3 Reset Tips

(1)

RESET & TIPS

PROCEDURES

GENERAL CONFIGURATION

(2)

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’

(3)

FAP LAYOUT SELECTION= CODE “318” ENTER

COMPUTE

R C/B C/B pulled power-up test

ACP n1:G6 , n2:G7 , n3:M02 1s 1s ADF n1: H14 2s 2s ADIRU N04-10 ; F06-09 >20sec 5s AEVC D06/06 ; Y17 1s 85s ATC n1:G11 , n2:K07 1s 3s BMC AVIONIC COMPARTMENT 1s 22s BSCU M32 - 36 >30ms 1.6sec CFDIU J17/18 >3sec 60s CHC … 200ms 28s CIDS G01/02/(03-05);M05-07/(08-14) >10sec 180s CPC n1:D09 , n2:Y22 >2sec 1s DMC (Sply)n1:E11,n2:Q08,n3:E10/Q09 >1sec 4s DMCU 1s 10s DME n1:G14 ; n2:K06 2s 2s DMU (AIDS) K15 1s 40s

DU n1:E01-04 ; n2:R03-06; Ecam:E05/6,R10/11 >6sec 5-20sec max ECB L41 >250ms 3sec max EIU n1:A04,R41 n2:A05,Q40 >200ms 3sec ELAC n1:B11 n2:R20 30ms or pb _OFF-ON _8sec EVMU R44 >140ms 25 - 100 sec FAC n1:B03/04 n2:M18/19 >5s 90 sec FADEC Eng1:A06/R21 Eng2:A04/Q40 1sec 2 sec max FCDC n1:B10 n2:Q20 >3sec 3 sec FCU n1:B05 n2:M21 >7sec 10 sec

FDIU K17 1sec 25 sec max

FDU Eng1:A06/Q38 Eng2:A07/Q39 APU:L43/44 200ms 57 sec FMGC n1:B02 n2:M17 (FD's:OFF) >5sec 120 sec max FQIC(320) chan1:A13 chan2:M27 >2sec 80 sec max FQIC(321) chan1:A13 chan2:M27 >8sec 150 sec max FWC n1:F01 n2:Q07 >1sec 50 sec GCU n1:T26 n2:T27 APU:Y25 15ms 30ms

GPCU Y24 none 35ms

GPWS P06/07 1sec 2 sec

ILS n1: G12 n2:K09 1sec 1 sec LGCIU 1GND: Q34 n1:C09 n2:Q35 >3sec 210ms MCDU n1:B01 n2:N20 >200ms 45 sec PACK CTRLR n1:X21/22; W21/22 n2:Y18-21 2ms 30 sec PHC n1:D03 n2:Y12 n3:Y16 3sec 9 sec RAD ALT n1:K11 n2:K12 2sec 3 sec RADAR n1:K13 1sec 15 - 30 sec RMP n1:G10 , n2:L02 , n3:L03 (not used) 2sec 2 sec SDAC F02-05 and P02-05 and Q02-06 >1sec 5 sec SDCU chan1:C06 chan2:T18 200ms 70 sec SEC n1:B08 n2:Q18 n3:Q19 5sec 18 sec SFCC(320) FLP:B07/Q21 SLT:B12/P16 >200ms < 2 sec

(4)

SFCC(321) FLP:B07/Q21 SLT:B12/P16 >50ms 65 sec VHF/HF n1:G09 n2:L04 n3:L05 1sec 10 sec VOR n1:G13 ; n2:K08 RMI:F13 3sec 3 sec WHC n1:X13 n2:W13 5 sec 5 sec ZONE

CTRLR 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:

(5)

TSM

24-00-00-810-818

ATA21

-System

Procedure

Length

Self

Test

G

CPCU – Cabin

Pressure Control BRAKES….SET

1 sec Unit Pull and reset the relevant CB:

CPCU # 1………... D9 CPCU # 2…………...Y22

F

AEVC – Avionic Pull and reset the relevant CBs:

85 sec Equipment

Ventilation Control Air Cond / avncs vent Ctl D5 / D6 Air Cond / avncs vent mong Y17

F

AVIONIC SMOKE

ALERT Cycle both push button:

-

Generator 1 Line

-

Generator 2 Line

G

AEVC P/B BLOWER and EXTRACT….. ……AUTO

VENT AVIONICS

SYS FAULT DITCHING ...OFF BRAKES ...SET AVNCS/VENT/MONG

Y17 / 122VU 85 sec

G

VENT AVIONICS SYSTEM FAULT DUE TO THE FILTER

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

G

AVIONICS VENT EXTRACT VALVE AMBER/OPEN

Cycle c/b:

Aircond. Avionics vent ctrl

………..D5

Aircond. Avionics vent ctrl

………..D6

Aircond. Avionics vent Mong …………

Y17

Perform TEMP Control Test

F

Cargo Ventilation Pull and reset the relevant CB:

Fwd Cargo Vent Ctl C8 Fwd Cargo Vent Fan T22 30 sec

F

AFT Cargo HEAT

(6)

F

AFT Cargo VENT

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

F

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

Procedure

Length

Self

Test

G

Pack Controller

ON GND only - BRAKES SET Pack 1 or 2 OFF

30 sec Pack Flow Control Valves Shut

Pull and reset the relevant 4 CBs: No.1. Air Cond/Pack Temp/Ctl Sys

X21 X22 Y18 Y19 No.2. Air Cond/Pack Temp/Ctl Sys

W21 W22 Y20 Y21

G

PACK 1 OR 2

FAULT 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

G

PACK TURBINE BYPASS VALVE POS. INDICATION X - OUT

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

G

PACK OVERHEAT Pack Sensor 13HH fault

G

Zone Controller OnGND only - BRAKES set NO BLEED air

Note: if engines running FLT IDLE will be set during

reset

(7)

Air Cond/Pack Temp/Ctl Sys V17 V18 V19 V20 / 122vu

Note

: Resetting zone controllers with engines

running will generate the warnings ENG1(2)

FADEC under the MAINTENACE heading on

the STATUS page.

30 sec up to 2 min

ATA21

-System

Procedure

Length

Self

Test

F

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

F

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

G

PACK REGULATOR FAULT with no associated Maint. Message

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

Hot Air Valve Wait 30 sec after switching the Packs ON before

attempting a 60s reset using the HOT AIR push button

G

ACSC Pull for at least 5s. AirConditioning N1

Sys Controller TEMP CTL SYS1 CHAN B D8/49VU A318 -

ENHANCED TEMP CTL SYS1 CHAN A(B) X21,X22,Y18/122VU

N2

TEMP CTL SYS2 CHAN A(B) W21,W22,Y20,Y21/122VU

G

CABIN TRIM AIR

AC on GND

VALVE MSG

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:

(8)

from C to H and from back

ATA22 - System

Procedure

_{Self Test}

Length

F

FMGC – Flight Management Guidance

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

2 min

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 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

G

FMGC – Flight Management Guidance Computer

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 Do not use MCDU until end of self test. Wait a further 10 sec prior to switching the FD to ON

G

DOUBLE FMGC Fault ADIRU 1,2,3… ALIGNED FD 1 and 3…….OFF Pull and push at same time : FMGC1………B2/49VU FMGC2………M17 / 121VU

(9)

wait 10 seconds before re-engage FD

ATA22 - System

Procedure

Length

Self

Test

F

MCDU

Both MCDUs locked or blank

FMGS malfunction

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

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)

45sec

G

FAC – Flight Augmentation Computer

ON GND - BRAKES SET Engine 1 and 2 OFF 95 sec

Hydraulics OFF or ON (p/b Yellow Elec pump 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

(10)

Note: With Hydraulic pressurized the Yaw Damper, output is also tested. Do not alter hydraulic configuration during self test

G

FMGC msg: "OPPOSITE FM IN PROGRESS OF

FMA SHOWS OFFSIDE FDs"

ENGINES OFF Pull for at least 4 sec : FMGC 1……B2/49vu

FMGC 2……M17/49vu _120sec

G

AUTO PILOT 1 FAULT ENGINES OFF

Pull for at least 4 sec : FMGC 1……B2/49vu 120sec

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

2min

ATA22

-System

Procedure

Length

Self

Test

G

/

F

FCU – Flight Control Unit

_{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.

On ground:

Pull simultaneously for 7 Min and reset the

following 2 CBs:

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)

10 sec

(11)

G

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

95s

G

Rudder travel

Limit

system 1

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

G

Rudder travel Limit

system 2

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

G

AUTO FLT RUDTRV LIM SYS Reset FAC1 and FAC2 p/b FAULT MSG

F

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

F

Ecam

Time indication

Reset c/b CFDIU ……….J18

ATA22 - System

Procedure

Length

Self

Test

(12)

ATA23 - System

Procedure

Length

Self

Test

F

HF Pull and reset the following CB:

10 sec HF1 L10/121VU or HA14/49VU HF2 L13/121VU

VHF Pull and reset the following CBs:

11 sec VHF 1……….G9

VHF 2……….L4 VHF3/ACARS (SB23-1030)..L5 ACP Audio Control Pnl Pull and reset the following CB:

1 sec ACP Capt G6 ACP F/O G7 ACP 3 M2

F

G

ACP Freqs will not change from standby to active windows

Turn affected RMP OFF then ON to reset

ON GND With ENGs OFF If No help, Then pull for at least 4 sec: FMGC1: B2 and

FMGC2:MJ17 120sec

F

RMP – Radio

Management Panel Pull for at least 2 sec and reset the relevant CBs:

2 sec RMP 1 – Com RMP 1……..G10

RMP 2 – Com Nav RMP 2… L2 RMP 3 – Com Nav RMP 3 …L3

(13)

G

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.

2 min doors open

If unsuccessful: Pull and reset the following CBs for at least 10 sec if doors are closed and 30 sec if doors are open.

1 min doors closed 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)

Pull also P13 and P14 (121u) if NO FROZEN RMP

Push CBs in opposite order

F

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. Directors

ATA23

System

Procedure

Length

Self Test

G

4min

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}

(14)

1sec

F

G

EVAC

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

Alarm steady

active

F

4 min

(15)

F

CVR

with engines Shutdown, pull for at least 10sec and then push:

CVR SPLY………..E14/49VU

F

FAP

CIDS I (CLASSIC)

pull for 10sec and push

FWD ATTND PNL……M14 or Q14/121VU

if no help, reset for 10sec:

PRAM………..panel 2000VU

CIDS II (ENHANCED)

Pull for 10 secs :

FAP ESS………..H1 /49VU

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

ATA23 - System

Procedure

Length

Self

Test

F

Cain Phone / pull and push after 10sec: Music / PRAM………..panel 2000VU Prerecordered ads

PAX Entertain. Reset cb:

will not turn ON CABIN COM SYS PES….F6/2000vu or OFF If no help, then reset all DEUs:

A318

FAP ESS…….H1

FAP 1Norm….Q13

Push Q13 then H1

(16)

M7 through M13 /121vu

F

SEAT VIDEO sys Reset individual video unit, unit problems small hole just fwd of screen on

the same panel is reset button (on-off)

If no help Turn off to stow

F

AIRFONE sysAirPHONE sys ONLY ONE RESET IS ALLOWEDcb reset 3 min:

AIRFONE……….……E7/2000VU 1sec

F

ATSU

(ACARS)

reset

Cycle c/b

L15 and L16

G

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

F

Pilot

SATCOM

handset

blue led

light on and

no tone

Reset cycling cb on 2000VU –

FWD cabin ceiling panel

Pilot Handset A321 – C08

A320 – F08

A319 – C08

ATA24 - System

Procedure

Length

Self

Test

G

No AVAIL green legend on Ext Pwr P/b switch

On GND- ENGs OFF - APU OFF - GPU connected Reset the following cb: Y24/122vu GPCU

G

Transformer Rectifier Unit Fault

Reset T/R through MCDU or Reset all three using guarded button on 103vu panel in electrical bay

(17)

G

BCL – Battery Charger Limiter

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

1 sec If no help, reset from panel 105VU:

BAT REF BCL1

BAT BUS REF BCL1

BAT REF BCL 2

BAT BUS REF BCL 2

G

GCU – Generator Control Unit

Relevant generator control push button switch at the overhead panel OFF then ON

1 sec

If no help:

Engines……Shutdown

APU………Shutdown

BAT 1 & 2..Shutdown

Gen Faulty…….OFF &ON

BAT 1 & 2…….ON

G

GPCU – Ground ON GND - BRAKES SET ENG 1 and 2……….OFF Power Control Unit APU………...OFF

(18)

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

Then RE - ENERGISE

G

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

A318&

ENHANCED

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

(19)

EXT PWR….keep ON 3s

G

ENGINE GEN on ENGINE MUST BE SHUT line(green line) DOWN!! Than reset : and parameters Eng1: GCU1………....T26/122vu

not shown Eng2: GCU2………….T27/122vu 30ms

G

STATIC INVERTER

FAULT Cycle BAT 1 and 2 p/b after otherIf no success Static Inverter plug must be dis/reconnected for reet – PLUG IS SEALED

ATA24 - System

Procedure

Length

Self

Test

G

If the RAT deploys when Battery switches to OFF

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

(20)

ATA25 - System

Procedure

_{Self Test}

Length

F

CDLS

Overhead panel

Cokpit Door

Select CKPT DOOR LKG SYS

Locking sys

OFF 10sec than NORM

If no help MeL

1sec

F

CDDS

video instable, with message VIDEO

NOT AVAIL, reset to be performed

Cokpit

Surveillance sys

Pedestal VIDEO sel……….OFF

INTEGRATED ON

P/B CokpitDoor Video OFF

Lower ECAM

wait 2 minutes than:

P/B CokpitDoor Video ON

wait 15sec than:

(21)

ATA26

-System

Procedure

Length

Self

Test

G

SDCU – Smoke

Detection ON GND- BRAKES SET Pull and reset the following CB:

10 sec up to 60 sec Control Unit SDCU Chan 1 T17 or C6

CLASSIC SDCU Chan 2 T18 to empty the memory, peform a reset of both FWCs (ata31)

G

SDF –

Smoke

Detection

Toilet &

Cargo

ENHANCED

Perform CIDS reset

(ata23)and to empty the memory,

perform a reset of both FWCs (ata31)

G

FDU – Fire

Detection

Unit

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

57 sec

G

SMOKE

CARGO

BOTTLE

FAULT

Pull C5-C6 /T18 –T17 , wait 5 sec,

than push simultanesly

C5+C6 within 2s T18+T17

G

SMOKE

LAV + CRG

DET FAULT

=>CIDS

-SDF

Pull C5-C6 /T18 –T17 , wait 5 sec,

than push simultanesly

C5+C6 within 2s T18+T17

G

SMOKE

LAVATORY

DET FAULT

with all lav

declared

NOP on

FAP

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:

(22)

‐ 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

Whatever afterwards AFT CARGO VENT C

B resetting

ATA27

-System

Procedure

Self Test

Length

G

SFCC/ WTB

ON GROUND ONLY

wing tip

brake

BRAKES SET

CFDS reset

ENGINES…….OFF

G , Y , B hyd depressurized

G

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

FLAPS LOCKED procedure for BOTH SFCC1 and SFCC2 _reset cb 1s Pwr up: 2s

(23)

G

SLATS LOCKED procedure for BOTH SFCC1 and SFCC2 or SLAT WTB BRAKE FAULT

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

reset cb 1s Pwr up: 2s

G

SIDE STICK priority msg

reset pb: FAC 1 & 2 switches

SEC 1,2 & 3 switches ELAC 1 & 2 switches

G

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

Procedure

Length

Self Test

G

Flight Control FLAPS LOCKED

OUT HYD MUST BE OFF Must perform WingTipBrake (WTB)reset through MCDU amm27-50-00

G

FLT/CTL Maintenance msg

(can be deferred) A/C on GND Reset for at least 3s: FCDC 1 SPLY..B10/49vu FCDC 2 SPLY..Q20/121vu 3s

N

B

:

R

E

S

E

T

O

N

E

G

ELAC –

Elevator

Aileron

Computer

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

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

ELAC 10sec 8sec 8sec

(24)

U

N

IT

P

E

R

T

IM

E

!

!!

!

not recommended.

G

SEC – Spoiler

Elevator

Computer

On GND - BRAKES SET

Appropriate SEC push button……….. OFF SEC 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 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

G

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

FCDC – Flight

Control Data

Concentrator

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

(25)

ATA27

-System

Procedure

Length

Self Test

G

SFCC – Slat

Flap Control

Computer

On GND - BRAKES SET ENG 1 and 2 OFF

2 sec

Pull and reset all 4 CBs with or without Hydraulic

Pressure: B6 R21 B7 Q21

-OR-ENG 1 and 2 Running or OFF Pull and reset the relevant CB according to ECAM Warning.

See table below.

G

RUD TRIM

TRAVEL

LIMITER

FAULT

See ATA 22 : HYD ON and reset p/b FAC1 and

FAC2 or c/b B3-B4 and M18-M19

95s

G

SLAT

PROBLEM

FCDC and SEC C7b Reset requie

Perform F/CTL Test

G

FLIGHT

CONTROL

WARNING

Perform GND SCAN for reset and fault

identification

G

“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 :

(26)

RESET FAC1 & FAC 2 c/b B3-B4-M18 –

M19

ATA27

-System

Procedure

Self Test

Length

G

LH/RH

ELEVATOR

FAULT AFTER

ENGINE

START

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

G

AILERON

SERVO FAULT

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

G

YAW DAMPER

FAULT After

engines start

BEFORE ATTEMPTING ANY CB RESET:

Consult MPM 03-22 page 1 Item

22-63-01

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

(27)

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

90 sec

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

Procedure

Self Test

Length

G

ELAC 1 / 2

PITCH FAULT

AFTER ENG

START

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)

ECAM

Warning

B 6

SLT/CTL AND MONG/SYS1

R 21

SLT/CTL/SY

S2

B 7

SLT/CTL AND MONG/SYS 1

Q 21

FLP/CTL AND MONG/SYS 2

(28)

Slats Fault

Reset

Together

Flaps Fault

Reset

Together

Slat Sys 1 Fault

Reset

Slat Sys 2 Fault

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

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

80 sec

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

G

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

(29)

G

Simul. Trigger

of fuel

L XFR valve

closed

R XFR valve

closed

FUEL SD no

fault

FQIC RESET REQUIRED

FUEL

LEAKAGE

RATE

ANALYSIS

ACC AMM

28-11-00

P502

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.

ATA28

-System

Procedure

Length

Self

Test

G

WRONG

FUEL

USED

INDICATI

ON

AFTER

ENGINE

SHUT

DOWN

PERFORM EIS DMC SWITCHING F/O 3

CAPT 3 AND BACK TO NORMAL

G

ENG 1 / 2

LO PRESS

VALVE

FAULT

( On

ECAM vlv

Orange,

in transit

Pos.)

MASTER LEVER ON - OFF

G

XFR

VALVE

28QM

71 QM

11 QM +

XFR

VALVE

A/C De-energized

Bite Test of FLSS on the second Fuel

page

(30)

30 QM

73 QM

12 QM

Inside

PFR

FUEL XFR

Fault

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

G

FUEL

RETURN

VALVE

TEST

TEST POSSIBLE ONLY WITH FADEC “B”

ATA28

-System

Procedure

Length

Self

Test

G

FOLLOWING ECAM MESSAGGE S (ON GROUND AFTER REFUELLIN G)

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)

(31)

ATA29

-System

Procedure

Self Test

Length

G

Hyd

Reservoir

Low

Pressure

msg

To Clear: Run engs or pressurize hyd

reservoir with apu (usually happens

after maitenance)

G

PTU Faults

Reset N34/121vu

Saol Valve G/Y PTU

(not caused

by

cargo door

ops

after eng

start)

G

PTU FAULT

Reset with Engines running:

a)Reset msg using Master/caut

b)sel HYD page Ecam

caused by

cargo door ops within

(32)

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

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

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

Procedure

Self Test

Length

G

HYD

COMPONEN

TS

EXTERNAL

LEAKAGE

(33)

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

F

A320

ONLY

B RSVR LO

AIR

PRESSURE

ON GND

CYCLE CB

B RSVR AIR PRESS XMTR…………P34

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

ATA30

-System

Procedure

Length

Self

Test

G

AntiIce L(R)

windshield

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

5sec

(34)

G

Windshiel

d Heat

FAULT or

WINDOW

FAULT

WHC –

Window

Heat

Computer

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

5 sec

G

DMCU –

Drain

Mast

Control

Unit

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

10 sec

G

ICE DET Pull and push 2c/b ICE DET L(R)…..V12 and V13 /122VU

G

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

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 after these checks,

maintenance is required.

CAPTS AOA……..D4 F/O AOA ……….Y13 SBY AOA ….….. Z15 CAPT PITOT …….D2 F/O PITOT……...Y14

PHC –

Probe

Heat

Computer

SBY PITOT……...Z16 CAPT STATIC…...Z13 F/O STATIC……..Y11

(35)

9 sec up to 14 sec

ATA30

-System

Procedure

Self Test

Length

G

System 1

System 2

System 3

If no help reset

ADIRU1: F7,T6

ADIRU2:N9,N7,N5,N11

ADIRU3:N8,N6,N4,F9,N10

G

WING

ANTI ICE

TEST

WITH

APU

BLEED

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

(36)

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

AOA1……….…..D4/49VU

1 CAPT PITOT

PITOT 1………….…..D2/49VU

CAPT L (R)STAT

1STATIC………..…Z13/122VU

CAPT TAT

1 TAT…………..….Z12/122VU

F/O AOA

2AOA………….….Y13/122VU

2 F/OPITOT

2PITOT……...…..Y14/122VU

F/O L (R)STAT

2STATIC…………Y11/122VU

F/O TAT

2 TAT……….…….Y15/122VU

STBY AOA

3AOA………...…..Z15/122VU

3 STBY PITOT

3PITOT.…………..Z16/49VU

STBY L (R)STAT

3STATIC………….Z14(122VU)

ATA31

-System

Procedure

Length

Self Test

G

ADIRS Fault 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 5sec

G

/

F

FWC – Flight Warning

Pull and reset the relevant CB: for 1sec in FLT , for 50 sec on GND

FWC 1….. F1 or E2 FWC 2……...Q7

IN FLIGHT

PULL AND PUSH with NO 50sec WAITING

(37)

Only pull one CB at a time 50 sec

G

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

25sec

G

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

60 sec

G

FDIU

Flight Data–

Interface Unit (CLASSIC) FDIMU (Enhanced )

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

25 sec

G

25sec

G

DMC – Display Manageme nt Computer

Pull and reset the relevant CB:

DMC 1...E9 and E11

DMC 2...Q8 and R8

DMC 3...E9, E10, Q9

4sec

G

DMU –

Display ENG 1 and 2 OFF 40 sec

Manager Unit

Pull and reset the following CB:

AIDS DMU & DAR….K15

G

DU – Display

Unit

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

(38)

G

SDAC – System Data

Pull and reset the relevant CB:

SDAC.1

SDAC 1 F2 and F4 SDAC 1 and 2 F5,P3 and P4 EIS SDAC 1 Q3 and Q4

SDAC.2

SDAC 2 F3 SDAC 1 and 2 F5 , P3 , P4 EIS SDAC 2 Q2, Q5 and Q6 Acquisition Concentrator 5sec

ATA31

-System

Procedure

Length

Self Test

G

ECP Pull and push c/b:

Ecam Ctrl pnl EIS/ECAM/CTL PNL…E12/49vu

G

No AIDS Indic.displayed on AC ON GND!reset at least 1sec:

MCDU menu AIDS DU & QAR…..K15/121vu 40sec

G

ECAM page(s)Locked… Reset for at least 1sec:FWS FWC 1 SPLY….F1/49vu

EIS FWC 2 SPLY….Q7/121vu 50sec

G

ELECTRICAL BRAKES SET

CFDS/CFDIU/BACKUP………..J17/ 121vu CFDS/CFDIU/SPLY………...… CLOCK Located On

reset: 3s

(39)

Pwr: 1m

F

MAINT

STS

“DAR”

RESET BY CYCLING OF:

AIDS DMU AND DAR ….K15

IF UNSUCCESSFUL

FWC 1 SPLY…………F01

FWC 2 SPLY………...Q07

G

SDAC

FAULT

RESET BY CB:

SDAC 1………F04

SDAC 2 ………..Q06

F

MASTER

WARNING

OR

CAUTION &

ECAM

PAGE

BLOCKED

- 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

G

CIDS in

Status

display is

ok

Reset CBs from M05 to M14, Q14,

from G01 and G05

calculation f

ueling send

ACARS is no

t possible

or not FOB i

s shut down

after engine

shut down

DMU FAULTY

ATA31

-System

Procedure

Self Test

Length

DMU

Maintenanc

e status

DMU change, because the backup

battery is "low".

(40)

FWC 1 and 2

WARNING

FWC Test : with MCDU

_{1- Instrument}

2- FADEC1 or 2 switch

3- ECAM 1 or 2 Test (= FWC 1 or 2 )

ATA32

-System

Procedure

Length

Self Test

(41)

F

BSCU – Brake and Steering Control Unit BRAKES SYS 1(2) FAULT or BRAKES BSCU CH 1(2) FAULT OR WHEEL N.W STEER FAULT or WHEEL N/W STRG FAULT 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

G

LGCIU – Landing Gear Control Interface Unit

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

F

TPIS – Tire Pressure Indication System

Pull and reset the following CB:

Hyd Tire Press M31 Self test last 45 sec if CFDS is not available

5 sec or 45 sec

F

BTMUBrake Temp. Pull and push:

Monit. Unit BRK TEMP DET UNIT…M37 or M32

G

NW

STEER

FAULT on

Ecam

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

G

GEAR RETRACTIO N FAULT ALERT

This warning can be triggered by heavy

rains on the ground

G

NW STRG

DISCON

WITH

SELECTO

R

NORMAL

CYCLE A/SKID & n/w STRG SWITCH

ON-OFF-ON

TECH.KNOCK ON ELECTRICAL BOX MAY

HELP TO OPEN SWITCH.

IN OFFICIAL PROCEDURE TO FLY A/C TO

BASE:

(42)

STEERING ELECT. BOX AND SECURE

ATA32

-System

Procedure

Length

Self Test

G

NOSE WHEEL STEERING FUNCTION CHECK TASK 32- 51-00-720-003 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

LDG SHOCK ABSORBER FAULT

CB RESET WILL NOT SOLVE THE PROBLEM 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.

G

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

(43)

G

TRIPLE INDICATOR ACCU PRESSURE UNDER GREEN MARK

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,

accu-pressure check required.

G

PARKING BRAKE IS NOT SHOWN ON MEMO PAGE

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.

ATA32

-System

Procedure

Self Test

Length

CHECK LDG HYDR PIPING WARNING

BRAKE SELECTOR VALVE MUST BE

REPLACED

(44)

ATA33

-System

Procedure

Length

Self

Test

F

Cabin

lights

Reset CIDS2 through MCDU. If no help reset

DEU A’s

M8 thru M13/121vu

stuck in bright

F

Cabin

lights

will not

turn ON

reset:

CIDS FWD ATT PNL M14 /

121vu

F

Cabin

Light

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

reamains ON BRIGHT when selected OFF or DIM

F

CABIN,

ALL

LIGHTS

FLICKERIN

G

TRY TO INCREASE THRUST ON ENGINE NR 2

(FAULT FROM IDG#2 )

F

EXIT

SIGN/S

ABOVE

CABIN

DOOR/S

INOP

CYCLE CBs SIMULTANEOUSLY:

LIGHTING/EMER LT/CABIN

………H05

LIGHTING/EMER LT/CABIN

………H06

LIGHTING/EMER LT/CABIN

………H07

(45)

LIGHTING/CABIN/EMER/LT

………V07

G

STROBE

LIGHT

ALWAYS

ON AT

ALL

SWITCH

POSITION

REPLACE RELAY 12 LV ON PANEL 103VU

G

STROB

E LIGHT

ON AT

ALL

POSITI

ON

EXCEPT

OFF

REPLACE RELAY 13LV ON PANEL 103VU

G

PAX READING LIGHT WHOLE ROW OF SEATS DOES NOT LIGHT

TEST ON CIDS WILL RESET THE SYSTEM

ATA33

-System

Procedure

Length

Self

Test

G

INTEGRATE D LTS (ATC,ECAM SWITCHING PNL, TRIM PNL NO LIGHT

REPLACE FUSE L , FRONT AVIONIC COMPT, IN

FRONT OF F/O PEDALS

G

INTEGRAL LTS OVERHEAD PANEL NO LIGHT

REPLACE FUSEBOX 6LF BEHIND COCKPIT

OVERHEAD PANEL

G

BEACON UPPER ALWAYS ON EVEN IN OFF POSITION

(46)

G

BEACON LOWER ALWAYS ON EVEN IN OFF POSITION

REPLACE RELAY 9 LV , PANEL 103VU

G

EMERGEN CY LIGHT TEST

-

EMERGENCY

LIGHTS……….OFF

-

NO SMOKING LIGHTS

……….OFF

-

TEST ON FAP (EMERG. LIGHTS)

ATA34

-System

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 3 ATC 2 …………..…….K7/121vu

(47)

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 3

G

ADIRU – Air

Data Position the selector switch of the

Pwr up5 sec

Inertial

(48)

unit

Wait for at least 3 min then to NAV

G

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

Ac on GND and Eng stopped

Reset 1sec :

DMU & QAR……... K15/121vu

FDIU & QAR ……….K17/121vu

ACCLRM………..K18/121vu

during test <Aids indication disappears 40sec

G

GPWS

Fault

GPWS P6/121vu

GPWS P7/121vu

This problem may be by ILS freq's that are

close and interfering with gpws sys Let Flt

crew taxi for 2-4 FT this will cause Gpws

recheck itself and clear the fault

If steady, 10 sec reset:

GPWS P6/121vu

GPWS P7/121vu

25sec

G

WINDSHEA

R Note: Msg on GND system may not be at Fault

DET Fault Reset FACS pbs first, IF no help

(49)

cb out 4s FAC2………..M18/121vu

ATA34

-System

Procedure

Length

Self Test

G

WINDSHE

AR DET

Fault

(Predictive

)

cb out 4s

CHECK for FAC RESET ata22

Note: Msg on GND system may not be at

Fault

Reset FACS pbs first, IF no help

RADAR 1 ………...….K13/121vu

G

TCAS fault

BRAKES SET

Reset the c/b for 5s.

COM/NAV/TCAS………...k10/121vu

TEST:

ADIRUS ALIGHED

FLIGHT INITIALISED

NAV

TCAS TEST

(4 SYMBOLS AND RATE OF CLIMB RANGE

RED)

G

ISIS

Malfunction

With aircraft STOPPED (no moving)

Pull c/b F12 wait 5sec Push F12

IF Aircraft MOVING (refuel- Loading..) ATT

flag may appear so RST P/b for 2sec than

auto test

120sec

F

DOUBLE

ATC-TRANSP

ORDER

FAILURE

RESET XPDR C/B:

ATC XPDR 1…..G11

ATC XPDR 2……K07

AFTER RESET WAIT FOR TERMINATION OF

INTERNAL TESTS

G

F/O ND

SHOWING

OFFSET

RANGE

BEFORE

ENG START

FMGC 1 / 2FAIL AFTER ENG START

CYCLE C/B B2 AND M17

G

FMS INIT

“B” PAGE

NOT

AVAILAB

LE

CYCLE BOTH FMGC CBs B2/M17 FOR AT

LEAST 1 MIN.

IF NO HELP, MAKE A COMPLETE A/C

POWER RESET FOR 1 MIN. POWER UP

TEST TAKES 2 MIN

2 MIN

F

GPS 1

OR 2

FAULT

MMR-FAULT REVIEW SHOWS

- COAX CABLE MMR 1 40RT1

- COAX CABLE MMR 2 40RT2

FAULT IS CAUSED DUE TO NO GPS SIGNAL

IN CERTAIN AREAS LIKE GREEK ISLANDS

(50)

RESET BY CYCLING:

MMR1…….G12

MMR2…….K09

G

MCDU –

AFS

TEST

THIS WILL TEST THE FOLLOWING UNITS:

FAC 1 AND 2

FMGC 1 AND 2

ATA34

-System

Procedure

Self Test

Length

G

WX-

RADAR

TEST

WEATHER RADAR TEST IS INITIATED

TROUGH THE CFDIU USING MCDU.

WX TEST: CFDS – SYST REPORT/TEST –

NAV – NEXT PAGE – RADAR1/2 – TEST :

ONCAPT AND F/O NDs

TILT INDICATION APPEARS ON THE RIGHT

TILL END OF TEST

TEST PATTERN SHOWN FROM ONE SIDE

TO THE OTHER

WR TEST INDICATION ON RH SIDE WITH

SCAN FROM 0° TO 135°

WR TEST INDICATION DISAPPEARS. WR

ATT WARNING INDICATION WITH SCAN

FROM 135° TO 180° SHOWN

TEST SETTING:

ADIRUS – FCU IN ARC MODE, WXR OFF,

MODE SWITCH-WX MODE. TILT SWITCH 0,

GAIN SWITCH IN AUTO MODE, NAV WXR

TEST

VOR

STATION

NOT

ADJUSTAB

LE

FMGC RESET

(51)

ATA35

System

Procedure

_{Self Test}

Length

G

CREW

OXY

REGUL.

LOW

PRESSU

RE IND.

CHECK THAT THE CREW OXY p/b is in ON

position

(52)

ATA36

-System

Procedure

Self Test

Length

G

BRAKES SET

BMC – Bleed

Monitoring

Computer

Procedure applicable for example in case

of false alarm L(R)WING LEAK!

ENG1(2)BLEED….OFF and ON

Pull and reset 2 relevant CBs:

22 sec

LH

Air Bleed Eng 1

D11 and D12

RH

Air Bleed Eng 2

Z22 and Z23

F

CROSS BLEED

Valve msg

reset the cbs:

AirBleed Xfeed bat…...D13

AirBleed Xfeed norm... Z20

F

Cross Bleed

reset the cbs:

faults use in

AirBleed Eng1 Mong….D11

addition to

AirBleed Eng1 CTL……..D12

Xfeed valve

AirBleed Eng2 Mong….Z22

Faults(msg)

AirBleed Eng2 CTL……..Z23

SDAC1 Sply………F4/49vu

SDAC2 Sply…………Q6/121vu

G

PNEUMATIC

PRESSURE

FROM APU IS

NOT

ENOUGH TO

ENGINE...

Most likely the APU IGV actuator is

defective.

IGV actuator check: call MCDU / AIDS /

CALL UP /

PARAMETERS / MENU / APUpage.

WB and PT are the

SENSOR PACK OUTLET,

if this sensor is spread ---, then this

sensor is defective.

- IGV 0.82 = CLOSED.

-IGV N 05= OPEN. APU under stress =

APU BLEED "on" , PACKS "on"

- If the value alter under stress,

then the IGV actuator is defective.

G

ENG 1 / 2

BLEED NOT

CLOSED

WARNING

AIR ENG 1 / 2 BLEED NOT CLOSED

WARNING AFTER APU START.

CYCLE ENG RELATED BMC CBs:

BMC 1 : MONG

………D-11

(53)

CTL………

……D12

BMC 2:

MONG………

…..Z22

CTL………

…….Z23

IF NO SUCCESS

DO IDLE RUN AND CHECK FUNCTION OF

BLEED VALVE WITH APU BLEED OFF

ATA38

-System

Procedure

Length

Self Test

F

Toilet Vacuum sys

Pull for at least 30s Location depends from

configuration

Panel 2000VU VACUUM LAV SYS/LAV PWR Panel 2001VU

VACUUM LAVATORY SYSTEM/LAV PWR VACUUM LAVATORY SYSTEM/VACUUM SYS VACUUM LAVATORY SYSTEM/VACUUM GEN

F

NOTE:

If the light SYSTEM INOP is on FAP and the reset doesn't help the toilet can be used above 16000ft provided:

3 Reset Tips

Full text

RESET & TIPS

PROCEDURES

GENERAL CONFIGURATION

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’

FAP LAYOUT SELECTION= CODE “318” ENTER

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:

TSM

24-00-00-810-818

ATA21

-System

Procedure

Length

Self

Test

G

F

F

-

Generator 1 Line

-

Generator 2 Line

G

G

G

Cycle c/b:

Aircond. Avionics vent ctrl

………..D5

Aircond. Avionics vent ctrl

………..D6

Aircond. Avionics vent Mong …………

Y17

Perform TEMP Control Test

F

F

F

F

ATA21

-System

Procedure

Length

Self

Test

G

G

G

G

G

Note

: Resetting zone controllers with engines

running will generate the warnings ENG1(2)

_{Self Test}

_{In flight:}