A330 Computer Reset

PROCEDURES SUPPLEMENTARY PROCEDURES A330/A340

ELECTRICAL

FLIGHT CREW OPERATING MANUAL

COMPUTER RESET TABLE Applicable to: MSN 0275-0366, 0946

ATA

EQUIPMENT

MANUAL RESET OVHD System RESET Panel Control Panel

REMARKS

Ident.: PRO-SUP-24-B-00012109.0001001 / 16 NOV 11

21

PACK CONT ZONE CONT VENT CONT AEVC CPC

2 1 2 1 2

NIL

To force a CPC changeover: ‐ MODE SEL pb (MAN) AFTER 3 s: ‐ MODE SEL (AUTO) The inactive CPC may then be reset (check the CAB PRESS SD page). During the reset phase, the following cabin effects may occur: ‐ cabin lights may come on at full intensity ‐ cabin chimes may sound. Continued on the following page

HVN A330/A340 FLEET FCOM

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Continued from the previous page REMARKS


Ident.: PRO-SUP-24-B-00012110.0001001 / 30 MAR 12

FCU

2

‐ In flight: • When PART FCU is displayed as INOP SYS, do not reset the FCU • When FCU is displayed as INOP SYS, check FCU targets after the reset ‐ On ground: • The flight crew can reset the FCU when either FCU or PART FCU is displayed as INOP SYS • The FCU has to be reconfigured after the reset Note:

22

FMGEC and FM

MCDU


4

Following a total FCU reset either in flight or on ground, FCU targets are FCU entries (selected modes).

• FMGEC or FM resets results in onside AP disconnection (if engaged) • Resynchronization of both FMs will occur after a reset sequence, with associated messages on the MCDU and ND: ‐ PLEASE WAIT ‐ MAP NOT AVAIL • It is recommended to use FMGEC R/B, rather than FM R/B. BRT OFF CTL In case the MCDU is blank or locked, Refer to PRO-SUP-22-10-Other Abnormal procedures-MCDU Locked or Blank. Continued on the following page

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CIDS

2

ACP/AMU RMP

2

23


In the event of active CIDS reset (usually CIDS 1 when both are operative), a complete power-up test is performed. ‐ In flight, test lasts about 20 s: • The cabin light comes on at full intensity. If selected, dimming is lost and must be reselected after the test. • PA, CALL and INTERPHONE functions are interrupted and have to be reselected after the test. • FAP cabin temperature corrections are lost, and have to be reselected after the test. ‐ On ground, test lasts about 80 s, and includes additionally: • A sequencial cabin loudspeakers test (triggers a tone for about 10 s). • The cabin light might flash shortly. Dimming selection is lost (as in flight). NIL ON/OFF CTL In case of freezing of one RMP (impossibility to interchange the ACTIVE and STBY radio navigation or communication frequencies,...), all the RMP’s have to be reset, one after the other, to recover a normal operation. In order to be reset, RMP’s must be switched off at least 5 s by using the ON/OFF selector on the RMP control panels. Continued on the following page

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Ident.: PRO-SUP-24-B-00012112.0001001 / 24 APR 13

GPCU

2 pb on ELEC panel

24

BCL 24 Ident.: PRO-SUP-24-B-00012113.0001001 / 18 MAR 11

Commercial equipments and galleys

25

GPCU reset may be attempted, if AVAIL and ON lights do not light up. 1. Press once the affected EXT A(B) pb to reset the functions of GPCU. 2. Check the GPU is connected to the aircraft, then started. 3. Check AVAIL light is ON and press the EXT A(B) pb to connect the GPU.

If unsuccessful, check GPU voltage and frequency (bite is available on batteries only). 3 BAT pb-sw Use BAT pb-sw to reset the BCL. on ELEC panel Do not reset the BCL when the BAT FAULT caution has been triggered, and the BAT OFF selection has been requested by the ECAM. 2 pb on ELEC panel

On ground When the commercial equipment and/or galley loads have been shed by the ECMU, they can be recovered when more electrical power is available. ‐ If COMMERCIAL OFF is displayed on the ECAM ELEC page: Switch the COMMERCIAL pb OFF then ON. ‐ If GALLEY SHED or GALLEY PARTIALLY SHED is displayed on the ECAM ELEC page: Switch the GALLEY pbOFF then ON. Do not reset more than one pushbutton at a time. Continued on the following page


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SDCU

2

Only a simultaneous reset of SDCU 1 and SDCU 2 is authorized. On ground ‐ Simultaneously pull both SDCU 1 reset pb and SDCU 2 reset pb ‐ Wait 2 min ‐ Simultaneously push both SDCU 1 reset pb and SDCU 2 reset pb ‐ Wait 3 min for the system restart to be completed.

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In flight ‐ Simultaneously pull both SDCU 1 reset pb and SDCU 2 reset pb ‐ Wait 3 s ‐ Simultaneously push both SDCU 1reset pb and SDCU 2 reset pb ‐ Wait 15 s for the system restart to be completed. Ident.: PRO-SUP-24-B-00012491.0002001 / 27 JAN 12

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PRIM and SEC

FLT/CTL panel

‐ PRIM/SEC may be reset, except in the following case: • The DC BUS 2 FAULT caution is present. Note:

Do not attempt a reset because this would result in a loss of related PRIM/SEC

‐ If a reset is performed on ground, it must be followed by a flight controls’ check (Refer to PRO-NOR-SOP-10-TAXI). WARNING Note:

FCDC


2

NIL

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Do not reset more than one computer at a time.

When a PRIM reset is performed on ground, the crew must check the pitch trim position. Continued on the following page

PRO-SUP-24 P 7/42 05 MAR 14


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Ident.: PRO-SUP-24-B-00012492.0003001 / 22 OCT 13

FCMC

28

2

‐ If the reset is done before engine start, the ZFW and ZFWCG must be re-entered on the MCDU INIT B page, ‐ If the reset is done after engine start, the actual GW and CG displayed on the MCDU FUEL PRED page are computed by the FE. However, the GW computed by the FE may be less accurate, therefore, when time permits: • If the reset is successful, the actual GW and CG must be re-entered on the MCDU FUEL PRED page, • If the reset is unsuccessful, the flight crew must determine the FOB from the engine start fuel quantity minus the FU quantity indication. In the case of triggering of FUEL ZFW ZFCG DISAGREE, if the ZFW, ZFWCG, ECAM GW are the same as the loadsheet values, but the difference between the ECAM CG and the loadsheet CG is more than 2 %: On ground: ‐ Reinsert the ZFW and ZFCG values. If the ECAM caution is still displayed after reinsertion: • Simultaneously pull FCMC 1 and FCMC 2 reset buttons • Simultaneously push FCMC 1 and FCMC 2 reset buttons. If unsuccessful, on ground: ‐ Simultaneously pull FCMC 1, FCMC 2, FMGEC 1 and FMGEC 2 reset buttons ‐ Simultaneously push FCMC 1, FCMC 2, FMGEC 1 and FMGEC 2 reset buttons. Refer to PRO-SUP-24 Computer Reset Table 22-Auto Flight for additional information regarding the FMGEC resets. Continued on the following page


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PHC WHC

3 2

Associated heating is interrupted, when the reset pb is pulled.


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DU (ECAM, PFD, ND) DMC

3

FWC SDAC

2 2

OFF/BRT CTL If DU reset is unsuccessful, DMC (driving the affected DU) reset may be attempted. EFIS/ECAM displays are lost for 40 s on ground after reset or power-up. NIL NIL

Ident.: PRO-SUP-24-B-00012495.0001001 / 11 APR 13 Impacted by TDU: 00015236 Computer Reset Table - 32-Landing Gear

In flight: Not authorized.

Braking malfunction

BSCU

32

On ground and only for the following cases: In case of WHEEL N/W STRG FAULT or BRAKES RESIDUAL BRAKING: ‐ STOP aircraft, ‐ Set PARK BRK handle to ON, ‐ Set A/SKID & N/W STRG sw to OFF, ‐ Set A/SKID & N/W STRG sw to ON. In the case of a WHEEL N/W STRG FAULT, the flight crew may attempt only one BSCU reset. If the BSCU reset is successful, the flight crew must return to the gate for troubleshooting. The taxi speed must not exceed 10 kt. Note:

LGCIU

2

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

An LGCIU reset must neither be made during landing gear maneuvers, nor just prior to touchdown.

1 Ident.: TDU / PRO-SUP-24-B-00015236.0001001 / 25 FEB 14

Impacted DU: 00012495 Computer Reset Table - 32-Landing Gear

Continued on the following page


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PRO-SUP-24 P 9/42 05 MAR 14


ELECTRICAL


ATA

EQUIPMENT Braking malfunction



In flight: Not authorized. On ground and only for the following cases: In case of BRAKES RESIDUAL BRAKING: ‐ STOP aircraft, ‐ Set PARK BRK handle to ON, ‐ Set A/SKID & N/W STRG sw to OFF, ‐ Set A/SKID & N/W STRG sw to ON. In case of WHEEL N/W STRG FAULT:

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BSCU

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


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After any BSCU reset: 1. Check brake efficiency, 2. Check absence of aircraft veering, Continued on the following page

PRO-SUP-24 P 10/42 05 MAR 14


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LGCIU


2

3. Record the BSCU reset in the logbook.

An LGCIU reset must neither be made during landing gear maneuvers, nor just prior to touchdown. Continued on the following page

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Ident.: PRO-SUP-24-B-00014541.0001001 / 27 MAY 13

ENG BLEED

AIR panel

ENG BLEED reset is only authorized in the two following cases: ‐ CASE A: AIR ENG 1(2) BLEED FAULT alert ‐ CASE B: AIR ENG 1(2) BLEED NOT CLSD alert Note:

Do not attempt more than one reset.

CASE A: AIR ENG 1(2) BLEED FAULT alert: On ground or in flight • If the PACK (non-affected side) is operative, and If the Wing Anti-Ice is OFF: ‐ ENG BLEED (affected side)................................OFF ▪ If the ENG BLEED (affected side) pb-sw FAULT light is on: ‐ Delay application of the reset until FAULT light extinguishes. ▪ If the ENG BLEED (affected side) pb-sw FAULT light is off: ‐ X BLEED................................................AUTO Disregard the AIR ABNORM BLEED CONFIG alert. ‐ PACK (affected side)..................................ON ‐ ENG BLEED (affected side).......................ON ‐ Check that the affected Engine Bleed Valve is open on the BLEED SD page. • If AIR ENG (AFFECTED) BLEED FAULT alert reoccurs, or If Engine Bleed Valve (affected side) not open on the BLEED SD page: - ENG BLEED (affected side)..............OFF - X BLEED........................................OPEN

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Note:

Record the ENG BLEED reset in the logbook (successful or unsuccessful).

CASE B: AIR ENG 1(2) BLEED NOT CLSD alert: On ground only ‐ ENG BLEED (affected side)...............................OFF Continued on the following page


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▪ If the ENG BLEED (affected side) pb-sw FAULT light is on: ‐ Delay application of the reset until FAULT light extinguishes. ▪ If the ENG BLEED (affected side) pb-sw FAULT light is off: ‐ ENG BLEED (affected side)........................ON Note:

Record the ENG BLEED reset in the logbook (successful or unsuccessful). Continued on the following page


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VSC

38

Cabin aft C/B panel (VACUUM TOILET SYSTEM)

On ground or in flight In case all toilets on one or both sides of the aircraft are shut down (on the cabin aft C/B panel): ‐ VACUUM TOILET SYSTEM (blue pb) RESET The repeated use of the blue reset pb is not recommended. If the reset does not fix the problem, apply the following procedure to both system sides, on the cabin aft C/B panel (VACUUM TOILET SYSTEM). Do not apply the following procedure in case of a waste tank overfills. On the cabin aft C/B panel: ‐ C/B SYSTEM (both) and VACUUM GEN (both) (4 C/Bs) PULL ‐ C/B LAVATORY POWER (LH and RH) (8 C/Bs) PULL ‐ C/B LAVATORY POWER (LH and RH) (8 C/Bs ) PUSH LH and RH SYSTEM and both VACUUM GEN C/Bs remain pulled. LH and RH SYSTEM and both VACUUM GEN C/Bs remain pulled. In this configuration: • The waste quantity indication is lost, • The protection against waste tank overfill is lost, • When the aircraft is below 16 000 ft do not use the toilets. • On ground, during servicing, do not use toilets. Continued on the following page


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ATSU

1

When the ATSU is reset, ADS-C connections are no longer active. The ATC center(s) assumes that the connection is still active because a disconnection message has not been sent to the ATC center(s). Therefore, the ATC center(s) will not attempt to re-establish ADS-C contracts with the aircraft, even after re-notification.

46

ATSU reset, with the ATSU 1 reset sw on 261 VU (overhead panel), should only be attempted, if: ‐ ″INVALID DATA″ is displayed on the DCDU. ‐ Key selection has no effect on the DCDU or any of the MCDU ATSU DATALINK submenus. Ident.: PRO-SUP-24-B-00012498.0001001 / 18 MAR 11

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ECB


52

PSCU

2

EIVMU

2

APU Reset must only be attempted when APU speed is below MASTER sw 7 % NIL


During the reset, and the subsequent 5 s, the following occurs: ‐ On the corresponding engine: • Loss of thrust reverser • Loss of vibration indication • If idle is selected, only high idle is available • Loss of man start and wet crank • Loss of bleed corrections on thrust limit. ‐ On both engines: • Loss of autothrust • Loss of Flex/Derated T.O.

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ELECTRICAL


COMPUTER RESET TABLE Applicable to: MSN 0943, 0962-1019

ATA

EQUIPMENT


REMARKS


21


2 1 2 1 2

NIL



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FCU

2


22

FMGEC and FM

MCDU


4



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CIDS

2

ACP/AMU RMP

2

23



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GPCU

2 pb on ELEC panel

24



25





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SDCU

2

Only a simultaneous reset of SDCU 1 and SDCU 2 is authorized. On ground ‐ Simultaneously pull both SDCU 1 reset pb and SDCU 2 reset pb ‐ Wait 2 min ‐ Simultaneously push both SDCU 1 reset pb and SDCU 2 reset pb ‐ Wait 3 min for the system restart to be completed.

26

In flight ‐ Simultaneously pull both SDCU 1 reset pb and SDCU 2 reset pb ‐ Wait 3 s ‐ Simultaneously push both SDCU 1reset pb and SDCU 2 reset pb ‐ Wait 15 s for the system restart to be completed. Ident.: PRO-SUP-24-B-00012491.0002001 / 27 JAN 12

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PRIM and SEC

FLT/CTL panel




FCDC


2

NIL

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FCMC

28

2

‐ If the reset is done before engine start, the ZFW and ZFWCG must be re-entered on the MCDU INIT B page, ‐ If the reset is done after engine start, the actual GW and CG displayed on the MCDU FUEL PRED page are computed by the FE. However, the GW computed by the FE may be less accurate, therefore, when time permits: • If the reset is successful, the ZFW and ZFWCG from the loadsheet must be re-entered on the MCDU FUEL PRED page, • If the reset is unsuccessful, the flight crew must determine the FOB from the engine start fuel quantity minus the FU quantity indication. In the case of triggering of FUEL ZFW ZFCG DISAGREE, if the ZFW, ZFWCG, ECAM GW are the same as the loadsheet values, but the difference between the ECAM CG and the loadsheet CG is more than 2 %: On ground: ‐ Reinsert the ZFW and ZFCG values. If the ECAM caution is still displayed after reinsertion: • Simultaneously pull FCMC 1 and FCMC 2 reset buttons • Simultaneously push FCMC 1 and FCMC 2 reset buttons. If unsuccessful, on ground: ‐ Simultaneously pull FCMC 1, FCMC 2, FMGEC 1 and FMGEC 2 reset buttons ‐ Simultaneously push FCMC 1, FCMC 2, FMGEC 1 and FMGEC 2 reset buttons. Refer to PRO-SUP-24 Computer Reset Table 22-Auto Flight for additional information regarding the FMGEC resets. Continued on the following page


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30

PHC WHC

3 2



31


3

FWC SDAC

2 2




Braking malfunction

BSCU

32


LGCIU

2







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BSCU



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LGCIU


2



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ENG BLEED

AIR panel




36

Note:




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ATSU

1

When the ATSU is reset, ADS-C connections are no longer active. The ATC center(s) assumes that the connection is still active because a disconnection message has not been sent to the ATC center(s). Therefore, the ATC center(s) will not attempt to re-establish ADS-C contracts with the aircraft, even after re-notification.

46

ATSU reset, with the ATSU 1 reset sw on 261 VU (overhead panel), should only be attempted, if: ‐ ″INVALID DATA″ is displayed on the DCDU. ‐ Key selection has no effect on the DCDU or any of the MCDU ATSU DATALINK submenus. Ident.: PRO-SUP-24-B-00012498.0001001 / 18 MAR 11

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ECB


52

PSCU

2

EIVMU

2




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ELECTRICAL


COMPUTER RESET TABLE Applicable to: MSN 1256-1266

ATA

EQUIPMENT


REMARKS


21


2 1 2 1 2

NIL



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ELECTRICAL


ATA

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FCU

2


22

FMGEC and FM

MCDU


4



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ATA

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CIDS

2

ACP/AMU RMP

2

23



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ATA

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GPCU

2 pb on ELEC panel

24



25





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Smoke detection function of the CIDS-SDF

2

On ground ‐ Pull both SDF1 (261VU) and SDF2 (262VU) reset buttons ‐ Wait 10 s ‐ Push both SDF1 and SDF2 reset buttons. ‐ Wait 3 min for the system restart to be completed.

26

In flight ‐ Pull both SDF1 (261VU) and SDF2 (262VU) reset buttons ‐ Wait 3 s ‐ Push both SDF1 and SDF2 reset buttons. ‐ Wait 1 min for the system restart to be completed.

Ident.: PRO-SUP-24-B-00012491.0002001 / 27 JAN 12

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PRIM and SEC

FLT/CTL panel




FCDC


2

NIL

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FCMC

28

2

‐ If the reset is done before engine start, the ZFW and ZFWCG must be re-entered on the MCDU INIT B page, ‐ If the reset is done after engine start, the actual GW and CG displayed on the MCDU FUEL PRED page are computed by the FE. However, the GW computed by the FE may be less accurate, therefore, when time permits: • If the reset is successful, the ZFW and ZFWCG from the loadsheet must be re-entered on the MCDU FUEL PRED page, • If the reset is unsuccessful, the flight crew must determine the FOB from the engine start fuel quantity minus the FU quantity indication. In the case of triggering of FUEL ZFW ZFCG DISAGREE, if the ZFW, ZFWCG, ECAM GW are the same as the loadsheet values, but the difference between the ECAM CG and the loadsheet CG is more than 2 %: On ground: ‐ Reinsert the ZFW and ZFCG values. If the ECAM caution is still displayed after reinsertion: • Simultaneously pull FCMC 1 and FCMC 2 reset buttons • Simultaneously push FCMC 1 and FCMC 2 reset buttons. If unsuccessful, on ground: ‐ Simultaneously pull FCMC 1, FCMC 2, FMGEC 1 and FMGEC 2 reset buttons ‐ Simultaneously push FCMC 1, FCMC 2, FMGEC 1 and FMGEC 2 reset buttons. Refer to PRO-SUP-24 Computer Reset Table 22-Auto Flight for additional information regarding the FMGEC resets. Continued on the following page


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30

PHC WHC

3 2



31


3

FWC SDAC

2 2




Braking malfunction

BSCU

32


LGCIU

2







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BSCU



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LGCIU


2



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ENG BLEED

AIR panel




36

Note:




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ATSU

1

When the ATSU is reset, ADS-C connections are no longer active. The ATC center(s) assumes that the connection is still active because a disconnection message has not been sent to the ATC center(s). Therefore, the ATC center(s) will not attempt to re-establish ADS-C contracts with the aircraft, even after re-notification. ATSU reset, with the ATSU 1 reset sw on 261 VU (overhead panel), should only be attempted, if: ‐ ″INVALID DATA″ is displayed on the DCDU. ‐ Key selection has no effect on the DCDU or any of the MCDU ATSU DATALINK submenus.

46

AINS

1

Use the AINS reset sw on the 262 VU (overhead panel) to reset the AINS. Note: An AINS reset may take up to 20 min.


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ECB


52

PSCU

2

EIVMU

2




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ELECTRICAL

Intentionally left blank


PRO-SUP-24 P 42/42 05 MAR 14

A330 Computer Reset

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