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ABCU Norm Norm Norm
L/G BRK PRESS IND Norm Norm Norm
PARK BRK Norm Norm Norm
LIGHTS EEMMEERR CCAKBPT NNoorrmm NNoorrmm NNoorrmm
IR N° 1 only (2) N° 1 only (2) N° 1 only (2)
ADR N° 1 only N° 1 only N° 1 only
ADF N° 1 only Inop Inop
VOR-MMR N° 1 only N° 1 only N° 1 only (1)
DME N° 1 only Inop Inop
VOR/DDRMI Norm Norm Norm (1)
ATC N° 1 only Inop Inop
NAV
ISIS Norm Norm Norm
(1) IR2 and IR3 are lost 5 min after failure of the main generators. But, if IR3
replaces IR1 (ATT-HDG selector at CAPT3), IR3
remains supplied
(6) Lost, when speed is below 50 kt.
ENG 1 BLEED Norm BMC 1 inop BMC 1 inop
ENG 2 BLEED BMC 2 inop BMC 2 inop BMC 2 inop
APU BLEED Inop Inop Inop (1) PNEU
X BLEED (MAN CTL) Norm Inop Inop
(7) Restored, when speed is below 100 kt.
ECB - STARTER Norm (2) Inop Inop (1)
APU FUEL LP VALVE Norm Norm Norm
FUEL PUMP Norm Norm Norm
(1) Restored, when speed is below 100 kt.
(2) For APU start only.
FADEC A + B (1) A + B (1) A + B (1)
PWR PLT IGNITION A only A only A only
HP FUEL VALVE closure Norm Norm Norm
(1) Channels A and B are self-powered above 10 % N2. If N2 is below 10 % , only
Channel A is powered.
MISC MECH HORN Norm Norm Norm
FLT ON BAT ONLY
Flight time on batteries only may be increased to at least 30 min as follows:
ENG MODE
SEL.................................................................................................................................
NORM
ANTI ICE PITOT 1 C/B
(D02).................................................................................................................PULL
26 V ADIRU 1 C/B
(F07)........................................................................................................................PUL
L
CM 1 altitude, speed, and vertical speed indication on PFD are lost. Use standby
instruments
�� 7 min before landing:
ANTI ICE PITOT 1 C/B
(D02)....................................................................................................... RESET
�� After 1 min:
CAUTION This time delay is necessary to ensure reliable speed information even in
icing
conditions when the ADIRU is reset to ON.
26 V ADIRU 1 C/B
(F07)........................................................................................................ RESET
ABN-24
3/4
AQU3I1CK8 R/AEF3E1RE9N/ACE3 H2A0ND/A B3O2OK1
ABNORMAL AND
EMERGENCY PROCEDURES 30 AUG 10
A318/A319/A320/A321 FLEET MSN
ELEC EMER CONFIG SUMMARY
CRUISE
MAX
SPD..................................................................................................................................
......... 320 KT
ALTN
LAW
: PROT LOST
ONLY CAPT PITOT AND AOA HEATED
FUEL: CTR TK UNUSABLE BY GRAVITY (2T UNUSABLE)
COM: VHF1, ATC1, RMP1, only
NAV: ILS1, VOR1, GPS1 (if MMR is installed) only
LANDING CONF APPROACH SPEED
Use FLAP 3 VAPP = VREF + 10 kt + APPR COR/140 kt
APPROACH
MINIMUM RAT SPEED 140 KT CAT 2 INOP
SLATS FLAPS SLOW
�� When L/G down: USE MAN PITCH TRIM.
LANDING
FLARE: Only 2 spoilers per wing. Direct law
SPOILERS: Only 2 per wing
NO?REVERSER
BRAKING: ALTERNATE without antiskid
MAX BRK PR 1000 PSI
NO?NOSEWHEEL?STEERING
GO-AROUND
NIL
ACTUAL LANDING DISTANCES (m) WITH FAILURE WITHOUT REV
WEIGHT (1000 KG) 58 62 66 70 74 78 82 86 90 94
DRY runway 2 260 2 340 2 450 2 560 2 670 2 810 2 970 3 550 3 800 4 050
WET runway Refer to FPE-IFL Landing Distance Without AUTOBRAKE
- CONF FULL and apply LDG DIST Factor = 2.20
CONTA runway Refer to FPE-IFL Landing Distance Without AUTOBRAKE
- CONF FULL and apply LDG DIST Factor = 1.95
CORRECTIONS +1 000 ft above SL +10 kt tailwind
DRY Runway +4 % +17 %
Refer to ABN-80 VAPP CALCULATION for the approach speed computation method.
ABN-24
4/4
AQU3I1CK8 R/AEF3E1RE9N/ACE3 H2A0ND/A B3O2OK1
ABNORMAL AND
EMERGENCY PROCEDURES 30 AUG 10
Intentionally left blank
A318/A319/A320/A321 FLEET MSN
ABN-25
1/2
AQU3I1CK8 R/AEF3E1RE9N/ACE3 H2A0ND/A B3O2OK1
ABNORMAL AND
EMERGENCY PROCEDURES 30 AUG 10
A318/A319/A320/A321 FLEET , , , , , , , ,
, , , , , , , , , , , ,
, , , , ,
COCKPIT DOOR FAULT
This procedure should be applied, if the Cockpit Door Locking System (CDLS) fails.
This failure is indicated
when the FAULT light on the center pedestal’s COCKPIT DOOR panel comes on.
In the case of a DC BUS 2 fault, no FAULT indication appears on the center
pedestal’s COCKPIT DOOR
　
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