A/C NOT FOR ALL

The SD is divided into two areas:

One large area at the top, to show the system pages
One small area at the bottom, to show permanent data.
The permanent data area is always shown (with the page shown).
It contains the data that follows:
Total Air Temperature (TAT)
Static Air Temperature (SAT)
Delta ISA indication (available after pin-programming activation)
G load too high
or a message related to the DU monitoring process:
CHECK CAPT PFD (top line)
CHECK F/O ND (bottom line)
DISPLAY SYSTEM VERSION INCONSISTENCY (the three available lines are necessary)
DU NOT MONITORED
Identification of the active DMC during the switching test
UTC
Gross weight.

NOTE: (a) The display indications given in this note are for description only and do not show an operational configuration.

NOTE: (b) The separating lines and the drawing background are grey; the units are cyan, the page title is white.

NOTE: (c) Data are not available when there is no normal operation upon ARINC transmission status or when there is no data refresh.

(3) Pages presentation
Thirteen different pages can be displayed on the SD.
Eleven system pages can be called manually by means of the related key on the ECAM control panel.

List of the available aircraft system pages:

- Air conditioning COND

- Cabin pressurization CAB PRESS

- Electrical power supply ELEC

- Flight controls F/CTL

- Fuel FUEL

- Hydraulic power HYD

- Landing gear, wheels, brakes WHEEL

- Air bleed BLEED

- APU APU

- Doors and oxygen DOOR/OXY

- Engine secondary parameters ENGINE

SD - COND Page ** ON A/C NOT FOR ALL

SD - CAB PRESS Page ** ON A/C NOT FOR ALL

SD - ELEC Page ** ON A/C NOT FOR ALL

SD - F/CTL Page ** ON A/C NOT FOR ALL

SD - FUEL Page ** ON A/C NOT FOR ALL

SD - HYD Page ** ON A/C NOT FOR ALL

SD - WHEEL Page ** ON A/C NOT FOR ALL

SD - BLEED Page ** ON A/C NOT FOR ALL

SD - APU Page ** ON A/C NOT FOR ALL

SD - DOOR/OXY Page ** ON A/C NOT FOR ALL

SD - ENGINE (secondary parameters) Page

SD - ENGINE (secondary parameters) Page ** ON A/C NOT FOR ALL

A STATUS page is also available.

SD - STATUS Page ** ON A/C NOT FOR ALL

It can be called either manually through the STS key on the ECAM control panel or automatically upon FWS request. It displays the aircraft status, limitations, approach procedures.

In addition a CRUISE page is automatically displayed in flight.

SD - Cruise Page ** ON A/C NOT FOR ALL

It displays engine, pressurization and air conditioning parameters to be monitored during this part of the flight.

(4) Pages selection and priority
A page can be displayed on the SD through one of the four modes:

manual mode
warning mode
ADV (advisory) mode
flight phase mode.

(5) Pages selection and priority - Manual mode
All the aircraft system pages of the SD plus the status page can be manually displayed after a crew action on the relevant key located on the ECAM control panel.
It is not the case for the CRUISE page which is only automatically displayed.
The ECAM control panel has a key per aircraft system page and a key for the status page.

(6) Pages selection and priority - Warning mode
In case of failure, the aircraft system page(s) is (are) automatically displayed, according to the warning/caution messages written in the warning area of the EWD. The aircraft system page related to the primary failure is displayed first.
Then, once the crew has taken the related corrective actions and procedures, the system pages related to the secondary failures are automatically displayed.
Once all the aircraft system pages related to the failure have been displayed, the status page is automatically displayed.
A last action on the CLR key (ECAM control panel) enables to display another system page, according to the other requests:
manual, advisory or flight phase modes.

(7) Pages selection and priority - ADV (advisory) mode
An ADV (advisory) occurs when an aircraft system parameter is out of its normal range (but not at a warning level). When this occurs, the crew must examine the related system page on the lower ECAM display unit, where the affected parameter is displayed and pulses in green. The title of the related system page pulses in white.
When there is an advisory, the related system page is automatically shown on the lower ECAM display unit and the related key on the ECAM control panel comes on. When this key is pushed, the advisory is acknowledged and is inhibited for the rest of the flight.

If the system page cannot be shown because another page has priority or because the flight phase does not allow to perform an automatic system page change, nothing is shown.
If no SD image is shown (due to a failure), there is no automatic system page display. But the ADV reminder is shown and flashes in white, and the key related to the system page flashes on the ECAM control panel. The crew must push and hold this key to get access to the system page.

(8) Pages selection and priority - ADV (advisory) mode
An ADV (advisory) occurs when an aircraft system parameter is out of its normal range (but not at a warning level). When this occurs, the crew must examine the related system page on the lower ECAM display unit, where the affected parameter is shown and pulses in green.
When there is an advisory, the related system page is automatically shown on the lower ECAM display unit. A boxed ADV message is shown and flashes in white in the center of the upper ECAM display unit and the related key on the ECAM control panel comes on. When this key is pushed, the advisory is acknowledged and the automatic system page call is inhibited for the rest of the flight for this advisory.

If the system page cannot be shown because another page has priority, the boxed ADV reminder is shown and flashes in white in the center of the upper ECAM display unit.
If the system page cannot be shown because the flight phase does not allow to perform an automatic system page change, nothing is shown.
If no SD image is shown (due to a failure), there is no automatic system page display. But the ADV reminder is shown and flashes in white, and the key related to the system page flashes on the ECAM control panel. The crew must push and hold this key to get access to the system page.

(9) Pages selection and priority - Flight phase mode

Definition of the Flight Phases

When there is no failure, no manual call and no advisory, the most appropriate aircraft system page is automatically displayed according to the current flight phase, but since the DMC computation is not only linked to the flight phases the figure should be regarded as a general clue for the change of the system pages with respect to the flight phases.

(10) Pages selection and priority - Flight phase mode (Phase 1)
The DOOR page comes into view first,
the ELEC page comes into view after an emergency generator test,
the ENG START page comes into view after any crank is selected or one engine is not running and ignition is selected,
the APU page comes into view after the APU master switch is ON and lasts until the APU speed has reached 95 %.

(11) Pages selection and priority - Flight phase mode (Phase 2)
The WHEEL page comes into view first, but other pages have more priority,
the F/CTL page comes into view after a pitch command or a roll command or a significant move of the rudder,
the ENG START page may come into view if the AUTO or MANUAL START sequence is in progress.

(12) Pages selection and priority - Flight phase mode (Phase 3 or 4)
The ENGINE page comes into view after a TOGA or a FLEX T/O is selected.

(13) Pages selection and priority - Flight phase mode (Phase 5)
The ENGINE page comes into view after a TOGA or a FLEX T/O is selected,
the ENG START page may come into view if the AUTO or MANUAL START sequence is in progress.

(14) Pages selection and priority - Flight phase mode (Phase 6)
The ENGINE page comes into view until the slat/flap lever is not selected to 0,
the ENG START page may come into view if the AUTO or MANUAL START sequence is in progress,
the CRUISE page comes into view after the slat/flap lever is selected to 0.
the WHEEL page comes into view if the gear lever is selected down, and the altitude is below 16000 ft.

(15) Pages selection and priority - Flight phase mode (Phase 7)
The WHEEL page comes into view after all gears are locked down with the gear lever selected down, and the altitude is below 16000 ft,
the ENG START page may come into view if the AUTO or MANUAL START sequence is in progress.

(16) Pages selection and priority - Flight phase mode (Phase 8 and 9)
The WHEEL page comes into view if the gear lever is selected down, and the altitude is below 16000 ft.

(17) Pages selection and priority - Flight phase mode (Phase 10)
The DOOR page comes into view.

NOTE: When no particular page is triggered, the CRUISE page comes into view, whatever the flight phase.

(18) Pages selection and priority - Mode priorities
The priority between the different operational modes of the SD are:

Priority 1 (upper level) . . . - Manual mode
Priority 2 . . . . . . . . . . - Warning mode
Priority 3 . . . . . . . . . . - Advisory mode
Priority 4 (lower level) . . . - Flight phase mode

B. Description of the Pages

The pages are described in the following sections:

Permanent data (page bottom) . . . in 31-67-00
CRUISE page. . . . . . . . . . . . in 31-67-00
STATUS page. . . . . . . . . . . . in 31-67-00
COND page. . . . . . . . . . . . . in 31-67-21

CAB PRESS page . . . . . . . . . . in 31-67-21

ELEC page. . . . . . . . . . . . . in 31-67-24
F/CTL page . . . . . . . . . . . . in 31-67-27
FUEL page. . . . . . . . . . . . . in 31-67-28
HYD page . . . . . . . . . . . . . in 31-67-29
WHEEL page . . . . . . . . . . . . in 31-67-32

BLEED page . . . . . . . . . . . . in 31-67-36

APU page . . . . . . . . . . . . . in 31-67-49
DOOR/OXY page. . . . . . . . . . . in 31-67-52

ENGINE page . . . . . . . . . . . .in 31-67-77

NOTE: Each page is described with all graphic symbol changes refering to the physical background of the navigation process which might be different from the actual DMC computation. For example we state:
(e.g) "the arrow of the vertical speed is green and upward when:
25FT/MN < CAB VERT SPEED "
where the actual computation of the DMC is:
25FT/MN less than or equal to CAB VERT SPEED

C. Permanent Data

(1) Total Air Temperature (TAT) indication
Item (1):

SD - Permanent Parameters ** ON A/C NOT FOR ALL

TAT digital value with 1°C resolution:
This information is normally acquired by the ECAM, from the ADIRU bus of the DMC. Its features are as follows:

normally green
(case 1)
Permanent Parameters - Display of TAT and SAT ** ON A/C NOT FOR ALL
Permanent Parameters - Display of TAT and SAT ** ON A/C NOT FOR ALL
Permanent Parameters - Display of TAT and SAT ** ON A/C NOT FOR ALL
Permanent Parameters - Display of TAT and SAT ** ON A/C NOT FOR ALL
Permanent Parameters - Display of TAT and SAT ** ON A/C NOT FOR ALL
Permanent Parameters - Display of TAT and SAT ** ON A/C NOT FOR ALL
replaced by amber XX when no valid data are available. (case 2)
the sign is displayed for positive and negative values.

The display can vary from -99°C up to +99°C

(2) Static Air Temperature (SAT) indication
Item (2):

SD - Permanent Parameters ** ON A/C NOT FOR ALL

Same presentation as for the TAT indication.

Permanent Parameters - Display of TAT and SAT ** ON A/C NOT FOR ALL

(3) Static Air Temperature (SAT) indication
Item (6):

SD - Permanent Parameters ** ON A/C NOT FOR ALL

Same presentation as for the TAT indication.

Permanent Parameters - Display of TAT and SAT ** ON A/C NOT FOR ALL

(4) Delta International Standard Atmosphere (ISA) indication (available after pin-programming activation)
Item (5):

SD - Permanent Parameters ** ON A/C NOT FOR ALL

Delta ISA numerical value with 1°C resolution:

The value is normally shown in green, in standard altitude mode (the standard mode is selected on the Flight Control Unit (FCU) when the standard altitude is valid) and when the SAT is correct.
The sign is shown (green) for the positive and negative values.
The title is always shown in white color.
The value can change from -99 deg.C (-146.20 deg.F) to +99 deg.C (210.20 deg.F).

Note: Delta ISA = SAT + (ALTstd*2/1000) - 15.

(5) Universal Coordinated Time (UTC) indication
Item (4):

SD - Permanent Parameters ** ON A/C NOT FOR ALL

UTC hour and minutes:

normally green
(case 1)
Permanent Parameters - Display of the time ** ON A/C NOT FOR ALL
replaced by amber XX when data are not available from the CFDIU.
(case 2)

The minutes can take any value between 00 and 59 in 1 mn steps.

The hours can take any value between 00 and 23 in 1 hour steps.

Permanent Parameters - Display of G LOAD, ALT SEL, GMT ** ON A/C NOT FOR ALL

Permanent Parameters - Display of G LOAD, ALT SEL and the time ** ON A/C NOT FOR ALL

(6) G LOAD or ALT SEL indication
Item (3):

SD - Permanent Parameters ** ON A/C NOT FOR ALL

Permanent Parameters - Display of G LOAD, ALT SEL, GMT ** ON A/C NOT FOR ALL

Permanent Parameters - Display of G LOAD, ALT SEL and the time ** ON A/C NOT FOR ALL

G LOAD is displayed in amber for flight phases 4 to 10, when G Load is less than 0.7 G or more than 1.4 G for more than 2 s. Information remains displayed 5 s after excessive G Load condition has disappeared.

G LOAD is not displayed in the other cases or when no valid data are available from the ADIRUs.
G Load digital value is amber, with 0.1 G resolution. The sign is displayed for negative values only.
The display can vary from -9.9G to 0.7G, and from 1.4G to 9.9G.
ALT SEL is selected through the flight control unit, if the flight crew has selected metric units, when the G Load function is not displayed.

(7) G LOAD or ALT SEL indication
Item (3):

SD - Permanent Parameters ** ON A/C NOT FOR ALL

Permanent Parameters - Display of G LOAD, ALT SEL, GMT ** ON A/C NOT FOR ALL

Permanent Parameters - Display of G LOAD, ALT SEL and the time ** ON A/C NOT FOR ALL

The G LOAD indication is displayed in amber for the flight phases 4 to 8, when the G load is less than 0.7 G or more than 1.4 G for more than 2 seconds. The information remains displayed for 5 seconds after the excessive G load condition has disappeared.

The G LOAD indication is not displayed in all the other cases or when there is no valid data available from the ADIRUs.
The G Load digital value is displayed in amber with 0.1 G resolution. The sign (-) is displayed for the negative values only.
The display can vary from -3.0 G to 5.0 G.
If the flight crew has selected metric units and when the G load function is not displayed, the ALT SEL function can be selected through the FCU.

(8) Gross Weight (GW) indication
Item (5):

SD - Permanent Parameters ** ON A/C NOT FOR ALL

Gross Weight unit is in KG.
Gross Weight digital value is given by the FMGC with 100 KG resolution.

(9) Gross Weight (GW) indication
Item (5):

SD - Permanent Parameters ** ON A/C NOT FOR ALL

Gross Weight unit is in LBS.
Gross Weight digital value is given by the FMGC with 200 LBS resolution.

(10) Gross Weight (GW) indication
Item (2):

SD - Permanent Parameters ** ON A/C NOT FOR ALL

The GW unit is in KG.
The GW digital value is given by the Flight Management and Guidance Computer (FMGC) with 100 KG resolution.

(11) Gross Weight (GW) indication
Item (2):

SD - Permanent Parameters ** ON A/C NOT FOR ALL

The GW unit is in LBS.
The GW digital value is given by the Flight Management and Guidance Computer (FMGC) with 200 LBS resolution.

(12) Gross Weight (GW) indication - Digital value

normally green
(case 1)
Permanent Parameters - Display of the Gross Weight ** ON A/C NOT FOR ALL
Permanent Parameters - Display of the Gross Weight ** ON A/C NOT FOR ALL
Permanent Parameters - Display of the Gross Weight ** ON A/C NOT FOR ALL
it is replaced by cyan dashes when the gross weight value is coded as No Computed Data.
(case 2)
replaced by amber XX when data are not available in all other cases.
(case 3)

(13) Gross Weight (GW) indication - Digital value

normally green
(case 1)

Permanent Parameters - Display of the Gross Weight ** ON A/C NOT FOR ALL
Permanent Parameters - Display of the Gross Weight ** ON A/C NOT FOR ALL
it displayed in amber when the information is valid and the value is out of limit, before the phase 4 is reached.
(case 2)
it is not displayed when the gross weight value is coded as No Computed Data.
(case 3)
replaced by amber XX when data are not available in all other cases.
(case 4)

(14) Gross Weight (GW) indication - Variation
The display can vary from 0 to 99,900 KG in 100 KG steps.

(15) Gross Weight (GW) indication - Variation
The display can vary from 0 to 999,800 LBS in 200 LBS steps.

(16) Feedback monitoring messages
A safety device is implemented in the DMC and DU, in order to monitor the critical parameters displayed on the SD. For example the UTC parameter displayed on the permanent data area is a critical parameter and must be monitored. Likewise the SD monitors the parameters of two other DUs (in normal configuration: thePFD and ND of the F/O side). When a discrepancy occurs between an incoming parameter (at the DMC input) and the same parameter ready to be drawn on the relevant DU (inside the DU), then a feedback message is generated on the DUs which monitor the faulty DU.
These messages are displayed in amber on the SD in the permanent data area, on two lines:
On the upper zone:
CHECK F/O PFD . . . (case 5: the SD image is displayed on the SD or the capt ND)
CHECK CAPT PFD. . . (case 6: the SD image is displayed on the EWD or the f/off ND)
On the lower zone:
CHECK F/O ND. . . . (case 3: the SD image is displayed on the SD)
CHECK CAPT ND . . . (case 4: the SD image is displayed on the EWD)
CHECK SD .. . . . . (case 5 the SD image is displayed on the f/off ND or the capt ND)

Permanent Parameters - Display of G LOAD, ALT SEL, GMT ** ON A/C NOT FOR ALL

Permanent Parameters - Display of G LOAD, ALT SEL and the time ** ON A/C NOT FOR ALL

D. CRUISE page

SD - CRUISE Page: Display of 9 Parameters ** ON A/C NOT FOR ALL

SD - CRUISE Page: Display of 10 Parameters ** ON A/C NOT FOR ALL

E. CRUISE page - ENGINE Parameters

(1) OIL Quantity left and right (item 1)

(2) FUEL USED left and right (item 2)

(3) ENGINE N1 Vibration left and right (item 3)

(4) ENGINE N2 Vibration left and right (item 4)

F. CRUISE page - AIR Parameters

(1) Landing Field Elevation value and mode (item 5)

(2) Cabin Vertical Speed (item 6)

(3) Cabin Altitude (item 7)

(4) Cabin Temperature: cockpit, FWD cabin, AFT cabin, Bulk cargo (item 8)

(5) Cabin Differential Pressure (item 9)

G. CRUISE page

SD - CRUISE Page: Display of 9 Parameters

SD - CRUISE Page: Display of 10 Parameters ** ON A/C NOT FOR ALL

H. CRUISE page - ENGINE Parameters

(1) OIL Quantity left and right (item 1)

(2) FUEL USED left and right (item 2)

(3) ENGINE N1 Vibration left and right (item 3)

(4) ENGINE N2 Vibration left and right (item 4)

(5) CLOG indication fuel filter (item 10).

I. CRUISE page - AIR Parameters

(1) Landing Field Elevation value and mode (item 5)

(2) Cabin Vertical Speed (item 6)

(3) Cabin Altitude (item 7)

(4) Cabin Temperature: cockpit, FWD cabin, AFT cabin (item 8)

(5) Cabin Differential Pressure (item 9)

(6) Landing Field Elevation value and mode (item 5)

(7) Cabin Vertical Speed (item 6)

(8) Cabin Altitude (item 7)

(9) Cabin Temperature: cockpit, FWD cabin, AFT cabin, Forward cargo (item 8)

(10) Cabin Differential Pressure (item 9)

J. CRUISE page - Oil quantity
Item (1):
Digits for the engine oil quantity, with 0.5 QT resolution. The display can vary from 0 to 99.5 QT:

normally green

green and pulses when the quantity drops below 5 QT.
It stops pulsing from the value of 7 QT.

replaced by amber XX when the information is not available from the SDAC, nor the FWC.

Item (1):
Digits for the engine oil quantity, with 0.5 QT (or 0.5 LTR) resolution.
The oil quantity can be measured in Quartz (QT) or Litre (LTR).
1 QT = 0.946 LTR.
The display can vary from 0 to 99.5 QT (or 99.5 LTR):

Normally green

Green and pulses when the quantity drops below 3 QT (or 3 LTR).
It stops pulsing when the value is equal to or more than 5 QT (or 5 LTR).

Replaced by amber XX when the information is not available from the SDAC or the FWC.

Normally green

Green and pulses when the quantity drops below 3 QT (or 3 LTR).
It stops pulsing when the value is equal to or more than 5 QT (or 5 LTR).

Replaced by amber XX when the information is not available from the SDAC or the FWC.

Item (1):
Digits for the engine oil quantity with 0.5 Quartz (QT) (or 0.5 Liter (LTR)) resolution.
The oil quantity can be measured in QT or LTR.
1 QT = 0.946 LTR.
The display can vary from 0 to 99.5 QT (or 99.5 LTR) and:

normally shown in green color

shown in green and pulsing when the quantity is less than or equal to the low oil quantity advisory (OILQTYLIM*ENG*).
The display stops pulsing when the quantity is more than or equal to the low oil quantity advisory ((OILQTYLIM*ENG*) + 2 QT)

replaced by amber XX when the information is not available from the System Data Acquisition Concentrator (SDAC) nor the Flight Warning Computer (FWC).

K. CRUISE page - Fuel used (F. USED)
Item (2):
fuel used by both engines
Item (2):

Digits for the fuel used by each engine, with 10 KG (or 20 LBS) resolution. The display can vary from 0 to 45360 KG (or 99980 LBS).

Digits for the fuel used by each engine, in LBS, with 20 LBS resolution. The display can vary from 0 to 99,980 LBS.

Digits for the fuel used by each engine or by both engines (1+2) in KG, with 10 KG resolution. The display can vary from 0 to 45,360 KG.

Digits for the fuel used by each engine or by both engines (1+2) in LBS, with 20 LBS resolution. The display can vary from 0 to 99,980 LBS.

green, even after the power cut of the ECU (by memorizing the last value received) which computes the fuel used from the engine start up to its shut down

green, even after the power cut of the EEC (by memorizing the last value received) which computes the fuel used from the engine start up to its shut down

all the digits are dashed with two horizontal amber lines when the information for the fuel flow is not correctly received by the DMC in flight (ref. to the FUEL page 31-67-28).

In this case, the digits of the total fuel used (1+2) are also dashed with two horizontal amber lines.

all the digits are dashed with two horizontal amber lines when the information for the fuel flow is not correctly received by the DMC in flight (ref. to the FUEL page 31-67-28).

replaced by amber XX when the fuel used information is not available from the ECU in flight. XX are displayed until the data are available again.

*** MOD PW ENGINE ***

replaced by amber XX when the fuel used information is not available from the EEC in flight. XX are displayed until the data are available again.

replaced by amber XX when the fuel used information is not available from the EEC in flight. XX are displayed until the data are available again.

replaced by amber XX when the fuel used information is not available from the ECU in flight. XX are displayed until the data are available again.

Likewise the total fuel used is replaced by two amber XX as soon as at least one FUEL USED is XX.

L. CRUISE page - Vibrations
Item (3): N1 Vibration
Digits for the engine vibrations, with 0.1 unit resolution. The display can vary from 0 to 9.9 units:

normally green
green and pulses in case of abnormal vibrations (indication from the EIVMU)
replaced by amber XX when the vibrations information is not available from the SDAC.

Item (4): N2 Vibration
The same principles apply.
Refer to item 3 above

Item (3): N1 Vibration
Digits for the engine vibrations, with 0.1 unit resolution. The display can vary from 0 to 12.7 units:

normally green
green and pulses in case of abnormal vibrations
replaced by amber XX when the vibrations information is not available from the SDAC.

Item (4): N2 Vibration
The same principles apply.
Refer to item 3 above

Item (3): N1 Vibration
Digits for the engine vibrations with 0.1 unit resolution. The display can vary from 0 to 12.8 units:

normally shown in green color
shown in green and pulsing on Electronic Engine Control (EEC) request, if N1 (N2) vibrations are high
amber on EEC request, if N1 (N2) vibrations are excessive
replaced by amber XX when the vibration information is not available from the SDAC.

Item (4): N2 Vibration
The same principles apply.
Refer to item (3) above.

Item (3): N1 Vibration
Digits for the engine vibrations, with 0.1 unit resolution. The display can vary from 0 to 12.8 units:

normally green
green and pulses in case of abnormal vibrations (indication from the EIVMU)
replaced by amber XX when the vibrations information is not available from the SDAC.

Item (4): N2 Vibration
The same principles apply.
Refer to item 3 above

Item (10): Fuel filter clog

CLOG message is displayed in amber under the digital fuel used indication, if the pressure loss across the fuel filter is excessive.

M. CRUISE page - Landing field elevation
Item (5)
The landing field elevation indication is not displayed when the manual mode is selected.

In the other cases:
Item (5)
The landing field elevation indication is not displayed when the manual mode is selected.

In the other cases:

(1) LDG ELEV MAN 500 FT is displayed (500 is an example) with:

(a) LDG ELEV: always white

(b) Digits for the landing field elevation, with 50 FT resolution.
The display can vary from -9950 to 99,950 FT:

always green

replaced by amber XX when the landing field elevation information is not available from the SDAC.

(2) LDG ELEV MAN 500 FT is displayed (500 is an example) with:

(a) LDG ELEV: always white

(b) Digits for the landing field elevation, with 50 FT resolution.
The display can vary from -9950 to 32,750 FT:

always green

replaced by amber XX when the landing field elevation information is not available from the SDAC.

N. CRUISE page - Cabin Vertical Speed (V/S) indications

(1) Indications in AUTO mode, item (6)

(a) CAB V/S: always white

(b) Digits for the absolute value of the cabin vertical speed, with 50 FT/MN resolution.

The display can vary from 0 to 9950 FT/MN:

normally green
green and pulses when:
1800 < absolute value of CAB V/S < 2000 FT/MN
It stops pulsing when the absolute value drops below 1600FT/MN
It is amber when:
2000 FT/MN < absolute value of CAB V/S
It is replaced by amber XX when the CAB V/S is not available neither from the SDAC.

green and upward when:
the value of the cabin vertical speed is from 25 FT/MN to 2000 FT/MN
amber and upward when:
2000 FT/MN < cabin vertical speed
green and downward when:
-2000 FT/MN < CAB V/S < -25 FT/MN
amber and downward when:
CAB V/S < -2000 FT/MN
not displayed when:
-25 FT/MN < CAB V/S < 25 FT/MN
or when the CAB V/S is not available from the SDAC.

(2) Item 6: Indications in AUTO mode

(a) CAB V/S:
Always white.

(b) Digits for the absolute value of the cabin vertical speed:

It can vary from -6350 to 6350 FT/MN by step of 50 FT/MN.
The cabin vertical speed indication is:

Normally green
Green pulsing when 1750 FT/MN < |CAB V/S| (confirmed 3s). It stops pulsing when |CAB V/S| < 1650 FT/MN.
Amber XX when CAB V/S is not available from the SDAC.

Steady green and upward when:
The value of the cabin vertical speed is from 25 FT/MN to 1750 FT/MN.
It is green pulsing when CAB V/S > 1750 FT/MN (confirmed 3s). It stops pulsing when CAB V/S < 1650 FT/MN.
Steady green and downward when:
CAB V/S from -1750 FT/MN to -25 FT/MN.
It is green pulsing when CAB V/S < -1750 FT/MN (confirmed 3s). It stops pulsing when CAB V/S > -1650 FT/MN.
It is not displayed when:
-25 FT/MN < CAB V/S < 25 FT/MN
or
When the CAB V/S is not available from the SDAC.

(3) Indications in AUTO mode, item (6)

(a) CAB V/S: always white

(b) Digits for the absolute value of the cabin vertical speed, with 50 FT/MN resolution.

The display can vary from 0 to 6350 FT/MN:

normally green
green and pulses when:
1750 < absolute value of CAB V/S (confirmed 3s).
It stops pulsing when the absolute value drops below 1600FT/MN
It is replaced by amber XX when the CAB V/S is not available neither from the SDAC.

green and upward when:
the value of the cabin vertical speed is from 25 FT/MN to 1750 FT/MN
it stop pulsing when CAB V/S < 1650 FT/MN
green and downward when:
CAB V/S from -1750 FT/MN to -25 FT/MN
green pulsing when CAB V/S < -1750 FT/MN
It stop pulsing when CAB V/S > -1650 FT/MN
not displayed when:
-25 FT/MN < CAB V/S < 25 FT/MN
or when the CAB V/S is not available from the SDAC.

O. CRUISE page - Cabin altitude
Item (7):
Item (7):

(1) CAB ALT is always white

(2) Digits for the cabin altitude, with 50 FT resolution. The display can vary from -9950 to 99,950 FT:

normally green

(3) CAB ALT is always white

(4) Digits for the cabin altitude, with 50 FT resolution. The display can vary from -9950 to 32,750 FT:

green and pulses when CAB ALT is more than 8800 FT and less than 9550 FT. It stops pulsing when the cabin altitude drops below 8600 FT
red when CAB ALT > 9550 FT
replaced by amber XX when the cabin altitude is not available from neither SDAC.

normally green
green and pulses when CAB ALT is more than 8800 FT and less than 9550 FT. It stops pulsing when the cabin altitude drops below 8600 FT
red when CAB ALT > 9550 FT
replaced by amber XX when the cabin altitude is not available from neither SDAC.

P. CRUISE page - Cabin air temperature
Item (8):
Digits for the air temperature, in °C, with 1°C resolution.

Digits for the air temperature, in °F, with 2°F resolution.
The display can vary from -99°C to 999°C:
The display can vary from -99°C to 255°C:
The display can vary from -98°F to 490°F:

always green

replaced by amber XX when the air temperature is not available from the Zone Controller (via the SDAC).

replaced by amber XX when the air temperature is not available from the Air Conditioning System Controller (ACSC) (via the SDAC).

Q. CRUISE page - Cabin differential pressure
Item (9):
Item (9):

(1) delta P is always white

(2) Digits for the cabin differential pressure, with 0.1 PSI resolution. The display can vary from -9.9 to 9.9 PSI:

normally green when:
CAB delta P from -0.4 PSI to 8.5 PSI

amber when CAB delta P is less than 0.4 PSI or delta P is more than 8.5 PSI
replaced by amber XX when the CAB delta P is not available from the SDAC.

(3) Delta P is always displayed in white color.

(4) Delta P digital value can vary from -9.9 to 9.9 PSI by display step of 0.1 PSI.
Delta P is displayed:

Steady green when:
. CAB delta P greater than or equal to -0.4 or CAB delta P < 8.5 PSI.

Shown in green and pulsing when:
. CAB delta P < 8.5 PSI and CAB delta P > -0.4
and
. CAB delta P > 1.5 PSI with increase value
and
. When the A/C is in flight phase 7 with landing gear locked down or gear lever selected down.
It stops pulsing when CAB delta P < 1 PSI with decrease value.

Shown in amber when CAB delta P < -0.4 PSI or CAB delta P greater than or equal to 8.5 PSI.
Replaced by amber XX when:
. Pressure system is under control and all cabin differential pressure data from the SDAC is invalid
or
. Pressure system is not under control, corrected average static pressure and cabin pressure are invalid.

(5) delta P is always white

(6) Digits for the cabin differential pressure, with 0.1 PSI resolution. The display can vary from -9.9 to 9.9 PSI:

normally green when:
CAB delta P from -0.4 PSI to 8.5 PSI

green and pulsing when:
1.5 < CAB delta P < 8.5 PSI and the A/C is in final approach (flight phase 7). It stops pulsing when CAB delta P < 1 PSI.

amber when CAB delta P is less than 0.4 PSI or delta P is more than 8.5 PSI
replaced by amber XX when the CAB delta P is not available from the SDAC.

[Rev.10 from 2021] 2026.04.01 05:30:34 UTC