Airbus a320 Fault Verification Guide

FAULT VERIFICATION GUIDE ATA PROBLEM OR MESSAGE CIRCUIT BREAKERS TO RESET

21 VENT AVIONICS FAULTS

122 VU Y17 AVNCS VENT MONG IF NO HELP, THEN RESET: 49 VU D5 AVNCS VENT CTL 49 VU D6 AVNCS VENT CTL Reset circuit breaker(s) in accordance with the following procedure

ATA: 21 AFFECTED COMPUTER: AEVC

1-CONDITIONS OF POWER-UP TESTS INITIALIZATION

HOW LONG THE COMPUTER MUST BE DE-ENERG1ZED: 1 SEC. A/C CONFIGURATION:

A/C ON GROUND AND BLOWER AND EXTRACT PUSH-BUTTONS ON VENTILATION PANEL: - AUTO DITCHING PUSHBUTTON: -OFF

2-PROGRESS OF POWER-UP TESTS

DURATION: 85 SEC. FLIGHT DECK EFFECTS:

BLOWER AND EXTRACT LOCAL FAULTS SMOKE ATGEN1 LINE SKIN VALVES MOVING TO FULLY OPEN POSITION

3-RESULTS OF POWER-UP TESTS

TESTS PASS: ABOVE MENTIONED FAULT MESSAGES NO LONGER DISPLAYED

TESTS FAIL: (FAULT CONFIRMED)

PROCEED TO MEL/TSM FOR DEFERAL/TROUBLESHOOTING


21

VENT AVIONICS EXTC FAULTS

122 VU Y17 AVNCS VENT MONG IF NO HELP, THEN RESET: 49 VU D5 AVNCS VENT CTL 49 VU D6 AVNCS VENT CTL IF NO HELP,THEN RESET: 123 VU AE2 AVNCS VENT EXTC FAN Reset circuit breaker(s) in accordance with the following procedure

ATA: 21

AFFECTED COMPUTER: AEVC


HOW LONG THE COMPUTER MUST BE DE-ENERGIZED: 1 SEC A/C CONFIGURATION:

A/C ON GROUND AND BLOWER AND EXTRACT PUSH-BUTTONS ON VENTILATION PANEL: AUTO DITCHING PUSH-BUTTON: OFF

2-PROGRESS OF POWER-UP TESTS DURATION: 85 SEC. FLIGHT DECK EFFECTS:

BLOWER AND EXTRACT LOCAL FAULTS SMOKEATGEN1UNE SKIN VALVES MOVING TO FULLY OPEN POSITION

3-RESULTS OF POWER-UP TESTS TESTS PASS: ABOVE MENTIONED FAULT MESSAGES NO LONGER DISPLAYED




21

COND TRIM AIR FAULT AND MSG “TRIM AIR III PR”

DISREGARD IF THE WARNING AND MSG “TRIM AIR III PR” IS TRIGGERRED WHEN ALL TRIM AIR VALVES ARE CLOSED REF FLT MANUAL 7-60





FAULT VERIFICATION GUIDE

ATA PROBLEM OR MESSAGE CIRCUIT BREAKERS TO RESET

21

CABIN TRIM AIR VALVE MSG

122 VU V17 ZONE TEMP CTL 115 VAC SYS 1 122 VU V18 ZONE TEMP CTL 115 VAC SYS 2 122 VU V19 ZONE TEMP CTL 28 VDC SYS 1 122 VU V20 ZONE TEMP CTL 28 VDC SYS 2 Reset circuit breaker(s) in accordance following procedure

ATA: 21 AFFECTED COMPUTER: ZONE CONTROLLER


HOW LONG THE COMPUTER MUST BE DE-ENERGIZED: 200 MS

A/C CONFIGURATION: A/C ON GROUND BOTH PACK SELECTED: - OFF FLOW CONTROL VALVE3; - CLOSED

NOTE: BOTH PACK CONTROLLERS ENERGIZED AND HAVING FINISHED THEIR

POWER-UP TESTS PLUS 5 SEC. DELAY FOR CONFIRMATION


DURATION: 38 SEC FLIGHT CHECK EFFECTS: 3 TRIM AIR VALVES ARE MOVING FROM COOL TO HOT AND FROM HOT TO COOL







22

AUTO FLT A/THR LIMITED WARNING MSG

MSC IS DISPLAYED WHEN AUTO THR ENGAGED AND THE THROTTLES ARE BELOW THE CL DETENT. MOVE THROTTLES PER FLT MANUAL 7-50

22

AUTO FLT A/THR OFF MSG

UPPER ECAM MSG AFTER ENGINE START AND BEFORE T.O. THRUST IS APPLIED (ON THE GROUND). THIS MSG SHOULD BE DISREGARDED BY FLIGHT CREWS PER FLT MANUAL 7-50






ATA: 22 AFFECTED COMPUTER: FCU


HOW LONG THE COMPUTER MUST B£ DE-ENERGI2ED: > 7 MIN ON BOTH FCU'S A/C CONFIGURATION:

A/C ON GROUND 2-PROGRESS OF POWER-UP TESTS


ECAM STATUS PAGE: - FCU 1+2INOP- AP 1+2INOP- A/THR INOP 3-RESULTS OF POWER-UP TESTS





22

FCU FAULTS

49 VU B5 FCU1 121 VU M21 FCU 2 Reset circuit breaker(s) in accordance with the following procedure


ATA: 22 AFFECTED COMPUTER: FMGC


HOW LONG THE COMPUTER MUST BE DE-ENERGIZED: > 4 SEC. A/C CONFIGURATION:

A/C ON GROUND WITH ENGINES STOPPED


DURATION: 120 SEC, FLIGHT DECK EFFECTS:

ECAM STATUS PAGE: AP 1(2) INOP 3-RESULTS OF POWER-UP TESTS





22

FMGC MSG "OPPOSITE FM IN PROGRESS OF FMA SHOWS OFFSIDE FD'S"

49 VU B2 FMCC I 121 VU M17 FMGC 2 Reset circuit breaker(s) In accordance with The Procedure

FAULT VERFICATION GUIDE

ATA; 22 AFFECTED COMPUTER: FMGC



A/C ON GROUND 2- PROGRESS OF POWER-UP TESTS DURATION: 120 SEC, FLIGHT DECK EFFECTS:

ECAM STATUS PAGE: AP 1(2) INOP

3- RESULT OF POWER-UP TESTS

TEST PASS: ABOVE MENTION FAULT MESSAGES NO LONGER DISPLAYED TESTS FAIL :( FAULT CONFIRMED): PROCEED TO MEL/TSM FOR DEFERAL/TROUBLESHOOTING


22

FMGC MSG "SET OFFSIDE RANGE MODE"

49 VU B2 FMGC 1 121 VU M17 FMGC 2 Reset circuit breaker(s) in according with the following procedure.


ATA; 22 AFFECTED COMPUTER: FMGG

1-CONDITIONS OF POWER –UP TEST INTIALIZATION

HOW LONG THE COMPUTER MUST BE DE-ENERGIZED:.4 SEC A/C CONFIGURATIONS:


2-PROGRESS OF POWER-UP TEST

DURATION: 120 SEC. FLIGHT DECK EFFECTS;




TESTS FAIL :( FAULT CONFIRMED)



22

AUTO PILOT # 1FAULT

49 VU B2 FMGC 1 Reset circuit breaker(s) in accordance with the following procedure.


ATA: 22 AFFECTED COMPUTER: FMGC


HOWLONG THE COMPUTER MUST BE DE-ENERGIZED: > 4 SEC. A/C CONFIGURATION:



DURATION: 120 SEC FLIGHT DECK EFFECTS:







22

AUTO PILOT # 2FAULT

121 VU M17 FMGC 2 Read circuit breaker(s) in accordance with the following procedure.


ATA: 22 AFFECTED COMPUTER: FAC


HOW LONG THE COMPUTER MUST BE DE-ENERGIZED :> 4 SEC A/C CONFIGURATION;

1. A/C ON GROUND AND ENGINES STOPPED FOR ELECTRICAL POWER-UP TESTS,

2. A/C ON GROUND AND HYORAUUCALLY ENERGIZED FOR YAW DAMPER POWER LOOP POWER-UP TESTS


DURATION: 1.-90 SEC. 2.-5 SEC.

FLIGHT DECK EFFECT: AUTO FLT RUDDER TRIM 1(2) AUTOFLT RUD TRAV LIM 1(2) AUTO FLT RUDDER TRIM 1(2) AUTO FLT YAW DAMPER 1(2)

FLT CTL PANEL: - "FAULT1”LEGEND FLASHES ON FAC 1 PUSHBUTTON






22

FAC FAULTS SYSTEM #1

RESET FAC 1 PUSHBUTTON SWITCH IF NO HELP, THEN RESET: 49 VU B3 FAC1 26 VAC 49 VU B4 FAC1 28 VDC Reset circuit breaker(s) in accordance with the following procedure




HOW LONG THE COMPUTER MUST BE DE-ENERGIZED> 4 SEC A/C CONFIGURATION:

1.A/C ON GROUND AND ENGINES STOPPED FOR ELECTRICAL POWER-UP TESTS,

2.A/C ON GROUNQ AND HYDRAULICALLY ENERGIZED FOR YAW DAMPER POWER LOOP POWER-UP TESTS

2-PROGRESS OF POWER-UP TESTS;

DURATION: 1:- 90 SEC. 2:- 5 SEC.

FLIGHT DECK EFFECT: AUTO FLT RUDDER TRIM 1(2) AUTO FLT RUD TRAV LIM 1(2) AUTO FLT RUDDER TRIM 1(2) AUTO FLT YAW DAMPER 1(2)

FLT CTL PANEL: - FAULT LEGEND FLASHES ON FAC 2 PUSHBUTTON

3-RESULTS OF POWER UP TESTS:



PROCEED TO MEL/TSM FOR DEFERAL/TROUBLE SHOOTING


22

FAC FAULTS SYSTEM #2

RESET FAC 1 PUSHBUTTON SWITCH IF NO HELP, THEN RESET: 49 VU B3 FAC 1 26VAC 121 VU M19 FAC2 28VDC Reset circuit breaker(s) in accordance with the following procedure




HOW LONG THE COMPUTER MUST BE DE-ENERGIZED :> 4 SEC A/C CONFIGURATION:


2.A/C ON GROUND AND HYORAULICALLY ENERGIZED FOR YAW DAMPER POWER LOOP POWER-UP TESTS


DURATION: 1.-90 SEC. 2- 5 SEC.

FLIGHT DECK EFFECT: AUTO FLT RUDDER TRIM 112) AUTO FLT RUD TRAV LIM 1 (2) AUTO FLT RUODER TRIM 1(2) AUTO FLT YAW DAMPER 1(2)

FLT CTL PANEL: - "FAULT1 LEGEND FLASHES


TESTS PASS: ABOVE MENTIONED FAULT MESSAGES NO LONGER DISPLAYEO


PROCEED TO MEL/TSM FOR DEFERAL/TROUBLESHOOTING.


22

DUAL CAT 111 MSG

49 VU B4 FAC 1 28 VAC 121 VU M19 FAC 2 28VDC Reset circuit breaker(s) In accordance with the following procedure


ATA: 22

AFFECTED COMPUTER: MCDU


HOW LONG THE COMPUTER MUST BE DE-ENERGIZEO: > 200 MS A/C CONFIGURATION:

A/C ON GROUND


DURATI0N:4 SEC. FLIGHT DECK EFFECTS:

MCDU SCREEN IS BLANK

3-RESULTS OF POWER-UP TESTS:



PROCEED TO MEL/TSM FOR DEFERAL/TROU8LESHOOTING


22

MCDU FAULT SYSTEM # 1

49 VU B1 MCDU 1 Reset circuit breaker(s) in accordance with the following procedure


ATA; 22 AFFECTED COMPUTER: MCDU


HOW LONG THE COMPUTER MUST BE DE ENERGIZED: > 200 MS A/C CONFIGURATION:

A/C ON GROUND



MCDU SCREEN IS BLANK




PROCEED TO MEL/TSM DEFERAL / TROUBLESHOOTING.


22 MCDU FAULT SYSTEM # 2.

121 VU N20 MCDU 2 Reset circuit breaker(s) in accordance with the following procedure







22

AUTO FLT RUD TRV LIM SYS FAULT MSG

RESET FAC 1 AND FAC 2 PUSHBUTTON SWITCHES

FAULT VERJFICATION GUIDE



HOW LONG THE COMPUTER MUST BE DE-ENERGIZED : > 4 SEC A/C CONFIGURATION:

1. A/C ON GROUND AND ENGINES STOPPEO FOR ELECTRICAL POWER-UP TESTS, 2. A/C ON GROUND AND HYDRAULICALLY ENERGIZED FOR YAW

DAMPER POWER LOOP POWER-UP TESTS


DURATION: 1.-90 SEC. 2.. 5 SEC. FLIGHT DECK EFFECT:

AUTO FLT RUDDER TRIM 1(2) AUTO FLT RUD TRAV LIM 1(2) AUTO FLT RUDDER TRIM 1(2) AUTO FLT YAW DAMPER 1(2)

FLT CTL PANEL: • "FAULT LEGEND FLASHES



TESTS FAIL (FAULT CONFIRMED)

PROCEED TO MEL/TSM FOR DEFERAL/ TROUBLESHOOOTING.


22

RUDDER TRAVEL LIMIT SYSTEM # 1.

49 VU B3 FAC1 26VAC 49 VU B4 FAC 2 28VDC IF NO HELP, THEN RESET: 49 VU B2 FMGC 1 (Sec Ch 22, Autopilot #1Fault for procedure) Reset circuit breaker(s) in accordance with the following procedure


ATA: 22

AFFECTED COMPUTER: FAC

1-CONDITIONS OF POWER-UP TESTS INITIALIZATION.


1. A/C ON GROUND AND ENGINES STOPPED FOR ELECTRICAL POWER-UP TESTS, 2.A/C ON GROUND AND HYDRAULICALLY ENERGIZED FOR YAW DAMPER

POWER LOOP POWER-UP TESTS


DURATION: 1.-90 SEC. 2 - 5 SEC. FLIGHT DECK EFFECT:

AUTO FLT RUDDER TRIM 1(2) AUTOFLT RUD TRAV LIM 1(2) AUTO FLT RUDDER TRIM 1(2| AUTO FLT YAW DAMPER 1(2|

FLT CTL PANEL: - "FAULT1 LEGEND FLASHES




‘PROCEED TO MEL/TSM FOR DEFERAL/TROUBLESHOOTING


22

RUDDER TRAVEL LIMIT SYSTEMS # 2

121 VU M18 FAC 2 26VAC VUI21 M19 FAC 2 28VDC IF NO HELP, THEN RESET 121 VU M17 FMGC 2 {See Ch 22, Autopilot #2 Fault for procedure) Reset circuit breaker(s) in accordance with the following procedure


ATA: 23 AFFECTED COMPUTER: CIDS DIRECTOR


HOW LONG THE COMPUTER MUST BE DE-ENERGIZED: 1. 10 SEC; 2. 30 SEC.

A/C CONFIGURATION: 1.A/C ON GROUND WITH BOTH CABIN DOORS CLOSED 2.A/C ON GROUND WITH ENGINES STOPPED AND A CABIN DOOR OPEN


DURATION: 1.-50 SEC. 2.-120 SEC.

FLIGHT DECK EFFECTS: "CIDS 1" ON THEN OFF AFTER 30 SEC. "CIDS 2" ON THEN OFF AFTER 8O SEC. AUDIO CONTROL PANEL: "ATT' LIGHT IS FLASHING

CABIN EFFECTS: 1. CABIN LIGHTS ARE OFF DURING 1 SEC. 2. CABIN LIGHTS AND PAX ATT LIGHTS ARE FLASHING




PROCEED TO MEL/TSM FOR DEFERAL / TROUBLESHOOTING.


23

CIDS SYSTEM FAULTS

ATTEMPT A RESET AT PTP PANEL FIRST IF NO HELP, THEN RESET NOTE:RESET CB.'S TOGETHER 49 VU G2 CID DIR 1 & 2 ESS 121 VU M5 CIDS DIR 1 & 2 NORM Reset circuit breaker(s) In accordance with the following procedure





PROCEED TO MEL/TSM FOR DEFERAL/ TROUBLESHOOTING.


23

FLT ATTD/PNL LOCKED UP

121 VU M14 CIDS FWD ATTND/PNL

23 PAX ENTERTAINMENT NOT TURN ON OR OFF

2000 VU F6 CABIN COM SYS PES IF NO HELP, THEN RESET ALL DEU'S 121 VU M7 THROUGH M13

23 PAX SEAT AUDIO 1NOP

2000 VU F6 CABIN COM SYS PES

23 SEAT VIDEO SYS UNIT PROBLEMS

RESET INDIVIDUAL VIDEO UNIT, SMALL HOLE JUST FWD OF SCREEN ON THE SAME PANEL IS RESET BUTTON (ON-OFF) IF NO HELP TURN OFF TO STOW

23 RMP FAULTS

TURN AFFECTED RMP OFF THEN ON TO RESET


ATA:22 AFFECTED COMPUTER: FMGC












23

ACP FREQ'S WILL NOT CHANGE FROM THE STANDBY TO ACTIVE WINDOWS

TURN AFFECTED RMP OFF THEN ON TO RESET IF NO HELP, THEN RESET 49 VU B2 FMGC 1 121 VU MJ17 FMGC 2 Reset circuit breaker(s) In accordance with the following procedure

FAULT VERFICATION GUIDE



TESTS' FAIL: (FAULT CONFIRMED)



23

TCAS INOP MSG

121 VU KI0 TCAS NOTE SYS TEST THRU MCDU ALSO WORKS

23 COM VHF EMITTING FAULT MSGS

CHECK: -TRANSMISSION KEY AUDIO PANEL-SIDE STICK RADIO SEL -HAND MIKE SEL NOT IN TRANS POSITION IF NOT FOUND IN TRANS RESET 49 VU G9 VHF1 121 VU L4 VHF2 121 VU L5 VHF 3 IF NO HELP LEAVE C.B. OPEN(PULLED) REF FLIGHT MANUAL 7-58

23 VHF SYSTEM INOP

49 VU G9 VHF 1 (SYS 1) 121 VU L4 VHF2 (SYS2) 121 VU L5 VHF3 (SYS3)




TESTS FAIL: (FAULT CONFIRMED) PROCEED TO MEL/TSM FOR DEFERAL/TROUBLESHOOTING


24

ECAM MSG RELATED TO TRIPPED GREEN CB'S

NO REQUIREMENT- HOWEVER, IF TIME PERMITS RESET MAY BE ATTEMPTED, IF UNSUCCESSFUL, DO NOT MAKE A SECOND ATTEMPT FLT MANUAL 7-57


ATA: 24 AFFECTED COMPUTER: GCU

1-CONDITlONS OF POWER-UP TESTS INITIALIZATION

HOW LONG THE COMPUTER MUST BE DE-ENERGIZED: 15 MS A/C CONFIGURATION:

A/C ON GROUND AND ENGINES STOPPED


DURATION: 30 MS FLIGHT DECK EFFECTS: NONE






24

ENGINE 1 (2) GENERATOR ON LINE (GREEN LINE) AND PARAMETERS NOT SHOWN

ENGINE(S) MUST BE SHUT DOWN 122 VU T26 GCU 1 (ENGINE 1) 122 VU T27 GCU 2 (ENGINE 2) Reset circuit breaker(s) in accordance with the Following procedure


ATA: 24 AFFECTED COMPUTER: GPCU


HOW LONG THE COMPUTER MUST BE DE-ENERGIZED: NONE A/C CONFIGURATION:

A/C ON GROUND, ENGINES STOPPED, APU STOPPED GROUND POWER UNIT CONNECTED TO THE A/C






PROCEED TO MEL/ TSM FOR DEFERAL / TROUBLESHOOTING.


24

NO "AVAIL" GREEN LEGEND DISPLAYED ON "EXT PWR" PUSHBUTTON SWITCH

ENGINES AND APU SHUT DOWN AND GROUND POWER CONNECTED 122 VU Y24 GPCU Reset circuit breaker(s) in accordance with the Following procedure







24

BATTERY CHARGE LIMITER (BCL)

RESET SHIPS BATTERIES ONE AT A TIME WITH APU OPERATING IF NO HELP, THEN RESET 105 VU N/A BAT REF BCL1 105 VU N/A BAT BUS REF BCL 1 105 VU N/A BAT REF BCL 2 105 VU N/A BAT BUS REF BCL 2





PROCEED TO MEL/TSM FOR DEFERAL /TROUBLESHOOTING.


24

TRANSFORMER RECTIFIER FAULTS

RESET T/R THROUGH MCDU OR RESET ALL THREE USING GUARDED BUTTON ON 103VU PANEL IN ELECTRICAL BAY







25

CREW SEAT PROBLEMS

122 VU U 1 1 CKPT SEAT CTL CAPT 122 VU U14 CKPT SEAT CTL F/O ADDITIONAL C.B. IS LOCATED UNDER EACH SEAT ON THE CONTROL BOX


ATA: 28 AFFECTED COMPUTER: SDCU



A/C ON GROUND


DURATION: 10 SEC. FLIGHT DECK EFFECTS: NONE



TESTS FAIL: {FAULT CONFIRMED)



26

FWD AND A FT CARGO DETECT MSGS

49 VU C6 SDCU CHAN 1 122 VU T18 SDCU CHAN 2 NOTE: RESET C.B'S TOGETHER IF NO HELP, THEN RESET: 49 VU C6 SDCU CHAN 1 122 VU T18 SDCU CHAN 2 49 VU AFT CARGO VENT & HEAT CTL/ MONC 122 VU S22 AFT CARGO VENT & HTG FAN Reset circuit breaker(s) in accordance with the following procedure


ATA; 21 AFFECTED COMPUTER: CHC


HQW LONG THE COMPUTER MUST DE -ENERGIZED: 200 MS A/C CONFIGURATION:

A/C ON GROUND 2-PRQGRESS OF POWER-UP TESTS







26

FWD AND AFT CARGO DETECT FAULTS

49 VU AFT CARGO VENT & HEAT CTL /MONG 122 VU S22 AFT CARGO VENT & HTG FAN Reset circuit breaker(s) in accordance with the following procedure


ATA: 26

AFFECTED COMPUTER: SDCU

1-CONDITIONS OF POWSR-UP TESTS INITIALIZATION


A/C ON GROUND 2-PROGRESS OF POWER-UP TESTS

DURATION: 10 SEC. . FLIGHT DECK EFFECTS: NONE

3-RE5ULTS OF POWER-UP TESTS





26

LAV SMOKE DETECT MSG

49 VU C6 SDCU CHAN 1 122 VU T18 SDCU CHAN 2 Reset circuit breaker(s) in accordance with the following procedure







27

SIDE STICK PRIORTY MSG

FAC 1 & 2 SWITCHES SEC 1, 2 & 3 SWITCHES ELAC 1 & 2 SWITCHES


ATA: 27 AFFECTED COMPUTER: SEC


HOW LONG THE COMPUTER MUST BE DE-ENERGIZED: 6 SEC. A/C CONFIGURATION:

HYDRAULIC SYSTEM DE-PRESSURIZED

2--PROGRESS OF POWER-UP TESTS


ECAM F/CTL PAGE:: SEC AMBER INDICATION, ASSOCIATED ELEVATORS AMBER CROSSED, ASSOCIATED SPOILERS AMBER CROSSED THEN FLASHING AT THE END OF THE TEST

ECAM WARNING: F/CTL SEC 1(2)(3) FAULT DURING AROUND 23 SEC. FLT CONTROL PANEL: SEC FAULT LEGEND IS

PUSHING AT THE BEGINNING AND AT THE END OF TEST






27

SEC 1, 2 OR 3 FAULTS

USE PUSHBUTTON SWITCHES FIRST IF NO HELP, THEN RESET; 49 VU B8 SEC I NORM SPLY (SEC 1) 105 VU N/A SEC 1 STBY SPI.Y (SEC 1) 121 VU Q18 SEC 2 SPLY (SEC 2) 121 VU Q19 SEC 3 SPLY (SEC 3) Reset circuit breaker(s) in accordance with the following procedure


ATA: 27 AFFECTED COMPUTER: ELAC

1-CONDlTIONS OF POWER-UP TESTS INITIALIZATION;

HOW LONG THE COMPUTER MUST BE DE-ENERGIZED: 30 MS BY C/B OR RESET PUSHBUTTON OFF

THEN ON; A/C CONFIGURATION; HYDRAULIC SYSTEM DE-PRESSURIZED



ECAM F/CTL PAGE: ELAC AMBER INDICATION AND ASSOCIATED AILERON SERVO CONTROL AMBER BOXED ECAM WARNING: F/CTL ELAC 1(2) FAULT DISPLAYED DURING 3 SEC. IF

SUBSEQUENT TO C/B RESET

NOTE: NONE IF SUBSEQUENT TO PUSHBUTTON RESET

FLT CONTROL PANEL: FAULT LEGEND ILLUMINATED DURING 9 SEC.



TESTS FAIL :( FAULT CONFIRMED) PROCEED TO MEL/TSM FOR DEFERAL/TROUBLESHOOTING


27

ELAC1 OR 2 FAULTS

USE PUSHBUTTON SWITCHES FIRST IF NO HELP, THEN RESET; 49 VU Dl 1 ELAC 1 NORM SPLY(ELAC I) 105 VU N/A ELAC 1 STBY SPLY(ELAC 1) 121 VU R20 ELAC 2 NORM SPLY(ELAC 2) 105 VU5 N/A ELAC 2 STBY SPLY(ELAC 2) Reset circuit breaker (s) In accordance with the following procedure



27

FLIGHT CONTROL FLAPS LOCKED OUT

MUST PERFORM WING TIP BRAKE (WTB) RESET THROUGH MCDU PER AMM 27-50-00 PG209-21] (HYD MUST BE OFF )


ATA: 27 AFFECTED. COMPUTER: SFCC

1-CONDITIONS OF POWER-UP TESTS INITIAUZATION

HOW LONG THE COMPUTER MUST BE DE ENERGIZED :> 200 MS A/C CONFIGURATION:

A/C ON GROUND WITH ENGINES STOPPED AND NEW DATE FROM CFDS.


DURATION: < 2 SEC. FLIGHT DECK EFFECTS:

ECAM WARNING: IF HYDRAULIC CIRCUIT PRESSURIZED: FLT CTL SLAT SYS 1(2) OR FLAP SYS 1(2) FAULT IF HYDRAULIC CIRCUIT NOT PRESSURIZED: NONE






27

FLT/CTL MSG WITH SLAT/FLAPS FAULTS

49 VU B6 SLT CTL & MONG SYS 1 49 VU B7 FLP CTL & MONG SYS 1 121 VU R21 SLT CTL SYS 2 121 VU Q21 FLP CTL&MONG SYS 2 Reset circuit breaker(s) in accordance with the following procedure


ATA:27 AFFECTED COMPUTER: FCDC




2-PROGRESS OF POWER-UP TESTS -


ECAM WARNING:F/CTL FCDC 1(2) FAULT' DURING 3 SEC.




PROCEED TO TSM/ MEL FOR DEFERAL/ TROUBLESHOOTING.


27

FLT/CTL MAINTENANCE MSG (CAN BE DEFERRED)

49 VU B10 FCDC 1 SPLY 121 VU Q20 FCDC2 SPLY Reset circuit breaker(s) in accordance with the following procedure


ATA: 27

AFFECTED COMPUTER: SFCC


HOW LONG THE COMPUTER MUST BE DE-Energized :> 200 MS A/C CONFIGURATION:

A/C ON GROUND WITH ENGINES STOPPED AND NEW DATE FROM CFDS.



ECAM WARNING: IF HYDRAULIC CIRCUIT PRESSURIZED: FLT CTL SLAT SYS 1(2) OR FLAP SYS 1(2) FAULT

IF HYDRAULIC CIRCUIT NOT PRESSURIZED; NONE

3 RESULTS OF POWER-UP TESTS





27

SLOW SLATS

49 VU B6 SLT CTL & MONG SYS 1 121 VU R21 SLAT CTL SYS 2 Reset circuit breaker(s) in accordance with the following procedure


ATA: 23 AFFECTED COMPUTER: FQIC

1-CONDITIONS OF POWER-UP TESTS INITIALISATION


AJC ON GROUND AND REFUEL PANEL DOOR OPEN


DURATION: 80 SEC MAXIMUM FIGHT DECK EFFECTS: ECAM FUEL PAGE: INTER-CELL TRANSFER VALVE INDICATION MOVING,

AMBER “XXX" IN PLACE OF FUEL QUANTITY INDICATIONS THEN NORMAL INDICATIONS ARE DISPLAYED






28

FQI INOP

49 VU A13 FQI CHAN1 121 VU M27 FQI CHAN2 121 VU L26 FQI CHAN 1 & 2 Reset circuit breaker(s) in accordance with the following procedure







28

FUEL APU LP VALVE FAULT MSG. TRIGGERED WHEN THE APU MASTER SW IS SELECTEDOFF DURING AN EMER SHUT DOWN OR AUTO SHUT DOWN

CYCLING THE MASTER SWITCH ON THEN OFF MAY CLEAR THIS MSG REFFLT MANUAL 7-114 Reset circuit breaker(s) in accordance with the following procedure.






ATA PROBLEM OR MESSAGE CICUIT BREAKER TO RESET

29

HYD REVS LOW PRESSURE MSG

TO CLEAR: RUN ENGINES OR PRESSURIZE HYDRAULIC RESERVOIRS WITH APU. NOTE: THIS HAPPENS AFTER WORKING ON HYDRAULIC SYSTEM

29

PTU FAULTS (NOT CAUSED BY CARGO DOOR OPERATION AFTER ENGINE STARTS)

121 VU N34 SOL VALVE G/Y PTU


FAULTS CAUSED BY CARGO DOOR OPERATION WITHIN 30 SECONDS AFTER SECOND ENGINE START AND PTU ECAM FAILURE MESSAGES

NOTE:THIS PROCEDURE WILL NOT RESET REAL PTU FAILURES OR HIDE REAL FAULTS IN THE PTU SYSTEM

RESET WITH ENGINES RUNNING:

A) RESET MESSAGE USING MASTER / CAUTION PUSHBUTTON SWITCHES

B) SELECT HYD PAGE ON ECAM C) SELECT YELLOW HYD ELEC. PUMP ON D) SELECT YELLOW HYD ELEC PUMP OFF E) WAIT A MINIMUM OF 30 SECONDS F) CYCLE PTU SWITCH FROM ON. TO OFF

TO ON G) SELECT #1 ENGINE GREEN HYD PUMP

OFF PTU SHOULD OPERATE YELLOW TO GREEN

H) SELECT #1 ENGINE GREEN HYD PUMP ON

I) SELECT #2 ENGINE YELLOW HYD PUMP OFF PTU SHOULD OPERATE GREEN TO YELLOW

J) SELECT #2 ENGINE YELLOW HYD PUMP ON

K) ECAM SHOULD BE NORMAL






29

PTU FAULTS

SEE NOTES THAT FOLLOW REGARDING FAULTS


ATA: 30 AFFECTED COMPUTER: WHC

1-CONDITIONS OF POWER-UP TEST INITIALIZATION


A/C ON GROUND





TESTS FAIL: (FAULT CONFIRMED) .



30

WINDSHIELD HEAT FAULT

122 VU XI3 WHC 1 (LEFT SIDE) 122 VU XI4 WINDOW L HEAT 122 VU WI3 WHC 2 (RIGHT SIDE) 122 VU W14 WINDOWS R HEAT Reset circuit breaker(s) in accordance with the following procedure.







30

FWD (AFT) DRAIN MAST ECAM MSG

2000 VU D1 FWD DRAIN MAST 2001 VU D5 AFT DRAIN MAST







30

ANTI ICE PROBE MSGS SYSTEM #1

49 VU D2 PITOT 1 122 VU Z13 STATIC I 49 VU D4 AOA 1 122 VU Z12 TAT1 IF NO HELP, THEN RESET: 49 VU F7 ADIRU 1 & AOA 1 26VAC 49 VU 49T6ADIRU 1 115VA 105VU N/A ADIRU 1 28VDC

30 ANTI ICE PROBE MSGS SYSTEM # 2

122 VU Y14 PITOT 2 122 VU Y11 STATIC 2 122 VU Y13 AOA 2 122 VU Y15 TAT 2 IF NO HELP, THEN RESET: 121 VU N9 ADIRU 2 26VAC & AOA 121 VU N7 ADIRU 2 115VAC 121VU N5 ADIRU 2 28VDC 121 VU N11 ADIRU 2 PWR SHED

30 ANTI ICE PROBE MSGS SYSTEM # 3

122 VU Z16 PITOT 3 122 VU Z14 STATIC 3 122 VU Z15 AOA 3 IF NO HELP, THEN RESET: 121 VU N8 ADIRU 3 26VAC & AOA 121 VU N6 ADIRU 3 115VAC 121 VU N4 ADIRU 3 28VDC 49 VU F9 ADIRU 3 SYWG SPLY 121 VU N10 ADIRU 3 STWG SPLY


ATA: 31 AFFECTED COMPUTER: DMC

1-CONDITIONS QF POWER-UP TESTS INITIALIZATION

HOW LONG THE COMPUTER MUST BE OE-ENERGIZED: > 1 SEC. A/C CONFIGURATION:

A/C ON GROUND


DURATION: 4 SEC.

FLIGHT DECK EFFECTS:

ECAM WARNING: "EIS DMC 1 OR 2 OR 3 FAULT”

NOTE: A DIAGONAL IS DISPLAYED ON THE THREE ASSOCIATED DISPLAY UNITS.




PROCEED TO MEL / TSM FOR DEFERAL/TROUBLESHOOTING


31

DMC FAULT MSG EIS DMC 1, 2 OR 3.

49 VU E11 EIS DMC 1 SPLY (SYS1) 121 VU Q8 EIS DMC 2 SPLY (SYS 2) 121 VU Q9 EIS DMC 3 SPLY (SYS 3) 49 VU E10 EIS DMC 3 STBY SPLY(SYS 3) Reset circuit breaker(s) In accordance following procedure.





PROCEED TO MEL/TSM FOR DEFERAL/TROUBLE SHOOTING.


31

UNABLE TO SWITCH DU

49 VU E-J EIS PFD CAPTSWTC 49 VU E2 EIS ND CAPT SWTG 121 VU RS EIS PFD F/O SWTG 121 VU R6 EIS ND F/O SWTG 49 VU E6 EIS ECAM DU UPPER SWTG 49 VU E6 EIS ECAM DU UPPER SWTG 121 VU RIO ECAM DU LOWER SWTG


ATA: 31 AFFECTED COMPUTER: AIDS DMU

1-CONDITIONS QF POWER-UP TESTS INITIALIZATION


A/C ON GROUND

2-PROCRESS OF POWER-UP TESTS


ECAM WARNING: NONE

NOTE: A DIAGONAL IS DISPLAYED ON THE THREE ASSOCIATED DISPLAY UNITS


TESTS PASS: AIDS PROMPT RETURNS


PROCEED TO MEL/ TSM FOR DEFERAL/TROUBLESHOOTING


31

NO AIDS INDICATION DISPLAYED ON THE MCDU MENU PAGE

121 VU K15AIDS DMU & QAR


ATA:34 AFFECTED COMPUTER: ADIRU

1-CONDITIONS OF POWER-UP TEST INITIALISATION

HOW LONG THE COMPUTER MUST BE DE-ENERGlZED: 15 SEC. A/C CONFIGURATION:

A/C ON GROUND AND IR 1(2)(3) ROTARY BUTTON (LOCATED ON THE ADIRS PANEL) SWITCHED TO "OFF." FOR 15 SEC, THEN TO "NAV"


DURATION: 5 SEC . FLIGHT DECK EFFECTS:

ADIRS PANEL: "ON BAT" LEGEND ILLUMINATED FOR 5 SEC, 2 SEC. AFTER POWER-UP TEST INITIALIZATION






31

ADIRU FAULT

49 VU F6 ADIRU 1 115VAC (SYS 1) 105 VU ADIRS ADIRU 1 28VDC (SYS1) 121 VU N7 ADIRU 2 115VAC(SYS 2) 121 VU N5 ADIRU 2 28VDC(SYS 2) 121 VU N6 ADIRU 3 115VAC(SYS 3) 121 VU N4 ADIRU 3 28VDC (SYS 3) Reset circuit breakers in accordance with the following procedure.


ATA: 31 AFFECTED COMPUTER: FWC

1-CONDITIONS OF POWER-UP TESTS INITIALIZATION HOW LONG THE COMPUTER MUST BE DE-ENERGIZED: > 1 SEC. A/C CONFIGURATION:

A/C ON GROUND

2- PROGRESS OF POWER-UP TESTS


ECAM WARNING: "EIS 1(2) FWS FAULT

3-RESULT OF POWFR-UP TESTS

TE'STS PASS: ABOVE MENTIONED FAULT MESSAGES NO LONGER DISPLAYED




31

ECAM PAGE(S) LOCKED (I.E DOORS-WHEELS ETC.)

49 VU F1 FWS FWC 1 SPLY 121 VUQ7 EIS FWC2 SPLY Reset circuit breaker(s) in accordance with the following procedure.


ATA: 31 AFFECTED COMPUTER: SDAC



A/C ON GROUND



ECAM WARNING “EIS 1(2) SDAC FAULT”






31

SDAC 1 OR 2 FAULTS

49 VU F2 SDAC 1 26 VAC SYNC AC ESS BUS 49 VU F4SDAC1SPLY 121 VU Q3 SDAC1 26VAC SYNC AC 121 VU Q4 SDAC I 26VAC SYNC AC 121 VU P4 SDAC 128VAC 49 VU F5 SDAC 1& 2 28VAC ESS BUS 121 VU Q2 SDAC 2 26VAC SYNC AC 121 VU Q5 SDAC 2 26VAC SYNC AC 121 VU Q6 SDAC 2 SPLY 121 VU P3 SDAC2 28VAC Reset circuit breaker(s) in accordance with the following procedure.

ATA: 32 AFFECTED COMPUTER: LGCIU

1- CONDITIONS OF POWER-UP TEST INITIALIZATION

HOW LONG THE COMPUTER MUST BE DE ENERGIZED: 1 SEC. A/C CONFIGURATION:

A/C ON GROUND

2. PROGRESS OF POWER-UP TESTS DURATION: 210 MSEC. FLIGHT DECK EFFECTS:

LGCIU 1 LDG GEAR PANEL: "UNLK" RED INDICATIONS ARE FLASHING BRIEFLY LGCIU 2 NONE




PROCEED TO MEL/ TSM DEFERAL / TROUBLESHOOTING.


32

LGCIU FAULTS SYSTEM # 1

49 VU C9 L/G LGCIU SYS 1 121 VU Q34 HYD LGCIU SYS1 GND SPLY Reset circuit breaker(s) in accordance with the following procedure.


ATA: 32 AFFECTED COMPUTER: LGCIU

1-CONDITIONS OF POWER-UPTESTS INITIALIZATION

HOW LONG THE COMPUTER MUST BE DE-ENERGIZED; 1 SEC.

A/C CONFIGURATION: A/C ON GROUND


DURATION: 210 MSEC. FLIGHT DECK EFFECTS:

LGCIU 2 LDG GEAR PANEL: "UNLK" RED INDICATIONS ARE FLASHING BRIEFLY LGCIU 1 NONE






32

LGCIU FAULTS SYSTEM # 2

121 VU Q35 HYD LGCIU SYS 2 Reset circuit breaker(s) in accordance with the following procedure.


3- RESULTS OF POWER-UP TESTS TEST PASS: ABOVE MENTIONED FAULTS MESSAGES NO LONGER DISPLAYED TEST FAIL: (FAULT CONFIRMED) PROCEED TO MEL/TSM FOR DEFERAL/TROUBLESHOOTING


32

BSCU FAULTS

IF A/C NOT MOVING TURN NOSE WHEEL STEERING AND ANTI-SKID OFF THEN ON IF NO HELP, SEE BSCU SYSTEM FAULTS 1 & 2 ON FOLLOWING PAGES


ATA: 32 AFFECTED COMPUTER: BSCU


HOW LONGTHE COMPUTER MUST BE DE-ENERGIZED: 1 SEC. A/C CONFIGURATION:

A/C ON GROUND


DURATION: 1 SEC FLIGHT DECK EFFECTS: NONE

3-RESULTS OF POWER-UP TESTS,





32

BSCU FAULTS SYSTEM #1

121 VU M33 BRK & STEERING SYS 1 IND & SPLY. 121 VU M34 BRK & STEERING SYS 1 CTL. Reset circuit breaker(s) in accordance with the following procedure


ATA: 32 AFFECTED COMPUTER: BSCU



A/C ON GROUND



3-RESULTS OFPOWFR-UP TESTS





32

BSCU FAULTS SYSTEM # 2

121 VU M35 BRK & STEERING SYS 2 CTL 121 VU M36 BRK & STEERING SYS 2 SPLY Reset circuit breaker(s) in accordance with the following procedure





PROCEED TO MEL/ TSM FOR DEFERAL/ TROUBLESHOOTING.


32

NO BRAKE TEMPS DISPLAYS

121 VU M32 BRK TEMP DET UNIT

3-RESULTS OF POWER-UP TESTS TESTS PASS: ABOVE MENTIONED FAULT MESSAGES NO LONGER DISPLAYED TEST FAIL :( FAULT CONFIRMED) PROCEED TO MEL/TSM FOR DEFERAL/TROUBLESHOOTING


33

NO LIGHT IN MLG WHEEL AREAS

2001 VU F5 LIGHTS SEC 19

33 APU AREA LIGHTS INOP

2001 VU F6 APU SVC LIGHTS

33 CABIN LIGHTS STUCK IN BRIGHT

RESET # 2 CIDS THROUGH MCDU IF NO HELP, THEN RESET: RESET DEU A 'S 121 VU M8 THRU M13

33 CABIN LIGHTS WILL NOT TURN ON

121 VU M14 CIDS FWD ATTND/ PNL

33 CABIN LIGHT REMAINS ON BRIGHT WHEN SELECTED OFF OR DIM

CHECK IF CORRECT LAMP INSTALLED IF CORRECT LAMP INSTALLED CHECK CIDS THROUGH THE PTP FOR FAILED DEU AND RESET DEU IF POSSIBLE. NOTE: ALL LIGHTS CONTROLLED BYTHE

FAILED DEU WILL REMAIN ON BRIGHT.


ATA:31 AFFECTED COMPUTER: DMU






MCDU"< AIDS" INDICATION DISAPPEARS



TESTS FAIL (FAULT CONFIRMED)



34

DAR MSG

MSG MAY BE RELATED TO MEDIA(TAPE) BEING FULL 121 VU K15 DMU & QAR 121 VU KI7 FDIU & QAR 121 VU K18 ACCLRM Reset circuit breaker(s) in accordance with the following procedure.


ATA; 31 AFFECTED COMPUTER: FDIU

1-CONDITIONS OF POWER-UP TESTS INITIALIZATION.



2-PROGRESS OF POWER-UP TEST

DURATION: 25 SEC. MAX FLIGHT DECK EFFECTS:

ECAM WARNING: "RECORDER FDIU FAULT" IS DISPLAYED DURING 3 SEC.




PROCEED TO MEL/ TSM FOR DEFERAL/ TROUBLESHOOTING.


34

FLT RECORDER PROBLEM IN FLIGHT OR FLT REC MSG

121 VU K17 FCDR FDIU & QAR Reset circuit breaker(s) in accordance with the following procedure.


ATA: 34 AFFECTED COMPUTER: GPWS


HOW LONG THE COMPUTER MUST BE DE-ENERGIZED: 1 SEC. A /C CONFIGURATION:



DURATION; 25 SEC. MAX FLIGHT DECK EFFECTS:

ECAM WARNING: “RECORDER FDIU FAULT’”IS DISPLAYED DURING 3 SEC.



TESTS FAIL; (FAULT CONFIRMED)



34

GPWS FAULTS

121 VU P6 EIS GPWS 28VDC 121 VU P7 EIS GPWS 115VAC THIS PROBLEM MAY BE BY ILS FREQ'S THAT ARE CLOSE AND INTERFERING WITH THE GPWS SYSTEM HAVE FLT CREW TAXI FWD 2-4 FEET. THIS WILL CAUSE THE GPWS TO RECHECK ITSELF AND IN MOST CASES CLEAR ALL FAULTS Reset circuit breaker(s) in accordance with the following procedure.






2.A/C ON GROUND AND HYDRAUCALLY ENERGIZED FOR YAW DAMPER POWER LOOP POWER-UP TESTS

2- PROGRESS OF POWER-UP TESTS

DURATION: 1-90 SEC. 2. - 5 SEC.

FLIGHT DECK EFFECT: AU|O FLT RUDDER TRIM 1(2) AUTOFLT RUD TRAV LIM 1(2) AUTO FLTRUDDER TRIM 1(2) AUTO FLT.YAW DAMPER 1(2|

FLT CTL PANEL - FAULT1 LEGEND FLASHES




PROCEED TO MEL / TSM FOR DEFERAL / TROUBLESHOOTING.


34

WINDSHEAR DET FAULT

ON THE GROUND MSG MAY OCCUR SPURIOUSLY. RESET FACS REF. FLT MANUAL 7-139 ATTEMPT PUSHBUTTON SWITCHES RESET FIRST IF NO HELP, THEN RESET: 49 VU BJ FAC 1 26VAC 49 VU B4 FAC 1 28VDC 121 VU M18 FAC 2 26VAC 121 VU M13 FAC 2 28VDC Reset circuit breaker(s) in accordance with the following procedure.







35

O2 LOW PRESSURE MSG

INSURE CREW O2 SUPPLY SWITCH IS ON







36

BMC

49 VU D11 AIR BLEED ENG 1 MONG (BMC 1) 121 VU Z22 AIR BLEED ENG 2 MONG (BMC 2)

36 AIR L{R) WING BLEED LEAK (OR APU BLEED LEAK) MSG AFTER ELECTRICAL TRANSIENTS

RESET AFFECTED BLEED PUSHBUTTON SWITCH ON TO OFF TO ON TO CLEAR MSG. REF. FLT MANUAL BULLETIN 95-01


ATA: 36 AFFECTED COMPUTER: BMC


HOW LONG THE COMPUTER MUST BE DE-ENERGIZED: 1 SEC A/C CONFIGURATION:

A/C ON GROUND

2-PROGRE5S OF POWER-UP TESTS


ECAM BLEED PAGE: BLEED TEMPERATURE INDICATION RESET TO 0 DEG. ENG 1(2) BLEED AND APU BLEED PUSH-BUTTON: LIGHT FLASHING.




PROCEED TO MEL/ TSM FOR DEFERAL/TROUBLESHOOTING.


36

LEFT WING LEAK MSGS

49 VU D11 AIR BLEED ENG 1 MONG (BMC 1) 49 VU D12 AIR BLEED ENG 1 CTL Reset circuit breaker(s) in accordance with the following procedure.


ATA: 3S AFFECTED COMPUTER: BMC



A/C ON GROUND



ECAM BLEED PAGE: BLEED TEMPERATURE INDICATION RESET TO 0 DEG ENG 1(2) BLEED AND APU BLEED PUSH-BUTTON: LIGHT FLASHING






36

RIGHT WING LEAK MSG

122 VU Z22 AIR BLEED ENG 2 MONG (BMC 2) 122 VU Z23 AIR BLEED ENG 2 CTL. Reset circuit breaker(s) In accordance with the following procedure.







36

CROSS BLEED VALVE MSG

49 VU D13 AIR BLEED XFEED VALVE BAT 122 VU Z20 AIR BLEED XFEED VALVE NORMAL


ATA: 31 AFFECTED COMPUTER: SDAC



A/C ON GROUND



ECAM WARNING: "EIS SINGLE SDAC FAULT






36

CROSS BLEED FAULTS USE IN ADDITION TO X FEED VALVE FAULTS (MSG)

49 VU DII AIR BLEED ENG 1 MONG (BMC 1) 49 VU DI2 AIR BLEED ENG 1 CTL 122 VU Z22 AIR BLEED ENC 2 MONG (BMC 2) 122 VU Z23 AIR BLEED ENG 2 CTL 49 VU F4 SDAC 1 SPLY 121 VU Q6 SDAC 2 SPLY Reset circuit breaker(s) in accordance with the following procedure.







38

LOSS OF WATER QUATITY

2000 VU D3 WATER SYSTEM

38 TOILET WILL NOT FLUSH

2001 VU B1 VAC TOILET SYS LAV PWR 2001 VU B3 VAC TOILET SYS LAV PWR 2001 VU B4 VAC TOILET SYS LAV PWR

38 GALLEY WATER SYS NOISE

REMOVE AFT GALLEY RIGHT COFFEE MAKER AND PLACE FINGER TIP OVER DRAIN TUBE. THIS WILL RESEAT THE CHECK VALVE.

FAULT VERIFICATION GUIDE.

ATA: 49 AFFECTED COMPUTER: ECB

1-CONDITIONS OF POWER-UP TESTS INIALIZATION

HOW LONG THE COMPUTER MUST BE DE-ENERGIZED: NONE A/C CONFIGURATION:

A/C ON GROUND AND APU STOPPED APU CONTROL PANEL MASTER SWTICH “ON”


DURATION: 3 SEC MAX FLIGHT DECK EFFECTS;

APU CONTROL PANEL: "FAULT” ON MASTER SWITCH PUSH-BUTTON



TESTS FAIL :( FAULT CONFIRMED) PROCEED TO MEL/TSM FOR DEFERAL/TROUBLESHOOTING


49

APU BLEED FAULTS

SHUT DOWN APU AND RESET CB.'S 121 VU L41 ECB SPLY 121 VU L42 APU CTL Reset circuit breaker(s) in accordance with the following procedure.







49

APU WILL NOT SHUT DOWN

OPEN THESE C.B.'S 121 VU L42 APU CTL IF NO HELP, THEN RESET; 121 VU L4I ECB SPLY.

FAULT VERJFICATION GUIDE

ATA:24 AFFECTED COMPUTER: GCU


HOW LONG THE COMPILER MUST BE DE-ENERGIZED: 15 MS A/C CONFIGURATION:




3-.RESULTS OF POWERUP TESTS

TESTS PASS' ABOVE MENTIONED FAULT MESSAGES NO LONGER DISPLAYED

TESTS FAIL' (FAULT CONFIRMED)



49

APU ELEC NO VOLTS OR FREQS

SELECT APU ELEC OFF AND RESET TO ON IF NO HELP, THEN RESET: 122 VU Y25 ELEC APU GCU R«et circuit breaker(s) in accordance with the following procedure.


ATA: 73 AFFECTED COMPUTER: FADEC


HOW LONG THE COMPUTER MUST BE DE-ENERGIZED: 1 SEC. A/C CONFIGURATION: A/C ON GROUND WITH ENGINES STOPPED

2-PROGRESS OF PQWER-UP TESTS.

DURATION: 2 SEC. MAX FLIGHT DECK EFFECTS: NONE






73

FADEC FAULT MSGS “ENG 1 (2) FADEC FAULT" OR "ENG 1(2) FADEC A OR B FAULT" NOT RELATED TO REAL FAILURE.

TURN FADEC PUSHBUTTON SWITCH ON THEN OFF TO RESET FADEC. IF NO HELP, THEN RESET: 49 VU A4 ENG 1 FADEC A & EIU 1 121 VU R41 ENG 1 FADEC B & EIU 1 49 VU A5 ENG 2 FADEC A & EIU 2 121 VU Q40 ENG 2 FADEC A & EIU 2 Reset circuit breaker(s) in accordance with the following procedure.







73

ENG 1(2) EPR MODE FAULT MSG

RECOVERY OF EPR ON BOTH ENGINES MAY BE ATTEMPED BY SWITCHING OFF EACH ENGINE'S N1 MODE SWITCH REF. FLT MANUAL 7-86







79

ENG 1(2) OIL FILTER CLOG

MAINTENANCE ACTION REQUIRED EXCEPT WHEN WARNING IS TEMPORARILY DISPLAYED DURING ENGINE START WITH ENGINE OIL TEMP. BETWEEN 10 – 32deg C REF. FLT. MANUAL 7-80

Airbus a320 Fault Verification Guide

Documents

cargo door operation

flight deck effects

flight deck effect

fault verification guide

mentioned fault messages

fault verjfication guide

mel tsm

ecam status page