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Stabilize at VAPP before L/G down, to be trimmed for approach.
L/G GRAVITY EXTENSION
LANDING
FLARE: PITCH AUTHORITY REDUCED (No stabilizer).
MAN TRIM Unusable
Only 1 spoiler per wing – Direct law
SPOILERS: Only 1 per wing
NO?REVERSER
BRAKING: BRK Y ACCU PR ONLY (7 applications)
MAX BRK PR 1 000 PSI
NO?NOSEWHEEL?STEERING
GO-AROUND
NO GEAR RETRACTION. Increased fuel consumption
�� For circuit:
MAINTAIN SLATS/FLAPS CONFIGURATION
Recommended?speed: MAX SPD – 10 kt
�� For diversion:
�� If Flaps at zero:
SELECT CLEAN CONFIGURATION
Normal operating speeds
�� If Flaps not at zero:
MAINTAIN SLATS/FLAPS CONFIG
Recommended?speed: MAX SPD – 10 kt
ACTUAL LANDING DISTANCES (m) WITH FAILURE WITHOUT REV
WEIGHT (1 000 KG) 40 44 48 52 56 60 64 68 72 76
DRY runway 1 900 1 900 1 930 2 010 2 090 2 150 2 260 2 370 2 590 2 780
WET runway Refer to FPE-IFL Landing Distance Without AUTOBRAKE
- CONF FULL and apply LDG DIST Factor = 2.10
CONTA runway Refer to FPE-IFL Landing Distance Without AUTOBRAKE
- CONF FULL and apply LDG DIST Factor = 2.05
CORRECTIONS + 1 000 ft above SL + 10 kt tailwind
DRY runway + 3 % + 19 %
Refer to ABN-80 VAPP CALCULATION for approach speed computation method.
ABN-29
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AQU3I1CK8 R/AEF3E1RE9N/ACE3 H2A0ND/A B3O2OK1
ABNORMAL AND
EMERGENCY PROCEDURES 30 AUG 10
Intentionally left blank
A318/A319/A320/A321 FLEET , , , , , , ,
ABN-29
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AQU3I1CK8 R/AEF3E1RE9N/ACE3 H2A0ND/A B3O2OK1
ABNORMAL AND
EMERGENCY PROCEDURES 30 AUG 10
A318/A319/A320/A321 FLEET , , , , , , , ,
,
HYD B + Y SYS LO PR SUMMARY
CRUISE
MAX
SPD..................................................................................................................................
......... 320/.77
MANEUVER WITH CARE
Flight controls remain in normal law.
LANDING CONF APPROACH SPEED
3 VAPP = VREF +10 kt + APPR COR
FULL VAPP = VREF + APPR COR
W (1 000 KG) 44 48 52 56 60 64 68 72 76
VREF = VLS CONF FULL 110 113 117 122 126 130 134 138 142
APPROACH
SLATS SLOW/FLAPS SLOW CAT 2 INOP
L/G GRAVITY EXTENSION
LANDING
FLARE Only one ELEV and two spoilers per wing
SPOILERS Only 2 per wing
REVERSER Only N°1
BRAKING NORMAL
NO?NOSEWHEEL?STEERING
GO-AROUND
NO GEAR RETRACTION. Increased fuel consumption
ACTUAL LANDING DISTANCES (m) WITH FAILURE WITHOUT REV
(See )
WEIGHT (1000
KG) 40 44 48 52 56 60 64 68 72 76
DRY runway
(CONF full)
1 280 1 280 1 300 1 360 1 410 1 450 1 520 1 600 1 740 1 870
DRY runway
(CONF 3)
1 250 1 250 1 260 1 320 1 370 1 410 1 480 1 550 1 700 1 820
WET runway
(CONF full)
1 760 1 760 1 820 1 940 2 050 2 150 2 250 2 380 2 520 2 600
WET runway
(CONF 3)
1 800 1 800 1 860 1 980 2 100 2 200 2 300 2 440 2 580 2 660
CONTA
runway
(CONF full)
Refer to FPE-IFL Landing Distance Without AUTOBRAKE - CONF FULLand apply
LDG DIST Factor = 1.80
CONTA
runway
(CONF 3)
Refer to FPE-IFL Landing Distance Without AUTOBRAKE - CONF FULLand apply
LDG DIST Factor = 1.95
CORRECTIONS + 1 000 ft above SL + 10 kt tailwind
DRY runway + 3 % + 19 %
WET runway + 3 % + 23 %
(1) If the credit of the remaining reverser needs to be taken into account, Refer to
ABN-80-B LDG CONF/APPR SPD/LDG DIST
On Dry Runways Following Failures - 29 - HYD.
Refer to ABN-80 VAPP CALCULATION for approach speed computation method.
ABN-29
2/4
AQU3I1CK8 R/AEF3E1RE9N/ACE3 H2A0ND/A B3O2OK1
ABNORMAL AND
EMERGENCY PROCEDURES 30 AUG 10
A318/A319/A320/A321 FLEET , , , , , , , ,
,
HYD G + B SYS LO PR SUMMARY
CRUISE
SPD
BRK.................................................................................................................................
DO NOT USE
MAX
SPD..................................................................................................................................
....... 320/0.77
MANEUVER WITH CARE
ALTN LAW : PROT LOST
LANDING CONF APPROACH SPEED
Use FLAP 3 VAPP = VREF + 25 kt
W (1000 KG) 44 48 52 56 60 64 68 72 76
VREF = VLS CONF FULL 110 113 117 122 126 130 134 138 142
APPROACH
SLATS JAMMED/FLAPS SLOW CAT 2 INOP
ATHR..............................................................................................................................
.........................OFF
GPWS LDG FLAP
3.................................................................................................................................ON
　
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