导航
ADIRS
IR 1（2）（3）在ATT方式下工作。
IR 1（2）（3）仅提供姿态和航向数据（如果由机组输入）。导航数据不可用。
航向必须通过MCDU输入，且必须经常复位（大约每10 min）。
注:
在飞行中，如果IR方式 选择器从NAV设置到ATT或从NAV设置到OFF，NAV方式在剩余航段失效。
在ATT方式时，飞行机组只能通过完全校准在地面恢复NAV方式。
监视
ATC
气象雷达
GPWS
ATC/TCAS
(1) TCAS mode selector
TA/RA:
Normal position.
Other and proximate intruders, TAs and RAs are displayed if the ALT RPTG switch
is ON and the ATC mode selector is ON or AUTO.
TA:All RAs are converted into TAs.
TAs, proximate and other intruders are displayed.
STBY:The TCAS is on standby.
(2)TRAFFIC selector
THRT :Threat traffic is displayed. Others and proximates are only displayed when there is a
TA or a RA.
ALL:Only affects the other intruders : Altitude range is 2 700 ft above and below the
aircraft.
TA, RA, proximate and other intruders are displayed (full time).
ABV :Only affects the others intruders which appear within 9 900 ft above the aircraft and
2 700 ft below.
BLW :
Only affects the other intruders which appear within 9 900 ft below the aircraft and
2 700 ft above.
ND INDICATIONS
Applicable to: ALL
The traffic is displayed in all ROSE modes and ARC mode whatever NM range is selected. Only the
eight most threatening intruders are displayed.
(1)Other intruder
Indicated by a white empty diamond.
(2)Proximate intruder
Indicated by a white filled diamond.
(3)TA intruder
Indicated by an amber circle.
Associated with the "TRAFFIC-TRAFFIC" aural message.
(4)RA intruder
Indicated by a red square.
Associated with vertical orders displayed on the PFD and aural messages.
Note:
If the range of an intruder is not available, the intruder is not displayed.
An intruder may be partially displayed when its range is out of scale.
(5)Relative altitude/Vertical Speed arrow
Relative altitude:indicated in hundred of feet above or below the symbol depending on
the intruder position.
Vertical speedarrow:displayed only if the intruder vertical speed is greater than ± 500 ft/min
The relative altitude and vertical speed arrow are displayed in the same color as the associated
intruder symbol.
When an intruder does not report its altitude, the relative altitude and the vertical movement are
not displayed.
(6)No Bearing Intruder
If the bearing of TA or RA intruder is not available the following data is presented in digital form
at the bottom of the ND :
‐ range
‐ relative altitude and vertical speed arrow if available.
Displayed amber or red according to threat level.
(7)Range Ring
A 2.5 NM white range ring is displayed when a 10 or 20 NM range is selected.
MESSAGES ON ND
MODE AND RANGE MESSAGES
Following messages can be displayed to draw pilot’s attention:
TCAS : REDUCE RANGE
Displayed when a TA is detected and ND range above40 NM.
TCAS : REDUCE RANGE
Displayed when a RA is detected and ND range above40 NM.
TCAS : CHANGE MODE
Displayed when a TA is detected and ND mode isPLAN.
TCAS : CHANGE MODE
Displayed when a RA is detected and ND mode is PLAN.
OPERATION MESSAGES
TA ONLY
Displayed when the TA mode is selected automatically, or manually by the flight crew.
TCAS ADS-B (ATSAW )
Displayed in the case of an internal TCAS failure affecting also the ATSAW function.
TCAS ADS-B ONLY (ATSAW )
Displayed in the case of an internal TCAS failure not affecting the ATSAW function.
Note: TCAS symbols are removed from ND.
ATSAW traffic is displayed with "ADS-BOnly" symbols.
ADS-B (ATSAW )
Displayed in the case of ATSAW failure withoutTCAS failure.
Note:ATSAW traffic symbols are removedfrom ND. TCAS symbols remain available.
PFD INDICATIONS
Applicable to: ALL
In case of RA detection, the vertical speed scale becomes rectangular and the PFD presents vertical
orders on the vertical speed scale. The vertical speed scale background is normally grey, but may be
partially replaced by green and/or red areas.
Note:
When TCAS information has to be displayed on the vertical speed scale, the greybackground of the air speed and heading scales are removed.
(1)Red area
Indicates the vertical speed where the risk of conflict is high.
(2)Green area
Indicates the recommended vertical speed range. ("FLY TO" sector).
Note:
The aircraft can also fly in the grey vertical speed range without the risk of conflict
(preventive RA).
(3)TCAS message
It is displayed when the TCAS cannot deliver RA data, or in case of a TCAS internal failure,
provided that the TCAS is not in standby.
Note:
When within the red area, the vertical speed needle and digits change to red, but in a
different pattern, so that it is possible to clearly distinguish them from the background.
AURAL MESSAGES
TA/RA detection is associated with the following messages:
“TRAFFIC TRAFFIC”:Only in case of TA detection.
"CLIMB CLIMB":Climb at the vertical speed indicated by thegreen area on the PFD.
“CLIMB, CROSSING CLIMB” (twice):Same as above. Indicates that you will cross through the intruder altitude.
“INCREASE CLIMB” (twice):Triggered after the CLIMB message, if the vertical speed is insufficient to achieve safe vertical separation.
“DESCEND, DESCEND": Descend at the vertical speed indicated by the green area on the PFD.
“DESCEND, CROSSING DESCEND” (twice): Same as above. Indicates that you will cross through the intruder altitude.
“INCREASE DESCEND” (twice): Triggered after the DESCEND message, if the vertical speed is insufficient to achieve safe vertical separation.
"LEVEL OFF, LEVEL OFF" : Set the Vertical Speed to 0.
“CLIMB, CLIMB NOW” (twice) : Triggered after the DESCEND message, if the intruder trajectory has changed.
“DESCEND, DESCEND NOW” (twice) : Triggered after the CLIMB message, if the
intruder trajectory has changed.
“MONITOR VERTICAL SPEED” : Ensure that the vertical speed remains outside the red area. Triggered only once, in case of preventive RA.
"MAINTAIN VERTICAL SPEED, MAINTAIN": Maintain the vertical speed within the green area and/or out of the red area of the vertical speed scale.
"MAINTAIN VERTICAL SPEED ... CROSSING MAINTAIN" : Maintain the vertical speed indicated on the
green area of the PFD. Indicates that you will cross through the intruder altitude.
“CLEAR OF CONFLICT”: The range increases, and separation is adequate. Return to assigned clearance.
MEMO DISPLAY
TCAS STBY: This memo appears in amber in flight phase 6 when:
‐ The flight crew selects TCAS STBY or ATC STBY on the ATC/TCAS panel, or
‐ Both ATCs or both RAs fail, or
‐ The flight crew turns OFF the ALT RPTG sw, or
‐ In the case of a triple ADR failure.
TCAS STBY:
This memo appears in green in flight phases 2 and 7 when:
‐ The flight crew selects TCAS STBY or ATC STBY on the ATC/TCAS panel, or
‐ Both ATCs or both RAs fail, or
‐ The flight crew turns OFF the ALT RPTG sw, or
‐ In the case of a triple ADR failure.
氧气
(1)
CREW SUPPLY pushbutton
This pushbutton controls the solenoid valve.
On :
The valve is open, and supplies low pressure oxygen to the masks (normal position in
flight).
OFF:
The valve is closed, and the white light comes on.
(1)
Blinker flowmeter (yellow)
This indicator flashes when oxygen is flowing.
(2)
RESET / TEST control slide
The crewmember presses the slide, and pushes it in the direction of the arrow to test: The
operation of the blinker, the regulator supply, the system sealing downstream of the valve, and
the regulator sealing and system operation. Pressing the RESET control slide, after the oxygen
mask has been used, cuts off the oxygen and the mask microphone.
(3)
OXY ON flag
As soon as the left flap door opens, the mask is supplied with oxygen and, once it closes (mask
still supplied with oxygen), the “OXY ON“ flag appears.
气源
(1)
ENG 1 (2) BLEED pb sw
On:
The bleed valve opens, provided:
‐ Upstream pressure is above 8 PSI.
‐ The APU BLEED pb-sw is OFF, or the APU bleed valve is closed.
‐ There is no onside wing or pylon leak, overpressure, or overtemperature
detected.
‐ The ENG FIRE pushbutton is not released out
‐ The ENG start valve is closed.
FAULT lt :
illuminates amber, associated with ECAM caution, in case of:
‐ Bleed valve is not closed during engine start
‐ Bleed valve is not closed with APU bleed ON (and for RH engine X-bleed
open).
and additionally associated with autoclosure of the bleed and HP valves:
‐ Overpressure downstream of the bleed valve.
‐ Bleed overheat
‐ Wing or pylon leak on the related side.
It goes off, when the ENG BLEED pushbutton is OFF, provided the failure has
disappeared.
OFF:
The Bleed valve and HP valve close. OFF light comes on white. The FAULT light and the auto closure signal are reset.
(2)
APU BLEED pb sw
ON:
APU valve opens provided:
‐ N > 95 %
‐ Altitude < 25 000 ft climbing
or < 23 000 ft descending
‐ No leak detected on APU or LH bleed (Should a leak occur on the RH side, the
X-bleed would close).
ON light illuminates blue.
Off:
APU valves closes.
FAULT lt :
illuminates amber, associated with ECAM caution, when APU leak is detected.
(3)
X-BLEED sel
AUTO:
X-bleed valve is open if APU bleed valve is open
X-bleed valve is closed if APU bleed valve is closed.
OPEN:
X-bleed valve is open.
CLOSE :
X-bleed valve is closed.
Precooler inlet pressure
It is normally in green.
It becomes amber, if lower than 4 PSI, or in case the BMC detects an overpressure (above 60 PSI).
Precooler outlet temperature
It is normally in green.
It becomes amber, if the BMC detects an overheat or low temperature.
Overheat: Temperature exceeds:
‐ 290 °C for more than 5 s, or
‐ 270 °C for more than 15 s, or
‐ 257 °C for more than 55 s.
Low temperature is detected (only in-flight), if the bleed temperature drops below 150 °C, the wing anti-ice is on, and the pressure regulating valve is in the open position. Low temperature may, however, only be due to low outside air temperature.
Note:
When the engines are at idle, and depending on the ambient temperature, the precooler outlet temperature may be below 150 °C (displayed in amber).
APU
(1) APU MASTER SW pb-sw
This pushbutton controls the electric supply for APU operation, and its protective features. It also controls the start and shutdown sequences
FAULT lt :
This amber FAULT light comes on, and a caution appears on the ECAM, when an automatic APU shutdown occurs (Refer to DSC-49-10-20 Ground Operations Safety Devices).
Note: In case of automatic, non emergency shutdown, the air inlet flap closes 15 min after the APU speed is lower than 7 %.
If an automatic, non-emergency shutdown happens on ground, the
15 min countdown starts after liftoff.
ON/R :
‐ The blue ON light comes on.
‐ Electric power goes to the APU system, and the ECB performs a power-up
test.
‐ The APU air-intake flap opens.
‐ The APU fuel isolation valve and APU LP valve open.
‐ The FWD APU and aft APU fuel pumps operate during the trim tank fuel
transfer, and depending on the pressure in the trim tank line.
‐ If the aircraft has ground power or main generator power, the APU page
appears on the ECAM display.
Off :
Manual shutdown sequence.
‐ The ON light of the MASTER SW pb-sw goes off.
‐ After a running period of 15 s (for No Break Power Transfer), the APU shuts
down and the AVAIL light goes off,
‐ If the APU BLEED was selected, the APU performs a cooling period of 85 s at 82 % speed,
‐ At N 7 % the air-inlet flap closes.
Note:
Switching the MASTER SW off then on, resets the ECB.
(2) APU START pb-sw
ON : The blue light comes on.
When the flap is completely open, the APU starter is energized.
When N = 7 %, ignition is turned on.
When N = 50 %, the APU starter is de-energized, and ignition is turned off.
When N = 95 %, the ON light on the START pushbutton goes off and AVAIL
comes on in green.
The APU may now supply bleed air and electrical power to the aircraft systems.
10 s later, the APU page disappears from the ECAM display.
AVAIL lt : This light comes on green, when N reaches 95 %.
(1) AVAIL Indication
It is in green, when APU N is above 95 %.
(2) APU Bleed Valve Position
It is only displayed, if the APU MASTER sw is ON/R.
In line – Green:
The APU valve is fully open.
Crossline – Green:
The APU valve is not fully open, and APU BLEED pb is OFF.
Crossline – Amber:
The APU valve is not fully open, if APU BLEED pb is ON.
(3) APU Bleed Air Pressure
This box displays the relative bleed air pressure in green.
It shows an amber XX, when ADIRS 1 is not available or selected OFF.
(4) APU GEN Line ContactorIndication
It is in green, when the APU GEN line contactor is closed.
It is in white, if the line contactor is open.
(5) APU GEN
It is identical to the APU GEN parameters on the ELEC page.
(6) FUEL LO PR
It is in amber, if APU fuel low pressure is detected.
(7) FLAP OPEN
Displayed in green, when the APU air intake flap is fully open (MASTER SW pb-sw is ON).
(8) APU N
‐ Displays the APU speed in green
‐ It becomes red, when N ≥ 107 %.
(9) APU EGT
‐ It displays the APU EGT (needle and digital indication) in green
‐ It pulses, when the ECB detects an advisory
‐ It becomes red, when EGT ≥ RED EGT LIM. In this case an automatic shutdown of the APU occurs.
Note:
ECB calculates the RED EGT LIM and transmits it to the ECAM. It is equal to the lower border of the red sector. It is a function of N during start, and a function of ambient temperature and pressure when the APU is running.
Maximum EGT during start : 1 250 °C (corresponding to 0 % APU speed).
Maximum EGT with APU running : 650 °C (Sea level, standard day).
(10) LOW OIL LEVEL
This advisory is displayed, if the ECB detects a low APU oil level, when the aircraft is on ground and the APU is not running.
MEMO DISPLAY
APU AVAIL:
This memo appears in green when APU N is above 95%.
ECAM舱门/氧气
舱门关闭且锁好。
舱门未锁好。
信息无效。侧滑预位。
舱门未锁好。
信息无效。
驾驶舱窗
COCKPIT WINDSHIELD AND WINDOWS DESCRIPTION
All cockpit windows are fail-safe design.
The windows are made of:
‐ A non structural ply, the Outer ply (1), which is only a protective layer
‐ Two structural plies, the Middle ply (2) and the Inner ply (3)
Each structural ply is able to sustain individually the pressurization loads
‐ A heating film (4) to defog and/or de-ice the windshield/window
‐ Two interlayers (5).
发动机
ENG N1 MODE pb-sw
Off:The FADEC controls the engine in EPR mode, if available.
ON:The FADEC controls the engine in N1 mode.
ENG MAN START pb-sw
ON:
‐ Initiates the manual start sequence of the associated engine, when the ENG START selector is set to IGN/START, or
‐ Initiates the wet crank process of the associated engine, when the ENG START selector is set to CRANK and the ENG MASTER lever is set to ON, or
‐ Initiates the dry crank process of the associated engine, when the ENG START selector is set to CRANK and the ENG MASTER lever is set to OFF.
Off:
‐ Aborts the manual start sequence of the associated engine, when the ENG START selector is set to IGN/START and the ENG MASTER lever is set to OFF, or
‐ Stops the dry crank process of the associated engine, when the ENG START selector is set to CRANK and the ENG MASTER lever is set to OFF.
发动机人工起动 按钮电门
ON:‐ 当 ENG START 选择器设置到 IGN/START 位时，开始相关发
动机的人工起动顺序，或
‐ 当 ENG START 选择器设置到 CRANK 位且 ENG MASTER手
柄在 ON 位时，开始相关发动机的湿冷转过程，或
‐ 当 ENG START 选择器设置到 CRANK 位且 ENG MASTER手
柄在 OFF 位时，开始相关发动机的干冷转过程。
关:‐ 当 ENG START 选择器设置到 IGN/START 位且 ENG MASTER
手柄在 OFF 位时，中止相关发动机的人工起动顺序。
‐ 当 ENG START 选择器设置到 CRANK 位且 ENG MASTER手
柄在 OFF 位时，停止相关发动机的干冷转过程。
ENG START SELECTOR
NORM:
Normal mode of operation.
IGN/START:
Use the IGN/START position to:
‐ Initiate the automatic or manual start sequences of the associated
engine, when the ENG MASTER lever is set to OFF, or
‐ Initiate the ignitors in flight as required.
CRANK:
Use the CRANK position to:
‐ Initiate the dry crank process of the associated engine, when the ENG
MASTER lever is set to OFF and the ENG MAN START pb-sw is set to
ON.
‐ Initiate the wet crank process of the associated engine for maintenance
purposes, when the ENG MASTER lever, and the ENG MAN START
pb-sw are set to ON.
The FADEC:
‐ Provides the associated engine with continuous ignition, when both
orengines are running and the ENG START selector is set to IGN/START,
‐ Initiates the wet crank process of the associated engine for maintenance
purpose, when the ENG START selector is set to CRANK and the ENG
MAN START pb-sw is set to ON, or
‐ Initiates the automatic start sequence of the associated engine, when
the ENG START selector is set to IGN/START, or
‐ Initiates the manual start sequence of the associated engine, when the
ENG START selector is set to IGN/START and the ENG MAN START
pb-sw is set to ON.
The FADEC:
‐ Shuts down the associated engine, or
‐ Aborts the start sequence of the associated engine.
ENG MASTER LIGHT
FIRE light:
A fire is detected in the corresponding engine.
FAULT light:
‐ The position of the HP fuel shutoff valve is abnormal, or
‐ The automatic start sequence of the associated engine aborts, or
‐ There is a malfunction of the thrust control.
THRUST LEVERS
The flight crew uses the thrust levers in order to:
‐ Adjust the thrust, or
‐ Select a thrust stop or detent.
The flight crew can move each thrust lever individually.
The position of the thrust levers appears on the E/WD, via a blue circle on the thrust gauge.
The flight crew can move each thrust lever forward the Idle (0) stop, when the associated thrust
reverser lever is set to the stowed detent.
THRUST DETENTS AND STOPS
There are one stop and three detents, for the thrust levers:
‐ The Idle (0) stop
‐ The Climb (CL) detent
‐ The Maximum Continuous Thrust (MCT)/Flexible Take Off (FLX) detent
‐ The Takeoff (TO)/Go-Around (GA) detent.
There are two stops and one detent, for the thrust reverser levers:
‐ The stowed stop
‐ The idle reverser (IDLE REV) detent
‐ The maximum reverser (MAX REV) stop.
THRUST REVERSER LEVERS
The flight crew uses the thrust reverser levers in order to:
‐ Control the deployment and the stowage of the associated reversers
‐ Adjust the associated reverse thrust.
The flight crew can move the thrust reverser lever backward the stowed detent (to the IDLE REV detent or MAX REV stop), when the associated thrust lever is set to the Idle (0) stop.
A/THR INSTINCTIVE DISCONNECT pb
Pressing the A/THR INSTINCTIVE DISCONNECT pb disconnects the A/THR.
For more information about the A/THR INSTINCTIVE DISCONNECT pb
ENG FADEC GND PWR pb
Off:
The electrical network of the aircraft or the FADEC alternator automatically
supplies the FADEC.
ON:
On ground, when pressed the electrical network of the aircraft supplies the
FADEC for 5 min, when:
‐ The ENG FIRE pb-sw is not pressed
‐ The FADEC alternator does not supply the FADEC.
The ON light comes on 2 s after the ENG FADEC GND PWR pb is pushed.
THRUST RATING MODE AND THRUST LIMIT VALUE
Indicates the thrust limit value and the associated thrust rating mode based on:
‐ The position of the thrust levers,
‐ Aircraft on ground or in flight,
‐ The engine status, i.e. running or not running,
‐ The data entered in the T.O and CLB panels of the FMS ACTIVE/PERF page.
THRUST RATING MODE
The thrust rating modes are:
TOGA:Takeoff or go-around (TOGA) thrust rating mode is selected.
MCT:Maximum Continuous Thrust (MCT) rating mode is selected.
CLB:Climb (CLB) thrust rating mode is selected.
FLX:Flexible (FLX) takeoff thrust rating mode is selected.
DCLB1(2):Derated Climb (DCLB) thrust rating mode is selected.
There are 2 levels of derated climb: DCLB1 and DCLB2.
D04:Derated Takeoff thrust rating mode is selected.
There are several levels of derated takeoff: D04, D08, D12, D16, D20, ...
GA SOFT:Soft go-around thrust rating mode is selected.
XX in amber :There is no thrust rating mode selected, the selected rating mode is not available, or at least one engine operates in degraded N1 mode on ground.
The thrust rating mode disappears when the thrust reversers are selected.
THRUST LIMIT VALUE
EPR value: Indicates the EPR limit value associated with the thrust rating mode, when at least one engine operates in EPR mode.
N1 value: Indicates the N1 limit value associated with the thrust rating mode, when all engines operate in rated N1 mode.
The N1 MODE indication appears.
XX in amber :
Indicates that the thrust limit value is not available, or that at least one engine operates in degraded N1 mode on ground.
The thrust limit value disappears when the thrust reversers are selected.
FLEX TEMPERATURE
Cyan: Indicates the flexible temperature that the flight crew entered in the T.O panel of the FMS PERF page, when the FLX rating mode is selected.
IDLE INDICATION
Both engines are at idle speed, and the aircraft is in flight.
Pulses during 10 s, and then remains steady.
AVAIL INDICATION
The engine is started, and at or above idle.
On ground, appears steady during 10 s after a successful start.
In flight, pulses during 1 min after a successful relight.
The AVAIL indication disappears when the flight crew moves the thrust lever forward the idle detent.
REV INDICATION
REV in green :
On ground, the thrust reverser system is fully deployed.
REV in amber :
The thrust reverser system is unlocked.
In flight, the REV indication pulses during 9 s and then remains steady.
CURRENT EGT
Green: The current EGT is in normal range.
The scale goes from 0 °C to 1 200 °C.
Amber: The current EGT exceeds the EGT limit.
Red: The EGT is above the EGT red limit.
The current EGT:
‐ Is between 900 °C and 920 °C for more than 20 s, or
‐ Exceeds 920 °C.
EGT LIMIT
The amber line indicates the maximum EGT (i.e. the EGT limit).
The maximum EGT is:
‐ 700 °C, during the engine start sequence on ground, or
‐ 900 °C, in all other cases.
The EGT limit does not appear:
‐ When a takeoff or a go-around mode is selected, or
‐ When the thrust reversers are selected, or
‐ If the alpha floor protection is activated.
EGT EXCEEDANCE
The EGT exceedance is the highest value that the EGT reached.
The EGT exceedance appears when:
‐ The current EGT exceeds the EGT red limit, or
‐ The EGT exceeded the EGT red limit.
The red mark no longer appears at the next engine start sequence on ground, or after a maintenance action.
EGT RED LINE
The EGT red line appears between the EGT red limit and the end of the scale.
The EGT red limit is 920 °C.
CURRENT EPR
Green: The current EPR is valid and the engine operates in EPR mode.
XX in amber :
The Current EPR is not valid, or the engine operates in N1 mode.
The EPR scale appears in amber.
The EPR needle and the box around current the EPR value disappear.
EPR TREND
The green triangle indicates the direction of the N1 trend, when the A/THR mode is active.
EPR COMMAND
Indicates the EPR target, when the A/THR mode is active.
TRANSIENT EPR
The four green arcs indicate the difference between the EPR command and the current EPR, when the A/THR is active.
THRUST LEVER POSITION
The blue circle indicates:
‐ In manual mode, the thrust (EPR value) after the engine stabilization
‐ In automatic mode, the thrust (EPR value) that corresponds to the position of the associated thrust lever.
The thrust lever position disappears when the flight crew selects the thrust reversers.
EPR LIMIT
The amber mark indicates the EPR limit.
This corresponds to the maximum EPR value when the thrust levers are in TO/GA detent.
The amber mark disappears when the thrust reversers are selected.
CURRENT N1
Green: The current N1 is in normal range.
The box around current N1 appears, when the engine operates in N1 mode.
Red: The current N1 exceeds the N1 red limit.
N1 red limit is 99 %.
Dashed: The accuracy of the N1 measurement is degraded.
Two amber dashes appear over the last digit.
N1 TREND
The green triangle indicates the direction of the N1 trend, when the A/THR mode is active and all engines operate in N1 mode.
For N1 trend indication applicability, Refer to DSC-70-35-20 N1 Mode.
N1 COMMAND
Indicates the N1 target, when the A/THR mode is active, when all engines operate in N1 mode.
TRANSIENT N1
The four green arcs indicate the difference between the N1 command and the current N1, when the A/THR is active and all engines operate in N1 mode.
THRUST LEVER POSITION
When the engine operates in N1 mode, the blue circle indicates:
‐ In manual mode, the thrust (N1 value) after the engine stabilization
‐ In automatic mode, the thrust (N1 value) that corresponds to the position of the associated thrust lever.
The thrust lever position disappears when the flight crew selects the thrust reversers.
N1 LIMIT
The amber mark indicates the N1 limit.
This corresponds to the maximum N1 value:
‐ When the thrust levers are in TO/GA detent and the engine operates in rated N1 mode, or
‐ When the thrust levers are in MAX REV position.
N1 EXCEEDANCE
The N1 exceedance is the highest value that the N1 reached.
The N1 exceedance appears when the current N1 exceeds the N1 red limit.
The N1 exceedance remains even if the N1 value decreases below the N1 red limit.
The red mark no longer appears at the next engine start sequence on ground, or after a maintenance action.
N1 RED LINE
The N1 red line appears between the N1 red limit and the end of the scale.
The N1 red limit is 99 %.
N3
In a grey box :
The engine start sequence or the crank process is in progress.
Green: N3 is in normal range.
Red: N3 exceeds the N3 red limit.
N3 red limit is 100 %.
A red cross appears.
The red cross no longer appears at the next engine start sequence on ground, or after a maintenance action.
Dashes: The accuracy of the N3 measurement is degraded.
Two amber dashes appear over the last digit.
THRUST BUMP INDICATION
The thrust bump is engaged.
MEMO DISPLAY
IGNITION: This message is displayed in green, either when selected automatically by the FADEC or manually by the crew.
N2
Green: N2 is in normal range.
Red: N2 exceeds the N2 red limit.
N2 red limit is 103.3 %.
A red cross appears.
The red cross no longer appears at the next engine start sequence on ground, or after a maintenance action.
Dashed: The accuracy of the N2 measurement is degraded.
Two amber dashes appear over the last digit.
FUEL USED INDICATION
Green: Indicates the fuel used by each engine.
This value automatically resets on ground, at the next engine start.
Appears in multiples of 10 kg (20 lb).
Dashed: The value accuracy is degraded.
Two amber dashes appear over all five digits.
This occurs when the Fuel Flow is not valid in flight, for more than 1 min.
FUEL FILTER CLOG INDICATION
Indicates that the pressure loss across the fuel filter is excessive.
OIL QUANTITY
Green: The oil quantity is in normal range.
The scale goes from 0 to 22 QT.
Pulses green :
The needle and the oil quantity value pulse green.
The advisory limit is 4 QT.
OIL PRESSURE
Green: The oil pressure is in normal range.
The scale goes from 0 to 250 PSI.
Red: The oil pressure is in the red range.
The red range is between 0 and 25 PSI.
OIL TEMPERATURE
Green: The oil temperature is in normal range.
Amber: The oil temperature is above 190 °C.
OIL FILTER CLOG INDICATION
Indicates that the pressure loss across the oil filter is excessive.
N1, N2, N3 VIBRATIONS
Green: The vibration of the LP (IP) (HP) rotor is in normal range.
Pulses green :
The level of LP (IP) (HP) rotor vibration is excessive.
STARTING SEQUENCE INDICATION
During the engine start sequence, the starting sequence indication appears on the ENG SD page.
IGNITION INDICATION
:
The igniter A(B) is used for the engine start sequence.
Both igniters A and B are used for the engine start sequence or continuous
ignition.
The engine start valve is fully closed.
The engine start valve is fully open.
The engine start valve failed in the closed position.
The engine start valve failed in the open position.
STARTER INLET PRESSURE
Green: The starter inlet pressure is normal.
Amber: The starter inlet pressure is either:
‐ Abnormally high, or
‐ Abnormally low (below 15 PSI, when N3 is above 8 % and the starter valve
is not closed).
NACELLE TEMPERATURE INDICATION
Green: The nacelle temperature is normal.
Pulses green : The nacelle temperature goes above the advisory limit, that correspond to the white dash.
The advisory limit is 260 °C.