3 Reset Tips

RESET & TIPS PROCEDURES GENERAL CONFIGURATION

46

ALERT CLASSIFICATION (ECAM) LEVEL 3: Red MASTER WARNING + CHIME (Multiple) LEVEL 2: Amber MASTER CAUTION + CHIME (Single) LEVEL 1:Amber ECAM message – NO CHIME

FAILURE CLASSIFICATION (On Board Maintenance sys) CLASS 1: Logbook Entry = MEL CLASS 2: Logbook Entry= DELAYED MAINTANCE ACTION CLASS 3: No Logbook entry = Scheduled maintenance

SYSTEM TYPES (OMS) TYPE 1: MEMORIZATION 64FLTs TYPE 2: MEMORIZATION LAST FLIGHT TYPE 3: NO MEMORIZATION (TEST/RESET) See avionic status in CFDS menu’

46

FAP LAYOUT SELECTION= CODE “318” ENTER COMPUTE R ACP ADF ADIRU AEVC ATC BMC BSCU CFDIU CHC CIDS CPC DMC DMCU DME DMU (AIDS)

C/B n1:G6 , n2:G7 , n3:M02 n1: H14 N04-10 ; F06-09 D06/06 ; Y17 n1:G11 , n2:K07 AVIONIC COMPARTMENT M32 - 36 J17/18 … G01/02/(03-05);M05-07/(08-14) n1:D09 , n2:Y22 (Sply)n1:E11,n2:Q08,n3:E10/Q09

DU ECB EIU

n1:G14 ; n2:K06 K15 n1:E01-04 ; n2:R03-06; Ecam:E05/6,R10/11 L41 n1:A04,R41 n2:A05,Q40

ELAC

n1:B11 n2:R20

EVMU FAC FADEC FCDC FCU FDIU

R44 n1:B03/04 n2:M18/19 Eng1:A06/R21 Eng2:A04/Q40 n1:B10 n2:Q20 n1:B05 n2:M21 K17 Eng1:A06/Q38 Eng2:A07/Q39 APU:L43/44 n1:B02 n2:M17 (FD's:OFF) chan1:A13 chan2:M27 chan1:A13 chan2:M27 n1:F01 n2:Q07 n1:T26 n2:T27 APU:Y25 Y24 P06/07 n1: G12 n2:K09 1GND: Q34 n1:C09 n2:Q35 n1:B01 n2:N20 n1:X21/22; W21/22 n2:Y18-21 n1:D03 n2:Y12 n3:Y16 n1:K11 n2:K12 n1:K13 n1:G10 , n2:L02 , n3:L03 (not used) F02-05 and P02-05 and Q02-06 chan1:C06 chan2:T18 n1:B08 n2:Q18 n3:Q19 FLP:B07/Q21 SLT:B12/P16

FDU FMGC FQIC(320) FQIC(321) FWC GCU GPCU GPWS ILS LGCIU MCDU PACK CTRLR PHC RAD ALT RADAR RMP SDAC SDCU SEC SFCC(320)

C/B pulled 1s 2s >20sec 1s 1s 1s >30ms >3sec 200ms >10sec >2sec >1sec 1s 2s 1s

power-up test 1s 2s 5s 85s 3s 22s 1.6sec 60s 28s 180s 1s 4s 10s 2s 40s

>6sec >250ms >200ms 30ms or pb OFF-ON >140ms >5s 1sec >3sec >7sec 1sec

5-20sec max 3sec max 3sec

200ms >5sec >2sec >8sec >1sec 15ms none 1sec 1sec >3sec >200ms 2ms 3sec 2sec 1sec 2sec >1sec 200ms 5sec >200ms

57 sec 120 sec max 80 sec max 150 sec max 50 sec 30ms 35ms 2 sec 1 sec 210ms 45 sec 30 sec 9 sec 3 sec 15 - 30 sec 2 sec 5 sec 70 sec 18 sec < 2 sec

8sec 25 - 100 sec 90 sec 2 sec max 3 sec 10 sec 25 sec max

46

SFCC(321) VHF/HF VOR WHC ZONE CTRLR

FLP:B07/Q21 SLT:B12/P16 n1:G09 n2:L04 n3:L05 n1:G13 ; n2:K08 RMI:F13 n1:X13 n2:W13

>50ms 1sec 3sec 5 sec

65 sec 10 sec 3 sec 5 sec

n1:V17/19 n2:V18/20

200ms

36 sec

W A R N I N G: BE CAREFULL TO CHOSE THE PROPER INSTRUCTIONS :

F

Can be reset on Ground AND in Flight

G To be reset ON GROUND ONLY

FOR MORE INFOS ABOUT COMPUTER RESET, CHECK: 46

TSM 24-00-00-810818

ATA21 System

G F F

CPCU – Cabin Pressure Control Unit

AEVC – Avionic Equipment Ventilation Control AVIONIC SMOKE ALERT AEVC

G

G

VENT AVIONICS SYS FAULT

VENT AVIONICS SYSTEM FAULT DUE TO THE FILTER AVIONICS VENT EXTRACT VALVE AMBER/OPEN

G

Cargo Ventilation

F F

Length Self Test

Procedure BRAKES….SET Pull and reset the relevant CB: CPCU # 1………..... D9 CPCU # 2…………...Y22 Pull and reset the relevant CBs: Air Cond / avncs vent Ctl Air Cond / avncs vent mong Cycle both push button:

-

1 sec

D5 / D6 Y17

85 sec

Generator 1 Line Generator 2 Line

P/B BLOWER and EXTRACT….. ……AUTO DITCHING ...OFF BRAKES ...SET AVNCS/VENT/MONG Y17 / 122VU For return flight to BASE only Remove Avionics vent filter (20hrs max) acc to MEL AOM 1.2.21 page 2 item 21-21-09

85 sec

Cycle c/b: Aircond. Avionics vent ctrl ……………..D5 Aircond. Avionics vent ctrl ……………..D6 Aircond. Avionics vent Mong ………… Y17 Perform TEMP Control Test Pull and reset the relevant CB: Fwd Cargo Vent Ctl Fwd Cargo Vent Fan

C8 T22

30 sec

AFT Cargo HEAT Aft CargoVent & HTV fan….S22

46

F F

AFT Cargo VENT FAULT

Cycle c/b: Aft cargo vent CTL & Mong…. C07 Aft Cargo vent fan…………….S22

Ecam HOT AIR VALVE FAULT Or TRIM AIR VALVE FAULT

Cycle c/b: Zone temp ctrl 115vac sys1 –V17 Zone temp ctrl 28vdc sys 1 – V19 Zone temp ctrl 115vac sys2 – V18 Zone temp ctrl 28vdc sys2 – V20

ATA21 System Pack Controller

PACK 1 OR 2 FAULT

G

G

ON GND only - BRAKES SET Pack 1 or 2 OFF Pack Flow Control Valves Pull and reset the relevant 4 CBs: No.1. Air Cond/Pack Temp/Ctl Sys

G

PACK TURBINE BYPASS VALVE POS. INDICATION X - OUT PACK OVERHEAT

Length Self Test

Procedure

Shut

X21 X22 Y18 Y19 No.2. Air Cond/Pack Temp/Ctl Sys W21 W22 Y20 Y21 Reset for at least 1 minute: Pack ctrl sys1 1…………..X22 Pack ctrl sys1 1…………..X21 Pack ctrl sys1 2………….W22 Pack ctrl sys1 2………….W21 Pack ctrl sys1 ……………V17 Pack ctrl sys1 ……………V19 Pack ctrl sys2 1………….Y18 Pack ctrl sys2 1………….Y19 Pack ctrl sys2 2…………Y20 Pack ctrl sys2 2…………Y21 Pack ctrl sys2 …………..V18 Pack ctrl sys2 ………….V20 D8 on 49vu

30 sec

Reset c/b for at least one minute: Zone temp ctrl 115vac sys1 –V17 Zone temp ctrl 28vdc sys 1 – V19 Zone temp ctrl 115vac sys2 – V18 Zone temp ctrl 28vdc sys2 – V20 Pack Sensor 13HH fault

G G

Zone Controller

OnGND only - BRAKES set NO BLEED air Note: if engines running FLT IDLE will be set during reset Pull and reset the relevant CBs:

46

Air Cond/Pack Temp/Ctl Sys 122vu

V17 V18 V19 V20 /

Note: Resetting zone controllers with engines running will generate the warnings ENG1(2) FADEC under the MAINTENACE heading on the STATUS page.

ATA21 System AIR PACK 1 REGUL FAULT

Reset the following cb: Pack Temp CTL AC sys1…X22 Pack Temp CTL DC sys1…X21 Pack Temp CTL AC sys2…Y13 Pack Temp CTL DC sys2…Y19

AIR PACK 2 REGUL FAULT

Reset the following cb: Pack Temp CTL AC sys1…W22 Pack Temp CTL DC sys1…W21 Pack Temp CTL AC sys2…Y20 Pack Temp CTL DC sys2…Y21 If this warning occurs on GND ,reset the primary channel of the affected pack controller by cycling c/b of the secondary channel 2HH or 22HH After reset of c/b, a system test must be performed. If successful, No further action is required

F F G F

Procedure

PACK REGULATOR FAULT with no associated Maint. Message Hot Air Valve ACSC AirConditioning Sys Controller A318 ENHANCED

30 sec up to 2 min

Length Self Test

Wait 30 sec after switching the Packs ON before attempting a 60s reset using the HOT AIR push button Pull for at least 5s. N1 TEMP CTL SYS1 CHAN B D8/49VU TEMP CTL SYS1 CHAN A(B) X21,X22,Y18/122VU N2 TEMP CTL SYS2 CHAN A(B)

G

W21,W22,Y20,Y21/122VU CABIN TRIM AIR VALVE MSG

G

AC on GND Both PACKS OFF Flow CTRL valves CLOSED reset 1 sec: Zone temp ctl sys1...…V17 Zone temp ctl sys2..….V18 Zone temp ctl sys1..….V19 Zone temp ctl sys2…....V20

36s

Note: Trim air valves are moving

46

from C to H and from back

ATA22 - System FMGC – Flight Management Guidance Computer

Procedure

Length Self Test

Note: Do not reset CB’s with in 2 min of aircraft power-up. (Self test of PMGC)

Only reset one system at time. If a single reset fails and the aircraft is on the ground refer to the procedure for the ground only. ADIRU 1-2-3 ALIGN FD 1and 2 OFF AP operative ON if available Pull for between 5 and 10 sec and reset relevant CB: FMGC 1 B2 FMGC 2 M17

F

Do not use the MCDU until the end of self test. Wait a further 5 sec prior to switching FD ON and 1min before AP FMGC – Flight Management Guidance Computer

2 min

Note: this procedure may be used on the ground only if the single reset has failed as described earlier for systems that can be reset in Flight and on Ground. Do not reset CBs with in 3 min of power up (self test of FMGC) ENG 1 and 2 OFF Flight Directors 1 and 2 OFF Pull and reset simultaneously (Between 5 and 10 sec) the following CBs: FMGC 1 B2 FMGC 2 M17

G

G

DOUBLE FMGC Fault

Do not use MCDU until end of self test. Wait a further 10 sec prior to switching the FD to ON ADIRU 1,2,3… ALIGNED FD 1 and 3…….OFF Pull and push at same time : FMGC1………B2/49VU FMGC2………M17 / 121VU

2min

46

wait 10 seconds before re-engage FD

Length

ATA22 - System MCDU

Both MCDUs locked or blank FMGS malfunction

F

G

Self Test

Procedure Pull 1s and reset the relevant CB: MCDU 1 B1 MCDU 2 N20

45sec

On ground: ‐ Apply external power or APU generator power ‐ Wait 2 min before resetting the FMGC circuit breakers ‐ FD 1(or 2) (OFF) ‐ Pull the CB of the affected FMGC and reset it after 5 s. The circuit breakers for the FMGC's are: • AUTO FLT/FMGC 1 B2 ON 49 VU (Overhead Panel) • AUTO FLT/FMGC 2 M17 ON 121 VU (Right Rear Maintenance Panel) In flight: ‐ FD 1(or 2) (OFF) ‐ Pull the CB of the affected FMGC and reset it after 5 s. The circuit breakers for the FMGC's are: • AUTO FLT/FMGC 1 B2 ON 49 VU (Overhead Panel) • AUTO FLT/FMGC 2 M17 ON 121 VU (Right Rear Maintenance Panel) ON GND - BRAKES SET

Engine 1 and 2 OFF

95 sec

FAC – Flight Augmentation Computer Hydraulics (p/b Yellow Elec pump ON)

OFF or ON

Pull for at least 10sec and reset relevant 2 CBs: Auto Flt FAC 1 B3 and B4 Auto Flt FAC 2 M18 and M19

46

G G

FMGC msg: "OPPOSITE FM IN PROGRESS OF FMA SHOWS OFFSIDE FDs" AUTO PILOT 1 FAULT

Note: With Hydraulic pressurized the Yaw Damper, output is also tested. Do not alter hydraulic configuration during self test ENGINES OFF Pull for at least 4 sec : FMGC 1……B2/49vu FMGC 2……M17/49vu ENGINES OFF Pull for at least 4 sec : FMGC 1……B2/49vu

G

AUTO PILOT 2 FAULT

ENGINES OFF Pull for at least 4 sec : FMGC 2……M17

G

FMS INIT or PAGE NOT AVAILABLE

Cycle circuit breaker Both: FMGC B3 & M17 more than 1 min Or complete Pwr off more thean 1 minute (pwr up test approx. 2 minutes )

120sec

2min

Length

ATA22 System FCU – Flight Control Unit

120sec

Procedure

Self Test

In flight: ‐ Pull the C/B B05 on 49VU for FCU1, or M21 on 121VU for FCU2. ‐ Push it after 5 s. ‐ CHECK the displayed targets and the barometer reference, and correct them if necessary.

10 sec

On ground: Pull simultaneously for 7 Min and reset the following 2 CBs:

G / F

FCU 1………... B5 FCU2………….M21 In case of FCU 1+2 Fault : pull in order B5 and M21 for at least 5sec than push both. ‐ If FCU1(2) FAULT disappears, CHECK the displayed targets and barometer reference, and correct them if necessary (RESET successful) ‐ If FCU1(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 ‐ Wait at least 30 s for FCU1 and FCU2 safety tests completion ‐ CHECK the displayed targets and barometer reference, and correct them if necessary (RESET successful)

5sec

46

CAT 3 Dual Inop Msg

Reset pb One at a time (every 5s) If no help: See FAC reset proc!!!! Pull for at least 4sec: FAC1……..B4/49vu FAC2…….M19/121vu

Rudder travel Limit system 1 Rudder travel Limit system 2

ENGINES ….OFF see FAC reset proc!!! If No Help then reset: FMGC 1 …..B2/49vu

AUTO FLT RUD TRV LIM SYS FAULT MSG

Reset FAC1 and FAC2 p/b

Ecam “ A/THR OFF WARNING”

Perform a manual Thrust Take off Fault may be reset itself after reducing T/O PWR to CLB in FLT. Ref OM-B-2.2.1 pag 3 para22.9

Ecam

Reset c/b

Time indication

CFDIU ……….J18

G G G

G F F

95s

ENGINES ….OFF see FAC reset proc!!! If No Help then reset: FMGC 2…..M17/121vu

Length

ATA22 - System

Procedure

Self Test

46

Length

ATA23 - System HF

VHF

F ACP Audio Control Pnl

F

ACP Freqs will not change from standby to active windows

RMP – Radio Management Panel

Self Test

Pull and reset the following CB: HF1 L10/121VU or HA14/49VU HF2 L13/121VU Pull and reset the following CBs: VHF 1……………….G9 VHF 2……………….L4 VHF3/ACARS (SB23-1030)..L5 Pull and reset the following CB: ACP Capt G6 ACP F/O G7 ACP 3 M2 Turn affected RMP OFF then ON to reset

ON GND With ENGs OFF least 4 sec: FMGC2:MJ17

G F

Procedure

10 sec

11 sec

1 sec

If No help, Then pull for at FMGC1: B2 and

Pull for at least 2 sec and reset the relevant CBs: RMP 1 – Com RMP 1……..G10 RMP 2 – Com Nav RMP 2… L2 RMP 3 – Com Nav RMP 3 …L3

120sec

2 sec

46

CIDS – Cabin Intercom Data System

Resetting in flight is not recommended as the normal functioning of the cabin systems are lost during self test. Try reset on Programming and Test PTP test page. If unsuccessful: Pull and reset the following CBs for at least 10 sec if doors are closed and 30 sec if doors are open. Only one CB at a time in Flight. Com CICS Director 1 and 2 Ess …….G2 (or G1 ) Com Nav CIDC Director 1 and 2 Norm…….. …...M5 (or M6)

G

2 min doors open 1 min doors closed

Pull also P13 and P14 (121u) if NO FROZEN RMP Push CBs in opposite order Directors

F

ATA23 System

CIDS II (ENHANCED) SDF ESS……C6 and C5 /49VU SDF NORM…T17 and T18/122VU CIDS/Dir1(2)Bat Bus…P13 and P14 CIDS/Dir1(2)Norm…M5 and M6 CIDS/DIR1(2) ESS..G1 and G2/49vu wait 10sec and push within30sec in the following order: G1 & G2 ; M5 & M6 ; P13 & P14 ; AND simultaneously C5 & C6 AND within 2secs, simultaneously T17 & T18 and wait the auto-test Note:This procedure could restore the normal function and if the message COM CIDS1 + 2 FAULT shows , push CLR to cancel.

Procedure

Length

Self Test

4min

G Directors CLASSIC

CIDS I (CLASSIC)

CIDS/DIR 1 + 2 BAT…N11/121VU

CIDS/DIR 1 + 2 ESS…G2/49VU

CIDS/DIR 1 + 2 NORM…M5/121VU wait 10 sec than push them in the order: M5 ; G2; N11 (12) and wait the end of the auto-test

F

ACARS

5 min Reset c/b ACARS MU…..L6 /121VU

46

1sec

F G

EVAC Alarm steady active

F

Push the button EVAC HORN SHUT OFF - if no help move the selector

EVAC CAPRT & PURS to CAPT - if no help within 3sec A320CLASSIC : reset CIDS A320ENHANCED pull c/b DIR2 CIDS/DIR2 ESS……...G2/49VU CIDS/DIR2 NORM..…M6/121VU - if no help pull c/b DIR1 CIDS/DIR1 ESS…….G1/49VU CIDS/DIR1 NORM….M6/121VU wait 1min than push DIR2 M6 and G2 and wait the end of the auto-test

4 min

46

F

CVR

with engines Shutdown, pull

for at least 10sec and then push:

CVR SPLY…………………..E14/49VU

FAP

CIDS I (CLASSIC)

pull for 10sec and push

F FWD ATTND PNL……M14 or Q14/121VU

if no help, reset for 10sec:

PRAM………………..panel 2000VU

CIDS II (ENHANCED)

Pull for 10 secs :

A318 FAP ESS…….H1

FAP FAP ESS………………..H1 /49VU

1Norm….Q13 Push Q13 then H1

FAP 1 NORM………..Q14/121VU than push Q14 than H1

Length

ATA23 - System

F

Procedure

Cain Phone / Music / Prerecordered ads

pull and push after 10sec: PRAM………………..panel 2000VU

PAX Entertain. will not turn ON or OFF

Reset cb: CABIN COM SYS PES….F6/2000vu If no help, then reset all DEUs:

Self Test

46

M7 through M13 /121vu

F F F

G

F

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

AIRFONE sys AirPHONE sys

ONLY ONE RESET IS ALLOWED cb reset 3 min: AIRFONE……….……E7/2000VU

ATSU (ACARS) reset

Cycle c/b L15 and L16

ATT & MECH lts blinking on all 3 ACP

Once on GND, cycle c/b : Audio ACP : G07 – M02 – If no success do a CIDS reset at F/A station If still persisting: CIDS DIR NORM 1 – M05 CIDS DIR ESS - G01 Reset cycling cb on 2000VU – FWD cabin ceiling panel Pilot Handset A321 – C08 A320 – F08 A319 – C08

Pilot SATCOM handset blue led light on and no tone

1sec

Length

ATA24 - System

G

No AVAIL green legend on Ext Pwr P/b switch

G

Transformer Rectifier Unit Fault

Procedure

Self Test

On GND- ENGs OFF - APU OFF - GPU connected Reset the following cb: Y24/122vu GPCU Reset T/R through MCDU or Reset all three using guarded button on 103vu panel in electrical bay

46

BCL – Battery Charger Limiter

ON GND - BRAKES SET ENGINES OFF Reset affected Battery one at a time with pb

If no help, reset from panel 105VU:

G

BAT REF BCL1

BAT BUS REF BCL1

BAT REF BCL 2

GCU – Generator Control Unit

BAT BUS REF BCL 2 Relevant generator control push button switch at the overhead panel OFF then ON

1 sec

1 sec If no help:

Engines……Shutdown

APU………Shutdown

G

BAT 1 & 2..Shutdown

Gen Faulty…….OFF &ON

BAT 1 & 2…….ON

G GPCU – Ground Power Control Unit

ON GND - BRAKES SET ENG 1 and 2……….OFF APU………………...OFF

46

Batt 1 and 2 ……...OFF

External Power OFF and Disconnected

Then RE - ENERGISE

1 sec

if no help:

ALL POWER OFF

pull and push c/b:

EXT PWR/CTL..X29/122VU

GPCU……………Y24/122VU GndPwrProt….. AB7/123VU

A318& ENHANCED Then

G

With at least one pwr source connected on RE(BATT/IDG/APU) - ENERGISE Reset EXT PWR P/b

GAPCU

If GCU doens't connect to

Ground and

the a/c (AVAIL lt off)

Auxiliary power

With NO POWER ON

Control Unit

BAT 1 & 2……….AUTO

(ENHANCED)

With POWER from Bat or APU Gen or Eng Gen

46

EXT PWR….keep ON 3s

G

G

ENGINE GEN on

ENGINE MUST BE SHUT

line(green line) and parameters not shown STATIC INVERTER FAULT

DOWN!! Than reset : Eng1: GCU1………....T26/122vu Eng2: GCU2………….T27/122vu Cycle BAT 1 and 2 p/b after other If no success Static Inverter plug must be dis/reconnected for reet – PLUG IS SEALED

30ms

Length

ATA24 - System

G

If the RAT deploys when Battery switches to OFF

Procedure

Self Test

Replace relay 16XE EMERG GEN TEST CONDITION: panel 103VU

46

ATA25 - System

F

F

CDLS Cokpit Door Locking sys

CDDS Cokpit Surveillance sys INTEGRATED ON Lower ECAM

Procedure Overhead panel Select CKPT DOOR LKG SYS OFF 10sec than NORM If no help MeL video instable, with message VIDEO NOT AVAIL, reset to be performed

Length Self Test

1sec

Pedestal VIDEO sel……….OFF P/B CokpitDoor Video OFF wait 2 minutes than: P/B CokpitDoor Video ON wait 15sec than: VIDEO sel………..CKPT ENTRY

46

ATA26 System

G

G

G G G

G

SDCU – Smoke Detection Control Unit CLASSIC

SDF – Smoke Detection Toilet & Cargo ENHANCED FDU – Fire Detection Unit

SMOKE CARGO BOTTLE FAULT SMOKE LAV + CRG DET FAULT =>CIDS -SDF SMOKE LAVATORY DET FAULT with all lav declared NOP on FAP

Length

Procedure ON GND- BRAKES SET Pull and reset the following CB: SDCU Chan 1 T17 or C6 SDCU Chan 2 T18 to empty the memory, peform a reset of both FWCs (ata31)

Self Test

10 sec up to 60 sec

Perform CIDS reset (ata23)and to empty the memory, perform a reset of both FWCs (ata31)

Pull and reset the relevant 2 CBs: ENG 1 Fire Det Loop A and B A6 and Q38 ENG 2 Fire Det Loop A and B A7 and Q39 APU Fire Ovht Det Loop A and B L43 and L44 /121vu Pull C5-C6 /T18 –T17 , wait 5 sec, than push simultanesly C5+C6 within 2s T18+T17

57 sec

Pull C5-C6 /T18 –T17 , wait 5 sec, than push simultanesly C5+C6 within 2s T18+T17 Pull P13 – P14-G01-G02-M05 –M06-M07 Wait 5 sec than push inverse order: M07-M06-M05-G02-G01-P14-P13

If unsuccessful, on ground only:

Apply the following actions in the presented order:

46

‐ Pull the C/Bs C06 and C05 on 49VU, T17 and T18 on 122VU. ‐ Wait 5 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.

F

SDCU RESET

ATA27 System

G

SFCC/ WTB wing tip brake CFDS reset

FLAPS LOCKED procedure for BOTH SFCC1 and SFCC2

G

Whatever afterwards AFT CARGO VENT C B resetting

Procedure

Length Self Test

ON GROUND ONLY BRAKES SET ENGINES…….OFF G , Y , B hyd depressurized SYS Report/test menu….press F/CTL line key…….press Pull c/b FLIGHT CONTROLS/FLP/CTL&MONG/SYS 2… …………………………………………Q21 /121VU ( SFCC2 is isolated) SFCC1(2) key NEXT PAGE key TEST/RESET FLP key WTB-RESET line key START WTB RESET line key If reset not successfull, repeat the reset RESET Q21/121vu Pull c/b FLIGHT CONTROLS/FLP/CTL&MONG/SYS 1….B07 /49VU (SFCC 1 is isolated) repeat the WTB reset procedure RESET B07/49vu RETURN key to exit CFDS

reset cb 1s Pwr up: 2s

46

SLATS LOCKED procedure for BOTH SFCC1 and SFCC2 or

G

G

G

SLAT WTB BRAKE FAULT

SIDE STICK priority msg

reset pb: FAC 1 & 2 switches SEC 1,2 & 3 switches ELAC 1 & 2 switches

THS will not return to zero on LDG

Pwr up all three hyd sys and turn the ELACs pb switches to OFF, Manually trim nose down a few degrees and return ELACs to ON. THS should return to Zero. Turn OFF ELACs and manual trim nose up. Return ELACs to ON. THS should return to zero

ATA27 System

G

NB:

RESET ONE

G G

SYS Report/test menu….press F/CTL line key…….press Pull c/b FLIGHT CONTROLS/SLT/CTL/SYS2 ….R21 / 121VU ( SFCC2 is isolated) SFCC1(2) key NEXT PAGE key SLT TEST/RESET FLP key WTB-RESET line key START WTB RESET line key If reset not successfull, repeat the reset RESET Q21/121vu Pull c/b FLIGHT CONTROLS/SLT/CTL/SYS1 ….B06 / 49VU (SFCC 1 is isolated) repeat the WTB reset procedure RESET B06/49vu RETURN key to exit CFDS

Flight Control FLAPS LOCKED OUT FLT/CTL Maintenance msg (can be deferred)

ELAC – Elevator Aileron Computer

For the ELAC only, in case of uncommanded maneuvers during the flight, the reset is

reset cb 1s Pwr up: 2s

Length Self Test

Procedure HYD MUST BE OFF Must perform WingTipBrake (WTB) reset through MCDU amm27-50-00 A/C on GND Reset for at least 3s: SPLY..B10/49vu FCDC 2 SPLY..Q20/121vu

FCDC 1

On GND - BRAKES SET Appropriate ELAC push button…………….. OFF for 10 sec and then….ON If no help: -HYD SYS DE-PRESS -All hydr pumps ….OFF -Parking brake…….. ON -ELAC 1&2 ….OFF&ON Wait 8 sec of AutoTest If no help: reset of c/b: ELAC1/NORM SPLY …….B11/49vu ELAC2/NORM SPLY ……..R20/121vu Wait 8 sec of AutoTest Hyd Panel to NORMAL - PERFORM A FLIGHT CTRLS CHECK - CHECK PITCH TRIM POSITION

3s ELAC 10sec 8sec 8sec

46

UNIT PER TIME !!!!!!!!

not recommended.

SEC – Spoiler Elevator Computer

G

On GND - BRAKES SET Appropriate SEC push button…………….. OFF for 10 sec and then….ON

18 sec

If no help: -Hyd to zero -All hydr pumps ….OFF -Parking brake…….. ON -SEC faulty ….OFF&ON Wait 25sec of AutoTest If no help:

25sec

SEC

reset 5s of c/b: SEC1/NORM SPLY …….B8/49vu SEC2/NORM SPLY ……..Q18/121vu SEC3/NORM SPLY ……..Q19/121vu Wait 25sec of AutoTest Hyd Panel to NORMAL FLIGHT CTRL CHECK 25 sec

FCDC – Flight Control Data Concentrator

On GND - BRAKES SET Note: On the ground reset without hydraulic pressure. ( Reset with hydraulic pressure causes LAF DEGRADED warning (A320CLASSIC) HYD………... OFF Pull for at least 3 sec and reset the relevant CB: FCDC 1 Sply B10 FCDC 2 Sply Q20 or Q6

G

3 sec

G

SLOW SLATS After enignes start or approaching IDLE

Reset c/b for at leat 1s: SLT CTL & Mong sys1..B6 SLT CTL SLT CTL & Mong sys2…..R21 or Q21

2sec

46

ATA27 System SFCC – Slat Flap Control Computer

G

G

G G

G

RUD TRIM TRAVEL LIMITER FAULT SLAT PROBLEM

Procedure

On GND - BRAKES SET ENG 1 and 2 OFF Pull and reset all 4 CBs with or without Hydraulic Pressure: B6 R21 B7 Q21 -ORENG 1 and 2 Running or OFF Pull and reset the relevant CB according to ECAM Warning. See table below.

See ATA 22 : HYD ON and reset p/b FAC1 and FAC2 or c/b B3-B4 and M18-M19

Length Self Test

2 sec

95s

FCDC and SEC C7b Reset requie Perform F/CTL Test

FLIGHT CONTROL WARNING

Perform GND SCAN for reset and fault identification

“FLT CTRL ALTERNATE LAW” MESSAGE ON ECAM AFTER ENGINE START

Reset procedure with Engines running - SET PARKING BRAKE - DEPRESS BLUE HYD (P/B OFF) - DEPRESS GREEN AND YELLOW HYD (Eng 1 pump and Eng 2 pumpp/b switches OFF - Check Ecam all HYD systems are at 0psi. - RESET ELAC 1 and ELAC 2 p/b - 8 secs later, check Ecam-warnings “ELAC 1 FAULT” and “ALTN LAW” are not displayed anymore. ALTN LAW may remain displayed but should disappeared after hyd syst pressurization. - RE-PRESSURIZE ALL THREE HYDR. SYS AND CHECK THE AVAILABILITY OF THE HYDR. SYSTEMS ON THE ECAM HYD PAGE SEE AOM 2.1.27 page 5 IF NOT SUCCESS :

46

RESET FAC1 & FAC 2 c/b B3-B4-M18 – M19

ATA27 System

G

G

LH/RH ELEVATOR FAULT AFTER ENGINE START

AILERON SERVO FAULT

Procedure

Length Self Test

RESET ELAC 1/SEC1/ELAC2/SEC2/SEC3 by push buttons IF NEGATIVE: ELAC 1 NORM SPLY…..B11 SEC1 SPLY ………………B08 ELAC2 NORM SPLY …R20 SEC 2 SPLY………………Q18 SEC3 SPLY……………..Q19 After C/b reset perform reset by push buttons again. See AOM 27.1.P4 Try to reset with ELAC1 or ELAC2 (on/off switching p/B) IF UNSUCCESFULL SWITCH OFF BLUE AND GREEN HYD SYS REPEAT ELAC1 OR ELAC2 p/b reset ELAC 1 FOR LH AILERON BLUE HYDR SYSTEM AND RH AILERON GREEN HYDR SYS ELAC 2 FOR LH AILERON GREEN HYDR SYSTEM AND RH AILERON BLUE HYDR SYSTEM

YAW DAMPER FAULT After engines start

G

BEFORE ATTEMPTING ANY CB RESET: Consult MPM 03-22 page 1 Item 2263-01 NOTE: Application of this Maintenance proceude for Deactivation of the affected YawDamper system may be delayed as long as: The a/c remains electrically powered and the 28VDC c/b of the associated FAC are not opened wich both

46

engines stopped (AUTO/FLT FAC 1 c/b B04 and FAC 2 c/b M19) For reset cycle c/b: FAC 1 26VAC and 28 VDC B03 –B04 FAC 2 26VAC and 28VDC M18 – M19 Pull for more than 30sec and allow 90 sec for pwr up test

G

F/CTL SIDESTICK PRIORITY FAULT

SEE OM B 2.1.27 P09 Reset ELAC 1 and 2, Turn off and on again

ATA27 System

G

ELAC 1 / 2 PITCH FAULT AFTER ENG START

ECAM Warning

90 sec

Length Self Test

Procedure CYCLE RESPECTIVE ELAC P/B OFF-ON IF No success - CYCLE ALLA SEVEN FLT CTL P/B OFF-ON IF Still No success - SWITCH OFF ALL HYD PUMPS - Pull all c/b for 30 secs: ELAC 1 Norm sply ….B11 ELAC 2 Norm sply ….R20 FCDC 1 sply……………B10 FCDC 2 sply …………..Q20 - Push this c/b again and wait 2 minutes for pwr up test - Switch on HYD press EFCS 1 or 2 test ( with blue pump on)

B6 SLT/CTL AND MONG/SYS1

R 21

SLT/CTL/SY S2

B7

Q 21

SLT/CTL AND MONG/SYS 1

FLP/CTL AND MONG/SYS 2

46

Slats Fault

Reset

Together

Flaps Fault Slat Sys 1 Fault Slat Sys 2 Fault

Reset

Together

Reset Reset

Flap Sys 1 Fault

Reset

Flap Sys 2 Fault

Reset

Slats / Flaps Locked

ATA28 System

Procedure

Length

Self Test

WARNING: Crews are directed not to reset tripped wing fuel tank pump circuit breaker (N23,Q23,N25,Q26 on 121VU) under any circumstance

G

G

FQIC – Fuel Quantity Indication Computer ( This proc will reset any fuel transfer valves that indicates amber: Pulling and reset all the cb's)

Ext.fuel Pnl : BRAKES SET, ENGs OFF,PANEL OPEN but MODE SELECT….OFF Cookpit Ref Pnl P/B REFUEL…OFF Pull and reset the relevant CBs: Fuel FQI Chan 1 A13 Fuel FQI Chan 2 M27 Fuel FQI Chan ½ L26 /121VU FUEL LEAK DETECTION FUNCTION WILL BE LOST FOR THE REMAINEDER OF THE FLIGHT. FLIGHT CREW FCOM 3.03.15 THE FUEL AUTO FEED FAULT ECAM CAUTION WILL BE LOST FOR THE REMAINDER OF THE FLIGHT

Fuel Apu LP vlv Fault msg. Triggered when the Apu master sw is selected off during an emer shut down or auto shut down

Cycling the master sw on then off may clear this msg

80 sec

46

G

Simul. Trigger of fuel L XFR valve closed R XFR valve closed FUEL SD no fault FUEL LEAKAGE RATE ANALYSIS ACC AMM 28-11-00 P502

ATA28 System

G

G

G

WRONG FUEL USED INDICATI ON AFTER ENGINE SHUT DOWN ENG 1 / 2 LO PRESS VALVE FAULT ( On ECAM vlv Orange, in transit Pos.) XFR VALVE 28QM 71 QM 11 QM + XFR VALVE

FQIC RESET REQUIRED

Previously Dry the leak area - LIGHT LEAKAGE After 10 minutes there is a fuel leak indication that does not go further than 100MM/3.94 INCH and 180MM/7.09INCH in any direction. - CONTINUOUS LEAK After 10minutes there is a fuel leak indication that is more than 180MM/7.09INCH in any direction.

Procedure

Length Self

Test

PERFORM EIS DMC SWITCHING F/O 3 CAPT 3 AND BACK TO NORMAL

MASTER LEVER ON - OFF

A/C De-energized Bite Test of FLSS on the second Fuel page

46

30 QM 73 QM 12 QM Inside PFR FUEL XFR Fault

G

FUEL RETURN VALVE TEST

ATA28 System

G

FOLLOWING ECAM MESSAGGE S (ON GROUND AFTER REFUELLIN G)

four valve XFR CB overall. (2 x overhea d, back wall 2 X) ECAM FUEL page to choose Pull a CB. Action on ECAM: A ride on Valve, a valve is in transit orange The CB drawn into print again. Action: Both Valve to go. Reset with the PB Refueling the system, then the same procedure with the othe r three CB FQIS CB reset the COMPLETE SYSTEM TEST POSSIBLE ONLY WITH FADEC “B”

Procedure

Length Self

Test

FUEL L XFR VALVE CLOSED -L/H OUTER TANK UNUSABLE FUEL R XFR VALVE CLOSED -R/H OUTER TANK UNUSUABLE CLEAR THIS NUISANCE MESSAGES BY OPENING THEN CLOSE AFTER 5 SECS : FUEL/FQI/CHAN 1……….A13 FUEL/FQI/CHAN 2……….M27 (THIS CB RESET TRIGGERS THE FQIC POWER UP TEST FOLLOWED BY AN FLSS BITE TEST. DURATION MAX 2 MINUTES)

2 MIN

46

ATA29 System

G

G G

Procedure

Hyd Reservoir Low Pressure msg PTU Faults (not caused by cargo door ops after eng start)

To Clear: Run engs or pressurize hyd reservoir with apu (usually happens after maitenance)

PTU FAULT caused by cargo door ops within

Reset with Engines running: a)Reset msg using Master/caut b)sel HYD page Ecam

Length Self Test

Reset N34/121vu Saol Valve G/Y PTU

46

30sec after second engine start and ptu ecam failure msg. NOTE: This procedure will not reset real ptu failure or hide real faults in ptu sys

F

HYD “Y” SYS LO PR DURING FLT

c)Yellow Hyd Elec pump ON d)select Yellow Hyd Elec OFF e)wait min 30sec f)cycle PTU ON-OFF-ON g)sel 1eng Green hyd pump OFF ptu should operate Y to G h)sel 1eng Green hyd pump ON I) Sel 2eng Y hyd pump OFF ptu should operate G to Y J) sel 2eng Y hyd pump ON k) Ecam should be normal

IF ON THE FLT/CTL PAGE ALL YELLOW HYD POWERED ACTUATORS ARE AMBER IF ON THE HYD PAGE ELEC PUMP IS STILL RUNNING . SYSTEM PRESURE INDICATES 3000PSI, BUT THE WORD YELLOW IS INDICATED IN AMBER THE CARGO DOOR OPS LOGIC IS STILL ENGAGED. DUE TO A DEFECTIVE RELAY 6MJ OR 3816GX _(COULD HAPPEN INTERMITTEND,ON/OFF CYCLES) >PULL CB T12 DOORS CARGO/CTL WAIT 45 SEC IF SOLVED, LEAVE THE CB OUT AND CONTINUE OPS. IF NOT, FURTHER T/s NEEDED NOTE: CARGO DOORS OPS WITH HANDPUMP NORMAL OPS OF Y ELEC PUMP IS NOT AFFECTED

ATA29 System

G

HYD COMPONEN TS EXTERNAL LEAKAGE

Procedure

Length Self Test

ACC AMM 29-00-00 PAGE 601

46

F

F

HYD G/B/Y SYS LO PR WARNING WITH SYST PRESS 3000 PSI ON ECAM HYD PAGE

(FOR REFERENCE SEE AOM/OM-B29.1 PAGE 4) CHECK LEAK MEAUSEREMNT VALVES ARE STILL OPEN

A320 ONLY

CYCLE CB B RSVR AIR PRESS XMTR…………P34

B RSVR LO AIR PRESSURE ON GND

ATA30 System AntiIce L(R) windshield

G

BLUE HYD SYS IS EQUIPPED WITH ADDITIONAL RESERVOIR LOW AIR PRESSURE SWITCH 2387GH WICH IS ACTIVATED AT 30PSI DUE TO MORE DELICATED RAT ISTALLED ON A320

Procedure If the warning occur on GND with OAT greater than 40° - 60° C and AC packs OFF. Switch ON both Air Conditioning PACKS, 5s reset CBs: WHC 1………….X13/121vu WHC 2 ………...W13/122vu

Length Self Test

5sec

46

G

Windshiel d Heat FAULT or WINDOW FAULT WHC – Window Heat Computer

G

G

DMCU – Drain Mast Control Unit

ICE DET

G

BRAKES SET Pull for at least 5 sec and reset the relevant CB: WHC 1 Left…….X13 Window L heat…..X14 WHC 2 Right …. W13 Window R heat…..W14 PUSH THE HEATER FIRST X14-W14 BEFORE THE CONTROLLERS X13 – W13 ON GND ONLY - BRAKES SET Pull and reset the relevant CB: FWD Pax Comp 2000VU Drain Mast REAR Pax Comp 2001VU Drain Mast If the self test is satisfactory, the message “Drain Mast OK” will appear on the PTP system status page of CIDS

5 sec

10 sec

Pull and push 2c/b ICE DET L(R)…..V12 and V13 /122VU BRAKES SET ECAM Warnings: ANTI–ICE CAPT F/O SBY PITOT ANTI–ICE CAPT F/O SBY AOA ANTI–ICE CAPT F/O SBY TAT ANTI–ICE CAPT F/O SBY PROBES For all these messages pull for 3 sec and reset the following CBs: ADIRS……….OFF PHC 1………..D3 PHC 2 ……... Y12 PHC 3 ……….Y16

PHC – Probe Heat Computer

Verify ECAM warning disappears. If warning persists follow procedure related to warning. Pull CB relevant to faulty system listed below. Verify relevant ECAM warning appears for associated component, then reset CB. If ECAM warning concerning the suspect component remains, refer to MEL. If other associated component remains SBY after these checks, PITOT……...Z16 maintenance is required. CAPTS AOA……..D4 F/O AOA ……….Y13 SBY AOA ….….. Z15 CAPT PITOT …….D2 F/O PITOT……...Y14

CAPT STATIC…...Z13 F/O STATIC……..Y11

46

9 sec up to 14 sec

ATA30 System

G

System 1 System 2 System 3

G

WING ANTI ICE TEST WITH APU BLEED

Procedure

Length Self Test

If no help reset ADIRU1: F7,T6 ADIRU2:N9,N7,N5,N11 ADIRU3:N8,N6,N4,F9,N10 CONDITIONS: - PACKS OFF - APU BLEED ON - CB V17/ZONE TEMP CTL OPEN - CHECK BLEED PRESS APROX 48PSI TEST: 1)WING ANTIICE SWITCH ON ON BLEED PAGE CHECK LINES GREEN AND TRIANGLES(AI VALVES) GREEN. SWITCH BLUE ON ( DRG TRANSIT FAULT LT MAY APPEAR FOR A SHORT TIME) 2) AFTER 10SEC BOTH TRIANGLES AMBER/LINE GREEN 3) AFTER 30SEC BOTH TRIANGLES OFF/LINE

46

GREEN. (DRG TRANSIT FAULT LT MAY APPEAR FOR A SHORT TIME) THIS CONFIRMS OPERATION OF AI VALVES WITH SUFFICIENT PRESSURE AS FAULTS ARE OFTEN TRIGGERED DUE LOW PRESS (SEE ALSO QRH)

ECAM Warning

C/b

PHC

CAPT AOA CAPT PITOT CAPT L (R)STAT CAPT TAT

AOA1…………….…..D4/49VU PITOT 1………….…..D2/49VU 1STATIC………..…Z13/122VU 1 TAT…………..….Z12/122VU

1

F/O AOA F/OPITOT F/O L (R)STAT F/O TAT

2AOA………….….Y13/122VU 2PITOT……...…..Y14/122VU 2STATIC…………Y11/122VU 2 TAT……….…….Y15/122VU

2

STBY AOA STBY PITOT STBY L (R)STAT

3AOA………...…..Z15/122VU 3PITOT.…………..Z16/49VU 3STATIC………….Z14(122VU)

ATA31 System ADIRS Fault

G G / F

FWC – Flight Warning

Procedure Reset 15sec the cb: ADIRU1….F6 /49vu ADIRU1…. /105vu ADIRU2…..N7/121vu ADIRU2…..N5/121vu ADIRU3…..N6/121vu ADIRU3…..N4/121vu to power-up the test : On GND, IR 1(2)(3) rotary sel switched to OFF for 15sec, then to NAV Pull and reset the relevant CB: for 1sec in FLT , for 50 sec on IN FLIGHT GND PULL AND PUSH with NO 50sec WAITING

3

Length

Self Test

5sec

FWC 1….. F1 or E2 FWC 2……...Q7

46

Only pull one CB at a time

50 sec

DFDR

Both Engines OFF pull and push c/b: RCDR/DFDR…K16/121VU FDIU test with RCDR GND CTR on DFDR test on MCDU via FDIU

CFDIU – Central Fault Data Interface Unit

Pull for minimum 3 sec and reset the following CBs: CFDS CFDIU Sply J 18 CFDS CFDIU Backup J 17

FDIU –

ENG 1 and 2 OFF BRAKES ON Pull and reset the following CBs: RCDR FDIU and QAR K17 ENG 1 and 2 OFF Pull and push : AIDS & RCDR FDIMU…....K15/121vu

G

25sec

G G G

G

Flight Data Interface Unit (CLASSIC) FDIMU (Enhanced ) DMC – Display Manageme nt Computer DMU – Display

G

60 sec

25 sec

25sec 4sec

Pull and reset the relevant CB: DMC 1...E9 and E11 DMC 2...Q8 and R8 DMC 3...E9, E10, Q9 ENG 1 and 2

OFF

40 sec

Manager Unit Pull and reset the following CB:

AIDS DMU & DAR….K15 DU – Display Unit

G

Pull for at least 6 sec and reset the following CB: EIS PFD Capt E3 and E4 EIS PFD F/O R3 and R4 EIS ND Capt E1 and E2 EIS ND F/O R4 and R6 EIS ECAM DU Upper E5 and E6 EIS ECAM DU Lower R10 and R11

5 sec to

20 sec

46

SDAC – System Data

Acquisition

Concentrator 5sec

G

Pull and reset the relevant CB:

SDAC.1 SDAC 1 SDAC 1 and 2 EIS SDAC 1

F2 and F4 F5,P3 and P4 Q3 and Q4

SDAC.2 SDAC 2 SDAC 1 and 2 EIS SDAC 2

ATA31 System

G G G G

ECP Ecam Ctrl pnl No AIDS Indic. displayed on MCDU menu ECAM page(s) Locked… ELECTRICAL CLOCK Located On LWR ECAM

F3 F5 , P3 , P4 Q2, Q5 and Q6

Procedure Pull and push c/b: EIS/ECAM/CTL PNL…E12/49vu AC ON GND! reset at least 1sec: AIDS DU & QAR…..K15/121vu Reset for at least 1sec: FWS FWC 1 SPLY….F1/49vu EIS FWC 2 SPLY….Q7/121vu BRAKES SET CFDS/CFDIU/BACKUP………………………………..J17/ 121vu CFDS/CFDIU/SPLY………………………………...… J18/121vu

Length

Self Test

40sec

50sec

reset: 3s

46

Pwr: 1m

MAINT

F STS

“DAR”

G SDAC

FAULT

F

MASTER WARNING OR CAUTION & ECAM PAGE BLOCKED

G CIDS in

Status display is ok

calculation f ueling send ACARS is no t possible or not FOB i s shut down after engine shut down

ATA31 System DMU Maintenanc e status

RESET BY CYCLING OF: AIDS DMU AND DAR ….K15 IF UNSUCCESSFUL FWC 1 SPLY…………F01 FWC 2 SPLY………...Q07 RESET BY CB: SDAC 1…………………F04 SDAC 2 ………………..Q06 - ON EITHER COCKPIT SIDE MASTER CAUTION ON - ON OPPOSITE SIDE MASTER CAUTION OR WARNING ON AND /OR ECAM PAGE IMPOSSIBLE TO RESET: PULL SIMULTANEOUSLY FOR 10SEC: FWC 1 SPLY…F01 & FWC 2 SPLY….Q07

50Sec

Reset CBs from M05 to M14, Q14, from G01 and G05

DMU FAULTY

Procedure

Length Self Test

DMU change, because the backup battery is "low".

46

FWC 1 and 2 WARNING

ATA32 System

FWC Test : with MCDU 1- Instrument 2- FADEC1 or 2 switch 3- ECAM 1 or 2 Test (= FWC 1 or 2 )

Procedure

Length Self Test

46

BSCU – Brake and Steering Control Unit

F

BRAKES SYS 1(2) FAULT or BRAKES BSCU CH 1(2) FAULT

OR WHEEL N.W STEER FAULT or WHEEL N/W STRG FAULT

LGCIU – Landing Gear

G

F F

G

Control Interface Unit

TPIS – Tire Pressure Indication System BTMU Brake Temp. Monit. Unit

NW STEER FAULT on Ecam

G

GEAR RETRACTIO N FAULT ALERT

G

NW STRG DISCON WITH SELECTO R NORMAL

In Flight L/G RETRACTED: Anti Skid and NWS switch OFF For 1 sec and then ON On Ground: Aircraft must be stationary. Anti Skid and NWS switch OFF , Parking Brake ON then Pull and reset the following CBs: HYD Braking and Steering M33 M34 M35 M36 And then Anti Skid and NWS switch ON Note: After any BSCU reset : 1. Check brake efficiency 2. Record BSCU reset in the logbook

1 sec

BRAKES SET - G HYD Depress - ENG master sw1 off – PTU off Pull and reset the following CB: One at time PULL for a minimum of 30 sec LGCIU1…...C9 & Q34 PUSH in order Q34 - C9 LGCIU 2…..Q35

1 sec

Pull and reset the following CB: Hyd Tire Press Self test last 45 sec if CFDS is not available

5 sec or 45 sec

M31

Pull and push: BRK TEMP DET UNIT…M37 or M32

RESET BY EITHER -CYCLING A/SKID & n/w STRG SWITCH ON-OFF-ON OR DO NOT RESET BELOW CDs WHILE A/C IS MOVING BRK & STGR SYS 1 CTL……………………… M34 BRK & STGR SYS 1 IND &SPLY…………..M33 BRK & STGR SYS 2 CTL……………………… M35 BRK & STGR SYS 2 SPLY…………………….M36 This warning can be triggered by heavy rains on the ground CYCLE A/SKID & n/w STRG SWITCH ONOFF-ON TECH.KNOCK ON ELECTRICAL BOX MAY HELP TO OPEN SWITCH. IN OFFICIAL PROCEDURE TO FLY A/C TO BASE: DISCONNECT ELECTRICAL PLUG ON NW

46

STEERING ELECT. BOX AND SECURE

ATA32 System NOSE WHEEL STEERING FUNCTION CHECK TASK 3251-00-720003

G

Procedure

Length Self Test

LANDING GEAR CTRL LEVER…………………………………..DOWN FREE FALL CONTROL HANDLE.. ……………………………...NORMAL TOWING LEVER………………………………………………….. ….NORMAL POS ANTI SKID NOSE WHEEL SWITCH…………………………..ON ECAM SYSTEM WHEEL PAGE………………………………… ON VIEW RUDDER PEDALS AND NOSE WHEEL STEERING HANDWHEEL………………………………………………..NE UTRAL POSITION PULL CBs: ENG 1 OIL PRESS…………………………N40 ENG 2 OIL PRESS…………………………N42 GREEN HYD POWER ACCU CHEKLIST…………………..ON OPERATE NSW STEERING WHEN A/C IS ON JACKS ADDITIONALLY PULL: BCSU SYS 2 …………….U37 INSIDE E/E COMPT

G

G

LDG SHOCK ABSORBER FAULT

CB RESET WILL NOT SOLVE THE PROBLEM

AIRCRAFT BRAKE NOISY

Should have been set the park brake while the engine shut down, then the BSCU assumes that there is a pressure loss. So the brake pressure for the next cycle for safety reasons by up to 40 bar increases. The reset is for: Nose wheel steering on-off, or C / B reset M36

TROUBLE CAUSED BY PUDDLES OF WATER OR SHLUSH ON THE RUNWAY OR TAXIWAY. LEADING TO A WRONG RADIO ALTIMETER INPUT: AIRCRAFT MUST BE TOWED / TAXIED TO A POSITION WHERE IS NO SUCH INFLUENCE.

46

G

G

TRIPLE INDICATOR ACCU PRESSURE UNDER GREEN MARK

PARKING BRAKE IS NOT SHOWN ON MEMO PAGE

ATA32 System CHECK LDG HYDR PIPING WARNING

Yellow hydraulics pump ON (about 2850 psi) switch PTU, when the hydraulic pressure now coincides (approximately 2100 psi) then the component is leaking internally as LDG MLG door selector valve. everything should be normal, accupressure check required. At the park brake control valve plug # B, a bridge between D & E do when the parking brake then page indicated on the memo, then the Park Brake Control Valve mechanism to be changed. FYI: Without this input one CVR test is not possible.

Procedure

Length Self Test

BRAKE SELECTOR VALVE MUST BE REPLACED

46

ATA33 System

Length

Self Test

Procedure

Cabin lights stuck in bright

Reset CIDS2 through MCDU. If no help reset DEU A’s M8 thru M13/121vu

F

Cabin lights will not turn ON

reset: CIDS FWD ATT PNL 121vu

F

Cabin Light reamains 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 by the failed deu will remain on BRG

F

F

F

CABIN, ALL LIGHTS FLICKERIN G EXIT SIGN/S ABOVE CABIN DOOR/S INOP

M14 /

TRY TO INCREASE THRUST ON ENGINE NR 2 (FAULT FROM IDG#2 )

CYCLE CBs SIMULTANEOUSLY: LIGHTING/EMER LT/CABIN …………………………H05 LIGHTING/EMER LT/CABIN …………………………H06 LIGHTING/EMER LT/CABIN …………………………H07

46

LIGHTING/CABIN/EMER/LT …………………………V07

G

G

G

STROBE LIGHT ALWAYS ON AT ALL SWITCH POSITION STROB E LIGHT ON AT ALL POSITI ON EXCEPT OFF PAX READING LIGHT WHOLE ROW OF SEATS DOES NOT LIGHT

ATA33 System

G

G G

INTEGRATE D LTS (ATC,ECAM SWITCHING PNL, TRIM PNL NO LIGHT INTEGRAL LTS OVERHEAD PANEL NO LIGHT BEACON UPPER ALWAYS ON EVEN IN OFF POSITION

REPLACE RELAY 12 LV ON PANEL 103VU

REPLACE RELAY 13LV ON PANEL 103VU

TEST ON CIDS WILL RESET THE SYSTEM

Length

Procedure

Self Test

REPLACE FUSE L , FRONT AVIONIC COMPT, IN FRONT OF F/O PEDALS

REPLACE FUSEBOX 6LF BEHIND COCKPIT OVERHEAD PANEL

REPLACE RELAY 8 LV , PANEL 103VU

46

G

G

BEACON LOWER ALWAYS ON EVEN IN OFF POSITION EMERGEN CY LIGHT TEST

REPLACE RELAY 9 LV , PANEL 103VU

-

ATA34 System

EMERGENCY LIGHTS……………….OFF NO SMOKING LIGHTS …………….OFF TEST ON FAP (EMERG. LIGHTS)

Procedure

Length

Self Test

F Navigation

Pull for at least 3 sec and reset the relevant CB:

ADF 1…………..……..K3 or H14

2

ADF 2………….…..…..K2/121vu

ATC 1 …………..….…G11/49vu ATC 2 …………..…….K7/121vu

3

46

DME 1……………..…G14/49vu

2

DME 2……….………K6/121vu

GPWS………………...P6 or P7

2

ILS 1……..…………..G12

1

ILS 2…….…………..K9

1

MMR1………………..G12/49vu

1

MMR2………………..L7 or K9

1

TCAS out 5s….………K10/121vu

3

RADAR 1………..…..K13

30

RADAR 2……..……..K14

30

Radio Altimeter 1…...K11

3

Radio Altimeter 2…...K12

3

VOR 1……………….G13

3

VOR 2……………....K8

G

ADIRU – Air Data Inertial Reference

3 Pwr up5 sec

Position the selector switch of the relevant unit to OFF

46

unit

Wait for at least 3 min then to NAV

DAR msg

Msg may be related to media(tape) being full.

Ac on GND and Eng stopped

Reset 1sec :

G

DMU & QAR……... K15/121vu

FDIU & QAR ……….K17/121vu

ACCLRM……………..K18/121vu

during test