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Combined Reset Tables Mod6

This document provides a table of circuit breakers and their locations for an aircraft. It also provides procedures for resetting computers, including opening the relevant circuit breaker, waiting, and then closing it. Resetting is suggested as a first step to resolve computer issues before further troubleshooting. The procedures are for resetting cabin pressure controllers, cargo ventilation controllers, and air conditioning pack regulators.

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Sallak Idris

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100% found this document useful (1 vote)

528 views275 pages

Combined Reset Tables Mod6

Uploaded by

Sallak Idris

We take content rights seriously. If you suspect this is your content, claim it here.

Available Formats

Download as PDF, TXT or read online on Scribd

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** ON A/C ALL

TASK 24-00-00-810-818-A
Computer Reset
1.Possible Causes

2.Fault Confirmation
Subtask 24-00-00-710-059-A
A.Test
(1) Not applicable
3. Fault Isolation
Subtask 24-00-00-865-051-A
A. Table of the circuit breakers used in this procedure:
PANEL DESIGNATION FIN LOCATION
49VU FUEL/FQI/CHAN/1 1QT A13
49VU ENGINE/2/FIRE DET/LOOP B 8WD2 A07
49VU ENGINE/1/FIRE DET/LOOP A 7WD1 A06
49VU ENGINE/2/FADEC A/AND EIU 2 2KS2 A05
49VU ENGINE/1/FADEC A/AND EIU 1 2KS1 A04
49VU FLIGHT CONTROLS/ELAC1/NORM/SPLY 15CE1 B11
49VU FLIGHT CONTROLS/FCDC1/SPLY 20CE1 B10
49VU FLIGHT CONTROLS/SEC1/NORM/SPLY 21CE1 B08
49VU AUTO FLT/FCU/1 9CA1 B05
49VU AUTO FLT/FAC1/28VDC 5CC1 B04
49VU AUTO FLT/FAC1/26VAC 14CC1 B03
49VU AUTO FLT/FMGC/1 10CA1 B02
49VU AUTO FLT/MCDU/1 11CA1 B01
49VU L/G/LGCIU/SYS1/NORM 1GA C09
49VU AIR COND/AFT CARGO/VENT/CTL & MONG 31HN C07
49VU AIR COND/AFT CARGO/VENT/CTL & MONG 31HN C07
49VU AIR COND/CAB/PRESS/CTL1 1HL D09
49VU AIR COND/TEMP CTL/SYS 1 CHAN B/28VDC 52HH D08
49VU EIS/DMC1/SPLY 10WT1 E11
49VU FWS/FWC1/SPLY 3WW F01
49VU NAV/MMR/1 42RT1 G12
49VU COM/CIDS/DIR ESS/2 157RH G02
49VU COM/CIDS/DIR ESS/1 150RH G01
49VU COM/CIDS/FLT ATTND PNL/ESS 171RH H01
** ON A/C 001-002
121VU DUMMY CB 11CA3 N21
** ON A/C ALL
121VU COM NAV/RAD ALTM/2 1SA2 K12
121VU COM NAV/RAD ALTM/1 1SA1 K11
121VU COM NAV/T2CAS 104SG K10
121VU APU/FIRE AND OVHT/DET/LOOP B 2WG L44
121VU APU/FIRE AND OVHT/DET/LOOP A 1WG L43
** ON A/C ALL
121VU FUEL/FQI/CHANNEL/1 AND 2 8QT L26
** ON A/C ALL
121VU ATSU 1 3TX1 L16

1
121VU ATSU 1/SWTG 5TX1 L15
121VU COM NAV/MMR/2 42RT2 L07
121VU HYDRAULIC/BRAKING AND 4GG M36
STEERING/SYS2/SPLY
121VU HYDRAULIC/BRAKING AND 3GG M35
STEERING/SYS2/CTL
121VU HYDRAULIC/BRAKING AND 1GG M34
STEERING/SYS1/CTL
121VU HYDRAULIC/BRAKING AND 2GG M33
STEERING/SYS1/IND AND/SPLY
121VU FUEL/FQI/CHAN/2 2QT M27
121VU AUTO FLT/FCU/2 9CA2 M21
121VU AUTO FLT/FAC2/28VDC 5CC2 M19
121VU AUTO FLT/FAC2/26VAC 14CC2 M18
121VU AUTO FLT/FMGC/2 10CA2 M17
121VU COM NAV/CIDS/DIR NORM/2 156RH M06
121VU COM NAV/CIDS/DIR NORM/1 151RH M05
121VU AUTO FLT/MCDU/2 11CA2 N20
121VU ENGINE/ENG2/FADEC B 4KS2 Q40
121VU ENGINE/ENG2/FIRE DET/LOOP A 7WD2 Q39
121VU ENGINE/ENG1/FIRE DET/LOOP B 8WD1 Q38
121VU HYDRAULIC/LGCIU/SYS2 2GA Q35
121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY 52GA Q34
121VU FLIGHT CONTROLS/FCDC2/SPLY 20CE2 Q20
121VU FLIGHT CONTROLS/SEC3/SPLY 21CE3 Q19
121VU FLIGHT CONTROLS/SEC2/SPLY 21CE2 Q18
121VU COM/FAP1/NORM 170RH Q14
121VU EIS/DMC3/SPLY 10WT3 Q09
121VU EIS/DMC2/SPLY 10WT2 Q08
121VU EIS/FWC2/SPLY 2WW Q07
121VU ENGINE/ENG1 AND 2/EVMU 1EV R44
121VU ENGINE/ENG1/FADEC B/AND EIU 1 4KS1 R41
121VU FLIGHT CONTROLS/ELAC2/NORM/SPLY 15CE2 R20
122VU AIR COND/TEMP CTL SYS 2/CHAN A/115VAC 53HH W22
122VU AIR COND/TEMP CTL SYS 2/CHAN A/28VDC 55HH W21
122VU ANTI ICE/WHC/2 5DG2 W13
122VU AIR COND/TEMP CTL SYS 1/CHAN A/115VAC 49HH X22
122VU AIR COND/TEMP CTL SYS 1/CHAN A/28VDC 51HH X21
122VU ANTI ICE/WHC/1 5DG1 X13
122VU AIR COND/CAB PRESS/CTL/2 2HL Y22
122VU AIR COND/TEMP CTL SYS 2/CHAN B/28VDC 56HH Y21
122VU AIR COND/TEMP CTL SYS 2/CHAN B/115VAC 54HH Y20
122VU AIR COND/TEMP CTL SYS 1/CHAN B/115VAC 50HH Y18
122VU AIR COND/AVNCS/VENT/MONG 3HQ Y17
** ON A/C 001-100
2001VU VACUUM TOILET SYSTEM/VACUUM SYS 35MG A06
** ON A/C 101-200

2
2001VU VACU TOIL SYS-VACUUM-SYS 35MG A06

** ON A/C ALL

Subtask 24-00-00-810-069-A
B.Computer reset procedure

NOTE: This reset procedure is used when a computer does not operate correctly.

NOTE:The line maintenance personnel can use it a first time to avoid a computer replacement (a reset must be
done for the applicable computer as indicated in the Computer Reset Table).

But, if there is more than one reset for each flight cycle for a given computer, it is necessary to do the
specific troubleshooting procedure for the applicable system.

If after a reset, the computer operates correctly, no more action is necessary.

(1)To do computer reset:

(a)Set the related normal cockpit control to OFF, or open the related circuit breaker as specified in the reset
procedure.
(b)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).
(c)Set the related normal cockpit control to ON, or close the related circuit breaker.
(d)Wait 3 seconds for the end of the reset.
Subtask 24-00-00-810-075-E
C. Air Conditioning
(1)Computer Reset Table
ATA SYSTEM MALFUNCTION COMPUTER RESET PROCEDURE

21 CAB PR SYS 1(2) FAULT CABIN For CPC 1:

PRESSURE - On panel 49VU, open the
CONTROLLER circuit breaker 1HL. D09
(CPC) 1(2) FOR CPC 2:
- On panel 122VU, open the
circuit breaker 2HL. Y22
After five seconds, close the
circuit breaker.

21 AIR FWD (AFT) CRG VENT CARGO On panel 49VU:

FAULT VENTILATION - Open the circuit breaker
31HN C07
CONTROLLER
After five seconds, close the
circuit breaker.

21 VENT AVNCS SYS FAULT AVIONICS EQUIPMENT VENTILATION On panel 122VU:

COMPUTER - Open the circuit breaker
3HQ. Y17
After five seconds, close the
circuit breaker.

21 AIR PACK 1(2) REGUL AIR COND For the ACSC 1:

FAULT SYSTEM - On panel 122VU, open

3
ATA SYSTEM MALFUNCTION COMPUTER RESET PROCEDURE

CONTROLLER the circuit breaker 49HH, X22

(ACSC) 1(2) circuit breaker 50HH Y18
and circuit breaker 51HH. X21
- On panel 49VU, open
the circuit breaker 52HH. D08
Then close the circuit
breakers.
For the ACSC2:
- On panel 122VU, open
the circuit breaker 53HH, W22
circuit breaker 54HH, Y20
circuit breaker 55HH and W21
circuit breaker 56HH. Y21
Then close the circuit
breakers.

21 COND AFT CRG HEAT AFT CARGO On panel 49VU:

FAULT
HEAT - Open the circuit breaker
31HN.
CONTROLLER
- After five seconds, close
the circuit breaker. C07
Subtask 24-00-00-810-076-A
D. Auto Flight
(1)Computer Reset Table
ATA SYSTEM MALFUNCTION COMPUTER RESET PROCEDURE

22 AUTO FLT YAW DAMPER 1(2) FAC1(2) Open these C/Bs with the
FAULT Yellow and Green hydraulic
systems pressurized:
- for the FAC 1: on the
panel 49VU, C/B 5CC1 B04
- for the FAC 2: on the
panel 121VU, C/B 5CC2 M19
Then close the C/Bs after 10
seconds.

22 WINDSHEAR DET FAULT or FAC 1+2 Open then close the C/Bs in
REAC W/S DET FAULT this the order:
- on the panel 49VU, C/B
B04 5CC1 and C/B 14CC1 B03
- on the panel 121VU, C/B
M19 5CC2 and C/B 14CC2. M18

22 AUTO FLT FCU 1(2) FAULT FCU For the FCU1:

4
ATA SYSTEM MALFUNCTION COMPUTER RESET PROCEDURE

- on the panel 49VU, open

the C/B 9CA1. B05
For the FCU2:
- on the panel 121VU, open
the C/B 9CA2. M21
Close the C/B after 5
seconds.
If the fault does not
continue, do a check of the
target and barometer
references shown, and
correct them if necessary
(reset successful).
If the fault continues, open
again the two C/Bs 9CA1 B05
on 49VU and 9CA2 on 121VU.
Close the C/Bs after 7 min, M21
with an interval less than
5 sec between side 1 and
side 2.
At least 30 sec are necessary
until the end of the FCU1
and FCU2 safety test.
If the fault does not
continue, do a check of the
target and barometer
references shown, and
correct them if necessary
(reset successful)
If the fault continues, end
of procedure (reset
unsuccessful).

22 One MCDU locked or blank MCDU Open then close the C/B of
Both MCDUs locked or blank FMGC the defective MCDU after 10
seconds:
- For the MCDU1: on the
panel 121VU or panel 49VU,
C/B 11CA1. B01
- For the MCDU2: on the
panel 121VU, C/B 11CA2. N20
- For the MCDU3: on the

5
ATA SYSTEM MALFUNCTION COMPUTER RESET PROCEDURE

panel 121VU, C/B 11CA3. N21

22 FMGC malfunction FMGC On the panel 121VU or 49VU:

- open the FMGC 1 C/B 10CA1 B02
and close it after 10
seconds.
NOTE: RESET DURATION 2 MIN.
If there is no reset of the
FMGC 1, do a reset of the
FMGC 2 on the panel 121VU:
- open the C/B 10CA2 and M17
close it after 10 seconds.
Subtask 24-00-00-810-077-D FOR LONG FMGC RESET SEE QRH
E. Communications
(1)Computer Reset Table
ATA SYSTEM MALFUNCTION COMPUTER RESET PROCEDURE

23 COM CIDS 1+2 FAULT CIDS - Open the C/Bs in this

order:
on the panel 49VU, C/B 150RH G01
on the panel 121VU, C/B
[SEE ATA23 ADDENDUM] 151RH M05
on the panel 49VU, C/B 157RH G02
on the panel 121VU, C/B
156RH M06
- After 10 seconds, close
the C/Bs in this order:
156RH, 157RH, 151RH and
150RH. M06,G02,M05&G01

23 Uncommanded EVAC horn CIDS Press the EVAC/HORN SHUT

actuation OFF switch.
If unsuccessful:
- Open the C/Bs in this
order:
on the panel 49VU, C/B 150RH G01
on the panel 121VU, C/B
151RH M05
on the panel 49VU, C/B 157RH G02
on the panel 121VU, C/B
156RH M06
- After 10 seconds, close
the C/Bs in this order:
156RH, 157RH, 151RH and M06,G02,M05&G01

6
ATA SYSTEM MALFUNCTION COMPUTER RESET PROCEDURE

150RH.

23 Frozen RMP RMP You must do a reset of all

the RMPs, one after the
other.
On the RMP control panel:
- set the ON/OFF switch to
OFF
- after 5 seconds, set the
ON/OFF switch to ON.

23 Frozen FAP FAP Open the C/Bs in this order:

On the panel 49VU, CB 171RH H01
On the panel 121VU, CB
170RH Q14
- After 10 seconds, close
the C/Bs in this order:
Q14 170RH, 171RH H01
If unsuccessful:
on the panel 2000VU (for PRAM/tape reproducer reset if installed)
- open the tape reproducer
/PRAM C/B 2RX. (Shed Bus 115V)
After 10 seconds, close the
C/B.

** ON A/C ALL

Subtask 24-00-00-810-088-A
F. Electrical Power
(1)Computer Reset Table
ATA SYSTEM MALFUNCTION COMPUTER RESET PROCEDURE

24 GPU cannot be connected GAPCU If at least one power source

to the aircraft (IDG 1 or IDG 2, APU GEN or
batteries) is connected to
the electrical network of
the aircraft:
- On the ELEC control panel
35VU:
. Push and release the
EXT PWR pushbutton
switch.
If no power source is

7
Customer : AAW Manual : TSM
Type : A318/A319/A320/A321 Selected applicability : ALL
Rev. Date : Nov 01, 2017
24-00-00-810-818-A - Computer Reset

ATA SYSTEM MALFUNCTION COMPUTER RESET PROCEDURE

/PRAM C/B 2RX.
After 10 seconds, close the
C/B.

Subtask 24-00-00-810-088-A
F. Electrical Power
(1) Computer Reset Table

ATA SYSTEM MALFUNCTION COMPUTER RESET PROCEDURE

24 GPU cannot be connected GAPCU If at least one power source
to the aircraft (IDG 1 or IDG 2, APU GEN or
batteries) is connected to
the electrical network of
the aircraft:
- On the ELEC control panel
35VU:
. Push and release the
EXT PWR pushbutton
switch.
If no power source is
connected to the electrical
network of the aircraft:
- On the ELEC control panel
35VU:
. Push the BAT 1 and BAT 2
pushbutton switches
(the OFF legend goes
off).

Subtask 24-00-00-810-105-A
G. Fire Protection
(1) Computer Reset Table

ATA SYSTEM MALFUNCTION COMPUTER RESET PROCEDURE

26 ENG1(2) LOOP k FAULT ENGINE FDU On the panel 49VU:
- For ENG1 FDU, open the
C/B 7WD1. A06
- For ENG2 FDU, open the
C/B 8WD2. A07
On the panel 121VU:
- For ENG1 FDU, open the
C/B 8WD1. Q38
- For ENG2 FDU, open the
C/B 7WD2. Q39
After 5 seconds, close
the C/Bs.
26 APU FIRE LOOP k FAULT APU FDU On the panel 121VU: L44 & L43
- Open the C/Bs 2WG and 1WG.
After 5 seconds, close the
C/Bs.

Print Date: January 03, 2018 Page 7 of 13

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
ATA SYSTEM MALFUNCTION COMPUTER RESET PROCEDURE

connected to the electrical

network of the aircraft:
- On the ELEC control panel
35VU:
. Push the BAT 1 and BAT 2
pushbutton switches
(the OFF legend goes
off).
Subtask 24-00-00-810-079-A
G. Flight Controls
(1)Computer Reset Table
ATA SYSTEM MALFUNCTION COMPUTER RESET PROCEDURE

27 F/CTL ELAC 1(2) FAULT ELAC Reset the defective ELAC:

F/CTL ALTN LAW FAULT - Make sure that the
hydraulic systems are
depressurized before the
reset.
- Set the ELAC pushbutton
switch to OFF, then to ON.

27 ELAC or SEC malfunction ELAC or SEC Reset the defective ELAC:

- Make sure that the
hydraulic systems are
*WHEN RESETTING SEC/ELAC: depressurized before the
1. HYD SYS DEPRESSURIZED. reset.
2. WAIT 30s AFTER RELEASING P/B SW Open, then close the C/B of
(OR PULLING CB). the defective ELAC or SEC.
3. WAIT 60s AFTER PUSHING P/B SW For the ELAC 1(2):
(OR PUSHING CB). - On the panel 49VU, C/B
4. C/O GRD SCAN BEFORE RESET 15CE1. B11
(RESETTING CAN MODIFY MAINT MSG). - On the panel 121VU, C/B
15CE2. R20
For the SEC 1(2)(3):
- On the panel 49VU, C/B
21CE1. B08
- On the panel 121VU, C/B
21CE2 or 21CE3. Q18 or Q19

27 E/W FCDC1(2) FAULT FCDC On the panel 49VU:

- For FCDC1, open the C/B
20CE1. B10
- For FCDC2, open the C/B

8
ATA SYSTEM MALFUNCTION COMPUTER RESET PROCEDURE

20CE2. Q20
- After 5 seconds, close
the C/Bs.
Subtask 24-00-00-810-089-A
H.Fuel
(1) Computer Reset Table
ATA SYSTEM MALFUNCTION COMPUTER RESET PROCEDURE

28 Loss of fuel quantity FQIC On the overhead circuit

indication or, breaker panel 49VU:
Simultaneous triggering - Open the C/B 1QT. A13
of FUEL L XFR VALVE On the rear circuit
CLOSED and FUEL R XFR breaker panel 121VU:
VALVE CLOSED, although - Open the C/Bs 2QT and 8QT. M27&L26
FUEL SD indicates no After 5 seconds, close the
anomaly. three C/B's.
Subtask 24-00-00-810-080-A
J. Ice and Rain Protection
(1)Computer Reset Table
ATA SYSTEM MALFUNCTION COMPUTER RESET PROCEDURE

30 ANTI ICE WHC Open then close the C/B of

L(R)/WINSHIELD (WINDOW) the defective WHC.
For the WHC1:
- on the panel 122VU, C/B
5DG1. X13
For the WHC2:
- on the panel 122VU, C/B
5DG2. W13
Subtask 24-00-00-810-081-A
K. Indicating/Recording Systems
(1)Computer Reset Table
ATA SYSTEM MALFUNCTION COMPUTER RESET PROCEDURE

31 FWS FWC 1(2) FAULT FWC Open then close the C/B of • Wait 50 s after losing the
the defective FWC C/Bs.
For the FWC1:
- on the panel 49VU, C/B 3WW F01
For the FWC2:
- on the panel 121VU, C/B
2WW. Q07

31 EIS DMC 1(2)(3) FAULT DMC Open then close the

circuit breaker of

9
ATA SYSTEM MALFUNCTION COMPUTER RESET PROCEDURE

the defective DMC

For the DMC1:
- on the overhead C/B panel
49VU, the circuit breaker
10WT1. E11
For the DMC2:
- on the rear C/B panel
121VU, the circuit breaker
10WT2. Q08
For the DMC3:
- on the rear C/B panel
121VU, the circuit breaker
10WT3. Q09

31 CAPT PFD DU malfunction CAPT PFD DU On the CAPT lightning/loud

speaker control-panel 301VU,
turn the PFD potentiometer
from the BRT position to
the OFF position.
- Wait for more than five
seconds.
On the CAPT lightning/loud
speaker control-panel 301VU,
turn the PFD potentiometer
from the OFF position to
the BRT position.

31 CAPT ND DU malfunction CAPT ND DU On the CAPT lightning/loud

speaker control-panel 301VU,
turn the ND potentiometer
from the BRT position to
the OFF position.
- Wait for more than five
seconds.
On the CAPT lightning/loud
speaker control-panel 301VU,
turn the ND potentiometer
from the OFF position to
the BRT position.

31 F/O PFD DU malfunction F/O PFD DU On the F/O lightning/loud

speaker control-panel 500VU,

10
ATA SYSTEM MALFUNCTION COMPUTER RESET PROCEDURE

turn the PFD potentiometer

from the BRT position to
the OFF position.
- Wait for more than five
seconds.
On the F/O lightning/loud
speaker control-panel 500VU,
turn the PFD potentiometer
from the OFF position to
the BRT position.

31 F/O ND DU malfunction F/O ND DU On the F/O lightning/loud

speaker control-panel 500VU,
turn the ND potentiometer
from the BRT position to
the OFF position.
- Wait for more than five
seconds.
On the F/O lightning/loud
speaker control-panel 500VU,
turn the ND potentiometer
from the OFF position to
the BRT position.

31 EWD malfunction EWD On the ECAM control panel

turn the UPPER DISPLAY
potentiometer from the
BRT + position to the OFF
position.
- Wait for more than five
seconds.
On the ECAM control panel
turn the UPPER DISPLAY
potentiometer from the
OFF position to the BRT +
position.

31 SD malfunction SD On the ECAM control panel

turn the LOWER DISPLAY
potentiometer from the
BRT position to the OFF
position.

11
ATA SYSTEM MALFUNCTION COMPUTER RESET PROCEDURE

- Wait for more than five

seconds.
On the ECAM control panel
turn the LOWER DISPLAY
potentiometer from the
OFF position to the BRT
position.
Subtask 24-00-00-810-082-A
L. Landing Gear
(1)Computer Reset Table
ATA SYSTEM MALFUNCTION COMPUTER RESET PROCEDURE

32 Braking malfunction BSCU On the panel 121VU:

- open the C/Bs 1GG, 2GG,
Notes:
1. Reset attempt first by anti-skid/NWS sw. 3GG and 4GG M34,M33,M35&M36
2. Resetting by anti-skid/NWS sw causes - after 5 seconds, close
NO BSCU 1 DATA maint msg to show. the CB's

32 L/G LGCIU 1(2) FAULT LGCIU 1(2) For the LGCIU 1:

• Depressurize the green
- on the panel 121VU, open
hydraulic system before resetting
Q34 the C/B 52GA then on 49VU, the LGCIU.
C09 C/B 1GA. Then close the • Wait for 15 s , before closing the
C09 C/B 1GA and C/B 52GA Q34 CBs.
• If L/G BITE inaccessible,
For the LGCIU 2:
energize A/C from EXT PWR
- on the panel 121VU, open
then close the C/B 2GA. Q35
Subtask 24-00-00-810-083-B
M. Navigation
(1)Computer Reset Table
ATA SYSTEM MALFUNCTION COMPUTER RESET PROCEDURE

34 NAV MMR 1(2) FAULT MMR1(2) For the MMR 1:

If ILS1 & ILS2 shows (not
- On the panel 49VU, open MMR1 & MMR2) on MCDU
the C/B 42RT1. G12 NAV page, open and close
- After 5 seconds, close the
after 30s CFDIU BACK UP &
C/B.
For the MMR 2: CFDIU SUPPLY (J17 & J18)
- On the panel 121VU, open [with engines shutdown &
the C/B 42RT2. L07 MMRs CBs closed]. Wait
- After 5 seconds, close the
180s.
C/B.

34 NAV TCAS FAULT T2CAS On the panel 121VU:

- Open the C/B 104SG. K10

12
ATA SYSTEM MALFUNCTION COMPUTER RESET PROCEDURE

- After 5 seconds, close

the C/B.

34 NAV GPWS FAULT T2CAS On the panel 121VU:

NAV GPWS TERR DET FAULT - Open the C/B 104SG. K10
- After 5 seconds, close
the C/B.

34 NAV GPS 1(2) FAULT GPSSU On the panel 121VU:

- For GPSSU1, open the C/B
2SN1. (for MMR1 G12)
- For GPSSU2, open the C/B
2SN2. (for MMR2 L07)
- After 5 seconds, close
the C/Bs.

34 NAV RA 1(2) FAULT XCVR-RA On the panel 121VU:

- For XCVR-RA 1, open the
C/B 1SA1. K11
- For XCVR-RA 2, open the
C/B 1SA2. K12
- After 5 seconds, close
the C/Bs.
Subtask 24-00-00-810-085-A
N. Information Systems
(1)Computer Reset Table
ATA SYSTEM MALFUNCTION COMPUTER RESET PROCEDURE

46 ATSU malfunction ATSU On the rear circuit

breaker panel 121VU:
- Open the C/Bs in this
order: 3TX1 and 5TX1. L16&L15
- After 5 seconds, close
the C/Bs in this order:
5TX1 and 3TX1. L15&L16
Subtask 24-00-00-810-086-A
P.Engine
(1) Computer Reset Table
ATA SYSTEM COMPUTER RESET PROCEDURE
MALFUNCTION

70 ENG 1(2) IGN A + B FADEC and On the overhead circuit-breaker panel 49VU and rear circuit-breaker
FAULT panel 121VU, open then close the circuit breakers of the defective
EIU
FADEC.
For engine 1:

13
ATA SYSTEM COMPUTER RESET PROCEDURE
MALFUNCTION
A04 - 2KS1 and 4KS1. R41
For engine 2:
A05 - 2KS2 and 4KS2. Q40
70 ENG 1(2) FADEC FADEC On the overhead circuit-breaker panel 49VU and rear circuit-breaker
A(B) FAULT panel 121VU, open then close the circuit breakers of the defective
FADEC.
For engine 1:
A04 - 2KS1 and 4KS1. R41
For engine 2:
A05 - 2KS2 and 4KS2. Q40
Subtask 24-00-00-810-090-A
Q. Engine Indicating
(1)Computer Reset Table
ATA SYSTEM MALFUNCTION COMPUTER RESET PROCEDURE

77 Loss of N1VIB and N2VIB EVMU On the panel 121VU:

indications for ENG1(2) - Open the C/B 2EV. R44
in ECAM SD - After 5 seconds, close the
C/B.

14
TSM - AAW - A318/A319/A320/A321 REV DATE: Nov 01/2022
Tail Number - MSN - FSN: ALL
24-00-00-810-818-A - System Reset Guidelines

** ON A/C FSN ALL

TASK 24-00-00-810-818-A
System Reset Guidelines
1. Possible Causes:
2. Job Set-up Information

A. Referenced Information

REFERENCE DESIGNATION
Ref. AMM 10-11-00-555-014 Removal of the Aircraft Protection Equipment

3. Fault Confirmation
SUBTASK 24-00-00-710-059-A
A. Test
(1) Not applicable

4. Fault Isolation
SUBTASK 24-00-00-810-069-A
A. System Reset Procedure
(1) The aim of this task is to provide guidelines for system reset and table further to fault indication
due to transient or intermittent failure.
(a) If it is obvious that this "System malfunction or ECAM Alert" is consecutive to an electrical
power up or transient, then the reset may be performed according to the following
guidelines:
- for the affected computers listed in the reset table: a reset is authorized only for the
listed ECAM alerts or system malfunctions
- for all other computers: there is no restriction.
(b) If this "System malfunction or ECAM Alert" is not consecutive to an electrical power up or
transient, then the maintenance operators shall do a check of the fault history and:
1 if an ECAM Alert linked with this computer has been triggered on the previous
flights then the TSM procedure shall be performed
2 if no ECAM Alert linked with this computer has been triggered on the previous
flights then the reset may be performed according to the following guidelines:
- for the affected computers listed in the reset table: a reset is authorized only
for the listed ECAM alerts or system malfunctions
- for all other computers: there is no restriction.
(2) To do system reset:
(a) Set the related normal cockpit control to OFF, or open the related circuit breaker as
specified in the reset procedure.
(b)

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System Reset Guidelines CONFIDENTIAL AND PROPRIETARY DOCUMENT. PRINT DATE: Feb 14/2023
TSM - AAW - A318/A319/A320/A321 REV DATE: Nov 01/2022
Tail Number - MSN - FSN: ALL
24-00-00-810-818-A - System Reset Guidelines

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).
(c) Set the related normal cockpit control to ON, or close the related circuit breaker.
(d) Wait 3 seconds for the end of the reset.
SUBTASK 24-00-00-868-089-A
B. If it is obvious that this "System malfunction or ECAM Alert" is consecutive to an electrical power up or
transient, then the reset may be performed.
If this "System malfunction or ECAM Alert" is not consecutive to an electrical power up or transient,
then the maintenance operators shall do a check of the fault history and:
- If an ECAM Alert linked with this computer has been triggered on the previous flights then the
TSM procedure shall be performed,
- If no ECAM Alert linked with this computer has been triggered on the previous flights then the
reset may be performed.

ECAM-ALERT OR SYSTEM AFFECTED

ATA RESET PROCEDURE
MALFUNCTION COMPUTER
21 VENT AVNCS SYS FAULT AEVC Open the C/B 3HQ. Y17
After 5 seconds, close the C/B 3HQ.

Table of the circuit breakers used in this procedure:

PANEL DESIGNATION FIN LOCATION

122VU AIR COND/AVNCS/VENT/MONG 3HQ Y17

SUBTASK 24-00-00-868-079-A
C. If it is obvious that this "System malfunction or ECAM Alert" is consecutive to an electrical power up or
transient, then the reset may be performed.
If this "System malfunction or ECAM Alert" is not consecutive to an electrical power up or transient,
then the maintenance operators shall do a check of the fault history and:
- If an ECAM Alert linked with this computer has been triggered on the previous flights then the
TSM procedure shall be performed,
- If no ECAM Alert linked with this computer has been triggered on the previous flights then the
reset may be performed.

ECAM-ALERT OR SYSTEM AFFECTED

ATA RESET PROCEDURE
MALFUNCTION COMPUTER
21 CAB PR SYS 1 FAULT CPC (Cabin For CPC 1: D09
CAB PR SYS 2 FAULT Pressure - Open the C/B 1HL,
Controller) - After 5 seconds, close the C/B
1HL.
For CPC 2: Y22
- Open the C/B 2HL,
- After 5 seconds, close the C/B
2HL.

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Table of the circuit breakers used in this procedure:

PANEL DESIGNATION FIN LOCATION

49VU AIR COND/CAB/PRESS/CTL1 1HL D09
122VU AIR COND/CAB PRESS/CTL/2 2HL Y22

SUBTASK 24-00-00-868-088-B
D. If it is obvious that this "System malfunction or ECAM Alert" is consecutive to an electrical power up or
transient, then the reset may be performed.
If this "System malfunction or ECAM Alert" is not consecutive to an electrical power up or transient,
then the maintenance operators shall do a check of the fault history and:
- If an ECAM Alert linked with this computer has been triggered on the previous flights then the
TSM procedure shall be performed,
- If no ECAM Alert linked with this computer has been triggered on the previous flights then the
reset may be performed.

ECAM-ALERT OR SYSTEM AFFECTED

ATA RESET PROCEDURE
MALFUNCTION COMPUTER
21 AIR PACK 1 REGUL FAULT AIR COND Do this procedure in the sequence
AIR PACK 2 REGUL FAULT SYSTEM shown: W21
COND TRIM AIR SYS FAULT (ACSC (Air- - Open the C/Bs 55HH and
Conditioning 53HH, W22
System - Open the C/Bs 51HH and X21
Controller) 49HH, X22 Y18 Y20
- Open the C/Bs 50HH, 22HH
and 56HH,Y21
- Open the C/B 52HH, D08
- After 5 seconds close the C/Bs
52HH, 50HH, 22HH, 56HH,
51HH, 49HH, 55HH and 53HH.

NOTE: During the reset, a small

increase of the engine
thrust may be observed. If
the parking brake is set,
vibrations can occur.

Table of the circuit breakers used in this procedure:

PANEL DESIGNATION FIN LOCATION

AIR COND/TEMP CTL/SYS 1 CHAN B
49VU 52HH D08
/28VDC
AIR COND/TEMP CTL SYS 2/CHAN A
122VU 53HH W22
/115VAC
AIR COND/TEMP CTL SYS 2/CHAN A

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122VU /28VDC 55HH W21

AIR COND/TEMP CTL SYS 1/CHAN A
122VU 49HH X22
/115VAC
AIR COND/TEMP CTL SYS 1/CHAN A
122VU 51HH X21
/28VDC
AIR COND/TEMP CTL SYS 2/CHAN B
122VU 56HH Y21
/28VDC
AIR COND/TEMP CTL SYS 1/CHAN B
122VU 50HH Y18
/115VAC

SUBTASK 24-00-00-868-055-A
E. If it is obvious that this "System malfunction or ECAM Alert" is consecutive to an electrical power up or
transient, then the reset may be performed.
If this "System malfunction or ECAM Alert" is not consecutive to an electrical power up or transient,
then the maintenance operators shall do a check of the fault history and:
- If an ECAM Alert linked with this computer has been triggered on the previous flights then the
TSM procedure shall be performed,
- If no ECAM Alert linked with this computer has been triggered on the previous flights then the
reset may be performed.

ECAM-ALERT OR SYSTEM AFFECTED

ATA RESET PROCEDURE
MALFUNCTION COMPUTER
22 AUTO FLT FCU 1 FAULT FCU For the FCU 1:
AUTO FLT FCU 2 FAULT - Open the C/B 9CA1, B05
- After 5 seconds, close the C/B
9CA1.
For the FCU 2:
- Open the C/B 9CA2, M21
- After 5 seconds, close the C/B
9CA2.
If the fault does not continue:
- Do a check of the target and
barometer references shown,
and correct them if necessary
(reset successful).
If the fault continues: B05
- Open the C/Bs 9CA1 and
9CA2, M21
- After 7 minutes, close the C/Bs
9CA1 and 9CA2 in less than 5
seconds between side 1 and
side 2,
-

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A minimum of 30 seconds are

necessary for the FCU 1 and
the FCU 2 to complete the
safety test,
- If the fault does not continue:
* Do a check of the target and
barometer references shown, and
correct them if necessary (reset
successful).
- If the fault continues:
* End of procedure (reset
unsuccessful).

Table of the circuit breakers used in this procedure:

PANEL DESIGNATION FIN LOCATION

49VU AUTO FLT/FCU/1 9CA1 B05
121VU AUTO FLT/FCU/2 9CA2 M21

SUBTASK 24-00-00-868-056-A
F. If it is obvious that this "System malfunction or ECAM Alert" is consecutive to an electrical power up or
transient, then the reset may be performed.
If this "System malfunction or ECAM Alert" is not consecutive to an electrical power up or transient,
then the maintenance operators shall do a check of the fault history and:
- If an ECAM Alert linked with this computer has been triggered on the previous flights then the
TSM procedure shall be performed,
- If no ECAM Alert linked with this computer has been triggered on the previous flights then the
reset may be performed.

ECAM-ALERT OR SYSTEM AFFECTED

ATA RESET PROCEDURE
MALFUNCTION COMPUTER
22 AUTO FLT FCU 1+2 FAULT FCU Open the C/Bs 9CA1 and 9CA2. B05,M21
After 5 seconds close the C/Bs 9CA1
and 9CA2.
If the fault does not continue:
- Do a check of the target and
barometer references shown,
and correct them if necessary
(reset successful).
If the fault continues: B05,M21
- Open the C/Bs 9CA1 and
9CA2,
- After 7 minutes, close the C
/Bs 9CA1 and 9CA2 in less
than 5 seconds between side
1 and side 2,
-

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A minimum of 30 seconds are

necessary for the FCU 1 and
the FCU 2 to complete the
safety test,
- Do a check of the target and
barometer references shown,
and correct them if necessary
(reset successful),
- FCU targets are synchronized
on current aircraft values and
displayed as selected targets,
- Re-enter the barometer
altimeter setting value, if
necessary.

Table of the circuit breakers used in this procedure:

PANEL DESIGNATION FIN LOCATION

49VU AUTO FLT/FCU/1 9CA1 B05
121VU AUTO FLT/FCU/2 9CA2 M21

SUBTASK 24-00-00-868-057-A
G. If it is obvious that this "System malfunction or ECAM Alert" is consecutive to an electrical power up or
transient, then the reset may be performed.
If this "System malfunction or ECAM Alert" is not consecutive to an electrical power up or transient,
then the maintenance operators shall do a check of the fault history and:
- If an ECAM Alert linked with this computer has been triggered on the previous flights then the
TSM procedure shall be performed,
- If no ECAM Alert linked with this computer has been triggered on the previous flights then the
reset may be performed.

ECAM-ALERT OR SYSTEM AFFECTED

ATA RESET PROCEDURE
MALFUNCTION COMPUTER
22 AFS-MCDU-One MCDU locked or MCDU For the MCDU 1:
blank - Open the C/B 11CA1, B01
- After 10 seconds, close the C
/B 11CA1.
For the MCDU 2: N20
- Open the C/B 11CA2,
- After 10 seconds, close the C
/B 11CA2.
For the MCDU 3: N21 (Dummy CB)
- Open the C/B 11CA3,
- After 10 seconds, close the C
/B 11CA3.

Table of the circuit breakers used in this procedure:

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PANEL DESIGNATION FIN LOCATION

49VU AUTO FLT/MCDU/1 11CA1 B01
121VU AUTO FLT/MCDU/2 11CA2 N20

SUBTASK 24-00-00-868-058-A
H. If it is obvious that this "System malfunction or ECAM Alert" is consecutive to an electrical power up or
transient, then the reset may be performed.
If this "System malfunction or ECAM Alert" is not consecutive to an electrical power up or transient,
then the maintenance operators shall do a check of the fault history and:
- If an ECAM Alert linked with this computer has been triggered on the previous flights then the
TSM procedure shall be performed,
- If no ECAM Alert linked with this computer has been triggered on the previous flights then the
reset may be performed.

ECAM-ALERT OR SYSTEM AFFECTED

ATA RESET PROCEDURE
MALFUNCTION COMPUTER
22 AFS-FMGC malfunction FMGC If no engine running:
AFS-MCDU-All MCDUs locked or - Apply external power or APU
blank generator power,
- For FMGC 1:
* After 2 minutes, set the FD1 P/B
SW to OFF,
* Open the C/B 10CA1, B20
* After 10 seconds, close the C/B
10CA1.
- For FMGC 2:
* After 2 minutes, set the FD2 P/B
SW to OFF,
M17
* Open the C/B 10CA2,
* After 10 seconds, close the C/B
10CA2.
- Always wait 1 minute after the
reset or 1minute after the
"PLEASE WAIT" message
disappears from MCDU,
before engaging or
reengaging the FD and the AP
of the reset FMGC.
If engine running:
- For FMGC 1:
* Set the FD1 P/B SW to OFF,
* Open the C/B 10CA1, B20
* After 10 seconds, close the C/B
10CA1.
- For FMGC 2:

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* Set the the FD2 P/B SW to OFF,

* Open the C/B 10CA2, M17
* After 10 seconds, close the C/B
10CA2.
- Always wait 1 minute after the
reset or 1minute after the
"PLEASE WAIT" message
disappears from MCDU,
before engaging or
reengaging the FD and the AP
of the reset FMGC.
- If the FMGC reset is
unsuccessful:
* Consider FMGC reset with engines
not running.

NOTE: The FMGC reset is more

effective with engines not
running.

Table of the circuit breakers used in this procedure:

PANEL DESIGNATION FIN LOCATION

49VU AUTO FLT/FMGC/1 10CA1 B02
121VU AUTO FLT/FMGC/2 10CA2 M17

SUBTASK 24-00-00-868-103-A
J. If it is obvious that this "System malfunction or ECAM Alert" is consecutive to an electrical power up or
transient, then the reset may be performed.
If this "System malfunction or ECAM Alert" is not consecutive to an electrical power up or transient,
then the maintenance operators shall do a check of the fault history and:
- If an ECAM Alert linked with this computer has been triggered on the previous flights then the
TSM procedure shall be performed,
- If no ECAM Alert linked with this computer has been triggered on the previous flights then the
reset may be performed.

ECAM-ALERT OR SYSTEM AFFECTED

ATA RESET PROCEDURE
MALFUNCTION COMPUTER
22 AUTO FLT A/THR OFF FCU If no engine is in operation:
- On the FCU, push the A/THR
pushbutton switch to engage
the A/THR again (this step
cancels the ECAM message).
- On the thrust levers, push the
A/THR instinctive-disconnect
pushbutton-switch to
disconnect the A/THR.

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If a minimum of one engine is in

operation:
- Apply the external power or
the APU generator power.
- Set the ENG MASTER control
switches to the OFF position.
- On the FCU, push the A/THR
pushbutton switch to engage
the A/THR again (this step
cancels the ECAM message).
- On the thrust levers, push the
A/THR instinctive-disconnect
pushbutton-switch to
disconnect the A/THR.

SUBTASK 24-00-00-868-104-A
K. If it is obvious that this "System malfunction or ECAM Alert" is consecutive to an electrical power up or
transient, then the reset may be performed.
If this "System malfunction or ECAM Alert" is not consecutive to an electrical power up or transient,
then the maintenance operators shall do a check of the fault history and:
- If an ECAM Alert linked with this computer has been triggered on the previous flights then the
TSM procedure shall be performed,
- If no ECAM Alert linked with this computer has been triggered on the previous flights then the
reset may be performed.

ECAM-ALERT OR SYSTEM AFFECTED

ATA RESET PROCEDURE
MALFUNCTION COMPUTER
22 AFS-FAC-"CAT 3 DUAL" message FAC If the "CAT 3 DUAL" message is
is shown on the "INOP SYS" shown on the "INOP SYS" section of
section of the SD without other the SD without other ECAM message
ECAM message related to the FAC. (s):
- Change the AP in command.
If not satisfactory:
- Release the FAC 1 pushbutton
switch (the OFF legend comes
on).
- Wait for three seconds.
- Push the FAC 1 pushbutton
switch (the OFF legend goes
off).
Wait for the "AUTO FLT FAC 1
FAULT" message to go out of view:
- Release the FAC 2 pushbutton
switch (the OFF legend comes
on).
- Wait for three seconds.
-

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Push the FAC 2 pushbutton

switch (the OFF legend goes
off).

NOTE: If the "CAT 3 DUAL"

message (on the "INOP
SYS" section of the SD) is
related to an "ADR" or "IR"
ECAM message, the FAC
or the FMGC do not see
the ADR or the IR as
defective. Thus, a change
of the AP or a reset of the
FAC will not clear the "CAT
3 DUAL" message.

SUBTASK 24-00-00-868-090-D
L. If it is obvious that this "System malfunction or ECAM Alert" is consecutive to an electrical power up or
transient, then the reset may be performed.
If this "System malfunction or ECAM Alert" is not consecutive to an electrical power up or transient,
then the maintenance operators shall do a check of the fault history and:
- If an ECAM Alert linked with this computer has been triggered on the previous flights then the
TSM procedure shall be performed,
- If no ECAM Alert linked with this computer has been triggered on the previous flights then the
reset may be performed.

ECAM-ALERT OR SYSTEM AFFECTED

ATA RESET PROCEDURE
MALFUNCTION COMPUTER
23 COM CIDS 1+2 FAULT CIDS Do this procedure in the sequence
shown: P13
(Booting from ESS Power) - Open circuit breaker 147RH (if
installed). P14
- Open circuit breaker 146RH (if
installed). G01
- Open circuit breaker 150RH
and circuit breaker 157RH. G02
- Open circuit breaker 151RH M05
and circuit breaker 156RH. M06
- After 10 seconds, close circuit
breaker 150RH. G01
- Close circuit breaker 157RH. G02
- After 5 minutes, close circuit
breaker 151RH. M05
- Close circuit breaker 156RH. M06
- Close circuit breaker 147RH (if P13
installed).
- Close circuit breaker 146RH (if P14
installed).

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- After CIDS reset,

approximately 4 minutes are
necessary before recovering
normal operation.

Table of the circuit breakers used in this procedure:

PANEL DESIGNATION FIN LOCATION

49VU COM/CIDS/DIR ESS/2 157RH G02
49VU COM/CIDS/DIR ESS/1 150RH G01
121VU COM NAV/CIDS/DIR NORM/2 156RH M06
121VU COM NAV/CIDS/DIR NORM/1 151RH M05
121VU COM/CIDS/DIR 2/BAT 146RH P14
121VU COM/CIDS/DIR 1/BAT 147RH P13

SUBTASK 24-00-00-868-091-D
M. If it is obvious that this "System malfunction or ECAM Alert" is consecutive to an electrical power up or
transient, then the reset may be performed.
If this "System malfunction or ECAM Alert" is not consecutive to an electrical power up or transient,
then the maintenance operators shall do a check of the fault history and:
- If an ECAM Alert linked with this computer has been triggered on the previous flights then the
TSM procedure shall be performed,
- If no ECAM Alert linked with this computer has been triggered on the previous flights then the
reset may be performed.

ECAM-ALERT OR SYSTEM AFFECTED

ATA RESET PROCEDURE
MALFUNCTION COMPUTER
23 COM-CIDS-Evac horn starts CIDS Do this procedure in the sequence
spuriously shown:
- Press the EVAC/HORN SHUT
OFF SW.
- Set the EVAC CAPT & PURS
/CAPT SW to the CAPT only
position.
- After 3 seconds, if
unsuccessful, for DIR 2:
* Open the C/B 157RH, G02
* Open the C/B 156RH, M06
* If unsuccessful again, for DIR 1:
** Open the C/B 150RH, G01
** Open the C/B 151RH, M05
** After 1 minute, for DIR 2:
*** Close the C/B 156RH, M06
*** Close the C/B 157RH, G02

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- After CIDS reset,

approximately 4 minutes are
necessary before recovering
normal operation.

Table of the circuit breakers used in this procedure:

PANEL DESIGNATION FIN LOCATION

49VU COM/CIDS/DIR ESS/2 157RH G02
49VU COM/CIDS/DIR ESS/1 150RH G01
121VU COM NAV/CIDS/DIR NORM/2 156RH M06
121VU COM NAV/CIDS/DIR NORM/1 151RH M05

SUBTASK 24-00-00-868-092-A
N. If it is obvious that this "System malfunction or ECAM Alert" is consecutive to an electrical power up or
transient, then the reset may be performed.
If this "System malfunction or ECAM Alert" is not consecutive to an electrical power up or transient,
then the maintenance operators shall do a check of the fault history and:
- If an ECAM Alert linked with this computer has been triggered on the previous flights then the
TSM procedure shall be performed,
- If no ECAM Alert linked with this computer has been triggered on the previous flights then the
reset may be performed.

ECAM-ALERT OR SYSTEM AFFECTED

ATA RESET PROCEDURE
MALFUNCTION COMPUTER
23 COM-RMP-no function (frozen) RMP You must do a reset of all the RMPs,
one after the other.
On the RMP control panel:
- Set the ON/OFF SW to OFF,
- After 5 seconds, set the ON
/OFF SW to ON.

SUBTASK 24-00-00-868-093-D
P. If it is obvious that this "System malfunction or ECAM Alert" is consecutive to an electrical power up or
transient, then the reset may be performed.
If this "System malfunction or ECAM Alert" is not consecutive to an electrical power up or transient,
then the maintenance operators shall do a check of the fault history and:
- If an ECAM Alert linked with this computer has been triggered on the previous flights then the
TSM procedure shall be performed,
- If no ECAM Alert linked with this computer has been triggered on the previous flights then the
reset may be performed.

ECAM-ALERT OR SYSTEM AFFECTED

ATA RESET PROCEDURE
MALFUNCTION COMPUTER
23 Open the C/B 171RH, H01

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COM-CIDS-FAP - no function FAP or Tape Open the C/B 170RH, Q14

(frozen) reproducer After 10 seconds, close the C/B
/PRAM 170RH Q14
Close the C/B 171RH.H01
If unsuccessful, for tape reproducer
/PRAM:
- Open the C/B 2RX,
- After 10 seconds, close the C
/B 2RX.

Table of the circuit breakers used in this procedure:

PANEL DESIGNATION FIN LOCATION

49VU COM/CIDS/FLT ATTND PNL/ESS 171RH H01
121VU COM/FAP1/NORM 170RH Q14

SUBTASK 24-00-00-868-074-A
Q. If it is obvious that this "System malfunction or ECAM Alert" is consecutive to an electrical power up or
transient, then the reset may be performed.
If this "System malfunction or ECAM Alert" is not consecutive to an electrical power up or transient,
then the maintenance operators shall do a check of the fault history and:
- If an ECAM Alert linked with this computer has been triggered on the previous flights then the
TSM procedure shall be performed,
- If no ECAM Alert linked with this computer has been triggered on the previous flights then the
reset may be performed.

ECAM-ALERT OR SYSTEM AFFECTED

ATA RESET PROCEDURE
MALFUNCTION COMPUTER
23 COM-SATCOM-malfunction SDU Open the C/B 102RV1.
After 5 seconds, close the C/B
N/A N/A 102RV1. N/A
NOTE: The Satellite Data Unit
(SDU) should reset in less
than 2 minutes.
You cannot perform a software reset
for SATCOM via MCDU.

Table of the circuit breakers used in this procedure:

** ON A/C FSN 003-003, 005-100, 103-200
SUBTASK 24-00-00-868-075-B
R. If it is obvious that this "System malfunction or ECAM Alert" is consecutive to an electrical power up or
transient, then the reset may be performed.
If this "System malfunction or ECAM Alert" is not consecutive to an electrical power up or transient,
then the maintenance operators shall do a check of the fault history and:
-

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If an ECAM Alert linked with this computer has been triggered on the previous flights then the
TSM procedure shall be performed,
- If no ECAM Alert linked with this computer has been triggered on the previous flights then the
reset may be performed.

ECAM-ALERT OR SYSTEM AFFECTED

ATA RESET PROCEDURE
MALFUNCTION COMPUTER
23 COM-Flickering or total loss of CDSS On the center pedestal VIDEO panel,
video camera display (on SD) with set the VIDEO rotary selector to OFF.
the VIDEO NOT AVAIL message On the overhead panel, set the
shown COCKPIT DOOR VIDEO P/B SW to
OFF.
After 2 minutes, on the overhead
panel, set the COCKPIT DOOR
VIDEO P/B SW to ON.
After 15 seconds, on the center
pedestal VIDEO panel, set the
VIDEO rotary selector to CKPT
ENTRY.

** ON A/C FSN ALL

SUBTASK 24-00-00-868-105-A
S. If it is obvious that this "System malfunction or ECAM Alert" is consecutive to an electrical power up or
transient, then the reset may be performed.
If this "System malfunction or ECAM Alert" is not consecutive to an electrical power up or transient,
then the maintenance operators shall do a check of the fault history and:
- If an ECAM Alert linked with this computer has been triggered on the previous flights then the
TSM procedure shall be performed,
- If no ECAM Alert linked with this computer has been triggered on the previous flights then the
reset may be performed.

ECAM-ALERT OR SYSTEM AFFECTED

ATA RESET PROCEDURE
MALFUNCTION COMPUTER
23 COM-HF Datalink/HF HF - Pull circuit breaker 1RE1. HA14
TRANSCEIVER - Wait for two seconds.
- Push circuit breaker 1RE1.

PANEL DESIGNATION FIN LOCATION

49VU HF1 1RE1 HA14

SUBTASK 24-00-00-868-059-A
T. If it is obvious that this "System malfunction or ECAM Alert" is consecutive to an electrical power up or
transient, then the reset may be performed.
If this "System malfunction or ECAM Alert" is not consecutive to an electrical power up or transient,
then the maintenance operators shall do a check of the fault history and:
-

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ECAM-ALERT OR SYSTEM AFFECTED

ATA RESET PROCEDURE
MALFUNCTION COMPUTER
24 ELEC-AC EXT PWR CTL-No PWR GAPCU If at least one power source (IDG 1
SPLY of A/C electrical circuits from or IDG 2, APU GEN or batteries) is
the external power connected to the electrical network of
the aircraft:
On the ELEC control panel 35VU:
- Push and release the EXT
PWR P/B SW.
If no power source is connected to
the electrical network of the aircraft:
On the ELEC control panel 35VU:
- Push the BAT 1 P/B SW and
the BAT 2 P/B SW (the OFF
legend goes off).

SUBTASK 24-00-00-868-061-B
U. If it is obvious that this "System malfunction or ECAM Alert" is consecutive to an electrical power up or
transient, then the reset may be performed.
If this "System malfunction or ECAM Alert" is not consecutive to an electrical power up or transient,
then the maintenance operators shall do a check of the fault history and:
- If an ECAM Alert linked with this computer has been triggered on the previous flights then the
TSM procedure shall be performed,
- If no ECAM Alert linked with this computer has been triggered on the previous flights then the
reset may be performed.

ECAM-ALERT OR SYSTEM AFFECTED

ATA RESET PROCEDURE
MALFUNCTION COMPUTER
26 SMOKE DET FAULT SDCU Do this procedure in the sequence
shown: C06
- Open the C/Bs 18WH and
15WH. C05 T17
- Open the C/Bs 17WH and
14WH. T18
- After 10 seconds, close at the
same time the C/Bs 18WH and C06,C05
15WH, and in less than 2
seconds, close at the same
time the C/Bs 17WH and T17,T18
14WH.
- After CIDS reset,
approximately 4 minutes are

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necessary before recovering

normal operation.

Table of the circuit breakers used in this procedure:

PANEL DESIGNATION FIN LOCATION

49VU AIR COND/CIDS/SDF/DIR2 ESS 18WH C06
49VU AIR COND/CIDS/SDF/DIR1 ESS 15WH C05
122VU AIR COND/CIDS/SDF/DIR NORM/2 14WH T18
122VU AIR COND/CIDS/SDF/DIR NORM/1 17WH T17

SUBTASK 24-00-00-868-061-A
DELETED
SUBTASK 24-00-00-868-062-A
V. If it is obvious that this "System malfunction or ECAM Alert" is consecutive to an electrical power up or
transient, then the reset may be performed.
If this "System malfunction or ECAM Alert" is not consecutive to an electrical power up or transient,
then the maintenance operators shall do a check of the fault history and:
- If an ECAM Alert linked with this computer has been triggered on the previous flights then the
TSM procedure shall be performed,
- If no ECAM Alert linked with this computer has been triggered on the previous flights then the
reset may be performed.

ECAM-ALERT OR SYSTEM AFFECTED

ATA RESET PROCEDURE
MALFUNCTION COMPUTER
26 SMOKE LAVATORY DET FAULT With all Do this procedure in the sequence
lavatories shown:
declared - Open the C/Bs 147RH and P13,P14
inoperative on 146RH (if installed).
the FAP. - Open the C/Bs 150RH and G01,G02
CIDS or CIDS- 157RH,
SDF - Open the C/Bs 151RH and M05,M06
156RH.
- After 10 seconds, close the C
/Bs 151RH and 156RH.M05,M06
- Close the C/Bs 150RH and
157RH, G01,G02
- Close the C/Bs 147RH and
146RH (if installed).P13,P14
- After CIDS reset,
approximately 4 minutes are
necessary before recovering
normal operation.
If unsuccessful, do this procedure in
the sequence shown:

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- Open the C/Bs 18WH and

15WH, C06,C05
- Open the C/Bs 17WH and
14WH, T17,T18
- After 10 seconds, close at the
same time the C/Bs 18WH C05,C06
and 15WH, and in less than 2
seconds, close at the same
time the C/Bs 17WH and
14WH, T17,T18
- After CIDS reset,
approximately 4 minutes are
necessary before recovering
normal operation.

Table of the circuit breakers used in this procedure:

PANEL DESIGNATION FIN LOCATION

49VU AIR COND/CIDS/SDF/DIR2 ESS 18WH C06
49VU AIR COND/CIDS/SDF/DIR1 ESS 15WH C05
49VU COM/CIDS/DIR ESS/2 157RH G02
49VU COM/CIDS/DIR ESS/1 150RH G01
121VU COM NAV/CIDS/DIR NORM/2 156RH M06
121VU COM NAV/CIDS/DIR NORM/1 151RH M05
121VU COM/CIDS/DIR 2/BAT 146RH P14
121VU COM/CIDS/DIR 1/BAT 147RH P13
122VU AIR COND/CIDS/SDF/DIR NORM/2 14WH T18
122VU AIR COND/CIDS/SDF/DIR NORM/1 17WH T17

SUBTASK 24-00-00-868-063-A
W. If it is obvious that this "System malfunction or ECAM Alert" is consecutive to an electrical power up or
transient, then the reset may be performed.
If this "System malfunction or ECAM Alert" is not consecutive to an electrical power up or transient,
then the maintenance operators shall do a check of the fault history and:
- If an ECAM Alert linked with this computer has been triggered on the previous flights then the
TSM procedure shall be performed,
- If no ECAM Alert linked with this computer has been triggered on the previous flights then the
reset may be performed.

ECAM-ALERT OR SYSTEM AFFECTED

ATA RESET PROCEDURE
MALFUNCTION COMPUTER
26 SMOKE FWD CRG DET FAULT CIDS-SDF

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SMOKE LAV+CRG DET FAULT Do this procedure in the sequence

SMOKE AFT CRG DET FAULT shown:
SMOKE FWD CRG BTL1 FAULT - Open the C/Bs 18WH and
SMOKE FWD CRG BTL2 FAULT 15WH,C06,C05
SMOKE AFT CRG BTL1 FAULT - Open the C/Bs 17WH and
SMOKE AFT CRG BTL2 FAULT 14WH, T17,T18
- After 10 seconds, close at the
same time the C/Bs 18WH and C06,C05
15WH, and in less than 2
seconds, close at the same
time the C/Bs 17WH and
14WH. T17,T18
- After CIDS reset,
approximately 4 minutes are
necessary before recovering
normal operation.

Table of the circuit breakers used in this procedure:

PANEL DESIGNATION FIN LOCATION

49VU AIR COND/CIDS/SDF/DIR2 ESS 18WH C06
49VU AIR COND/CIDS/SDF/DIR1 ESS 15WH C05
122VU AIR COND/CIDS/SDF/DIR NORM/2 14WH T18
122VU AIR COND/CIDS/SDF/DIR NORM/1 17WH T17

SUBTASK 24-00-00-868-064-A

WARNING: MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS SURFACES
ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS
AND/OR DAMAGE TO EQUIPMENT.
X. If it is obvious that this "System malfunction or ECAM Alert" is consecutive to an electrical power up or
transient, then the reset may be performed.
If this "System malfunction or ECAM Alert" is not consecutive to an electrical power up or transient,
then the maintenance operators shall do a check of the fault history and:
- If an ECAM Alert linked with this computer has been triggered on the previous flights then the
TSM procedure shall be performed,
- If no ECAM Alert linked with this computer has been triggered on the previous flights then the
reset may be performed.

ECAM-ALERT OR SYSTEM AFFECTED

ATA RESET PROCEDURE
MALFUNCTION COMPUTER
27 F/CTL ELAC 1 PITCH FAULT ELAC CAUTION:
- Do not reset ELAC in case of
dispatch with MMEL item SEC
1 or SEC 2.

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- Do not attempt more than one

reset.
- Set ELAC 2 P/B SW to OFF.
- Set pitch trim to 5 UP position.
- Set ELAC 1 P/B SW to OFF.
- After 3 seconds, set ELAC 1 P
/B SW to ON.
- After 15 seconds, do a check
of pitch trim at 0 position.
- Do a check of the flight control.
- Set ELAC 2 P/B SW to ON.
- Set pitch trim to takeoff CG.

NOTE: Record the ELAC 1 reset in

the logbook (successful or
unsuccessful).

SUBTASK 24-00-00-868-065-A

WARNING: MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS SURFACES
ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS
AND/OR DAMAGE TO EQUIPMENT.
Y. If it is obvious that this "System malfunction or ECAM Alert" is consecutive to an electrical power up or
transient, then the reset may be performed.
If this "System malfunction or ECAM Alert" is not consecutive to an electrical power up or transient,
then the maintenance operators shall do a check of the fault history and:
- If an ECAM Alert linked with this computer has been triggered on the previous flights then the
TSM procedure shall be performed,
- If no ECAM Alert linked with this computer has been triggered on the previous flights then the
reset may be performed.

ECAM-ALERT OR SYSTEM AFFECTED

ATA RESET PROCEDURE
MALFUNCTION COMPUTER
27 F/CTL ELAC 2 PITCH FAULT ELAC CAUTION:
- Do not reset ELAC in case of
dispatch with MMEL item
ELAC 1, SEC 1 or SEC 2.
- Do not attempt more than one
reset.
- Set ELAC 1 P/B SW to OFF.
- Set pitch trim to 5 UP position.
- Set ELAC 2 P/B SW to OFF.
- After 3 seconds, set ELAC 2 P
/B SW to ON.
- After 15 seconds, do a check
of pitch trim at 0 position.
- Do a check of flight control.

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- Set ELAC 1 P/B SW to ON.

- Set pitch trim to takeoff CG.

NOTE: Record the ELAC 2 reset in

the logbook (successful or
unsuccessful).

SUBTASK 24-00-00-868-066-A

WARNING: MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS SURFACES
ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS
AND/OR DAMAGE TO EQUIPMENT.
AA. If it is obvious that this "System malfunction or ECAM Alert" is consecutive to an electrical power up or
transient, then the reset may be performed.
If this "System malfunction or ECAM Alert" is not consecutive to an electrical power up or transient,
then the maintenance operators shall do a check of the fault history and:
- If an ECAM Alert linked with this computer has been triggered on the previous flights then the
TSM procedure shall be performed,
- If no ECAM Alert linked with this computer has been triggered on the previous flights then the
reset may be performed.

ECAM-ALERT OR SYSTEM AFFECTED

ATA RESET PROCEDURE
MALFUNCTION COMPUTER
27 F/CTL AIL SERVO FAULT ELAC CAUTION:
- Do not reset ELAC if more
than one aileron actuator
indication box is displayed in
amber on the F/CTL SD page.
- Do not reset ELAC in case of
dispatch with MMEL item
ELAC 1, SEC 1, SEC 2 or
SEC 3.
- Do not attempt more than one
reset.
- Set ELAC 1 P/B SW to OFF.
- Set ELAC 2 P/B SW to OFF.
- After 3 seconds, set ELAC 2 P
/B SW to ON.
- Do a check of flight control.
- Set ELAC 2 P/B SW to OFF.
- Set ELAC 1 P/B SW to ON.
- Do a check of flight control.
- Set ELAC 2 P/B SW to ON.
- Set pitch trim to takeoff CG.

NOTE: Record the ELAC 1 and

ELAC 2 reset in the

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logbook (successful or
unsuccessful).

SUBTASK 24-00-00-868-067-A

WARNING: MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS SURFACES
ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS
AND/OR DAMAGE TO EQUIPMENT.
AB. If it is obvious that this "System malfunction or ECAM Alert" is consecutive to an electrical power up or
transient, then the reset may be performed.
If this "System malfunction or ECAM Alert" is not consecutive to an electrical power up or transient,
then the maintenance operators shall do a check of the fault history and:
- If an ECAM Alert linked with this computer has been triggered on the previous flights then the
TSM procedure shall be performed,
- If no ECAM Alert linked with this computer has been triggered on the previous flights then the
reset may be performed.

ECAM-ALERT OR SYSTEM AFFECTED

ATA RESET PROCEDURE
MALFUNCTION COMPUTER
27 F/CTL SPLR FAULT SEC CAUTION:
- Do not reset SEC in case of
dispatch with MMEL item
ELAC 1, SEC 1, SEC 2 or
SEC 3.
- Do not attempt more than one
reset.
- Set SEC 1 P/B SW to OFF.
- After 3 seconds, set SEC 1 P
/B SW to ON.
- Set SEC 2 P/B SW to OFF.
- After 3 seconds, set SEC 2 P
/B SW to ON.
- Set SEC 3 P/B SW to OFF.
- After 3 seconds, set SEC 3 P
/B SW to ON.
- Do a check of flight control.

NOTE: Record the SEC 1, SEC 2

and SEC 3 reset in the
logbook (successful or
unsuccessful).

SUBTASK 24-00-00-868-068-A
AC. If it is obvious that this "System malfunction or ECAM Alert" is consecutive to an electrical power up or
transient, then the reset may be performed.
If this "System malfunction or ECAM Alert" is not consecutive to an electrical power up or transient,
then the maintenance operators shall do a check of the fault history and:

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- If an ECAM Alert linked with this computer has been triggered on the previous flights then the
TSM procedure shall be performed,
- If no ECAM Alert linked with this computer has been triggered on the previous flights then the
reset may be performed.

ECAM-ALERT OR SYSTEM AFFECTED

ATA RESET PROCEDURE
MALFUNCTION COMPUTER
28 FUEL-Loss of quantity indication FQIC Open the C/B 1QT. A13
FUEL-Simultaneous triggering of Open the C/B 2QT. M27
FUEL L XFR VALVE CLOSED and Open the C/B 8QT. L26
FUEL R XFR VALVE CLOSED After 5 seconds, close the C/B 1QT.
although FUEL SD indicates no Close the C/B 2QT. A13,M27,L26
anomaly Close the C/B 8QT.
FUEL-Simultaneous triggering of
FUEL L OUTER XFR CLOSED NOTE: The fuel quantity indication
and FUEL R OUTER XFR is available after 1 minute.
CLOSED although FUEL SD
indicates no anomaly

Table of the circuit breakers used in this procedure:

PANEL DESIGNATION FIN LOCATION

49VU FUEL/FQI/CHAN/1 1QT A13
121VU FUEL/FQI/CHANNEL/1 AND 2 8QT L26
121VU FUEL/FQI/CHAN/2 2QT M27

SUBTASK 24-00-00-868-069-A
AD. If it is obvious that this "System malfunction or ECAM Alert" is consecutive to an electrical power up or
transient, then the reset may be performed.
If this "System malfunction or ECAM Alert" is not consecutive to an electrical power up or transient,
then the maintenance operators shall do a check of the fault history and:
- If an ECAM Alert linked with this computer has been triggered on the previous flights then the
TSM procedure shall be performed,
- If no ECAM Alert linked with this computer has been triggered on the previous flights then the
reset may be performed.

ECAM-ALERT OR SYSTEM AFFECTED

ATA RESET PROCEDURE
MALFUNCTION COMPUTER
30 ANTI ICE L WINDSHIELD WHC If the air conditioning packs are OFF
ANTI ICE L WINDOW with the OAT above 40 deg.C, and/or
ANTI ICE R WINDSHIELD the windshield is under direct
ANTI ICE R WINDOW sunlight, a spurious ANTI ICE L(R)
WINDSHIELD(WINDOW) may
trigger. In that case:
- Set both air conditioning packs
to ON,

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- After 5 minutes:
* For the WHC 1:
** Open the C/B 5DG1, X13
** Close the C/B 5DG1.
* For the WHC 2:
** Open the C/B 5DG2, W13
** Close the C/B 5DG2.

Table of the circuit breakers used in this procedure:

PANEL DESIGNATION FIN LOCATION

122VU ANTI ICE/WHC/2 5DG2 W13
122VU ANTI ICE/WHC/1 5DG1 X13

SUBTASK 24-00-00-868-070-A
AE. If it is obvious that this "System malfunction or ECAM Alert" is consecutive to an electrical power up or
transient, then the reset may be performed.
If this "System malfunction or ECAM Alert" is not consecutive to an electrical power up or transient,
then the maintenance operators shall do a check of the fault history and:
- If an ECAM Alert linked with this computer has been triggered on the previous flights then the
TSM procedure shall be performed,
- If no ECAM Alert linked with this computer has been triggered on the previous flights then the
reset may be performed.

ECAM-ALERT OR SYSTEM AFFECTED

ATA RESET PROCEDURE
MALFUNCTION COMPUTER
31 FWS FWC 1 FAULT FWC For the FWC 1:
FWS FWC 2 FAULT - Open the C/B 3WW, F01
- Close the C/B 3WW.
For the FWC 2:
- Open the C/B 2WW, Q07
- Close the C/B 2WW.
50 seconds are necessary after you
close the C/Bs.

Table of the circuit breakers used in this procedure:

PANEL DESIGNATION FIN LOCATION

49VU FWS/FWC1/SPLY 3WW F01
121VU EIS/FWC2/SPLY 2WW Q07

SUBTASK 24-00-00-868-071-A
AF. If it is obvious that this "System malfunction or ECAM Alert" is consecutive to an electrical power up or
transient, then the reset may be performed.

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If this "System malfunction or ECAM Alert" is not consecutive to an electrical power up or transient,
then the maintenance operators shall do a check of the fault history and:
- If an ECAM Alert linked with this computer has been triggered on the previous flights then the
TSM procedure shall be performed,
- If no ECAM Alert linked with this computer has been triggered on the previous flights then the
reset may be performed.

ECAM-ALERT OR SYSTEM AFFECTED

ATA RESET PROCEDURE
MALFUNCTION COMPUTER
32 L/G LGCIU 1 FAULT LGCIU Make sure that the protective covers
L/G LGCIU 2 FAULT on the probes are removed Ref.
AMM 10-11-00-555-014.
Depressurize the Green hydraulic
system:
- ENG 1 PUMP OFF
- PTU OFF
When there is no Green hydraulic
pressure:
To reset LGCIU1, do the steps that
follow:
- Open C/B 52GA.Q34
- Open C/B 1GA. C09
- After 15 seconds, close C/B
1GA.
- Close C/B 52GA.
To reset LGCIU2, do the steps that
follow:
- Open C/B 2GA. Q35
- After 15 seconds, close C/B
2GA.
After the LGCIU reset, pressurize the
Green hydraulic system:
- ENG 1 PUMP ON
- PTU AUTO

Table of the circuit breakers used in this procedure:

PANEL DESIGNATION FIN LOCATION

49VU L/G/LGCIU/SYS1/NORM 1GA C09
121VU HYDRAULIC/LGCIU/SYS2 2GA Q35
HYDRAULIC/LGCIU/SYS1/GRND
121VU 52GA Q34
SPLY

SUBTASK 24-00-00-868-072-A
AG. If it is obvious that this "System malfunction or ECAM Alert" is consecutive to an electrical power up or
transient, then the reset may be performed.

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ECAM-ALERT OR SYSTEM AFFECTED

ATA RESET PROCEDURE
MALFUNCTION COMPUTER
32 WHEEL N.W STEER FAULT BSCU Case A:
WHEEL N/W STRG FAULT If the three conditions below are
fulfilled:
- the WHEEL N/W STRG
FAULT alert was triggered just
after the engine start
- the N/W STRG DISC memo
was displayed before the start
of the pushback (before the
aircraft starts moving)
- the N/W STRG DISC memo
remained displayed even after
the pushback is finished
(nosewheel steering selector
bypass pin is in the steering
position).
Apply the below reset procedure.
If the ECAM alert disappears after
the reset, the flight crew may
continue the flight without
troubleshooting.
Case B:
In all other cases, including in case
of doubt on the above conditions,
troubleshooting must be performed
before continuing the flight.
Reset Procedure:
- STOP aircraft,
- Set PARK BRK handle to ON,
- Confirm the towing bar is
disconnected,
- Set A/SKID & N/W STRG SW
to OFF,
- Set A/SKID & N/W STRG SW
to ON.
After any BSCU reset:
- Do a check of brake efficiency,
- Do a check of absence of
aircraft veering,

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- Record the BSCU reset in the

logbook.

SUBTASK 24-00-00-868-073-A
AH. If it is obvious that this "System malfunction or ECAM Alert" is consecutive to an electrical power up or
transient, then the reset may be performed.
If this "System malfunction or ECAM Alert" is not consecutive to an electrical power up or transient,
then the maintenance operators shall do a check of the fault history and:
- If an ECAM Alert linked with this computer has been triggered on the previous flights then the
TSM procedure shall be performed,
- If no ECAM Alert linked with this computer has been triggered on the previous flights then the
reset may be performed.

ECAM-ALERT OR SYSTEM AFFECTED

ATA RESET PROCEDURE
MALFUNCTION COMPUTER
32 BRAKES SYS 1 FAULT BSCU Reset Procedure:
BRAKES BSCU CH1 FAULT - STOP aircraft,
BRAKES SYS 2 FAULT - Set PARK BRK handle to ON,
BRAKES BSCU CH2 FAULT - Confirm the towing bar is
BRAKES BSCU CH1 FAULT disconnected,
BRAKES BSCU CH2 FAULT - Set A/SKID & N/W STRG SW
to OFF,
- Set A/SKID & N/W STRG SW
to ON,
- If unsuccessful:
* Open the C/B 2GG and 1GG M33,M34
* Open the C/B 4GG and 2GG M36,M35
* Close the C/B 2GG, 1GG, 4GG and
2GG.
After a successful reset, resume to
normal operation.
After any BSCU reset:
- Do a check of the brake
efficiency,
- Record the BSCU reset in the
logbook.

Table of the circuit breakers used in this procedure:

PANEL DESIGNATION FIN LOCATION

HYDRAULIC/BRAKING AND
121VU 4GG M36
STEERING/SYS2/SPLY
HYDRAULIC/BRAKING AND
121VU 3GG M35
STEERING/SYS2/CTL
HYDRAULIC/BRAKING AND
121VU 1GG M34
STEERING/SYS1/CTL

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HYDRAULIC/BRAKING AND
121VU 2GG M33
STEERING/SYS1/IND AND/SPLY

SUBTASK 24-00-00-868-084-A
AJ. If it is obvious that this "System malfunction or ECAM Alert" is consecutive to an electrical power up or
transient, then the reset may be performed.
If this "System malfunction or ECAM Alert" is not consecutive to an electrical power up or transient,
then the maintenance operators shall do a check of the fault history and:
- If an ECAM Alert linked with this computer has been triggered on the previous flights then the
TSM procedure shall be performed,
- If no ECAM Alert linked with this computer has been triggered on the previous flights then the
reset may be performed.

ECAM-ALERT OR SYSTEM AFFECTED

ATA RESET PROCEDURE
MALFUNCTION COMPUTER
34 NAV-STBY-ISIS malfunction ISIS In aircraft without movement:
- Open circuit breaker 5FN. F12
- After five seconds, close circuit
breaker 5FN.
- Normal operation is possible
after approximately two
minutes.
- After ISIS reset, approximately
two minutes are necessary
before you start the normal
operation.

NOTE: If there is a small aircraft

movement during the circuit
breaker reset (refueling,
cargo loading conditions or
other conditions), the ATT
red flag comes into view on
the ISIS. In this condition,
push the RST pushbutton
for two seconds and wait
for two minutes before you
start the normal operation.

Table of the circuit breakers used in this procedure:

PANEL DESIGNATION FIN LOCATION

49VU NAV/STBY/INST 5FN F12

SUBTASK 24-00-00-868-086-A
AK. If it is obvious that this "System malfunction or ECAM Alert" is consecutive to an electrical power up or
transient, then the reset may be performed.

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ECAM-ALERT OR SYSTEM AFFECTED

ATA RESET PROCEDURE
MALFUNCTION COMPUTER
34 NAV TCAS FAULT TCAS For the applicable C/Bs only shown
or T2CAS in the C/B table:
or T/TISS - Open the C/B 4SG or 104SG
or 1004SG or 2004SG. K10
- After 5 seconds, close the C/B
4SG or 104SG or 1004SG or
2004SG. K10

Table of the circuit breakers used in this procedure:

PANEL DESIGNATION FIN LOCATION

121VU COM NAV/T2CAS 104SG K10

SUBTASK 24-00-00-868-087-A
AL. If it is obvious that this "System malfunction or ECAM Alert" is consecutive to an electrical power up or
transient, then the reset may be performed.
If this "System malfunction or ECAM Alert" is not consecutive to an electrical power up or transient,
then the maintenance operators shall do a check of the fault history and:
- If an ECAM Alert linked with this computer has been triggered on the previous flights then the
TSM procedure shall be performed,
- If no ECAM Alert linked with this computer has been triggered on the previous flights then the
reset may be performed.

ECAM-ALERT OR SYSTEM AFFECTED

ATA RESET PROCEDURE
MALFUNCTION COMPUTER
34 NAV GPWS FAULT GPWC Open the C/B 3WZ. P07
AND Set GPWS SYS P/B and GPWS
NAV GPWS TERR DET FAULT TERR P/B to ON. P07
After 5 seconds, close the C/B 3WZ.

Table of the circuit breakers used in this procedure:

SUBTASK 24-00-00-868-076-A
AM. If it is obvious that this "System malfunction or ECAM Alert" is consecutive to an electrical power up or
transient, then the reset may be performed.
If this "System malfunction or ECAM Alert" is not consecutive to an electrical power up or transient,
then the maintenance operators shall do a check of the fault history and:
-

JCP Title: 24-00-00-810-818-A - © AIRBUS S.A.S. ALL RIGHTS RESERVED. Page 28 of 31

ECAM-ALERT OR SYSTEM AFFECTED

ATA RESET PROCEDURE
MALFUNCTION COMPUTER
36 AIR ENG 1 BLEED FAULT Engine bleed If the PACK (non-affected side) is
AIR ENG 2 BLEED FAULT supply system operative, and if the Wing Anti-ice is
AIR ENG 1 BLEED ABNORM PR OFF:
AIR ENG2 BLEED ABNORM PR - ENG BLEED (affected side)
OFF
* If the ENG BLEED (affected side) P
/B SW FAULT light is on:
** Delay application of the reset until
FAULT light goes off.
* If the ENG BLEED (affected side) P
/B SW FAULT light is off:
** X BLEED: AUTO
** PACK (affected side): ON
** ENG BLEED (affected side): ON
- On the BLEED SD page,
make sure that the affected
bleed valve is open.
If AIR ENG (affected) BLEED FAULT
alert or AIR ENG (affected) BLEED
ABNORM PR alert reoccurs, or if the
bleed valve (affected side) not open
on the BLEED SD page:
- ENG BLEED (affected side):
OFF
- X BLEED: OPEN

NOTE: record the ENG BLEED

reset in the logbook
(successful or
unsuccessful).

SUBTASK 24-00-00-868-077-A
AN. If it is obvious that this "System malfunction or ECAM Alert" is consecutive to an electrical power up or
transient, then the reset may be performed.
If this "System malfunction or ECAM Alert" is not consecutive to an electrical power up or transient,
then the maintenance operators shall do a check of the fault history and:
- If an ECAM Alert linked with this computer has been triggered on the previous flights then the
TSM procedure shall be performed,
- If no ECAM Alert linked with this computer has been triggered on the previous flights then the
reset may be performed.

JCP Title: 24-00-00-810-818-A - © AIRBUS S.A.S. ALL RIGHTS RESERVED. Page 29 of 31

ATA ECAM-ALERT OR SYSTEM AFFECTED RESET PROCEDURE

MALFUNCTION COMPUTER
36 AIR ENG 1 BLEED NOT CLSD Engine bleed - ENG BLEED (affected side)
AIR ENG 2 BLEED NOT CLSD supply system OFF
* If the ENG BLEED (affected side) P
/B SW FAULT light is on:
** Delay application of the reset until
FAULT light goes off.
* If the ENG BLEED (affected side) P
/B SW FAULT light is off:
** ENG BLEED (affected side): ON
- On the BLEED SD page, make
sure that the affected bleed
valve is closed.

NOTE: record the ENG BLEED

reset in the logbook
(successful or
unsuccessful).

SUBTASK 24-00-00-868-097-A
AP. If it is obvious that this "System malfunction or ECAM Alert" is consecutive to an electrical power up or
transient, then the reset may be performed.
If this "System malfunction or ECAM Alert" is not consecutive to an electrical power up or transient,
then the maintenance operators shall do a check of the fault history and:
- If an ECAM Alert linked with this computer has been triggered on the previous flights then the
TSM procedure shall be performed,
- If no ECAM Alert linked with this computer has been triggered on the previous flights then the
reset may be performed.

ECAM-ALERT OR SYSTEM AFFECTED

ATA RESET PROCEDURE
MALFUNCTION COMPUTER
46 INFO SYS-ATIMS-ATSU ATSU The ATSU reset should be attempted
malfunction only if:
- INVALID DATA is displayed on
the DCDU, or
- key selection has no effect on
the DCDU or any of the MCDU
ATSU DATALINK submenus,
or
- ADS-C, CPDLC or AOC are
inoperative.
Open the C/B 3TX1. L16,L15
Open the C/B 5TX1,Open the C/B
5TX1.
After 5 seconds close the C/B 5XT1.
Close the C/B 3XT1. L15,L16

JCP Title: 24-00-00-810-818-A - © AIRBUS S.A.S. ALL RIGHTS RESERVED. Page 30 of 31

Table of the circuit breakers used in this procedure:

PANEL DESIGNATION FIN LOCATION

121VU ATSU 1 3TX1 L16
121VU ATSU 1/SWTG 5TX1 L15

JCP Title: 24-00-00-810-818-A - © AIRBUS S.A.S. ALL RIGHTS RESERVED. Page 31 of 31

System Reset Guidelines CONFIDENTIAL AND PROPRIETARY DOCUMENT. PRINT DATE: Feb 14/2023
21 Unable to complete ACSC 1&2 With all bleed sources OFF open, wait for 10 seconds and
temperature control test close the CBs for Sys 2 & Sys1:
(MCDU) W21,W22,Y21,Y20(X21,X22,D8,Y18)
21 Pack 1(2) Regulation Fault with ACSC 1(2) With all bleed sources OFF open, wait for 10 seconds and
Amber XX Bypass Valve close the CBs for Sys 2& Sys1:
Indication. W21,W22,Y21,Y20(X21,X22,D8,Y18)
(or a Spurious Fault)
21 TRIM AIR SYSTEM FAULT with ACSC 1(2) With all bleed sources OFF open, wait for 10 seconds and
Amber XX COCKPIT (or close the CBs for Sys 2 & Sys1:
FWD/AFT CABIN) Indication. Make sure that TSD fault code (">" at the right of Class
(or a Spurious Fault) number of fault message) gives 36F9 for sys1 / 5E09 for sys2.
W21,W22,Y21,Y20(X21,X22,D8,Y18)
21 BLOWER FAN 20HQ fault BLOWER FAN Push BLOWER/EXTRAXT FAN reset Pb/sw for > 2 sec.
EXTRACT FAN 18HQ fault EXTRACT FAN If red light stays on, replace fan.
Open for 60s and close FWC 1&2 CBs [F01,Q07] if warning
is latched.
21 VENT EXTRACT FAULT / VENT AEVC Open for > 5 sec and close AEVC CB  [Y17]
BLOWER FAULT / AVIONICS Open for 60s and close FWC 1&2 CBs [F01,Q07] if warning
SMOKE (on ECAM)   is latched.
(most Equip Cooling faults)    Note: Always do system BITE testing + read CLASS 3 FAULTS

22 CAT 2 Message on ECAM MMR 1&2 Open and close MMR 1&2 CBs [G12,L07]

STATUS (INOP SYS)

22 FMGC Malfunction, both FMGC 1&2 A. SHORT FMGC RESET:

MCDUs blank, INDEPENDENT Open and close after 10 sec FMGC 1&2 CBs  [B02,M17]
OPERATION, diff bet target B. LONG FMGC RESET:
speeds, Electrical Transient Effect Open and close after 15 min FMGC 1&2 CBs  [B02,M17]

NOTES:
1. If a reset of FMGC1 and FMGC2 is done at the same
time, the flight plan will be deleted.
2. Make sure FD Pb/switches OFF.
3. Reset FMSCs not less than 2 min after power‐up.
4. If Elec transient effect makes both FMGCs inop, reset
them one by one. If still faulty, open and close FMGC
1&2 CBs > 5sec at the same time.
5. If FMGC fault not detected on PFR or by AFS Test,
print and sent to Airbus FM & FG COM&MON TSD.

22 AP 1(2) engage PB inop FMGC 1(2) Open and close after >15s CBs 9CA1 & 10CA1 (9CA2 &
10CA2).
Wait 1 min and perform AFS TEST.
[B05 & B02 (M21 & M17)]
22 Yaw Damper Fault FAC 1(2) With Yellow and Green hydraulic systems pressurized open >
(Not resettable by Pb/sw ) 10 sec & close FAC 1(2) CBs in this sequence:
[B04 & B03 (M19 & M18)]

22 RTL, RUD TRIM, FAC inop FAC 1(2) open > 15 sec & close FAC 1(2) CBs in this sequence :
(Sys 1 or 2) [B04 (M19)]
Note: Do AFS GRD Scanning & Operational Test.

22 FD 1(2) engage PB inop FCU Open and close after >15s FCU 1(2) CBs.

(no ind on FMA or Pb/sw) [B05(M21)]

1
23 HF/VHF EMITTING (or COM FWC 1&2 Open for 60s and close FWCs CBs before engine start (if no
SINGLE PTT STUCK) remains on actual fault present).
after releasing handmike, RAD [F01,Q07]
and sidestick PTTs
23 Loss of the RMP1, RMP2 and RMP 1/2/3 Switch all RMPs off.
RMP3 Displays Open >5s CBs (2RG1), (2RG2) and (2RG3). One by one close
each CB and the respective RMP sw, and check each display.
[G10,L02,L03]
23 FAULT IN ALL CIDS CABIN CIDS DIR 1&2 With a cabin door open and EMER LIGHT switch off, open,
FUNCTIONS (or BOOMSET(s), wait for 10 seconds the circuit breakers in this sequence and
HANDEST(s) PA or interphone close them in reverse order:
function, FSB switch), Incorrect [G01, G02, C05, C06, M05, M06, T18, T17]
Doors/Slides status Perform Interface & Power‐up test after 120s.
Note1: Wait 4 min to recover CIDS operation.
Note2: To make Dir2 active (for T/S), keep Dir1 CBs open and
c/o power up‐test.
Note3: It is possible when booting in ESS mode, no internal
faults will show.
23 Complete Loss of any CIDS DIR 1/2 Deactivation of a faulty DIR may recover a lost CIDS function
Function (AMM 23-73-00-040-001-A / MEL 23-73-01-01A) by opening
in sequence:
For DIR1 [P13,G01,M05] ‐ For DIR2 [P14,G02,M06]
Perform Interface & Power‐up test after 120s.

23 Fault in Dir1 & Dir2 DIR 1&2 Open Dir 2&1 Norm CBs  [M06, M05]
Open Dir 2&1 Ess CBs  [G02, G01]
After > 10 sec
Close Dir 2&1 Ess CBs  [G02, G01]
After > 5 min
Close Dir 2&1 Norm CBs  [M06, M05]
It is possible that when booting in ESS mode, no internal
faults will show (TSM 23-73-00-810-879-A)

24 AC GEN Maint STS shows during LGCIU 1&2 Open CBs 52GA, 1GA and 2GA. [Q34,C09,Q35]

ATA 32 maint action. FWC 1&2 After 30 sec open CBs 3WW and 2WW.           [F01,Q07]
After 30 sec close CBs 52GA, 1GA and 2GA    [Q34,C09,Q35]
After 30 sec close CBs 3WW and 2WW           [F01,Q07]

26 Smoke Warnings without Smoke AEVC Open and close after 10 sec CB 5HQ

[D05]
Reset FWC1 and FWC2
[F01,Q07]
26 CARGO SMOKE /LAVATORY DIR 1&2 Open CBs 14WH, 15WH, 17WH and 18W.
SMOKE Warning or Detection (SDF) Close them after 10 sec.
Inop.

Fire‐Exting Bottle LOW PR
[C06,C05,T18,T17]

27 FLAP ASYMMETRY, UCM, WTB Reset Wingtip Brake of the affected flap sys through MCDU.

RUNAWAY, COMMAND
SENSOR UNIT FAULT Note 1: Keeping flap lever out of detent, can cause FLAP
FAULT to show on ECAM. Place lever in actual flap position.
Note 2: Ref. SLT SYSTEM DATA ‐‐> PPU DATA on MCDU to
compare APPUs & FPPU real‐time data (to see faulty sensor).
Note 3: Sys 1&2 APPU connectors can be swapped for T/S.

2
27 Failure of an Aileron Actuator ELAC 1 With Hyd sys depressurized, release ELAC 1 P/B SW.
Servo‐valve Wait 5s and push P/B SW.
Otherwise, open & close after >5 sec ELAC 1 CBs.   [B11,A01]
27 FLP FPPU or SFCC Interface (e.g. SFCC 1&2 Open for 3s CBs 6CV (FLIGHT CONTROLS/FLP/CTL AND
NO LGCIU DATA on ECAM) Fault MONG/SYS1) and 8CV (FLIGHT CONTROLS/FLP/CTL AND
FLAP HALF SPEED MONG/SYS2).
Close CBs and wait 60s.                        [B07,Q21]
27 SLAT HALF SPEED Detected. SFCC 1&2 Open for 3s CBs 5CV (FLIGHT CONTROLS/SLT/CTL AND
FAULT on UPPER ECAM and the MONG/SYS1) and 7CV (FLIGHT CONTROLS/SLT/CTL/SYS2)
SD FLT/CTL page (and on SLT ON
GROUND FAULTS – GROUND LOG [B06,R21]
page).
27 SLAT Channels No Cross‐talk SFCC 1&2 Open for 3s CBs 5CV (FLIGHT CONTROLS/SLT/CTL AND
between SFCC1 and SFFC2 (and MONG/SYS1) and 7CV (FLIGHT CONTROLS/SLT/CTL/SYS2)
SLT2 NO SFCC1 DATA on SYSTEM [B06,R21]
STATUS SLAT page).
27 Failure of the THS Actuator ELAC2 With Hyd sys depressurized, release ELAC2 P/B SW.
Servo Motor 1 Wait 30s and push P/B SW.
WAIT 60s before BITE test.
27 Failure of the THS Actuator ELAC1 With Hyd sys depressurized, release ELAC1 P/B SW.
Servo Motor 2 Wait 30s and push P/B SW.
WAIT 60s before BITE test.

27 Failure of the THS Actuator SEC 2 With Hyd sys depressurized, release SEC2 P/B SW.

Servo Motor 3 for the SEC 2 Wait 30s and push P/B SW.
WAIT 60s before BITE test.

27 SLT APPU LH/RH or SFCC SFCC Open for 3s and close CBs 5CV & 7CV.

Interface Fault (on upper ECAM
and SD + MCDU SLT ON GROUND [B06,R21]
FAULTS)
27 Loss of the Side Stick Priority ELAC 1/2 Release ELAC1, SEC1,ELAC2,SEC2,SEC3 P/B SWs
Signal SEC 1/2/3 Push all P/B SWs after 60 sec.

28 Center Tank AUTOFEED FQIC Fault will disappear after correcting fuel distribution.

warning/fault (CTR tank pump circuit resets (de‐latches) when any refuel
(Outer < 5 tons + CTR >250Kg) valve relay energizes, i.e. during normal refueling).
28 CTR tank pump(s) don’t de‐ FQIC Push CTR tank Mode Pb/sw to MAN then to AUTO.
latch (resume operation) on
If still the same, try de-latching by Center-Tank Fuel Control
refueling after FLT
test AMM 28-21-00-720-001-A.

28 Fuel transfer from one wing To FQIC Open for 30s and close the C/Bs 1QT, 2QT and 8QT.
the other. After 60s check ECAM FUEL page, FQIS STATUS and FLSS
Inter‐cell valves fail to de‐latch STATUS on MCDU.
or don’t open. Note: Intercell VLVs don’t operate on batt power.
Erratic FUEL QTY or TEMP ind [A13,M27,L26]
(warning , xx) or sys op. faults
28 L(R) WING TK LO LVL false SDAC 1(2) Perform FLSS BITE.
warning  or no warning Open the C/Bs 3WV (SDAC1) and 2WV (SDAC2) in turn:
[F04,Q06]
If the fault shows with an active SDAC, swap SDACs to
confirm the faulty one.
Cross-check SDACs on AIDS PARA LABEL CALL-UP Menu.
3
29 HYD PTU FAULT warning Open & close CB HYDRAULIC/SOL VALVES/G/Y/PTU (1801GL)

[N34]

29 Y Hyd pump doesn’t stop 10 sec Open & close CB DOORS/CARGO (1MJ)
after cargo door operation
[T12]

30 L/R FIXED WINDOW SENSOR WHC‐1/2 Open and close WHC‐1/2 CB

fault [X13(W13)]
Note: If OAT>40 deg C or directly heated by sun, operate
packs for >5min before resetting CB.

31 DAR Inoperative DAR Open for 60s and close CBs 5TV (AIDS & RCDR/FDIMU) and
9TU (RCDR/ACCLRM).
[K15,K18]
Do the DAR test (AMM 31-36-00-740-003)
31 No AIDS Indication on MCDU1 FDIMU Open for 60s and close CB 5TV (AIDS & RCDR/FDIMU)
or MCDU2
[K15]

31 Spurious Warnings / Indications FWC1&2 Open FOR 60s and close FWC 1&2 CBs.
related to the SDAC [F01,Q07]

SDAC 1(2) If fault still exists, open C/Bs 3WV (SDAC1) and 2WV (SDAC2)
one by one (for T/S). When the fault shows with any active
SDAC, swap SDACs to confirm the faulty one.
[F04,Q06]
31 No Access to System BITEs from CFDIU Open and close CFDIU SPLY & BACKUP CBs
the MCDU [J18,J17]
NOTE: The same reset is done to recover GMT time on ECAM
permanent display.
31 VERSION INCONSISTENCY DU Switch the DU pot OFF then to mid BRT pos.
shows on any DU (and INVALID
LRU IDENT following EIS System Note1: Chk DU software is the same as EIS; otherwise do cross‐
Test) loading from DMC1 to L/S & ECAM DUs or DMC2 to R/S DUs.
Note2: If all DUs affected, reset DMC1; if only F/O PFD & ND,
reset DMC2. Otherwise, upload faulty software to faulty DMC.
[E11,Q09]

32 L/G and doors don't operate LGCIU1&2 Open for 15s and close SYS 1&2 CBs.
after selection. [C09,Q35,Q34,R32,R33]
Note1: Green hyd sys depressurized.
Note2: For only comp reset, use the following CBs:
LGCIU 1 [C09,Q35] - LGCIU 2 [Q34]
32 LGCIU 1 & 2 simultaneous faults LGCIU 1&2 Keeping Sys 2 CBs open [Q35 ,R33], open for >15s & close
on upper ECAM & STS pages Sys 1 CBS [C09,Q34,R32] to reset Sys 1 after 60s powerup.
Keeping Sys 1 CBs open [C09,Q34,R32], open for >15s &
close Sys 2 CBS [Q35 ,R33] to reset Sys 2.
32 Failure of the left BRK ALTN BSCU Depress Green Sys, switch PTU off, A/SKID & N/W STRG sw
MANIFOLD OFF then ON, pressurize Yellow Sys, set Park BRK on.
After >5s do BSCU GROUND SCANNING.

32 No Data from CFDIU Interactive LGCIU 1(2) Open for 15s and close LGCIU 1(2) CBs one system at a time.
Mode Selection & Monitor Note: If reset successful (no ECAM warning), do Ground
Sequence Fault Scanning to make sure GROUND LOG is cleared.
[C09,Q34(Q35)] TSM 32-31-00-810-801-A

4
33 One LED anti-collision light Toggle cockpit switch OFF > 3sec then ON.
doesn’t operate.

34 ISIS reset ISIS Open and close after >5s CB 5FN (NAV/STBY/INST).
(AMM 34-20-00-710-001) INIT page comes on after a few seconds.
[F12]

34 To clear ECAM MSG relating to ADIRU Turn ADIRU sw to OFF for a few seconds then to NAV to
non-existing ADIRU fault initiate FULL alignment (fast re-alignment is not sufficient).

34 Loss of the GPS Input to ADIRU MMR 1&2 Reset MMRs

[G12,L7]

34 GPS PRIMARY LOST displayed MMR(s) Reset MMRs

on ND [G12,L7]
No GPS 1(2) data on GPS
MONITOR page (dashes)
34 ECAM warning NAV RA RA Will reset automatically in Phase 2 (engine start + 30s).
DEGRADED + erroneous RA Note: Don’t swap MMRs prior to next FLT.
height ind.

34 Loss of MMR1 Data Input to MMR 1(2) Open >10 sec & close MMR 1(2) CB [G12(L07)]
ATC/Mode S Transponder 1(2) ATC 1(2) Open >10 sec & close ATC 1(2) CB [G11(K07)]

35 Loss of CREW OXY sys CREW OXY OXYGEN/CREW/OXY/SPLY CB

Indication (REGUL LO PR) REG/XMTR
[HA01]

35 OXY cylinder valve closing not Perform BLEEDING at CAPT & F/O oxygen-mask stowage
possible boxes.
Push and hold the PRESS TO TEST AND RESET control
button and PRESS TO TEST/EMERGENCY knob for > 3sec.
Release them in reverse order.

36 AIR BLEED ECAM STS MSG BMCs Open for 30 sec and close BMC 1&2 (MONG&CTL) CBs +
FWCs FWC 1&2 CBs
Note1: All bleed sources off.
Note2: If fault is due to elec PWR XFR, it will go off on next
ENG start. After shutdown, AIR BLEED reappears then goes
off after 5 minutes.
[D12,D11,Z23,Z22, F01,Q07]

38 Toilet Flushes Continuously FCU Open and close after 30s the related toilet CB on 2001VU:
39MG (VACU TOIL SYS-LAV PWR-D) [A03]
34MG (VACU TOIL SYS-LAV PWR-E) [A04]
32MG (VACU TOIL SYS-LAV PWR-A) [A01]

5
38 VACUUM GEN INOP CIDS If VACU GENERATOR: DISABLED & VACU GEN OVHT:
YES on MCDU CIDS TOILET SYS STATUS page, perform
reset by CIDS Interface and Power-Up Test (if fault due to
temp OVHT cond).

46 Loss of VDR3 Data Detected by VDR3(VHF3) 1) Open and close CB 2RC3 (COM/VHF/3). [L05]
the ATSU. 2) After 60s, if ATIMS BITE still shows
ATSU VDR3(1RC3)/ATSU1(1TX1),
- open for 5s in this order: 3TX1 and 5TX1 [L16,L15]
- close CBs in this order: 5TX1 and 3TX1 [L15,L16]
46 Loss of HFDR Data Detected by HFDR Open and close CB 1RE1 to reset the HFDR1.
the ATSU. After 60s, if ATIMS BITE still shows
HFDR1(3RE1)/ATSU1(1TX1),
ATSU
- open for 5s in this order: 3TX1 and 5TX1 [L16,L15]
- close CBs in this order: 5TX1 and 3TX1 [L15,L16]
46 ATSU Software Failure ATSU - open for 5s in this order: 3TX1 and 5TX1 [L16,L15]
(ATSU menu doesn’t show) - close CBs in this order: 5TX1 and 3TX1 [L15,L16]
Wait 1 min for fault to clear.

47 FUEL INERTING SYS FAULT IGGS CTL On the cockpit rear panel 121VU open, wait for 5 seconds and

UNIT close the circuit breaker 7YA (IGGS/CTLR) and 1HW (CSAS /
CTLR).
[N28 & U17]

49 APU DMM shows WRITE ECB Set APU MASTER sw OFF and wait >35s. Set APU MASTER sw

FAILURE on MCDU menu ON position. Check APU GND SCANNING menu.
If the same, repeat reset after APU start and shutdown.

49 ECB reset (ECB de‐powering) ECB Open and close after >5s CBs 2KD (APU/APU/CTL) and 1KD
(APU/ECB/SPLY). After power‐up, put APU master sw on and
do SYSTEM SELF-TEST (TEST OK comes on). [L42 & L41]

52 Fault of the Cockpit Door Lock 24MQ (Door Manually unlock the cockpit door and open it ∙ set the toggle sw

System ‐ General Locking Cont to the UNLOCK position ∙ wait for >10s and release sw to NORM
Unit) position.
If the same, open for >5s and close CB 1MQ (DOORS CKPT
LOCK). Chk ind on OVHD PNL. TSM 52-51-00-810-801-A

73 Loss of all Engine 1 ECU 1(2) Perform ECU reset (master switch OFF for 30 sec the ON).

Identification Connector Data Perform Engine Non Motoring Test and read TSD to check if
fault still exists.

6
Customer : AAW Manual : AMM
Type : A318/A319/A320/A321 Selected applicability : ALL
Rev. Date : Nov 01, 2017

** ON A/C ALL
A. Circuit Breakers Data Tables by Circuit

PANEL DESIGNATION FIN CLIPPED LOCATION

49VU FLIGHT CONTROLS/SLT FLP/POS/IND 1 1CN B12
122VU ANTI ICE/PROBES/1/TAT 1DA1 Z12
122VU ANTI ICE/PROBES/2/TAT 1DA2 Y15
49VU ANTI ICE/RAIN/RPLNT/CAPT 1DB1 D01
122VU ANTI ICE/RAIN/RPLNT/F/O 1DB2 W11
123VU ANTI ICE/L/WHSLD 1DG1 AF10
123VU ANTI ICE/R/WHSLD 1DG2 AF03
49VU ANTI ICE/WING/MONG 1DL C01
122VU ANTI ICE/ENG/1 1DN1 X10
122VU ANTI ICE/ENG/2 1DN2 W10
122VU FOOT WARMER 1DR X15

** ON A/C 001-002, 006-100

2000VU WASTE WIP-DRAINMAST-FWD 1DU B06

** ON A/C 101-200
2000VU WASTE WIP-DRAINMAST-FWD 1DU B03

** ON A/C ALL
2000VU POT/WASTE WIP-HEATER-LINE 1DW A02
121VU ENG1/REV/LOCK 1EG1 N44
121VU ENG2/REV/LOCK 1EG2 N45
121VU ENGINE/ENG1/OIL/QTY 1EN1 N39
121VU ENGINE/ENG2/OIL/QTY 1EN2 N41
121VU ENGINE/ENG1 AND 2/EVMU 1EV R44
49VU L/G/LGCIU/SYS1/NORM 1GA C09
121VU HYDRAULIC/BRAKING AND STEER- 1GG M34
ING/SYS1/CTL
121VU HYDRAULIC/BRK FAN/WHEELS/1 AND 2 1GS L32
121VU DUMMY CB 1GV M31
121VU HYDRAULIC/BRK/TEMP/DET/UNIT 1GW M37

** ON A/C 007-100
122VU CKPT/FOOT/HEATERS 1HE V23

** ON A/C ALL
122VU AIR COND/RECIRC FAN/L/SPLY 1HG X18
49VU AIR COND/CAB/PRESS/CTL1 1HL D09
123VU AVNCS VENT/BLOWER/FAN 1HQ AD10
49VU OXYGEN/CREW/OXY/SPLY 1HT HA01
122VU AIR BLEED/X FEED VALVE/NORM 1HV Z20

** ON A/C 007-100
122VU CSAS / CTLR 1HW U17

** ON A/C ALL
49VU AIR COND/RAM/AIR/INLET 1HZ D10

Print Date: June 21, 2018 Page 1 of 18

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Customer : AAW Manual : AMM
Type : A318/A319/A320/A321 Selected applicability : ALL
Rev. Date : Nov 01, 2017

PANEL DESIGNATION FIN CLIPPED LOCATION

49VU ENGINE/1 AND 2/IGN/SYS A 1JH A03
49VU ENGINE/1/HP FUEL SOV 1KC1 A01
49VU ENGINE/2/HP FUEL SOV 1KC2 A02
121VU APU/ECB/SPLY 1KD L41
121VU DUMMY CB 1KT K41

** ON A/C 001-002, 101-200

122VU LIGHTING/EXT LT/NAV1/AND LOGO/LT 1LA T03

** ON A/C 006-100
122VU LIGHT/EXT LT NAV1/AND LOGO/LT 1LA T03

** ON A/C ALL
122VU LIGHTING/LANDING LT/L/SPLY 1LB T04
122VU LIGHTING/EXT LT/RWY TURN OFF/L 1LC1 W06
122VU LIGHTING/EXT LT/RWY TURN OFF/R 1LC2 W05
49VU LIGHTING/EMER LT/CKPT/DOME 1LE H08
49VU LIGHTING/STBY/COMP/LIGHT 1LF H04
2001VU LIGHT SEC-19 1LJ E07
2000VU AIR CONDTN COMPT OUTLET 1LK G08
122VU LIGHTING/WHL WELL/LTG/OUT 1LL X07

** ON A/C 101-200
2000VU LIGHT-LAV 1LQ J01

** ON A/C 001-002, 006-100

2000VU LAV LIGHT 1LQ J01

** ON A/C ALL
122VU LIGHTING/EXT LT/TAXI AND TAKE OFF/ 1LR W08
TAXI
122VU LIGHTING/AVNCS COMPT/DOME 1LS Z07
2000VU LIGHT-CARGO COMPT-FWD 1LU J06
122VU LIGHTING/EXT LT/BEACON/UPPER 1LV U06
2000VU PASSENGER/READING/LIGHT 1LW G01
122VU LIGHTING/EXT LT/WING/AND ENG 1LX W03
SCAN/R
122VU LIGHTING/LOGO/R 1LY V02
2000VU LIGHT-ATTND-WORK 1LZ J03

** ON A/C 001-002, 006-100

2000VU WATER SYSTEM-QANT-IND 1MA B01

** ON A/C 101-200
2001VU WATER SYS-QUANT-IND 1MA B06

** ON A/C ALL
2000VU LAV FWD & MID-HOT WATER-A 1MB F02

** ON A/C 001-002, 006-100

2000VU VACUUM CLEANER SOCKET-CABIN 1ME A03
Z222

Print Date: June 21, 2018 Page 2 of 18

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Customer : AAW Manual : AMM
Type : A318/A319/A320/A321 Selected applicability : ALL
Rev. Date : Nov 01, 2017

PANEL DESIGNATION FIN CLIPPED LOCATION

** ON A/C 101-200
2000VU VACUUM CLEANER SOCKET-CABIN 1ME F07
Z222

** ON A/C ALL
122VU DOORS/CARGO 1MJ T12
2001VU WATER SYS-DRAIN 1MP B05
122VU DOORS CKPT LOCK 1MQ T13
122VU COCKPIT SEATS/SEAT CTL/CAPT 1MS1 U11
122VU COCKPIT SEATS/SEAT CTL/F/O 1MS2 U14
121VU PILOTS OUTLETS/STAT INV 1NA K25
106VU EMER/SHED/CNTOR/SPLY 1PH C07
125VU 101PP/SPLY 1PN1 CD01
124VU 202PP/SPLY 1PN2 BG01
122VU ELEC/REFLNG/ON/BAT 1PR U28
124VU SVCE/601PP/602PP/SPLY 1PX BB01
121VU FUEL/L WING TK/PUMP1 SPLY 1QA N23
121VU APU/FUEL/BLOW OFF/CTL 1QC K39
121VU FUEL/X FEED/VALVE/MOT2 1QE M24
121VU APU/FUEL/LP VALVE/CTL 1QF M40
49VU FUEL/LP VALVE/MOT1/ENG1 1QG A08
121VU FUEL/HI/LVL/SPLY 1QJ L25
49VU FUEL/XFR VALVE1/WING/L 1QP A10
49VU FUEL/FQI/CHAN/1 1QT A13
121VU FUEL/RFL/DFL/XFR/DEFUEL/VALVE 1QU L23
49VU COM/HF1 1RE1 HA14
49VU NAV/ADF/1 1RP1 H14
121VU DUMMY CB 1RP2 K02
121VU COM NAV/RAD ALTM/1 1SA1 K11
121VU COM NAV/RAD ALTM/2 1SA2 K12
49VU NAV/DME/1 1SD1 G14
121VU COM NAV/DME/2 1SD2 K06
121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/ 1WE1 Q43
SQUIB/A
121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/ 1WE2 Q41
SQUIB/A
121VU APU/FIRE/EXTIG/SQUIB/A 1WF L38
121VU APU/FIRE AND OVHT/DET/LOOP A 1WG L43
2000VU LAV FWD-OCCUPIED 1WJ F01
49VU LIGHTING/EMER LT/CABIN 1WL H05
49VU OXYGEN/PASSENGER/CTL AND WARN 1WR HA02

** ON A/C 007-100
49VU AIR COND/CARGO FIRE/EXTIG/BTL1 1WX C03

** ON A/C 001-002, 006-006, 101-200

122VU AIR COND/CARGO/FIRE/EXTIG 1WX T19

Print Date: June 21, 2018 Page 3 of 18

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Customer : AAW Manual : AMM
Type : A318/A319/A320/A321 Selected applicability : ALL
Rev. Date : Nov 01, 2017

PANEL DESIGNATION FIN CLIPPED LOCATION

** ON A/C ALL
122VU ELEC/GALY & CAB/CTL 1XA S26
123VU AC ESS/BUS ON/BUS 1 1XC AC12
106VU AC/SHED/ESS BUS/CNTOR/CTL 1XH C04
123VU BUS 1/101XP/SPLY 1XN1 AD11
123VU BUS 2/202XP/SPLY 1XN2 AD02
122VU ELEC/IDG1/DISC 1XT T24
123VU TR2/SVCE/BUS 2/SPLY 1XX AB08
121VU FLIGHT CONTROLS/SLT FLP/2POS/IND 2CN P16
49VU ANTI ICE/PROBES/PHC/1 2DA1 D03
122VU ANTI ICE/PROBES/PHC/2 2DA2 Y12
122VU ANTI ICE/PROBES/PHC/3 2DA3 Y16
49VU ANTI ICE/WING/CTL 2DL C02
2000VU POT/WASTE WIP-HEATER-CTL 2DW A01
121VU ENGINE/ENG1/OIL/PRESS 2EN1 N40
121VU ENGINE/ENG2/OIL/PRESS 2EN2 N42
121VU HYDRAULIC/LGCIU/SYS2 2GA Q35
121VU HYDRAULIC/BRAKING AND STEER- 2GG M33
ING/SYS1/IND AND/SPLY
121VU HYDRAULIC/BRK FAN/WHEELS/3 AND 4 2GS L35
49VU AIR BLEED/ENG 1/MONG 2HA1 D11
122VU AIR BLEED/ENG 2/MONG 2HA2 Z22
122VU AIR COND/RECIRC FAN/L/CTL 2HG X20
122VU AIR COND/CAB PRESS/CTL/2 2HL Y22
123VU AVNCS VENT/EXTC/FAN 2HQ AE02
49VU AIR BLEED/X FEED/VALVE/BAT 2HV D13
121VU ENGINE/IGN/ENG1/SYS A BAT 2JH1 P39
121VU ENGINE/IGN/ENG2/SYS A BAT 2JH2 P40
121VU APU/APU/CTL 2KD L42
49VU ENGINE/1/FADEC A/AND EIU 1 2KS1 A04
49VU ENGINE/2/FADEC A/AND EIU 2 2KS2 A05
122VU LIGHTING/EXT LT/NAV2/AND LOGO/LT 2LA T02
122VU LIGHTING/LANDING LT/R/SPLY 2LB T06
122VU LIGHTING/FLOOD/CTR INST/PNL 2LE Z04
2001VU LIGHT APU 2LJ E08
122VU LIGHTING/WHL WELL/LTG/DOME 2LL X08
122VU LIGHTING/EXT LT/TAXI AND TAKE OFF/ 2LR W09
CTL
2000VU LIGHT-CARGO COMPT-AFT 2LU J07
2000VU PASSENGER/READING/LIGHT 2LW G02
122VU LIGHTING/LOGO/L 2LY V03
2001VU LAVATORY AFT-HOT WATER-D 2MB B02
121VU PILOTS OUTLETS/115V 60HZ 2NA K23
122VU ELEC/REFLNG/NORM 2PR S27
123VU TR1/SPLY 2PU1 AB10
123VU TR2/214XP/SPLY 2PU2 AB04
121VU FUEL/R WING TK/PUMP1 SPLY 2QA Q23
49VU APU/FUEL/BLOW OFF/PUMP 2QC B14

Print Date: June 21, 2018 Page 4 of 18

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Customer : AAW Manual : AMM
Type : A318/A319/A320/A321 Selected applicability : ALL
Rev. Date : Nov 01, 2017

PANEL DESIGNATION FIN CLIPPED LOCATION

49VU FUEL/X FEED/VALVE/MOT1 2QE A12
121VU APU/FUEL/LP VALVE/SPLY 2QF M39
49VU FUEL/LP VALVE/MOT1/ENG2 2QG A09
49VU FUEL/XFR VALVE1/WING/R 2QP A11
121VU FUEL/FQI/CHAN/2 2QT M27
121VU FUEL/RFL/DFL/SPLY 2QU L24
49VU COM/VHF/1 2RC1 G09

** ON A/C 001-002, 101-200

121VU COM NAV/VHF/2 2RC2 L04

** ON A/C 006-100
121VU COM/VHF/2 2RC2 L04
121VU COM/VHF/3 2RC3 L05

** ON A/C 001-002, 101-200

121VU COM NAV/VHF/3 2RC3 L05

** ON A/C ALL
49VU COM/RMP/1 2RG1 G10
121VU COM NAV/RMP/2 2RG2 L02
121VU COM NAV/RMP/3 2RG3 L03
49VU COM/CVR/SPLY 2RK E14
49VU NAV/VOR/1 2RS1 G13
121VU COM NAV/VOR/2 2RS2 K08
121VU MAT & PRINTER/STAT INV 2TA C K27

** ON A/C 001-002, 006-006, 101-200

122VU AINS/SIU 2TL C Y07

** ON A/C ALL
121VU CFDS/CFDIU/SPLY 2TW J18
121VU EIS/HORN/SPLY 2WC P09
121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/ 2WE1 Q44
SQUIB/B
121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/ 2WE2 Q42
SQUIB/B
121VU APU/FIRE/EXTIG/SQUIB/B 2WF L39
121VU APU/FIRE AND OVHT/DET/LOOP B 2WG L44
49VU LIGHTING/EMER LT/CABIN 2WL H06
49VU OXYGEN/PASSENGER/CTL AND WARN 2WR HA03
121VU EIS/SDAC/2/SPLY 2WV Q06
121VU EIS/FWC2/SPLY 2WW Q07
121VU EIS/GPWS/28VDC 2WZ P06
123VU AC ESS/BUS ON/BUS 2 2XC AC01
123VU GND/PWR/PROT 2XG AB07
106VU AC ESS BUS/MONG/SPLY 2XH C05
122VU ELEC/IDG2/DISC 2XT T25
122VU ELEC/GCU/1 2XU1 T26
122VU ELEC/GCU/2 2XU2 T27
123VU SVCE/BUS 2/212XP SPLY 2XX AB05

Print Date: June 21, 2018 Page 5 of 18

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Customer : AAW Manual : AMM
Type : A318/A319/A320/A321 Selected applicability : ALL
Rev. Date : Nov 01, 2017

PANEL DESIGNATION FIN CLIPPED LOCATION

49VU ANTI ICE/PROBES/PITOT/1 3DA1 D02
122VU ANTI ICE/PROBES/2/PITOT 3DA2 Y14
122VU ANTI ICE/PROBES/3/PITOT 3DA3 Z16
121VU HYDRAULIC/BRAKING AND STEER- 3GG M35
ING/SYS2/CTL
121VU HYDRAULIC/BRK/FAN/CTL 3GS M32
49VU AIR BLEED/ENG 1/CTL 3HA1 D12
122VU AIR BLEED/ENG 2/CTL 3HA2 Z23
122VU AIR COND/RECIRC FAN/R/SPLY 3HG W18
122VU AIR COND/CAB PRESS/CTL/MAN 3HL Y23
122VU AIR COND/AVNCS/VENT/MONG 3HQ Y17
121VU ENGINE/IGN/ENG1/SYS B 3JH1 P41
121VU ENGINE/IGN/ENG2/SYS B 3JH2 P42
122VU LIGHTING/LANDING LT/L/CTL 3LB T05
122VU LIGHTING/CKPT/DOME 3LE Y06
122VU LIGHTING/INSTL LT/OVHD/PNL 3LF Y03
122VU LIGHTING/EXT LT/TAXI AND TAKE OFF/ 3LR W07
TO
2000VU LIGHT-LDG-AREA 3LU J08
2000VU PASSENGER/READING/LIGHT 3LW G03
122VU ELEC/CNTOR/ESS/DC BUS/TIE 3PC W26
125VU 103PP/SPLY 3PN1 CE01
124VU 204PP/SPLY 3PN2 BF01
122VU ELEC/TR1/MONG 3PU1 X25
122VU ELEC/TR2/MONG 3PU2 X26
121VU FUEL/PUMPS/1/L CTL AND R IND 3QA R23
121VU APU/FUEL/PUMP/CTL 3QC M38
121VU FUEL/LP VALVE/MOT2/ENG1 3QG M25
121VU FUEL/XFR VALVE2/WING/L 3QP M22
121VU MAT & PRINTER/115V 60HZ 3TA C K29
121VU DATA/LOADER/SPLY 3TD J16
121VU ATSU 1 3TX1 L16
121VU APU/FIRE/LP VALVE/STBY 3WF M41
122VU LIGHTING/CABIN/EMER/LT 3WL V07
49VU OXYGEN/PASSENGER/CTL AND WARN 3WR HA04
49VU SDAC/1/SPLY 3WV F04
49VU FWS/FWC1/SPLY 3WW F01
121VU EIS/GPWS/115VAC 3WZ C P07
123VU BUS 1/103XP/SPLY 3XN1 AB11
123VU BUS 2/204XP/SPLY 3XN2 AB02
122VU ELEC/AC PWR/SVCE/CTL 3XX V29
49VU ANTI ICE/PROBES/AOA/1 4DA1 D04
122VU ANTI ICE/PROBES/2/AOA 4DA2 Y13
122VU ANTI ICE/PROBES/3/AOA 4DA3 Z15
122VU ANTI ICE/WIPER/CAPT 4DB1 X12
122VU ANTI ICE/F/O/WIPER 4DB2 W12
122VU ANTI ICE/WINDOWS/L 4DG1 X14
122VU ANTI ICE/WINDOWS/R 4DG2 W14
121VU ENGINE/ENG1/OIL/CHIP/DET 4EN1 N38

Print Date: June 21, 2018 Page 6 of 18

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Customer : AAW Manual : AMM
Type : A318/A319/A320/A321 Selected applicability : ALL
Rev. Date : Nov 01, 2017

PANEL DESIGNATION FIN CLIPPED LOCATION

121VU ENGINE/ENG2/OIL/CHIP/DET 4EN2 N43
49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06
121VU ADIRS/ADIRU/2/115VAC 4FP2 N06
121VU ADIRS/ADIRU/3/115VAC 4FP3 N05
121VU CLOCK/STBY/SPLY 4FS N02
121VU HYDRAULIC/BRAKING AND STEER- 4GG M36
ING/SYS2/SPLY
122VU RPCU 4HL X23
121VU ENGINE/ENG1/FADEC B/AND EIU 1 4KS1 R41
121VU ENGINE/ENG2/FADEC B/AND EIU 2 4KS2 Q40
122VU LIGHTING/LANDING LT/R/CTL 4LB T07
122VU LIGHTING/FLOOD/F/O/SIDE 4LE Z06
122VU LIGHTING/INSTL LT/MAIN INST/PNL 4LF Y04
AND/PED
2000VU PASSENGER READING LIGHT 4LW G04
106VU ESS TR/SPLY 4PE C01
122VU ELEC/RFL/SPLY/LOGIC 4PR U29
125VU TR1/CNTOR/SPLY 4PU1 CF01
124VU TR2/CNTOR/SPLY 4PU2 BC01
121VU FUEL/PUMPS/1/R CTL AND L IND 4QA R28
121VU FUEL/LP VALVE/MOT2/ENG2 4QG M26
121VU FUEL/XFR VALVE2/WING/R 4QP M23
49VU COM/CVR/CTL 4RK E13
49VU COM/AUDIO/ACP/CAPT 4RN G06
121VU MAT & PRINTER/MAT CTL 4TA C K26

** ON A/C 001-002, 006-006, 101-200

122VU AINS/ANSU 4TL C Y08

** ON A/C ALL
121VU APU/FIRE/LP VALVE/NORM 4WF M42
49VU OXYGEN/PASSENGER/ACTUATION 4WR HA05
121VU EIS/F/O/LOUD/SPKR 4WW P08
106VU AC ESS/BUS NORM/CNTOR/CTL 4XC B03
122VU ELEC/EXT PWR/LT CLT/AVAIL 4XG X31
106VU 26VAC/ESS BUS/SPLY 4XH B06
123VU SVCE/BUS 2/214XP SPLY 4XX AA05
49VU AUTO FLT/FAC1/28VDC 5CC1 B04
121VU AUTO FLT/FAC2/28VDC 5CC2 M19
49VU FLIGHT CONTROLS/SLT/CTL AND 5CV B06
MONG/SYS1
122VU ANTI ICE/PROBES/1/STATIC 5DA1 Z13
122VU ANTI ICE/PROBES/2/STATIC 5DA2 Y11
122VU ANTI ICE/PROBES/3/STATIC 5DA3 Z14
122VU ANTI ICE/WHC/1 5DG1 X13
122VU ANTI ICE/WHC/2 5DG2 W13
49VU NAV/STBY/INST 5FN F12
49VU NAV PROBES/ADIRU 1/AND AOA 1/ 5FP1 F07
26VAC
121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N08

Print Date: June 21, 2018 Page 7 of 18

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Customer : AAW Manual : AMM
Type : A318/A319/A320/A321 Selected applicability : ALL
Rev. Date : Nov 01, 2017

PANEL DESIGNATION FIN CLIPPED LOCATION

121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N07
49VU AIR COND/AVNCS VENT/CTL 5HQ D05
122VU AIR COND/LAV/GALLEY VENT CTL/EX- 5HU U21
TRACT FAN/CTL
122VU LIGHTING/FLOOD/CAPT/SIDE 5LE Z05
122VU LIGHTING/INSTL LT/GLARE/SHLD 5LF Y05
122VU LIGHTING/EXT LT/BEACON/LOWER 5LV U03
2000VU PASSENGER/READING/LIGHT 5LW G05
122VU LIGHTING/EXT LT/WING/AND ENG 5LX W02
SCAN/L

** ON A/C 001-002, 006-100

2001VU VACUUM CLEANER SOCKET-CABIN 5ME F01
Z261

** ON A/C 101-200
2001VU VACUUM CLEANER SOCKET-CABIN 5ME F06
Z261

** ON A/C ALL
105VU ELEC/HOT BUS/701PP SPLY 5PB1 D01
105VU ELEC/HOT BUS/702PP SPLY 5PB2 D02
106VU ESS TR/CNTOR/CTL 5PE C02
122VU ELEC/DC/SVCE/BUS 5PN X24
122VU ELEC/DC SVCE/BUS/ON TR2 5PX U30
49VU COM/AUDIO/ACP/F/O 5RN G07
49VU COM NAV/ATC/1 5SH1 G11
121VU COM NAV/ATC/2 5SH2 K07
121VU COM NAV/RADAR/1 5SQ1 K13

** ON A/C 001-002, 006-100

121VU COM NAV/RADAR/2 5SQ2 C K14

** ON A/C 101-200
121VU COM NAV/RADAR/2 5SQ2 K14

** ON A/C ALL
121VU DLS&/DLRB/SPLY 5TD J15
121VU AIDS & RCDR/FDIMU 5TV K15
121VU ATSU 1/SWTG 5TX1 L15
49VU OXYGEN/PASSENGER/ACTUATION 5WR HA06
49VU SDAC/1/26VAC SYNC/AC ESS BUS 5WV F02
49VU CAPT/LOUD/SPKR 5WW F10
106VU AC ESS BUS/STBY/CNTOR/CTL 5XC B08
106VU AC ESS BUS/EMER/CNTOR/CTL 5XE B07
123VU BUS 1/131XP-A/SPLY 5XN1 AB12
123VU BUS 2/231XP-A/SPLY 5XN2 AB01
122VU ELEC/GEN1/OFF/BTC1 SPLY 5XU T28
49VU FLIGHT CONTROLS/FLP/CTL AND 6CV B07
MONG/SYS1
105VU ADIRS/ADIRU1/28VDC 6FP1 C02

Print Date: June 21, 2018 Page 8 of 18

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Customer : AAW Manual : AMM
Type : A318/A319/A320/A321 Selected applicability : ALL
Rev. Date : Nov 01, 2017

PANEL DESIGNATION FIN CLIPPED LOCATION

121VU ADIRS/ADIRU/2/28VDC 6FP2 N04
121VU ADIRS/ADIRU/3/28VDC 6FP3 N03
49VU CLOCK/NORM/SPLY 6FS F11
49VU AIR COND/AVNCS VENT/CTL 6HQ D06
122VU AIR COND/LAV/GALLEY VENT CTL/EX- 6HU U19
TRACT FAN/SPLY
2000VU PASSENGER READING LIGHT 6LW G06
2001VU MEDICAL OUTLET-DC 6MF B07
124VU 206PP/208PP/SPLY 6PN BE01
121VU COM NAV/ACP/THIRD/OCCPNT 6RN M02
121VU PTR/SPLY 6TW J21

** ON A/C 001-002, 007-101

POST SB 46-1074 for A/C 006-006, 102-103

EMB SB 46-1074 for A/C 001-002, 101-101

121VU DCDU 1 6TX1 L17

** ON A/C 006-006, 102-200

PRE SB 46-1074 for A/C 006-006, 102-103
121VU DCDU 1 6TX1 C L17

** ON A/C 001-002, 007-101

POST SB 46-1074 for A/C 006-006, 102-103

EMB SB 46-1074 for A/C 001-002, 101-101

121VU DCDU 2 6TX2 L18

** ON A/C 006-006, 102-200

PRE SB 46-1074 for A/C 006-006, 102-103
121VU DCDU 2 6TX2 C L18

** ON A/C ALL
49VU OXYGEN/PASSENGER/ACTUATION 6WR HA07
49VU SDAC/2/26VAC SYNC/AC ESS BUS 6WV F03
122VU ESS NTWK AUTO ALTN 6XC V24
106VU CSM/G /EV/MAN/SPLY 6XE B04
122VU ELEC/EXT PWR/LT CLT/NOT IN/USE 6XG X30
49VU ELEC/AC BUS/8XP/MONG 6XH H11
121VU FLIGHT CONTROLS/SLT/CTL/SYS2 7CV R21
122VU ELEC/GALLEY/CNTOR 7MC S28
2001VU MEDICAL OUTLET-AC 7MF B08
122VU ELEC/TR1/FAULT/DC BUS TIE/CONFIG 7PC1 W29
122VU ELEC/TR2/FAULT/DC BUS TIE/CONFIG 7PC2 W30
124VU DC SVCE/602PP/SPLY 7PN BD01
121VU FUEL/L WING TK/PUMP2 SPLY 7QA N26
121VU COM NAV/ACP/AVNCS/COMPT 7RN C M03
121VU RCDR/DFDR 7TU K16
49VU ENGINE/1/FIRE DET/LOOP A 7WD1 A06
121VU ENGINE/ENG2/FIRE DET/LOOP A 7WD2 Q39

Print Date: June 21, 2018 Page 9 of 18

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Customer : AAW Manual : AMM
Type : A318/A319/A320/A321 Selected applicability : ALL
Rev. Date : Nov 01, 2017

PANEL DESIGNATION FIN CLIPPED LOCATION

49VU OXYGEN/PASSENGER/ACTUATION 7WR HA08
121VU EIS/SDAC/1/BUS2/26VAC SYNC AC 7WV Q03
122VU ELEC/GALY & CAB/GND/FLT/LOGIC 7XA S24
105VU ELEC/CSM/G /EV AUTO/SPLY 7XE C01
122VU ELEC/GPCU 7XG C Y24
123VU BUS 1/110XP/SPLY 7XN1 AF11
123VU BUS 2/210XP/SPLY 7XN2 AF02

** ON A/C 007-100
121VU IGGS/CTLR 7YA N28

** ON A/C ALL
121VU FLIGHT CONTROLS/FLP/CTL AND/ 8CV Q21
MONG/SYS2
49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09
105VU ELEC/BAT BUS/REF/BCL1 8PB1 G01
105VU ELEC/BAT BUS/REF/BCL2 8PB2 J02
121VU FUEL/R WING TK/PUMP2 SPLY 8QA Q26
121VU FUEL/FQI/CHANNEL/1 AND 2 8QT L26
121VU COM NAV/SELCAL 8RN M04
121VU CFDS/CFDIU/BACK/UP 8TW J17
121VU ENGINE/ENG1/FIRE DET/LOOP B 8WD1 Q38
49VU ENGINE/2/FIRE DET/LOOP B 8WD2 A07
121VU EIS/SDAC/2/BUS2/26VAC SYNC AC 8WV Q02

** ON A/C 007-100
49VU AIR COND/CARGO FIRE/EXTIG/BTL2 8WX C04

** ON A/C ALL
122VU ELEC/GALY & CAB/FAULT/LT CTL 8XA S25
122VU ELEC/COML/SHED/SYS2 8XN V28
122VU ELEC/GEN2/OFF/BTC2 SPLY 8XU T31
49VU AUTO FLT/FCU/1 9CA1 B05
121VU AUTO FLT/FCU/2 9CA2 M21
122VU FLIGHT CONTROLS/WTB/SLT/SYS1 9CV S06
121VU ADIRS/ADIRU/3PWR/SWTG 9FP N09
2001VU LAV AFT&MID HOT WATER 9MB B03
105VU ELEC/BAT REF/BCL1 9PB1 F01
105VU ELEC/BAT REF/BCL2 9PB2 F02
122VU ELEC/CNTOR/DC/BUS/TIE1 9PC W25
122VU ELEC/DC SHED BUS/CNTR 9PN U26
121VU FUEL/PUMPS/2/L CTL AND R IND 9QA R24

** ON A/C 101-200
121VU ACT/XFR VALVE/AUTO CTL 9QH P29

** ON A/C ALL
49VU COM/AUDIO/FLT/INTPH 9RN G08
121VU RCDR/ACCLRM 9TU K18
121VU CFDS/TEST PLUG/1 9TW J19
122VU ELEC/EMER GEN AUTO/2 9XE Z26

Print Date: June 21, 2018 Page 10 of 18

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Customer : AAW Manual : AMM
Type : A318/A319/A320/A321 Selected applicability : ALL
Rev. Date : Nov 01, 2017

PANEL DESIGNATION FIN CLIPPED LOCATION

122VU ELEC/COML/SHED/SYS1 9XN V26
49VU AUTO FLT/FMGC/1 10CA1 B02
121VU AUTO FLT/FMGC/2 10CA2 M17
122VU FLIGHT CONTROLS/WTB/FLP/SYS1 10CV S07
121VU ADIRS/ADIRU/2PWR/SHED 10FP N10
122VU LIGHTING/WING/STROBE 10LV V05

** ON A/C 006-100
106VU 802PP SPLY 10PH B09

** ON A/C ALL
121VU FUEL/PUMPS/2/R CTL AND L IND 10QA R29
121VU CFDS/TEST PLUG/2 10TW J20
49VU EIS/DMC1/SPLY 10WT1 E11
121VU EIS/DMC2/SPLY 10WT2 Q08
121VU EIS/DMC3/SPLY 10WT3 Q09
121VU EIS/SDAC/2/BUS1/26VAC SYNC AC 10WV Q05
106VU AC ESS BUS/EMER/STBY/CNTOR/SPLY 10XE C06
123VU BUS 2/212XP/SPLY 10XN AD03
49VU AUTO FLT/MCDU/1 11CA1 B01
121VU AUTO FLT/MCDU/2 11CA2 N20

** ON A/C 001-002
121VU DUMMY CB 11CA3 N21

** ON A/C ALL
121VU FLIGHT CONTROLS/WTB/SLT/SYS2 11CV P19
122VU ANTI ICE/PROBES/P2/T2/ENG1 11DA1 C Z10
122VU ANTI ICE/PROBES/P2/T2/ENG2 11DA2 C Y10
2001VU WASTE WIP-DRAINMAST-AFT 11DU E01
122VU AIR COND/RECIRC FAN/R/CTL 11HG W20
122VU LIGHTING/AVNCS COMPT/OUT/28VDC 11LS Z08
125VU BAT BUS/301PP/SPLY 11PB CC01
124VU SHED BUS 210PP/212PP/SPLY 11PN BA01
123VU L WING TK/PUMP 1/STBY SPLY 11QA AD12
2001VU LAVATORY AFT-OCCUPIED 11WJ B04
49VU LIGHTING/EMER LT/CABIN 11WL. H05
49VU EIS/PFD/CAPT/SPLY 11WT1 E03
121VU EIS/PFD/F/O 11WT2 R03
122VU ELEC/EMER GEN AUTO/1 11XE Z25
122VU ELEC/EXT PWR/CTL 11XG X29
121VU FLIGHT CONTROLS/WTB/FLP/SYS2 12CV P20

** ON A/C 001-002, 006-006, 101-200

49VU NAV/VOR/DME/RMI 12FN F13

** ON A/C ALL
122VU LIGHTING/AVNCS COMPT/OUT/115VAC 12LS Z09
105VU ELEC/HOT BUS/701PP SPLY 12PB1 E01
105VU ELEC/HOT BUS/702PP SPLY 12PB2 E02

Print Date: June 21, 2018 Page 11 of 18

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Customer : AAW Manual : AMM
Type : A318/A319/A320/A321 Selected applicability : ALL
Rev. Date : Nov 01, 2017

PANEL DESIGNATION FIN CLIPPED LOCATION

123VU R WING TK/PUMP 1/STBY SPLY 12QA AE12
49VU LIGHTING/EMER LT/CABIN 12WL. H06
49VU EIS/ND CAPT/SPLY 12WT1 E01
121VU EIS/ND/F/O 12WT2 R04
49VU SDAC/1 AND 2/28VDC/ESS BUS 12WV F05
105VU ELEC/STAT INV/BUS 901XP/SPLY 12XB H02
121VU AUTO FLT/STICK/LOCK 13CA N16
121VU EIS/SLIDES/ARM AND WARN/GND 13WN P10
49VU EIS/ECAM DU/UPPER/SPLY 13WT1 E05
121VU EIS/ECAM DU/LOWER/SPLY 13WT2 R11
49VU ELEC/LT/CTL 13XG H10
121VU AUTO FLT/RUDDER/ARTF/FEEL 14CA N17
49VU AUTO FLT/FAC1/26VAC 14CC1 B03
121VU AUTO FLT/FAC2/26VAC 14CC2 M18

** ON A/C 001-002, 006-006, 101-200

121VU DUMMY CB 14FN K04

** ON A/C ALL
122VU ELEC/CNTOR/DC BUS/TIE 1/FAULT 14PC U24
121VU PDL/PWR/SPLY 14TD K19
121VU AIDS & RCDR/QAR 14TU K17
122VU AIR COND/CIDS/SDF/DIR NORM/2 14WH T18
49VU EIS/DMC3/STBY/SPLY 14WT1 E10
121VU EIS/SDAC1 AND 2/BUS1/28VDC 14WV P04
121VU AUDIO MIXING 14WW K03
105VU ELEC/STAT INV/CNTOR/CTL 14XB G02
122VU ELEC/GEN1/OFF/BTC2 SPLY 14XU T30
121VU AUTO FLT/RUDDER/TRIM/IND 15CC M20
49VU FLIGHT CONTROLS/ELAC1/NORM/SPLY 15CE1 B11
121VU FLIGHT CONTROLS/ELAC2/NORM/SPLY 15CE2 R20

** ON A/C 101-200
2001VU WATER SERVICE PANEL HEATER 15DV D01

** ON A/C 001-002, 006-100

2001VU POT/WASTE WIP SVCE PNL 15DV D01

** ON A/C ALL
106VU AC ESS/BUS/EMER/CNTOR/SPLY 15PC C08

** ON A/C ALL

EMB SB 23-1431 for A/C 001-002, 101-102

122VU DOORS/CKPT/VIDEO/SPLY 15RA T16

** ON A/C ALL
49VU AIR COND/CIDS/SDF/DIR1 ESS 15WH C05
121VU EIS/SLIDES/ARM AND WARN/FLT 15WN P11
49VU EIS/ECAM/CTL/PNL 15WT E12

Print Date: June 21, 2018 Page 12 of 18

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Customer : AAW Manual : AMM
Type : A318/A319/A320/A321 Selected applicability : ALL
Rev. Date : Nov 01, 2017

PANEL DESIGNATION FIN CLIPPED LOCATION

122VU ELEC/GEN2/OFF/BTC1 SPLY 15XU T29
105VU FLT CTL/ELAC1/STBY SPLY 16CE1 A01
105VU FLIGHT CONTROLS/ELAC2/STBY SPLY 16CE2 A02
122VU AIR COND/CIDS/SDF/DIR NORM/1 17WH T17
122VU ELEC/GAPCU 17XG W24
122VU ELEC/AC/BUS1/CTL 17XN1 V25
122VU ELEC/BUS/2XP/CTL 17XN2 V27
122VU ELEC/DC BUS/TIE2//APU/START 18PC W31
49VU AIR COND/CIDS/SDF/DIR2 ESS 18WH C06
121VU FLIGHT CONTROLS/THS ACTR/MOT1 19CE1 Q16
49VU FLIGHT CONTROLS/THS/ACTR/MOT2 19CE2 B09
121VU FLIGHT CONTROLS/THS ACTR/MOT3 19CE3 Q17
2001VU WATER SYS-AIR-COMPRESSOR 19MD F01
49VU FLIGHT CONTROLS/FCDC1/SPLY 20CE1 B10
121VU FLIGHT CONTROLS/FCDC2/SPLY 20CE2 Q20
2000VU IFE-IFE CENTER-DC-VCC 20MH C01
2000VU IFE/SEAT-POWER-PAX SYS 20MK C07
49VU FLIGHT CONTROLS/SEC1/NORM/SPLY 21CE1 B08
121VU FLIGHT CONTROLS/SEC2/SPLY 21CE2 Q18
121VU FLIGHT CONTROLS/SEC3/SPLY 21CE3 Q19

** ON A/C 101-200
2000VU POT/WASTE WIP-HEATER-LINE 21DW A03

** ON A/C ALL
2000VU IFE-IFE CENTER-AC-VCC 21MH C02
2000VU IFE-IFE CENTER-DC-IFEC 21MK C03
49VU EIS/DMC1/SWTG 21WT1 E09
121VU EIS/DMC2/SWTG 21WT2 R08
49VU EIS/DMC3/SWTG 21WT3 E07
105VU FLT CTL/SEC1/STBY SPLY 22CE B01

** ON A/C 101-200
2000VU IFE-CABIN-TU-LH 22MH D01

** ON A/C 001-002, 006-100

2000VU IFE-CABIN-TU L/H 22MH D01

** ON A/C ALL
2000VU IFE-IFE CENTER-AC-IFEC 22MK C04
49VU EIS/PFD CAPT/SWTG 22WT1 E04
121VU EIS/PFD/F/O/SWTG 22WT2 R05
105VU NAV/STBY/INST/BAT 23FN J01
2000VU IFE-CABIN-ADB1 23MK C05
49VU EIS/ND CAPT/SWTG 23WT1 E02
121VU EIS/ND/F/O/SWTG 23WT2 R06
123VU APU GEN/EGIU2/115VAC 23XS AA08

** ON A/C 101-200
2000VU IFE-CABIN-TU-RH 24MH D02

Print Date: June 21, 2018 Page 13 of 18

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Customer : AAW Manual : AMM
Type : A318/A319/A320/A321 Selected applicability : ALL
Rev. Date : Nov 01, 2017

PANEL DESIGNATION FIN CLIPPED LOCATION

** ON A/C 001-002, 006-100

2000VU IFE-CABIN-TU R/H 24MH D02

** ON A/C ALL
2000VU IFE-CABIN-ADB2 24MK C06
49VU EIS/ECAM DU/UPPER/SWTG 24WT1 E06
121VU EIS/ECAM DU/LOWER/SWTG 24WT2 R10

** ON A/C 101-200
121VU ACT PUMP SUPPLY 25QH Q29

** ON A/C ALL
122VU LIGHTING/ANN LT SPLY/XFMR/BUS 1 26LP X04
122VU ELEC/AC SHED BUS/CNTOR 26XN U25
122VU LIGHTING/ANN LT SPLY/XFMR/BUS 2 27LP X05
106VU EMER/GEN/REF 27WV B05
122VU LIGHTING/ANN LT SPLY/XFMR/STAT 28LP X03
INV
123VU SHED BUS/218XP/220XP SPLY 28XN AC02
49VU LIGHTING/XFMR/115V.5V/ESS BUS 29LP H03
121VU FUEL/CTR TK/PUMP1 SPLY 29QA P23
122VU AIR COND/AFT CARGO VENT/FAN 30HN S22
122VU LIGHTING/TST/BOARD/SPLY 30LP X06
121VU FUEL/CTR TK/PUMP2 SPLY 30QA P26

** ON A/C 101-200
121VU ACT XFR VALVE MAN CTL 30QH N29

** ON A/C ALL
121VU APU/AUTO/EXTIG/GND/TEST 30WF L40

** ON A/C 101-200
2001VU WASTE WIP-HEATER-LINE 31DU E04
2001VU POT/WASTE WIP-HEATER-LINE 31DW D03

** ON A/C ALL
49VU AIR COND/AFT CARGO/VENT/CTL & 31HN C07
MONG
121VU FUEL/CTR TK/PUMPS1 AND 2/CTL AND 31QA R25
IND

** ON A/C 101-200
2001VU POT/WASTE WIP HEATER-CTL 32DW D02

** ON A/C ALL
2001VU VACU TOIL SYS-LAV PWR-A 32MG A01
121VU FUEL/CTR TK/PUMPS1 AND 2/CTL AND 32QA R26
IND

** ON A/C 101-200
2001VU VACU TOIL SYS-VACUUM-GEN 33MG A08

Print Date: June 21, 2018 Page 14 of 18

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Customer : AAW Manual : AMM
Type : A318/A319/A320/A321 Selected applicability : ALL
Rev. Date : Nov 01, 2017

PANEL DESIGNATION FIN CLIPPED LOCATION

** ON A/C 001-002, 006-100

2001VU VACUUM TOILET SYSTEM/VACUUM 33MG A08
GEN

** ON A/C 101-200
121VU ACT/RFL/VALVE 33QU L29

** ON A/C ALL
2001VU VACU TOIL SYS-LAV PWR-E 34MG A04

** ON A/C 101-200
2001VU VACU TOIL SYS-VACUUM-SYS 35MG A06

** ON A/C 001-002, 006-100

2001VU VACUUM TOILET SYSTEM/VACUUM 35MG A06
SYS

** ON A/C ALL
2000VU IFE-VCC-SMOKE 37MH D06
2001VU VACU TOIL SYS-LAV PWR-D 39MG A03
49VU NAV/MMR/1 42RT1 G12
121VU COM NAV/MMR/2 42RT2 L07
121VU EIS/SDAC1 AND 2/BUS2/28VDC 44WV P03
2001VU VACU TOIL SYS-LAV PWR 45MG C A02
121VU EIS/SDAC1 AND 2/DOOR/DET/AVNCS 46WV P02
121VU FUEL/CTR TK/AUTO/CTL 47QA R27
121VU EIS/SDAC1 AND 2/DOOR/DET/PAX 48WV P05
122VU AIR COND/TEMP CTL SYS 1/CHAN A/ 49HH X22
115VAC
122VU AIR COND/TEMP CTL SYS 1/CHAN B/ 50HH Y18
115VAC
2000VU DR AREA HTG PNLS-DR1-FPH-LH 51DS A05

** ON A/C 101-200
2001VU POT/WASTE WIP-HEATER-LINE 51DW D04

** ON A/C ALL
122VU AIR COND/TEMP CTL SYS 1/CHAN A/ 51HH X21
28VDC

** ON A/C 101-200
121VU ACT LOW LVL R 51QJ M29

** ON A/C ALL
2000VU DR AREA HTG PNLS-DR1-FPH-RH 52DS A06
121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY 52GA Q34
49VU AIR COND/TEMP CTL/SYS 1 CHAN B/ 52HH D08
28VDC

** ON A/C 101-200
121VU ACT LOW LVL L 52QJ M28

Print Date: June 21, 2018 Page 15 of 18

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Customer : AAW Manual : AMM
Type : A318/A319/A320/A321 Selected applicability : ALL
Rev. Date : Nov 01, 2017

PANEL DESIGNATION FIN CLIPPED LOCATION

** ON A/C ALL
122VU AIR COND/TEMP CTL SYS 2/CHAN A/ 53HH W22
115VAC
2000VU DOOR AREA HTG PANELS-CTL 54DS A07
122VU AIR COND/TEMP CTL SYS 2/CHAN B/ 54HH Y20
115VAC
122VU AIR COND/TEMP CTL SYS 2/CHAN A/ 55HH W21
28VDC
49VU FUEL/SMOKE/CONFIG/PUMP CTL 55QA A14
122VU AIR COND/TEMP CTL SYS 2/CHAN B/ 56HH Y21
28VDC

** ON A/C ALL

EMB SB 32-1346 for A/C 001-002

121VU LGCIU/BAT SPLY/SYS1 58GA R32

** ON A/C ALL
49VU AIR COND/TEMP/CTL/IND 58HH D07

** ON A/C 101-200
2000VU SEAT POWER-MCU 1 58HP B05

** ON A/C 001-002, 006-100

2000VU SEAT POWER-MCU1 58HP B05

** ON A/C ALL

EMB SB 32-1346 for A/C 001-002

121VU LGCIU/BAT SPLY/SYS2 59GA R33

** ON A/C ALL
2000VU SEAT POWER-MCU 2 59HP B08
49VU ABCU &/Y BRK/PRESS IND 61GG C10
106VU DC BUS/1 AND 2/MONG 68WV C03
121VU HYDRAULIC/PARK BRK/CTL/NORM 70GG N36
121VU HYDRAULIC/PARK BRK/CTL/STBY 71GG N37
121VU RUDDER FTU 75CE R16
49VU LIGHTING/EMER LT/CABIN 79WL H07

** ON A/C 007-100
PRE SB 27-1248 for A/C 007-008
121VU THS ACTR/ELSD 95CE C P15

** ON A/C
POST SB 27-1248 for A/C 007-008
121VU THS ACTR/ELSD 95CE P15

** ON A/C ALL
2000VU LIGHT-STWG 100LZ J04

Print Date: June 21, 2018 Page 16 of 18

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Customer : AAW Manual : AMM
Type : A318/A319/A320/A321 Selected applicability : ALL
Rev. Date : Nov 01, 2017

PANEL DESIGNATION FIN CLIPPED LOCATION

121VU COM NAV/T2CAS 104SG K10
121VU ABCU/HOT BUS/SPLY 110GG P30
121VU COM/CIDS/DEU B/BAT 143RH N12
121VU COM/CIDS/DIR 2/BAT 146RH P14
121VU COM/CIDS/DIR 1/BAT 147RH P13
121VU COM/CIDS/BAT/CTL 148RH P12
121VU COM/CIDS/FLT ATTND PANL/BAT 149RH Q13
49VU COM/CIDS/DIR ESS/1 150RH G01
121VU COM NAV/CIDS/DIR NORM/1 151RH M05
49VU COM/CIDS/DEU B/ESS 153RH G03
121VU COM NAV/CIDS/DIR NORM/2 156RH M06
49VU COM/CIDS/DIR ESS/2 157RH G02
49VU COM/CIDS/DEU A ESS/FWD R 158RH HA10
49VU COM/CIDS/DEU A ESS/FWD L 159RH HA09
121VU COM NAV/CIDS/DEU B/NORM 162RH M08
121VU COM NAV/CIDS/DEU A NORM/L FWD 163RH M09
121VU COM NAV/CIDS/DEU A NORM/R FWD 164RH M10
121VU COM NAV/CIDS/DEU A NORM/L AFT 167RH M11
121VU COM NAV/CIDS/DEU A NORM/R AFT 168RH M12
121VU COM/FAP1/NORM 170RH Q14
49VU COM/CIDS/FLT ATTND PNL/ESS 171RH H01
49VU COM/CIDS/DEU A ESS/AFT R 172RH HA12
49VU COM/CIDS/DEU A ESS/AFT L 179RH HA11
2000VU PES PFIS RADVR 188MH C C08
2000VU PES/PFIS 189MH G09
121VU COM/CIDS/DEU A BAT/FWD R 258RH N14
121VU COM/CIDS/DEU A BAT/L FWD 259RH N13
121VU COM/CIDS/DEU A BAT/AFT R 272RH Q11
121VU COM/CIDS/DEU A BAT/AFT L 279RH Q10
2000VU CAB LIGHT PWR-WINDOW-FWD 300LG H01
2000VU CAB LIGHT PWR-WINDOW-AFT 301LG H03
2000VU CABIN LIGHT POWER-WINDOW AFT 302LG H04
2000VU CAB LIGHT PWR-WINDOW-FWD 303LG H02
2000VU CAB LIGHT PWR-CEILING-AFT 304LG H07
2000VU CAB LIGHT PWR-CEILING-FWD 305LG H05
2000VU CAB LIGHT PWR-CEILING-FWD 306LG H06
2000VU CAB LIGHT PWR-CEILING-AFT 307LG H08
2000VU LIGHT-CABIN-ENTRY 308LG J02

** ON A/C 001-002, 006-100

2000VU LIGHT-NON DIMM-HANDRAIL 309LG J05

** ON A/C 101-200
2000VU LIGHT-NON-DIMM-HANDRAIL 309LG J05

** ON A/C ALL
121VU HYDRAULIC/G HYD/PUMP ENG1/CTL 1701GK R35
121VU HYDRAULIC/G HYD/PUMP ENG1/MONG 1702GK R34
49VU HYD/FIRE VALVE/G/ENG1 1703GK C13
121VU HYDRAULIC/SOL VALVES/G/Y/PTU 1801GL N34

Print Date: June 21, 2018 Page 17 of 18

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Customer : AAW Manual : AMM
Type : A318/A319/A320/A321 Selected applicability : ALL
Rev. Date : Nov 01, 2017

PANEL DESIGNATION FIN CLIPPED LOCATION

** ON A/C ALL

EMB SB 29-1126 for A/C 001-002, 101-103

121VU PTU INHIT/G SYS 1807GL Q32
121VU PTU INHIT/Y SYS 1808GL Q33

** ON A/C ALL
121VU HYDRAULIC/HYD/QTY/IND 1831GQ P35
121VU HYDRAULIC/LOW/LVL/IND 1832GQ N32
49VU HYD/HYD/PRESS/XMTR 1841GN C11
121VU HYDRAULIC/SOL VALVES/G/Y/B/LEAK/ 1881GP N35
TST
123VU B HYD/ELEC PUMP 2701GJ AB09
49VU HYD/HYD PWR/B WARN/& CTL 2702GJ C12
49VU HYD/RAT/CTL 2801GE D14
121VU HYDRAULIC/RAT/SPLY/EXTN/SOL1 2803GE P33
121VU HYDRAULIC/Y HYD/PUMP ENG2/MONG 3700GD Q37
121VU HYDRAULIC/Y HYD/PUMP ENG2/CTL 3701GD Q36
49VU HYD/FIRE VALVE/Y/ENG2 3702GD C14
123VU Y HYD/ELEC/ELEC PUMP/NORM 3801GX AB03
123VU Y HYD/ELEC/PUMP 3802GX AB06
121VU HYDRAULIC/HYD POWER/Y 3803GX N30

** ON A/C 008-100
POST SB 24-1135 for A/C 001-002, 101-103

EMB SB 24-1135 for A/C 008-008

121VU USB CAPT 8501NA 08U
121VU USB/F/O 8502NA 09U

End of document

Print Date: June 21, 2018 Page 18 of 18

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
ABNORMAL AND 02.01A
A318/A319/A320/A321 EMERGENCY PROCEDURES
QUICK REFERENCE HANDBOOK 22 MAY 19

SYSTEM RESET - GENERAL

WARNING Only perform one reset at a time, unless indicated differently.

Guidelines to reset a system:

‐ Set the related normal cockpit control to OFF, or pull the corresponding circuit breaker,
‐ Wait 3 s if a normal cockpit control is used, or 5 s if a circuit breaker is used (unless a different time is
indicated),
‐ Set the related normal cockpit control to ON, or push the corresponding circuit breaker,
‐ Wait 3 s for the end of the reset.
 On ground:
Reset ECU (CFM) or EEC (IAE) or EIU only when engine shut down.
Reset BSCU only when aircraft stopped.
Reset ELAC or SEC only when listed in the System Reset Table.
Other Systems not listed in the System Reset Table can be reset following the guidelines described
above.
Refer to System Reset Table
 In flight:

WARNING The flight crew can attempt a system reset only when:
‐ An ECAM/OEB/FCOM/QRH procedure requests to reset the
system, or
‐ The System Reset Table permits.

CAUTION Do not pull the following circuit breakers:

‐ SFCC
‐ ECU or EEC or EIU.
Note: Before taking any action on the cockpit C/Bs, both the PF and PM must crosscheck and
ensure that the C/B label corresponds to the affected system.
Refer to System Reset Table

AAW MSN 05448 5A-ONO

ABNORMAL AND 02.02A
A318/A319/A320/A321 EMERGENCY PROCEDURES
QUICK REFERENCE HANDBOOK 22 MAY 19

SYSTEM RESET TABLE

System malfunction
ECAM System or ECAM Alert Reset Procedure
(Affected System)

ANTI ICE L(R) On ground:

If the air conditioning packs are OFF with the OAT above 40 °C, and/or
WINDSHIELD(WINDOW)
the windshield is under direct sunlight, a spurious ANTI ICE L(R)
(WHC)
WINDSHIELD(WINDOW) may trigger.
A-ICE In that case, select both air conditioning packs to ON and wait at least 5 minutes
for the cockpit temperature to decrease. After, pull, then push the C/B of the
affected WHC:
‐ X13 on 122VU (WHC1)
‐ W13 on 122VU (WHC2).

AAW MSN 05448 5A-ONO

ABNORMAL AND 02.02B
A318/A319/A320/A321 EMERGENCY PROCEDURES
QUICK REFERENCE HANDBOOK 22 MAY 19

Continued from the previous page

System malfunction
ECAM System or ECAM Alert Reset Procedure
(Affected System)

AIR PACK 1(2) On ground only:

REGUL FAULT ‐ Pull C/Bs W21 and W22 on 122VU
(ACSC) ‐ Pull C/Bs X21 and X22 on 122VU
‐ Pull C/Bs Y18, Y20 and Y21 on 122VU
‐ Pull C/B D8 on 49VU
‐ Wait 5 s before pushing all the C/Bs.

Note: During the reset, a small increase of the engine thrust may be observed
(N1 or EPR, as applicable). If the parking brake is set, vibrations can
occur.

AIR ENG 1(2) Note: Do not attempt more than one reset. However, if the first reset is
BLEED FAULT or unsuccessful and if the AIR ENG 1(2) BLEED FAULT alert occurred
AIR ENG 1(2) after takeoff with APU bleed ON, a second reset may be attempted
when flight conditions permit and when the aircraft is stabilized in level
BLEED ABNORM flight.
PR On ground or in flight:
(Engine Bleed Supply
System) If the PACK (non-affected side) is operative, and If the Wing Anti-Ice is OFF:
‐ Set ENG BLEED pb-sw (affected side) to OFF
▪ If ENG BLEED pb-sw FAULT light (affected side) is on:
‐ Delay application of the reset until FAULT light extinguishes.
▪ If ENG BLEED pb-sw FAULT light (affected side) is off:
‐ Set X BLEED selector to AUTO
‐ Set PACK pb-sw (affected side) to ON
‐ Set ENG BLEED pb-sw (affected side) to ON
AIR ‐ Check that the affected Engine Bleed Valve is open on the BLEED SD
page.
• If AIR ENG (AFFECTED) BLEED FAULT alert or AIR ENG
(AFFECTED) BLEED ABNORM PR alert reoccur, or
If Engine Bleed Valve (affected side) is not open on the BLEED SD
page:
- Set ENG BLEED pb-sw(affected side) to OFF
- Set X BLEED selector to OPEN.

Note: Record the ENG BLEED reset in the logbook (successful or

unsuccessful).

AIR ENG 1(2) Note: Do not attempt more than one reset.
BLEED NOT CLSD
(Engine Bleed Supply On ground only:
System) ‐ Set ENG BLEED pb-sw (affected side) to OFF
▪ If ENG BLEED pb-sw FAULT light (affected side) is on:
‐ Delay application of the reset until FAULT light extinguishes.
▪ If ENG BLEED pb-sw FAULT light (affected side) is off:
‐ Set ENG BLEED pb-sw (affected side) to ON.

‐ Check that the affected Engine Bleed Valve is closed on the BLEED SD page.

Note: Record the ENG BLEED reset in the logbook (successful or

unsuccessful).

AAW MSN 05448 5A-ONO

ABNORMAL AND 02.02C
A318/A319/A320/A321 EMERGENCY PROCEDURES
QUICK REFERENCE HANDBOOK 22 MAY 19

Continued from the previous page

System malfunction
ECAM System or ECAM Alert Reset Procedure
(Affected System)
1
AUTO FLT A/THR On ground, before taxi only:
OFF • If no engine running:
‐ Press FCU A/THR pb in order to re-engage the A/THR (this will cancel the
ECAM alert)
‐ Press A/THR instinctive disconnect pb to disconnect A/THR.
• If at least one engine is running:
‐ Apply external power or APU generator power
‐ ENG MASTER (running engine(s))…………………………...OFF
‐ Press FCU A/THR pb in order to re-engage the A/THR (this will cancel the
ECAM alert)
‐ Press A/THR instinctive disconnect pb to disconnect A/THR.

AUTO FLT FCU In flight:

1(2) FAULT ‐ Pull the C/B B05 on 49VU for FCU 1, or M21 on 121VU for FCU 2
(FCU) ‐ Push it after 5 s
‐ Check the displayed targets and the barometer reference, and correct them if
necessary.
On ground:
‐ Pull the C/B B05 on 49VU for FCU 1, or M21 on 121VU for FCU 2
‐ Push it after 5 s
‐ If AUTO FLT FCU 1(2) FAULT disappears, check the displayed
targets and barometer reference, and correct them if necessary (RESET
successful)
‐ If AUTO FLT FCU 1(2) FAULT remains, pull both C/B B05 on
49VU and M21 on 121VU
‐ Push them after 7 min , with a delay of less than 5 s between side 1 and 2
AUTO FLT ‐ Wait at least 30 s for FCU 1 and FCU 2 safety tests completion
‐ Check the displayed targets and barometer reference, and correct them if
necessary (RESET successful).

AUTO FLT FCU 1 In flight:

+ 2 FAULT ‐ Pull the C/B B05 on 49VU for FCU 1, and then pull M21 on 121VU for FCU 2
(FCU) ‐ Push them after 5 s
‐ Check the displayed targets and the barometer reference, and correct them if
necessary.
On ground:
‐ Pull the C/B B05 on 49VU for FCU 1, and then pull M21 on 121VU for FCU 2
‐ Push the C/Bs after 5 s
‐ If AUTO FLT FCU 1+2 FAULT disappears, check the displayed
targets and barometer reference, and correct them if necessary (RESET
successful)
‐ If AUTO FLT FCU 1+2 FAULT remains, pull again both C/B B05
on 49VU and M21 on 121VU
‐ Push them after 7 min , with a delay of less than 5 s between side 1 and 2
‐ Wait at least 30 seconds for FCU 1 and FCU 2 safety tests completion
‐ Check the displayed targets and barometer reference, and correct them if
necessary (RESET successful)
FCU targets are synchronized on current aircraft values and displayed as selected
targets.
‐ Re–enter the barometer altimeter setting value, if necessary.

AUTO FLT YAW In flight:

[ALSO, SEE 24-00-00-810-818-A]

DAMPER 1(2) If AP is inoperative:

(FAC 1(2)) ‐ Set FAC 1(2) pb to OFF
‐ Wait 3 s

AAW MSN 05448 5A-ONO

ABNORMAL AND 02.02D
A318/A319/A320/A321 EMERGENCY PROCEDURES
QUICK REFERENCE HANDBOOK 22 MAY 19

Continued from the previous page

System malfunction
ECAM System or ECAM Alert Reset Procedure
(Affected System)
‐ Set FAC 1(2) pb to ON.

One MCDU locked or blank

On ground, or in flight:
(MCDU)
‐ Pull the C/B for the locked or blank MCDU and push it back after 10 s.
The circuit breakers for the MCDUs are:
• AUTO FLT/MCDU 1 B1 ON 49 VU (Overhead Panel)
• AUTO FLT/MCDU 2 N20 ON 121 VU (Right Rear Maintenance Panel)
• AUTO FLT/MCDU 3 N21 ON 121 VU (Right Rear Maintenance Panel)

Both MCDU locked or blank

The circuit breakers for the FMGCs are:
or FMGC malfunction
• AUTO FLT/FMGC 1 B2 ON 49 VU (Overhead Panel)
(FMGC)
• AUTO FLT/FMGC 2 M17 ON 121 VU (Right Rear Maintenance Panel)
Short FMGC Reset:
On ground:
• If no engine running:
‐ Apply external power or APU generator power.
‐ Wait 2 min before resetting the FMGC circuit breakers.
‐ Set FD 1(2) pb to OFF.
‐ Pull the C/B of the affected FMGC.
‐ Wait 10 s.
‐ Push the C/B of the affected FMGC.

CAUTION Always wait 1 min after the reset,

before engaging or reengaging the FD
and the AP of the reset FMGC.
• If engines running:
‐ Set FD 1(2) pb to OFF.
‐ Pull the C/B of the affected FMGC.
‐ Wait 10 s.
‐ Push the C/B of the affected FMGC.

CAUTION Always wait 1 min after the reset,

before engaging or reengaging the
FD and the AP of the reset FMGC.
• If FMGC reset is unsuccessful:
‐ Consider FMGC reset with engines not running.

Note: The FMGC reset is more effective with engines not running.

In flight:
‐ Set FD 1(2) pb to OFF.
‐ Pull the C/B of the affected FMGC.
‐ Wait 10 s.
‐ Push the C/B of the affected FMGC.

CAUTION Always wait 1 min after the reset,

before engaging or reengaging the FD
and the AP of the reset FMGC.
Long FMGC Reset:
On ground:
• If no engine running:
‐ Apply external power or APU generator power.
‐ Wait 2 min before resetting the FMGC circuit breakers.
‐ Set FD 1(2) pb to OFF.

AAW MSN 05448 5A-ONO

ABNORMAL AND 02.02E
A318/A319/A320/A321 EMERGENCY PROCEDURES
QUICK REFERENCE HANDBOOK 22 MAY 19

Continued from the previous page

System malfunction
ECAM System or ECAM Alert Reset Procedure
(Affected System)
‐ Pull the C/B of the affected FMGC.
‐ Wait 15 min.
‐ Push the C/B of the affected FMGC.

CAUTION Always wait 1 min after the reset,

before engaging or reengaging the FD
and the AP of the reset FMGC.
• If engines running:
‐ Set FD 1(2) pb to OFF.
‐ Pull the C/B of the affected FMGC.
‐ Wait 15 min.
‐ Push the C/B of the affected FMGC.

CAUTION Always wait 1 min after the reset,

before engaging or reengaging the
FD and the AP of the reset FMGC.
• If FMGC reset is unsuccessful:
‐ Consider FMGC reset with engines not running.

Note: The FMGC reset is more effective with engines not running.

In flight:
‐ Set FD 1(2) pb to OFF.
‐ Pull the C/B of the affected FMGC.
‐ Wait 15 min.
‐ Push the C/B of the affected FMGC.

CAUTION Always wait 1 min after the reset,

before engaging or reengaging the FD
and the AP of the reset FMGC.
Note: Consider a long FMGC reset only if a short FMGC reset has no
effect.

AAW MSN 05448 5A-ONO

ABNORMAL AND 02.02F
A318/A319/A320/A321 EMERGENCY PROCEDURES
QUICK REFERENCE HANDBOOK 22 MAY 19

Continued from the previous page

System malfunction
ECAM System or ECAM Alert Reset Procedure
(Affected System)

BRAKES SYS 1(2) On ground:

FAULT ‐ STOP aircraft
or ‐ Set PARK BRK handle to ON
BRAKES BSCU ‐ Confirm that towing bar is disconnected
‐ Set A/SKID & N/W STRG sw to OFF
CH 1(2) FAULT ‐ Set A/SKID & N/W STRG sw to ON.
(BSCU)
• IF UNSUCCESSFUL:
‐ Pull C/Bs M33 and M34 on 121VU for BSCU channel 1
‐ Pull C/Bs M36 and M35 on 121VU for BSCU channel 2
‐ Push C/Bs.

After a successful reset, resume to normal operation.

BRAKES
Note: After any BSCU reset:
1. Check brake efficiency
2. Record BSCU reset in the logbook.

In flight:
When landing gear is up only:
‐ Set A/SKID & N/W STRG sw to OFF
‐ Set A/SKID & N/W STRG sw to ON
‐ If required, rearm the autobrake.
When landing gear is down: reset not authorized.

Note: After any BSCU reset:

‐ Record BSCU reset in the logbook.

AAW MSN 05448 5A-ONO

ABNORMAL AND 02.02G
A318/A319/A320/A321 EMERGENCY PROCEDURES
QUICK REFERENCE HANDBOOK 22 MAY 19

Continued from the previous page

System malfunction
ECAM System or ECAM Alert Reset Procedure
(Affected System)

COM CIDS 1+2 Confirm if spurious:

FAULT and/or Loss of ‐ Check PA function
Passenger Address and/or ‐ Check Cabin Interphone function
Loss of Cabin Interphone ‐ Check Cabin Lighting function.
(CIDS)
If spurious, reset the CIDS when aircraft is self powered (APU or engine).
On ground or in flight:
‐ Pull the C/Bs in the following order:
P13  and P14  on 121VU
G01 and G02 on 49VU
M05 and, M06 on 121VU
‐ Wait 10 s, then
‐ Push the C/B in the following order:
M05, M06, G01, G02, P13  , P14 
‐ After CIDS reset, wait approximately 4 min before recovering normal operation.

Uncommanded EVAC horn

On ground, or in flight:
activation
(CIDS) Press the EVAC HORN SHUT OFF pb. Set the EVAC CAPT & PURS CAPT sw to
the CAPT only position. Wait for 3 s.
• IF UNSUCCESSFUL:
‐ Pull the C/Bs for DIR 2 in the following order: G02 on 49VU, M06 on 121VU.
• IF UNSUCCESSFUL:
‐ Pull the C/Bs for DIR 1 in the following order: G01 on 49VU, M05 on
121VU
‐ Wait for 1 min, then
COM ‐ Push the C/Bs for DIR 2 in the following order: M06, G02
‐ After CIDS reset, wait approximately 4 min, before recovering normal
operation.

Frozen RMP
On ground, or in flight:
(RMP)
The flight crew must reset all the RMPs one after the other via the RMP control
panel:
‐ Set RMP ON/OFF sw to OFF position
‐ Wait 5 s
‐ Set RMP ON/OFF sw to ON position.

FAP freezing For tape reproducer or PRAM,

On ground, or in flight:
(FAP) open tape reproducer
‐ Pull the C/Bs in the following order: /PRAM C/B 2RX (Shed Bus 115V)
H01 on 49VU, Q14 on 121VU
‐ Wait 10 s, then on the panel 2000VU.
‐ Push the C/Bs in the following order:
Q14, H01.

SATCOM  malfunction On ground, or in flight:

(SATCOM  )
‐ Pull the SATCOM C/B K01 C/B on 121VU
‐ Wait 5 s
‐ Push the SATCOM C/B K01 C/B on 121VU.

Note: ‐ The Satellite Data Unit (SDU) should reset in less than 2 min
‐ The flight crew cannot perform a software reset for SATCOM via the
MCDU.

AAW MSN 05448 5A-ONO

ABNORMAL AND 02.02H
A318/A319/A320/A321 EMERGENCY PROCEDURES
QUICK REFERENCE HANDBOOK 22 MAY 19

Continued from the previous page

System malfunction
ECAM System or ECAM Alert Reset Procedure
(Affected System)
ATSU  The ATSU reset should be attempted, only if:
(ATSU or DCDU) ‐ "INVALID DATA" is displayed on the DCDU, or
‐ Key selection has no effect on the DCDU or any of the MCDU ATSU DATALINK
submenus, or
‐ ADS-C, CPDLC or AOC are inoperative
When the ATSU is reset, the following connections are no longer active:
‐ CPDLC:
• The flight crew should send a notification to the ATC center to re-establish
the CPDLC connection
DATALINK
‐ ADS-C:
• As no ADS-C disconnect message is sent, the ATC center(s) assumes that
the ADS-C connection is still alive
• The flight crew must check that ADS-C is ARMED or ON.
On ground or in flight:
‐ Pull the C/Bs in the following order: L16, L15 on 121VU
‐ Wait 5 s, then
‐ Push the C/Bs in the following order: L15, L16.

Flickering or total loss of the

On ground, or in flight:
video camera display (on
the SD) accompanied by ‐ Set the VIDEO rotary selector to OFF, on the center pedestal VIDEO panel
the ″VIDEO NOT AVAIL″ ‐ Set the COCKPIT DOOR VIDEO pb-sw to OFF, on the overhead panel
DOOR message. ‐ Wait 2 min, then
(CDSS) ‐ Set the COCKPIT DOOR VIDEO pb-sw back on, on the overhead panel
‐ Wait 15 s, then
‐ Set the VIDEO rotary selector to ″CKPT ENTRY″, on the center pedestal VIDEO
panel.

GPU cannot be connected to

On ground only:
the aircraft
(GAPCU) The GPU cannot be connected to the electrical network of the aircraft (AVAIL light
is OFF):
• If at least one power source (IDG 1 or 2, APU GEN or batteries) is connected to
the electrical network of the aircraft:
ELEC
‐ Reset the EXT PWR pb on 35VU (Press and release).
• If no power source is connected to the electrical network of the aircraft:
‐ Set the BAT 1 pb-sw and BAT 2 pb-sw to AUTO.
FOR A COLD RESET, SWITHCH ALL POWER OFF AND REMOVE RECEPTACLE.

ENG 1(2) FADEC On ground only:

A(B) FAULT If this alert triggers at engine start, apply the following procedure:
(FADEC) ‐ Set ENG MASTER (affected) pb-sw to OFF
ENG ‐ Wait until N2 speed below 5 %
‐ Pull C/B A04 or A05 on 49VU for ENG 1(2) FADEC channel A
‐ Pull C/B R41 or Q40 on 121VU for ENG 1(2) FADEC channel B
‐ Wait 5 s before pushing the C/Bs
‐ After ECU power-up sequence, the Flight Crew can restart the engine.

AAW MSN 05448 5A-ONO

ABNORMAL AND 02.02I
A318/A319/A320/A321 EMERGENCY PROCEDURES
QUICK REFERENCE HANDBOOK 22 MAY 19

Continued from the previous page

System malfunction
ECAM System or ECAM Alert Reset Procedure
(Affected System)

F/CTL ELAC 1 In flight:

PITCH FAULT ‐ Not authorized.
(ELAC)
On ground:

CAUTION ‐ Do not reset ELAC in case of dispatch

with MMEL item SEC 1 or SEC 2.
‐ Do not attempt more than one reset.
‐ Set ELAC 2 pb-sw to OFF
‐ Set pitch trim to 5 UP position
‐ Set ELAC 1 pb-sw to OFF
‐ Wait 3 s
‐ Set ELAC 1 pb-sw to On
‐ After 15 s, check pitch trim at 0 position
‐ Perform a flight control check
‐ Set ELAC 2 pb-sw to On
‐ Set pitch trim to takeoff CG

Note: Record the ELAC 1 reset in the logbook (successful or unsuccessful).

F/CTL ELAC 2 In flight:

PITCH FAULT ‐ Not authorized.
(ELAC)
On ground:

CAUTION ‐ Do not reset ELAC in case of dispatch

with MMEL item ELAC 1, SEC 1 or
SEC 2.
F/CTL ‐ Do not attempt more than one reset.
‐ Set ELAC 1 pb-sw to OFF
‐ Set pitch trim to 5 UP position
‐ Set ELAC 2 pb-sw to OFF
‐ Wait 3 s
‐ Set ELAC 2 pb-sw to On
‐ After 15 s, check pitch trim at 0 position
‐ Perform a flight control check
‐ Set ELAC 1 pb-sw to On
‐ Set pitch trim to takeoff CG

Note: Record the ELAC 2 reset in the logbook (successful or unsuccessful).

F/CTL AIL SERVO In flight:

FAULT ‐ Not authorized.
(ELAC)
On ground:

CAUTION ‐ Do not reset ELAC if more than one

aileron actuator indication box is
displayed in amber on the F/CTL SD
page.
‐ Do not reset ELAC in case of dispatch
with MMEL item ELAC 1, SEC 1, SEC
2 or SEC 3.
‐ Do not attempt more than one reset.
‐ Set ELAC 1 pb-sw to OFF

AAW MSN 05448 5A-ONO

ABNORMAL AND 02.02J
A318/A319/A320/A321 EMERGENCY PROCEDURES
QUICK REFERENCE HANDBOOK 22 MAY 19

Continued from the previous page

System malfunction
ECAM System or ECAM Alert Reset Procedure
(Affected System)
‐ Set ELAC 2 pb-sw to OFF
‐ Wait 3 s
‐ Set ELAC 2 pb-sw to On
‐ Perform a flight control check
‐ Set ELAC 2 pb-sw to OFF
‐ Set ELAC 1 pb-sw to On
‐ Perform a flight control check
‐ Set ELAC 2 pb-sw to On
‐ Set pitch trim to takeoff CG

Note: Record the ELAC 1 and ELAC 2 resets in the logbook (successful or
unsuccessful).

F/CTL SPLR In flight:

FAULT ‐ Not authorized.
(SEC)
On ground:

CAUTION ‐ Do not reset SEC in case of dispatch

with MMEL item ELAC 1, SEC 1, SEC
2 or SEC 3.
‐ Do not attempt more than one reset.
‐ Set SEC 1 pb-sw to OFF
‐ Wait 3 s
‐ Set SEC 1 pb-sw to On
‐ Set SEC 2 pb-sw to OFF
‐ Wait 3 s
‐ Set SEC 2 pb-sw to On
‐ Set SEC 3 pb-sw to OFF
‐ Wait 3 s
‐ Set SEC 3 pb-sw to On
‐ Perform a flight control check

Note: Record the SEC 1, SEC 2 and SEC 3 resets in the logbook (successful
or unsuccessful).

Loss of fuel quantity

On ground, or in flight:
indication or Simultaneous
‐ Pull the three C/Bs:
triggering of FUEL
• Channel 1 (A13 on 49VU)
L OUTER XFR • Channel 2 (M27 on 121VU)

FUEL CLOSED and FUEL • Channel 1 and 2 (L26 on 121VU).

‐ Wait 5 s, before pushing the three C/Bs.
R OUTER XFR
CLOSED although Note: 1. The fuel quantity indication will be re-established within 1 min
2. The fuel leak detection function will be lost for the remainder of the
FUEL SD indicates no
flight. The flight crew must monitor the fuel quantity.
anomaly.
(FQIC)

FWS FWC 1(2) On ground:

FAULT Pull, then push, the C/B of the affected FWC:
(FWC) ‐ FWC 1 (F01 on 49VU)
‐ FWC 2 (Q7 on 121VU).
FWS Wait 50 s after pushing the C/Bs.
In flight:
Pull, then push, the C/B of the affected FWC:
‐ FWC 1 (F01 on 49VU)
‐ FWC 2 (Q7 on 121VU).

AAW MSN 05448 5A-ONO

ABNORMAL AND 02.02K
A318/A319/A320/A321 EMERGENCY PROCEDURES
QUICK REFERENCE HANDBOOK 22 MAY 19

Continued from the previous page

System malfunction
ECAM System or ECAM Alert Reset Procedure
(Affected System)
2

L/G LGCIU 1(2) On ground only:

FAULT The flight crew must depressurize the green hydraulic system before resetting the
(LGCIU 1(2)) LGCIU:
‐ ENG 1 PUMP OFF
‐ PTU OFF.
When there is no green hydraulic pressure:
L/G ‐ To reset LGCIU 1:
• Pull C/B Q34 on 121VU, then C09 on 49VU, then R32 on 121VU.
• Wait for 15 s, then push the C/Bs.
‐ To reset LGCIU 2:
• Pull C/B Q35 on 121VU, then R33 on 121VU.
• Wait for 15 s, then push the C/Bs.
After the LGCIU reset, restore green hydraulic pressure (ENG 1 PUMP ON, PTU
AUTO).

NAV TCAS FAULT

On ground only:
(TCAS) ‐ Pull C/B K10 on 121VU
‐ Wait 5 s, then push the C/B.

ISIS malfunction
On ground only:
(ISIS)
With aircraft not moving:
NAV ‐ Pull C/B F12 on 49VU
‐ Wait 5 s, then push the C/B
‐ Normal operation is expected after approximately 2 min.

Note: In the case of small aircraft motion during the C/B reset (refueling, cargo
loading conditions, etc.), the ATT red flag may appear on the ISIS. In
this case, press the RST P/B for 2 s, and wait 2 min to recover normal
operation.

AAW MSN 05448 5A-ONO

ABNORMAL AND 02.02L
A318/A319/A320/A321 EMERGENCY PROCEDURES
QUICK REFERENCE HANDBOOK 22 MAY 19

Continued from the previous page

System malfunction
ECAM System or ECAM Alert Reset Procedure
(Affected System)

SMOKE DET On ground or in flight:

FAULT Apply the following actions in the presented order:
(CIDS-SDF) ‐ Pull the C/Bs C05 and C06 on 49VU, T17 and T18 on 122VU
‐ Wait 10 s, then
‐ Push simultaneously the C/Bs C05 and C06 on 49VU
‐ Within 2 s push simultaneously the C/Bs T17 and T18 on 122VU
‐ After CIDS reset, wait approximately 4 min before recovering normal operation.

SMOKE On ground or in flight:

LAVATORY DET Apply the following actions in the presented order:
FAULT with all lavatories ‐ Pull the C/Bs P13 and P14  on 121VU, G01 and G02 on 49VU, M05 or M06
declared inoperative on the and M06 or M07 on 121VU
FAP ‐ Wait 10 s, then
(CIDS or CIDS-SDF) ‐ Push the C/Bs in the following order: M05 or M06 and M06 or M07 on 121VU,
G01 and G02 on 49VU, P13 and P14  on 121VU
‐ After CIDS reset, wait approximately 4 min before recovering normal operation.
SMOKE
If unsuccessful, on ground only:
Apply the following actions in the presented order:
‐ Pull the C/Bs C06 and C05 on 49VU, T17 and T18 on 122VU
‐ Wait 10 s, then
‐ Push simultaneously the C/Bs C05 and C06 on 49VU
‐ Within 2 s push simultaneously the C/Bs T17 and T18 on 122VU
‐ After CIDS reset, wait approximately 4 min before recovering normal operation.

SMOKE FWD On ground:

(AFT) CARGO Apply the following actions in the presented order:
DET FAULT ‐ Pull the C/Bs C05 and C06 on 49VU, T17 and T18 on 122VU
‐ Wait 10 s, then
SMOKE FWD ‐ Push simultaneously the C/Bs C05 and C06 on 49VU
(AFT) CRG 1/2 ‐ Within 2 s push simultaneously the C/Bs T17 and T18 on 122VU
‐ After CIDS reset, wait approximately 4 min before recovering normal operation.
BTL FAULT
(CIDS-SDF)

VENT AVNCS On ground only:

VENT SYS FAULT ‐ Pull C/B Y17 on 122VU
(AEVC) ‐ Wait 5 s before pushing the C/B.

AAW MSN 05448 5A-ONO

ABNORMAL AND 02.02M
A318/A319/A320/A321 EMERGENCY PROCEDURES
QUICK REFERENCE HANDBOOK 22 MAY 19

Continued from the previous page

System malfunction
ECAM System or ECAM Alert Reset Procedure
(Affected System)

WHEEL N.W On ground only:

STEER FAULT Case A

or If the three conditions below are fulfilled:
WHEEL N/W ‐ the WHEEL N/W STRG FAULT alert was triggered just after

STRG FAULT engine start

‐ the N/W STRG DISC memo was displayed before the start of the
(BSCU)
pushback (before the aircraft starts moving)
‐ the N/W STRG DISC memo remained displayed even after the
pushback is finished (nosewheel steering selector bypass pin is in the steering
position).
Apply the below reset procedure.
If the ECAM alert disappears after the reset, the flight crew may continue the flight
without troubleshooting.
Case B
WHEEL
In all other cases, including in case of doubt on the above conditions,
troubleshooting must be performed before continuing the flight, even if the ECAM
alert disappears after the reset. For a return to the gate :
‐ Apply the below reset procedure
‐ The taxi speed must not exceed 10 kt.
Reset Procedure:
‐ STOP aircraft
‐ Set PARK BRK handle to ON
‐ Confirm that towing bar is disconnected
‐ Set A/SKID & N/W STRG sw to OFF
‐ Set A/SKID & N/W STRG sw to ON.

Note: After any BSCU reset:

1. Check brake efficiency
2. Check absence of aircraft veering
3. Record the BSCU reset in the logbook.

AAW MSN 05448 5A-ONO

CAB PRESS SYS 1(2)FAULT

 Aircraft configuration prior to reset:

No specific.

Circuit breakers to reset:

Steps to clear warning:

Open associated breakers for 5 seconds, then reset.

Y23 for classic

Reset duration:

5 seconds.

Results of power up test or reset:

Pass: Ecam fault disappears.

Fail: Ecam fault remains.

Notes:

No notes at this time.

Sign off:

AMM21-31-00-710-002.

Applicable deferrals:

MEL21-31-01=Auto System.
MEL21-31-02=Manual System.

AIR-PACK 1(2) FAULT

 Aircraft configuration prior to reset:

Associated fault light illuminated on overhead pushbutton. Valve is amber on bleed page.

COMPUTER (ACSC"1" 2)

Circuit breakers to reset: FOR SYS 1:ON PANEL 122VU OPEN THE C/B X22,Y18 & X21.ON
PANEL 49VU OPEN THE C/B D8 THEN CLOSE ..

FOR SYS2 : ON PANEL 122VU OPEN THE C/B W22,Y20,W21,&Y21 THEN CLOSE.

Steps to clear warning : FOR CLASSIC

Select associated PACK “OFF”, then“ON” using overhead pushbuttons.

Reset duration:

5 seconds.

Results of power up test or reset:

Pass: Valve will show in-line green on bleed page.

Fail: Valve indication will be crossline amber.

Notes:

To easily determine if the valve is faulty, disconnect the flow control valve cannon plug with bleed
air present. Valve should open as per design.

Sign off:

AMM21-61-00-710-001.

Applicable deferrals:

MEL21-51-01=Flow Control Valve.

MEL21-52-01=Packs.

VENT-AVNCS BLOWER FAULT

 Aircraft configuration prior to reset:

Blower/Exract fans in "AUTO", Ditching pushbutton "OFF".

Circuit breakers to reset:

Steps to clear warning:

Open Y17 C/B for 2 seconds, then close. If no help, open all three breakers for 2 seconds, then
close.

Reset duration:

90 seconds.

Results of power up test or reset:

Pass: Ecam fault disappears.

Fail: Ecam fault remains. Perform CFDS AVEC test.

Notes:

There is a thermal reset button on the fan motor.

Sign off:

AMM21-26-00-710-001.

Applicable deferrals:

MEL21-26-01=Blower Fan.

VENT-AVNCS EXTRACT FAULT

 Aircraft configuration prior to reset:

Blower/Exract fans in AUTO, Ditching pushbutton OFF.

Circuit breakers to reset:

Steps to clear warning:

Open Y17 C/B for 2 seconds, then close. If no help, open all three breakers for 2 seconds, then
close.

Reset duration:

90 seconds.

Results of power up test or reset:

Pass: Ecam fault disappears.

Fail: Ecam fault remains. Perform CFDS AVEC test.

Notes:

There is a thermal reset button on the fan motor.

Sign off:

AMM21-26-00-710-001.

Applicable deferrals:

MEL21-26-02=Extract Fan

VENT-AVNCS SKIN VALVE FAULT

 Aircraft configuration prior to reset:

Blower/Exract fans in AUTO, Ditching pushbutton OFF.

Circuit breakers to reset:

Steps to clear warning:

Open Y17 C/B for 2 seconds, then close. If no help, open all three breakers for 2 seconds, then
close.

Reset duration:

90 seconds.

Results of power up test or reset:

Pass: Ecam fault disappears.

Fail: Ecam fault remains. Perform CFDS AVEC test.

Notes:

Make sure the deactivation switch on skin air valve is in the "ON" position.

Sign off:

AMM21-26-00-710-001.
Applicable deferrals:

MEL21-26-03=SkinAirInletBypassValve.
MEL21-26-04=SkinAirOutletValve.
MEL21-26-05=Skin Air Inlet Valve.
VENT-AVNCS SYS FAULT

 Aircraft configuration prior to reset:

Blower/Exract fans in AUTO, Ditching pushbutton OFF.

Circuit breakers to reset:

Steps to clear warning:

First perform a AVEC test through CFDS. If no help, open Y17 C/B for 5 seconds, then close. If still
no help, open all three breakers for 5 seconds, then close.

Reset duration:

90 seconds.

Results of power up test or reset:

Pass: Ecam fault disappears.

Fail: Ecam fault remains.

Notes:

No notes at this time.

Sign off:

AMM21-26-00-710-001.

Applicable deferrals:

MEL21-26-10=Avionics Equipment Vent Computer.

COND-ZONE REGUL FAULT

 Aircraft configuration prior to reset:

Select affacted Pack OFF, comfirm on bleed page the flow control valve is closed. The Pack
controllers are powered and are operational

Circuit breakers to reset:

Steps to clear warning:

Open associated breakers for 2 seconds. If no help perform a CAB TEMP CTL test (300sec)
through CFDS.

Reset duration:

36 seconds.

Results of power up test or reset:

Pass: Ecam fault disappears.

Fail: Ecam fault remains.

Notes:

No notes at this time.

Sign off:

AMM21-63-00-710-004.

Applicable deferrals:

MEL21-63-01=Zone Controller System.

COND-TRIM AIR SYS FAULT

 Aircraft configuration prior to reset:

Select affacted Pack OFF, comfirm on bleed page the flow control valve is closed. The Pack
controllers are powered and are operational

Circuit breakers to reset:

Steps to clear warning:

Open associated breakers for 2 seconds. If no help perform a CAB TEMP CTL test (300sec)
through CFDS.

Reset duration:

36 seconds.

Results of power up test or reset:

Pass: Ecam fault disappears.

Fail: Ecam fault remains.

Notes:

No notes at this time.

Sign off:

AMM21-63-00-710-004.

Applicable deferrals:

MEL21-63-02=Cockpit/Cabin Trim Air Valves.

COND-AFT CARGO HEAT FAULT

 Aircraft configuration prior to reset:

No specfic.

Circuit breakers to reset:

ON PANEL 49 VU OPEN C/B C07 AFTER 5 SEC CLOSE THE C/B.

Steps to clear warning:

Open associated breakers for 5 seconds then close. If no help perform a ground report in CFDS.

Reset duration:

28 seconds.

Results of power up test or reset:

Pass: Ecam fault disappears.

Fail: Ecam fault remains.

Notes:

No notes at this time.

Sign off:

AMM21-28-00-710-006.

Applicable deferrals:

MEL21-43-02=Aft Cargo Heating System.

AIR FWD (AFT) CARGO VENT FAULT

 Aircraft configuration prior to reset:

COMPUTER ( CARGO VENTILATION CONTROLLER

Circuit breakers to reset:

ON PANEL 49VU : OPEN THE C/B C07 THEN CLOSE AFTER 5 SEC .
Reset duration

30 seconds.

Results of power up test or reset:

Pass: Ecam fault disappears.

Fail: Ecam fault remain
COND-RECIRC FAN FAULT

 Aircraft configuration prior to reset:

No specfic.

Circuit breakers to reset:

Steps to clear warning:

Open associated breakers for 2 seconds then close.

Reset duration:

28 seconds.

Results of power up test or reset:

Pass: Ecam fault disappears.

Fail: Ecam fault remains.

Notes:

No notes at this time.

Sign off:

AMM21-21-00-710-001.

Applicable deferrals:

MEL21-21-01=Cabin Fans.
LAV/GALLEY EXTRACT FAN FAULT

 Aircraft configuration prior to reset:

No specfic.

Circuit breakers to reset:

Steps to clear warning:

Open associated breakers for 2 seconds then close.

Reset duration:

28 seconds.

Results of power up test or reset:

Pass: Ecam fault disappears.

Fail: Ecam fault remains.

Notes:

No notes at this time.

Sign off:

AMM21-61-00-710-001.

Applicable deferrals:

MEL21-23-01=Lavatory And Galley Extract Fans.

VENT AVNCS SYS FAULT

COMPUTER (AEVC)
RESET : ON PANEL 49VU : OPEN THE C/B Y17.THEN CLOSE AFTER 5 SEC.

CHAPTER 21-CIRCUIT BREAKERS

|AIR COND/FLOW/CTL AND IND/2 | V21 | 122VU

|AIR COND/FLOW/MIXER/FLAP | V22 | 122VU

|AIR COND/RECIRC FAN/L/SPLY | X18 | 122VU

|AIR COND/RECIRC FAN/L/CTL | X20 | 122VU

|AIR COND/RECIRC FAN/R/SPLY | W18 | 122VU

|AIR COND/RECIRC FAN/R/CTL | W20 | 122VU

|AIR COND/PACK TEMP/CTL SYS1/1/115VAC | X22 | 122VU

|AIR COND/PACK TEMP CTL SYS2/1/115VAC | Y18 | 122VU

|AIR COND/PACK TEMP/CTL SYS1/1/28VDC | X21 | 122VU

|AIR COND/PACK TEMP CTL SYS2/1/28VDC | Y19 | 122VU

|AIR COND/PACK TEMP/CTL SYS1/2/115VAC | W22 | 122VU

|AIR COND/PACK TEMP CTL SYS2/2/115VAC | Y20 | 122VU

|AIR COND/PACK TEMP/CTL SYS1/2/28VDC | W21 | 122VU

|AIR COND/PACK TEMP CTL SYS2/2/28VDC | Y21 | 122VU

|AIR COND/ZONE TEMP CTL/115VAC/SYS1 | V17 | 122VU

|AIR COND/ZONE TEMP CTL/115VAC/SYS2 | V18 | 122VU

|AIR COND/ZONE TEMP CTL/28VDC/SYS1 | V19 | 122VU

|AIR COND/ZONE TEMP CTL/28VDC/SYS2 | V20 | 122VU

|AIR COND/CAB/PRESS/CTL1 | D09 | 49VU

|AIR COND/CAB PRESS/CTL/2 | Y22 | 122VU

|AIR COND/CAB PRESS/CTL/MAN | Y23 | 122VU

|AIR COND/AVNCS/VENT/MONG | Y17 | 122VU

|AIR COND/AVNCS VENT/CTL | D05 | 49VU

|AIR COND/AVNCS VENT/CTL | D06 | 49VU

|AIR COND/LAV/GALLEY VENT CTL/EXTRACT FAN/CTL | U21 | 122VU

|AIR COND/LAV/GALLEY VENT CTL/EXTRACT FAN/SPLY | U19 | 122VU

|AIR COND/RAM/AIR/INLET | D10 | 49VU

OFFSIDE RANGE MODE ON NAV DISPLAY

 Aircraft configuration prior to reset:

Turn off both flight directors. Both engines off.

Circuit breakers to reset:

Steps to clear warning:

Open associated breaker for 10 seconds, then reset. Do not reset again for at least two minutes.

Reset duration:

120 seconds.

Results of power up test or reset:

Pass: Message disappears.

Fail: Message remains, perform CFDS AFS test.

Notes:

(Please Wait), will be displayed on MCDU, do not touch MCDU for 120 seconds.

Sign off:

AMM22-91-00-710-001.(AFSGroundScan)
AMM22-96-00-710-001-A. (AFS Test)

Applicable deferrals:

MEL22-83-01=FMGC.

MCDU 1 (2) SCREEN BLANK

 Aircraft configuration prior to reset:

No specific.

Circuit breakers to reset:

Steps to clear warning:

Open associated breaker for 30 seconds, then reset.

Reset duration:

45 seconds.

Results of power up test or reset:

Pass: The page is displayed.

Fail: Screen remains blank.

Notes:

No notes at this time.

Sign off:

AMM22-70-00-710-001

Applicable deferrals:

MEL22-82-01=MCDU

AUTO FLT-RUDDER TRIM 1(2) FAULT

 Aircraft configuration prior to reset:

Both engines stopped and hydraulics off.

Circuit breakers to reset:

Steps to clear warning:

First, reset associated FAC pushbutton. If no help, open associated FAC breakers for 10 seconds,
then close.

Reset duration:

90 seconds.

Results of power up test or reset:

Pass: Fault messages disappear.

Fail: Message remains.

Notes:

After reset, energize hydraulics, varify no Yaw damper message display.

Sign off:

AMM22-91-00-710-001.(AFSGroundScan)
AMM22-96-00-710-001-A. (AFS Test)

Applicable deferrals:

MEL27-22-01=Rudder Trim Systems.

AUTO FLT-RUDDER TRIM SYSTEM FAULT

 Aircraft configuration prior to reset:

Both engines stopped and hydraulics off.

Circuit breakers to reset:

Steps to clear warning:

First, reset associated FAC pushbutton. If no help, open associated FAC breakers for 10 seconds,
then close.

Reset duration:

90 seconds.

Results of power up test or reset:

Pass: Fault messages disappear.

Fail: Message remains.

Notes:

After reset, energize hydraulics, varify no Yaw damper message display.

Sign off:

AMM22-91-00-710-001.(AFSGroundScan)
AMM22-96-00-710-001-A. (AFS Test)

Applicable deferrals:

MEL27-22-01=Rudder Trim Systems.

AUTO FLT-RUDDER TRAVEL LIMIT 1(2) FAULT

 Aircraft configuration prior to reset:

Both engines stopped and hydraulics off.

Circuit breakers to reset:

Steps to clear warning:

First, reset associated FAC pushbutton. If no help, open associated FAC breakers for 10 seconds,
then close.

Reset duration:

90 seconds.

Results of power up test or reset:

Pass: Fault messages disappear.

Fail: Message remains.

Notes:

After reset, energize hydraulics, varify no Yaw damper message display.

Sign off:

AMM22-91-00-710-001.(AFSGroundScan)
AMM22-96-00-710-001-A. (AFS Test)

Applicable deferrals:

MEL27-23-01=Rudder Travel Limiter System.

AUTO FLT-RUDDER TRAVEL LIMIT SYSTEM FAULT

 Aircraft configuration prior to reset:

Both engines stopped and hydraulics off.

Circuit breakers to reset:

Steps to clear warning:

First, reset associated FAC pushbutton. If no help, open associated FAC breakers for 10 seconds,
then close.

Reset duration:

90 seconds.

Results of power up test or reset:

Pass: Fault messages disappear.

Fail: Message remains.

Notes:

After reset, energize hydraulics, varify no Yaw damper message display.

Sign off:

AMM22-91-00-710-001.(AFSGroundScan)
AMM22-96-00-710-001-A. (AFS Test)

Applicable deferrals:

MEL27-23-01=Rudder Travel Limiter System.

AUTO FLT-YAW DAMPER 1(2) FAULT

 Aircraft configuration prior to reset:

Both engines stopped and hydraulics yallow and green sys pressurized.

Circuit breakers to reset:

FAC 1 ON PANEL 49 B02

FAC 2 ON PANEL 121 M19

Steps to clear warning:

First, reset associated FAC pushbutton. If no help, open associated FAC breakers for 10 seconds,
then close. If yaw damper is a class 2, then cycle FAC’s with hydraulics on.

Reset duration:

90 seconds.

Results of power up test or reset:

Pass: Fault messages disappear.

Fail: Message remains.

Notes:

After reset, energize hydraulics, varify no Yaw damper message display.

Sign off:

AMM22-91-00-710-001.(AFSGroundScan)
AMM22-96-00-710-001-A. (AFS Test)

Applicable deferrals:

MEL22-63-01=Yaw Dampers.
AUTO FLT-A/P OFF DISPLAYED ON GROUND

 Aircraft configuration prior to reset:

ECAM warning displayed and will not clear. Engines shut down.

Circuit breakers to reset:

None

Steps to clear warning:

Select AP1 pushbutton on FCU, the pushbutton will, illuminate. Push the red autopilot disconnect
button on one of the sidesticks.

Reset duration:

10 seconds.

Results of power up test or reset:

Pass: Message will clear and not recall.

Fail: Red AP OFF message will display.

Notes:

A/P pushbuttons must not be selected before starting engines. If selected, and engines are started,
the message is latched and will not clear. If this occurs after engine start, shut engines down then
complete steps above.

Sign off:

AMM22-91-00-710-001.(AFSGroundScan)
AMM22-96-00-710-001-A. (AFS Test)

Applicable deferrals:

MEL22-10-01=Autopilot Systems.

AUTO FLT-A/P 1(2) DISPLAYED IN INOP STATUS

 Aircraft configuration prior to reset:

Turn off both flight directors. Both engines off.

Circuit breakers to reset:

Steps to clear warning:

Open associated breaker for 10 seconds, then reset. Do not reset again for at least two minutes. If
reset fails, power down aircraft.

Reset duration:

120 seconds, triple click.

Results of power up test or reset:

Pass: Message disappears.

Fail: Message remains, perform CFDS AFS test.

Notes:

(Please Wait), will be displayed on MCDU, do not touch MCDU for 120 seconds.
Sign off:
AMM22-91-00-710-001.(AFSGroundScan)
AMM22-91-00-701-001. (AFS Test)

Applicable deferrals:

MEL22-83-01=FMGC.
MEL22-10-01=Autopilot.

AUTO FLT-A/THR OFF DISPLAYED ON GROUND

 Aircraft configuration prior to reset:

ECAM warning displayed and will not clear. Engines shut down.

Circuit breakers to reset:

None

Steps to clear warning:

Select A/THR pushbutton on FCU, the pushbutton will illuminate, then push the red instinctive
disconnect button on one of the thrust levers. If message is still displayed, cycle the FADEC switches
on the 50VU, if no help reset FCU’s then FMGC’s then try realigning ADIRU’s.

Reset duration:

10 seconds.

Results of power up test or reset:

Pass: Message will clear and not recall.

Fail: A/THR OFF message will display.

Notes:

A/THR pushbutton must not be selected before starting engines. The message is latched and will
not clear using the CLR key on the ECAM control panel. If this occurs after engines start,the message
will be reset(cleared) upon takeoff power selection. (Thanks Chute for the update)

Sign off:

AMM22-91-00-710-001.(AFSGroundScan)
AMM22-96-00-710-001-A. (AFS Test)

Applicable deferrals:

MEL22-30-01=Autothrust Function.

OPPOSITE FM IN PROCESS DISPLAYED ON MCDU

 Aircraft configuration prior to reset:

Turn off both flight directors. Both engines off.

Circuit breakers to reset:

Steps to clear warning:

Open associated breaker for 10 seconds, then reset. Do not reset again for at least two minutes.

Reset duration:

120 seconds.

Results of power up test or reset:

Pass: Message disappears.

Fail: Message remains.

Notes:

(Please Wait), will be displayed on MCDU, do not touch MCDU for 120 seconds.

Sign off:

AMM22-91-00-710-001.(AFSGroundScan)
AMM22-96-00-710-001-A. (AFS Test)

Applicable deferrals:

MEL22-83-01=FMGC.

AUTO FLT-FCU 1(2) FAULT

 Aircraft configuration prior to reset:

None specific.

Circuit breakers to reset:

Steps to clear warning:

Open associated breaker for 7 minutes, then reset.

Reset duration:

10 seconds.

Results of power up test or reset:

Pass: Message disappears.

Fail: Message remains.

Notes:

(Please Wait), will be displayed on MCDU, do not touch MCDU for 120 seconds.

Sign off:

AMM22-91-00-710-001.(AFSGroundScan)
AMM22-96-00-710-001-A. (AFS Test)

Applicable deferrals:

MEL22-81-01=FCU

WINDSHEAR FAULT

 Aircraft configuration prior to reset:

Aircraft stopped, flaps up.

COMPUTER TO BE RESET :

FAC1+FAC2

C/BS TO BE RESET:

OPEN THEN CLOSE THIS C/BS

ON PANEL 49 B04 B03

ON PANEL 121 M19 M18

Steps to clear warning:

Select FAC #1&2 pushbutton off, pull FAC #1 &2 breaker for 30 seconds, then reset breaker and
FAC #1 &2 pushbutton.

Reset duration:

90 seconds.

Results of power up test or reset:

Pass: Message disappears.

Fail: Message remains.

Notes:

No notes at this time.

Sign off:

AMM22-60-00-710-004(CFDS/AFS/WindShear)
AMM34-41-00-740-002 (Bite Test Weather Radar)

Applicable deferrals:

MEL22-66-03-Windshear Detection.
BARO REF FAULT DISPLAYED

 Aircraft configuration prior to reset:

Both flight directors off.

Circuit breakers to reset:

Steps to clear warning:

Open FAC #1 breaker for 10 seconds, then reset.

Reset duration:

10 seconds.

Results of power up test or reset:

Pass: Message disappears.

Fail: Message remains.

Notes:

No notes at this time.

Sign off:

AMM22-91-00-710-001.(AFSGroundScan)
AMM22-96-00-710-001-A. (AFS Test)

Applicable deferrals:

MEL22-81-01=FCU.

RUDDER ARTIFICIAL FEEL INOP

 Aircraft configuration prior to reset:

None specific.

Circuit breakers to reset:

Steps to clear warning:

Open rudder artificial feel breaker for 10 seconds, then reset.

Reset duration:

10 seconds.

Results of power up test or reset:

Pass: Message disappears.

Fail: Message remains.

Notes:

No notes at this time.

Sign off:

AMM22-61-00-710-001

Applicable deferrals:

MEL27-23-01=Rudder Travel Limit

SIDE STICK LOCK

 Aircraft configuration prior to reset:

None specific.

Circuit breakers to reset:

Steps to clear warning:

Open side stick lock breaker for 10 seconds, then reset.

Reset duration:

10 seconds.

Results of power up test or reset:

Pass: Message disappears.

Fail: Message remains.

Notes:

No notes at this time.

Sign off:

AMM27-96-00-710-003 (Priority Test).

Applicable deferrals:

MEL=None.

FMGC MALFUNCTION

COMPUTER:

FMGC

C/BS TO BE RESET

ON PANEL 121VU OR 49VU : OPEN THE FMGC 1 C/B B02 ON 49VU ,AND CLOSE AFTER 10 SEC
.IF THERE IS NO RESET OF FMGC 1 , DO RESET OF FMGC 2 ON PANEL 121VU OPEN C/B M17
,AND CLOSE AFTER 10 SEC .

CHAPTER 22‐CIRCUIT BREAKER LOCATION
|Designation|Location|Panel|

|AUTO FLT/FCU/1 | B05 | 49VU

|AUTO FLT/FCU/2 | M21 | 121VU

|AUTO FLT/FMGC/1 | B02 | 49VU

|AUTO FLT/FMGC/2 | M17 | 121VU

|AUTO FLT/MCDU/1 | B01 | 49VU

|AUTO FLT/MCDU/2 | N20 | 121VU

|AUTO FLT/STICK/LOCK | N16 | 121VU

|AUTO FLT/RUDDER/ARTF/FEEL | N17 | 121VU

|AUTO FLT/FAC1/28VDC | B04 | 49VU

|AUTO FLT/FAC2/28VDC | M19 | 121VU

|AUTO FLT/FAC1/26VAC | B03 | 49VU

|AUTO FLT/FAC2/26VAC | M18 | 121VU

|AUTO FLT/RUDDER/TRIM/IND | M20 | 121VU
COM-VHF 1(2)(3) EMITTING

 Aircraft configuration prior to reset:

None specfic.

Circuit breakers to reset:

Steps to clear warning:

First, check the transmission key on audio panel, then the side stick radio select button, and then
the hand held mic for a stuck button. If no help, open associated breaker for 2 seconds, then close.

Reset duration:

10 seconds.

Results of power up test or reset:

Pass: Message disappears.

Fail: Message remains.

Notes:

No notes at this time.

Sign off:

AMM23-12-00-710-001.

Applicable deferrals:

MEL23-12-01=VHF Communications Systems.

COM-VHF TRANSMISSION PROBLEMS

 Aircraft configuration prior to reset:

None specfic.

Circuit breakers to reset:

Steps to clear warning:

Open associated circuit breaker for 2 seconds, then close.

Reset duration:

10 seconds.

Results of power up test or reset:

Pass: Message disappears.

Fail: Message remains.

Notes:

No notes at this time.

Sign off:

AMM23-12-00-710-001.

Applicable deferrals:

MEL23-12-01=VHF Communications Systems.

RMP LOCKED UP OR WINDOW BLANK

 Aircraft configuration prior to reset:

None specfic.

Circuit breakers to reset:

Steps to clear warning:

Turn off all RMP’s then on to reset. If no help, open all above circuit breakers for 2 seconds, then
close.

Reset duration:

2 seconds.

Results of power up test or reset:

Pass: RMP functions normally.

Fail: Still locked up.

Notes:

RMP lock up could be caused by another RMP that otherwise functions normally. Thats why all
three must be reset.

Sign off:

AMM23-13-00-710-001.

Applicable deferrals:

MEL23-13-01=Radio Management Panel (RMP).

ACP INOP

 Aircraft configuration prior to reset:

None specfic.

Circuit breakers to reset:

Steps to clear warning:

Turn “OFF” all RMP’s then turn “ON” to reset. If no help, reset associated ACP breakers.

Reset duration:

120 seconds.

Results of power up test or reset:

Pass: ACP functions normally.

Fail: Still will not change.

Notes:

No notes at this time.

Sign off:

AMM23-51-00-740-002.

Applicable deferrals:

MEL23-51-02=Audio Control Panel Systems (ACP).

AMU (AUDIO MANAGEMENT UNIT) FAULT

 Aircraft configuration prior to reset:

None specfic.

Circuit breakers to reset:

Steps to clear warning:

Open associated breaker for 2 seconds, then close. If no help reset C/B's M-02, M-03, M-04.

Reset duration:

10 seconds.

Results of power up test or reset:

Pass: AMU functions normally.

Fail: Still inop.

Notes:

No notes at this time.

Sign off:

AMM23-51-00-740-002.

Applicable deferrals:

MEL23-51-01=Audio Management Unit (AMU).

ACARS TRANSMISSION PROBLEMS

 Aircraft configuration prior to reset:

None specfic.

Circuit breakers to reset:

Steps to clear warning:

Open associated breaker for 5 seconds, then close.

Reset duration:

180 seconds.

Results of power up test or reset:

Pass: ACARS standby memo disappears and weather uplink is succesful.

Fail: Still inop.

Notes:

If NO COMM is reported durning flight, yet ACARS operates ok on ground, suspect failure of VHF3
transmissions on some frequencies.

Sign off:

AMM23-24-00-710-001.
AMM46-24-00-710-001.

Applicable deferrals:

MEL23-24-01=ACARS.
COM-HF 1 (2) INOP

 Aircraft configuration prior to reset:

None specfic.

Circuit breakers to reset:

Steps to clear warning:

Open associated breaker for 5 seconds, then close.

Reset duration:

10 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

No notes at this time.

Sign off:

AMM23-11-00-740-001.

Applicable deferrals:

MEL23-11-01=HF Communication System.

CIDS SYSTEM FAULTS

 Aircraft configuration prior to reset:

Aircraft on ground, both engines stopped, all cabin doors closed.

Circuit breakers to reset:

Steps to clear warning:

First, try reset at PTP. If no help open all breakers for 10 seconds, then close.

Reset duration:

120 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

Cabin lights will flash durning test. Test pass will be displayed on the PTP upon successful power
up.

Sign off:

AMM23-73-00-740-005.

Applicable deferrals:

MEL23-73-01=CIDS Director.

FORWARD ATTENDANT PANEL (FAP) LOCKED UP

 Aircraft configuration prior to reset:

No specific.

Circuit breakers to reset:

COM/CIDS/FLT ATTND PNL/ESS 94VU HO1

COM/FAP1/NORM 121VU Q14

Steps to clear warning:

Open circuit breaker for 10 seconds, then close in this order q14 , h01 .if unsuccessful: on panel
2000VU open the tape reproducer /PRAM C/B 2RX ,after 10 sec close the C/B.

Reset duration:

10 seconds.

Results of power up test or reset:

Pass: Panel not lock up.

Fail: Fault remains.

Notes:

Cabin lights will flash durning test. Test pass will be displayed on the PTP upon successful power
up.

Sign off:

AMM23-73-00-740-005.

Applicable deferrals:

MEL23-73-04=FAP(OLD).
MEL23-73-08=FAP(NEW).
FWD FLIGHT ATTENDANT PTP PANEL INOP

 Aircraft configuration prior to reset:

No specific.

Circuit breakers to reset:

Steps to clear warning:

Open circuit breaker for 5 seconds, then close.

Reset duration:

5 seconds.

Results of power up test or reset:

Pass: Panel powers up.

Fail: Panel inop.

Notes:

PTP = Programmed and Test Panel.

Sign off:

AMM23-73-00-740-005.

Applicable deferrals:

MEL23-73-07=FTP.

FLIGHT INTERPHONE INOP

 Aircraft configuration prior to reset:

No specific.

Circuit breakers to reset:

Steps to clear warning:

Open circuit breaker for 2 seconds, then close. If no help reset breaker for DEU”B”-M7.

Reset duration:

10 seconds.

Results of power up test or reset:

Pass: Flight interphone works.

Fail: Still inop.

Notes:

DEU-A controls lights, call signs and speakers. DEU-B controls interphone, P/A, call, and EVAC.

Sign off:

AMM23-73-00-740-005.

Applicable deferrals:

MEL23-43-02=Crewmember Interphone System.

PASSENGER ADDRESS SYSTEM INOP

 Aircraft configuration prior to reset:

Aircraft on ground

Circuit breakers to reset:

Steps to clear warning:

First try reseting CIDS director at PTP. If no help, open circuit breakers for 10 seconds, then reset.

Reset duration:

180 seconds.

Results of power up test or reset:

Pass: Passenger address system works.

Fail: Passenger address system still inop.

Notes:

DEU-A controls lights, call signs and speakers. DEU-B controls interphone, P/A, call, and EVAC.

Sign off:

AMM23-73-00-740-005.

Applicable deferrals:

MEL23-31-01=Passenger Adress Systems Inop.

DEU-A FAULT ON CIDS

 Aircraft configuration prior to reset:

Aircraft on ground

Circuit breakers to reset:

Steps to clear warning:

First try reseting CIDS director at PTP. If no help, open circuit breakers for 10 seconds, then reset.

Reset duration:

180 seconds.

Results of power up test or reset:

Pass: Fault clears from cids

Fail: Fault remains.

Notes:

DEU-A controls lights, call signs and speakers. DEU-B controls interphone, P/A, call, and EVAC.

Sign off:

AMM23-73-00-740-005.

Applicable deferrals:

MEL23-73-02=CIDS (Decoder Encoder Unit) DEU-A.

DEU-B FAULT ON CIDS

 Aircraft configuration prior to reset:

Aircraft on ground

Circuit breakers to reset:

Steps to clear warning:

First try reseting CIDS director at PTP. If no help, open circuit breakers for 10 seconds, then reset.

Reset duration:

180 seconds.

Results of power up test or reset:

Pass: Fault clears from cids

Fail: Fault remains.

Notes:

DEU-A controls lights, call signs and speakers. DEU-B controls interphone, P/A, call, and EVAC.

Sign off:

AMM23-73-00-740-005.

Applicable deferrals:

MEL23-73-03A=CIDS (Decoder Encoder Unit) DEU-B.

UNCOMMANDED EVAC HORN ACTUATION

COMPUTER :::CIDs

Procedure to reset:
Press the EVAC/HORN shut off S/W .

If unsuccessful ::open the C/BS on this order ::

COM/CIDS/DIRESS/1 49VU G01

COM/CIDS/DIR ESS/2 49VU G02

COM/NAV/CIDS/DIR NORM/1 121VU M05

COM/NAV/CIDS/DIR NORM/2 121VU M06

After 10 sec close the C/BS on order ::M06,,G02,,,M05,,&,,G01

‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐

CHAPTER 23‐CIRCUIT BREAKER LOCATION
|Designation|Location|Panel|

|COM/VHF/1 | G09 | 49VU

|COM NAV/VHF/2 | L04 | 121VU

|COM/RMP/1 | G10 | 49VU

|COM NAV/RMP/2 | L02 | 121VU

|COM/CIDS/DIR 1 AND 2/ESS | G02 | 49VU

|COM NAV/CIDS/DIR 1 AND 2/NORM | M05 | 121VU

|COM/CIDS/DEU B/ESS | G03 | 49VU

|COM/CIDS/DEU A ESS/LINE 1 | G04 | 49VU
|COM/CIDS/DEU A ESS/LINE 2 | G05 | 49VU

|COM NAV/CIDS/PROG AND TST PNL | M06 | 121VU

|COM NAV/CIDS/DEU B/NORM | M07 | 121VU

|COM NAV/CIDS/DEU A NORM/L FWD | M08 | 121VU

|COM NAV/CIDS/DEU A NORM/R FWD | M09 | 121VU

|COM NAV/CIDS/DEU A NORM/L MID | M10 | 121VU

|COM NAV/CIDS/DEU A NORM/R MID | M11 | 121VU

|COM NAV/CIDS/DEU A NORM/L AFT | M12 | 121VU

|COM NAV/CIDS/DEU A NORM/R AFT | M13 | 121VU

|COM NAV/CIDS/FWD ATTND/PNL | M14 | 121VU

170RH |COM NAV/CIDS/FWD ATTND/PNL | Q14 | 121VU

|COM/CVR/SPLY | E14 | 49VU

|COM/CVR/CTL | E13 | 49VU

|COM/AUDIO/ACP/CAPT | G06 | 49VU

|COM/AUDIO/ACP/F/O | G07 | 49VU

|COM NAV/ACP/THIRD/OCCPNT | M02 | 121VU

|COM NAV/ACP/AVNCS/COMPT | M03 | 121VU

|COM NAV/SELCAL | M04 | 121VU

|COM/AUDIO/FLT/INTPH | G08 | 49VU

|CABIN COMMUNICATION SYSTEM‐PRAM | F07 |2000VU

|EIS/HORN/SPLY | P09 | 121VU

|AUDIO MIXING | K03 | 121VU
ENGINE GENERATORS PARAMETERS NOT SHOWN

 Aircraft configuration prior to reset:

Aircraft on ground, Engines shut down.

Circuit breakers to reset:

Steps to clear warning:

Open associated circuit breakers for 1 second, then close.

Reset duration:

1 seconds.

Results of power up test or reset:

Pass: Engine parameters return to nomral.

Fail: Fault remains.

Notes:

Associated GCU or EGIU is at fault, There is a reset button on each GCU (Nose E&E).

Sign off:

TSM24-22-00-810-805(#1engineparametercheck).
TSM24-22-00-810-807 (#2 engine parameter check).

Applicable deferrals:

MEL24-20-01=Engine Driven Generator.

ELEC-CIRCUIT BREAKER TRIPPED

 Aircraft configuration prior to reset:

No specific.

Circuit breakers to reset:

Tripped breaker.

Steps to clear warning:

Reset tripped circuit breaker only once, If unsuccessful, do not make second attempt, troubleshoot
and fix problem.

Reset duration:

N/A.

Results of power up test or reset:

Pass: Message clears, associated system operates.

Fail: Fault remains.

Notes:

If no tripped breakers can be located, a green circuit breaker in the identified panel has failed.
Remember, green breakers do exist in relay panels 105VU and 106VU located in the E&E bay.

Sign off:

US AMM CHAPTER20-24-20.

Applicable deferrals:

MEL ?

TRANSFORMER RECTIFIER PROBLEMS

 Aircraft configuration prior to reset:

Aircraft on ground.

Circuit breakers to reset:

Steps to clear warning:

First, reset T/R’s through MCDU or all three using guarded button on 103VU panel in E&E bay. If
unsuccessful, reset associated breaker.

Reset duration:

1 seconds.

Results of power up test or reset:

Pass: T/R operated correctly.

Fail: Fault remains.

Notes:

If ESS TR3 is in operation with TR1 & TR2 sericable, release the AC ESS FEED pushbutton on the
35VU, than push the AC ESS FEED pushbutton. ESS TR3 will return to standby.

Sign off:

TSM24-30-00-810-801(#1TRtest).
TSM24-30-00-810-802(#2TRtest).
Applicable deferrals:
MEL24-30-01=Transformer/Rectifier Units (TR).

ELEC-BCL 1(2) FAULT

 Aircraft configuration prior to reset:

Aircraft on ground.

Circuit breakers to reset:

Steps to clear warning:

Reset using associated battery pushbutton in overhead. If no help, open associated breakers for 1
second, then close.

Reset duration:

10 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

All curcuit breakers are located on the 105VU in the E&E panel.

Sign off:

AMM24-38-00-710-001.

Applicable deferrals:

No MEL

GROUND POWER WON’T CONNECT, NO AVAIL LIGHT IN PUSHBUTTON

 Aircraft configuration prior to reset:

Aircraft on ground, engines stopped, APU stopped, ground power connected.

Circuit breakers to reset:

Steps to clear warning:

Open breaker , then close.

Reset duration:

1 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

No notes at this time.

Sign off:

AMM24-41-00-740-002.

Applicable deferrals:

MEL24-41-01=ExternalPowerControl
MEL24-41-02=”Notinuse”or“AVIL”lightinop
MEL24-41-03=EXT PWR PB Switch
GPU CAN NOT CONNECTED TO AIR CRAFT WITH ONE POWER SOURCE IS CONNECTED

COMPUTER : GAPCU

On ELEC control panel 35vu :

PUSH AND RELEASE THE EXT PWR PUSH-BUTON S/W TWICE WITH GPU
DISCONNECT .

If no power source is connected to electrical network of the aircraft, push the BAT 1& BAT2
PUSHBUTTON S/Ws (the OFF legend goes off).

CHAPTER 24‐CIRCUIT BREAKER LOCATION
|Designation|Location|Panel|

|COM/VHF/1 | G09 | 49VU

|ELEC/GALLEY/CNTOR | S28 | 122VU

|ELEC/HOT BUS/701PP SPLY | D01 | 105VU

|ELEC/HOT BUS/702PP SPLY | D02 | 105VU

|ELEC/BAT BUS/REF/BCL1 | G01 | 105VU

|ELEC/BAT BUS/REF/BCL2 | J02 | 105VU

|ELEC/BAT REF/BCL1 | F01 | 105VU

|ELEC/BAT REF/BCL2 | F02 | 105VU

|ELEC/HOT BUS/701PP SPLY | E01 | 105VU

|ELEC/HOT BUS/702PP SPLY | E02 | 105VU
|ELEC/CNTOR/ESS/DC BUS/TIE | W26 | 122VU

|ELEC/TR1/FAULT/DC BUS TIE/CONFIG | W29 | 122VU

|ELEC/TR2/FAULT/DC BUS TIE/CONFIG | W30 | 122VU

|ELEC/CNTOR/DC/BUS/TIE1 | W25 | 122VU

|ELEC/CNTOR/DC BUS/TIE 1/FAULT | U24 | 122VU

|AC ESS/BUS/EMER/CNTOR/SPLY | C08 | 106VU

|ELEC/DC BUS/TIE2//APU/START | W31 | 122VU

|ESS TR/SPLY | C01 | 106VU

|ESS TR/CNTOR/CTL | C02 | 106VU

|EMER/SHED/CNTOR/SPLY | C07 | 106VU

|ELEC/DC/SVCE/BUS | X24 | 122VU

|ELEC/DC SHED BUS/CNTR | U26 | 122VU

|ELEC/REFLNG/ON/BAT | U28 | 122VU

|ELEC/REFLNG/NORM | S27 | 122VU

|ELEC/RFL/SPLY/LOGIC | U29 | 122VU

|ELEC/TR1/MONG | X25 | 122VU

|ELEC/TR2/MONG | X26 | 122VU

|ELEC/DC SVCE/BUS/ON TR2 | U30 | 122VU

|ELEC/GALY & CAB/CTL | S26 | 122VU

|ELEC/GALY & CAB/GND/FLT/LOGIC | S24 | 122VU

|ELEC/GALY & CAB/FAULT/LT CTL | S25 | 122VU

|ELEC/STAT INV/BUS 901XP/SPLY | H02 | 105VU

|ELEC/STAT INV/CNTOR/CTL | G02 | 105VU

|AC ESS/BUS NORM/CNTOR/CTL | B03 | 106VU

|AC ESS BUS/STBY/CNTOR/CTL | B08 | 106VU
|AC ESS BUS/EMER/CNTOR/CTL | B07 | 106VU

|CSM/G /EV/MAN/SPLY | B04 | 106VU

|ELEC/CSM/G /EV AUTO/SPLY | C01 | 105VU

|ELEC/EMER GEN AUTO/2 | Z26 | 122VU

|AC ESS BUS/EMER/STBY/CNTOR/SPLY | C06 | 106VU

|ELEC/EMER GEN AUTO/1 | Z25 | 122VU

|ELEC/EXT PWR/LT CLT/AVAIL | X31 | 122VU

|ELEC/EXT PWR/LT CLT/NOT IN/USE | X30 | 122VU

|ELEC/GPCU | Y24 | 122VU

|ELEC/EXT PWR/CTL | X29 | 122VU

|ELEC/EXT PWR/COCKPIT/AVAIL/LT | X28 | 122VU

|ELEC/LT/CTL | H10 | 49VU

|AC/SHED/ESS BUS/CNTOR/CTL | C04 | 106VU

|AC ESS BUS/MONG/SPLY | C05 | 106VU

|26VAC/ESS BUS/SPLY | B06 | 106VU

|ELEC/AC BUS/8XP/MONG | H11 | 49VU

|ELEC/AC/BUS1/CTL | V25 | 122
CREW SEAT PROBLEMS

 Aircraft configuration prior to reset:

No specific.

Circuit breakers to reset:

Steps to clear warning:

Open associated circuit breakers for 1 second, then close.

Reset duration:

1 second.

Results of power up test or reset:

Pass: Seat operates correctly.

Fail: Fault remains.

Notes:

Additional circuit breaker is located under each seat on the control box.

Sign off:

AMM25-11-00-710-001.

Applicable deferrals:

MEL25-11-01=Pilot Seat Adjustment.

OVEN OR TIMER

 Aircraft configuration prior to reset:

No specific.

Circuit breakers to reset:

Steps to clear warning:

Open associated circuit breakers for 1 second, then close.

Reset duration:

1 seconds.

Results of power up test or reset:

Pass: Oven operates correctly.

Fail: Fault remains.

Notes:

No notes at this time.

Sign off:

AMM25-35-00-710-015.

Applicable deferrals:

NEF.

CHAPTER 25‐CIRCUIT BREAKER LOCATION
|Designation|Location|Panel|

|VACUUM CLEANER SOCKET CARGO Z0261 | F01 |2001VU

|COCKPIT SEATS/SEAT CTL/CAPT | U11 | 122VU

|COCKPIT SEATS/SEAT CTL/F/O | U14 | 122VU

|PILOTS OUTLETS/STAT INV | K25 | 121VU

|PILOTS OUTLETS/115V 60HZ | K23 | 121VU
SMOKE - LAVATORY DET FAULT

 Aircraft configuration prior to reset:

On ground.

Circuit breakers to reset:

Steps to clear warning:

Open both circuit breakers for 60 second, then close both at same time.

Reset duration:

80 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

Wait two minutes after reset before testing system.

Sign off:

AMM26-17-00-710-001.

Applicable deferrals:

MEL26-17-01=Lavatory Smoke Detection System.

SMOKE - FWD/AFT CARGO SMOKE DET

 Aircraft configuration prior to reset:

On ground.

Circuit breakers to reset:

Steps to clear warning:

Open both circuit breakers for 60 second, then close both at same time.

Reset duration:

80 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

Wait two minutes after reset before testing system.

Sign off:

AMM26-16-00-710-001.

Applicable deferrals:

MEL26-16-03=FWDCargoSmokeDet.
MEL26-16-04=AFT/Bulk Cargo Smoke Det.

SDCU TROUBLE SHOOT DATA (TSD) INFO

 Aircraft configuration prior to reset:

On ground.

Circuit breakers to reset:

No breakers

Steps to clear warning:

Do a read-out of the TROUBLE SHOOTING DATA from the CFDS.

The TSD shows the total number of smoke detectors installed on the smoke detection loop, e.g. xxxx
xxxx xxxx xxxx aa/bb (aa=bb shows all installed smoke detectors). The cabin layout specifies the
numberofsmokedetectors.

If the TSD gives the complementary information xxxx xxxx xxxx xxxx A/b
(b < A)

- replace the SD (b) counted counterclockwise from the SDCU Channel 2.

- If the fault continues: replace the SD(b+1) counted counterclockwise from SDCU Channel 2 until the
TSD gives the information xxxx xxxx xxxx xxxx A/B (A=B)

If the TSD gives the complementary information xxxx xxxx xxxx xxxx a/B
(a < B)
- replace the SD(a) counted clockwise from the SDCU Channel 1.

- If the fault continues: replace the SD(a+1) counted clockwise from SDCU Channel 1 until the TSD
gives the information xxxx xxxx xxxx xxxx A/B (A=B).

A319 & A320 Configuration

A321
Configuration

Notes:

If system will not test, than you can not apply MEL.

Applicable deferrals:

MEL26-17-02=Smoke Detection Control Unit (SDCU).

SMOKE - SDCU MAINT. MESSAGE (CLASS 2)

 Aircraft configuration prior to reset:

On ground.

Circuit breakers to reset:

Steps to clear warning:

Open both circuit breakers for 60 second, then close both at same time.

Reset duration:

80 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

Wait two minutes after reset before testing system.

Sign off:

AMM26-16-00-710-001.

Applicable deferrals:

MEL26-17-02=Smoke Detection Control Unit (SDCU).

COND/AIR-AFT CARGO HEAT/VENT FAULT

 Aircraft configuration prior to reset:

On ground.

Circuit breakers to reset:

Steps to clear warning:

Open both circuit breakers for 1 second, then close.

Reset duration:

28 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

During reset, cargo heat trim air valves cycles.

Sign off:

AMM21-28-00-710-006.

Applicable deferrals:

MEL21-28-04=AFTCargoExtractionFan.
MEL21-28-05=AFT Cargo Isolation Valves.

CHAPTER 26‐CIRCUIT BREAKER LOCATION
|Designation|Location|Panel|

|ENGINE/1/FIRE DET/LOOP A | A06 | 49VU

|ENGINE/ENG2/FIRE DET/LOOP A | Q39 | 121VU

|ENGINE/ENG1/FIRE DET/LOOP B | Q38 | 121VU

|ENGINE/2/FIRE DET/LOOP B | A07 | 49VU

|ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/A | Q43 | 121VU

|ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/A | Q41 | 121VU

|ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/B | Q44 | 121VU

|ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/B | Q42 | 121VU

|APU/FIRE/EXTIG/SQUIB/A | L38 | 121VU

|APU/FIRE/EXTIG/SQUIB/B | L39 | 121VU

|APU/FIRE/LP VALVE/STBY | M41 | 121VU

|APU/FIRE/LP VALVE/NORM | M42 | 121VU

|APU/AUTO/EXTIG/GND/TEST | L40 | 121VU

|APU/FIRE AND OVHT/DET/LOOP A | L43 | 121VU

|APU/FIRE AND OVHT/DET/LOOP B | L44 | 121VU

|AIR COND/SDCU/CHAN1 | C06 | 49VU

|AIR COND/SDCU/CHAN2 | T18 | 122VU

|AIR COND/CARGO/FIRE/EXTIG/BTL1 | C04 | 49VU

|AVIONIC SMOKE / AEVC | Y17 | 122VU

|AVIONIC SMOKE / AEVC | D6 | 49VU

|AVIONIC SMOKE / AEVC | D7 | 49VU
F/CTL-FCDC 1(2) FAULT

 Aircraft configuration prior to reset:

On ground, hydraulics depressurized.

Circuit breakers to reset:

Steps to clear warning:

Open circuit breakers for 5 second, then close.

Reset duration:

20 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

FCDC=Flght Control Data Concentrators.

Sign off:

AMM27-96-00-710-001.

Applicable deferrals:

MEL27-95-01=FCDC.

F/CTL-MAINENANCE STATUS (CLASS 2)

 Aircraft configuration prior to reset:

On ground, hydraulics depressurized, engines stopped, ADIRU’s aligned.

Circuit breakers to reset:

Steps to clear warning:

Open circuit breakers for 5 second, then close.

Reset duration:

20 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

If time, run a ground scan in CFDS/FCTL/EFCS #1 to identify cause of message.

Sign off:

AMM27-96-00-710-001.

Applicable deferrals:

MEL27-00=Class 2 Maintenance Message.

THS DIDN’T RETURN TO ZERO AFTER LANDING

 Aircraft configuration prior to reset:

On ground.

Circuit breakers to reset:

None

Steps to clear warning:

Reset ELAC’s using overhead pushbutton switches. Select both ELAC switches off, then on. THS
will return to zero.

Reset duration:

8 seconds.

Results of power up test or reset:

Pass: THS zeros.

Fail: THS stays.

Notes:

THS=Trimmable Horizontal Stabilizer.

Sign off:

AMM27-93-00-810-945.

Applicable deferrals:

MEL27-44-01=Stabilizer Actuator Electric Motors.

F/CTL-SEC 1(2)(3)FAULT OR SPLR FAULT

 Aircraft configuration prior to reset:

Aircraft on ground. Hydraulics depressurized.

Circuit breakers to reset:

Steps to clear warning:

First, reset applicable SEC pushbutton. If no help, open associated breaker for 5 seconds, then
reset. The pushbutton to remain in "ON" postion during breaker reset.

Reset duration:

20 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

 If Hydraulics are pressurized, pushbutton reset will not be successful.

 SEC #1 controls spoilers 3 & 4.
 SEC#2 controls spoilers 5.
 SEC#3controlsspoilers1&2.
Sign off:
AMM27-94-00-710-001(SEC#3).
AMM27-94-00-710-002(SEC#1).
AMM27-94-00-710-003(SEC#2).
Applicable deferrals:
MEL27-92-01=SEC’s.
MEL27-92-02=GND Spoilers.
F/CTL-ELAC 1(2) FAULT.
F/CTL ALTN LAW FAULT.

 Aircraft configuration prior to reset:

Aircraft on ground.

Circuit breakers to reset:

Steps to clear warning:

First, reset applicable ELAC pushbutton WITH HYD SYS DEPRESSURIZED. If no
help, open associated breaker for 5 seconds. Pushbutton to remain in “ON” position
during breaker reset.

Reset duration:

20 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

 ELAC #1 controls left outboard (Blue) and right inboard (Green) aileron servos.
 ELAC #2 controls Left inboard (Green) and right outboard (Blue) ailerons servos.
 ELAC #1 is primary in roll,
 ELAC #2 is primary in pitch.
 ELAC #1 controls outboard (Blue) elevator servos.
 ELAC #2 controls inboard left (Green) & inboard right (Yellow) elevator servos.
Sign off:
AMM27-93-00-710-001.
Applicable deferrals:
MEL27-93-01=ELEC.

F/CTL-AILERON SERVO FAULT

 Aircraft configuration prior to reset:

Aircraft on ground.

Circuit breakers to reset:

Steps to clear warning:

First, reset applicable ELAC pushbutton. If no help, open associated breaker for 5 seconds.
Pushbutton to remain in “ON” position during breaker reset.

Reset duration:

20 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

If fault is isolated to a servo, change the servo valve first prior to changing the complete servo
control.

Sign off:

AMM27-93-00-710-001.
Applicable deferrals:
MEL27-14-01=AileronServoControls.
MEL27-14-02=Aileron indications on ECAM inop.

F/CTL-ALTN LAW DISPLAY AT ENGINE START

 Aircraft configuration prior to reset:

On ground, with engines running, wheels chocked.

Circuit breakers to reset:

None

Steps to clear warning:

 With engines running,

 set parking brake,
 use overhead pushbuttons to switch “OFF” engine hydraulics,
 when hydraulics are depressurized, select “OFF” ELAC #1 and #2 using overhead swich.
 After 3 seconds, switch ELAC #1 and ELAC #2 “ON”.
 After approx 15 seconds, select hydraulics back “ON”.

Reset duration:

30 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

Follow reset steps closely.

Sign off:

AMM27-93-00-710-001.

Applicable deferrals:

No MEL.

F/CTL-FLAP/SLAT 1 (2) FAULTS OR SLOW OPERATION

 Aircraft configuration prior to reset:

On ground, hydraulics depressurized, engines stopped.

Circuit breakers to reset:

Steps to clear warning:

Open associated breakers for 5 seconds, then close.Only reset one breaker at time, reseting both
system breakers could lock out WTB.

Reset duration:

60 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

Slats slow or flaps slow message will display only durning operation. Remember running slats/flaps
without all hydraulics on can cause these faults to display. Slats use Blue & Green hydraulics. Flaps
use Yellow & Green hydraulics.

Sign off:

AMM27-51-00-740-002.
Applicable deferrals:
MEL27-51-01=Slat/Flap Control System (SFCS).

F/CTL-FLAPS(SLATS) LOCKED

 Aircraft configuration prior to reset:

On ground, hydraulics depressurized.

Circuit breakers to reset:

None

Steps to clear warning:

Reset wing tip brakes though MCDU/CFDS/SFCC/TEST/RESET.

Reset duration:

30 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

After reset of wing tip brakes, fault message clears.

Sign off:
AMM27-51-00-710-002.
Applicable deferrals:
MEL27-51-02=Flap Wing Tip Brake Solenoids.

F/CTL-FLAP/SLAT INDICATION AMBER

 Aircraft configuration prior to reset:

On ground, hydraulics depressurized.

Circuit breakers to reset:

Steps to clear warning:

Open circuit breakers for 5 second, then close.

Reset duration:

20 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

If ECAM upper flap/slat indications are amber, reset system #1. If not reset system #2.

Sign off:

AMM27-93-00-710-001
Sign off:
AMM27-51-00-740-002.
Applicable deferrals:
MEL27-51-01=SFCS.

SIDE STICK PRIORTY MESSAGE

 Aircraft configuration prior to reset:

Aircraft on ground.

Circuit breakers to reset:

Steps to clear warning:

First, reset all FAC/SEC/ELAC overhead pushbuttons. If no help, reset ELAC circuit breakers
followed by performing a side stick priorty test.

Reset duration:

20 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

Check PFR for associated messages. If you have any associated faults T/S IAW TSM.

Sign off:

AMM27-96-00-710-003 (Priority Test).

Applicable deferrals:

MEL27-92-06=Side Stick Dual Input Warning System.

CHAPTER 27‐CIRCUIT BREAKER LOCATION
|Designation|Location|Panel|

|FLIGHT CONTROLS/ELAC1/NORM/SPLY | B11 | 49VU

|FLIGHT CONTROLS/ELAC2/NORM/SPLY | R20 | 121VU

|FLT CTL/ELAC1/STBY SPLY | A01 | 105VU

|FLIGHT CONTROLS/ELAC2/STBY SPLY | A02 | 105VU

|FLIGHT CONTROLS/THS ACTR/MOT1 | Q16 | 121VU

|FLIGHT CONTROLS/THS/ACTR/MOT2 | B09 | 49VU

|FLIGHT CONTROLS/THS ACTR/MOT3 | Q17 | 121VU

|FLIGHT CONTROLS/FCDC1/SPLY | B10 | 49VU

|FLIGHT CONTROLS/FCDC2/SPLY | Q20 | 121VU

|FLIGHT CONTROLS/SEC1/NORM/SPLY | B08 | 49VU

|FLIGHT CONTROLS/SEC2/SPLY | Q18 | 121VU

|FLIGHT CONTROLS/SEC3/SPLY | Q19 | 121VU

|FLT CTL/SEC1/STBY SPLY | B01 | 105VU

|FLIGHT CONTROLS/SLT FLP/POS/IND 1 | B12 | 49VU

|FLIGHT CONTROLS/SLT FLP/POS/IND2 | P16 | 121VU

|FLIGHT CONTROLS/SLT/CTL AND MONG/SYS1 | B06 | 49VU

|FLIGHT CONTROLS/FLP/CTL AND MONG/SYS1 | B07 | 49VU

|FLIGHT CONTROLS/SLT/CTL/SYS2 | R21 | 121VU

|FLIGHT CONTROLS/FLP/CTL AND/MONG/SYS2 | Q21 | 121VU

|FLIGHT CONTROLS/WTB/SLT/SYS1 | S06 | 122VU

|FLIGHT CONTROLS/WTB/FLP/SYS1 | S07 | 122VU

|FLIGHT CONTROLS/WTB/SLT/SYS2 | P19 | 121VU

|FLIGHT CONTROLS/WTB/FLP/SYS2 | P20 | 121VU
FUEL-FQI 1(2) FAULT

 Aircraft configuration prior to reset:

Aircraft on ground.

Circuit breakers to reset:

Steps to clear warning:

Open associated breakers for 5 seconds, then close. During reset the intercell transfer valves
cycle.

Reset duration:

80 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

Each reset causes fuel to move form the outer cells to the inner cells. Too many resets can cause
fuel configuration problems.

Sign off:

AMM28-42-00-710-001.

Applicable deferrals:

MEL28-40-02=Fuel Quantity Indicating Computer.

FUEL-AUTOFEED FAULT

 Aircraft configuration prior to reset:

Center tank greater then 550lbs with wing tanks below 11,000.

Circuit breakers to reset:

None

Steps to clear warning:

The fault is indicated if either wing tank quantity becomes less than 11,023lbs when center tank is
above 550lbs. When fuel is reconfigured, fault will clear.

Reset duration:

N/A.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

Fuelburnsequence:

1st) Center tanks (greater pump output pressure).

2nd) Inner wing tanks

3rd) At approx 1700lbs in either inner tank, all 4 transfer valves open and outer wing tank fuel flows to
the inner tanks for consumption.

Sign off:

AMM28-42-00-710-001

Applicable deferrals:

MEL28-20-01=Automatic Fuel Feed System.

CENTER TANK LOW PRESSURE WARNING

 Aircraft configuration prior to reset:

Less than 400 pounds of fuel in the center tank.

Circuit breakers to reset:

None

Steps to clear warning:

With less then 400lbs in center tank, select the mode switch to Auto. The center pumps should not
run with low center tank fuel.

Reset duration:

N/A.

Results of power up test or reset:

Pass: Center tank pumps shows “cross line green”

Fail: Pumps run in AUTO and no fuel in center tank.

Notes:

This could be a spurious fault with less than 400LBS in center tank, check previous PFR for
history.

Sign off:
AMM28-21-00-720-001
Applicable deferrals:
MEL28-21-02=Center Tank System.

INTERCELL TRANSFER VALVES OPEN

 Aircraft configuration prior to reset:

On ground, refueling, with inner tanks greater than 1700lbs.

Circuit breakers to reset:

Steps to clear warning:

The Intercell transfer valves normally close when the refuel door opens. If valves fail to close
properly, cycle associated circuit breakers.

Reset duration:

10 seconds.

Results of power up test or reset:

Pass: Valves close properly when refuel door opens.

Fail: Valves remain open.

Notes:

Nuisance, caused by fuel movement in tanks due to aircraft attitude changes.

Sign off:

AMM28-46-00-740-001.

Applicable deferrals:

MEL28-15-01=Intercell Transfer Valves.

APU FUEL LP VALVE FAULT MESSAGE

 Aircraft configuration prior to reset:

Fuel APU LP valve fault message triggered when the APU master switch is selected off durning
autoshut down.

Circuit breakers to reset:

Steps to clear warning:

First, cycle the APU master switch "ON" then "OFF". If no help cycle the associated circuit
breakers.

Reset duration:

10 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

No notes at this time.

Sign off:

AMM28-29-00-710-001
Applicable deferrals:
MEL49-70-01=APU INOP.

CHAPTER 28‐CIRCUIT BREAKER LOCATION
|Designation|Location|Panel|

|FUEL/L WING TK/PUMP1 SPLY | N23 | 121VU

|FUEL/R WING TK/PUMP1 SPLY | Q23 | 121VU

|FUEL/PUMPS/1/L CTL AND R IND | R23 | 121VU

|FUEL/PUMPS/1/R CTL AND L IND | R28 | 121VU

|FUEL/L WING TK/PUMP2 SPLY | N26 | 121VU

|FUEL/R WING TK/PUMP2 SPLY | Q26 | 121VU

|FUEL/PUMPS/2/L CTL AND R IND | R24 | 121VU

|FUEL/PUMPS/2/R CTL AND L IND | R29 | 121VU

|FUEL/CTR TK/PUMP1 SPLY | P23 | 121VU

|FUEL/CTR TK/PUMP2 SPLY | P26 | 121VU

|FUEL/CTR TK/PUMPS1 AND 2/CTL AND IND | R25 | 121VU

|FUEL/CTR TK/PUMPS1 AND 2/CTL AND IND | R26 | 121VU

|FUEL/CTR TK/AUTO/CTL | R27 | 121VU

|FUEL/SMOKE/CONFIG/PUMP CTL | A14 | 49VU

|APU/FUEL/BLOW OFF/CTL | K39 | 121VU

|APU/FUEL/BLOW OFF/PUMP | B14 | 49VU

|APU/FUEL/PUMP/CTL | M38 | 121VU

|FUEL/X FEED/VALVE/MOT2 | M24 | 121VU

|FUEL/X FEED/VALVE/MOT1 | A12 | 49VU

|APU/FUEL/LP VALVE/CTL | M40 | 121VU

|APU/FUEL/LP VALVE/SPLY | M39 | 121VU

|FUEL/LP VALVE/MOT1/ENG1 | A08 | 49VU

|FUEL/LP VALVE/MOT1/ENG2 | A09 | 49VU
|FUEL/LP VALVE/MOT2/ENG1 | M25 | 121VU

|FUEL/LP VALVE/MOT2/ENG2 | M26 | 121VU

|FUEL/HI/LVL/SPLY | L25 | 121VU

|FUEL/XFR VALVE1/WING/L | A10 | 49VU

|FUEL/XFR VALVE1/WING/R | A11 | 49VU

|FUEL/XFR VALVE2/WING/L | M22 | 121VU

|FUEL/XFR VALVE2/WING/R | M23 | 121VU

|FUEL/FQI/CHAN/1 | A13 | 49VU

|FUEL/FQI/CHAN/2 | M27 | 121VU

|FUEL/FQI/CHANNEL/1 AND 2 | L26 | 121VU

|FUEL/RFL/DFL/XFR/DEFUEL/VALVE | L23 | 121VU

|FUEL/RFL/DFL/SPLY | L24 | 121VU
HYD RESERVOIR LOW AIR PRESSURE MSG

 Aircraft configuration prior to reset:

On ground.

Circuit breakers to reset:

Steps to clear warning:

To clear, run engines or pressurize hydraulics reservoirs with APU air. If no help, check the
reservoir gauge. If still low, service it manually with N2 to 45 PSI. If no help, cycle circuit breakers.

Reset duration:

10 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

This fault normally occurs after working on hydraulic system.All 3 systems pressure switches are
set at 40psi. The blue system has an additional press switch set at 45PSI displayed on ground only.
Remember some A/C have a APU boost setting.

Sign off:

AMM29-14-00-720-001.
Applicable deferrals:
MEL29-30-04A RSVR LO AIR PRESSURE.

PTU FAULT

Aircraft configuration prior to reset:

checkOn ground with engines running.

Circuit breakers to reset:

checkN34

Normal PTU reset

1st) Yellow electric pump “ON”, wait 2 seconds.Turn yellow electric pump “OFF”

2nd) Set brakes, both engine pumps “OFF” yellow electric pumps “ON” , PTU pushbutton “OFF” then to
“AUTO” ,yellow electric pumps “OFF”, engine pumps “ON”.

PTU reset cause by cargo door operation:

Reset with engines running.

1) Reset message using master caution P/B switch.

2) Select hydaulic page on ECAM.

3) Select yellow hydraulic electric pump "ON" then "OFF".

4) Wait minimum of 30 seconds.

5) Cycle the PTU switch "ON"‐"OFF"‐"ON".

6) Select engine #1 green hydraulic pump "OFF", PTU should operate yellow to green.

7) Select engine #1 green hydraulic pump "ON".

8) Select engine #2 yellow hydraulic pump "OFF", PTU should operate green to yellow.

9) Select engine #2 yellow hydraulic pump "ON".

10) ECAM should be normal.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

checkPTU fault can be caused by cargo door operation 30 seconds after 2nd engine start.

Sign off:

TSM29‐23‐00‐810‐801

Applicable deferrals:

MEL29‐23‐01=Power Transfer Unit.

HYDRAULIC SYSTEM SCHEMATIC



CHAPTER 29‐CIRCUIT BREAKER LOCATION
|Designation|Location|Panel|

|HYDRAULIC/Y HYD/PUMP ENG2/MONG | Q37 | 121VU

|HYDRAULIC/Y HYD/PUMP ENG2/CTL | Q36 | 121VU

|HYD/FIRE VALVE/Y/ENG2 | C14 | 49VU

|HYD/RAT/CTL | D14 | 49VU

|HYDRAULIC/RAT/SPLY/EXTN/SOL1 | P33 | 121VU

|HYD/HYD PWR/B WARN/& CTL | C12 | 49VU

|HYDRAULIC/G HYD/PUMP ENG1/CTL | R35 | 121VU

|HYDRAULIC/G HYD/PUMP ENG1/MONG | R34 | 121VU

|HYD/FIRE VALVE/G/ENG1 | C13 | 49VU

|HYDRAULIC/SOL VALVES/G/Y/PTU | N34 | 121VU

|HYD/HYD/PRESS/XMTR | C11 | 49VU

|HYDRAULIC/SOL VALVES/G/Y/B/LEAK/TST | N35 | 121VU

|HYDRAULIC/HYD/QTY/IND | P35 | 121VU

|HYDRAULIC/LOW/LVL/IND | N32 | 121VU

|HYDRAULIC/HYD POWER/Y | N30 | 121VU

ANTI ICE - LEFT OR RIGHT WINDOW

 Aircraft configuration prior to reset:

On ground.

Circuit breakers to reset:

Steps to clear warning:

If the warning occurs on the ground with OAT greater then 40°C and AC packs off, turn both packs
on cool or place damp towel on inner pane over sensors for 5 minutes. Open circuit breakers for 5
seconds, then close.

Reset duration:

5 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

If possible, cover sensors from the exterior of the aircraft.

Sign off:

AMM30-42-00-710-001.

Applicable deferrals:

MEL30-42-02=Fixed Lateral & Sliding Window Heat.

ANTI ICE - LEFT OR RIGHT WINDSHIELD

 Aircraft configuration prior to reset:

On ground.

Circuit breakers to reset:

Steps to clear warning:

Reset duration:

5 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

If possible, cover sensors from the exterior of the aircraft.

Sign off:

AMM30-42-00-710-001.

Applicable deferrals:

MEL30-42-03=Windshield Heating System.

DRAIN MAST HEATER FAULT (FWD/AFT)

 Aircraft configuration prior to reset:

On ground.

Circuit breakers to reset:

Steps to clear warning:

Open circuit breakers for 5 second, then close.

Reset duration:

18 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains, CIDS caution light on FAP.

Notes:

If time, perform a bite on associated controller in cargo pit.

Sign off:

AMM30-71-00-710-001

Applicable deferrals:

MEL30-71-01=Waste Water Drain Mast Heating.

ANTI ICE MESSAGE

 Aircraft configuration prior to reset:

On ground, probe heat not selected "ON".

Circuit breakers to reset:

Steps to clear warning:

Open associated circuit breakers for 1 second, then close.

Reset duration:

3 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

No notes at this time.

Sign off:

AMM30-31-00-710-001.

Applicable deferrals:

MEL30-31-01=Probe Heat Computers.

ANTI ICE - PROBE MESSAGE SYSTEM #1

 Aircraft configuration prior to reset:

On ground, probe heat not selected "ON".

Circuit breakers to reset:

Steps to clear warning:

Open associated probe breaker for 1 second, then reset. If no help, open PHC #1 (49VU-D3) for 1
second, then reset.

Reset duration:

3 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

If probe reset did not clear, reset ADIRU C/B’s. #1=F6,C2 #2=N6,N4 #3=N5,N3

Sign off:

AMM30-31-00-710-001.

Applicable deferrals:

MEL30-31-01/02/03/04/05=Probe Heat.

ANTI ICE - PROBE MESSAGE SYSTEM #2

 Aircraft configuration prior to reset:

On ground, probe heat not selected "ON".

Circuit breakers to reset:

Steps to clear warning:

Open associated probe breaker for 1 second, then reset. If no help, open PHC #2 (122VU-Y12) for
1 second, then reset.

Reset duration:

3 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

If probe reset did not clear, reset ADIRU C/B’s. #1=F6,C2 #2=N6,N4 #3=N5,N3

Sign off:

AMM30-31-00-710-001.

Applicable deferrals:

MEL30-31-01/02/03/04/05=Probe Heat.

ANTI ICE - PROBE MESSAGE SYSTEM #3

 Aircraft configuration prior to reset:

On ground, probe heat not selected "ON".

Circuit breakers to reset:

Steps to clear warning:

Open associated probe breaker for 1 second, then reset. If no help, open PHC #3 (122VU-Y16) for
1 second, then reset.

Reset duration:

3 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

If probe reset did not clear, reset ADIRU C/B’s. #1=F6,C2 #2=N6,N4 #3=N5,N3

Sign off:

AMM30-31-00-710-001.

Applicable deferrals:

MEL30-31-01/02/03/04/05=Probe Heat.

ENGINE ANTI ICE FAULT

 Aircraft configuration prior to reset:

On ground, engines stopped.

Circuit breakers to reset:

Steps to clear warning:

Open circuit breakers for 1 second, then close. If no help work valve several times, make sure
valve is closed.

Reset duration:

3 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

Engine anti-ice valve should be spring loaded closed on the ground with engines off.

Sign off:

AMM30-21-00-710-002 (test with engines running).

Applicable deferrals:

MEL30-21-01/02=Engine Anti Ice.

CHAPTER 30‐CIRCUIT BREAKER LOCATION
|Designation|Location|Panel|

|ANTI ICE/PROBES/1/TAT | Z12 | 122VU

|ANTI ICE/PROBES/2/TAT | Y15 | 122VU

|ANTI ICE/PROBES/PHC/1 | D03 | 49VU

|ANTI ICE/PROBES/2/PHC | Y12 | 122VU

|ANTI ICE/PROBES/PHC/3 | Y16 | 122VU

|ANTI ICE/PROBES/PITOT/1 | D02 | 49VU

|ANTI ICE/PROBES/2/PITOT | Y14 | 122VU

|ANTI ICE/PROBES/3/PITOT | Z16 | 122VU

|ANTI ICE/PROBES/AOA/1 | D04 | 49VU

|ANTI ICE/PROBES/2/AOA | Y13 | 122VU

|ANTI ICE/PROBES/3/AOA | Z15 | 122VU

|ANTI ICE/PROBES/1/STATIC | Z13 | 122VU

|ANTI ICE/PROBES/2/STATIC | Y11 | 122VU

|ANTI ICE/PROBES/3/STATIC | Z14 | 122VU

|ANTI ICE/PROBES/P2/T2/ENG1 | Z10 | 122VU

|ANTI ICE/PROBES/P2/T2/ENG2 | Y10 | 122VU

|ANTI ICE/RAIN/RPLNT/CAPT | D01 | 49VU

|ANTI ICE/RAIN/RPLNT/F/O | W11 | 122VU

|ANTI ICE/WIPER/CAPT | X12 | 122VU

|ANTI ICE/F/O/WIPER | W12 | 122VU

|ANTI ICE/WINDOWS/L | X14 | 122VU

|ANTI ICE/WINDOWS/R | W14 | 122VU

|ANTI ICE/WHC/1 | X13 | 122VU
|ANTI ICE/WHC/2 | W13 | 122VU

|ANTI ICE/WING/MONG | C01 | 49VU

|ANTI ICE/WING/CTL | C02 | 49VU

|ANTI ICE/ENG/1 | X10 | 122VU

|ANTI ICE/ENG/2 | W10 | 122VU

|WATER SYSTEM ICE PROT HTR | D07 |2000VU

|WATER SYSTEM ICE PROT CTL | D08 |2000VU
Class 2 ACMS message displayed

 Aircraft configuration prior to reset:

Aircraft on ground, engines stopped.

Circuit breakers to reset:

Steps to clear warning:

Open associated breakers for 10 seconds, then reset.

Reset duration:

40 seconds.

Results of power up test or reset:

Pass: ACMS message clears.

Fail: Fault remains.

Notes:

ACMS = Aircraft Condition Monitor Systems.

Sign off:

AMM31-36-00-710-001

Applicable deferrals:

MEL31-00 Class 2 Maintenance Message

DISPLAY UNITS SHOWS TELELOADING

 Aircraft configuration prior to reset:

On ground.

Circuit breakers to reset:

Steps to clear warning:

First, attempt to switch affected display unit to DMC #3 using switching panel. Next, open
associated display unit circuit breaker for 10 seconds, then reset.

Reset duration:

5 seconds.

Results of power up test or reset:

Pass: Display unit image is recovered.

Fail: Fault remains.

Notes:

Also try reset of associated DMC. (DMC #1 = E11) (DMC #2 = Q8) (DMC #3 = Q9). All DMC’s
must be the same manufacturer part number.

Sign off:

AMM31-60-00-710-001. (EIS start)

Applicable deferrals:

MEL31-63-01=Display Units.
DISPLAY UNIT IS BLANK OR HAS DIAGONAL LINE

 Aircraft configuration prior to reset:

On ground.

Circuit breakers to reset:

Steps to clear warning:

First select DMC #3 to isolate fault to DU or DMC. If DMC is at fault reset above associated circuit
breaker for 5 seconds. If fault is with DU reset these (CAPT PFD/ND = G3/E1) (FO's PFD/ND =
R3/R4) (Upper ECAM = E5) (Lower ECAM = R11).

Reset duration:

5 seconds.

Results of power up test or reset:

Pass: Display operates normally.

Fail: Fault remains.

Notes:

No notes at this time.

Sign off:

AMM31-60-00-710-001.(EISstart)
Applicable deferrals:
MEL31-63-01=DisplayUnits.
MEL31-63-02=Display Management Computers.

DMC 1(2)(3) FAULT

 Aircraft configuration prior to reset:

Circuit brekers to reset

Steps to clear warning:

Open associated breakers for 5 seconds, then reset.

Reset duration:

5 seconds.

Results of power up test or reset:

Pass: ECAM warning clears, display unit works.

Fail: Fault remains.

Notes:

Use switching panel 8VU to display DMC #3 images.

Sign off:

AMM31-60-00-710-001. (EIS start)

Applicable deferrals:

MEL31-63-02=Display Management Computers.

UNABLE TO SWITCH DISPLAY UNIT (DU)

 Aircraft configuration prior to reset:

On ground.

Circuit breakers to reset:

Steps to clear warning:

Open associated breakers for 5 seconds, then reset.

Reset duration:

5 seconds.

Results of power up test or reset:

Pass: Display unit image switches normally.

Fail: Fault remains.

Notes:

No notes at this time.

Sign off:

AMM31-60-00-710-001. (EIS start)

Applicable deferrals:

MEL31-61-01=EIS Switching Systems.

NO AIDS PROMPT ON MCDU

 Aircraft configuration prior to reset:

Aircraft on ground, engines stopped.

Circuit breakers to reset:

Steps to clear warning:

Open associated breakers for 1 seconds, then reset.

Reset duration:

40 seconds.

Results of power up test or reset:

Pass: AIDS appears on MCDU menu page.

Fail: Fault remains.

Notes:

There is a CFDS power up test bite. “CFDS-INSTRUMENT-DMU”.

Sign off:

AMM31-36-00-710-001

Applicable deferrals:

MEL31-30-07 Data Management Unit (DMU)

PFR PRINTS AUTOMATIC AFTER LANDING

 Aircraft configuration prior to reset:

Aircraft on ground.

Circuit breakers to reset:

None.

Steps to clear warning:

Go to MCDU-CFDS, the next page. Select ACARS PRINT/PROGRAM. Then select post flight
report PRINT to NO. Return to CFDS.

Reset duration:

N/A.

Results of power up test or reset:

Pass: PFR wont auto print.

Fail: PFR still auto prints.

Notes:

Sign off:

N/A
Applicable deferrals:
N/A

FLIGHT CONTROL PAGE WON’T AUTO-DISPLAY

 Aircraft configuration prior to reset:

Aircraft on ground, doors shut, one engine started.

Circuit breakers to reset:

Steps to clear warning:

Make sure “ALL” pushbutton light on ECAM control panel is extinguished. Move sidestick, If flight
control page doesn’t auto display, open FWC #1 breaker and try again. If successful, FWC is culprit.

Reset duration:

50 seconds.

Results of power up test or reset:

Pass: Fault message is no longer displayed, flight control page auto popup functions normally.
Fail: Fault remains.

Notes:

If any page on the ECAM control panel is manually selected, the auto-function is not operative.

Sign off:

AMM31-50-00-710-002.

Applicable deferrals:

MEL31-63-03=ECAM Memo Display.

CLOCK DOESN’T AGREE WITH LOWER ECAM

 Aircraft configuration prior to reset:

Aircraft on ground.

Circuit breakers to reset:

Steps to clear warning:

Open associated breaker for 5 seconds, then reset.

Reset duration:

60 seconds.

Results of power up test or reset:

Pass: A/C clock and lower ECAM clock will agree.

Fail: Fault remains.

Notes:

Verify clock is correctly set prior to reset of CFDIU. Clock C/B’s are F11/N02/N03.

Sign off:

AMM31-21-00-710-002.

Applicable deferrals:

MEL31-21-01=Clock System.

CFDS FAULT MESSAGE PRINTS IN FLIGHT

 Aircraft configuration prior to reset:

Aircraft on ground.

Circuit breakers to reset:

None.

Steps to clear warning:

Go to MCDU-CFDS, the next page. Select ACARS PRINT/PROGRAM. Then select REAL TIME
FAIL and WARN print to OFF. Return to CFDS.

Reset duration:

N/A.

Results of power up test or reset:

Pass: fault message wont auto print.

Fail: fault message still auto prints.

Notes:

Sign off:

N/A
Applicable deferrals:
N/A

SDAC 1(2) FAULT

 Aircraft configuration prior to reset:

On ground.

Circuit breakers to reset:

Steps to clear warning:

Open associated breakers together for 3 seconds, then reset.

Reset duration:

5 seconds.

Results of power up test or reset:

Pass: SDAC ECAM message clears

Fail: Fault remains.

Notes:

No notes at this time.

Sign off:

AMM31-50-00-710-003

Applicable deferrals:

MEL31-55-01=System Data Concentrator Units.

ECAM PAGE LOCKED

 Aircraft configuration prior to reset:

Aircraft on ground, engines stopped.

Circuit breakers to reset:

Steps to clear warning:

Open associated breaker for 5 seconds, then reset.

Reset duration:

60 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

If both FWC’s are reset together, all warnings , will be inoperative durning the reset.

Sign off:

AMM31-50-00-710-004

Applicable deferrals:

MEL31-56-01=ECAM Control Panel.

FWS FWC 1(2) FAULT

Computer: FWC.

REST PROCEDURE:

FOR FWC1 ON PANEL 49VU F01

FOR FWC2 ON PANEL121VU Q07

CHAPTER 31‐CIRCUIT BREAKER LOCATION
|Designation|Location|Panel|

CLOCK/NORM/SPLY | F11 | 49VU

|NAV/DME/1 | G14 | 49VU

|COM NAV/DME/2 | K06 | 121VU

|DATA/LOADER/SPLY | J16 | 121VU

|RCDR/DFDR | K16 | 121VU

|CFDS/CFDIU/SPLY | J18 | 121VU

|PTR/SPLY | J21 | 121VU

|AIDS/DMU | K15 | 121VU

|CFDS/CFDIU/BACK/UP | J17 | 121VU

|CFDS/TEST PLUG/1 | J19 | 121VU

|CFDS/TEST PLUG/2 | J20 | 121VU

|EIS/DMC1/SPLY | E11 | 49VU
|EIS/DMC2/SPLY | Q08 | 121VU

|EIS/DMC3/SPLY | Q09 | 121VU

|EIS/PFD CAPT/SPLY | E03 | 49VU

|EIS/PFD/F/O | R03 | 121VU

|EIS/ND CAPT/SPLY | E01 | 49VU

|EIS/ND/F/O | R04 | 121VU

|EIS/ECAM DU/UPPER/SPLY | E05 | 49VU

|EIS/ECAM DU/LOWER/SPLY | R11 | 121VU

|EIS/DMC3/STBY/SPLY | E10 | 49VU

|EIS/ECAM/CTL/PNL | E12 | 49VU

|EIS/RLY/BOX/CAPT | E08 | 49VU

|EIS/RLY/BOX/F/O | R07 | 121VU

|EIS/DMC1/SWTG | E09 | 49VU

|EIS/DMC2/SWTG | R08 | 121VU

|EIS/DMC3/SWTG | E07 | 49VU

|EIS/PFD CAPT/SWTG | E04 | 49VU

|EIS/PFD/F/O/SWTG | R05 | 121VU

|EIS/ND CAPT/SWTG | E02 | 49VU

|EIS/ND/F/O/SWTG | R06 | 121VU

|EIS/ECAM DU/UPPER/SWTG | E06 | 49VU

|EIS/ECAM DU/LOWER/SWTG | R10 | 121VU

|EIS/SDAC/2/SPLY | Q06 | 121VU

|SDAC/1/SPLY | F04 | 49VU

|SDAC/1/26VAC SYNC/AC ESS BUS | F02 | 49VU

|SDAC/2/26VAC SYNC/AC ESS BUS | F03 | 49VU
|EIS/SDAC/1/BUS2/26VAC SYNC AC | Q03 | 121VU

|EIS/SDAC/2/BUS2/26VAC SYNC AC | Q02 | 121VU

|EIS/SDAC/1/BUS1/26VAC SYNC AC | Q04 | 121VU

|EIS/SDAC/2/BUS1/26VAC SYNC AC | Q05 | 121VU

|SDAC/1 AND 2/28VDC/ESS BUS | F05 | 49VU

|EIS/SDAC1 AND 2/BUS1/28VDC | P04 | 121VU

|EMER/GEN/REF | B05 | 106VU

|EIS/SDAC1 AND 2/BUS2/28VDC | P03 | 121VU

|EIS/SDAC1 AND 2/DOOR/DET/AVNCS | P02 | 121VU

|EIS/SDAC1 AND 2/DOOR/DET/PAX | P05 | 121VU

|DC BUS/1 AND 2/MONG | C03 | 106VU

|EIS/FWC2/SPLY | Q07 | 121VU

|FWS/FWC1/SPLY | F01 | 49VU

|EIS/F/O/LOUD/SPKR | P08 | 121VU

|CAPT/LOUD/SPKR | F10 | 49VU
LGCIU 1(2) FAULT

 Aircraft configuration prior to reset:

Aircraft on ground.

Circuit breakers to reset:

Steps to clear warning:

Open associated breaker for 1 seconds, then reset.

Reset duration:

2 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

LGCIU #1 drives landing gear panel lights. also remember probes and window heat is driven to full
hot when LGCIU breakers are open.

Sign off:

AMM32-69-00-740-001

Applicable deferrals:

MEL32-31-01=LGCIU

L/G (LANDING GEAR) SYSTEM DISAGREE

 Aircraft configuration prior to reset:

Aircraft on ground.

Circuit breakers to reset:

None.

Steps to clear warning:

Check post flight report for faulted gear or door sensor. Or perform a CFDS / LG / LGCIU bite
check for current faults. Check rig and/or replace faulty sensor or target. If main gear uplock disagree
is shown on ground, make sure the main gear uplocks (Hooks) have not been physically tripped.

Reset duration:

N/A.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

Sign off:

AMM32-69-00-740-001
Applicable deferrals:
No MEL

BRAKES GRABBING DURNING TAXI

 Aircraft configuration prior to reset:

Aircraft on ground, “NOT MOVING”.

Circuit breakers to reset:

None.

Steps to clear warning:

Reset A/SKID-NWS switch on landing gear control panel. No help, bleed associated brakes.

Reset duration:

N/A.

Results of power up test or reset:

Pass: Control of brakes switch to other BSCU channel.

Fail: Fault remains.

Notes:

Flight crews can perform this with engines running. Just make sure the aircraft is stopped.
Sign off:
AMM32-46-00-740-001
Applicable deferrals:
MEL32-42-03=BSCU.
BSCU CHANNEL 1(2) FAULT

 Aircraft configuration prior to reset:

Aircraft on ground, not moving.

Circuit breakers to reset:

Steps to clear warning:

First, select the anti-skid/NWS off, then on. Second open associated circuit breaker for 5 seconds,
then close.

Reset duration:

3 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

No notes at this time.

Sign off:

AMM32-46-00-740-001.

Applicable deferrals:

MEL32-42-03=BSCU.

BRAKE SYSTEM 1(2) FAULT

 Aircraft configuration prior to reset:

Aircraft on ground, not moving.

Circuit breakers to reset:

Steps to clear warning:

First, select the anti-skid/NWS off, then on. Second open associated circuit breaker for 5 seconds,
then close.

Reset duration:

3 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

No notes at this time.

Sign off:

AMM32-46-00-740-001.

Applicable deferrals:

MEL32-42-03=BSCU.

NO BRAKE TEMPS DISPLAYED ON ECAM

 Aircraft configuration prior to reset:

Aircraft on ground.

Circuit breakers to reset:

Steps to clear warning:

Open associated breaker for 5 seconds, then reset.

Reset duration:

5 seconds.

Results of power up test or reset:

Pass: Brake temps show on ECAM.

Fail: Fault remains.

Notes:

Take off warning configuration horn will sound when BTMU is on MEL. T/O not allowed with hot
brakes. MEL requires removing cannon plug for affected wheel BTMU. Erroneos indications are
extreme HI temps or amber XX.

Sign off:

AMM32-47-00-710-001.

Applicable deferrals:

MEL32-47-01=Brake Temperature Monitoring Unit.

NOSE WHEEL STEERING FAULTY

 Aircraft configuration prior to reset:

Aircraft on ground, “NOT MOVING”.

Circuit breakers to reset:

None.

Steps to clear warning:

Reset A/SKID-NWS switch on landing gear control panel. No help, bleed associated brakes.

Reset duration:

N/A.

Results of power up test or reset:

Pass: Control of steering switch to other BSCU CH.

Fail: Fault remains.

Notes:

Flight crews can perform this with engines running. Just make sure the aircraft is stopped.
Sign off:
AMM32-51-00-720-003.
Applicable deferrals:
MEL32-60-04=N/WS Minor Fault Caution on ECAM.
NWS FAULT DURNING FLIGHT CONTROL CK.

 Aircraft configuration prior to reset:

Aircraft on ground.

Circuit breakers to reset:

None.

Steps to clear warning:

Determine which NWS disconnect button was pushed durning rudder check. Replace that steering
tiller.

Reset duration:

N/A.

Results of power up test or reset:

Pass: Fault clears.

Fail:Faultremains.
Notes:

Sign off:
AMM32-51-00-720-007.
Applicable deferrals:
MEL32-51.02=Pedal DISC.

CHAPTER 32‐CIRCUIT BREAKER LOCATION
|Designation|Location|Panel|

|L/G/LGCIU/SYS1/NORM | C09 | 49VU

|HYDRAULIC/LGCIU/SYS2 | Q35 | 121VU

|HYDRAULIC/LGCIU/SYS1/GRND SPLY | Q34 | 121VU

|HYDRAULIC/BRAKING AND STEERING/SYS1/CTL | M34 | 121VU

|HYD/BRAK AND STEERING/SYS1/IND AND/SPLY | M33 | 121VU

|HYD/BRAKING AND STEERING/SYS2/CTL | M35 | 121VU

|HYD/BRAKING AND STEERING/SYS2/SPLY | M36 | 121VU

|L/G/Y BRK/PRESS/IND | C10 | 49VU

|HYDRAULIC/PARK BRK/CTL/NORM | N36 | 121VU

|HYDRAULIC/PARK BRK/CTL/STBY | N37 | 121VU

|HYDRAULIC/BRK FAN/WHEELS/1 AND 2 | L32 | 121VU

|HYDRAULIC/BRK FAN/WHEELS/3 AND 4 | L35 | 121VU

|HYDRAULIC/BRK/FAN/CTL | M32 | 121VU

|HYDRAULIC/BRK/TEMP/DET/UNIT | M37 | 121VU
INTEGRAL PANEL LIGHTING INOP

 Aircraft configuration prior to reset:

No specific

Circuit breakers to reset:

Check light controllers below for circuit breaker or fuse locations.

Steps to clear warning:

If multiple panel lights are inop, a fuse is blown in the associated light controller. Replace
associated fuse, or controller.

Reset duration:

N/A.

Results of power up test or reset:

Pass: Panel lights work normally.

Fail: Panel lights remain inop.

Controllers:
Sign off:

AMM33-13-00-710-001.

Applicable deferrals:

MEL33-10-01=Instrument Panel Lighting System.

CABIN LIGHTS STUCK IN BRIGHT

 Aircraft configuration prior to reset:

None specfic.

Circuit breakers to reset:

Steps to clear warning:

Open associated breaker for 3 seconds, then reset. If no help, reset CIDS or associated DEU thru
PTP.

Reset duration:

2 seconds.

Results of power up test or reset:

Pass: Light dims.

Fail: Fault remains.

Notes:

If a couple successive rows of cabin lights won’t dim, associated DEU is failed.

Sign off:

AMM33-21-00-710-001(lightstest).
AMM23-73-00-740-005(CIDSbite).
Applicable deferrals:
MEL23-73-02=DEU#A.
MEL33-21-01=Cabin Light System.

STROBE LIGHT WON’T SHUT OFF

 Aircraft configuration prior to reset:

None specfic.

Circuit breakers to reset:

Steps to clear warning:

Open breaker to stop strobe lights flashing,replace 12LV relay to fix problem.

Reset duration:

N/A

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

The relay FIN number is 12LV P/N E0246-115B0 M&E-26-2400-3-0159.

Sign off:

AMM33-48-00-710-002.

Applicable deferrals:

MEL33-40-08=Strobe Lights.

COCKPIT FLOOR/CONSOLE/BRIEFCASE LIGHTS INOP

 Aircraft configuration prior to reset:

Aircraft on ground.

Circuit breakers to reset:

Capt's side = Z05. F/O's side = Z06.

Steps to clear warning:

Check the condition of underseat lights for damage sockets.

Reset duration:

N/A.

Results of power up test or reset:

Pass: Panel lights work normally.

Fail: Panel lights remain inop.

Notes:

Sign off:
AMM33-12-00-710-001.
Applicable deferrals:
MEL33-10-01=Cockpit Lighting System.

CABIN LIGHTS WON’T TURN ON

 Aircraft configuration prior to reset:

None specfic.

Circuit breakers to reset:

Steps to clear warning:

Open associated breaker for 3 seconds, then reset. If no help, reset CIDS thru PTP or MCDU.

Reset duration:

2 seconds.

Results of power up test or reset:

Pass: Lights turn on.

Fail: Fault remains.

Notes:

If a couple successive rows of cabin lights won’t turn on, associated DEU is failed.

Sign off:

AMM33-21-00-710-001 (lights test).

AMM23-73-00-740-005 (CIDS bite).

Applicable deferrals:

MEL23-73-02=DEU#A.
MEL33-21-01=Cabin Light System.
READING LIGHTS INOP

 Aircraft configuration prior to reset:

Aircraft on ground, reading lights switch on FAP selected “ON”.

Circuit breakers to reset:

Steps to clear warning:

Open associated breaker for 1 seconds, then reset. If no help, reset CIDS thru PTP or MCDU.

Reset duration:

1 seconds.

Results of power up test or reset:

Pass: Reading lights operate.

Fail: Fault remains.

Notes:

If no help, relamp inop reading light. In no help, replaced PCB fuse, If no help replaced the PCB.

Sign off:

AMM33-25-00-710-001(lightstest).
AMM23-73-00-740-005 (CIDS bite).

Applicable deferrals:

MEL33-20-01=Cabin Lighting System.

NO LIGHTS IN MLG WHEEL WELL AREAS

 Aircraft configuration prior to reset:

None specfic.

Circuit breakers to reset:

Steps to clear warning:

Open associated breaker for 1 seconds, then reset. No help, relamp or tap lens.

Reset duration:

1 seconds.

Results of power up test or reset:

Pass: Lights operates.

Fail: Fault remains.

Notes:

MLG wheel well light bulb P/N#311.

Sign off:

AMM33-37-00-710-001

Applicable deferrals:

MEL33-30-01=Cargo Service Lighting System.

EMERGENCY LIGHTS INOP

 Aircraft configuration prior to reset:

Aircraft on ground.

Circuit breakers to reset:

Steps to clear warning:

 Open associated breaker for 1 seconds, then reset. If multiple lights are inop, perform EPSU
test from PTP or individual EPSU.

Reset duration:
1seconds.
Results of power up test or reset:
Pass: Lights operates.
Fail:Faultremains.
Notes:

Sign off:
AMM33-51-00-710-001.
Applicable deferrals:
MEL33-50-02=OverheadEmergencyLights.
MEL33-50-03=Floor Path Emergency Lights.

CHAPTER 33‐CIRCUIT BREAKER LOCATION

|Designation|Location|Panel|

|LIGHTING/EXT LT/NAV1/AND LOGO/LT | T03 | 122VU

|LIGHTING/EXT LT/NAV2/AND LOGO/LT | T02 | 122VU

|LIGHTING/LANDING LT/L/SPLY | T04 | 122VU

|LIGHTING/LANDING LT/R/SPLY | T06 | 122VU

|LIGHTING/LANDING LT/L/CTL | T05 | 122VU

|LIGHTING/LANDING LT/R/CTL | T07 | 122VU

|LIGHTING/EXT LT/RWY TURN OFF/L | W06 | 122VU

|LIGHTING/EXT LT/RWY TURN OFF/R | W05 | 122VU

|LIGHTING/EMER LT/CKPT/DOME | H08 | 49VU

|LIGHTING/FLOOD/CTR INST/PNL | Z04 | 122VU

|LIGHTING/CKPT/DOME | Y06 | 122VU

|LIGHTING/FLOOD/F/O/SIDE | Z06 | 122VU

|LIGHTING/FLOOD/CAPT/SIDE | Z05 | 122VU

|LIGHTING/ICE AND STBY/COMP/LIGHT | H04 | 49VU

|LIGHTING/INSTL LT/OVHD/PNL | Y03 | 122VU

|LIGHTING/INSTL LT/MAIN INST/PNL AND/PED | Y04 | 122VU

|LIGHTING/INSTL LT/GLARE/SHLD | Y05 | 122VU

|CABIN LIGHT POWER‐WINDOW FWD | H01 |2000VU

|CABIN LIGHT POWER‐WINDOW AFT | H03 |2000VU

|CABIN LIGHT POWER‐WINDOW AFT | H04 |2000VU

|CABIN LIGHT POWER‐WINDOW FWD | H02 |2000VU

|CABIN LIGHT POWER‐CEILING AFT | H07 |2000VU
|CABIN LIGHT POWER‐CEILING FWD | H05 |2000VU

|CABIN LIGHT POWER‐CEILING FWD | H06 |2000VU

|CABIN LIGHT POWER‐CEILING AFT | H08 |2000VU

|LIGHT‐CABIN ENTRY | J04 |2000VU

|AIR CONDTN COMPT OUTLET | B08 |2000VU

|LIGHTING/WHL WELL/LTG/OUT | X07 | 122VU

|LIGHTING/WHL WELL/LTG/DOME | X08 | 122VU

|LIGHTING/ANN LT SPLY/XFMR/BUS 1 | X04 | 122VU

|LIGHTING/ANN LT SPLY/XFMR/BUS 2 | X05 | 122VU

|LIGHTING/ANN LT SPLY/XFMR/STAT INV | X03 | 122VU

|LIGHTING/XFMR/115V.5V/ESS BUS | H03 | 49VU

|LIGHTING/TST/BOARD/SPLY | X06 | 122VU

|LIGHTING/EXT LT/TAXI AND TAKE OFF/TAXI | W08 | 122VU

|LIGHTING/EXT LT/TAXI AND TAKE OFF/CTL | W09 | 122VU

|LIGHTING/EXT LT/TAXI AND TAKE OFF/TO | W07 | 122VU

|LIGHTING/AVNCS COMPT/DOME | Z07 | 122VU

|LIGHTING/AVNCS COMPT/OUT/28VDC | Z08 | 122VU

|LIGHTING/AVNCS COMPT/OUT/115VAC | Z09 | 122VU

|CARGO COMPT LIGHT‐FWD | B04 |2000VU

|CARGO COMPT LIGHT‐AFT | B05 |2000VU

|CARGO COMPT LIGHT‐LDG AERA | B06 |2000VU

|LIGHTING/EXT LT/BEACON/UPPER | U06 | 122VU

|LIGHTING/EXT LT/BEACON/LOWER | U03 | 122VU

|LIGHTING/WING/STROBE | V05
NAV - GPS 1(2) FAULT ONLY

 Aircraft configuration prior to reset:

Aircraft on ground.

Circuit breakers to reset:

ON PANEL 121VU GPSSU1 @ 2 POWER SUPLY

Steps to clear warning:

Open associated breaker for 5 seconds, then reset.

Reset duration:

10 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

Check troubleshoot data for “A7” fault code. GPS antenna normally at fault in this situation.

Sign off:

AMM34-36-00-740-003.

Applicable deferrals:

MEL34-58-01=Gobal Positioning System.

NAV ILS/MMR 1(2)

 Aircraft configuration prior to reset:

Aircraft on ground.

Circuit breakers to reset:

Steps to clear warning:

Open associated breaker for 5 seconds, then reset. If no help, check MMR in fwd E&E for fault
light.

Reset duration:

10 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

MMR is normally the cause of this fault.

Sign off:

AMM34-36-00-740-003.

Applicable deferrals:

MEL34-58-01=GobalPositioningSystem.
MEL34-36-01=ILS #2 System

ADIRU-FLASHING ALIGN LIGHT AT ALIGNMENT

 Aircraft configuration prior to reset:

Aircraft on ground, not moving, (PPOS)-present position entered thru MCDU INIT page.

Circuit breakers to reset:

None.

Steps to clear warning:

Affected ADIRU, turn rotary on knob on ADIRS control panel to ATT for 5 seconds, then to OFF for
20 seconds, then to NAV. If no help, affected ADIRU needs to cool down. If cool, replace ADIRU.

Reset duration:

600 seconds.

Results of power up test or reset:

Pass: Normal alignment.

Fail: Fault remains.

MCDU:

Sign off:
AMM34-13-00-740-002.
Applicable deferrals:
MEL34-10-01=ADIRS.

ADR OR IR 1(2)(3) FAULT

 Aircraft configuration prior to reset:

Aircraft on ground.

Circuit breakers to reset:

Steps to clear warning:

Above breakers are main/backup power for ADIRU's. Try reseting and realinging ADIRU. No help
check check CFDS for faults. To T/S, check the CFDS/NAV/ADR or IR/ T/S DATA. The first 4 digits in
the upper left corner is the fault analysis number. The two middle digits in the fault analysis number is
the failure code.

Reset duration:

600 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

A known problem of the ADIRU shelf vibrating and hitting the top of the ADIRU will cause this fault.

Sign off:

AMM34-13-00-740-002.

Applicable deferrals:

MEL34-10-01=ADIRS.

NAV GPWS FAULT OR

NAV GPWS TERR DET FAULT.
0R NAV TCAS FAULT
 Aircraft configuration prior to reset:

Aircraft on ground.

Circuit breakers to reset: ON CLASSIC A/C

CIRCUIT BREAKER TO RESET ..ON ENHANCED A/C: COMPUTER (T2CAS)

ON PANEL 121VU K10 COM NAV/T2CAS RESET DURATION( 5SEC)

OR ON A/C 004-100: COMPUTER(T/TISS)

ON PANEL 121VU K07 T/TISS RESET DURATON (10 SEC)

Steps to clear warning:

Open associated breaker for 1 seconds, then reset. No help, move aircraft approx 4 feet.

Reset duration: 25 seconds.

Results of power up test or reset: Pass: Fault clears. Fail: Fault remains.

Notes:

This problem may be by ILS freq’s that are close and interfering with the GPWS system. Move A/C.
This fault may appear and disappear during taxi for this reason.

Sign off:

AMM34-48-00-740-002.

Applicable deferrals:

MEL34-48-01=GPWS/EGPWS.

WINDSHEAR DET FAULT

 Aircraft configuration prior to reset:

Aircraft on ground, engines can be running, flaps up.

Circuit breakers to reset:

Steps to clear warning:

First reset FAC’S from overhead pushbuttons. Then open associated breaker for 10 seconds, then
reset.

Reset duration:

90 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

If hydraulics are powered, reset duration is less than 10 seconds, 90 seconds otherwise. Also
message may occur spuriously on ground.

Sign off:

AMM22-60-00-710-004(FACopstest).
AMM34-41-00-740-002(Weatherradartest).
Applicable deferrals:
MEL22-66-03-Windshear Detection.

NAV - PRED WINDSHEAR DET FAULT

 Aircraft configuration prior to reset:

Aircraft on ground.

Circuit breakers to reset:

Steps to clear warning:

Switch radar off, then on from the control panel, if no help open associated breaker for 5 seconds,
then reset.

Reset duration:

30 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

Sign off:
AMM34-41-00-740-002(Weatherradartest).
Applicable deferrals:
MEL22-66-03-Windshear Detection.

NAV - TCAS FAULT

 Aircraft configuration prior to reset:

No specific.

Circuit breakers to reset:

Steps to clear warning:

Open breaker for 5 seconds, then reset. No help, bite test TCAS computer located on the 82VU
rack.

Reset duration:

10 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

Sign off:
AMM34-43-00-740-001.
Applicable deferrals:
MEL34-43-01=TCAS System.

FLIGHT RECORDER PROBLEM

 Aircraft configuration prior to reset:

Aircraft on ground, engines stopped.

Circuit breakers to reset:

Steps to clear warning:

Open breaker for 1 seconds, then reset.

Reset duration:

25 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

No notes at this time.

Sign off:

AMM31-33-00-710-006

Applicable deferrals:

MEL31-30-02=Flight Data Recorder (FDR).

AUTO-TUNE INOP

 Aircraft configuration prior to reset:

Aircraft on ground.

Circuit breakers to reset:

None.

Steps to clear warning:

Try a different station position in the MCDU “INIT” page. The nav data could be at fault. Also verify
both RMP’s that the “NAV ON” switch is off-(Plastic Guarded Switch).

Reset duration:

N/A.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

RMP:

Sign off:
AMM.

Applicable deferrals:

MEL34-00-01=Autotune System.

WHITE “GPS PRIMARY” MESSAGE SHOWN

 Aircraft configuration prior to reset:

Aircraft on ground.

Circuit breakers to reset:

None.

Steps to clear warning:

“GPS PRIMARY” message is normal operartion. This is stating the the GPS is the primary mode of
operation. The clear button on the MCDU will erase this message.

Reset duration:

N/A.
Results of power up test or reset:
Pass: Fault clears.
Fail:Faultremains.
MCDU:

Sign off:
AMM34-36-00-740-003.

Applicable deferrals:

MEL34-58-01=Gobal Positioning System.

NAV-RA 1(2) INOP

 Aircraft configuration prior to reset:

Aircraft on ground.

Circuit breakers to reset:

Steps to clear warning:

Open associated breaker for 20 seconds, then reset. If no help, perform a CFDS/NAV/RA/ARINC
test.

Reset duration:

30seconds.
Results of power up test or reset:
Pass: Fault clears.
Fail:Faultremains.
Notes:

Sign off:
AMM34-42-00-740-002.

Applicable deferrals:

MEL34-42-01=Radio Altimeter System.

ON ENHANCED A/C 004-100:

NAV ATC /XPDR FAULT. FAULT MASSEGE.
COMPUTER : T/TISS.
RESET PROCEDURE"
ON PANEL 121VU K07 T/TISS RESET DURATION (10SEC)

CHAPTER 34‐CIRCUIT BREAKER LOCATION
|Designation|Location|Panel|

|NAV/STBY/HORIZON | F12 | 49VU

|NAV/VOR/DME/RMI | F13 | 49VU

|NAV/STBY/ALTM | F14 | 49VU

|NAV/STBY/INST/BAT | J01 | 105VU

|NAV PROBES/ADIRU1/115VAC | F06 | 49VU

|ADIRS/ADIRU/2/115VAC | N06 | 121VU

|ADIRS/ADIRU/2/115VAC | N07 | 121VU

|ADIRS/ADIRU/3/115VAC | N05 | 121VU

|ADIRS/ADIRU/3/115VAC | N06 | 121VU

|NAV PROBES/ADIRU 1/AND AOA 1/26VAC | F07 | 49VU

|ADIRS/ADIRU/2/26VAC AND AOA | N08 | 121VU

|ADIRS/ADIRU/2/26VAC AND AOA | N09 | 121VU

|ADIRS/ADIRU/3/26VAC AND AOA | N07 | 121VU

|ADIRS/ADIRU/3/26VAC AND AOA | N08 | 121VU

|ADIRS/ADIRU1/28VDC | C02 | 105VU

|ADIRS/ADIRU/2/28VDC | N05 | 121VU

|ADIRS/ADIRU/2/28VDC | N04 | 121VU

|ADIRS/ADIRU/3/28VDC | N04 | 121VU

|ADIRS/ADIRU/3/28VDC | N03 | 121VU

|NAV PROBES/ADIRU3/PWR/SWTG | F09 | 49VU
|ADIRS/ADIRU/3PWR/SWTG | N09 | 121V

|ADIRS/ADIRU/3PWR/SWTG | N10 | 121VU

|ADIRS/ADIRU/2PWR/SHED | N11 | 121VU

|ADIRS/ADIRU/2PWR/SHED | N10 | 121VU

|NAV/VOR/1 | G13 | 49VU

|COM NAV/VOR/2 | K08 | 121VU

|NAV/MMR/1 | G12 | 49VU

|COM NAV/MMR/2 | L07 | 121VU

|COM NAV/MMR/2 | K09 | 121VU

|COM NAV/RAD ALTM/1 | K11 | 121VU

|COM NAV/RAD ALTM/2 | K12 | 121VU

|COM NAV/TCAS | K10 | 121VU

|COM NAV/ATC/1 | G11 | 49VU

|COM NAV/ATC/2 | K07 | 121VU

|COM NAV/RADAR/1 | K13 | 121VU

|EIS/GPWS/28VDC | P06 | 121VU

|EIS/GPWS/115VAC | P07 | 121VU
CREW OXYGEN LOW PRESSURE MESSAGE

 Aircraft configuration prior to reset:

Aircraft on ground.

Circuit breakers to reset:

None.

Steps to clear warning:

Verify crew oxygen pushbutton swich is selected “ON”. If no help, make sure the crew oxygen
bottle valve is turned on. The bottle is in the FWD left equipment bay.

Reset duration:

N/A.

Results of power up test or reset:

Pass: Fault clears.

Fail:Faultremains.
Overhead Panel:

Sign off:
TSM35-10-00-810-820.
Applicable deferrals:
MEL35-13-01=ECAM Page Indications.

CHAPTER 35‐CIRCUIT BREAKER LOCATION

|Designation|Location|Panel|

|CREW SPLY | C1 | 49VU

|CTL & WARN | C2 | 49VU

|CTL & WARN | C3 | 49VU

|CTL & WARN | C4 | 49VU

|ACTUATION | C5 | 49VU

|ACTUATION | C6 | 49VU

|ACTUATION | C7 | 49VU

|ACTUATION | C8 | 49VU
CLASS 2 AIR BLEED MESSAGE

 Aircraft configuration prior to reset:

Aircraft on ground, emergency electrical generator test recently performed.

Circuit breakers to reset:

Steps to clear warning:

Open both FWC breaker for 5 seconds, then reset. If no help reset both BMC’s (D11,D12,Z22,Z23)
and FWC breakers again. If no help check BMC for faults.

Reset duration:

90 seconds, triple click.

Results of power up test or reset:

Pass: Message disappears.

Fail: Message remains. Check BMC for faults.

Notes:

This fault is latched after Emergency Generator test.

Sign off:

AMM36-11-00-740-001 (BMC TEST).

Applicable deferrals:

MEL36-00=Class 2 Maintenance MSG on ECAM.

AIR BLEED - LEFT WING LEAK/LOOP MESSAGE

 Aircraft configuration prior to reset:

Aircraft on ground, packs running, engines off.

Circuit breakers to reset:

Steps to clear warning:

Reset affected bleed pushbutton first, no help open associated breakers for 1 second, then reset.

Reset duration:

25 seconds.

Results of power up test or reset:

Pass: Message disappears.

Fail: Message remains. Check BMC for faults.

Notes:

Fault means high temp(or bleed leak) sensed by one of two loops. Can be generated in hot station,
then clear in cool station due to poor loop installation,(factory problem).

Sign off:

AMM36-11-00-740-001 (BMC TEST).

Applicable deferrals:

MEL36-00=Class 2 Maintenance Messages only

AIR BLEED - RIGHT WING LEAK/LOOP MESSAGE

 Aircraft configuration prior to reset:

Aircraft on ground, packs running, engines off.

Circuit breakers to reset:

Steps to clear warning:

Reset affected bleed pushbutton first, no help open associated breakers for 1 second, then reset.

Reset duration:

25 seconds.

Results of power up test or reset:

Pass: Message disappears.

Fail: Message remains. Check BMC for faults.

Notes:

Fault means high temp(or bleed leak) sensed by one of two loops. Can be generated in hot station,
then clear in cool station due to poor loop installation,(factory problem).

Sign off:

AMM36-11-00-740-001 (BMC TEST).

Applicable deferrals:

MEL36-00=Class 2 Maintenance Messages only

BMC PROBLEMS

 Aircraft configuration prior to reset:

Aircraft on ground, engines off.

Circuit breakers to reset:

Steps to clear warning:

Open associated breaker for 1 second, then reset.

Reset duration:

25 seconds.

Results of power up test or reset:

Pass: Message disappears.

Fail: Message remains. Check BMC for faults.

Notes:

No notes at this time.

Sign off:

AMM36-11-00-740-001 (BMC TEST).

Applicable deferrals:

MEL36-11-01=Bleed Air Systems.

CROSS BLEED VALVE FAULTS

 Aircraft configuration prior to reset:

Aircraft on ground. Packs off.

Circuit breakers to reset:

Steps to clear warning:

Open associated circuit breaker for 1 second, then reset.

Reset duration:

5 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

No notes at this time.

Sign off:

AMM36-12-00-710-001 (Crossbleed Valve Ops Test).

Applicable deferrals:

MEL36-12-04=Cross Bleed Valve

CHAPTER 36‐CIRCUIT BREAKER LOCATION

|Designation|Location|Panel|

|AIR BLEED/ENG 1/MONG | D11 | 49VU

|AIR BLEED/ENG 2/MONG | Z22 | 122VU

|AIR BLEED/ENG 1/CTL | D12 | 49VU

|AIR BLEED/ENG 2/CTL | Z23 | 122VU

|AIR BLEED/X FEED VALVE/NORM | Z20 | 122VU

|AIR BLEED/X FEED/VALVE/BAT | D13 | 49VU
TOILET’S WON’T FLUSH

 Aircraft configuration prior to reset:

Aircraft on ground, lav service panel door is closed and the waste tank is not full, depressurization
valve light off-(if installed).

Circuit breakers to reset:

Steps to clear warning:

Open breaker for 1 seconds, then reset.

Reset duration:

5 seconds.

Results of power up test or reset:

Pass: Lav’s flush normally

Fail: Lav’s won’t flush.

Notes:

CIDS fault light also displayed, troubleshoot thru CIDS. There is also a Toilets page in the
CFDS(page #2) via the MCDU. If Vacuum Generator is inop, toilets will still flush in flight above FL180.

Sign off:

AMM38-31-00-710-002.

Applicable deferrals:

MEL38-30-01=Lavatory Waste Systems.

NO WATER PRESSURE

 Aircraft configuration prior to reset:

Aircraft on ground. water service panel door closed, APU bleed on.

Circuit breakers to reset:

None.

Steps to clear warning:

Check fwd flight attendant panel. Verify WTR SYSTEM DEPRESS pushbutton is not illuminated.

Reset duration:

30 seconds.

Results of power up test or reset:

Pass: Water pressure is normal.

Fail: No water pressure.

Notes:

Verify the water servicing access door is closed and servicing valve is also closed. Not all aircraft
have the “WTR SYST DEPRES” button installed on FWD FAP.

Sign off:

TSM38-41-00-810-801.

Applicable deferrals:

MEL38-10-01=Potable Water Systems.

CHAPTER 38‐CIRCUIT BREAKER LOCATION

|Designation|Location|Panel|

All CIRCUIT BREAKERS ARE ON THE 2000VU/2001VU
TROUBLE LOADING ATSU SOFTWARE

 Aircraft configuration prior to reset:

Aircraft on ground.

Circuit breakers to reset:

None.

Steps to clear warning:

After loading 20TX, must disconnect loader for 3 minutes prior to loading 22TX, and again prior to
loading 24TX.

Reset duration:

N/A.

Results of power up test or reset:

Pass: Software loads.

Fail: Software will not load.

Notes:

Must load ATSU in order, 20TX, 22TX, 24TX. Adhere to manual loading procedure.

Sign off:

AMM46-21-00-740-001.

Applicable deferrals:

MEL23-24-01=ACARS.
MEL46-21-01=ATSU.
ATSU IS LOCKED UP ON THE MCDU

 Aircraft configuration prior to reset:

Aircraft on ground.

Circuit breakers to reset:

Steps to clear warning:

Open associated breakers for 5 seconds, then close. If this does not work pull and reset these
circuit breakers (49VU-MCDU#1/B01)+(49VU SDAC#1/F04)+(49VU FWC#1/F01)+(121VU
CFDIU/J18) (121VU VHF#3/L05)+(121VU MCDU#2/N20)+(121VU FWC#2/Q07)

Reset duration:

Approx. 2 minutes.

Results of power up test or reset:

Pass: ATSU selectable.

Fail: ATSU not selectable.

Notes:

Here you go Lukas!.

Sign off:

AMM46-21-00-740-001.
Applicable deferrals:
MEL23-24-01=ACARS.
MEL46-21-01=ATSU.

CHAPTER 46‐CIRCUIT BREAKER LOCATION

|Designation|Location|Panel|

|ATSU 1 | L16 | 121VU

|ATSU 1/SWTG | L15 | 121VU
Honeywell 131-9(A) APU T/S DATA
 No Start "Auto Shutdown" Message:

(No Acceleration) Reason-Apu Speed < %7 for 30 seconds.

o Action #1 = Restart with both A/C battery switches "ON" prior to master switch "ON".
o Action #2 = Verify APU rotates freely, if so R/R starter motor(8KA).
o Action #3 = If APU does not rotate freely (independent of the starter motor) R/R APU.
o General info = If A/C batteries are selected "ON" after the master switch is selected
"ON", possible no acceleration auto shutdown can occour, restart with A/C batteries "ON" first.

(No Acceleration) Reason-Accel < 0.1-0.5% for 15-60 seconds.

o Action #1 = Verify APU rotates freely. If so bleed the fuel line and perform a restart.
o Action #2 = If the auto shut down continues, R/R starter motor(8KA).
o Action #3 = If the auto shut down continues, R/R the Fuel Control Unit.
o General info = Subsequent "No Flame" and "Underspeed" auto shut downs can occur if
no T/S action is taken.
o CAUTION: LIMIT APU STARTS TO 3/HR, OTHERWISE STARTER MOTOR
DAMAGE CAN OCCUR.

No Flame.

o Action #1 = Bleed the fuel line and preform a restart.

o Action #2 = If the auto shut down continues R/R Ignition Exciter(P10).
o General info = Subsequent "No Flame" and "Underspeed" auto shut downs can occur if
no T/S action is taken.
o CAUTION: LIMIT APU STARTS TO 3/HR, OTHERWISE STARTER MOTOR
DAMAGE CAN OCCUR.

On Speed "Auto Shutdown" Message:

Emergency.

o Action #1 = Inspect 108VU panel for water ingestion and contamination of "APU
EMERGENCY SHUT DOWN" button (1KL). R/R 108VU panel per AIRBUS SB A320-92-1011.

Clogged Oil Filter.

o Action #1 = Inspect mag plug for metal contamination R/R lube and generator filter
elements.
o Action #2 = If auto shut down continues, R/R both differential pressure switches.
o Action #3 = If metal contanimation found on mag plug and auto shut down continues,
R/R APU.
o General info = Oil brand changes have been linked to filter clogging auto shutdowns.
(no adverse inpact to APU).

Overtemperature (High temp onspeed or high temp on droop)

o Action #1 = Most Overtemp auto shut downs are due to E/C-(engine cooling) shroud
delamination failures.
o Action #2 = If shroud is delamed, replace the shroud.
o Action #3 = If shroud is ok and auto shut downs continue, R/R APU.

Low Fuel Pressure.

o Action #1 = If the fault is in conjunction with an auto shut down(No Flame/No

Acceleration/or Underspeed) see ASD T/S recommendations above.
o Action #2 = If the fault continues however the APU still starts, R/R A/C Fuel Pressure
Switch(5030QM).
o Action #3 = If the fault continues, check for possible defects with the A/C Fuel Pressure
Switch (7QC). APU Fuel Pump, or Air Release Valve.
o CAUTION: LIMIT APU STARTS TO 3/HR, OTHERWISE STARTER MOTOR
DAMAGE CAN OCCUR.

No, Low, or Fluctuating Bleed Air Pressure:

No Air.

o Action #1 = If no APU LRU faults are found in the CFDS, restart APU and verify bleed
air operations in ECS 2-Pack mode.
o Action #2 = If NO AIR continues, R/R A/C Bleed Switch.
o General info = Most "NO AIR" defects should have a Faulted LRU observed in the
CFDS last leg reports.

FCN (Fault Code Number) = TSM Task.

(007, 008, 009, 010)=TSM49-70-00-810-816.

(016, 017, 018, 019)=TSM49-00-81-810-853.

(026, 027, 028, 029)=TSM49-00-81-810-854.

(031)=TSM49-00-81-810-852.

(076, 077, 215)=TSM49-00-81-810-835.

(079)=TSM49-00-81-810-802/806/813/824/836.

(081, 082)=TSM49-00-81-810-858.

(083)=TSM49-00-81-810-811/840.

(088, 096, 097)=TSM49-00-81-810-861.

(089, 091)=TSM49-00-81-810-856.

(099, 245)=TSM49-00-81-810-818/820/867.

(100)=TSM49-00-81-810-808/822/839.

(102)=TSM49-00-81-810-849.

(105, 106, 107)=TSM49-00-81-810-807/823/857.

(109, 110)=TSM49-00-81-810-851.

(113, 114)=TSM49-00-81-810-834.

(120)=TSM49-00-81-810-832.

(123)=TSM49-00-81-810-831.

(128, 146)=TSM49-00-81-810-825.

(204)=TSM49-00-81-810-805.

(205)=TSM49-00-81-810-810.

(206)=TSM49-00-81-810-812.

(208)=TSM49-00-81-810-819.

(209)=TSM49-00-81-810-821.

(211)=TSM49-00-81-810-829.

(212)=TSM49-00-81-810-830.

(215)=TSM49-00-81-810-835.

(216)=TSM49-00-81-810-847.

(218)=TSM49-00-81-810-850.

(240,241,242,243,244)=TSM49-00-81-810-821.
CFDS Diagram:
APU WILL NOT START

 Aircraft configuration prior to reset:

Aircraft on ground.

Circuit breakers to reset:

None.

Steps to clear warning:

Verifey both batteries are on, “FLAP OPEN” is displayed on APU page after APU master switch is
selected.

Reset duration:

N/A.

Results of power up test or reset:

Pass: APU Starts.

Fail: APU will not start.

Notes:

If APU still wont start, check CFDS/APU/T-S DATA.

Sign off:
AMM49-00-00-710-008.
Applicable deferrals:
MEL49-10-01=APU System.

APU WONT SHUT DOWN

 Aircraft configuration prior to reset:

No specific.

Circuit breakers to reset:

Steps to clear warning:

Open identified circuit breakers, APU will shut down.

Reset duration:

N/A

Results of power up test or reset:

Pass: N/A.
Fail: N/A.

Notes:

Troubleshoot fault per TSM.

Sign off:

AMM49-00-00-710-008.

Applicable deferrals:

MEL49-10-01=APU System.

APU BLEED FAULTS

 Aircraft configuration prior to reset:

No specific.

Circuit breakers to reset:

Steps to clear warning:

Shut down APU. Open above circuit breakers for 3 seconds, then reset.

Reset duration:

30 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

No notes at this time.

Sign off:

TSM36-12-00-810-801.
AMM49-00-00-710-001 (ECB self test).

Applicable deferrals:

MEL36-12-01=APU Bleed Air System.

APU ELECTRICS, NO VOLTS OR FREQS

 Aircraft configuration prior to reset:

Aircraft on ground, engines stopped.

Circuit breakers to reset:

Steps to clear warning:

Select APU ELEC OFF and reset back to ON. If no help, reset above circuit breaker.

Reset duration:

30 mirco-seconds

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

No notes at this time.

Sign off:

AMM24-41-00-740-002 (GPCU test).

Applicable deferrals:

MEL24-20-02=APU Generator Channel.

CHAPTER 49‐CIRCUIT BREAKER LOCATION
|Designation|Location|Panel|

1KD |APU/ECB/SPLY | L41 | 121VU

2KD |APU/APU/CTL | L42 | 121VU

1KT |APU/OIL/HTR/SPLY | K41 | 121VU
COCKPIT DOOR FAULT

 Aircraft configuration prior to reset:

Aircraft on ground.

Circuit breakers to reset:

Steps to clear warning:

Open associated circuit breakers for 5 seconds, then reset. If no help, check for faults on the
overhead door controller.

Reset duration:

5 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

Overheaddoorcontroller.
Sign off:
AMM52-51-00-710-001.
Applicable deferrals:
MEL52-50-01=DoorLockSolenoid.
MEL52-50-02=Door Locking System.
CABIN DOOR PRESSURE LIGHT FLASHING
 Aircraft configuration prior to reset:

Aircraft on ground, engines shut down, door disarmed, no risidual cabin pressure on board.

Circuit breakers to reset:

Steps to clear warning:

Try reseting above circuit breaker, if no help T/S by removing the connector from the 14WN
pressure switch in FWD E&E. If light extingishes change switch.

Reset duration:

5 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

Light normally flashes when both engines are shut down, the associated slide is disarmed and
cabin pressure is greater then .036 PSI.

Sign off:

TSM52-73-00-810-801.

Applicable deferrals:

MEL52-70-02=Cabin Pressure Light On Door.

HYD PUMP DOESN’T STOP WITH CARGO DOOR OPS.
 Aircraft configuration prior to reset:

Aircraft on ground.

Circuit breakers to reset:

Steps to clear warning:

Open above circuit breaker for 5 seconds, then reset If no help check the LGCIU for faults. (Could
be the time delay relay 6MJ).

Reset duration:

5 seconds.

Results of power up test or reset:

Pass: Fault clears.

Fail: Fault remains.

Notes:

No notes at this time.

Sign off:

AMM52-30-00-860-001.

Applicable deferrals:

MEL52-30-04=Cargo Door Elec. Opening System.

CHAPTER 52‐CIRCUIT BREAKER LOCATION
|Designation|Location|Panel|

|DOORS/CARGO | T12 | 122VU

|DOORS/PAX/MONG | T13 | 122VU

|EIS/SLIDES/ARM AND WARN/GND | P10 | 121VU

|EIS/SLIDES/ARM AND WARN/FLT | P11 | 121VU
ENGINE 1(2) OVERSPEED

 Aircraft configuration prior to reset:

No specific

Circuit breakers to reset:

None.

Steps to clear warning:

Read the specific data report from the MCDU=(CFDS/INST/EIS1/XLOAD(optional)/ENGINE).

Reset duration:

N/A.

Results of power up test or reset:

Pass: N/A.
Fail: N/A.

Notes:

If the valve of one of these parameters is higher than the max limit, the report also shows how long
(in seconds) the associated parameter was at that limit. If no overlimit condition occured, there is no
time indication.

CFM=N1 speed >104 and N2 speed >105 will require inspections. T/S per TSM

V2500=N1/N2=100% 5465RPM/14,915RPM will require inspections.

You can reset these values if necessary. Push the line key adjacent to the “RESET MAX VALUES”
then “CONFIRM RESET” indications.

Sign off:

CFM=TSM73-00-00-810-850.
V2500=AMM71-00-00-860-010.

Applicable deferrals:

No MEL.
ENGINE 1(2) OVERSPEED PROTECTION FAULT V2500

 Aircraft configuration prior to reset:

Overspeed Protection Fault identified by FMU/HC/EEC1/2 on PFR with fault code "OSFFMU".

Circuit breakers to reset:

None.

Steps to clear warning:

Read the FADEC fault codes shown in the FLIGHT DATA and GROUND DATA sections. If you
have fault code "OSFFMU" attempt to clear the overspeed protection fault as follow's. All other fault
codes trouble shoot iaw TSM.

1. On the 50VU, push the ENG FADEC GRD PWR pushbutton switch and release it again. (Resets
FADEC)

2. Push INT mode key on the MCDU and enter a new flight number.

3. Start the engine and run at idle for 4 minutes with engine generator on, then turnoff associated
engine generator for 1 minute.

4. Shutdown the engine, and if there are no ECAM/PFR faults, return to service.

5. If fault code OSFFMU continues, repeat above steps, If fault still wont clear, check "B" and "C"
contectors (Pins J/H) on FMU. Also check "J5" and "J11" contectors (Pins J/d) at EEC. Check TSM for
torque motor resistance valves.
Reset duration:

N/A.

Results of power up test or reset:

Pass: Return to service.

Fail: Repeat above steps until cleared.

Notes:

There is no limit to the number of times you may perform this procedure, and can be performed by
the crew after pushback without delaying the flight as long as the ecam message clears.
Sign off:
SupplementtoTSM73-22-00-810-851.
Applicable deferrals:
No MEL.
ENGINE 1(2) EGT OVERLIMIT

 Aircraft configuration prior to reset:

No specific

Circuit breakers to reset:

None.

Steps to clear warning:

Read the specific data report from the MCDU=(CFDS/INST/EIS1/XLOAD(optional)/ENGINE).

Reset duration:

N/A.

Results of power up test or reset:

Pass: N/A.
Fail: N/A.

Notes:

Check history, if more than 5 hits within the first 25 cycles of the first hit, the exceedance condition
must be idenified.

You can reset these values if necessary. Push the line key adjacent to the “RESET MAX VALUES”
then “CONFIRM RESET” indications.

Sign off:

CFM=TSM73-00-00-810-849, AMM72-00-00-200-008.

V2500=TSM73-22-00-810-861, AMM71-00-00-710-014.

Applicable deferrals:

No MEL.

ENGINE 1(2) FADEC A(B) CHANNEL FAULT

 Aircraft configuration prior to reset:

Aircraft on ground, engines stopped.

Circuit breakers to reset:

Steps to clear warning:

Select ECU’s off, then on using pushbuttons. If no help, open associated breaker for 1 second,
then reset.

Reset duration:

2 seconds.

Results of power up test or reset:

Pass: Fault Clears

Fail: Fault remains.

Notes:

No notes at this time.

Sign off:

AMM73-29-00-710-040.
Applicable deferrals:
No MEL.

ENGINE 1(2) EIU MAINTENANCE STATUS

 Aircraft configuration prior to reset:

Aircraft on ground, engines stopped.

Circuit breakers to reset:

Steps to clear warning:

Open associated breaker for 1 second, then reset.If no help, perform FADEC (A/B) bite test.

Reset duration:

2 seconds.

Results of power up test or reset:

Pass: Fault Clears

Fail: Fault remains.

Notes:

If associated with fault message check 17(16)HB circuitry or EIU 1(2), can be caused by failed flow
control valve or relay 16HB(17HB), pack closure relay.

Sign off:

AMM73-29-00-710-040.
Applicable deferrals:
MEL71-00=Class 2 Message.
ENGINE 1(2) FADEC FAULT

 Aircraft configuration prior to reset:

Aircraft on ground, engines stopped, ECU’s powered.

Circuit breakers to reset:

Steps to clear warning:

Select ECU’s off, then on using pushbuttons. If no help, open associated breaker for 1 second,
then reset.

Reset duration:

2 seconds.

Results of power up test or reset:

Pass: Fault Clears

Fail: Fault remains.

Notes:

HPTCC VLV(POS), HMU or TCC faults not confirmed on FADEC test are spurious.

Sign off:

AMM73-29-00-710-040.

Applicable deferrals:

NO MEL.

ENGINE 1(2) EPR MODE FAULT MESSAGE V2500

 Aircraft configuration prior to reset:

No specific

Circuit breakers to reset:

None.
Steps to clear warning:
Recovery of EPR on both engines may be attemped by switching off each engine’s N1 mode
switch.

Reset duration:
N/A.
Results of power up test or reset:
Pass: N/A.
Fail:N/A.
Notes:
If EPR was fluctuating, check PFR for associated failures.P2/T2 or P5 failures = check associated
linesforleaks.
Sign off:
AMM73-22-00-710-040.
Applicable deferrals:
No MEL.

ENG 1(2) IGN A+IGNB FAULT
OR ENG1(2) FADEC A(B) FAULT.

COMPUTER :FADEC & EIU

C/B RESET:

FOR ENG 1 (ON PANEL 49VU ) A04 (0N PANEL 121VU) R12

FOR ENG 2 (ON PANEL 49VU) A05 (ON PANEL 121VU) R41

LOSS OF N1 VIB & N2 VIB INDICATION S FOR ENG 1(2) IN ECAM SD:

COMPUTER ::: EVMU

C/B RESET:

ON PANEL 121VU OPEN THE C/B R44 FOR 5 SEC THEN CLOSE.

CHAPTER 73‐CIRCUIT BREAKER LOCATION
|Designation|Location|Panel|

|ENG1/REV/LOCK | N44 | 121VU

|ENG2/REV/LOCK | N45 | 121VU

|ENGINE/ENG1/OIL/QTY | N39 | 121VU

|ENGINE/ENG2/OIL/QTY | N41 | 121VU

|ENGINE/ENG1/OIL/PRESS/AND REV SNSR/CHAN A | N40 | 121VU

|ENGINE/ENG2/OIL/PRESS/AND REV SNSR/CHAN A | N42 | 121VU

|ENGINE/ENG1 AND 2/EVMU | R44 | 121VU

|ENGINE/1 AND 2/IGN/SYS A | A03 | 49VU

|ENGINE/IGN/ENG1/SYS A BAT | P39 | 121VU

|ENGINE/IGN/ENG2/SYS A BAT | P40 | 121VU

|ENGINE/IGN/ENG1/SYS B | P41 | 121VU

|ENGINE/IGN/ENG2/SYS B | P42 | 121VU

|ENGINE/1/HP FUEL SOV | A01 | 49VU

|ENGINE/2/HP FUEL SOV | A02 | 49VU

|ENGINE/1/FADEC A/AND EIU 1 | A04 | 49VU

|ENGINE/2/FADEC A/AND EIU 2 | A05 | 49VU

|ENGINE/ENG1/FADEC B/AND EIU 1 | R41 | 121VU

|ENGINE/ENG2/FADEC B | Q40 | 121VU
THRUST REV FAULT AT ENGINE SHUTDOWN

 Aircraft configuration prior to reset:

No specific

Circuit breakers to reset:

None.

Steps to clear warning:

Warning will clear on its own within 5 minutes.

Reset duration:

N/A.

Results of power up test or reset:

Pass: N/A.
Fail: N/A.

Notes:

No troubleshooting required if warning is generated at engine shutdown.

Sign off:

CFM=AMM78-31-00-710-042.
V2500=AMM78-31-00-710-042.

Applicable deferrals:

MEL78-30-01=Thrust Reverser Systems.

THRUST REV TEST THRU MCDU WON’T PASS

 Aircraft configuration prior to reset:

Aircraft on ground.

Circuit breakers to reset:

None.

Steps to clear warning:

Test thrust reversers with engines running.

Reset duration:

N/A.

Results of power up test or reset:

Pass: N/A.
Fail: N/A.

Notes:

See TSM 78-00-00-810-802, Thurst reverser test without CFDS, Engines running.

Sign off:

AMM78-31-00-710-04301. (Test with engines running)

Applicable deferrals:

MEL78-30-01=Thrust Reverser Systems.

THRUST REV FAULT AT ENGINE START

 Aircraft configuration prior to reset:

Aircraft on ground.

Circuit breakers to reset:

None.

Steps to clear warning:

 Shut down engine. Put engine mode select switch to IGN, wait 15 seconds, then back to norm.
If no faults, start engines.

Reset duration:

N/A.

Results of power up test or reset:

Pass: N/A.
Fail:N/A.
Notes:
To prevent fault, select FADEC’s on from the 50VU maintenance panel prior to mode select switch
toIGN.
Sign off:
CFM=AMM78-31-00-710-042.
V2500=AMM78-31-00-710-042.
Applicable deferrals:
MEL78-30-01=Thrust Reverser Systems.

CHAPTER 78‐CIRCUIT BREAKER LOCATION
|Designation|Location|Panel|

|ENG1/REV/LOCK | N44 | 121VU

|ENG2/REV/LOCK | N45 | 121VU

|ENGINE/ENG1/OIL/PRESS/AND REV SNSR/CHAN A | N40 | 121VU

|ENGINE/ENG2/OIL/PRESS/AND REV SNSR/CHAN A | N42 | 121VU

|ENGINE/1/FADEC A/AND EIU 1 | A04 | 49VU

|ENGINE/2/FADEC A/AND EIU 2 | A05 | 49VU

|ENGINE/ENG1/FADEC B/AND EIU 1 | R41 | 121VU

|ENGINE/ENG2/FADEC B | Q40 | 121VU
ENGINE 1(2) OIL FILTER CLOG MESSAGE

 Aircraft configuration prior to reset:

No specific

Circuit breakers to reset:

None.

Steps to clear warning:

 First select FADEC’s on then off to reset memory.

 Check the master chip detector and scavage filters for contamination.
 Then run engine at idle making sure the oil filter clog message doesn’t appear.
 Recheck chip detector and filter again.

Reset duration:

N/A.

Results of power up test or reset:

Pass: N/A.
Fail: N/A.

Notes:

This message could appear momentarily if OAT is below freezing.

Sign off:

CFM=TSM79-00-00-810-820.
V2500=TSM79-30-00-810-803.

Applicable deferrals:

MEL79-35-01=Engine Oli Filter Clog Message.

CHAPTER 79‐CIRCUIT BREAKER LOCATION
|Designation|Location|Panel|

|ENGINE/ENG1/OIL/QTY | N39 | 121VU

|ENGINE/ENG2/OIL/QTY | N41 | 121VU

|ENGINE/ENG1/OIL/PRESS/AND REV SNSR/CHAN A | N40 | 121VU

|ENGINE/ENG2/OIL/PRESS/AND REV SNSR/CHAN A | N42 | 121VU

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