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always rely
on any reactive windshear (″WINDSHEAR″).
W/S AHEAD RED
�� Takeoff
Associated with an aural synthetic voice “WINDSHEAR AHEAD, WINDSHEAR
AHEAD”.
�� Before takeoff
Delay takeoff, or select the most favorable runway.
�� During the takeoff run
Reject takeoff.
Note: Predictive windshear alerts are inhibited above 100 kts until 50 ft.
�� When airborne
THR
LEVERS......................................................................................................................
TOGA
As usual, the slat/flap configuration can be changed, provided the windshear is not
entered.
SRS ORDERS................................................................................................................
FOLLOW
Note: If engaged, the autopilot disengages when α is greater than α prot.
�� Landing
Associated with an aural synthetic voice “GO AROUND, WINDSHEAR AHEAD”.
GO
AROUND......................................................................................................................P
ERFORM
This includes the use of full backstick, if required.
Note: 1. If engaged, the autopilot disengages when α is greater than α prot.
2. If the FD is not available, use a pitch initial attitude up to 17.5 °. If necessary to
minimize the loss of height, increase this pitch attitude.
W/S AHEAD AMBER
Apply precautionary measures, as indicated in the SUPPLEMENTARY
TECHNIQUES TBD by AIRBUS.
WINDSHIELD/WINDOW ARCING
Affected WINDOW/WINDSHIELD ANTI ICE
C/B................................................................................... PULL
In case of electrical arcing, pull the circuit breaker of the affected window/windshield
heating system:
‐ ANTI ICE L WSHLD C/B AF10
‐ ANTI ICE/WINDOWS L C/B X14
‐ ANTI ICE R WSHLD C/B AF03
‐ ANTI ICE/WINDOWS R C/B W14
ABN-80
13/32
AQU3I1CK8 R/AEF3E1RE9N/ACE3 H2A0ND/A B3O2OK1
ABNORMAL AND
EMERGENCY PROCEDURES 30 AUG 10
A318/A319/A320/A321 FLEET ,
WINDSHIELD/WINDOW CRACKED
MAX
FL....................................................................................................................................
.................230
CAB PRESS MODE
SEL.........................................................................................................................MAN
MAN V/S
CTL................................................................................................................................
AS RQRD
Set the cabin altitude, according to the table below.
ΔP = 5 PSI CABIN AFLLTITUDE 1000 31 05000 62 00000 82 03000
�� When starting the final descent:
CAB PRESS MODE
SEL................................................................................................................ AUTO
Note: If sufficient visibility is not granted for approach, consider AUTOLAND. If
AUTOLAND is not
available, consider opening the sliding window on the PF’s side, after cabin
depressurization.
To manually depressurize the cabin:
CAB PRESS MODE
SEL.................................................................................................................. MAN
MAN V/S
CTL............................................................................................................................FU
LL UP
Due to the increased noise level, pay particular attention to visual warnings.
ABN-80
14/32
AQU3I1CK8 R/AEF3E1RE9N/ACE3 H2A0ND/A B3O2OK1
ABNORMAL AND
EMERGENCY PROCEDURES 30 AUG 10
A318/A319/A320/A321 FLEET ,
ECAM ADVISORY CONDITIONS
SYSTEM CONDITIONS RECOMMENDED ACTION
CAB VERTICAL SPEED
V/S > 1 800 ft/min CPC changeover is recommended :
‐ MODE SEL(MAN)
Wait 10 s, then :
‐ MODE SEL(AUTO)
CAB ALTITUDE
altitude ≥ 8 800 ft
MODE SEL(MAN)
Manual pressure control
CAB PRESS
CAB DIFF PRESS
ΔP ≥ 1.5 PSI in phase 7
LDG ELEV (ADJUST)
If unsuccessful : MODE SEL (MAN)
Manual pressure control
ELEC
IDG OIL TEMP ≥ 147 °C Reduce IDG load, if possible (GALLEY or GEN OFF).
If required, restore when the temperature has dropped.
Restrict generator use to a short time, if the temperature
rises again excessively.
Difference between wing fuel quantities
greater than 1 500 kg (3 307 lb)
FUEL MANAGEMENT (CHECK)
If a fuel leak is suspected, refer to the FUEL LEAK procedure.
For limitations, Refer to FCOM/LIM-28 MAXIMUM ALLOWED
WING FUEL IMBALANCE
Fuel temp greater than 45 °C in inner cell, or
55 °C in outer cell
　
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