SEQ 115
USE OF THE TABLE
A VREF accounts for corrections due to the failure and to the required landing configuration.
LDG DIST factor must be applied to the actual landing distance of CONF FULL.
FOR A SINGLE FAILURE
— Determine the required LDG CONF to be selected.
— Determine the A VREF.
 — VAPP = VREF + A VREF + WIND CORRECTION R (Refer to QRH page 2.31)
— Determine the LDG DIST factor.
FOR MULTIPLE FAILURES
— Use the lowest LDG CONE
— Use the highest A VREF to compute VAPP.
— Multiply the landing distance factors together, except when all failures are indicated by an asterisk (*). In this case, the highest factor has to be taken.
Example :
FLAPS FAULT (F < 3, S 1)
LDG CONF 3
A VREF = 10 KT
LDG DIST x 1.15*
BRK ANTI SKID
NORM CONF
A VREF = 0
LDG DIST x 1.4
TOTAL
LDG CONF 3
A VREF = 10 KT
LDG DIST x 1.61
ALTN LAW
LDG CONF 3
A VREF = 10 KT
LDG DIST x 1.2*
FLAPS FAULT (F < 1, S 1)
LDG CONF 3
A VREF = 25 KT
LDG DIST x 1.35*
TOTAL
LDG CONF 3
A VREF = 25 KT
LDG DIST x 1.35A319/A320/A321
oniatTril.,,
ABNORMAL PROCEDURES
REV 35
2.34

SEQ 001
R TRIPPED C/B RE-ENGAGEMENT
R In flight, do not re-engage a circuit breaker that has tripped by itself, R unless the Captain (using his/her emergency authority) judges it R necessary for the safe continuation of the flight. This procedure should R be adopted only as a last resort, and only one re-engagement should be R attempted.
R On ground, do not re-engage any wing tank fuel pump circuit breaker. R For all other circuit breakers, if the flight crew coordinates the action with R maintenance, they may re-engage a tripped C/B, provided the cause of R the tripped C/B is identified.
COMPUTER RESET
When a digital computer behaves abnormally, as a result of an electrical transient, for example, the Operator can stop the abnormal behavior by briefly interrupting the power supply to its processor.
The flight crew can reset most of the computers in this aircraft with a normal cockpit control (selector or pushbutton). However, for some systems, the only way to cut off electrical power is to pull the associated circuit breaker.
PROCEDURE
To perform a computer reset :
— Select the related normal cockpit control OFF, or pull the corresponding reset button or circuit breaker.
— Wait 3 seconds if a normal cockpit control is used, or 5 seconds if a circuit breaker is used (unless a different time is indicated).
— Select the related normal cockpit control ON, or push the corresponding reset button or circuit breaker,
— Wait 3 seconds for the end of the reset.

A319/A320/A321
oniatTril.,,
ABNORMAL PROCEDURES
REV 35
2.35

SEQ 001
COMPUTER RESET TABLE
The computers most prone to reset are listed in the table below, along with the associated reset procedure or FCOM reference, when applicable.
Specific reset procedures included in OEB or Temporary revisions are not referenced in this table and, when issued, supercede this table.
— On ground, almost all computers can be reset and are not limited to the ones indicated in the table.
The following computers are not allowed to be reset in specific circumstances :
. ECU (Engine Control Unit on CFM engines), or EEC (Electronic Engine Control on IAE engines), and EIU (Engine Interface Unit) while the engine is running.
. BSCU (Brake Steering Control Unit), if the aircraft is not stopped. (Refer to 3.04.32).
— In flight, as a general rule, the crew must restrict computer resets to those listed in the table, or to those in applicable TRs or OEBs. Before taking any action on other computes, the flight crew must consider and fully understand the consequences.
Also refer to the FCOM 3.04.24.
NOTE: In the table's "reser column, the "if applicable" note signifies that depending on the computer standard, the reset procedure may no longer be necessary. If this is the case, the reset procedure is removed from the applicable FCOM section.

A319/A320/A321
off,®y
ABNORMAL PROCEDURES
REV 35
2.36

SEQ 001
ATA
System malfunction
or ECAM
Warning/Caution
Affected
system
Reset
21
VENT AVNCS SYS
AEVC
On ground only :

FAULT

— Pull C/B Y 17 on 122VU.
— Wait 1 second before pushing the C/B.

AIR PACK 1(2) REGUL FAULT
PACK CONTROLLER 1(2)
Refer to the FCOM 3.02.21, if applicable.
22
AUTO FLT YAM
FAC 1(2)
　
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