@A310

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 74

TITLE: IGNITION - IGNITION STARTING AND CONTINUOUS RELIGHT -

INTRODUCE AUTO- RELIGHT FUNCTION FOR CF6-80C2 ENGINES

MODIFICATION No.: 13525S22817

This page transmits Revision No.06 of Service Bulletin No.A310-74-2003

ADDITIONAL WORK

**CONF ALL

For aircraft modified by revision 00, 01, 02, apply additional work as described in TASK

742003-831-802 001 Modification - ADDITIONAL WORK and TASK 742003-831-803 001 Modification -

ADDITIONAL WORK .

For aircraft modified by revision 03 only apply additional work as described in TASK 742003-831-803

001 Modification - ADDITIONAL WORK .

NOTE: Kit 742003A02R00, concerns aircraft affected by TASK 742003-831-802 001

Modification - ADDITIONAL WORK .

NOTE: Kit 742003A03R00, concerns aircraft affected by TASK 742003-831-803 001

Modification - ADDITIONAL WORK .

No additional work is required by this revision for aircraft modified by revision No. 04 and revision No. 5

of this Service Bulletin.

REASON

Revision No. 6 issued to:

- Add notes to clarify which kit should be used for each subtask.

- Update the Material - Price and Availability paragraph 2.A (2).

- Update Test paragraph.

- Update the effectivity:

. Config. 005 deleted.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 1

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

CHANGES

FRONT MATTER

IGNITION - IGNITION STARTING AND

CONTINUOUS RELIGHT - INTRODUCE

AUTO- RELIGHT FUNCTION FOR

CF6-80C2 ENGINES

CONFIGURATION UPDATED R

SUMMARY

MATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE

UPDATED

R

MATERIAL PRICE INFORMATION TABLE

UPDATED

R

MATERIAL PRICE INFORMATION TABLE

UPDATED

R

MATERIAL PRICE INFORMATION TABLE

DELETED FOR APPLICABLE MSN

D

MATERIAL PRICE INFORMATION TABLE

UPDATED

R

MATERIAL PRICE INFORMATION TABLE

UPDATED

R

MATERIAL PRICE INFORMATION TABLE

UPDATED

R

MATERIAL PRICE INFORMATION TABLE

UPDATED

R

EFFECTIVITY OPERATOR LIST UPDATED R

MANPOWER MANPOWER DELETED FOR APPLICABLE MSN D

PLANNING INFORMATION

EFFECTIVITY EFFECTIVITY RELATED INFORMATION

UPDATED

R

Configuration definition CONFIGURATION LIST UPDATED R

CONF 001 CONFIGURATION DEFINITION UPDATED R

CONF 002 CONFIGURATION DEFINITION UPDATED R

Configuration definition CONFIGURATION DELETED D

DESCRIPTION DESCRIPTION UPDATED R

MANPOWER MANPOWER DELETED FOR APPLICABLE MSN D

REFERENCES REFERENCED DOCUMENTATION UPDATED R

REFERENCED DOCUMENTATION UPDATED R

REFERENCED DOCUMENTATION UPDATED R

REFERENCED DOCUMENTATION DELETED FOR

APPLICABLE MSN

D

REFERENCED DOCUMENTATION UPDATED R

REFERENCED DOCUMENTATION UPDATED R

REFERENCED DOCUMENTATION UPDATED R

REFERENCED DOCUMENTATION UPDATED R

MATERIAL INFORMATION

MATERIAL - PRICE AND AVAILABILITY

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 2

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Price and Availability PRICE AND AVAILABILITY UPDATED

MATERIAL PRICE UPDATED

MATERIAL AVAILABILITY UPDATED

R

ACCOMPLISHMENT INSTRUCTIONS

TASK 742003- 831-801-001-Modification TASK SOLUTION UPDATED

NOTE UPDATED

CAUTION UPDATED

R

Task associated data - 005 TASK ASSOCIATED DATA DELETED FOR

APPLICABLE MSN

D

Subtask 742003-839-001-001 SUBTASK SOLUTION UPDATED

MANPOWER RESSOURCE UPDATED

R

Subtask 742003-839-001-001 SUBTASK SOLUTION UPDATED

MANPOWER RESSOURCE UPDATED

R

Subtask 742003-839-001-001 SUBTASK SOLUTION UPDATED

MANPOWER RESSOURCE UPDATED

R

GENERAL TOPIC CONTENT DELETED FOR APPLICABLE

MSN

D

Subtask 742003-839-001-001 SUBTASK SOLUTION UPDATED

MANPOWER RESSOURCE UPDATED

R

Subtask 742003-839-001-001 SUBTASK SOLUTION UPDATED

MANPOWER RESSOURCE UPDATED

R

Subtask 742003-839-001-001 SUBTASK SOLUTION UPDATED

MANPOWER RESSOURCE UPDATED

R

Subtask 742003-839-001-001 SUBTASK SOLUTION UPDATED

MANPOWER RESSOURCE UPDATED

R

Subtask 742003-941-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Subtask 742003-941-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Subtask 742003-941-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

PREPARATION TOPIC CONTENT DELETED FOR APPLICABLE

MSN

D

Subtask 742003-941-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Subtask 742003-941-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Subtask 742003-941-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Subtask 742003-941-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 3

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Subtask 742003-831-007-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 742003-831-004-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 742003-831-005-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 742003-831-006-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 742003-831-007-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 742003-831-004-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 742003-831-005-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 742003-831-006-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 742003-831-007-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 742003-831-004-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 742003-831-005-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 742003-831-006-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

R

PROCEDURE TOPIC CONTENT DELETED FOR APPLICABLE

MSN

D

Subtask 742003-831-007-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 742003-831-004-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 742003-831-005-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 742003-831-006-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

R

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 4

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Subtask 742003-831-007-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 742003-831-004-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 742003-831-005-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 742003-831-006-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 742003-831-004-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 742003-831-005-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 742003-831-006-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 742003-720-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Subtask 742003-720-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Subtask 742003-720-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

TEST TOPIC CONTENT DELETED FOR APPLICABLE

MSN

D

Subtask 742003-720-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Subtask 742003-720-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Subtask 742003-720-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Subtask 742003-720-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

CLOSE-UP TOPIC CONTENT DELETED FOR APPLICABLE

MSN

D

TASK 742003- 831-802-001-Modification -

ADDITIONAL WORK

TASK SOLUTION UPDATED

NOTE UPDATED

CAUTION UPDATED

R

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 5

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Task associated data - 005 TASK ASSOCIATED DATA DELETED FOR

APPLICABLE MSN

D

GENERAL TOPIC CONTENT DELETED FOR APPLICABLE

MSN

D

PREPARATION TOPIC CONTENT DELETED FOR APPLICABLE

MSN

D

PROCEDURE TOPIC CONTENT DELETED FOR APPLICABLE

MSN

D

Subtask 742003-710-001-001 SUBTASK SOLUTION UPDATED

LOCATION UPDATED

ZONE UPDATED

R

Subtask 742003-710-001-001 SUBTASK SOLUTION UPDATED

LOCATION UPDATED

ZONE UPDATED

R

Subtask 742003-710-001-001 SUBTASK SOLUTION UPDATED

LOCATION UPDATED

ZONE UPDATED

R

TEST TOPIC CONTENT DELETED FOR APPLICABLE

MSN

D

Subtask 742003-710-001-001 SUBTASK SOLUTION UPDATED

LOCATION UPDATED

ZONE UPDATED

R

Subtask 742003-710-001-001 SUBTASK SOLUTION UPDATED

LOCATION UPDATED

ZONE UPDATED

R

Subtask 742003-710-001-001 SUBTASK SOLUTION UPDATED

LOCATION UPDATED

ZONE UPDATED

R

Subtask 742003-710-001-001 SUBTASK SOLUTION UPDATED

LOCATION UPDATED

ZONE UPDATED

R

CLOSE-UP TOPIC CONTENT DELETED FOR APPLICABLE

MSN

D

TASK 742003- 831-803-001-Modification -

ADDITIONAL WORK

TASK SOLUTION UPDATED

NOTE UPDATED

CAUTION UPDATED

R

Task associated data - 005 TASK ASSOCIATED DATA DELETED FOR

APPLICABLE MSN

D

GENERAL TOPIC CONTENT DELETED FOR APPLICABLE

MSN

D

Subtask 742003-941-003-001 SUBTASK SOLUTION UPDATED R

Subtask 742003-941-003-001 SUBTASK SOLUTION UPDATED R

Subtask 742003-941-003-001 SUBTASK SOLUTION UPDATED R

PREPARATION TOPIC CONTENT DELETED FOR APPLICABLE

MSN

D

Subtask 742003-941-003-001 SUBTASK SOLUTION UPDATED R

Subtask 742003-941-003-001 SUBTASK SOLUTION UPDATED R

Subtask 742003-941-003-001 SUBTASK SOLUTION UPDATED R

Subtask 742003-941-003-001 SUBTASK SOLUTION UPDATED R

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 6

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

PROCEDURE TOPIC CONTENT DELETED FOR APPLICABLE

MSN

D

Subtask 742003-720-002-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

R

Subtask 742003-720-002-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

R

Subtask 742003-720-002-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

R

TEST TOPIC CONTENT DELETED FOR APPLICABLE

MSN

D

Subtask 742003-720-002-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

R

Subtask 742003-720-002-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

R

Subtask 742003-720-002-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

R

Subtask 742003-720-002-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

R

CLOSE-UP TOPIC CONTENT DELETED FOR APPLICABLE

MSN

D

Fig. A-FBAAE FIGURE SOLUTION DELETED FOR APPLICABLE

MSN

D

Fig. A-FCBAA FIGURE SOLUTION UPDATED

CONFIGURATION UPDATED

R

Fig. A-FCDAA FIGURE SOLUTION UPDATED

CONFIGURATION UPDATED

R

Fig. A-FCEAA FIGURE SOLUTION UPDATED

CONFIGURATION UPDATED

R

Fig. A-FCFAA FIGURE SOLUTION UPDATED

CONFIGURATION UPDATED

R

Fig. A-FDBAA FIGURE SOLUTION UPDATED

CONFIGURATION UPDATED

R

Fig. A-FDDAA FIGURE SOLUTION UPDATED

CONFIGURATION UPDATED

R

Fig. A-FDEAA FIGURE SOLUTION UPDATED

CONFIGURATION UPDATED

R

Fig. A-FDFAA FIGURE SOLUTION UPDATED

CONFIGURATION UPDATED

R

FILLING INSTRUCTIONS

This Service Bulletin has been generated electronically and is reissued as a complete document.

Replace the complete document.

Put this Revision Transmittal Sheet in front of the Service Bulletin.

HISTORY OF PREVIOUS REVISIONS

Revision No.01 issued to modify the Part Numbers of the Relay-Sockets 15JHA and 16JHA, and to

modify the pin allocation on connector 365VC.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 7

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

The equivalent of this Service Bulletin has been validated on A300-600 aircraft MSN 0719.

Revision No.02 issued to:

modify contacts following airline comments

update the effectivity

add supplementary KIT 742003A01S01 and KIT 742003A01S05 for aircraft having received KIT

742003A01R02 or KIT 742003A01R03

Revision No.03 issued to add additional work as described in TASK 742003-831-802 001 Modification -

ADDITIONAL WORK

The equivalent of this Service Bulletin has been validated on A300-600 aircraft MSN 0719 and on

A300-600ST aircraft MSN 0001.

Creation of Kit 742003A02R00 to cover the additional work for aircraft which have applied a previous

revision of this Service Bulletin

Revision No.04 issued to add additional work as described in TASK 742003-831-803 001 Modification -

ADDITIONAL WORK

This additional work is linked to a wire inversion, as a consequence

**CONF 001 thru 003, 005 thru 007 Fig. A-FCBAA

**CONF 008 thru 009 Fig. A-FCBAB and

**CONF 001 thru 003, 005 thru 007 Fig. A-FDBAA

**CONF 008 thru 009 Fig. A-FDBAB

have been updated accordingly.

The equivalent of this Service Bulletin has been validated on A300-600 aircraft MSN 0719 and on

A300-600ST aircraft MSN 0001.

Creation of Kit 742003A03R00 to cover the additional work for aircraft which have applied a previous

revision of this Service Bulletin

Revision No.05 issued to update:

wiring diagram (Connector 1598VC and wire 175 to be deleted (Hook up chart to be updated

accordingly))

**CONF 007 Fig. A-FCFAB Sheet 02

to delete the sentence "unless otherwise specified all routes are X2M" in wiring diagram

**CONF 001 thru 003, 005 thru 006, 008 thru 009 Fig. A-FCDAA

**CONF 007 Fig. A-FCDAB

REVISION SEQUENCE

ORIGINAL: Jul 02/10

REVISION No. : 01 - Apr 01/11

REVISION No. : 02 - Feb 09/12

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 8

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

REVISION No. : 03 - May 10/12

REVISION No. : 04 - Jan 09/13

REVISION No. : 05 - May 23/13

REVISION No. : 06 - Jan 27/14

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 9

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

This Page Intentionally Left Blank

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 10

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

SUMMARY

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

This summary is for information only and is not approved for modification of the aircraft.

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 74

TITLE: IGNITION - IGNITION STARTING AND CONTINUOUS RELIGHT -

INTRODUCE AUTO- RELIGHT FUNCTION FOR CF6-80C2 ENGINES

**CONF ALL

MODIFICATIONS

MODIFICATION CLASSIFICATION

MAJOR None

MINOR 13525S22817

NOTE: As per EASA IR 21, a minor change is one that has no appreciable effect on the

mass, balance, structural strength, reliability, operational characteristics affecting the

airworthiness of the product. All other changes are major changes.

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

Flameout events due to inclement weather have occurred on Airbus and other aircraft equipped with

CF6-80C2 engines.

To avoid long engine restart sequence after a non-selection of continuous relight by the crew and a

flame out event, the modification consists in improving the function "Continuous Relight". This

modification installs a shunt of the rotary selector to supply energy to the igniters, when an engine

power loss is detected, even if the continuous ignition was not selected by the crew.

For an aircraft in flight, if N2 indicator data is lower than 45 per cent on an engine, both ignition

systems (A and B) will be energized in continuous for the concerned engine then maintained for 120

seconds after engine relight. Accomplishment of this Service Bulletin will "cover" a non-selection of

continuous relight by the crew, in order to ensure quick engine restart in case of flameout/rollback,

especially at low altitude. This 120 seconds period is a minimum duration for the continuous ignition,

which ensures that the igniters are supplied long enough to fulfil the purpose of this modification.

Accomplishment of this Service Bulletin will ensure better protection to engines by avoiding severe

damage due to a long engine restart sequence. This modification was designed, not to interfere with the

engine ground start logic, through the ground/flight distinction. There is no impact on the ground start

operational procedure.

The operational maintenance consequences of this Service Bulletin are the modification of the Flight

Crew Operating Manual (FCOM) Vol. 1 and 2.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 1

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

SUMMARY

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO

POTENTIAL AD YES A/C OPERATION AFFECTED YES

RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO

COST SAVING NO ETOPS AFFECTED NO

STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO

NOTE (1): Service Bulletin must be accomplished.

MATERIAL PRICE INFORMATION

**CONF 001

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 742003A01R07 1 14,920.00 Bundle, Placard Set, Plates

Kit 742003A02R00 1 260.00 Bundle

Kit 742003A03R00 1 194.00 Bundle

Supplementary kit

742003A01S01

1 1,740.00 Socket

Supplementary kit

742003A01S05

1 2,130.00 Placard

Supplementary kit

742003A01S06

1 2,600.00 Bundle

TOTAL 21,844.00

**CONF 002

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 742003A01R07 1 14,920.00 Bundle, Placard Set, Plates

Kit 742003A02R00 1 260.00 Bundle

Kit 742003A03R00 1 194.00 Bundle

Supplementary kit

742003A01S01

1 1,740.00 Socket

Supplementary kit

742003A01S05

1 2,130.00 Placard

Supplementary kit

742003A01S06

1 2,600.00 Bundle

TOTAL 21,844.00

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 2

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

SUMMARY

**CONF 003

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 742003A01R07 1 14,920.00 Bundle, Placard Set, Plates

Kit 742003A02R00 1 260.00 Bundle

Kit 742003A03R00 1 194.00 Bundle

Supplementary kit

742003A01S01

1 1,740.00 Socket

Supplementary kit

742003A01S05

1 2,130.00 Placard

Supplementary kit

742003A01S06

1 2,600.00 Bundle

TOTAL 21,844.00

**CONF 006

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 742003A01R07 1 14,920.00 Bundle, Placard Set, Plates

Kit 742003A02R00 1 260.00 Bundle

Kit 742003A03R00 1 194.00 Bundle

Supplementary kit

742003A01S01

1 1,740.00 Socket

Supplementary kit

742003A01S05

1 2,130.00 Placard

Supplementary kit

742003A01S06

1 2,600.00 Bundle

TOTAL 21,844.00

**CONF 007

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 742003A01R07 1 14,920.00 Bundle, Placard Set, Plates

Kit 742003A02R00 1 260.00 Bundle

Kit 742003A03R00 1 194.00 Bundle

Supplementary kit

742003A01S01

1 1,740.00 Socket

Supplementary kit

742003A01S05

1 2,130.00 Placard

Supplementary kit

742003A01S06

1 2,600.00 Bundle

TOTAL 21,844.00

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 3

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

SUMMARY

**CONF 008

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 742003A01R07 1 14,920.00 Bundle, Placard Set, Plates

Kit 742003A02R00 1 260.00 Bundle

Kit 742003A03R00 1 194.00 Bundle

Supplementary kit

742003A01S01

1 1,740.00 Socket

Supplementary kit

742003A01S05

1 2,130.00 Placard

Supplementary kit

742003A01S06

1 2,600.00 Bundle

TOTAL 21,844.00

**CONF 009

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 742003A01R07 1 14,920.00 Bundle, Placard Set, Plates

Kit 742003A02R00 1 260.00 Bundle

Kit 742003A03R00 1 194.00 Bundle

Supplementary kit

742003A01S01

1 1,740.00 Socket

Supplementary kit

742003A01S05

1 2,130.00 Placard

Supplementary kit

742003A01S06

1 2,600.00 Bundle

TOTAL 21,844.00

EFFECTIVITY

**CONF ALL

This Service Bulletin is applicable to this (these) operator(s) :

18T 40T 58X 82Z 85Z 98W AFG AIC C9L CFC DGA FDX GAF

HFY IRA IRM JAV K1P KAC KZU MGL PIA QAF RJA RZO SBI

SGX THY TSC WHT

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU None

OEB None

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 4

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

SUMMARY

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER None

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

MANPOWER

**CONF 001

Task 742003-831-801-001: Modification

TOTAL MANHOURS 79.50

ELAPSED TIME (HOURS) 58.00

Task 742003-831-802-001: Modification - ADDITIONAL WORK

TOTAL MANHOURS 5.50

ELAPSED TIME (HOURS) 5.50

Task 742003-831-803-001: Modification - ADDITIONAL WORK

TOTAL MANHOURS 10.00

ELAPSED TIME (HOURS) 10.00

**CONF 002

Task 742003-831-801-001: Modification

TOTAL MANHOURS 79.50

ELAPSED TIME (HOURS) 58.00

Task 742003-831-802-001: Modification - ADDITIONAL WORK

TOTAL MANHOURS 5.50

ELAPSED TIME (HOURS) 5.50

Task 742003-831-803-001: Modification - ADDITIONAL WORK

TOTAL MANHOURS 10.00

ELAPSED TIME (HOURS) 10.00

**CONF 003

Task 742003-831-801-001: Modification

TOTAL MANHOURS 79.50

ELAPSED TIME (HOURS) 58.00

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 5

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

SUMMARY

Task 742003-831-802-001: Modification - ADDITIONAL WORK

TOTAL MANHOURS 5.50

ELAPSED TIME (HOURS) 5.50

Task 742003-831-803-001: Modification - ADDITIONAL WORK

TOTAL MANHOURS 10.00

ELAPSED TIME (HOURS) 10.00

**CONF 006

Task 742003-831-801-001: Modification

TOTAL MANHOURS 79.50

ELAPSED TIME (HOURS) 58.00

Task 742003-831-802-001: Modification - ADDITIONAL WORK

TOTAL MANHOURS 5.50

ELAPSED TIME (HOURS) 5.50

Task 742003-831-803-001: Modification - ADDITIONAL WORK

TOTAL MANHOURS 10.00

ELAPSED TIME (HOURS) 10.00

**CONF 007

Task 742003-831-801-001: Modification

TOTAL MANHOURS 79.00

ELAPSED TIME (HOURS) 58.00

Task 742003-831-802-001: Modification - ADDITIONAL WORK

TOTAL MANHOURS 5.50

ELAPSED TIME (HOURS) 5.50

Task 742003-831-803-001: Modification - ADDITIONAL WORK

TOTAL MANHOURS 10.00

ELAPSED TIME (HOURS) 10.00

**CONF 008

Task 742003-831-801-001: Modification

TOTAL MANHOURS 79.50

ELAPSED TIME (HOURS) 58.00

Task 742003-831-802-001: Modification - ADDITIONAL WORK

TOTAL MANHOURS 5.50

ELAPSED TIME (HOURS) 5.50

Task 742003-831-803-001: Modification - ADDITIONAL WORK

TOTAL MANHOURS 10.00

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 6

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

SUMMARY

Task 742003-831-803-001: Modification - ADDITIONAL WORK

ELAPSED TIME (HOURS) 10.00

**CONF 009

Task 742003-831-801-001: Modification

TOTAL MANHOURS 79.50

ELAPSED TIME (HOURS) 58.00

Task 742003-831-802-001: Modification - ADDITIONAL WORK

TOTAL MANHOURS 5.50

ELAPSED TIME (HOURS) 5.50

Task 742003-831-803-001: Modification - ADDITIONAL WORK

TOTAL MANHOURS 10.00

ELAPSED TIME (HOURS) 10.00

APPENDICES

**CONF ALL

Appendix 1

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 7

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

SUMMARY

**CONF ALL

B_SB_742003_5_SAAA_01_00

20VU

429VU

105VU 104VU

133VU

80VU FR1

FR20

1M

1M

1M 2M

2M

2M

Figure A-FSAAA - Sheet 01

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 8

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

SUMMARY

**CONF ALL

B_SB_742003_5_SBAA_01_00

BEFORE

Figure A-FSBAA - Sheet 01

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 9

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

SUMMARY

**CONF ALL

AFTER

B_SB_742003_5_SCAA_01_01

Figure A-FSCAA - Sheet 01

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 10

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 74

TITLE: IGNITION - IGNITION STARTING AND CONTINUOUS RELIGHT -

INTRODUCE AUTO- RELIGHT FUNCTION FOR CF6-80C2 ENGINES

MODIFICATION No.: 13525S22817

This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the

property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with

any information contained in it. It is delivered on the express condition that said document and the

information contained in it shall be treated as confidential, shall not be used for any purpose other than

that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall

not be duplicated in any manner (except for the purposes of performing the tasks described hereunder

and provided that any recipient of such document shall comply with the conditions herein), without

AIRBUS prior written consent.

1. PLANNING INFORMATION

**CONF ALL

A. EFFECTIVITY

NOTE: The equivalent of this Service Bulletin has been validated on A300-600

aircraft MSN 0719 and on A300-600ST aircraft MSN 0001.

NOTE: This modification is applicable by Service Bulletin only.

(1) Models

310-304 310-308

(2) Effectivity by MSN

0407 0413 0418 0421-0422 0425 0431 0434 0436 0441 0444-0447 0472-0473 0478

0480-0484 0488 0490-0491 0494-0499 0502-0503 0519-0520 0522-0524 0526-0527

0537 0545 0547 0550-0552 0562 0564-0565 0567 0571 0585-0588 0590 0592-0593

0595 0597 0599-0600 0620 0622 0646-0649 0651-0653 0656 0658 0661 0663 0667

0671 0691

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 1

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(3) Effectivity by Operator

The Operator/MSN relationship is provided for information only and is correct at the time

of issue in accordance with the information available to AIRBUS. Any future changes

resulting from transfer of an aircraft from one operator to another will not be reflected in

this list unless the Service Bulletin is revised for another reason.

OPERATOR MSN

18T 0473

40T 0413

58X 0431

82Z 0550 0551

85Z 0527

98W 0495

AFG 0496 0497

AIC 0407

C9L 0652

CFC 0425 0441 0444 0446 0482

DGA 0418 0421 0422

FDX 0552 0593

GAF 0434 0484 0498 0503 0522 0523

HFY 0565

IRA 0436 0671

IRM 0488 0499 0524 0537 0547 0564 0567 0586 0595 0620

JAV 0481

K1P 0648

KAC 0647 0649 0663

KZU 0592 0622 0646

MGL 0526

PIA 0585 0587 0590 0653 0656 0691

QAF 0667

RJA 0445 0490 0491

RZO 0571 0651 0661

SBI 0520

SGX 0519 0562

THY 0478 0480 0502

TSC 0447 0472 0483 0545 0588 0597 0599 0600 0658

WHT 0494

(4) Configuration by MSN

MSN CONFIGURATION

0407 0413 0421 0422 0431 0434 0436 0445 001

0418 0425 0441 0444 0446 0447 0472 0478 0480 0481 0482

0483 0484 0488 0490 0491 0494 0495 0496 0497 0498 0499

0502 0503 0519 0520 0522 0523 0524 0526 0527 0537 0545

0547 0552 0562 0564 0565 0567 0571 0585 0586 0587 0588

0590 0595 0597 0599 0600 0620 0648 0651 0653 0656 0658

0661 0667 0671 0691

002

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 2

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

MSN CONFIGURATION

0473 0550 0551 008

0592 0622 0646 009

0593 006

0647 0649 0663 003

0652 007

(5) Configuration definition

**CONF 001

Config. 001 is valid for aircraft for a given position 01 of relays in 105VU, Relay 220GB

installed in 80VU, CB 6XC not installed in 133VU, Mod 10890S20687 (Service Bulletin

No. A310-34-2174) not embodied

**CONF 002

Config. 002 is valid for aircraft for a given position 02 of relays in 105VU, Relay 220GB

installed in 80VU, CB 6XC not installed in 133VU, Mod 10890S20687 (Service Bulletin

No. A310-34-2174) not embodied

**CONF 003

Config. 003 is valid for aircraft for a given position 03 of relays in 105VU, Relay 220GB

installed in 80VU, CB 6XC not installed in 133VU, Mod 10890S20687 (Service Bulletin

No. A310-34-2174) not embodied

**CONF 006

Config. 006 is valid for aircraft for a given position 06 of relays in 105VU, Relay 220GB

installed in 80VU, CB 6XC not installed in 133VU, Mod 10890S20687 (Service Bulletin

No. A310-34-2174) not embodied

**CONF 007

Config. 007 is valid for aircraft for a given position 02 of relays in 105VU, Relay 220GB

not installed in 80VU, CB 6XC not installed in 133VU, Mod 10890S20687 (Service

Bulletin No. A310-34-2174) not embodied

**CONF 008

Config. 008 is valid for aircraft for a given position 02 of relays in 105VU, Relay 220GB

installed in 80VU, CB 6XC not installed in 133VU, Mod 10890S20687 (Service Bulletin

No. A310-34-2174) embodied

**CONF 009

Config. 009 is valid for aircraft for a given position 06 of relays in 105VU, Relay 220GB

installed in 80VU, CB 6XC not installed in 133VU, Mod 10890S20687 (Service Bulletin

No. A310-34-2174) embodied

(6) Material Effectivity

MATERIAL QTY PER A/C SEE NOTES

Kit 742003A01R07 1

Kit 742003A02R00 1

Kit 742003A03R00 1

Supplementary kit 742003A01S01 1

Supplementary kit 742003A01S05 1

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 3

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

MATERIAL QTY PER A/C SEE NOTES

Supplementary kit 742003A01S06 1

Consumable CMLA01 1

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

Flameout events due to inclement weather have occurred on Airbus and other aircraft

equipped with CF6-80C2 engines.

(2) Objective/Action

To avoid long engine restart sequence after a non-selection of continuous relight by

the crew and a flame out event, the modification consists in improving the function

"Continuous Relight". This modification installs a shunt of the rotary selector to supply

energy to the igniters, when an engine power loss is detected, even if the continuous

ignition was not selected by the crew.

(3) Advantages

For an aircraft in flight, if N2 indicator data is lower than 45 per cent on an engine, both

ignition systems (A and B) will be energized in continuous for the concerned engine then

maintained for 120 seconds after engine relight. Accomplishment of this Service Bulletin

will "cover" a non-selection of continuous relight by the crew, in order to ensure quick

engine restart in case of flameout/rollback, especially at low altitude. This 120 seconds

period is a minimum duration for the continuous ignition, which ensures that the igniters

are supplied long enough to fulfil the purpose of this modification. Accomplishment of

this Service Bulletin will ensure better protection to engines by avoiding severe damage

due to a long engine restart sequence. This modification was designed, not to interfere

with the engine ground start logic, through the ground/flight distinction. There is no

impact on the ground start operational procedure.

(4) Operational/Maintenance Consequences

The operational maintenance consequences of this Service Bulletin are the modification

of the Flight Crew Operating Manual (FCOM) Vol. 1 and 2.

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

**CONF 001

Task 742003-831-801-001: Modification

(1) Modify the Circuit Breaker panel 133VU

(2) Modify the wiring in Circuit Breaker panel 133VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 4

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(3) Modify the equipment in the Relay Box 105VU on bench

(4) Modify the wiring in the Relay Box 105VU on bench

(5) Modify the Eng Start/APU/Wiper Panel 429VU

(6) Modify the Relay Box 104VU on bench

(7) Modify the Electronics Rack 80VU

(8) Modify the wiring in Zones

Task 742003-831-802-001: Modification - ADDITIONAL WORK

(1) Modify the wiring in the Circuit Breaker panel 133VU

Task 742003-831-803-001: Modification - ADDITIONAL WORK

(1) Modify the wiring in the Relay Box 105VU on bench

**CONF 002

Task 742003-831-801-001: Modification

(1) Modify the Circuit Breaker panel 133VU

(2) Modify the wiring in Circuit Breaker panel 133VU

(3) Modify the equipment in the Relay Box 105VU on bench

(4) Modify the wiring in the Relay Box 105VU on bench

(5) Modify the Eng Start/APU/Wiper Panel 429VU

(6) Modify the Relay Box 104VU on bench

(7) Modify the Electronics Rack 80VU

(8) Modify the wiring in Zones

Task 742003-831-802-001: Modification - ADDITIONAL WORK

(1) Modify the wiring in the Circuit Breaker panel 133VU

Task 742003-831-803-001: Modification - ADDITIONAL WORK

(1) Modify the wiring in the Relay Box 105VU on bench

**CONF 003

Task 742003-831-801-001: Modification

(1) Modify the Circuit Breaker panel 133VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 5

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(2) Modify the wiring in Circuit Breaker panel 133VU

(3) Modify the equipment in the Relay Box 105VU on bench

(4) Modify the wiring in the Relay Box 105VU on bench

(5) Modify the Eng Start/APU/Wiper Panel 429VU

(6) Modify the Relay Box 104VU on bench

(7) Modify the Electronics Rack 80VU

(8) Modify the wiring in Zones

Task 742003-831-802-001: Modification - ADDITIONAL WORK

(1) Modify the wiring in the Circuit Breaker panel 133VU

Task 742003-831-803-001: Modification - ADDITIONAL WORK

(1) Modify the wiring in the Relay Box 105VU on bench

**CONF 006

Task 742003-831-801-001: Modification

(1) Modify the Circuit Breaker panel 133VU

(2) Modify the wiring in Circuit Breaker panel 133VU

(3) Modify the equipment in the Relay Box 105VU on bench

(4) Modify the wiring in the Relay Box 105VU on bench

(5) Modify the Eng Start/APU/Wiper Panel 429VU

(6) Modify the Relay Box 104VU on bench

(7) Modify the Electronics Rack 80VU

(8) Modify the wiring in Zones

Task 742003-831-802-001: Modification - ADDITIONAL WORK

(1) Modify the wiring in the Circuit Breaker panel 133VU

Task 742003-831-803-001: Modification - ADDITIONAL WORK

(1) Modify the wiring in the Relay Box 105VU on bench

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 6

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 007

Task 742003-831-801-001: Modification

(1) Modify the Circuit Breaker panel 133VU

(2) Modify the wiring in Circuit Breaker panel 133VU

(3) Modify the equipment in the Relay Box 105VU on bench

(4) Modify the wiring in the Relay Box 105VU on bench

(5) Modify the Eng Start/APU/Wiper Panel 429VU

(6) Modify the Relay Box 104VU on bench

(7) Modify the wiring in Zones

Task 742003-831-802-001: Modification - ADDITIONAL WORK

(1) Modify the wiring in the Circuit Breaker panel 133VU

Task 742003-831-803-001: Modification - ADDITIONAL WORK

(1) Modify the wiring in the Relay Box 105VU on bench

**CONF 008

Task 742003-831-801-001: Modification

(1) Modify the Circuit Breaker panel 133VU

(2) Modify the wiring in Circuit Breaker panel 133VU

(3) Modify the equipment in the Relay Box 105VU on bench

(4) Modify the wiring in the Relay Box 105VU on bench

(5) Modify the Eng Start/APU/Wiper Panel 429VU

(6) Modify the Relay Box 104VU on bench

(7) Modify the Electronics Rack 80VU

(8) Modify the wiring in Zones

Task 742003-831-802-001: Modification - ADDITIONAL WORK

(1) Modify the wiring in the Circuit Breaker panel 133VU

Task 742003-831-803-001: Modification - ADDITIONAL WORK

(1) Modify the wiring in the Relay Box 105VU on bench

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 7

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 009

Task 742003-831-801-001: Modification

(1) Modify the Circuit Breaker panel 133VU

(2) Modify the wiring in Circuit Breaker panel 133VU

(3) Modify the equipment in the Relay Box 105VU on bench

(4) Modify the wiring in the Relay Box 105VU on bench

(5) Modify the Eng Start/APU/Wiper Panel 429VU

(6) Modify the Relay Box 104VU on bench

(7) Modify the Electronics Rack 80VU

(8) Modify the wiring in Zones

Task 742003-831-802-001: Modification - ADDITIONAL WORK

(1) Modify the wiring in the Circuit Breaker panel 133VU

Task 742003-831-803-001: Modification - ADDITIONAL WORK

(1) Modify the wiring in the Relay Box 105VU on bench

**CONF ALL

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

(2) Accomplishment Timescale

This Service Bulletin has been classified Mandatory by the issue of an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA).

The AD must be used as the reference document for the mandated accomplishment

timescale.

F. APPROVAL

Approved under EASA Design Organisation Approval No. EASA 21J.031.

If an aircraft listed in the effectivity has a modification or repair embodied that is not of

AIRBUS origin, and which affects the content of this Service Bulletin, the operator is

responsible for obtaining approval by its airworthiness authority for any adaptation necessary

before incorporation of the Service Bulletin.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 8

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

G. MANPOWER

The manpower estimates given in this Service Bulletin are based on the direct labor cost to

do the work. These estimates assume that the work will be done by experienced personnel,

and may need to be revised upwards to suit operator’s circumstances. The estimates do not

include the time to prepare, plan or inspect the work. Manufacture and procurement of parts

and tools, drying times for paints, sealants, etc., and general administration work are also not

included.

**CONF 001

Task 742003-831-801-001: Modification

Get Access 7.00

On Aircraft

Modify the Circuit Breaker panel 133VU 1.00

Modify the wiring in Circuit Breaker panel 133VU 2.00

Modify the equipment in the Relay Box 105VU on

bench

2.00

Modify the wiring in the Relay Box 105VU on bench 8.00

Modify the Eng Start/APU/Wiper Panel 429VU 10.00

Modify the Relay Box 104VU on bench 3.00

Modify the Electronics Rack 80VU 0.50

Modify the wiring in Zones 8.00

Tests 33.00

Close-Up 5.00

TOTAL MANHOURS 79.50

ELAPSED TIME (HOURS) 58.00

NOTE: For detail concerning the Elapsed Time Assumption, refer to Appendix 1

Task 742003-831-802-001: Modification - ADDITIONAL WORK

Get Access 1.00

On Aircraft

Modify the wiring in the Circuit Breaker panel 133VU 3.00

Tests 0.50

Close-Up 1.00

TOTAL MANHOURS 5.50

ELAPSED TIME (HOURS) 5.50

Task 742003-831-803-001: Modification - ADDITIONAL WORK

Get Access 1.00

On Bench

Modify the wiring in the Relay Box 105VU on bench 3.00

Tests 5.00

Close-Up 1.00

TOTAL MANHOURS 10.00

ELAPSED TIME (HOURS) 10.00

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 9

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 002

Task 742003-831-801-001: Modification

Get Access 7.00

On Aircraft

Modify the Circuit Breaker panel 133VU 1.00

Modify the wiring in Circuit Breaker panel 133VU 2.00

Modify the equipment in the Relay Box 105VU on

bench

2.00

Modify the wiring in the Relay Box 105VU on bench 8.00

Modify the Eng Start/APU/Wiper Panel 429VU 10.00

Modify the Relay Box 104VU on bench 3.00

Modify the Electronics Rack 80VU 0.50

Modify the wiring in Zones 8.00

Tests 33.00

Close-Up 5.00

TOTAL MANHOURS 79.50

ELAPSED TIME (HOURS) 58.00

NOTE: For detail concerning the Elapsed Time Assumption, refer to Appendix 1

Task 742003-831-802-001: Modification - ADDITIONAL WORK

Get Access 1.00

On Aircraft

Modify the wiring in the Circuit Breaker panel 133VU 3.00

Tests 0.50

Close-Up 1.00

TOTAL MANHOURS 5.50

ELAPSED TIME (HOURS) 5.50

Task 742003-831-803-001: Modification - ADDITIONAL WORK

Get Access 1.00

On Bench

Modify the wiring in the Relay Box 105VU on bench 3.00

Tests 5.00

Close-Up 1.00

TOTAL MANHOURS 10.00

ELAPSED TIME (HOURS) 10.00

**CONF 003

Task 742003-831-801-001: Modification

Get Access 7.00

On Aircraft

Modify the Circuit Breaker panel 133VU 1.00

Modify the wiring in Circuit Breaker panel 133VU 2.00

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 10

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Task 742003-831-801-001: Modification

Modify the equipment in the Relay Box 105VU on

bench

2.00

Modify the wiring in the Relay Box 105VU on bench 8.00

Modify the Eng Start/APU/Wiper Panel 429VU 10.00

Modify the Relay Box 104VU on bench 3.00

Modify the Electronics Rack 80VU 0.50

Modify the wiring in Zones 8.00

Tests 33.00

Close-Up 5.00

TOTAL MANHOURS 79.50

ELAPSED TIME (HOURS) 58.00

NOTE: For detail concerning the Elapsed Time Assumption, refer to Appendix 1

Task 742003-831-802-001: Modification - ADDITIONAL WORK

Get Access 1.00

On Aircraft

Modify the wiring in the Circuit Breaker panel 133VU 3.00

Tests 0.50

Close-Up 1.00

TOTAL MANHOURS 5.50

ELAPSED TIME (HOURS) 5.50

Task 742003-831-803-001: Modification - ADDITIONAL WORK

Get Access 1.00

On Bench

Modify the wiring in the Relay Box 105VU on bench 3.00

Tests 5.00

Close-Up 1.00

TOTAL MANHOURS 10.00

ELAPSED TIME (HOURS) 10.00

**CONF 006

Task 742003-831-801-001: Modification

Get Access 7.00

On Aircraft

Modify the Circuit Breaker panel 133VU 1.00

Modify the wiring in Circuit Breaker panel 133VU 2.00

Modify the equipment in the Relay Box 105VU on

bench

2.00

Modify the wiring in the Relay Box 105VU on bench 8.00

Modify the Eng Start/APU/Wiper Panel 429VU 10.00

Modify the Relay Box 104VU on bench 3.00

Modify the Electronics Rack 80VU 0.50

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 11

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Task 742003-831-801-001: Modification

Modify the wiring in Zones 8.00

Tests 33.00

Close-Up 5.00

TOTAL MANHOURS 79.50

ELAPSED TIME (HOURS) 58.00

NOTE: For detail concerning the Elapsed Time Assumption, refer to Appendix 1

Task 742003-831-802-001: Modification - ADDITIONAL WORK

Get Access 1.00

On Aircraft

Modify the wiring in the Circuit Breaker panel 133VU 3.00

Tests 0.50

Close-Up 1.00

TOTAL MANHOURS 5.50

ELAPSED TIME (HOURS) 5.50

Task 742003-831-803-001: Modification - ADDITIONAL WORK

Get Access 1.00

On Bench

Modify the wiring in the Relay Box 105VU on bench 3.00

Tests 5.00

Close-Up 1.00

TOTAL MANHOURS 10.00

ELAPSED TIME (HOURS) 10.00

**CONF 007

Task 742003-831-801-001: Modification

Get Access 7.00

On Aircraft

Modify the Circuit Breaker panel 133VU 1.00

Modify the wiring in Circuit Breaker panel 133VU 2.00

Modify the equipment in the Relay Box 105VU on

bench

2.00

Modify the wiring in the Relay Box 105VU on bench 8.00

Modify the Eng Start/APU/Wiper Panel 429VU 10.00

Modify the Relay Box 104VU on bench 3.00

Modify the wiring in Zones 8.00

Tests 33.00

Close-Up 5.00

TOTAL MANHOURS 79.00

ELAPSED TIME (HOURS) 58.00

NOTE: For detail concerning the Elapsed Time Assumption, refer to Appendix 1

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 12

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Task 742003-831-802-001: Modification - ADDITIONAL WORK

Get Access 1.00

On Aircraft

Modify the wiring in the Circuit Breaker panel 133VU 3.00

Tests 0.50

Close-Up 1.00

TOTAL MANHOURS 5.50

ELAPSED TIME (HOURS) 5.50

Task 742003-831-803-001: Modification - ADDITIONAL WORK

Get Access 1.00

On Bench

Modify the wiring in the Relay Box 105VU on bench 3.00

Tests 5.00

Close-Up 1.00

TOTAL MANHOURS 10.00

ELAPSED TIME (HOURS) 10.00

**CONF 008

Task 742003-831-801-001: Modification

Get Access 7.00

On Aircraft

Modify the Circuit Breaker panel 133VU 1.00

Modify the wiring in Circuit Breaker panel 133VU 2.00

Modify the equipment in the Relay Box 105VU on

bench

2.00

Modify the wiring in the Relay Box 105VU on bench 8.00

Modify the Eng Start/APU/Wiper Panel 429VU 10.00

Modify the Relay Box 104VU on bench 3.00

Modify the Electronics Rack 80VU 0.50

Modify the wiring in Zones 8.00

Tests 33.00

Close-Up 5.00

TOTAL MANHOURS 79.50

ELAPSED TIME (HOURS) 58.00

Task 742003-831-802-001: Modification - ADDITIONAL WORK

Get Access 1.00

On Aircraft

Modify the wiring in the Circuit Breaker panel 133VU 3.00

Tests 0.50

Close-Up 1.00

TOTAL MANHOURS 5.50

ELAPSED TIME (HOURS) 5.50

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 13

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Task 742003-831-803-001: Modification - ADDITIONAL WORK

Get Access 1.00

On Bench

Modify the wiring in the Relay Box 105VU on bench 3.00

Tests 5.00

Close-Up 1.00

TOTAL MANHOURS 10.00

ELAPSED TIME (HOURS) 10.00

**CONF 009

Task 742003-831-801-001: Modification

Get Access 7.00

On Aircraft

Modify the Circuit Breaker panel 133VU 1.00

Modify the wiring in Circuit Breaker panel 133VU 2.00

Modify the equipment in the Relay Box 105VU on

bench

2.00

Modify the wiring in the Relay Box 105VU on bench 8.00

Modify the Eng Start/APU/Wiper Panel 429VU 10.00

Modify the Relay Box 104VU on bench 3.00

Modify the Electronics Rack 80VU 0.50

Modify the wiring in Zones 8.00

Tests 33.00

Close-Up 5.00

TOTAL MANHOURS 79.50

ELAPSED TIME (HOURS) 58.00

Task 742003-831-802-001: Modification - ADDITIONAL WORK

Get Access 1.00

On Aircraft

Modify the wiring in the Circuit Breaker panel 133VU 3.00

Tests 0.50

Close-Up 1.00

TOTAL MANHOURS 5.50

ELAPSED TIME (HOURS) 5.50

Task 742003-831-803-001: Modification - ADDITIONAL WORK

Get Access 1.00

On Bench

Modify the wiring in the Relay Box 105VU on bench 3.00

Tests 5.00

Close-Up 1.00

TOTAL MANHOURS 10.00

ELAPSED TIME (HOURS) 10.00

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 14

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

H. WEIGHT AND BALANCE

The weight and balance estimates given in this Service Bulletin are based on the

Manufacturer’s Empty Weight (MEW) and do not include operator item’s. For the definition of

MEW and operator’s items refer to Weight and Balance Manual (WBM) Chapter 1-00-07.

Manufacturers Empty Weight 0.39 KG (+0.8597 LB)

Effect on Balance 3.435 KGM (+24.845 LB.FT )

I. ELECTRICAL LOAD DATA

(1) Direct Current (DC) Load Changes

NOTE: The values listed in the table(s) below show the increase (+) or decrease

(-) of the electrical load resulting from the accomplishment of this Service

Bulletin.

(a) Circuit Breaker : 13JH (New)

Busbar : 301PP

Nominal Power : 6W

Flight Configuration Value W (Operational) Value W (Max)

T/OFF 0W 0W

Landing 0W +6W

(b) Circuit Breaker : 14JH (New)

Busbar : 305PP

Nominal Power : 6W

Flight Configuration Value W (Operational) Value W (Max)

T/OFF 0W 0W

Landing 0W +6W

(2) Alternating Current (AC) Load Changes

Not Changed

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 15

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

J. REFERENCES

**CONF 001

Aircraft Maintenance Manual (AMM) 11-00-00 20-21-12 20-28-11

21-21-00 21-22-00 21-23-12

21-31-11 22-18-34 22-36-34

22-40-00 23-12-00 23-12-13

23-71-12 24-00-00 24-22-15

24-23-13 24-31-00 24-31-11

24-41-00 24-50-20 25-13-11

25-13-12 26-12-20 26-13-20

28-22-55 28-24-31 28-25-17

28-28-12 28-42-38 28-42-41

30-45-00 31-10-00 31-51-00

31-53-34 31-55-22 31-69-00

32-31-11 33-12-00 33-12-11

33-13-00 33-14-00 33-46-00

34-25-00 34-25-25 34-44-34

34-68-34 34-73-34 36-11-00

36-11-19 49-10-00 49-31-00

52-10-00 52-51-00 71-00-00

71-13-00 74-00-00 77-12-21

78-31-00

Aircraft Wiring List (AWL)

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-25-51 20-33-00 20-33-44

20-46-50 20-52-10 20-52-20

20-52-21 20-55-00

Standards Manual (SM)

Weight and Balance Manual (WBM) 1-00-07

**CONF 002

Aircraft Maintenance Manual (AMM) 11-00-00 20-21-12 20-28-11

21-21-00 21-22-00 21-23-12

21-31-11 22-18-34 22-36-34

22-40-00 23-12-00 23-12-13

23-71-12 24-00-00 24-22-15

24-23-13 24-31-00 24-31-11

24-41-00 24-50-20 25-13-11

25-13-12 26-12-20 26-13-20

28-22-55 28-24-31 28-25-17

28-28-12 28-42-38 28-42-41

30-45-00 31-10-00 31-51-00

31-53-34 31-55-22 31-69-00

32-31-11 33-12-00 33-12-11

33-13-00 33-14-00 33-46-00

34-25-00 34-25-25 34-44-34

34-68-34 34-73-34 36-11-00

36-11-19 49-10-00 49-31-00

52-10-00 52-51-00 71-00-00

71-13-00 74-00-00 77-12-21

78-31-00

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 16

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Aircraft Wiring List (AWL)

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-25-51 20-33-00 20-33-44

20-46-50 20-52-10 20-52-20

20-52-21 20-55-00

Standards Manual (SM)

Weight and Balance Manual (WBM) 1-00-07

**CONF 003

Aircraft Maintenance Manual (AMM) 11-00-00 20-21-12 20-28-11

21-21-00 21-22-00 21-23-12

21-31-11 22-18-34 22-36-34

22-40-00 23-12-00 23-12-13

23-71-12 24-00-00 24-22-15

24-23-13 24-31-00 24-31-11

24-41-00 24-50-20 25-13-11

25-13-12 26-12-20 26-13-20

28-22-55 28-24-31 28-25-17

28-28-12 28-42-38 28-42-41

30-45-00 31-10-00 31-51-00

31-53-34 31-55-22 31-69-00

32-31-11 33-12-00 33-12-11

33-13-00 33-14-00 33-46-00

34-25-00 34-25-25 34-44-34

34-68-34 34-73-34 36-11-00

36-11-19 49-10-00 49-31-00

52-10-00 52-51-00 71-00-00

71-13-00 74-00-00 77-12-21

78-31-00

Aircraft Wiring List (AWL)

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-25-51 20-33-00 20-33-44

20-46-50 20-52-10 20-52-20

20-52-21 20-55-00

Standards Manual (SM)

Weight and Balance Manual (WBM) 1-00-07

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 17

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 006

Aircraft Maintenance Manual (AMM) 11-00-00 20-21-12 20-28-11

21-21-00 21-22-00 21-23-12

21-31-11 22-18-34 22-36-34

22-40-00 23-12-00 23-12-13

23-71-12 24-00-00 24-22-15

24-23-13 24-31-00 24-31-11

24-41-00 24-50-20 25-13-11

25-13-12 26-12-20 26-13-20

28-22-55 28-24-31 28-25-17

28-28-12 28-42-38 28-42-41

30-45-00 31-10-00 31-51-00

31-53-34 31-55-22 31-69-00

32-31-11 33-12-00 33-12-11

33-13-00 33-14-00 33-46-00

34-25-00 34-25-25 34-44-34

34-68-34 34-73-34 36-11-00

36-11-19 49-10-00 49-31-00

52-10-00 52-51-00 71-00-00

71-13-00 74-00-00 77-12-21

78-31-00

Aircraft Wiring List (AWL)

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-25-51 20-33-00 20-33-44

20-46-50 20-52-10 20-52-20

20-52-21 20-55-00

Standards Manual (SM)

Weight and Balance Manual (WBM) 1-00-07

**CONF 007

Aircraft Maintenance Manual (AMM) 11-00-00 20-21-12 20-28-11

21-21-00 21-22-00 21-23-12

21-31-11 22-18-34 22-36-34

22-40-00 23-12-00 23-12-13

23-71-12 24-00-00 24-22-15

24-23-13 24-31-00 24-31-11

24-41-00 24-50-20 25-13-11

25-13-12 26-12-20 26-13-20

28-22-55 28-24-31 28-25-17

28-28-12 28-42-38 28-42-41

30-45-00 31-10-00 31-51-00

31-53-34 31-55-22 31-69-00

32-31-11 33-12-00 33-12-11

33-13-00 33-14-00 33-46-00

34-25-00 34-25-25 34-44-34

34-68-34 34-73-34 36-11-00

36-11-19 49-10-00 49-31-00

52-10-00 52-51-00 71-00-00

71-13-00 74-00-00 77-12-21

78-31-00

Aircraft Wiring List (AWL)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 18

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-25-51 20-33-00 20-33-44

20-46-50 20-52-10 20-52-20

20-52-21 20-55-00

Standards Manual (SM)

Weight and Balance Manual (WBM) 1-00-07

**CONF 008

Aircraft Maintenance Manual (AMM) 11-00-00 20-21-12 20-28-11

21-21-00 21-22-00 21-23-12

21-31-11 22-18-34 22-36-34

22-40-00 23-12-00 23-12-13

23-71-12 24-00-00 24-22-15

24-23-13 24-31-00 24-31-11

24-41-00 24-50-20 25-13-11

25-13-12 26-12-20 26-13-20

28-22-55 28-24-31 28-25-17

28-28-12 28-42-38 28-42-41

30-45-00 31-10-00 31-51-00

31-53-34 31-55-22 31-69-00

32-31-11 33-12-00 33-12-11

33-13-00 33-14-00 33-46-00

34-25-00 34-25-25 34-44-34

34-68-34 34-73-34 36-11-00

36-11-19 49-10-00 49-31-00

52-10-00 52-51-00 71-00-00

71-13-00 74-00-00 77-12-21

78-31-00

Aircraft Wiring List (AWL)

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-25-51 20-33-00 20-33-44

20-46-50 20-52-10 20-52-20

20-52-21 20-55-00

Standards Manual (SM)

Weight and Balance Manual (WBM) 1-00-07

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 19

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 009

Aircraft Maintenance Manual (AMM) 11-00-00 20-21-12 20-28-11

21-21-00 21-22-00 21-23-12

21-31-11 22-18-34 22-36-34

22-40-00 23-12-00 23-12-13

23-71-12 24-00-00 24-22-15

24-23-13 24-31-00 24-31-11

24-41-00 24-50-20 25-13-11

25-13-12 26-12-20 26-13-20

28-22-55 28-24-31 28-25-17

28-28-12 28-42-38 28-42-41

30-45-00 31-10-00 31-51-00

31-53-34 31-55-22 31-69-00

32-31-11 33-12-00 33-12-11

33-13-00 33-14-00 33-46-00

34-25-00 34-25-25 34-44-34

34-68-34 34-73-34 36-11-00

36-11-19 49-10-00 49-31-00

52-10-00 52-51-00 71-00-00

71-13-00 74-00-00 77-12-21

78-31-00

Aircraft Wiring List (AWL)

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-25-51 20-33-00 20-33-44

20-46-50 20-52-10 20-52-20

20-52-21 20-55-00

Standards Manual (SM)

Weight and Balance Manual (WBM) 1-00-07

**CONF ALL

K. PUBLICATION AFFECTED

Aircraft Maintenance Manual (AMM) 24-50-00 74-00-00 74-10-00

74-30-00 77-12-00

Aircraft Schematic Manual (ASM) 24-59-14 24-59-18 31-69-17

74-31-01 80-10-01

Aircraft Wiring List (AWL)

Aircraft Wiring Manual (AWM) 24-59-14 24-59-18 31-69-17

74-31-01 74-31-02 80-11-01

80-11-03 91-11-05 91-11-33

91-14-29

Flight Crew Operating Manual (FCOM) Chapter 01

Chapter 02

Illustrated Parts Catalog (IPC) 31-14-01

Trouble Shooting Manual (TSM) 71-02-00 71-03-00 74-00-20

74-00-30

NOTE: This Service Bulletin has an operational impact. Please inform AIRBUS,

at least four weeks in advance, in case you need your operational

documentation to be amended by an intermediate revision prior to Service

Bulletin embodiment. For this purpose, please request the intermediate

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 20

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

revision by fax, telex or mail to :

SEDCC, AIRBUS

Customer Services Directorate

Fax No.: 33 (0) 5 61 93 28 06

Sita No.: TLSBP7X

E-mail: sb.reporting@airbus.com

These amendments will be confirmed by the next normal revision of

operational documentation, once your Service Bulletin accomplishment report

has been sent, as usual, to our Customer Services Directorate (SEDCC).

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 21

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 22

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

Kit 742003A01R07

Kit 742003A02R00

Kit 742003A03R00

Supplementary kit 742003A01S01

Supplementary kit 742003A01S05

Supplementary kit 742003A01S06

Customers with aircraft shown in the

effectivity of this Service Bulletin should send

a purchase order to AIRBUS. Quote the

number of this Service Bulletin. The address

is:

AIRBUS Material, Logistics and Suppliers

Weg beim Jaeger 150 D

22335 Hamburg

Germany

For ordering by internet:

http://spares.airbus.com

For ordering modification kits by fax: +49 40

50 76 25 90

For ordering E-mail: airbus.kit@airbus.com

(2) Price and Availability

NOTE: This table shows the supplemental kits (S kits) needed to update the kits

already held in your stock to the latest status.

Operator that has already received KIT 742003A01 at previous revision

must complete it as per table below :

Kit held by

operator

Supplementary

kit required

latest status of

kit

INST/DISP

742003A01R01

742003A01S01

+

742003A01S05

+

742003A01S06

742003A01R07

742003A01R03

or

742003A01R01

+

742003A01S01

742003A01S05

+

742003A01S06

742003A01R07

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 23

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

742003A01R06

or

742003A01R03

+

742003A01S05

or

742003A01R01

+

742003A01S01

+

742003A01S05

742003A01S06 742003A01R07

NOTE: Kit 742003A02R00, concerns aircraft affected by TASK 742003-831-802

001 Modification - ADDITIONAL WORK .

NOTE: Kit 742003A03R00, concerns aircraft affected by TASK 742003-831-803

001 Modification - ADDITIONAL WORK .

Kit 742003A01R07

Cost 14,920.00 USD

Availability 180 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require Kits before this time, please include a retrofit planning schedule with

your order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin.

The latest valid price and lead time for ordering purposes shall be obtained through the

AirbusSparesportal or through a request for quotation to airbus.kit @airbus.com

Kit 742003A02R00

Cost 260.00 USD

Availability 60 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require Kits before this time, please include a retrofit planning schedule with

your order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin.

Kit 742003A03R00

Cost 194.00 USD

Availability 60 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require Kits before this time, please include a retrofit planning schedule with

your order so that we can try to comply with your requirements.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 24

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

The sales terms (costs and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin.

Supplementary kit 742003A01S01

Cost 1,740.00 USD

Availability 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require Kits before this time, please include a retrofit planning schedule with

your order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin.

The latest valid price and lead time for ordering purposes shall be obtained through the

AirbusSparesportal or through a request for quotation to airbus.kit @airbus.com

Supplementary kit 742003A01S05

Cost 2,130.00 USD

Availability 60 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require Kits before this time, please include a retrofit planning schedule with

your order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin.

The latest valid price and lead time for ordering purposes shall be obtained through the

AirbusSparesportal or through a request for quotation to airbus.kit @airbus.com

Supplementary kit 742003A01S06

Cost 2,600.00 USD

Availability 60 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require Kits before this time, please include a retrofit planning schedule with

your order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin.

B. INDUSTRY SUPPORT INFORMATION

AIRBUS will provide a 15 per cent reduction to the applicable sales prices given in the

paragraph ’Price and Availability’ for orders placed before Dec 31/15.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 25

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

C. LIST OF COMPONENTS

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

1 A9251063000000 1 SUPPLATE

2 EN3646A02255AZ 1 CONNECTR

3 NSA937901RB0120 1 RAIL

4 NAS1100-06-7 3 SCREW

5 MS35333-37 3 WASHER

6 NAS1100-08-7 2 SCREW

7 NAS1149FN816P 2 WASHER

9 A9251133320000 1 PLATE

10 NAS1100-04-7 8 SCREW

11 MS21042-04 8 NUT

12 NAS1149FN416P 14 WASHER

13 NAS1100-04-6 6 SCREW

14 MS21042L04 6 NUT

A11321141C00 2 PLACARD

A9000095320695 1 BUNDLE

A9100095041095 1 PLCD SET

ABS1416A120CJ 2 RELAY

E0247A0 2 BASE

E0666D28A0 2 RELAY

EN2995-004A03AA 2 CB

EN3155-018M1616 1 PIN

EN3155-019F1616 1 CONTACT

EN3646A62255BZ 1 CONNECTR

NSA932844CJ 2 SOCKET

NSA935401-03 80 TIE

NSA935401-05 200 TIE

NSA935401-13 100 TIE

NSA937901E0 1 LABEL

NSA937901E1 5 LABEL

NSA937901E7 1 LABEL

NSA937901E8 1 LABEL

NSA937901E9 1 LABEL

NSA937901FM 1 MODULE

NSA937901M20-08 2 MODULE

NSA937901MA2004 2 MODULE

NSA937901MA2011 1 MODULE

NSA938003-22 1 BACKSHLL

NSA938150-02-22 1 BACKSHLL

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 26

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Kit 742003A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

A9000095320795 1 BUNDLE

NSA935401-03 20 TIE

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Kit 742003A03R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

A9000095321095 1 BUNDLE

NSA935401-03 50 TIE

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Supplementary kit 742003A01S01

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

NSA932844CJ 2 SOCKET

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Supplementary kit 742003A01S05

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

A11321141C00 2 PLACARD

EN3155-018M1616 1 PIN

EN3155-019F1616 1 CONTACT

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

A9000095320695 1 BUNDLE

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 27

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Pure Mineral Vaseline Or PetroLatum04-012 As required

Electrical Bond Varnish 07-001B As required

(2) Components

None

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

None

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 28

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

Task 742003-831-801-001 - Modification

WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS

INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO

THIS:

- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS

NECESSARY ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00.

NOTE: The accomplishment instructions of this Service Bulletin refer to procedures

included in other AIRBUS documents. When the words ’refer to’ are used and the

operator has an accepted alternative procedure, the accepted alternative procedure

can be used. When the words ’in accordance with’ are included in the instruction,

the procedure in the AIRBUS document must be used.

NOTE: The access and close-up instructions, not comprising return to service tests, in this

Service Bulletin do not constitute or affect the technical intent of the Service

Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or

close-up steps to add flexibility to their maintenance operations as long as the

technical intent of the Service Bulletin is met within the set parameters.

NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms.

Refer to paragraph 1.J., References, for the definition of acronyms.

Task Associated Data

**CONF 001

Zone

120 121 122 210

From 120 to 210

Modified FIN

13JH 14JH 15JH 15JHA 16JH 16JHA 17JH 17JHA 18JH 18JHA 1471VC 1471VCA

1471VCA1 1347VT 1347VT9

Manpower

TOTAL MANHOURS 79.50

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 29

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

ELAPSED TIME (HOURS) 58.00

**CONF 002

Zone

120 121 122 210

From 120 to 210

Modified FIN

13JH 14JH 15JH 15JHA 16JH 16JHA 17JH 17JHA 18JH 18JHA 1471VC 1471VCA

1471VCA1 1347VT 1347VT9

Manpower

TOTAL MANHOURS 79.50

ELAPSED TIME (HOURS) 58.00

**CONF 003

Zone

120 121 122 210

From 120 to 210

Modified FIN

13JH 14JH 15JH 15JHA 16JH 16JHA 17JH 17JHA 18JH 18JHA 1471VC 1471VCA

1471VCA1 1347VT 1347VT9

Manpower

TOTAL MANHOURS 79.50

ELAPSED TIME (HOURS) 58.00

**CONF 006

Zone

120 121 122 210

From 120 to 210

Modified FIN

13JH 14JH 15JH 15JHA 16JH 16JHA 17JH 17JHA 18JH 18JHA 1471VC 1471VCA

1471VCA1 1347VT 1347VT9

Manpower

TOTAL MANHOURS 79.50

ELAPSED TIME (HOURS) 58.00

**CONF 007

Zone

120 122 210

From 120 to 210

Modified FIN

13JH 14JH 15JH 15JHA 16JH 16JHA 17JH 17JHA 18JH 18JHA 1471VC 1471VCA

1471VCA1 1347VT 1347VT9

Manpower

TOTAL MANHOURS 79.00

ELAPSED TIME (HOURS) 58.00

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 30

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 008

Zone

120 121 122 210

From 120 to 210

Modified FIN

13JH 14JH 15JH 15JHA 16JH 16JHA 17JH 17JHA 18JH 18JHA 1471VC 1471VCA

1471VCA1 1347VT 1347VT9

Manpower

TOTAL MANHOURS 79.50

ELAPSED TIME (HOURS) 58.00

**CONF 009

Zone

120 121 122 210

From 120 to 210

Modified FIN

13JH 14JH 15JH 15JHA 16JH 16JHA 17JH 17JHA 18JH 18JHA 1471VC 1471VCA

1471VCA1 1347VT 1347VT9

Manpower

TOTAL MANHOURS 79.50

ELAPSED TIME (HOURS) 58.00

**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 742003-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 11-00-00

20-21-12

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-25-51

20-33-00

20-33-44

20-52-21

(a) Obey the instructions for the general wiring installation (Refer to ESPM 20-33-00).

(b) To install the new wires cut them to the necessary length, crimp the terminals and

connect them.

(c) Do a continuity test of the new and modified wires (Refer to ESPM 20-52-21).

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 31

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(d) Route the new wires with the wires that are in the aircraft.

(e) For the cable tie application and tooling, refer to ESPM 20-25-51 and ESPM

20-33-44.

(f) Bond the placards (Refer to AMM 11-00-00)

(g) For the specification of materials (Mat. No.) that you must use in this Service

Bulletin refer to Consumable Materials List (CML)

(h) Torque standard threaded fasteners (Refer to AMM 20-21-12).

(2) Subtask 742003-839-001-001 - Administrative

(a) Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF 002

(1) Subtask 742003-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 11-00-00

20-21-12

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-25-51

20-33-00

20-33-44

20-52-21

(a) Obey the instructions for the general wiring installation (Refer to ESPM 20-33-00).

(b) To install the new wires cut them to the necessary length, crimp the terminals and

connect them.

(c) Do a continuity test of the new and modified wires (Refer to ESPM 20-52-21).

(d) Route the new wires with the wires that are in the aircraft.

(e) For the cable tie application and tooling, refer to ESPM 20-25-51 and ESPM

20-33-44.

(f) Bond the placards (Refer to AMM 11-00-00)

(g) For the specification of materials (Mat. No.) that you must use in this Service

Bulletin refer to Consumable Materials List (CML)

(h) Torque standard threaded fasteners (Refer to AMM 20-21-12).

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 32

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(2) Subtask 742003-839-001-001 - Administrative

(a) Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF 003

(1) Subtask 742003-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 11-00-00

20-21-12

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-25-51

20-33-00

20-33-44

20-52-21

(a) Obey the instructions for the general wiring installation (Refer to ESPM 20-33-00).

(b) To install the new wires cut them to the necessary length, crimp the terminals and

connect them.

(c) Do a continuity test of the new and modified wires (Refer to ESPM 20-52-21).

(d) Route the new wires with the wires that are in the aircraft.

(e) For the cable tie application and tooling, refer to ESPM 20-25-51 and ESPM

20-33-44.

(f) Bond the placards (Refer to AMM 11-00-00)

(g) For the specification of materials (Mat. No.) that you must use in this Service

Bulletin refer to Consumable Materials List (CML)

(h) Torque standard threaded fasteners (Refer to AMM 20-21-12).

(2) Subtask 742003-839-001-001 - Administrative

(a) Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF 006

(1) Subtask 742003-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 33

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 11-00-00

20-21-12

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-25-51

20-33-00

20-33-44

20-52-21

(a) Obey the instructions for the general wiring installation (Refer to ESPM 20-33-00).

(b) To install the new wires cut them to the necessary length, crimp the terminals and

connect them.

(c) Do a continuity test of the new and modified wires (Refer to ESPM 20-52-21).

(d) Route the new wires with the wires that are in the aircraft.

(e) For the cable tie application and tooling, refer to ESPM 20-25-51 and ESPM

20-33-44.

(f) Bond the placards (Refer to AMM 11-00-00)

(g) For the specification of materials (Mat. No.) that you must use in this Service

Bulletin refer to Consumable Materials List (CML)

(h) Torque standard threaded fasteners (Refer to AMM 20-21-12).

(2) Subtask 742003-839-001-001 - Administrative

(a) Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF 007

(1) Subtask 742003-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 11-00-00

20-21-12

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-25-51

20-33-00

20-33-44

20-52-21

(a) Obey the instructions for the general wiring installation (Refer to ESPM 20-33-00).

(b) To install the new wires cut them to the necessary length, crimp the terminals and

connect them.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 34

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(c) Do a continuity test of the new and modified wires (Refer to ESPM 20-52-21).

(d) Route the new wires with the wires that are in the aircraft.

(e) For the cable tie application and tooling, refer to ESPM 20-25-51 and ESPM

20-33-44.

(f) Bond the placards (Refer to AMM 11-00-00)

(g) For the specification of materials (Mat. No.) that you must use in this Service

Bulletin refer to Consumable Materials List (CML)

(h) Torque standard threaded fasteners (Refer to AMM 20-21-12).

(2) Subtask 742003-839-001-001 - Administrative

(a) Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF 008

(1) Subtask 742003-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 11-00-00

20-21-12

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-25-51

20-33-00

20-33-44

20-52-21

(a) Obey the instructions for the general wiring installation (Refer to ESPM 20-33-00).

(b) To install the new wires cut them to the necessary length, crimp the terminals and

connect them.

(c) Do a continuity test of the new and modified wires (Refer to ESPM 20-52-21).

(d) Route the new wires with the wires that are in the aircraft.

(e) For the cable tie application and tooling, refer to ESPM 20-25-51 and ESPM

20-33-44.

(f) Bond the placards (Refer to AMM 11-00-00)

(g) For the specification of materials (Mat. No.) that you must use in this Service

Bulletin refer to Consumable Materials List (CML)

(h) Torque standard threaded fasteners (Refer to AMM 20-21-12).

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 35

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(2) Subtask 742003-839-001-001 - Administrative

(a) Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF 009

(1) Subtask 742003-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 11-00-00

20-21-12

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-25-51

20-33-00

20-33-44

20-52-21

(a) Obey the instructions for the general wiring installation (Refer to ESPM 20-33-00).

(b) To install the new wires cut them to the necessary length, crimp the terminals and

connect them.

(c) Do a continuity test of the new and modified wires (Refer to ESPM 20-52-21).

(d) Route the new wires with the wires that are in the aircraft.

(e) For the cable tie application and tooling, refer to ESPM 20-25-51 and ESPM

20-33-44.

(f) Bond the placards (Refer to AMM 11-00-00)

(g) For the specification of materials (Mat. No.) that you must use in this Service

Bulletin refer to Consumable Materials List (CML)

(h) Torque standard threaded fasteners (Refer to AMM 20-21-12).

(2) Subtask 742003-839-001-001 - Administrative

(a) Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 36

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

B. PREPARATION

**CONF 001

(1) Subtask 742003-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 23-12-13, Page Block 401

23-71-12, Page Block 401

24-00-00, Page Block 301

24-31-11, Page Block 401

25-13-11, Page Block 401

25-13-12, Page Block 401

26-12-20, Page Block 401

26-13-20, Page Block 401

28-42-41, Page Block 401

34-25-25, Page Block 401

52-10-00

52-10-00, Page Block 001

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page

Block 301).

(c) Put access platform(s) in position

(d) Open the passenger/crew door(s) (Refer to AMM 52-10-00)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 37

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(e) Remove the right side panels, the ceiling panels, as necessary, to get access to the

work area (Refer to AMM 25-13-11, Page Block 401)(Refer to AMM 25-13-12, Page

Block 401).

(f) On overhead panel 20VU, disconnect and remove for access if installed:

1 The Small VUs 45VU, 76VU, 424VU, 425VU, 430VU, 431VU, 433VU, 435VU,

438VU

2 The Fuel Quantity indicator 6QT (Refer to AMM 28-42-41, Page Block 401)

3 The Mode Selector Units 310FP1, 310FP2 and 310FP3 (Refer to AMM

34-25-25, Page Block 401)

4 the Cockpit Voice Recorder Unit 1RK (Refer to AMM 23-71-12, Page Block

401)

5 The APU Fire Control Module 20WG (Refer to AMM 26-13-20, Page Block

401)

6 The Engine Fire Control modules 39WD and 40WD (Refer to AMM 26-12-20,

Page Block 401)

7 The VHF3 Control Unit 2RC3 (Refer to AMM 23-12-13, Page Block 401)

(g) Make sure that the external connector(s) is (are) not connected to the aircraft

receptacle(s) EXT PW.

(h) Make sure that there is (are) warning notice(s) on external power receptacle to tell

persons not to connect an external power source.

(i) Make sure that the EMER EXIT LT pushbutton switch on 436VU is on DISARM

position.

(j) In the cockpit, on the overhead panel 424VU release BAT pushbutton switches.

(k) Put a warning notice on panel 424VU to tell persons not to operate the batteries.

(l) Put a warning notice on the refuel/defuel panel 110VU to tell persons not to operate

the NORMAL BATTERY switch.

(m) Put a warning notice in the cockpit to tell persons not to start the APU.

(n) Put a warning notice in the cockpit to tell persons not to start the ENG1, 2.

(o) Battery disconnection :

- For Job Set-up, refer to Removal of the Batteries (Refer to AMM 24-31-11,

Page Block 401).

- Turn the knurled nut a quarter turn.

- Disconnect the connectors.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 38

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

- Put blanking caps on the disconnected electrical connectors.

**CONF 002

(1) Subtask 742003-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 23-12-13, Page Block 401

23-71-12, Page Block 401

24-00-00, Page Block 301

24-31-11, Page Block 401

25-13-11, Page Block 401

25-13-12, Page Block 401

26-12-20, Page Block 401

26-13-20, Page Block 401

28-42-41, Page Block 401

34-25-25, Page Block 401

52-10-00

52-10-00, Page Block 001

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page

Block 301).

(c) Put access platform(s) in position

(d) Open the passenger/crew door(s) (Refer to AMM 52-10-00)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 39

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(e) Remove the right side panels, the ceiling panels, as necessary, to get access to the

work area (Refer to AMM 25-13-11, Page Block 401)(Refer to AMM 25-13-12, Page

Block 401).

(f) On overhead panel 20VU, disconnect and remove for access if installed:

1 The Small VUs 45VU, 76VU, 424VU, 425VU, 430VU, 431VU, 433VU, 435VU,

438VU

2 The Fuel Quantity indicator 6QT (Refer to AMM 28-42-41, Page Block 401)

3 The Mode Selector Units 310FP1, 310FP2 and 310FP3 (Refer to AMM

34-25-25, Page Block 401)

4 the Cockpit Voice Recorder Unit 1RK (Refer to AMM 23-71-12, Page Block

401)

5 The APU Fire Control Module 20WG (Refer to AMM 26-13-20, Page Block

401)

6 The Engine Fire Control modules 39WD and 40WD (Refer to AMM 26-12-20,

Page Block 401)

7 The VHF3 Control Unit 2RC3 (Refer to AMM 23-12-13, Page Block 401)

(g) Make sure that the external connector(s) is (are) not connected to the aircraft

receptacle(s) EXT PW.

(h) Make sure that there is (are) warning notice(s) on external power receptacle to tell

persons not to connect an external power source.

(i) Make sure that the EMER EXIT LT pushbutton switch on 436VU is on DISARM

position.

(j) In the cockpit, on the overhead panel 424VU release BAT pushbutton switches.

(k) Put a warning notice on panel 424VU to tell persons not to operate the batteries.

(l) Put a warning notice on the refuel/defuel panel 110VU to tell persons not to operate

the NORMAL BATTERY switch.

(m) Put a warning notice in the cockpit to tell persons not to start the APU.

(n) Put a warning notice in the cockpit to tell persons not to start the ENG1, 2.

(o) Battery disconnection :

- For Job Set-up, refer to Removal of the Batteries (Refer to AMM 24-31-11,

Page Block 401).

- Turn the knurled nut a quarter turn.

- Disconnect the connectors.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 40

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

- Put blanking caps on the disconnected electrical connectors.

**CONF 003

(1) Subtask 742003-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 23-12-13, Page Block 401

23-71-12, Page Block 401

24-00-00, Page Block 301

24-31-11, Page Block 401

25-13-11, Page Block 401

25-13-12, Page Block 401

26-12-20, Page Block 401

26-13-20, Page Block 401

28-42-41, Page Block 401

34-25-25, Page Block 401

52-10-00

52-10-00, Page Block 001

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page

Block 301).

(c) Put access platform(s) in position

(d) Open the passenger/crew door(s) (Refer to AMM 52-10-00)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 41

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(e) Remove the right side panels, the ceiling panels, as necessary, to get access to the

work area (Refer to AMM 25-13-11, Page Block 401)(Refer to AMM 25-13-12, Page

Block 401).

(f) On overhead panel 20VU, disconnect and remove for access if installed:

1 The Small VUs 45VU, 76VU, 424VU, 425VU, 430VU, 431VU, 433VU, 435VU,

438VU

2 The Fuel Quantity indicator 6QT (Refer to AMM 28-42-41, Page Block 401)

3 The Mode Selector Units 310FP1, 310FP2 and 310FP3 (Refer to AMM

34-25-25, Page Block 401)

4 the Cockpit Voice Recorder Unit 1RK (Refer to AMM 23-71-12, Page Block

401)

5 The APU Fire Control Module 20WG (Refer to AMM 26-13-20, Page Block

401)

6 The Engine Fire Control modules 39WD and 40WD (Refer to AMM 26-12-20,

Page Block 401)

7 The VHF3 Control Unit 2RC3 (Refer to AMM 23-12-13, Page Block 401)

(g) Make sure that the external connector(s) is (are) not connected to the aircraft

receptacle(s) EXT PW.

(h) Make sure that there is (are) warning notice(s) on external power receptacle to tell

persons not to connect an external power source.

(i) Make sure that the EMER EXIT LT pushbutton switch on 436VU is on DISARM

position.

(j) In the cockpit, on the overhead panel 424VU release BAT pushbutton switches.

(k) Put a warning notice on panel 424VU to tell persons not to operate the batteries.

(l) Put a warning notice on the refuel/defuel panel 110VU to tell persons not to operate

the NORMAL BATTERY switch.

(m) Put a warning notice in the cockpit to tell persons not to start the APU.

(n) Put a warning notice in the cockpit to tell persons not to start the ENG1, 2.

(o) Battery disconnection :

- For Job Set-up, refer to Removal of the Batteries (Refer to AMM 24-31-11,

Page Block 401).

- Turn the knurled nut a quarter turn.

- Disconnect the connectors.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 42

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

- Put blanking caps on the disconnected electrical connectors.

**CONF 006

(1) Subtask 742003-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 23-12-13, Page Block 401

23-71-12, Page Block 401

24-00-00, Page Block 301

24-31-11, Page Block 401

25-13-11, Page Block 401

25-13-12, Page Block 401

26-12-20, Page Block 401

26-13-20, Page Block 401

28-42-41, Page Block 401

34-25-25, Page Block 401

52-10-00

52-10-00, Page Block 001

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page

Block 301).

(c) Put access platform(s) in position

(d) Open the passenger/crew door(s) (Refer to AMM 52-10-00)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 43

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(e) Remove the right side panels, the ceiling panels, as necessary, to get access to the

work area (Refer to AMM 25-13-11, Page Block 401)(Refer to AMM 25-13-12, Page

Block 401).

(f) On overhead panel 20VU, disconnect and remove for access if installed:

1 The Small VUs 45VU, 76VU, 424VU, 425VU, 430VU, 431VU, 433VU, 435VU,

438VU

2 The Fuel Quantity indicator 6QT (Refer to AMM 28-42-41, Page Block 401)

3 The Mode Selector Units 310FP1, 310FP2 and 310FP3 (Refer to AMM

34-25-25, Page Block 401)

4 the Cockpit Voice Recorder Unit 1RK (Refer to AMM 23-71-12, Page Block

401)

5 The APU Fire Control Module 20WG (Refer to AMM 26-13-20, Page Block

401)

6 The Engine Fire Control modules 39WD and 40WD (Refer to AMM 26-12-20,

Page Block 401)

7 The VHF3 Control Unit 2RC3 (Refer to AMM 23-12-13, Page Block 401)

(g) Make sure that the external connector(s) is (are) not connected to the aircraft

receptacle(s) EXT PW.

(h) Make sure that there is (are) warning notice(s) on external power receptacle to tell

persons not to connect an external power source.

(i) Make sure that the EMER EXIT LT pushbutton switch on 436VU is on DISARM

position.

(j) In the cockpit, on the overhead panel 424VU release BAT pushbutton switches.

(k) Put a warning notice on panel 424VU to tell persons not to operate the batteries.

(l) Put a warning notice on the refuel/defuel panel 110VU to tell persons not to operate

the NORMAL BATTERY switch.

(m) Put a warning notice in the cockpit to tell persons not to start the APU.

(n) Put a warning notice in the cockpit to tell persons not to start the ENG1, 2.

(o) Battery disconnection :

- For Job Set-up, refer to Removal of the Batteries (Refer to AMM 24-31-11,

Page Block 401).

- Turn the knurled nut a quarter turn.

- Disconnect the connectors.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 44

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

- Put blanking caps on the disconnected electrical connectors.

**CONF 007

(1) Subtask 742003-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 23-12-13, Page Block 401

23-71-12, Page Block 401

24-00-00, Page Block 301

24-31-11, Page Block 401

25-13-11, Page Block 401

25-13-12, Page Block 401

26-12-20, Page Block 401

26-13-20, Page Block 401

28-42-41, Page Block 401

34-25-25, Page Block 401

52-10-00

52-10-00, Page Block 001

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page

Block 301).

(c) Put access platform(s) in position

(d) Open the passenger/crew door(s) (Refer to AMM 52-10-00)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 45

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(e) Remove the right side panels, the ceiling panels, as necessary, to get access to the

work area (Refer to AMM 25-13-11, Page Block 401)(Refer to AMM 25-13-12, Page

Block 401).

(f) On overhead panel 20VU, disconnect and remove for access if installed:

1 The Small VUs 45VU, 76VU, 424VU, 425VU, 430VU, 431VU, 433VU, 435VU,

438VU

2 The Fuel Quantity indicator 6QT (Refer to AMM 28-42-41, Page Block 401)

3 The Mode Selector Units 310FP1, 310FP2 and 310FP3 (Refer to AMM

34-25-25, Page Block 401)

4 the Cockpit Voice Recorder Unit 1RK (Refer to AMM 23-71-12, Page Block

401)

5 The APU Fire Control Module 20WG (Refer to AMM 26-13-20, Page Block

401)

6 The Engine Fire Control modules 39WD and 40WD (Refer to AMM 26-12-20,

Page Block 401)

7 The VHF3 Control Unit 2RC3 (Refer to AMM 23-12-13, Page Block 401)

(g) Make sure that the external connector(s) is (are) not connected to the aircraft

receptacle(s) EXT PW.

(h) Make sure that there is (are) warning notice(s) on external power receptacle to tell

persons not to connect an external power source.

(i) Make sure that the EMER EXIT LT pushbutton switch on 436VU is on DISARM

position.

(j) In the cockpit, on the overhead panel 424VU release BAT pushbutton switches.

(k) Put a warning notice on panel 424VU to tell persons not to operate the batteries.

(l) Put a warning notice on the refuel/defuel panel 110VU to tell persons not to operate

the NORMAL BATTERY switch.

(m) Put a warning notice in the cockpit to tell persons not to start the APU.

(n) Put a warning notice in the cockpit to tell persons not to start the ENG1, 2.

(o) Battery disconnection :

- For Job Set-up, refer to Removal of the Batteries (Refer to AMM 24-31-11,

Page Block 401).

- Turn the knurled nut a quarter turn.

- Disconnect the connectors.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 46

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

- Put blanking caps on the disconnected electrical connectors.

**CONF 008

(1) Subtask 742003-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 23-12-13, Page Block 401

23-71-12, Page Block 401

24-00-00, Page Block 301

24-31-11, Page Block 401

25-13-11, Page Block 401

25-13-12, Page Block 401

26-12-20, Page Block 401

26-13-20, Page Block 401

28-42-41, Page Block 401

34-25-25, Page Block 401

52-10-00

52-10-00, Page Block 001

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page

Block 301).

(c) Put access platform(s) in position

(d) Open the passenger/crew door(s) (Refer to AMM 52-10-00)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 47

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(e) Remove the right side panels, the ceiling panels, as necessary, to get access to the

work area (Refer to AMM 25-13-11, Page Block 401)(Refer to AMM 25-13-12, Page

Block 401).

(f) On overhead panel 20VU, disconnect and remove for access if installed:

1 The Small VUs 45VU, 76VU, 424VU, 425VU, 430VU, 431VU, 433VU, 435VU,

438VU

2 The Fuel Quantity indicator 6QT (Refer to AMM 28-42-41, Page Block 401)

3 The Mode Selector Units 310FP1, 310FP2 and 310FP3 (Refer to AMM

34-25-25, Page Block 401)

4 the Cockpit Voice Recorder Unit 1RK (Refer to AMM 23-71-12, Page Block

401)

5 The APU Fire Control Module 20WG (Refer to AMM 26-13-20, Page Block

401)

6 The Engine Fire Control modules 39WD and 40WD (Refer to AMM 26-12-20,

Page Block 401)

7 The VHF3 Control Unit 2RC3 (Refer to AMM 23-12-13, Page Block 401)

(g) Make sure that the external connector(s) is (are) not connected to the aircraft

receptacle(s) EXT PW.

(h) Make sure that there is (are) warning notice(s) on external power receptacle to tell

persons not to connect an external power source.

(i) Make sure that the EMER EXIT LT pushbutton switch on 436VU is on DISARM

position.

(j) In the cockpit, on the overhead panel 424VU release BAT pushbutton switches.

(k) Put a warning notice on panel 424VU to tell persons not to operate the batteries.

(l) Put a warning notice on the refuel/defuel panel 110VU to tell persons not to operate

the NORMAL BATTERY switch.

(m) Put a warning notice in the cockpit to tell persons not to start the APU.

(n) Put a warning notice in the cockpit to tell persons not to start the ENG1, 2.

(o) Battery disconnection :

- For Job Set-up, refer to Removal of the Batteries (Refer to AMM 24-31-11,

Page Block 401).

- Turn the knurled nut a quarter turn.

- Disconnect the connectors.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 48

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

- Put blanking caps on the disconnected electrical connectors.

**CONF 009

(1) Subtask 742003-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 23-12-13, Page Block 401

23-71-12, Page Block 401

24-00-00, Page Block 301

24-31-11, Page Block 401

25-13-11, Page Block 401

25-13-12, Page Block 401

26-12-20, Page Block 401

26-13-20, Page Block 401

28-42-41, Page Block 401

34-25-25, Page Block 401

52-10-00

52-10-00, Page Block 001

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page

Block 301).

(c) Put access platform(s) in position

(d) Open the passenger/crew door(s) (Refer to AMM 52-10-00)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 49

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(e) Remove the right side panels, the ceiling panels, as necessary, to get access to the

work area (Refer to AMM 25-13-11, Page Block 401)(Refer to AMM 25-13-12, Page

Block 401).

(f) On overhead panel 20VU, disconnect and remove for access if installed:

1 The Small VUs 45VU, 76VU, 424VU, 425VU, 430VU, 431VU, 433VU, 435VU,

438VU

2 The Fuel Quantity indicator 6QT (Refer to AMM 28-42-41, Page Block 401)

3 The Mode Selector Units 310FP1, 310FP2 and 310FP3 (Refer to AMM

34-25-25, Page Block 401)

4 the Cockpit Voice Recorder Unit 1RK (Refer to AMM 23-71-12, Page Block

401)

5 The APU Fire Control Module 20WG (Refer to AMM 26-13-20, Page Block

401)

6 The Engine Fire Control modules 39WD and 40WD (Refer to AMM 26-12-20,

Page Block 401)

7 The VHF3 Control Unit 2RC3 (Refer to AMM 23-12-13, Page Block 401)

(g) Make sure that the external connector(s) is (are) not connected to the aircraft

receptacle(s) EXT PW.

(h) Make sure that there is (are) warning notice(s) on external power receptacle to tell

persons not to connect an external power source.

(i) Make sure that the EMER EXIT LT pushbutton switch on 436VU is on DISARM

position.

(j) In the cockpit, on the overhead panel 424VU release BAT pushbutton switches.

(k) Put a warning notice on panel 424VU to tell persons not to operate the batteries.

(l) Put a warning notice on the refuel/defuel panel 110VU to tell persons not to operate

the NORMAL BATTERY switch.

(m) Put a warning notice in the cockpit to tell persons not to start the APU.

(n) Put a warning notice in the cockpit to tell persons not to start the ENG1, 2.

(o) Battery disconnection :

- For Job Set-up, refer to Removal of the Batteries (Refer to AMM 24-31-11,

Page Block 401).

- Turn the knurled nut a quarter turn.

- Disconnect the connectors.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 50

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

- Put blanking caps on the disconnected electrical connectors.

**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 742003-831-001-001 - Modify the Circuit Breaker panel 133VU

Work Zones and Access Panels

Zone Access/Work location

210

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A11321141C00 2 PLACARD

A9100095041095 PLCD SET

EN2995-004A03AA 2 CB

Supplementary kit 742003A01S05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A11321141C00 PLACARD

References

Aircraft Maintenance Manual (AMM) 24-50-20

Fig. A-FBBAB

Modification equipment in 133VU

Sheet 01

Fig. A-FBCAB

Modification Placard in 133VU

Sheet 01

(a) Inside panel 133VU, at position S69 and S74, install (Refer to AMM 24-50-20) :

FIN 13JH

1 Cb-Circuit Breaker EN2995-004A03AA

FIN 14JH

1 Cb-Circuit Breaker EN2995-004A03AA

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 51

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(b) Inside panel 133VU, at position S69 and S74, install two new self-sticking labels

supplied in Fig. A-FBBAB Sheet 01:

Placard Set A9100095041095

(c) On panel 133VU, in front of the two new Circuit Breakers, on the existing placard,

with a cutter, make two cut-out at position S69 and S74 so that you can insert the

two new self-sticking labels supplied in Fig. A-FBCAB Sheet 01:

2 Placard A11321141C00

For aircraft using Kit A01R03

2 Placard A11321141C00

supplied in Supplementary kit A01S05

NOTE: Adjust the size of the labels at assembly.

(2) Subtask 742003-831-002-001 - Modify the wiring in Circuit Breaker panel 133VU

Work Zones and Access Panels

Zone Access/Work location

210

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

NSA935401-03 20 TIE

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

References

Fig. A-FCAAA

Modification wiring in 133VU

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FDAAA

Hook-up Chart 133VU

Sheet 01

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 52

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(a) Remove the wires as shown on the wiring diagram Fig. A-FCAAA Sheet 01, Fig. AFCAAA Sheet 02, Fig. A-FCAAA Sheet 03, Fig. A-FCAAA Sheet 04 and as given in

the Hook-up Chart lines :

- 1 thru 6(Refer to Fig. A-FDAAA Sheet 01).

(b) Install the wires as shown on the wiring diagram Fig. A-FCAAA Sheet 01, Fig. AFCAAA Sheet 02, Fig. A-FCAAA Sheet 03, Fig. A-FCAAA Sheet 04 and as given in

the Hook-up Chart lines :

- 10 thru 21 (Refer to Fig. A-FDAAA Sheet 01)

supplied in :

Bundle A9000095320695

For aircraft using Kit A01R06, use

Bundle A9000095320695

supplied in Supplementary Kit A01S06

(c) Attach the wires with :

20 Tie-Cable NSA935401-03

(3) Subtask 742003-831-008-001 - Modify the equipment in the Relay Box 105VU on

bench

Work Zones and Access Panels

Zone Access/Work location

122

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 A9251133320000 1 PLATE

10 NAS1100-04-7 8 SCREW

11 MS21042-04 8 NUT

12 NAS1149FN416P 8 WASHER

A9100095041095 PLCD SET

ABS1416A120CJ 2 RELAY

E0247A0 2 BASE

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 53

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

E0666D28A0 2 RELAY

NSA932844CJ 2 SOCKET

NSA937901E0 1 LABEL

NSA937901E1 5 LABEL

NSA937901E7 1 LABEL

NSA937901E8 1 LABEL

NSA937901FM 1 MODULE

NSA937901M20-08 2 MODULE

NSA937901MA2004 2 MODULE

Supplementary kit 742003A01S01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NSA932844CJ 2 SOCKET

References

Aircraft Wiring List (AWL)

Fig. A-FBAAA

Modification equipment in 105VU

Sheet 01

(a) From the Relay Box 105VU, disconnect the bonding strip, remove the screws, the

clamps and the box front cover.

NOTE: Disconnect the connectors and remove the Relay Box 105VU to get

access to the inside of the box.

Put blanking caps on the disconnected electrical connectors.

Reconnect and install all the removed components after

modification.

(b) On bench, install on plate Item 9 :

FIN 17JH

1 Relay E0666D28A0

FIN 18JH

1 Relay E0666D28A0

with

FIN 17JHA

1 Base E0247A0

FIN 18JHA

1 Base E0247A0

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 54

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(c) On bench, install (Refer to Fig. A-FBAAA Sheet 01) :

1 Plate A9251133320000 Item 9

with

4 Screw NAS1100-04-7 Item 10

4 Washer NAS1149FN416P Item 12

4 Nut MS21042-04 Item 11

(d) On bench, install (Refer to Fig. A-FBAAA Sheet 01) :

FIN 15JH

1 Relay ABS1416A120CJ

FIN 15JHA

1 Socket-Relay NSA932844CJ

For aircraft using Kit A01R01

FIN 15JHA

1 Socket-Relay NSA932844CJ

supplied in Supplementary kit A01S01

FIN 16JH

1 Relay ABS1416A120CJ

FIN 16JHA

1 Socket-Relay NSA932844CJ

For aircraft using Kit A01R01

FIN 16JHA

1 Socket-Relay NSA932844CJ

supplied in Supplementary kit A01S01

with

4 Screw NAS1100-04-7 Item 10

4 Washer NAS1149FN416P Item 12

4 Nut MS21042-04 Item 11

NOTE: For aircraft using Kit 742003A01R01 the socket relay P/N

NSA932844CJ is suplied in suplemental kit 742003A01S01

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 55

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(e) Close to new relays, affix placards supplied in :

Placard Set A9100095041095

(f) On the mounting rail 192VT, on modules position 10 and 11, disconnect wires as

per Aircraft Wiring List (AWL)

(g) On the mounting rail 192VT, remove from position 10 and 11 :

2 modules

(h) On the mounting rail 192VT, at position 10 and 11, install :

2 Module NSA937901MA2004

with

3 Label Identification NSA937901E1

1 Label Identification NSA937901E0

(i) On the mounting rail 192VT, on modules 10 and 11, reconnect wires as per Aircraft

Wiring List (AWL) only on contacts A, B ,F, G if there are existing wires.

(j) On the mounting rail 192VT, remove and retain from position 16 the end-module.

(k) On the mounting rail 192VT, at position 16, install :

1 Module-False NSA937901FM

(l) On the mounting rail 192VT, at position 17 and 18, install :

2 Module NSA937901M20-08

with

2 Label Identification NSA937901E1

1 Label Identification NSA937901E7

1 Label Identification NSA937901E8

(m) On the mounting rail 192VT, at position 19, install the end-module retained at

removal.

(4) Subtask 742003-831-007-001 - Modify the wiring in the Relay Box 105VU on bench

Manpower Resources

Manhours 8.00

Minimum number of person 1

Subtask elapsed time 8.00

Skills ELECTRICAL

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 56

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

NSA935401-05 100 TIE

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Pure Mineral Vaseline Or

Petro- Latum

04-012 As required

Electrical Bond Varnish 07-001B As required

References

Aircraft Maintenance Manual (AMM) 20-28-11

Fig. A-FCBAA

Modification wiring in 105VU

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FDBAA

Hook-up Chart 105VU

Sheet 01

Sheet 02

Sheet 03

(a) Remove the wires as shown on the wiring diagram Fig. A-FCBAA Sheet 01, Fig. AFCBAA Sheet 02, Fig. A-FCBAA Sheet 03, Fig. A-FCBAA Sheet 04 and as given in

the Hook-up Chart lines :

- 1 thru 14 (Refer to Fig. A-FDBAA Sheet 01)

(b) Install the wires as shown on the wiring diagram Fig. A-FCBAA Sheet 01, Fig. AFCBAA Sheet 02, Fig. A-FCBAA Sheet 03, Fig. A-FCBAA Sheet 04 and as given in

the Hook-up Chart lines :

- 1 thru 25 (Refer to Fig. A-FDBAA Sheet 02)

- 1 thru 13 (Refer to Fig. A-FDBAA Sheet 03)

supplied in :

Bundle A9000095320695

For aircraft using Kit A01R06, use

Bundle A9000095320695

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 57

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

supplied in Supplementary Kit A01S06

(c) Attach the wires with :

100 Tie-Cable NSA935401-05

(d) On the relay box 105VU, do the electrical bonding (Refer to AMM 20-28-11) with :

Pure Mineral

Vaseline Or PetroLatum

04-012 As required

Electrical Bond

Varnish

07-001B As required

(e) Connect the bonding strip, install the screws, the clamps and the front box.

Reconnect and install the Relay Box 105VU

(5) Subtask 742003-831-003-001 - Modify the Eng Start/APU/Wiper Panel 429VU

Work Zones and Access Panels

Zone Access/Work location

210

Manpower Resources

Manhours 10.00

Minimum number of person 1

Subtask elapsed time 10.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 A9251063000000 1 SUPPLATE

2 EN3646A02255AZ 1 CONNECTR

3 NSA937901RB0120 1 RAIL

4 NAS1100-06-7 3 SCREW

5 MS35333-37 3 WASHER

6 NAS1100-08-7 2 SCREW

7 NAS1149FN816P 2 WASHER

12 NAS1149FN416P 6 WASHER

13 NAS1100-04-6 6 SCREW

14 MS21042L04 6 NUT

A9000095320695 BUNDLE

EN3646A62255BZ 1 CONNECTR

NSA935401-03 20 TIE

NSA937901E9 1 LABEL

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 58

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NSA937901MA2011 1 MODULE

NSA938003-22 1 BACKSHLL

NSA938150-02-22 1 BACKSHLL

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

References

Aircraft Wiring List (AWL)

Fig. A-FBDAA

Modification equipment in 429VU

Sheet 01

Fig. A-FCCAA

Modification wiring in 429VU

Sheet 01

Sheet 02

Fig. A-FDCAA

Hook-up Chart 429VU

Sheet 01

(a) On overhead panel 20VU, remove the panel 429VU fixed with four fasteners

Disconnect the three connectors FIN 1470VC-A, 1471VC-A, 1472VC-A

(b) On bench, separate the three connectors from plate Item (1) (Refer to Fig. AFBDAA Sheet 01)

Discard associated hardware.

Separate all the modules and end-modules from the mounting rail 1347VT without

disconnection.

Separate the mounting rail 1347VT from plate Item (1)

Discard associated hardware.

(c) On bench, remove (Refer to Fig. A-FBDAA Sheet 01) :

1 Plate Item (1)

Discard associated hardware.

(d) On bench, install (Refer to Fig. A-FBDAA Sheet 01) :

1 Supplate-Rear Assy A9251063000000 Item 1

with

3 Screw NAS1100-06-7 Item 4

3 Washer-Lock MS35333-37 Item 5

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 59

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(e) From connector FIN 1471VC, disconnect all the wires as per Aircraft Wiring List

(AWL)

(f) Remove :

1 Connector Item (2)

Discard associated hardware.

(g) On plate Item 1, install :

FIN 1471VC

1 Connector EN3646A02255AZ Item 2

with

2 Screw NAS1100-04-6 Item 13

2 Nut MS21042L04 Item 14

2 Washer NAS1149FN416P Item 12

(h) Behind connector 1471VC, install :

1 Backshell-Connector NSA938003-22

(i) On connector FIN 1471VC, reconnect all the wires as per Aircraft Wiring List (AWL)

(j) On plate Item 1, install the two others connectors FIN 1470VC and 1472VC with :

4 Screw NAS1100-04-6 Item 13

4 Washer NAS1149FN416P Item 12

4 Nut MS21042L04 Item 14

(k) On plate Item 1, install :

FIN 1347VT

1 Rail NSA937901RB0120 Item 3

with

2 Screw NAS1100-08-7 Item 6

2 Washer NAS1149FN816P Item 7

(l) On the mounting rail 1347VT, reinstall all the modules and install in position 9 :

FIN 1347VT9

1 Module NSA937901MA2011

with

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 60

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

1 Label Identification NSA937901E9

(m) On the mounting rail 1347VT, reinstall the two end modules.

(n) Remove the wires as shown on the wiring diagram Fig. A-FCCAA Sheet 01Fig. AFCCAA Sheet 02 and as given in the Hook-up Chart lines :

- 1 thru 4 (Refer to Fig. A-FDCAA Sheet 01)

(o) Install the wires as shown on the wiring diagram Fig. A-FCCAA Sheet 01Fig. AFCCAA Sheet 02 and as given in the Hook-up Chart lines :

- 8 thru 19 (Refer to Fig. A-FDCAA Sheet 01)

supplied in :

Bundle A9000095320695

For aircraft using Kit A01R06, use

Bundle A9000095320695

supplied in Supplementary Kit A01S06

(p) Attach the wires with :

20 Tie-Cable NSA935401-03

(q) On aircraft, disconnect as per Aircraft Wiring List (AWL), all the wires connected to

connector FIN 1471VC-A.

(r) Replace the connector FIN 1471VC-A and back-shell by :

FIN 1471VCA

1 Connector-Plug EN3646A62255BZ

FIN 1471VCA1

1 Backshell-Connector NSA938150-02-22

(s) Reconnect as per Aircraft Wiring List (AWL), all the wires disconnected to

connector FIN 1471VC-A.

(6) Subtask 742003-831-004-001 - Modify the Relay Box 104VU on bench

Work Zones and Access Panels

Zone Access/Work location

120

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 61

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

NSA935401-03 20 TIE

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Pure Mineral Vaseline Or

Petro- Latum

04-012 As required

Electrical Bond Varnish 07-001B As required

References

Aircraft Maintenance Manual (AMM) 20-28-11

Fig. A-FCDAA

Modification wiring in 104VU

Sheet 01

Fig. A-FDDAA

Hook-up Chart 104VU

Sheet 01

(a) From the Relay Box 104VU, disconnect the bonding strip, remove the screws, the

clamps and the box front cover

NOTE: Disconnect the connectors and remove the Relay Box 104VU to get

access to the inside of the box.

Put blanking caps on the disconnected electrical connectors.

Reconnect and install all the removed components after

modification.

(b) Install the wires as shown on the wiring diagram Fig. A-FCDAA Sheet 01 and as

given in the Hook-up Chart lines :

- 1 thru 2 (Refer to Fig. A-FDDAA Sheet 01)

supplied in :

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 62

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Bundle A9000095320695

For aircraft using Kit A01R06, use

Bundle A9000095320695

supplied in Supplementary Kit A01S06

(c) Attach the wires with :

20 Tie-Cable NSA935401-03

(d) On Relay Box 104VU, do the electrical bonding (Refer to AMM 20-28-11) with :

Pure Mineral

Vaseline Or PetroLatum

04-012 As required

Electrical Bond

Varnish

07-001B As required

(e) Connect the bonding strip, install the screws, the clamps and the front box.

Reconnect and install the Relay Box 104VU

(7) Subtask 742003-831-005-001 - Modify the Electronics Rack 80VU

Work Zones and Access Panels

Zone Access/Work location

121

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

NSA935401-03 20 TIE

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 63

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

References

Fig. A-FCEAA

Modification wiring in 80VU

Sheet 01

Fig. A-FDEAA

Hook-up Chart 80VU

Sheet 01

(a) Install the wires as shown on the wiring diagram Fig. A-FCEAA Sheet 01 and as

given in the Hook-up Chart lines :

- 1 thru 2 (Refer to Fig. A-FDEAA Sheet 01)

supplied in :

Bundle A9000095320695

For aircraft using Kit A01R06, use

Bundle A9000095320695

supplied in Supplementary Kit A01S06

(b) Attach the wires with :

20 Tie-Cable NSA935401-03

(8) Subtask 742003-831-006-001 - Modify the wiring in Zones

Work Zones and Access Panels

Zone Access/Work location

From 120

To 210

Manpower Resources

Manhours 8.00

Minimum number of person 2

Subtask elapsed time 4.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

EN3155-018M1616 1 PIN

EN3155-019F1616 1 CONTACT

NSA935401-05 100 TIE

NSA935401-13 100 TIE

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 64

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

EN3155-018M1616 PIN

EN3155-019F1616 1 CONTACT

References

Fig. A-FCFAA

Modification wiring in Zones

Sheet 01

Sheet 02

Fig. A-FDFAA

Hook-up Chart Zones

Sheet 01

Fig. A-FBEAA

Routing

Sheet 01

(a) Install the wires as shown on the wiring diagram Fig. A-FCFAA Sheet 01Fig. AFCFAA Sheet 02 and as given in the Hook-up Chart lines :

- 1 thru 9 (Refer to Fig. A-FDFAA Sheet 01)

supplied in :

Bundle A9000095320695

with:

1 Contact-Socket EN3155-019F1616

1 Pin-Contact EN3155-018M1616

For aircraft using Kit A01R06, use

Bundle A9000095320695

supplied in Supplementary Kit A01S06

For aircraft using Kit A01R01 or Kit A01R03, use:

1 Pin-Contact EN3155-018M1616

1 Contact-Socket EN3155-019F1616

supplied in Supplementary Kit A01S05

(b) Attach the wires with :

100 Tie-Cable NSA935401-05

100 Tie-Cable NSA935401-13

(c) On aircraft, reconnect the three connectors FIN 1471VC, 1470VC, 1472VC.

(d) On aircraft, on overhead panel 20VU, reinstall the panel 429VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 65

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 002

(1) Subtask 742003-831-001-001 - Modify the Circuit Breaker panel 133VU

Work Zones and Access Panels

Zone Access/Work location

210

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A11321141C00 2 PLACARD

A9100095041095 PLCD SET

EN2995-004A03AA 2 CB

Supplementary kit 742003A01S05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A11321141C00 PLACARD

References

Aircraft Maintenance Manual (AMM) 24-50-20

Fig. A-FBBAB

Modification equipment in 133VU

Sheet 01

Fig. A-FBCAB

Modification Placard in 133VU

Sheet 01

(a) Inside panel 133VU, at position S69 and S74, install (Refer to AMM 24-50-20) :

FIN 13JH

1 Cb-Circuit Breaker EN2995-004A03AA

FIN 14JH

1 Cb-Circuit Breaker EN2995-004A03AA

(b) Inside panel 133VU, at position S69 and S74, install two new self-sticking labels

supplied in Fig. A-FBBAB Sheet 01:

Placard Set A9100095041095

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 66

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(c) On panel 133VU, in front of the two new Circuit Breakers, on the existing placard,

with a cutter, make two cut-out at position S69 and S74 so that you can insert the

two new self-sticking labels supplied in Fig. A-FBCAB Sheet 01:

2 Placard A11321141C00

For aircraft using Kit A01R03

2 Placard A11321141C00

supplied in Supplementary kit A01S05

NOTE: Adjust the size of the labels at assembly.

(2) Subtask 742003-831-002-001 - Modify the wiring in Circuit Breaker panel 133VU

Work Zones and Access Panels

Zone Access/Work location

210

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

NSA935401-03 20 TIE

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

References

Fig. A-FCAAA

Modification wiring in 133VU

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FDAAA

Hook-up Chart 133VU

Sheet 01

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 67

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(a) Remove the wires as shown on the wiring diagram Fig. A-FCAAA Sheet 01, Fig. AFCAAA Sheet 02, Fig. A-FCAAA Sheet 03, Fig. A-FCAAA Sheet 04 and as given in

the Hook-up Chart lines :

- 1 thru 6(Refer to Fig. A-FDAAA Sheet 01).

(b) Install the wires as shown on the wiring diagram Fig. A-FCAAA Sheet 01, Fig. AFCAAA Sheet 02, Fig. A-FCAAA Sheet 03, Fig. A-FCAAA Sheet 04 and as given in

the Hook-up Chart lines :

- 10 thru 21 (Refer to Fig. A-FDAAA Sheet 01)

supplied in :

Bundle A9000095320695

For aircraft using Kit A01R06, use

Bundle A9000095320695

supplied in Supplementary Kit A01S06

(c) Attach the wires with :

20 Tie-Cable NSA935401-03

(3) Subtask 742003-831-008-003 - Modify the equipment in the Relay Box 105VU on

bench

Work Zones and Access Panels

Zone Access/Work location

122

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 A9251133320000 1 PLATE

10 NAS1100-04-7 8 SCREW

11 MS21042-04 8 NUT

12 NAS1149FN416P 8 WASHER

A9100095041095 PLCD SET

ABS1416A120CJ 2 RELAY

E0247A0 2 BASE

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 68

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

E0666D28A0 2 RELAY

NSA932844CJ 2 SOCKET

NSA937901E0 1 LABEL

NSA937901E1 5 LABEL

NSA937901E7 1 LABEL

NSA937901E8 1 LABEL

NSA937901FM 1 MODULE

NSA937901M20-08 2 MODULE

NSA937901MA2004 2 MODULE

Supplementary kit 742003A01S01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NSA932844CJ 2 SOCKET

References

Aircraft Wiring List (AWL)

Fig. A-FBAAC

Modification equipment in 105VU

Sheet 01

(a) From the Relay Box 105VU, disconnect the bonding strip, remove the screws, the

clamps and the box front cover

NOTE: Disconnect the connectors and remove the Relay Box 105VU to get

access to the inside of the box.

Put blanking caps on the disconnected electrical connectors.

Reconnect and install all the removed components after

modification.

(b) On bench, install on plate Item 9 :

FIN 17JH

1 Relay E0666D28A0

FIN 18JH

1 Relay E0666D28A0

with

FIN 17JHA

1 Base E0247A0

FIN 18JHA

1 Base E0247A0

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 69

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(c) On bench, install (Refer to Fig. A-FBAAC Sheet 01) :

1 Plate A9251133320000 Item 9

with

4 Screw NAS1100-04-7 Item 10

4 Washer NAS1149FN416P Item 12

4 Nut MS21042-04 Item 11

(d) On bench, install (Refer to Fig. A-FBAAC Sheet 01) :

FIN 15JH

1 Relay ABS1416A120CJ

FIN 15JHA

1 Socket-Relay NSA932844CJ

For aircraft using Kit A01R01

FIN 15JHA

1 Socket-Relay NSA932844CJ

supplied in Supplementary kit A01S01

FIN 16JH

1 Relay ABS1416A120CJ

FIN 16JHA

1 Socket-Relay NSA932844CJ

For aircraft using Kit A01R01

FIN 16JHA

1 Socket-Relay NSA932844CJ

supplied in Supplementary kit A01S01

with

4 Screw NAS1100-04-7 Item 10

4 Washer NAS1149FN416P Item 12

4 Nut MS21042-04 Item 11

NOTE: For aircraft using Kit 742003A01R01 the socket relay P/N

NSA932844CJ is suplied in suplemental kit 742003A01S01

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 70

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(e) Close to new relays, affix placards supplied in :

Placard Set A9100095041095

(f) On the mounting rail 192VT, on modules position 10 and 11, disconnect wires as

per Aircraft Wiring List (AWL)

(g) On the mounting rail 192VT, remove from position 10 and 11 :

2 modules

(h) On the mounting rail 192VT, at position 10 and 11, install :

2 Module NSA937901MA2004

with

3 Label Identification NSA937901E1

1 Label Identification NSA937901E0

(i) On the mounting rail 192VT, on modules 10 and 11, reconnect wires as per Aircraft

Wiring List (AWL) only on contacts A, B ,F, G if there are existing wires.

(j) On the mounting rail 192VT, remove and retain from position 16 the end-module.

(k) On the mounting rail 192VT, at position 16, install :

1 Module-False NSA937901FM

(l) On the mounting rail 192VT, at position 17 and 18, install :

2 Module NSA937901M20-08

with

2 Label Identification NSA937901E1

1 Label Identification NSA937901E7

1 Label Identification NSA937901E8

(m) On the mounting rail 192VT, at position 19, install the end-module retained at

removal.

(4) Subtask 742003-831-007-001 - Modify the wiring in the Relay Box 105VU on bench

Manpower Resources

Manhours 8.00

Minimum number of person 1

Subtask elapsed time 8.00

Skills ELECTRICAL

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 71

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

NSA935401-05 100 TIE

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Pure Mineral Vaseline Or

Petro- Latum

04-012 As required

Electrical Bond Varnish 07-001B As required

References

Aircraft Maintenance Manual (AMM) 20-28-11

Fig. A-FCBAA

Modification wiring in 105VU

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FDBAA

Hook-up Chart 105VU

Sheet 01

Sheet 02

Sheet 03

(a) Remove the wires as shown on the wiring diagram Fig. A-FCBAA Sheet 01, Fig. AFCBAA Sheet 02, Fig. A-FCBAA Sheet 03, Fig. A-FCBAA Sheet 04 and as given in

the Hook-up Chart lines :

- 1 thru 14 (Refer to Fig. A-FDBAA Sheet 01)

(b) Install the wires as shown on the wiring diagram Fig. A-FCBAA Sheet 01, Fig. AFCBAA Sheet 02, Fig. A-FCBAA Sheet 03, Fig. A-FCBAA Sheet 04 and as given in

the Hook-up Chart lines :

- 1 thru 25 (Refer to Fig. A-FDBAA Sheet 02)

- 1 thru 13 (Refer to Fig. A-FDBAA Sheet 03)

supplied in :

Bundle A9000095320695

For aircraft using Kit A01R06, use

Bundle A9000095320695

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 72

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

supplied in Supplementary Kit A01S06

(c) Attach the wires with :

100 Tie-Cable NSA935401-05

(d) On the relay box 105VU, do the electrical bonding (Refer to AMM 20-28-11) with :

Pure Mineral

Vaseline Or PetroLatum

04-012 As required

Electrical Bond

Varnish

07-001B As required

(e) Connect the bonding strip, install the screws, the clamps and the front box.

Reconnect and install the Relay Box 105VU

(5) Subtask 742003-831-003-001 - Modify the Eng Start/APU/Wiper Panel 429VU

Work Zones and Access Panels

Zone Access/Work location

210

Manpower Resources

Manhours 10.00

Minimum number of person 1

Subtask elapsed time 10.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 A9251063000000 1 SUPPLATE

2 EN3646A02255AZ 1 CONNECTR

3 NSA937901RB0120 1 RAIL

4 NAS1100-06-7 3 SCREW

5 MS35333-37 3 WASHER

6 NAS1100-08-7 2 SCREW

7 NAS1149FN816P 2 WASHER

12 NAS1149FN416P 6 WASHER

13 NAS1100-04-6 6 SCREW

14 MS21042L04 6 NUT

A9000095320695 BUNDLE

EN3646A62255BZ 1 CONNECTR

NSA935401-03 20 TIE

NSA937901E9 1 LABEL

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 73

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NSA937901MA2011 1 MODULE

NSA938003-22 1 BACKSHLL

NSA938150-02-22 1 BACKSHLL

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

References

Aircraft Wiring List (AWL)

Fig. A-FBDAA

Modification equipment in 429VU

Sheet 01

Fig. A-FCCAA

Modification wiring in 429VU

Sheet 01

Sheet 02

Fig. A-FDCAA

Hook-up Chart 429VU

Sheet 01

(a) On overhead panel 20VU, remove the panel 429VU fixed with four fasteners

Disconnect the three connectors FIN 1470VC-A, 1471VC-A, 1472VC-A

(b) On bench, separate the three connectors from plate Item (1) (Refer to Fig. AFBDAA Sheet 01)

Discard associated hardware.

Separate all the modules and end-modules from the mounting rail 1347VT without

disconnection.

Separate the mounting rail 1347VT from plate Item (1)

Discard associated hardware.

(c) On bench, remove (Refer to Fig. A-FBDAA Sheet 01) :

1 Plate Item (1)

Discard associated hardware.

(d) On bench, install (Refer to Fig. A-FBDAA Sheet 01) :

1 Supplate-Rear Assy A9251063000000 Item 1

with

3 Screw NAS1100-06-7 Item 4

3 Washer-Lock MS35333-37 Item 5

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 74

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(e) From connector FIN 1471VC, disconnect all the wires as per Aircraft Wiring List

(AWL)

(f) Remove :

1 Connector Item (2)

Discard associated hardware.

(g) On plate Item 1, install :

FIN 1471VC

1 Connector EN3646A02255AZ Item 2

with

2 Screw NAS1100-04-6 Item 13

2 Nut MS21042L04 Item 14

2 Washer NAS1149FN416P Item 12

(h) Behind connector 1471VC, install :

1 Backshell-Connector NSA938003-22

(i) On connector FIN 1471VC, reconnect all the wires as per Aircraft Wiring List (AWL)

(j) On plate Item 1, install the two others connectors FIN 1470VC and 1472VC with :

4 Screw NAS1100-04-6 Item 13

4 Washer NAS1149FN416P Item 12

4 Nut MS21042L04 Item 14

(k) On plate Item 1, install :

FIN 1347VT

1 Rail NSA937901RB0120 Item 3

with

2 Screw NAS1100-08-7 Item 6

2 Washer NAS1149FN816P Item 7

(l) On the mounting rail 1347VT, reinstall all the modules and install in position 9 :

FIN 1347VT9

1 Module NSA937901MA2011

with

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 75

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

1 Label Identification NSA937901E9

(m) On the mounting rail 1347VT, reinstall the two end modules.

(n) Remove the wires as shown on the wiring diagram Fig. A-FCCAA Sheet 01Fig. AFCCAA Sheet 02 and as given in the Hook-up Chart lines :

- 1 thru 4 (Refer to Fig. A-FDCAA Sheet 01)

(o) Install the wires as shown on the wiring diagram Fig. A-FCCAA Sheet 01Fig. AFCCAA Sheet 02 and as given in the Hook-up Chart lines :

- 8 thru 19 (Refer to Fig. A-FDCAA Sheet 01)

supplied in :

Bundle A9000095320695

For aircraft using Kit A01R06, use

Bundle A9000095320695

supplied in Supplementary Kit A01S06

(p) Attach the wires with :

20 Tie-Cable NSA935401-03

(q) On aircraft, disconnect as per Aircraft Wiring List (AWL), all the wires connected to

connector FIN 1471VC-A.

(r) Replace the connector FIN 1471VC-A and back-shell by :

FIN 1471VCA

1 Connector-Plug EN3646A62255BZ

FIN 1471VCA1

1 Backshell-Connector NSA938150-02-22

(s) Reconnect as per Aircraft Wiring List (AWL), all the wires disconnected to

connector FIN 1471VC-A.

(6) Subtask 742003-831-004-001 - Modify the Relay Box 104VU on bench

Work Zones and Access Panels

Zone Access/Work location

120

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 76

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

NSA935401-03 20 TIE

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Pure Mineral Vaseline Or

Petro- Latum

04-012 As required

Electrical Bond Varnish 07-001B As required

References

Aircraft Maintenance Manual (AMM) 20-28-11

Fig. A-FCDAA

Modification wiring in 104VU

Sheet 01

Fig. A-FDDAA

Hook-up Chart 104VU

Sheet 01

(a) From the Relay Box 104VU, disconnect the bonding strip, remove the screws, the

clamps and the box front cover

NOTE: Disconnect the connectors and remove the Relay Box 104VU to get

access to the inside of the box.

Put blanking caps on the disconnected electrical connectors.

Reconnect and install all the removed components after

modification.

(b) Install the wires as shown on the wiring diagram Fig. A-FCDAA Sheet 01 and as

given in the Hook-up Chart lines :

- 1 thru 2 (Refer to Fig. A-FDDAA Sheet 01)

supplied in :

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 77

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Bundle A9000095320695

For aircraft using Kit A01R06, use

Bundle A9000095320695

supplied in Supplementary Kit A01S06

(c) Attach the wires with :

20 Tie-Cable NSA935401-03

(d) On Relay Box 104VU, do the electrical bonding (Refer to AMM 20-28-11) with :

Pure Mineral

Vaseline Or PetroLatum

04-012 As required

Electrical Bond

Varnish

07-001B As required

(e) Connect the bonding strip, install the screws, the clamps and the front box.

Reconnect and install the Relay Box 104VU

(7) Subtask 742003-831-005-001 - Modify the Electronics Rack 80VU

Work Zones and Access Panels

Zone Access/Work location

121

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

NSA935401-03 20 TIE

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 78

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

References

Fig. A-FCEAA

Modification wiring in 80VU

Sheet 01

Fig. A-FDEAA

Hook-up Chart 80VU

Sheet 01

(a) Install the wires as shown on the wiring diagram Fig. A-FCEAA Sheet 01 and as

given in the Hook-up Chart lines :

- 1 thru 2 (Refer to Fig. A-FDEAA Sheet 01)

supplied in :

Bundle A9000095320695

For aircraft using Kit A01R06, use

Bundle A9000095320695

supplied in Supplementary Kit A01S06

(b) Attach the wires with :

20 Tie-Cable NSA935401-03

(8) Subtask 742003-831-006-001 - Modify the wiring in Zones

Work Zones and Access Panels

Zone Access/Work location

From 120

To 210

Manpower Resources

Manhours 8.00

Minimum number of person 2

Subtask elapsed time 4.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

EN3155-018M1616 1 PIN

EN3155-019F1616 1 CONTACT

NSA935401-05 100 TIE

NSA935401-13 100 TIE

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 79

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

EN3155-018M1616 PIN

EN3155-019F1616 1 CONTACT

References

Fig. A-FCFAA

Modification wiring in Zones

Sheet 01

Sheet 02

Fig. A-FDFAA

Hook-up Chart Zones

Sheet 01

Fig. A-FBEAA

Routing

Sheet 01

(a) Install the wires as shown on the wiring diagram Fig. A-FCFAA Sheet 01Fig. AFCFAA Sheet 02 and as given in the Hook-up Chart lines :

- 1 thru 9 (Refer to Fig. A-FDFAA Sheet 01)

supplied in :

Bundle A9000095320695

with:

1 Contact-Socket EN3155-019F1616

1 Pin-Contact EN3155-018M1616

For aircraft using Kit A01R06, use

Bundle A9000095320695

supplied in Supplementary Kit A01S06

For aircraft using Kit A01R01 or Kit A01R03, use:

1 Pin-Contact EN3155-018M1616

1 Contact-Socket EN3155-019F1616

supplied in Supplementary Kit A01S05

(b) Attach the wires with :

100 Tie-Cable NSA935401-05

100 Tie-Cable NSA935401-13

(c) On aircraft, reconnect the three connectors FIN 1471VC, 1470VC, 1472VC.

(d) On aircraft, on overhead panel 20VU, reinstall the panel 429VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 80

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 003

(1) Subtask 742003-831-001-001 - Modify the Circuit Breaker panel 133VU

Work Zones and Access Panels

Zone Access/Work location

210

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A11321141C00 2 PLACARD

A9100095041095 PLCD SET

EN2995-004A03AA 2 CB

Supplementary kit 742003A01S05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A11321141C00 PLACARD

References

Aircraft Maintenance Manual (AMM) 24-50-20

Fig. A-FBBAB

Modification equipment in 133VU

Sheet 01

Fig. A-FBCAB

Modification Placard in 133VU

Sheet 01

(a) Inside panel 133VU, at position S69 and S74, install (Refer to AMM 24-50-20) :

FIN 13JH

1 Cb-Circuit Breaker EN2995-004A03AA

FIN 14JH

1 Cb-Circuit Breaker EN2995-004A03AA

(b) Inside panel 133VU, at position S69 and S74, install two new self-sticking labels

supplied in Fig. A-FBBAB Sheet 01:

Placard Set A9100095041095

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 81

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(c) On panel 133VU, in front of the two new Circuit Breakers, on the existing placard,

with a cutter, make two cut-out at position S69 and S74 so that you can insert the

two new self-sticking labels supplied in Fig. A-FBCAB Sheet 01:

2 Placard A11321141C00

For aircraft using Kit A01R03

2 Placard A11321141C00

supplied in Supplementary kit A01S05

NOTE: Adjust the size of the labels at assembly.

(2) Subtask 742003-831-002-001 - Modify the wiring in Circuit Breaker panel 133VU

Work Zones and Access Panels

Zone Access/Work location

210

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

NSA935401-03 20 TIE

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

References

Fig. A-FCAAA

Modification wiring in 133VU

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FDAAA

Hook-up Chart 133VU

Sheet 01

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 82

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(a) Remove the wires as shown on the wiring diagram Fig. A-FCAAA Sheet 01, Fig. AFCAAA Sheet 02, Fig. A-FCAAA Sheet 03, Fig. A-FCAAA Sheet 04 and as given in

the Hook-up Chart lines :

- 1 thru 6(Refer to Fig. A-FDAAA Sheet 01).

(b) Install the wires as shown on the wiring diagram Fig. A-FCAAA Sheet 01, Fig. AFCAAA Sheet 02, Fig. A-FCAAA Sheet 03, Fig. A-FCAAA Sheet 04 and as given in

the Hook-up Chart lines :

- 10 thru 21 (Refer to Fig. A-FDAAA Sheet 01)

supplied in :

Bundle A9000095320695

For aircraft using Kit A01R06, use

Bundle A9000095320695

supplied in Supplementary Kit A01S06

(c) Attach the wires with :

20 Tie-Cable NSA935401-03

(3) Subtask 742003-831-008-004 - Modify the equipment in the Relay Box 105VU on

bench

Work Zones and Access Panels

Zone Access/Work location

122

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 A9251133320000 1 PLATE

10 NAS1100-04-7 8 SCREW

11 MS21042-04 8 NUT

12 NAS1149FN416P 8 WASHER

A9100095041095 PLCD SET

ABS1416A120CJ 2 RELAY

E0247A0 2 BASE

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 83

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

E0666D28A0 2 RELAY

NSA932844CJ 2 SOCKET

NSA937901E0 1 LABEL

NSA937901E1 5 LABEL

NSA937901E7 1 LABEL

NSA937901E8 1 LABEL

NSA937901FM 1 MODULE

NSA937901M20-08 2 MODULE

NSA937901MA2004 2 MODULE

Supplementary kit 742003A01S01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NSA932844CJ 2 SOCKET

References

Aircraft Wiring List (AWL)

Fig. A-FBAAD

Modification equipment in 105VU

Sheet 01

(a) From the Relay Box 105VU, disconnect the bonding strip, remove the screws, the

clamps and the box front cover

NOTE: Disconnect the connectors and remove the Relay Box 105VU to get

access to the inside of the box.

Put blanking caps on the disconnected electrical connectors.

Reconnect and install all the removed components after

modification.

(b) On bench, install on plate Item 9 :

FIN 17JH

1 Relay E0666D28A0

FIN 18JH

1 Relay E0666D28A0

with

FIN 17JHA

1 Base E0247A0

FIN 18JHA

1 Base E0247A0

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 84

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(c) On bench, install (Refer to Fig. A-FBAAD Sheet 01) :

1 Plate A9251133320000 Item 9

with

4 Screw NAS1100-04-7 Item 10

4 Washer NAS1149FN416P Item 12

4 Nut MS21042-04 Item 11

(d) On bench, install (Refer to Fig. A-FBAAD Sheet 01) :

FIN 15JH

1 Relay ABS1416A120CJ

FIN 15JHA

1 Socket-Relay NSA932844CJ

For aircraft using Kit A01R01

FIN 15JHA

1 Socket-Relay NSA932844CJ

supplied in Supplementary kit A01S01

FIN 16JH

1 Relay ABS1416A120CJ

FIN 16JHA

1 Socket-Relay NSA932844CJ

For aircraft using Kit A01R01

FIN 16JHA

1 Socket-Relay NSA932844CJ

supplied in Supplementary kit A01S01

with

4 Screw NAS1100-04-7 Item 10

4 Washer NAS1149FN416P Item 12

4 Nut MS21042-04 Item 11

NOTE: For aircraft using Kit 742003A01R01 the socket relay P/N

NSA932844CJ is suplied in suplemental kit 742003A01S01

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 85

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(e) Close to new relays, affix placards supplied in :

Placard Set A9100095041095

(f) On the mounting rail 192VT, on modules position 10 and 11, disconnect wires as

per Aircraft Wiring List (AWL)

(g) On the mounting rail 192VT, remove from position 10 and 11 :

2 modules

(h) On the mounting rail 192VT, at position 10 and 11, install :

2 Module NSA937901MA2004

with

3 Label Identification NSA937901E1

1 Label Identification NSA937901E0

(i) On the mounting rail 192VT, on modules 10 and 11, reconnect wires as per Aircraft

Wiring List (AWL) only on contacts A, B ,F, G if there are existing wires.

(j) On the mounting rail 192VT, remove and retain from position 16 the end-module.

(k) On the mounting rail 192VT, at position 16, install :

1 Module-False NSA937901FM

(l) On the mounting rail 192VT, at position 17 and 18, install :

2 Module NSA937901M20-08

with

2 Label Identification NSA937901E1

1 Label Identification NSA937901E7

1 Label Identification NSA937901E8

(m) On the mounting rail 192VT, at position 19, install the end-module retained at

removal.

(4) Subtask 742003-831-007-001 - Modify the wiring in the Relay Box 105VU on bench

Manpower Resources

Manhours 8.00

Minimum number of person 1

Subtask elapsed time 8.00

Skills ELECTRICAL

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 86

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

NSA935401-05 100 TIE

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Pure Mineral Vaseline Or

Petro- Latum

04-012 As required

Electrical Bond Varnish 07-001B As required

References

Aircraft Maintenance Manual (AMM) 20-28-11

Fig. A-FCBAA

Modification wiring in 105VU

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FDBAA

Hook-up Chart 105VU

Sheet 01

Sheet 02

Sheet 03

(a) Remove the wires as shown on the wiring diagram Fig. A-FCBAA Sheet 01, Fig. AFCBAA Sheet 02, Fig. A-FCBAA Sheet 03, Fig. A-FCBAA Sheet 04 and as given in

the Hook-up Chart lines :

- 1 thru 14 (Refer to Fig. A-FDBAA Sheet 01)

(b) Install the wires as shown on the wiring diagram Fig. A-FCBAA Sheet 01, Fig. AFCBAA Sheet 02, Fig. A-FCBAA Sheet 03, Fig. A-FCBAA Sheet 04 and as given in

the Hook-up Chart lines :

- 1 thru 25 (Refer to Fig. A-FDBAA Sheet 02)

- 1 thru 13 (Refer to Fig. A-FDBAA Sheet 03)

supplied in :

Bundle A9000095320695

For aircraft using Kit A01R06, use

Bundle A9000095320695

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 87

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

supplied in Supplementary Kit A01S06

(c) Attach the wires with :

100 Tie-Cable NSA935401-05

(d) On the relay box 105VU, do the electrical bonding (Refer to AMM 20-28-11) with :

Pure Mineral

Vaseline Or PetroLatum

04-012 As required

Electrical Bond

Varnish

07-001B As required

(e) Connect the bonding strip, install the screws, the clamps and the front box.

Reconnect and install the Relay Box 105VU

(5) Subtask 742003-831-003-001 - Modify the Eng Start/APU/Wiper Panel 429VU

Work Zones and Access Panels

Zone Access/Work location

210

Manpower Resources

Manhours 10.00

Minimum number of person 1

Subtask elapsed time 10.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 A9251063000000 1 SUPPLATE

2 EN3646A02255AZ 1 CONNECTR

3 NSA937901RB0120 1 RAIL

4 NAS1100-06-7 3 SCREW

5 MS35333-37 3 WASHER

6 NAS1100-08-7 2 SCREW

7 NAS1149FN816P 2 WASHER

12 NAS1149FN416P 6 WASHER

13 NAS1100-04-6 6 SCREW

14 MS21042L04 6 NUT

A9000095320695 BUNDLE

EN3646A62255BZ 1 CONNECTR

NSA935401-03 20 TIE

NSA937901E9 1 LABEL

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 88

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NSA937901MA2011 1 MODULE

NSA938003-22 1 BACKSHLL

NSA938150-02-22 1 BACKSHLL

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

References

Aircraft Wiring List (AWL)

Fig. A-FBDAA

Modification equipment in 429VU

Sheet 01

Fig. A-FCCAA

Modification wiring in 429VU

Sheet 01

Sheet 02

Fig. A-FDCAA

Hook-up Chart 429VU

Sheet 01

(a) On overhead panel 20VU, remove the panel 429VU fixed with four fasteners

Disconnect the three connectors FIN 1470VC-A, 1471VC-A, 1472VC-A

(b) On bench, separate the three connectors from plate Item (1) (Refer to Fig. AFBDAA Sheet 01)

Discard associated hardware.

Separate all the modules and end-modules from the mounting rail 1347VT without

disconnection.

Separate the mounting rail 1347VT from plate Item (1)

Discard associated hardware.

(c) On bench, remove (Refer to Fig. A-FBDAA Sheet 01) :

1 Plate Item (1)

Discard associated hardware.

(d) On bench, install (Refer to Fig. A-FBDAA Sheet 01) :

1 Supplate-Rear Assy A9251063000000 Item 1

with

3 Screw NAS1100-06-7 Item 4

3 Washer-Lock MS35333-37 Item 5

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 89

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(e) From connector FIN 1471VC, disconnect all the wires as per Aircraft Wiring List

(AWL)

(f) Remove :

1 Connector Item (2)

Discard associated hardware.

(g) On plate Item 1, install :

FIN 1471VC

1 Connector EN3646A02255AZ Item 2

with

2 Screw NAS1100-04-6 Item 13

2 Nut MS21042L04 Item 14

2 Washer NAS1149FN416P Item 12

(h) Behind connector 1471VC, install :

1 Backshell-Connector NSA938003-22

(i) On connector FIN 1471VC, reconnect all the wires as per Aircraft Wiring List (AWL)

(j) On plate Item 1, install the two others connectors FIN 1470VC and 1472VC with :

4 Screw NAS1100-04-6 Item 13

4 Washer NAS1149FN416P Item 12

4 Nut MS21042L04 Item 14

(k) On plate Item 1, install :

FIN 1347VT

1 Rail NSA937901RB0120 Item 3

with

2 Screw NAS1100-08-7 Item 6

2 Washer NAS1149FN816P Item 7

(l) On the mounting rail 1347VT, reinstall all the modules and install in position 9 :

FIN 1347VT9

1 Module NSA937901MA2011

with

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 90

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

1 Label Identification NSA937901E9

(m) On the mounting rail 1347VT, reinstall the two end modules.

(n) Remove the wires as shown on the wiring diagram Fig. A-FCCAA Sheet 01Fig. AFCCAA Sheet 02 and as given in the Hook-up Chart lines :

- 1 thru 4 (Refer to Fig. A-FDCAA Sheet 01)

(o) Install the wires as shown on the wiring diagram Fig. A-FCCAA Sheet 01Fig. AFCCAA Sheet 02 and as given in the Hook-up Chart lines :

- 8 thru 19 (Refer to Fig. A-FDCAA Sheet 01)

supplied in :

Bundle A9000095320695

For aircraft using Kit A01R06, use

Bundle A9000095320695

supplied in Supplementary Kit A01S06

(p) Attach the wires with :

20 Tie-Cable NSA935401-03

(q) On aircraft, disconnect as per Aircraft Wiring List (AWL), all the wires connected to

connector FIN 1471VC-A.

(r) Replace the connector FIN 1471VC-A and back-shell by :

FIN 1471VCA

1 Connector-Plug EN3646A62255BZ

FIN 1471VCA1

1 Backshell-Connector NSA938150-02-22

(s) Reconnect as per Aircraft Wiring List (AWL), all the wires disconnected to

connector FIN 1471VC-A.

(6) Subtask 742003-831-004-001 - Modify the Relay Box 104VU on bench

Work Zones and Access Panels

Zone Access/Work location

120

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 91

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

NSA935401-03 20 TIE

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Pure Mineral Vaseline Or

Petro- Latum

04-012 As required

Electrical Bond Varnish 07-001B As required

References

Aircraft Maintenance Manual (AMM) 20-28-11

Fig. A-FCDAA

Modification wiring in 104VU

Sheet 01

Fig. A-FDDAA

Hook-up Chart 104VU

Sheet 01

(a) From the Relay Box 104VU, disconnect the bonding strip, remove the screws, the

clamps and the box front cover

NOTE: Disconnect the connectors and remove the Relay Box 104VU to get

access to the inside of the box.

Put blanking caps on the disconnected electrical connectors.

Reconnect and install all the removed components after

modification.

(b) Install the wires as shown on the wiring diagram Fig. A-FCDAA Sheet 01 and as

given in the Hook-up Chart lines :

- 1 thru 2 (Refer to Fig. A-FDDAA Sheet 01)

supplied in :

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 92

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Bundle A9000095320695

For aircraft using Kit A01R06, use

Bundle A9000095320695

supplied in Supplementary Kit A01S06

(c) Attach the wires with :

20 Tie-Cable NSA935401-03

(d) On Relay Box 104VU, do the electrical bonding (Refer to AMM 20-28-11) with :

Pure Mineral

Vaseline Or PetroLatum

04-012 As required

Electrical Bond

Varnish

07-001B As required

(e) Connect the bonding strip, install the screws, the clamps and the front box.

Reconnect and install the Relay Box 104VU

(7) Subtask 742003-831-005-001 - Modify the Electronics Rack 80VU

Work Zones and Access Panels

Zone Access/Work location

121

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

NSA935401-03 20 TIE

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 93

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

References

Fig. A-FCEAA

Modification wiring in 80VU

Sheet 01

Fig. A-FDEAA

Hook-up Chart 80VU

Sheet 01

(a) Install the wires as shown on the wiring diagram Fig. A-FCEAA Sheet 01 and as

given in the Hook-up Chart lines :

- 1 thru 2 (Refer to Fig. A-FDEAA Sheet 01)

supplied in :

Bundle A9000095320695

For aircraft using Kit A01R06, use

Bundle A9000095320695

supplied in Supplementary Kit A01S06

(b) Attach the wires with :

20 Tie-Cable NSA935401-03

(8) Subtask 742003-831-006-001 - Modify the wiring in Zones

Work Zones and Access Panels

Zone Access/Work location

From 120

To 210

Manpower Resources

Manhours 8.00

Minimum number of person 2

Subtask elapsed time 4.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

EN3155-018M1616 1 PIN

EN3155-019F1616 1 CONTACT

NSA935401-05 100 TIE

NSA935401-13 100 TIE

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 94

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

EN3155-018M1616 PIN

EN3155-019F1616 1 CONTACT

References

Fig. A-FCFAA

Modification wiring in Zones

Sheet 01

Sheet 02

Fig. A-FDFAA

Hook-up Chart Zones

Sheet 01

Fig. A-FBEAA

Routing

Sheet 01

(a) Install the wires as shown on the wiring diagram Fig. A-FCFAA Sheet 01Fig. AFCFAA Sheet 02 and as given in the Hook-up Chart lines :

- 1 thru 9 (Refer to Fig. A-FDFAA Sheet 01)

supplied in :

Bundle A9000095320695

with:

1 Contact-Socket EN3155-019F1616

1 Pin-Contact EN3155-018M1616

For aircraft using Kit A01R06, use

Bundle A9000095320695

supplied in Supplementary Kit A01S06

For aircraft using Kit A01R01 or Kit A01R03, use:

1 Pin-Contact EN3155-018M1616

1 Contact-Socket EN3155-019F1616

supplied in Supplementary Kit A01S05

(b) Attach the wires with :

100 Tie-Cable NSA935401-05

100 Tie-Cable NSA935401-13

(c) On aircraft, reconnect the three connectors FIN 1471VC, 1470VC, 1472VC.

(d) On aircraft, on overhead panel 20VU, reinstall the panel 429VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 95

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 006

(1) Subtask 742003-831-001-001 - Modify the Circuit Breaker panel 133VU

Work Zones and Access Panels

Zone Access/Work location

210

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A11321141C00 2 PLACARD

A9100095041095 PLCD SET

EN2995-004A03AA 2 CB

Supplementary kit 742003A01S05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A11321141C00 PLACARD

References

Aircraft Maintenance Manual (AMM) 24-50-20

Fig. A-FBBAB

Modification equipment in 133VU

Sheet 01

Fig. A-FBCAB

Modification Placard in 133VU

Sheet 01

(a) Inside panel 133VU, at position S69 and S74, install (Refer to AMM 24-50-20) :

FIN 13JH

1 Cb-Circuit Breaker EN2995-004A03AA

FIN 14JH

1 Cb-Circuit Breaker EN2995-004A03AA

(b) Inside panel 133VU, at position S69 and S74, install two new self-sticking labels

supplied in Fig. A-FBBAB Sheet 01:

Placard Set A9100095041095

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 96

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(c) On panel 133VU, in front of the two new Circuit Breakers, on the existing placard,

with a cutter, make two cut-out at position S69 and S74 so that you can insert the

two new self-sticking labels supplied in Fig. A-FBCAB Sheet 01:

2 Placard A11321141C00

For aircraft using Kit A01R03

2 Placard A11321141C00

supplied in Supplementary kit A01S05

NOTE: Adjust the size of the labels at assembly.

(2) Subtask 742003-831-002-001 - Modify the wiring in Circuit Breaker panel 133VU

Work Zones and Access Panels

Zone Access/Work location

210

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

NSA935401-03 20 TIE

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

References

Fig. A-FCAAA

Modification wiring in 133VU

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FDAAA

Hook-up Chart 133VU

Sheet 01

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 97

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(a) Remove the wires as shown on the wiring diagram Fig. A-FCAAA Sheet 01, Fig. AFCAAA Sheet 02, Fig. A-FCAAA Sheet 03, Fig. A-FCAAA Sheet 04 and as given in

the Hook-up Chart lines :

- 1 thru 6(Refer to Fig. A-FDAAA Sheet 01).

(b) Install the wires as shown on the wiring diagram Fig. A-FCAAA Sheet 01, Fig. AFCAAA Sheet 02, Fig. A-FCAAA Sheet 03, Fig. A-FCAAA Sheet 04 and as given in

the Hook-up Chart lines :

- 10 thru 21 (Refer to Fig. A-FDAAA Sheet 01)

supplied in :

Bundle A9000095320695

For aircraft using Kit A01R06, use

Bundle A9000095320695

supplied in Supplementary Kit A01S06

(c) Attach the wires with :

20 Tie-Cable NSA935401-03

(3) Subtask 742003-831-008-007 - Modify the equipment in the Relay Box 105VU on

bench

Work Zones and Access Panels

Zone Access/Work location

122

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 A9251133320000 1 PLATE

10 NAS1100-04-7 8 SCREW

11 MS21042-04 8 NUT

12 NAS1149FN416P 8 WASHER

A9100095041095 PLCD SET

ABS1416A120CJ 2 RELAY

E0247A0 2 BASE

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 98

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

E0666D28A0 2 RELAY

NSA932844CJ 2 SOCKET

NSA937901E0 1 LABEL

NSA937901E1 5 LABEL

NSA937901E7 1 LABEL

NSA937901E8 1 LABEL

NSA937901FM 1 MODULE

NSA937901M20-08 2 MODULE

NSA937901MA2004 2 MODULE

Supplementary kit 742003A01S01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NSA932844CJ 2 SOCKET

References

Aircraft Wiring List (AWL)

Fig. A-FBAAF

Modification equipment in 105VU

Sheet 01

(a) From the Relay Box 105VU, disconnect the bonding strip, remove the screws, the

clamps and the box front cover

NOTE: Disconnect the connectors and remove the Relay Box 105VU to get

access to the inside of the box.

Put blanking caps on the disconnected electrical connectors.

Reconnect and install all the removed components after

modification.

(b) On bench, install on plate Item 9 :

FIN 17JH

1 Relay E0666D28A0

FIN 18JH

1 Relay E0666D28A0

with

FIN 17JHA

1 Base E0247A0

FIN 18JHA

1 Base E0247A0

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 99

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(c) On bench, install (Refer to Fig. A-FBAAF Sheet 01) :

1 Plate A9251133320000 Item 9

with

4 Screw NAS1100-04-7 Item 10

4 Washer NAS1149FN416P Item 12

4 Nut MS21042-04 Item 11

(d) On bench, install (Refer to Fig. A-FBAAF Sheet 01) :

FIN 15JH

1 Relay ABS1416A120CJ

FIN 15JHA

1 Socket-Relay NSA932844CJ

For aircraft using Kit A01R01

FIN 15JHA

1 Socket-Relay NSA932844CJ

supplied in Supplementary kit A01S01

FIN 16JH

1 Relay ABS1416A120CJ

FIN 16JHA

1 Socket-Relay NSA932844CJ

For aircraft using Kit A01R01

FIN 16JHA

1 Socket-Relay NSA932844CJ

supplied in Supplementary kit A01S01

with

4 Screw NAS1100-04-7 Item 10

4 Washer NAS1149FN416P Item 12

4 Nut MS21042-04 Item 11

NOTE: For aircraft using Kit 742003A01R01 the socket relay P/N

NSA932844CJ is suplied in suplemental kit 742003A01S01

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 100

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(e) Close to new relays, affix placards supplied in :

Placard Set A9100095041095

(f) On the mounting rail 192VT, on modules position 10 and 11, disconnect wires as

per Aircraft Wiring List (AWL)

(g) On the mounting rail 192VT, remove from position 10 and 11 :

2 modules

(h) On the mounting rail 192VT, at position 10 and 11, install :

2 Module NSA937901MA2004

with

3 Label Identification NSA937901E1

1 Label Identification NSA937901E0

(i) On the mounting rail 192VT, on modules 10 and 11, reconnect wires as per Aircraft

Wiring List (AWL) only on contacts A, B ,F, G if there are existing wires.

(j) On the mounting rail 192VT, remove and retain from position 16 the end-module.

(k) On the mounting rail 192VT, at position 16, install :

1 Module-False NSA937901FM

(l) On the mounting rail 192VT, at position 17 and 18, install :

2 Module NSA937901M20-08

with

2 Label Identification NSA937901E1

1 Label Identification NSA937901E7

1 Label Identification NSA937901E8

(m) On the mounting rail 192VT, at position 19, install the end-module retained at

removal.

(4) Subtask 742003-831-007-001 - Modify the wiring in the Relay Box 105VU on bench

Manpower Resources

Manhours 8.00

Minimum number of person 1

Subtask elapsed time 8.00

Skills ELECTRICAL

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 101

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

NSA935401-05 100 TIE

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Pure Mineral Vaseline Or

Petro- Latum

04-012 As required

Electrical Bond Varnish 07-001B As required

References

Aircraft Maintenance Manual (AMM) 20-28-11

Fig. A-FCBAA

Modification wiring in 105VU

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FDBAA

Hook-up Chart 105VU

Sheet 01

Sheet 02

Sheet 03

(a) Remove the wires as shown on the wiring diagram Fig. A-FCBAA Sheet 01, Fig. AFCBAA Sheet 02, Fig. A-FCBAA Sheet 03, Fig. A-FCBAA Sheet 04 and as given in

the Hook-up Chart lines :

- 1 thru 14 (Refer to Fig. A-FDBAA Sheet 01)

(b) Install the wires as shown on the wiring diagram Fig. A-FCBAA Sheet 01, Fig. AFCBAA Sheet 02, Fig. A-FCBAA Sheet 03, Fig. A-FCBAA Sheet 04 and as given in

the Hook-up Chart lines :

- 1 thru 25 (Refer to Fig. A-FDBAA Sheet 02)

- 1 thru 13 (Refer to Fig. A-FDBAA Sheet 03)

supplied in :

Bundle A9000095320695

For aircraft using Kit A01R06, use

Bundle A9000095320695

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 102

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

supplied in Supplementary Kit A01S06

(c) Attach the wires with :

100 Tie-Cable NSA935401-05

(d) On the relay box 105VU, do the electrical bonding (Refer to AMM 20-28-11) with :

Pure Mineral

Vaseline Or PetroLatum

04-012 As required

Electrical Bond

Varnish

07-001B As required

(e) Connect the bonding strip, install the screws, the clamps and the front box.

Reconnect and install the Relay Box 105VU

(5) Subtask 742003-831-003-001 - Modify the Eng Start/APU/Wiper Panel 429VU

Work Zones and Access Panels

Zone Access/Work location

210

Manpower Resources

Manhours 10.00

Minimum number of person 1

Subtask elapsed time 10.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 A9251063000000 1 SUPPLATE

2 EN3646A02255AZ 1 CONNECTR

3 NSA937901RB0120 1 RAIL

4 NAS1100-06-7 3 SCREW

5 MS35333-37 3 WASHER

6 NAS1100-08-7 2 SCREW

7 NAS1149FN816P 2 WASHER

12 NAS1149FN416P 6 WASHER

13 NAS1100-04-6 6 SCREW

14 MS21042L04 6 NUT

A9000095320695 BUNDLE

EN3646A62255BZ 1 CONNECTR

NSA935401-03 20 TIE

NSA937901E9 1 LABEL

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 103

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NSA937901MA2011 1 MODULE

NSA938003-22 1 BACKSHLL

NSA938150-02-22 1 BACKSHLL

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

References

Aircraft Wiring List (AWL)

Fig. A-FBDAA

Modification equipment in 429VU

Sheet 01

Fig. A-FCCAA

Modification wiring in 429VU

Sheet 01

Sheet 02

Fig. A-FDCAA

Hook-up Chart 429VU

Sheet 01

(a) On overhead panel 20VU, remove the panel 429VU fixed with four fasteners

Disconnect the three connectors FIN 1470VC-A, 1471VC-A, 1472VC-A

(b) On bench, separate the three connectors from plate Item (1) (Refer to Fig. AFBDAA Sheet 01)

Discard associated hardware.

Separate all the modules and end-modules from the mounting rail 1347VT without

disconnection.

Separate the mounting rail 1347VT from plate Item (1)

Discard associated hardware.

(c) On bench, remove (Refer to Fig. A-FBDAA Sheet 01) :

1 Plate Item (1)

Discard associated hardware.

(d) On bench, install (Refer to Fig. A-FBDAA Sheet 01) :

1 Supplate-Rear Assy A9251063000000 Item 1

with

3 Screw NAS1100-06-7 Item 4

3 Washer-Lock MS35333-37 Item 5

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 104

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(e) From connector FIN 1471VC, disconnect all the wires as per Aircraft Wiring List

(AWL)

(f) Remove :

1 Connector Item (2)

Discard associated hardware.

(g) On plate Item 1, install :

FIN 1471VC

1 Connector EN3646A02255AZ Item 2

with

2 Screw NAS1100-04-6 Item 13

2 Nut MS21042L04 Item 14

2 Washer NAS1149FN416P Item 12

(h) Behind connector 1471VC, install :

1 Backshell-Connector NSA938003-22

(i) On connector FIN 1471VC, reconnect all the wires as per Aircraft Wiring List (AWL)

(j) On plate Item 1, install the two others connectors FIN 1470VC and 1472VC with :

4 Screw NAS1100-04-6 Item 13

4 Washer NAS1149FN416P Item 12

4 Nut MS21042L04 Item 14

(k) On plate Item 1, install :

FIN 1347VT

1 Rail NSA937901RB0120 Item 3

with

2 Screw NAS1100-08-7 Item 6

2 Washer NAS1149FN816P Item 7

(l) On the mounting rail 1347VT, reinstall all the modules and install in position 9 :

FIN 1347VT9

1 Module NSA937901MA2011

with

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 105

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

1 Label Identification NSA937901E9

(m) On the mounting rail 1347VT, reinstall the two end modules.

(n) Remove the wires as shown on the wiring diagram Fig. A-FCCAA Sheet 01Fig. AFCCAA Sheet 02 and as given in the Hook-up Chart lines :

- 1 thru 4 (Refer to Fig. A-FDCAA Sheet 01)

(o) Install the wires as shown on the wiring diagram Fig. A-FCCAA Sheet 01Fig. AFCCAA Sheet 02 and as given in the Hook-up Chart lines :

- 8 thru 19 (Refer to Fig. A-FDCAA Sheet 01)

supplied in :

Bundle A9000095320695

For aircraft using Kit A01R06, use

Bundle A9000095320695

supplied in Supplementary Kit A01S06

(p) Attach the wires with :

20 Tie-Cable NSA935401-03

(q) On aircraft, disconnect as per Aircraft Wiring List (AWL), all the wires connected to

connector FIN 1471VC-A.

(r) Replace the connector FIN 1471VC-A and back-shell by :

FIN 1471VCA

1 Connector-Plug EN3646A62255BZ

FIN 1471VCA1

1 Backshell-Connector NSA938150-02-22

(s) Reconnect as per Aircraft Wiring List (AWL), all the wires disconnected to

connector FIN 1471VC-A.

(6) Subtask 742003-831-004-001 - Modify the Relay Box 104VU on bench

Work Zones and Access Panels

Zone Access/Work location

120

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 106

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

NSA935401-03 20 TIE

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Pure Mineral Vaseline Or

Petro- Latum

04-012 As required

Electrical Bond Varnish 07-001B As required

References

Aircraft Maintenance Manual (AMM) 20-28-11

Fig. A-FCDAA

Modification wiring in 104VU

Sheet 01

Fig. A-FDDAA

Hook-up Chart 104VU

Sheet 01

(a) From the Relay Box 104VU, disconnect the bonding strip, remove the screws, the

clamps and the box front cover

NOTE: Disconnect the connectors and remove the Relay Box 104VU to get

access to the inside of the box.

Put blanking caps on the disconnected electrical connectors.

Reconnect and install all the removed components after

modification.

(b) Install the wires as shown on the wiring diagram Fig. A-FCDAA Sheet 01 and as

given in the Hook-up Chart lines :

- 1 thru 2 (Refer to Fig. A-FDDAA Sheet 01)

supplied in :

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 107

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Bundle A9000095320695

For aircraft using Kit A01R06, use

Bundle A9000095320695

supplied in Supplementary Kit A01S06

(c) Attach the wires with :

20 Tie-Cable NSA935401-03

(d) On Relay Box 104VU, do the electrical bonding (Refer to AMM 20-28-11) with :

Pure Mineral

Vaseline Or PetroLatum

04-012 As required

Electrical Bond

Varnish

07-001B As required

(e) Connect the bonding strip, install the screws, the clamps and the front box.

Reconnect and install the Relay Box 104VU

(7) Subtask 742003-831-005-001 - Modify the Electronics Rack 80VU

Work Zones and Access Panels

Zone Access/Work location

121

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

NSA935401-03 20 TIE

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 108

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

References

Fig. A-FCEAA

Modification wiring in 80VU

Sheet 01

Fig. A-FDEAA

Hook-up Chart 80VU

Sheet 01

(a) Install the wires as shown on the wiring diagram Fig. A-FCEAA Sheet 01 and as

given in the Hook-up Chart lines :

- 1 thru 2 (Refer to Fig. A-FDEAA Sheet 01)

supplied in :

Bundle A9000095320695

For aircraft using Kit A01R06, use

Bundle A9000095320695

supplied in Supplementary Kit A01S06

(b) Attach the wires with :

20 Tie-Cable NSA935401-03

(8) Subtask 742003-831-006-001 - Modify the wiring in Zones

Work Zones and Access Panels

Zone Access/Work location

From 120

To 210

Manpower Resources

Manhours 8.00

Minimum number of person 2

Subtask elapsed time 4.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

EN3155-018M1616 1 PIN

EN3155-019F1616 1 CONTACT

NSA935401-05 100 TIE

NSA935401-13 100 TIE

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 109

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

EN3155-018M1616 PIN

EN3155-019F1616 1 CONTACT

References

Fig. A-FCFAA

Modification wiring in Zones

Sheet 01

Sheet 02

Fig. A-FDFAA

Hook-up Chart Zones

Sheet 01

Fig. A-FBEAA

Routing

Sheet 01

(a) Install the wires as shown on the wiring diagram Fig. A-FCFAA Sheet 01Fig. AFCFAA Sheet 02 and as given in the Hook-up Chart lines :

- 1 thru 9 (Refer to Fig. A-FDFAA Sheet 01)

supplied in :

Bundle A9000095320695

with:

1 Contact-Socket EN3155-019F1616

1 Pin-Contact EN3155-018M1616

For aircraft using Kit A01R06, use

Bundle A9000095320695

supplied in Supplementary Kit A01S06

For aircraft using Kit A01R01 or Kit A01R03, use:

1 Pin-Contact EN3155-018M1616

1 Contact-Socket EN3155-019F1616

supplied in Supplementary Kit A01S05

(b) Attach the wires with :

100 Tie-Cable NSA935401-05

100 Tie-Cable NSA935401-13

(c) On aircraft, reconnect the three connectors FIN 1471VC, 1470VC, 1472VC.

(d) On aircraft, on overhead panel 20VU, reinstall the panel 429VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 110

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 007

(1) Subtask 742003-831-001-001 - Modify the Circuit Breaker panel 133VU

Work Zones and Access Panels

Zone Access/Work location

210

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A11321141C00 2 PLACARD

A9100095041095 PLCD SET

EN2995-004A03AA 2 CB

Supplementary kit 742003A01S05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A11321141C00 PLACARD

References

Aircraft Maintenance Manual (AMM) 24-50-20

Fig. A-FBBAB

Modification equipment in 133VU

Sheet 01

Fig. A-FBCAB

Modification Placard in 133VU

Sheet 01

(a) Inside panel 133VU, at position S69 and S74, install (Refer to AMM 24-50-20) :

FIN 13JH

1 Cb-Circuit Breaker EN2995-004A03AA

FIN 14JH

1 Cb-Circuit Breaker EN2995-004A03AA

(b) Inside panel 133VU, at position S69 and S74, install two new self-sticking labels

supplied in Fig. A-FBBAB Sheet 01:

Placard Set A9100095041095

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 111

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(c) On panel 133VU, in front of the two new Circuit Breakers, on the existing placard,

with a cutter, make two cut-out at position S69 and S74 so that you can insert the

two new self-sticking labels supplied in Fig. A-FBCAB Sheet 01:

2 Placard A11321141C00

For aircraft using Kit A01R03

2 Placard A11321141C00

supplied in Supplementary kit A01S05

NOTE: Adjust the size of the labels at assembly.

(2) Subtask 742003-831-002-001 - Modify the wiring in Circuit Breaker panel 133VU

Work Zones and Access Panels

Zone Access/Work location

210

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

NSA935401-03 20 TIE

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

References

Fig. A-FCAAA

Modification wiring in 133VU

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FDAAA

Hook-up Chart 133VU

Sheet 01

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 112

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(a) Remove the wires as shown on the wiring diagram Fig. A-FCAAA Sheet 01, Fig. AFCAAA Sheet 02, Fig. A-FCAAA Sheet 03, Fig. A-FCAAA Sheet 04 and as given in

the Hook-up Chart lines :

- 1 thru 6(Refer to Fig. A-FDAAA Sheet 01).

(b) Install the wires as shown on the wiring diagram Fig. A-FCAAA Sheet 01, Fig. AFCAAA Sheet 02, Fig. A-FCAAA Sheet 03, Fig. A-FCAAA Sheet 04 and as given in

the Hook-up Chart lines :

- 10 thru 21 (Refer to Fig. A-FDAAA Sheet 01)

supplied in :

Bundle A9000095320695

For aircraft using Kit A01R06, use

Bundle A9000095320695

supplied in Supplementary Kit A01S06

(c) Attach the wires with :

20 Tie-Cable NSA935401-03

(3) Subtask 742003-831-008-003 - Modify the equipment in the Relay Box 105VU on

bench

Work Zones and Access Panels

Zone Access/Work location

122

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 A9251133320000 1 PLATE

10 NAS1100-04-7 8 SCREW

11 MS21042-04 8 NUT

12 NAS1149FN416P 8 WASHER

A9100095041095 PLCD SET

ABS1416A120CJ 2 RELAY

E0247A0 2 BASE

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 113

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

E0666D28A0 2 RELAY

NSA932844CJ 2 SOCKET

NSA937901E0 1 LABEL

NSA937901E1 5 LABEL

NSA937901E7 1 LABEL

NSA937901E8 1 LABEL

NSA937901FM 1 MODULE

NSA937901M20-08 2 MODULE

NSA937901MA2004 2 MODULE

Supplementary kit 742003A01S01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NSA932844CJ 2 SOCKET

References

Aircraft Wiring List (AWL)

Fig. A-FBAAC

Modification equipment in 105VU

Sheet 01

(a) From the Relay Box 105VU, disconnect the bonding strip, remove the screws, the

clamps and the box front cover

NOTE: Disconnect the connectors and remove the Relay Box 105VU to get

access to the inside of the box.

Put blanking caps on the disconnected electrical connectors.

Reconnect and install all the removed components after

modification.

(b) On bench, install on plate Item 9 :

FIN 17JH

1 Relay E0666D28A0

FIN 18JH

1 Relay E0666D28A0

with

FIN 17JHA

1 Base E0247A0

FIN 18JHA

1 Base E0247A0

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 114

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(c) On bench, install (Refer to Fig. A-FBAAC Sheet 01) :

1 Plate A9251133320000 Item 9

with

4 Screw NAS1100-04-7 Item 10

4 Washer NAS1149FN416P Item 12

4 Nut MS21042-04 Item 11

(d) On bench, install (Refer to Fig. A-FBAAC Sheet 01) :

FIN 15JH

1 Relay ABS1416A120CJ

FIN 15JHA

1 Socket-Relay NSA932844CJ

For aircraft using Kit A01R01

FIN 15JHA

1 Socket-Relay NSA932844CJ

supplied in Supplementary kit A01S01

FIN 16JH

1 Relay ABS1416A120CJ

FIN 16JHA

1 Socket-Relay NSA932844CJ

For aircraft using Kit A01R01

FIN 16JHA

1 Socket-Relay NSA932844CJ

supplied in Supplementary kit A01S01

with

4 Screw NAS1100-04-7 Item 10

4 Washer NAS1149FN416P Item 12

4 Nut MS21042-04 Item 11

NOTE: For aircraft using Kit 742003A01R01 the socket relay P/N

NSA932844CJ is suplied in suplemental kit 742003A01S01

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 115

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(e) Close to new relays, affix placards supplied in :

Placard Set A9100095041095

(f) On the mounting rail 192VT, on modules position 10 and 11, disconnect wires as

per Aircraft Wiring List (AWL)

(g) On the mounting rail 192VT, remove from position 10 and 11 :

2 modules

(h) On the mounting rail 192VT, at position 10 and 11, install :

2 Module NSA937901MA2004

with

3 Label Identification NSA937901E1

1 Label Identification NSA937901E0

(i) On the mounting rail 192VT, on modules 10 and 11, reconnect wires as per Aircraft

Wiring List (AWL) only on contacts A, B ,F, G if there are existing wires.

(j) On the mounting rail 192VT, remove and retain from position 16 the end-module.

(k) On the mounting rail 192VT, at position 16, install :

1 Module-False NSA937901FM

(l) On the mounting rail 192VT, at position 17 and 18, install :

2 Module NSA937901M20-08

with

2 Label Identification NSA937901E1

1 Label Identification NSA937901E7

1 Label Identification NSA937901E8

(m) On the mounting rail 192VT, at position 19, install the end-module retained at

removal.

(4) Subtask 742003-831-007-001 - Modify the wiring in the Relay Box 105VU on bench

Manpower Resources

Manhours 8.00

Minimum number of person 1

Subtask elapsed time 8.00

Skills ELECTRICAL

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 116

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

NSA935401-05 100 TIE

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Pure Mineral Vaseline Or

Petro- Latum

04-012 As required

Electrical Bond Varnish 07-001B As required

References

Aircraft Maintenance Manual (AMM) 20-28-11

Fig. A-FCBAA

Modification wiring in 105VU

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FDBAA

Hook-up Chart 105VU

Sheet 01

Sheet 02

Sheet 03

(a) Remove the wires as shown on the wiring diagram Fig. A-FCBAA Sheet 01, Fig. AFCBAA Sheet 02, Fig. A-FCBAA Sheet 03, Fig. A-FCBAA Sheet 04 and as given in

the Hook-up Chart lines :

- 1 thru 14 (Refer to Fig. A-FDBAA Sheet 01)

(b) Install the wires as shown on the wiring diagram Fig. A-FCBAA Sheet 01, Fig. AFCBAA Sheet 02, Fig. A-FCBAA Sheet 03, Fig. A-FCBAA Sheet 04 and as given in

the Hook-up Chart lines :

- 1 thru 25 (Refer to Fig. A-FDBAA Sheet 02)

- 1 thru 13 (Refer to Fig. A-FDBAA Sheet 03)

supplied in :

Bundle A9000095320695

For aircraft using Kit A01R06, use

Bundle A9000095320695

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 117

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

supplied in Supplementary Kit A01S06

(c) Attach the wires with :

100 Tie-Cable NSA935401-05

(d) On the relay box 105VU, do the electrical bonding (Refer to AMM 20-28-11) with :

Pure Mineral

Vaseline Or PetroLatum

04-012 As required

Electrical Bond

Varnish

07-001B As required

(e) Connect the bonding strip, install the screws, the clamps and the front box.

Reconnect and install the Relay Box 105VU

(5) Subtask 742003-831-003-001 - Modify the Eng Start/APU/Wiper Panel 429VU

Work Zones and Access Panels

Zone Access/Work location

210

Manpower Resources

Manhours 10.00

Minimum number of person 1

Subtask elapsed time 10.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 A9251063000000 1 SUPPLATE

2 EN3646A02255AZ 1 CONNECTR

3 NSA937901RB0120 1 RAIL

4 NAS1100-06-7 3 SCREW

5 MS35333-37 3 WASHER

6 NAS1100-08-7 2 SCREW

7 NAS1149FN816P 2 WASHER

12 NAS1149FN416P 6 WASHER

13 NAS1100-04-6 6 SCREW

14 MS21042L04 6 NUT

A9000095320695 BUNDLE

EN3646A62255BZ 1 CONNECTR

NSA935401-03 20 TIE

NSA937901E9 1 LABEL

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 118

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NSA937901MA2011 1 MODULE

NSA938003-22 1 BACKSHLL

NSA938150-02-22 1 BACKSHLL

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

References

Aircraft Wiring List (AWL)

Fig. A-FBDAA

Modification equipment in 429VU

Sheet 01

Fig. A-FCCAA

Modification wiring in 429VU

Sheet 01

Sheet 02

Fig. A-FDCAA

Hook-up Chart 429VU

Sheet 01

(a) On overhead panel 20VU, remove the panel 429VU fixed with four fasteners

Disconnect the three connectors FIN 1470VC-A, 1471VC-A, 1472VC-A

(b) On bench, separate the three connectors from plate Item (1) (Refer to Fig. AFBDAA Sheet 01)

Discard associated hardware.

Separate all the modules and end-modules from the mounting rail 1347VT without

disconnection.

Separate the mounting rail 1347VT from plate Item (1)

Discard associated hardware.

(c) On bench, remove (Refer to Fig. A-FBDAA Sheet 01) :

1 Plate Item (1)

Discard associated hardware.

(d) On bench, install (Refer to Fig. A-FBDAA Sheet 01) :

1 Supplate-Rear Assy A9251063000000 Item 1

with

3 Screw NAS1100-06-7 Item 4

3 Washer-Lock MS35333-37 Item 5

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 119

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(e) From connector FIN 1471VC, disconnect all the wires as per Aircraft Wiring List

(AWL)

(f) Remove :

1 Connector Item (2)

Discard associated hardware.

(g) On plate Item 1, install :

FIN 1471VC

1 Connector EN3646A02255AZ Item 2

with

2 Screw NAS1100-04-6 Item 13

2 Nut MS21042L04 Item 14

2 Washer NAS1149FN416P Item 12

(h) Behind connector 1471VC, install :

1 Backshell-Connector NSA938003-22

(i) On connector FIN 1471VC, reconnect all the wires as per Aircraft Wiring List (AWL)

(j) On plate Item 1, install the two others connectors FIN 1470VC and 1472VC with :

4 Screw NAS1100-04-6 Item 13

4 Washer NAS1149FN416P Item 12

4 Nut MS21042L04 Item 14

(k) On plate Item 1, install :

FIN 1347VT

1 Rail NSA937901RB0120 Item 3

with

2 Screw NAS1100-08-7 Item 6

2 Washer NAS1149FN816P Item 7

(l) On the mounting rail 1347VT, reinstall all the modules and install in position 9 :

FIN 1347VT9

1 Module NSA937901MA2011

with

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 120

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

1 Label Identification NSA937901E9

(m) On the mounting rail 1347VT, reinstall the two end modules.

(n) Remove the wires as shown on the wiring diagram Fig. A-FCCAA Sheet 01Fig. AFCCAA Sheet 02 and as given in the Hook-up Chart lines :

- 1 thru 4 (Refer to Fig. A-FDCAA Sheet 01)

(o) Install the wires as shown on the wiring diagram Fig. A-FCCAA Sheet 01Fig. AFCCAA Sheet 02 and as given in the Hook-up Chart lines :

- 8 thru 19 (Refer to Fig. A-FDCAA Sheet 01)

supplied in :

Bundle A9000095320695

For aircraft using Kit A01R06, use

Bundle A9000095320695

supplied in Supplementary Kit A01S06

(p) Attach the wires with :

20 Tie-Cable NSA935401-03

(q) On aircraft, disconnect as per Aircraft Wiring List (AWL), all the wires connected to

connector FIN 1471VC-A.

(r) Replace the connector FIN 1471VC-A and back-shell by :

FIN 1471VCA

1 Connector-Plug EN3646A62255BZ

FIN 1471VCA1

1 Backshell-Connector NSA938150-02-22

(s) Reconnect as per Aircraft Wiring List (AWL), all the wires disconnected to

connector FIN 1471VC-A.

(6) Subtask 742003-831-004-002 - Modify the Relay Box 104VU on bench

Work Zones and Access Panels

Zone Access/Work location

120

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 121

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

NSA935401-03 20 TIE

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Pure Mineral Vaseline Or

Petro- Latum

04-012 As required

Electrical Bond Varnish 07-001B As required

References

Aircraft Maintenance Manual (AMM) 20-28-11

Fig. A-FCDAB

Modification wiring in 104VU

Sheet 01

Fig. A-FDDAB

Hook-up Chart 104VU

Sheet 01

(a) From the Relay Box 104VU, disconnect the bonding strip, remove the screws, the

clamps and the box front cover

NOTE: Disconnect the connectors and remove the Relay Box 104VU to get

access to the inside of the box.

Put blanking caps on the disconnected electrical connectors.

Reconnect and install all the removed components after

modification.

(b) Install the wires as shown on the wiring diagram Fig. A-FCDAB Sheet 01 and as

given in the Hook-up Chart lines :

- 1 thru 4 (Refer to Fig. A-FDDAB Sheet 01)

supplied in :

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 122

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Bundle A9000095320695

For aircraft using Kit A01R06, use

Bundle A9000095320695

supplied in Supplementary Kit A01S06

(c) Attach the wires with :

20 Tie-Cable NSA935401-03

(d) On Relay Box 104VU, do the electrical bonding (Refer to AMM 20-28-11) with :

Pure Mineral

Vaseline Or PetroLatum

04-012 As required

Electrical Bond

Varnish

07-001B As required

(e) Connect the bonding strip, install the screws, the clamps and the front box.

Reconnect and install the Relay Box 104VU

(7) Subtask 742003-831-006-002 - Modify the wiring in Zones

Work Zones and Access Panels

Zone Access/Work location

From 120

To 210

Manpower Resources

Manhours 8.00

Minimum number of person 2

Subtask elapsed time 4

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

EN3155-018M1616 1 PIN

EN3155-019F1616 1 CONTACT

NSA935401-05 100 TIE

NSA935401-13 100 TIE

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 123

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

EN3155-018M1616 PIN

EN3155-019F1616 CONTACT

References

Fig. A-FCFAB

Modification wiring in Zones

Sheet 01

Sheet 02

Fig. A-FDFAB

Hook-up Chart Zones

Sheet 01

(a) Install the wires as shown on the wiring diagram Fig. A-FCFAB Sheet 01 Fig. AFCFAB Sheet 02and as given in the Hook-up Chart lines :

- 1 thru 8 (Refer to Fig. A-FDFAB Sheet 01)

supplied in :

Bundle A9000095320695

with:

1 Contact-Socket EN3155-019F1616

1 Pin-Contact EN3155-018M1616

For aircraft using Kit A01R06, use

Bundle A9000095320695

supplied in Supplementary Kit A01S06

For aircraft using Kit A01R01 or Kit A01R03, use:

1 Pin-Contact EN3155-018M1616

1 Contact-Socket EN3155-019F1616

supplied in Supplementary Kit A01S05

(b) Attach the wires with :

100 Tie-Cable NSA935401-05

100 Tie-Cable NSA935401-13

(c) On aircraft, reconnect the three connectors FIN 1471VC, 1470VC, 1472VC.

(d) On aircraft, on overhead panel 20VU, reinstall the panel 429VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 124

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 008

(1) Subtask 742003-831-001-001 - Modify the Circuit Breaker panel 133VU

Work Zones and Access Panels

Zone Access/Work location

210

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A11321141C00 2 PLACARD

A9100095041095 PLCD SET

EN2995-004A03AA 2 CB

Supplementary kit 742003A01S05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A11321141C00 PLACARD

References

Aircraft Maintenance Manual (AMM) 24-50-20

Fig. A-FBBAB

Modification equipment in 133VU

Sheet 01

Fig. A-FBCAB

Modification Placard in 133VU

Sheet 01

(a) Inside panel 133VU, at position S69 and S74, install (Refer to AMM 24-50-20) :

FIN 13JH

1 Cb-Circuit Breaker EN2995-004A03AA

FIN 14JH

1 Cb-Circuit Breaker EN2995-004A03AA

(b) Inside panel 133VU, at position S69 and S74, install two new self-sticking labels

supplied in Fig. A-FBBAB Sheet 01:

Placard Set A9100095041095

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 125

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(c) On panel 133VU, in front of the two new Circuit Breakers, on the existing placard,

with a cutter, make two cut-out at position S69 and S74 so that you can insert the

two new self-sticking labels supplied in Fig. A-FBCAB Sheet 01:

2 Placard A11321141C00

For aircraft using Kit A01R03

2 Placard A11321141C00

supplied in Supplementary kit A01S05

NOTE: Adjust the size of the labels at assembly.

(2) Subtask 742003-831-002-001 - Modify the wiring in Circuit Breaker panel 133VU

Work Zones and Access Panels

Zone Access/Work location

210

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

NSA935401-03 20 TIE

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

References

Fig. A-FCAAA

Modification wiring in 133VU

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FDAAA

Hook-up Chart 133VU

Sheet 01

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 126

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(a) Remove the wires as shown on the wiring diagram Fig. A-FCAAA Sheet 01, Fig. AFCAAA Sheet 02, Fig. A-FCAAA Sheet 03, Fig. A-FCAAA Sheet 04 and as given in

the Hook-up Chart lines :

- 1 thru 6(Refer to Fig. A-FDAAA Sheet 01).

(b) Install the wires as shown on the wiring diagram Fig. A-FCAAA Sheet 01, Fig. AFCAAA Sheet 02, Fig. A-FCAAA Sheet 03, Fig. A-FCAAA Sheet 04 and as given in

the Hook-up Chart lines :

- 10 thru 21 (Refer to Fig. A-FDAAA Sheet 01)

supplied in :

Bundle A9000095320695

For aircraft using Kit A01R06, use

Bundle A9000095320695

supplied in Supplementary Kit A01S06

(c) Attach the wires with :

20 Tie-Cable NSA935401-03

(3) Subtask 742003-831-008-003 - Modify the equipment in the Relay Box 105VU on

bench

Work Zones and Access Panels

Zone Access/Work location

122

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 A9251133320000 1 PLATE

10 NAS1100-04-7 8 SCREW

11 MS21042-04 8 NUT

12 NAS1149FN416P 8 WASHER

A9100095041095 PLCD SET

ABS1416A120CJ 2 RELAY

E0247A0 2 BASE

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 127

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

E0666D28A0 2 RELAY

NSA932844CJ 2 SOCKET

NSA937901E0 1 LABEL

NSA937901E1 5 LABEL

NSA937901E7 1 LABEL

NSA937901E8 1 LABEL

NSA937901FM 1 MODULE

NSA937901M20-08 2 MODULE

NSA937901MA2004 2 MODULE

Supplementary kit 742003A01S01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NSA932844CJ 2 SOCKET

References

Aircraft Wiring List (AWL)

Fig. A-FBAAC

Modification equipment in 105VU

Sheet 01

(a) From the Relay Box 105VU, disconnect the bonding strip, remove the screws, the

clamps and the box front cover

NOTE: Disconnect the connectors and remove the Relay Box 105VU to get

access to the inside of the box.

Put blanking caps on the disconnected electrical connectors.

Reconnect and install all the removed components after

modification.

(b) On bench, install on plate Item 9 :

FIN 17JH

1 Relay E0666D28A0

FIN 18JH

1 Relay E0666D28A0

with

FIN 17JHA

1 Base E0247A0

FIN 18JHA

1 Base E0247A0

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 128

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(c) On bench, install (Refer to Fig. A-FBAAC Sheet 01) :

1 Plate A9251133320000 Item 9

with

4 Screw NAS1100-04-7 Item 10

4 Washer NAS1149FN416P Item 12

4 Nut MS21042-04 Item 11

(d) On bench, install (Refer to Fig. A-FBAAC Sheet 01) :

FIN 15JH

1 Relay ABS1416A120CJ

FIN 15JHA

1 Socket-Relay NSA932844CJ

For aircraft using Kit A01R01

FIN 15JHA

1 Socket-Relay NSA932844CJ

supplied in Supplementary kit A01S01

FIN 16JH

1 Relay ABS1416A120CJ

FIN 16JHA

1 Socket-Relay NSA932844CJ

For aircraft using Kit A01R01

FIN 16JHA

1 Socket-Relay NSA932844CJ

supplied in Supplementary kit A01S01

with

4 Screw NAS1100-04-7 Item 10

4 Washer NAS1149FN416P Item 12

4 Nut MS21042-04 Item 11

NOTE: For aircraft using Kit 742003A01R01 the socket relay P/N

NSA932844CJ is suplied in suplemental kit 742003A01S01

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 129

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(e) Close to new relays, affix placards supplied in :

Placard Set A9100095041095

(f) On the mounting rail 192VT, on modules position 10 and 11, disconnect wires as

per Aircraft Wiring List (AWL)

(g) On the mounting rail 192VT, remove from position 10 and 11 :

2 modules

(h) On the mounting rail 192VT, at position 10 and 11, install :

2 Module NSA937901MA2004

with

3 Label Identification NSA937901E1

1 Label Identification NSA937901E0

(i) On the mounting rail 192VT, on modules 10 and 11, reconnect wires as per Aircraft

Wiring List (AWL) only on contacts A, B ,F, G if there are existing wires.

(j) On the mounting rail 192VT, remove and retain from position 16 the end-module.

(k) On the mounting rail 192VT, at position 16, install :

1 Module-False NSA937901FM

(l) On the mounting rail 192VT, at position 17 and 18, install :

2 Module NSA937901M20-08

with

2 Label Identification NSA937901E1

1 Label Identification NSA937901E7

1 Label Identification NSA937901E8

(m) On the mounting rail 192VT, at position 19, install the end-module retained at

removal.

(4) Subtask 742003-831-007-002 - Modify the wiring in the Relay Box 105VU on bench

Manpower Resources

Manhours 8.00

Minimum number of person 1

Subtask elapsed time 8.00

Skills ELECTRICAL

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 130

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

NSA935401-05 100 TIE

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Pure Mineral Vaseline Or

Petro- Latum

04-012 As required

Electrical Bond Varnish 07-001B As required

References

Aircraft Maintenance Manual (AMM) 20-28-11

Fig. A-FCBAB

Modification wiring in 105VU

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FDBAB

Hook-up Chart 105VU

Sheet 01

Sheet 02

Sheet 03

(a) Remove the wires as shown on the wiring diagram Fig. A-FCBAB Sheet 01, Fig. AFCBAB Sheet 02, Fig. A-FCBAB Sheet 03, Fig. A-FCBAB Sheet 04 and as given in

the Hook-up Chart lines :

- 1 thru 14 (Refer to Fig. A-FDBAB Sheet 01)

(b) Install the wires as shown on the wiring diagram Fig. A-FCBAB Sheet 01, Fig. AFCBAB Sheet 02, Fig. A-FCBAB Sheet 03, Fig. A-FCBAB Sheet 04 and as given in

the Hook-up Chart lines :

- 1 thru 25 (Refer to Fig. A-FDBAB Sheet 02)

- 1 thru 13 (Refer to Fig. A-FDBAB Sheet 03)

supplied in :

Bundle A9000095320695

For aircraft using Kit A01R06, use

Bundle A9000095320695

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 131

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

supplied in Supplementary Kit A01S06

(c) Attach the wires with :

100 Tie-Cable NSA935401-05

(d) On the relay box 105VU, do the electrical bonding (Refer to AMM 20-28-11) with :

Pure Mineral

Vaseline Or PetroLatum

04-012 As required

Electrical Bond

Varnish

07-001B As required

(e) Connect the bonding strip, install the screws, the clamps and the front box.

Reconnect and install the Relay Box 105VU

(5) Subtask 742003-831-003-001 - Modify the Eng Start/APU/Wiper Panel 429VU

Work Zones and Access Panels

Zone Access/Work location

210

Manpower Resources

Manhours 10.00

Minimum number of person 1

Subtask elapsed time 10.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 A9251063000000 1 SUPPLATE

2 EN3646A02255AZ 1 CONNECTR

3 NSA937901RB0120 1 RAIL

4 NAS1100-06-7 3 SCREW

5 MS35333-37 3 WASHER

6 NAS1100-08-7 2 SCREW

7 NAS1149FN816P 2 WASHER

12 NAS1149FN416P 6 WASHER

13 NAS1100-04-6 6 SCREW

14 MS21042L04 6 NUT

A9000095320695 BUNDLE

EN3646A62255BZ 1 CONNECTR

NSA935401-03 20 TIE

NSA937901E9 1 LABEL

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 132

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NSA937901MA2011 1 MODULE

NSA938003-22 1 BACKSHLL

NSA938150-02-22 1 BACKSHLL

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

References

Aircraft Wiring List (AWL)

Fig. A-FBDAA

Modification equipment in 429VU

Sheet 01

Fig. A-FCCAA

Modification wiring in 429VU

Sheet 01

Sheet 02

Fig. A-FDCAA

Hook-up Chart 429VU

Sheet 01

(a) On overhead panel 20VU, remove the panel 429VU fixed with four fasteners

Disconnect the three connectors FIN 1470VC-A, 1471VC-A, 1472VC-A

(b) On bench, separate the three connectors from plate Item (1) (Refer to Fig. AFBDAA Sheet 01)

Discard associated hardware.

Separate all the modules and end-modules from the mounting rail 1347VT without

disconnection.

Separate the mounting rail 1347VT from plate Item (1)

Discard associated hardware.

(c) On bench, remove (Refer to Fig. A-FBDAA Sheet 01) :

1 Plate Item (1)

Discard associated hardware.

(d) On bench, install (Refer to Fig. A-FBDAA Sheet 01) :

1 Supplate-Rear Assy A9251063000000 Item 1

with

3 Screw NAS1100-06-7 Item 4

3 Washer-Lock MS35333-37 Item 5

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 133

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(e) From connector FIN 1471VC, disconnect all the wires as per Aircraft Wiring List

(AWL)

(f) Remove :

1 Connector Item (2)

Discard associated hardware.

(g) On plate Item 1, install :

FIN 1471VC

1 Connector EN3646A02255AZ Item 2

with

2 Screw NAS1100-04-6 Item 13

2 Nut MS21042L04 Item 14

2 Washer NAS1149FN416P Item 12

(h) Behind connector 1471VC, install :

1 Backshell-Connector NSA938003-22

(i) On connector FIN 1471VC, reconnect all the wires as per Aircraft Wiring List (AWL)

(j) On plate Item 1, install the two others connectors FIN 1470VC and 1472VC with :

4 Screw NAS1100-04-6 Item 13

4 Washer NAS1149FN416P Item 12

4 Nut MS21042L04 Item 14

(k) On plate Item 1, install :

FIN 1347VT

1 Rail NSA937901RB0120 Item 3

with

2 Screw NAS1100-08-7 Item 6

2 Washer NAS1149FN816P Item 7

(l) On the mounting rail 1347VT, reinstall all the modules and install in position 9 :

FIN 1347VT9

1 Module NSA937901MA2011

with

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 134

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

1 Label Identification NSA937901E9

(m) On the mounting rail 1347VT, reinstall the two end modules.

(n) Remove the wires as shown on the wiring diagram Fig. A-FCCAA Sheet 01Fig. AFCCAA Sheet 02 and as given in the Hook-up Chart lines :

- 1 thru 4 (Refer to Fig. A-FDCAA Sheet 01)

(o) Install the wires as shown on the wiring diagram Fig. A-FCCAA Sheet 01Fig. AFCCAA Sheet 02 and as given in the Hook-up Chart lines :

- 8 thru 19 (Refer to Fig. A-FDCAA Sheet 01)

supplied in :

Bundle A9000095320695

For aircraft using Kit A01R06, use

Bundle A9000095320695

supplied in Supplementary Kit A01S06

(p) Attach the wires with :

20 Tie-Cable NSA935401-03

(q) On aircraft, disconnect as per Aircraft Wiring List (AWL), all the wires connected to

connector FIN 1471VC-A.

(r) Replace the connector FIN 1471VC-A and back-shell by :

FIN 1471VCA

1 Connector-Plug EN3646A62255BZ

FIN 1471VCA1

1 Backshell-Connector NSA938150-02-22

(s) Reconnect as per Aircraft Wiring List (AWL), all the wires disconnected to

connector FIN 1471VC-A.

(6) Subtask 742003-831-004-001 - Modify the Relay Box 104VU on bench

Work Zones and Access Panels

Zone Access/Work location

120

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 135

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

NSA935401-03 20 TIE

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Pure Mineral Vaseline Or

Petro- Latum

04-012 As required

Electrical Bond Varnish 07-001B As required

References

Aircraft Maintenance Manual (AMM) 20-28-11

Fig. A-FCDAA

Modification wiring in 104VU

Sheet 01

Fig. A-FDDAA

Hook-up Chart 104VU

Sheet 01

(a) From the Relay Box 104VU, disconnect the bonding strip, remove the screws, the

clamps and the box front cover

NOTE: Disconnect the connectors and remove the Relay Box 104VU to get

access to the inside of the box.

Put blanking caps on the disconnected electrical connectors.

Reconnect and install all the removed components after

modification.

(b) Install the wires as shown on the wiring diagram Fig. A-FCDAA Sheet 01 and as

given in the Hook-up Chart lines :

- 1 thru 2 (Refer to Fig. A-FDDAA Sheet 01)

supplied in :

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 136

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Bundle A9000095320695

For aircraft using Kit A01R06, use

Bundle A9000095320695

supplied in Supplementary Kit A01S06

(c) Attach the wires with :

20 Tie-Cable NSA935401-03

(d) On Relay Box 104VU, do the electrical bonding (Refer to AMM 20-28-11) with :

Pure Mineral

Vaseline Or PetroLatum

04-012 As required

Electrical Bond

Varnish

07-001B As required

(e) Connect the bonding strip, install the screws, the clamps and the front box.

Reconnect and install the Relay Box 104VU

(7) Subtask 742003-831-005-001 - Modify the Electronics Rack 80VU

Work Zones and Access Panels

Zone Access/Work location

121

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

NSA935401-03 20 TIE

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 137

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

References

Fig. A-FCEAA

Modification wiring in 80VU

Sheet 01

Fig. A-FDEAA

Hook-up Chart 80VU

Sheet 01

(a) Install the wires as shown on the wiring diagram Fig. A-FCEAA Sheet 01 and as

given in the Hook-up Chart lines :

- 1 thru 2 (Refer to Fig. A-FDEAA Sheet 01)

supplied in :

Bundle A9000095320695

For aircraft using Kit A01R06, use

Bundle A9000095320695

supplied in Supplementary Kit A01S06

(b) Attach the wires with :

20 Tie-Cable NSA935401-03

(8) Subtask 742003-831-006-001 - Modify the wiring in Zones

Work Zones and Access Panels

Zone Access/Work location

From 120

To 210

Manpower Resources

Manhours 8.00

Minimum number of person 2

Subtask elapsed time 4.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

EN3155-018M1616 1 PIN

EN3155-019F1616 1 CONTACT

NSA935401-05 100 TIE

NSA935401-13 100 TIE

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 138

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

EN3155-018M1616 PIN

EN3155-019F1616 1 CONTACT

References

Fig. A-FCFAA

Modification wiring in Zones

Sheet 01

Sheet 02

Fig. A-FDFAA

Hook-up Chart Zones

Sheet 01

Fig. A-FBEAA

Routing

Sheet 01

(a) Install the wires as shown on the wiring diagram Fig. A-FCFAA Sheet 01Fig. AFCFAA Sheet 02 and as given in the Hook-up Chart lines :

- 1 thru 9 (Refer to Fig. A-FDFAA Sheet 01)

supplied in :

Bundle A9000095320695

with:

1 Contact-Socket EN3155-019F1616

1 Pin-Contact EN3155-018M1616

For aircraft using Kit A01R06, use

Bundle A9000095320695

supplied in Supplementary Kit A01S06

For aircraft using Kit A01R01 or Kit A01R03, use:

1 Pin-Contact EN3155-018M1616

1 Contact-Socket EN3155-019F1616

supplied in Supplementary Kit A01S05

(b) Attach the wires with :

100 Tie-Cable NSA935401-05

100 Tie-Cable NSA935401-13

(c) On aircraft, reconnect the three connectors FIN 1471VC, 1470VC, 1472VC.

(d) On aircraft, on overhead panel 20VU, reinstall the panel 429VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 139

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 009

(1) Subtask 742003-831-001-001 - Modify the Circuit Breaker panel 133VU

Work Zones and Access Panels

Zone Access/Work location

210

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A11321141C00 2 PLACARD

A9100095041095 PLCD SET

EN2995-004A03AA 2 CB

Supplementary kit 742003A01S05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A11321141C00 PLACARD

References

Aircraft Maintenance Manual (AMM) 24-50-20

Fig. A-FBBAB

Modification equipment in 133VU

Sheet 01

Fig. A-FBCAB

Modification Placard in 133VU

Sheet 01

(a) Inside panel 133VU, at position S69 and S74, install (Refer to AMM 24-50-20) :

FIN 13JH

1 Cb-Circuit Breaker EN2995-004A03AA

FIN 14JH

1 Cb-Circuit Breaker EN2995-004A03AA

(b) Inside panel 133VU, at position S69 and S74, install two new self-sticking labels

supplied in Fig. A-FBBAB Sheet 01:

Placard Set A9100095041095

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 140

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(c) On panel 133VU, in front of the two new Circuit Breakers, on the existing placard,

with a cutter, make two cut-out at position S69 and S74 so that you can insert the

two new self-sticking labels supplied in Fig. A-FBCAB Sheet 01:

2 Placard A11321141C00

For aircraft using Kit A01R03

2 Placard A11321141C00

supplied in Supplementary kit A01S05

NOTE: Adjust the size of the labels at assembly.

(2) Subtask 742003-831-002-001 - Modify the wiring in Circuit Breaker panel 133VU

Work Zones and Access Panels

Zone Access/Work location

210

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

NSA935401-03 20 TIE

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

References

Fig. A-FCAAA

Modification wiring in 133VU

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FDAAA

Hook-up Chart 133VU

Sheet 01

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 141

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(a) Remove the wires as shown on the wiring diagram Fig. A-FCAAA Sheet 01, Fig. AFCAAA Sheet 02, Fig. A-FCAAA Sheet 03, Fig. A-FCAAA Sheet 04 and as given in

the Hook-up Chart lines :

- 1 thru 6(Refer to Fig. A-FDAAA Sheet 01).

(b) Install the wires as shown on the wiring diagram Fig. A-FCAAA Sheet 01, Fig. AFCAAA Sheet 02, Fig. A-FCAAA Sheet 03, Fig. A-FCAAA Sheet 04 and as given in

the Hook-up Chart lines :

- 10 thru 21 (Refer to Fig. A-FDAAA Sheet 01)

supplied in :

Bundle A9000095320695

For aircraft using Kit A01R06, use

Bundle A9000095320695

supplied in Supplementary Kit A01S06

(c) Attach the wires with :

20 Tie-Cable NSA935401-03

(3) Subtask 742003-831-008-007 - Modify the equipment in the Relay Box 105VU on

bench

Work Zones and Access Panels

Zone Access/Work location

122

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 A9251133320000 1 PLATE

10 NAS1100-04-7 8 SCREW

11 MS21042-04 8 NUT

12 NAS1149FN416P 8 WASHER

A9100095041095 PLCD SET

ABS1416A120CJ 2 RELAY

E0247A0 2 BASE

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 142

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

E0666D28A0 2 RELAY

NSA932844CJ 2 SOCKET

NSA937901E0 1 LABEL

NSA937901E1 5 LABEL

NSA937901E7 1 LABEL

NSA937901E8 1 LABEL

NSA937901FM 1 MODULE

NSA937901M20-08 2 MODULE

NSA937901MA2004 2 MODULE

Supplementary kit 742003A01S01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NSA932844CJ 2 SOCKET

References

Aircraft Wiring List (AWL)

Fig. A-FBAAF

Modification equipment in 105VU

Sheet 01

(a) From the Relay Box 105VU, disconnect the bonding strip, remove the screws, the

clamps and the box front cover

NOTE: Disconnect the connectors and remove the Relay Box 105VU to get

access to the inside of the box.

Put blanking caps on the disconnected electrical connectors.

Reconnect and install all the removed components after

modification.

(b) On bench, install on plate Item 9 :

FIN 17JH

1 Relay E0666D28A0

FIN 18JH

1 Relay E0666D28A0

with

FIN 17JHA

1 Base E0247A0

FIN 18JHA

1 Base E0247A0

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 143

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(c) On bench, install (Refer to Fig. A-FBAAF Sheet 01) :

1 Plate A9251133320000 Item 9

with

4 Screw NAS1100-04-7 Item 10

4 Washer NAS1149FN416P Item 12

4 Nut MS21042-04 Item 11

(d) On bench, install (Refer to Fig. A-FBAAF Sheet 01) :

FIN 15JH

1 Relay ABS1416A120CJ

FIN 15JHA

1 Socket-Relay NSA932844CJ

For aircraft using Kit A01R01

FIN 15JHA

1 Socket-Relay NSA932844CJ

supplied in Supplementary kit A01S01

FIN 16JH

1 Relay ABS1416A120CJ

FIN 16JHA

1 Socket-Relay NSA932844CJ

For aircraft using Kit A01R01

FIN 16JHA

1 Socket-Relay NSA932844CJ

supplied in Supplementary kit A01S01

with

4 Screw NAS1100-04-7 Item 10

4 Washer NAS1149FN416P Item 12

4 Nut MS21042-04 Item 11

NOTE: For aircraft using Kit 742003A01R01 the socket relay P/N

NSA932844CJ is suplied in suplemental kit 742003A01S01

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 144

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(e) Close to new relays, affix placards supplied in :

Placard Set A9100095041095

(f) On the mounting rail 192VT, on modules position 10 and 11, disconnect wires as

per Aircraft Wiring List (AWL)

(g) On the mounting rail 192VT, remove from position 10 and 11 :

2 modules

(h) On the mounting rail 192VT, at position 10 and 11, install :

2 Module NSA937901MA2004

with

3 Label Identification NSA937901E1

1 Label Identification NSA937901E0

(i) On the mounting rail 192VT, on modules 10 and 11, reconnect wires as per Aircraft

Wiring List (AWL) only on contacts A, B ,F, G if there are existing wires.

(j) On the mounting rail 192VT, remove and retain from position 16 the end-module.

(k) On the mounting rail 192VT, at position 16, install :

1 Module-False NSA937901FM

(l) On the mounting rail 192VT, at position 17 and 18, install :

2 Module NSA937901M20-08

with

2 Label Identification NSA937901E1

1 Label Identification NSA937901E7

1 Label Identification NSA937901E8

(m) On the mounting rail 192VT, at position 19, install the end-module retained at

removal.

(4) Subtask 742003-831-007-002 - Modify the wiring in the Relay Box 105VU on bench

Manpower Resources

Manhours 8.00

Minimum number of person 1

Subtask elapsed time 8.00

Skills ELECTRICAL

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 145

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

NSA935401-05 100 TIE

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Pure Mineral Vaseline Or

Petro- Latum

04-012 As required

Electrical Bond Varnish 07-001B As required

References

Aircraft Maintenance Manual (AMM) 20-28-11

Fig. A-FCBAB

Modification wiring in 105VU

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FDBAB

Hook-up Chart 105VU

Sheet 01

Sheet 02

Sheet 03

(a) Remove the wires as shown on the wiring diagram Fig. A-FCBAB Sheet 01, Fig. AFCBAB Sheet 02, Fig. A-FCBAB Sheet 03, Fig. A-FCBAB Sheet 04 and as given in

the Hook-up Chart lines :

- 1 thru 14 (Refer to Fig. A-FDBAB Sheet 01)

(b) Install the wires as shown on the wiring diagram Fig. A-FCBAB Sheet 01, Fig. AFCBAB Sheet 02, Fig. A-FCBAB Sheet 03, Fig. A-FCBAB Sheet 04 and as given in

the Hook-up Chart lines :

- 1 thru 25 (Refer to Fig. A-FDBAB Sheet 02)

- 1 thru 13 (Refer to Fig. A-FDBAB Sheet 03)

supplied in :

Bundle A9000095320695

For aircraft using Kit A01R06, use

Bundle A9000095320695

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 146

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

supplied in Supplementary Kit A01S06

(c) Attach the wires with :

100 Tie-Cable NSA935401-05

(d) On the relay box 105VU, do the electrical bonding (Refer to AMM 20-28-11) with :

Pure Mineral

Vaseline Or PetroLatum

04-012 As required

Electrical Bond

Varnish

07-001B As required

(e) Connect the bonding strip, install the screws, the clamps and the front box.

Reconnect and install the Relay Box 105VU

(5) Subtask 742003-831-003-001 - Modify the Eng Start/APU/Wiper Panel 429VU

Work Zones and Access Panels

Zone Access/Work location

210

Manpower Resources

Manhours 10.00

Minimum number of person 1

Subtask elapsed time 10.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 A9251063000000 1 SUPPLATE

2 EN3646A02255AZ 1 CONNECTR

3 NSA937901RB0120 1 RAIL

4 NAS1100-06-7 3 SCREW

5 MS35333-37 3 WASHER

6 NAS1100-08-7 2 SCREW

7 NAS1149FN816P 2 WASHER

12 NAS1149FN416P 6 WASHER

13 NAS1100-04-6 6 SCREW

14 MS21042L04 6 NUT

A9000095320695 BUNDLE

EN3646A62255BZ 1 CONNECTR

NSA935401-03 20 TIE

NSA937901E9 1 LABEL

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 147

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NSA937901MA2011 1 MODULE

NSA938003-22 1 BACKSHLL

NSA938150-02-22 1 BACKSHLL

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

References

Aircraft Wiring List (AWL)

Fig. A-FBDAA

Modification equipment in 429VU

Sheet 01

Fig. A-FCCAA

Modification wiring in 429VU

Sheet 01

Sheet 02

Fig. A-FDCAA

Hook-up Chart 429VU

Sheet 01

(a) On overhead panel 20VU, remove the panel 429VU fixed with four fasteners

Disconnect the three connectors FIN 1470VC-A, 1471VC-A, 1472VC-A

(b) On bench, separate the three connectors from plate Item (1) (Refer to Fig. AFBDAA Sheet 01)

Discard associated hardware.

Separate all the modules and end-modules from the mounting rail 1347VT without

disconnection.

Separate the mounting rail 1347VT from plate Item (1)

Discard associated hardware.

(c) On bench, remove (Refer to Fig. A-FBDAA Sheet 01) :

1 Plate Item (1)

Discard associated hardware.

(d) On bench, install (Refer to Fig. A-FBDAA Sheet 01) :

1 Supplate-Rear Assy A9251063000000 Item 1

with

3 Screw NAS1100-06-7 Item 4

3 Washer-Lock MS35333-37 Item 5

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 148

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(e) From connector FIN 1471VC, disconnect all the wires as per Aircraft Wiring List

(AWL)

(f) Remove :

1 Connector Item (2)

Discard associated hardware.

(g) On plate Item 1, install :

FIN 1471VC

1 Connector EN3646A02255AZ Item 2

with

2 Screw NAS1100-04-6 Item 13

2 Nut MS21042L04 Item 14

2 Washer NAS1149FN416P Item 12

(h) Behind connector 1471VC, install :

1 Backshell-Connector NSA938003-22

(i) On connector FIN 1471VC, reconnect all the wires as per Aircraft Wiring List (AWL)

(j) On plate Item 1, install the two others connectors FIN 1470VC and 1472VC with :

4 Screw NAS1100-04-6 Item 13

4 Washer NAS1149FN416P Item 12

4 Nut MS21042L04 Item 14

(k) On plate Item 1, install :

FIN 1347VT

1 Rail NSA937901RB0120 Item 3

with

2 Screw NAS1100-08-7 Item 6

2 Washer NAS1149FN816P Item 7

(l) On the mounting rail 1347VT, reinstall all the modules and install in position 9 :

FIN 1347VT9

1 Module NSA937901MA2011

with

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 149

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

1 Label Identification NSA937901E9

(m) On the mounting rail 1347VT, reinstall the two end modules.

(n) Remove the wires as shown on the wiring diagram Fig. A-FCCAA Sheet 01Fig. AFCCAA Sheet 02 and as given in the Hook-up Chart lines :

- 1 thru 4 (Refer to Fig. A-FDCAA Sheet 01)

(o) Install the wires as shown on the wiring diagram Fig. A-FCCAA Sheet 01Fig. AFCCAA Sheet 02 and as given in the Hook-up Chart lines :

- 8 thru 19 (Refer to Fig. A-FDCAA Sheet 01)

supplied in :

Bundle A9000095320695

For aircraft using Kit A01R06, use

Bundle A9000095320695

supplied in Supplementary Kit A01S06

(p) Attach the wires with :

20 Tie-Cable NSA935401-03

(q) On aircraft, disconnect as per Aircraft Wiring List (AWL), all the wires connected to

connector FIN 1471VC-A.

(r) Replace the connector FIN 1471VC-A and back-shell by :

FIN 1471VCA

1 Connector-Plug EN3646A62255BZ

FIN 1471VCA1

1 Backshell-Connector NSA938150-02-22

(s) Reconnect as per Aircraft Wiring List (AWL), all the wires disconnected to

connector FIN 1471VC-A.

(6) Subtask 742003-831-004-001 - Modify the Relay Box 104VU on bench

Work Zones and Access Panels

Zone Access/Work location

120

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 150

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

NSA935401-03 20 TIE

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Pure Mineral Vaseline Or

Petro- Latum

04-012 As required

Electrical Bond Varnish 07-001B As required

References

Aircraft Maintenance Manual (AMM) 20-28-11

Fig. A-FCDAA

Modification wiring in 104VU

Sheet 01

Fig. A-FDDAA

Hook-up Chart 104VU

Sheet 01

(a) From the Relay Box 104VU, disconnect the bonding strip, remove the screws, the

clamps and the box front cover

NOTE: Disconnect the connectors and remove the Relay Box 104VU to get

access to the inside of the box.

Put blanking caps on the disconnected electrical connectors.

Reconnect and install all the removed components after

modification.

(b) Install the wires as shown on the wiring diagram Fig. A-FCDAA Sheet 01 and as

given in the Hook-up Chart lines :

- 1 thru 2 (Refer to Fig. A-FDDAA Sheet 01)

supplied in :

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 151

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Bundle A9000095320695

For aircraft using Kit A01R06, use

Bundle A9000095320695

supplied in Supplementary Kit A01S06

(c) Attach the wires with :

20 Tie-Cable NSA935401-03

(d) On Relay Box 104VU, do the electrical bonding (Refer to AMM 20-28-11) with :

Pure Mineral

Vaseline Or PetroLatum

04-012 As required

Electrical Bond

Varnish

07-001B As required

(e) Connect the bonding strip, install the screws, the clamps and the front box.

Reconnect and install the Relay Box 104VU

(7) Subtask 742003-831-005-001 - Modify the Electronics Rack 80VU

Work Zones and Access Panels

Zone Access/Work location

121

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

NSA935401-03 20 TIE

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 152

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

References

Fig. A-FCEAA

Modification wiring in 80VU

Sheet 01

Fig. A-FDEAA

Hook-up Chart 80VU

Sheet 01

(a) Install the wires as shown on the wiring diagram Fig. A-FCEAA Sheet 01 and as

given in the Hook-up Chart lines :

- 1 thru 2 (Refer to Fig. A-FDEAA Sheet 01)

supplied in :

Bundle A9000095320695

For aircraft using Kit A01R06, use

Bundle A9000095320695

supplied in Supplementary Kit A01S06

(b) Attach the wires with :

20 Tie-Cable NSA935401-03

(8) Subtask 742003-831-006-001 - Modify the wiring in Zones

Work Zones and Access Panels

Zone Access/Work location

From 120

To 210

Manpower Resources

Manhours 8.00

Minimum number of person 2

Subtask elapsed time 4.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A01R07

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

EN3155-018M1616 1 PIN

EN3155-019F1616 1 CONTACT

NSA935401-05 100 TIE

NSA935401-13 100 TIE

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 153

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Supplementary kit 742003A01S06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320695 BUNDLE

EN3155-018M1616 PIN

EN3155-019F1616 1 CONTACT

References

Fig. A-FCFAA

Modification wiring in Zones

Sheet 01

Sheet 02

Fig. A-FDFAA

Hook-up Chart Zones

Sheet 01

Fig. A-FBEAA

Routing

Sheet 01

(a) Install the wires as shown on the wiring diagram Fig. A-FCFAA Sheet 01Fig. AFCFAA Sheet 02 and as given in the Hook-up Chart lines :

- 1 thru 9 (Refer to Fig. A-FDFAA Sheet 01)

supplied in :

Bundle A9000095320695

with:

1 Contact-Socket EN3155-019F1616

1 Pin-Contact EN3155-018M1616

For aircraft using Kit A01R06, use

Bundle A9000095320695

supplied in Supplementary Kit A01S06

For aircraft using Kit A01R01 or Kit A01R03, use:

1 Pin-Contact EN3155-018M1616

1 Contact-Socket EN3155-019F1616

supplied in Supplementary Kit A01S05

(b) Attach the wires with :

100 Tie-Cable NSA935401-05

100 Tie-Cable NSA935401-13

(c) On aircraft, reconnect the three connectors FIN 1471VC, 1470VC, 1472VC.

(d) On aircraft, on overhead panel 20VU, reinstall the panel 429VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 154

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

D. TEST

**CONF 001

(1) Subtask 742003-720-001-001 - Test

Manpower Resources

Skills ELECTRICAL

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 155

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 20-28-11, Page Block 001

21-21-00, Page Block 501

21-22-00, Page Block 501

21-23-12, Page Block 401

21-31-11, Page Block 401

22-18-34, Page Block 401

22-36-34, Page Block 401

22-40-00, Page Block 501

23-12-00, Page Block 501

23-71-12, Page Block 401

24-22-15, Page Block 401

24-23-13, Page Block 401

24-31-11, Page Block 401

24-41-00, Page Block 301

26-12-20, Page Block 401

26-12-20, Page Block 501

26-13-20, Page Block 401

26-13-20, Page Block 401

28-22-55, Page Block 401

28-24-31, Page Block 401

28-25-17, Page Block 401

28-28-12, Page Block 401

28-42-38, Page Block 401

28-42-41, Page Block 401

30-45-00, Page Block 501

31-10-00, Page Block 201

31-51-00, Page Block 501

31-69-00, Page Block 501

32-31-11, Page Block 401

33-12-00, Page Block 501

33-12-11, Page Block 401

33-13-00, Page Block 501

33-14-00, Page Block 501

33-46-00, Page Block 501

34-25-00, Page Block 501

34-44-34, Page Block 401

34-68-34, Page Block 401

34-73-34, Page Block 401

36-11-00, Page Block 501

36-11-19, Page Block 401

49-10-00, Page Block 501

49-31-00, Page Block 501

52-51-00, Page Block 501

71-00-00, Page Block 501

71-13-00, Page Block 301

74-00-00, Page Block 501

77-12-21, Page Block 401

Elec. Std. Practices Manual (ESPM) 20-46-50

20-52-10

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 156

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(a) Job Set-up

1 Battery re-connection

- For Job Set-up, refer to Installation of the Batteries (Refer to AMM

24-31-11, Page Block 401)

- Remove the blanking cap from the electrical connectors

- Make sure that the electrical connectors are clean and in correct condition

- Connect the connector on the battery

- Turn the knurled nut a quarter turn

2 Remove all warning notices.

3 Open, safety/lock and tag this (these) circuit breaker(s):

PANEL DESIGNATION FIN LOCATION SEE

NOTES

133 ENGINE 1/FUEL HP

VALVE/WARN

1KC T68

133 ENGINE 2/FUEL HP

VALVE/WARN

2KC R73

133 ENGINE 1/AUTORELIGHT 13JH S69

133 ENGINE 2/AUTORELIGHT 14JH S74

133 STBY GEN AIR VALVE 17XE T83

133 ENGINE 1/LO/PRESS 1ES Q69

4 Energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page Block

301)

5 Do a voltage check at pin 1 of each following circuit breaker to make sure that

there is 28VDC.

PANEL DESIGNATION FIN LOCATION SEE

NOTES

133 ENGINE 1/FUEL HP

VALVE/WARN

1KC T68

133 ENGINE 2/FUEL HP

VALVE/WARN

2KC R73

133 ENGINE 1/AUTORELIGHT 13JH S69

133 ENGINE 2/AUTORELIGHT 14JH S74

133 STBY GEN AIR VALVE 17XE T83

133 ENGINE 1/LO/PRESS 1ES Q69

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 157

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

6 Remove the safety clip(s) and/or tag(s) and close/unlock this (these) circuit

breaker(s):

PANEL DESIGNATION FIN LOCATION SEE

NOTES

133 ENGINE 1/FUEL HP

VALVE/WARN

1KC T68

133 ENGINE 2/FUEL HP

VALVE/WARN

2KC R73

133 ENGINE 1/AUTORELIGHT 13JH S69

133 ENGINE 2/AUTORELIGHT 14JH S74

133 STBY GEN AIR VALVE 17XE T83

133 ENGINE 1/LO/PRESS 1ES Q69

7 Preliminary Tests :

NOTE: If the aircraft is operated in CAT3 conditions, you must also do

the LAND test (Refer to AMM 22-40-00, Page Block 501)

a On each connector which was disconnected:

- Do the checks as defined by ESPM 20-52-10.

NOTE: The Functional test and/or operational test requested by

this ESPM procedure is given hereafter.

b Do the Operational Test of the Annunciator Light Test AMM (Refer to

AMM 33-14-00, Page Block 501).

c Do the Operational Test of the General Illumination, (Refer to AMM

33-12-00, Page Block 501).

d Do the Operational Test of the Instrument and Panel Integral Lighting,

(Refer to AMM 33-13-00, Page Block 501).

e Make certain that the ventillation system operates correctly, (Refer to

AMM 21-21-00, Page Block 501).

f Do the AFS (Automatic Flight System) Test, (Refer to AMM 22-40-00,

Page Block 501)(para 1.A)).

g Do the Operational Test of ECAM/EFIS Display Test, (Refer to AMM

31-51-00, Page Block 501).

h Do the Operational Test of the FWC1 and FWC2, (Refer to AMM

31-51-00, Page Block 501).

(b) Test

1 Procedure

a Do the Operational Test of the circuit breaker monitoring system for panel

133VU (Refer to AMM 31-69-00, Page Block 501).

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 158

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

b Do the tests program after R/I of the panel 20VU:

<1> Do the test procedure as specified after the installation of the FUEL

QUANTITY INDICATOR (6QT), (Refer to AMM 28-42-41, Page

Block 401)

<2> Do the tests program after R/I of the Panel 45VU, (Refer to AMM

31-10-00, Page Block 201)

<3> Do the tests program after R/I of the Panel 76VU (Refer to AMM

31-10-00, Page Block 201)

<4> Do the tests program after R/I of the Panel 424VU (Refer to AMM

31-10-00, Page Block 201)

<5> Do the tests program after R/I of the Panel 425VU (Refer to AMM

31-10-00, Page Block 201)

<6> Do the tests program after R/I of the Panel 430VU (Refer to AMM

31-10-00, Page Block 201)

<7> Do the tests program after R/I of the Panel 433VU (Refer to AMM

31-10-00, Page Block 201)

<8> Do the tests program after R/I of the Panel 435VU (Refer to AMM

31-10-00, Page Block 201)

<9> Do the tests program after R/I of the Panel 438VU (Refer to AMM

31-10-00, Page Block 201)

<10>Do the tests program after R/I of the Panel 431VU (Refer to AMM

31-10-00, Page Block 201)

<11>Do the test of alignment procedure up to step 4 as described in the

IRS operational test (Refer to AMM 34-25-00, Page Block 501) for

each mode selector unit which has been removed for access

<12>Do the test procedure as specified after the installation of the

Cockpit Voice Recorder control unit (1RK) (Refer to AMM 23-71-12,

Page Block 401)

<13>Do the test procedure as specified after the installation of the APU

FIRE CONTROL MODULE (20WG) (Refer to AMM 26-13-20, Page

Block 401)

<14>Do the test procedure as specified after the installation of the

Engine Fire Control Module (39WD) (Refer to AMM 26-12-20, Page

Block 401)

<15>Do the O/T of the VHF3 system (Refer to AMM 23-12-00, Page

Block 501)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 159

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

<16>If CDSS is active for A/C, do the "Operational test of Video

Monitoring System", NOTE: If the SB reference is not specified in

the latest operator’s AMM issue, do these steps:

<a> Job Set-Up

[1] Connect the electrical ground power unit and energize the

aircraft electrical network (Refer to AMM 24-41-00, Page

Block 301).

[2] Make certain that the electronic rack ventilation is correct.

[3] Make certain that the following circuit breaker is closed:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

132VU CKPT/DOOR VIDEO/SPLY 15RA

<b> 2 Operational test of the Video Monitoring System

ACTION RESULT

1. In the cockpit, on panel 512VU:

- push the ’CKPT DOOR VIDEO’ pushbutton

switch

In the cockpit:

- the OFF legend in the ’CKPT DOOR VIDEO’

pushbutton switch goes off.

In the cockpit on the LCD:

- the green LED comes on

- the LCD monitor shows the images from camera

1.

2. In the cockpit, on panel 119VU:

- push the ’VIDEO’ pushbutton one time.

In the cockpit,on the LCD monitor:

- the left half of the LCD monitor screen shows

the images from camera 2

- the right half of the LCD monitor screen shows

the images of camera 3.

3. In the Cockpit, on the panel 119VU:

- push the ’VIDEO’ pushbutton one time.

In the cockpit,on the LCD monitor:

- the LCD monitor shows the images from camera

1.

4. In the cockpit, on the LCD monitor:

- turn the LCD monitor brightness knob clockwise

then counter-clockwise.

In the cockpit,on the LCD monitor:

- the brightness of the images change.

5. In the cockpit, on the LCD monitor:

- turn the LCD monitor contrast knob clockwise

then counter-clockwise.

In the cockpit, on the LCD monitor:

- the contrast of the images change.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 160

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

ACTION RESULT

6. In the cockpit, on the LCD monitor:

- turn the brightness and the contrast knobs to

their center positions.

7. In the cockpit, on the LCD monitor:

- use a flashlight to increase the light on the light

sensor, switch the flashlight on.

In the cockpit,on the LCD monitor:

- the brightness of the images change.

8. In the cockpit, on the LCD monitor:

- decrease the light on the light sensor, switch the

flashlight off.

In the cockpit,on the LCD monitor:

- the brightness of the images change.

9. In the cockpit, on panel 119VU:

- push the ’VIDEO’ pushbutton one time.

In the cockpit,on the LCD monitor:

- the left half of the LCD monitor screen shows

the images from camera 2

- the right half of the LCD monitor screen shows

the images from camera 3

- after five minutes the images go off (Stand-by

mode).

10. In the cockpit, on the panel 119VU:

- before the images on the LCD monitor go off for

30 seconds, push the ’VIDEO’ pushbutton one

time.

In the cockpit,on the LCD monitor:

- the images from camera 2 and camera 3 are

shown(split screen).

- after 5 minutes,the images go off (power-down

mode).

11. In the cockpit entrance area on the keypad

25MQ:

- enter the code to request entry to the cockpit

(Refer to AMM 52-51-00, Page Block 501).

In the cockpit:

- the horn is heard

- on the LCD monitor the image from camera 1 is

shown.

12. In the cockpit on the panel 119VU:

- push the ’VIDEO’ pushbutton one time.

In the cockpit on the LCD monitor:

- the images from camera 2 and 3 are shown

(split screen).

13. In the cockpit entrance area, on the keypad

25MQ:

- after the images from camera 2 and camera 3

are shown on the LCD monitor and before 29

seconds request entry to the cockpit.

In the cockpit on the LCD monitor:

- the images from camera 2 and camera 3 are

shown (split screen).

14. In the cockpit, on the panel 119VU:

- push the ’VIDEO’ pushbutton one time.

In the cockpit,on the LCD monitor:

- the image from camera 1 is shown.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 161

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

ACTION RESULT

15. In the cockpit on the panel 512VU:

- push the ’CKPT DOOR VIDEO’ pushbutton

switch.

In the cockpit on the panel 512VU:

- the ’OFF’ legend in the ’CKPT DOOR VIDEO’

pushbutton switch comes on.

In the cockpit on the LCD monitor:

- the green LED goes off

- the screen goes off.

<c> Close-Up

[1] De-energize the AC-External Power Control (Refer to

AMM 24-41-00, Page Block 301).

[2] Make sure that the work area is clean and clear of tools

and miscellaneous items of equipment.

<17>Do the O/T of the CDLS (Refer to AMM 52-51-00, Page Block 501)

c Do the tests program after R/I of the panel 104VU:

<1> Do a check of the Electrical Bonding (Refer to AMM 20-28-11, Page

Block 001)

NOTE: For maximun permissible resistance values: Refer to

the Table (Refer to AMM 20-28-11, Page Block 001)

<2> Do the test procedure as specified after the installation of the TRIM

TANK ISOLATION VALVE ACTUATOR (48QB), (Refer to AMM

28-22-55, Page Block 401)

<3> Do the test procedure as specified after the installation of the

INBOARD EXTRACT VALVE (74HR), (Refer to AMM 21-23-12,

Page Block 401)

<4> Do the test procedure as specified after the installation of the EFIS

SGU (28FN1, 28FN2, 28FN3), (Refer to AMM 34-73-34, Page Block

401)

<5> Do the test procedure as specified after the installation of the APU

GEN PWR LINE CONTACTOR 3XS, (Refer to AMM 24-23-13, Page

Block 401)

<6> Do the test procedure as specified after the installation of the FUEL

QUANTITY COMPUTER (15QT), (Refer to AMM 28-42-38, Page

Block 401)

<7> Do the test procedure as specified after the installation of the

TRANSFER VALVE ACTUATOR, (Refer to AMM 28-25-17, Page

Block 401) (if equipped)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 162

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

<8> Do the test procedure as specified after the installation of the

ACTUATOR - SELECTOR VALVE, (Refer to AMM 28-28-12, Page

Block 401) (if equipped)

<9> Do the test procedure as specified after the installation of the GEN 1

(2) LINE CONTACTOR 9XU (10XU), (Refer to AMM 24-22-15, Page

Block 401)

<10>Do the test procedure as specified after the installation of the

CABIN PRESSURE CONTROLLER 105HM (106HM), (Refer to

AMM 21-31-11, Page Block 401)

<11>Do the test procedure as specified after the installation of

the PNEUMATIC CONTROLLER 41HA (42HA), (Refer to AMM

36-11-19, Page Block 401) (if equipped)

<12>Do the test procedure as specified after the installation of the APU

FIRE CONTROL MODULE, (Refer to AMM 26-13-20, Page Block

401)

<13>Do the test procedure as specified after the installation of the

FLIGHT CONTROL COMPUTER (301CA1, 301CA2), (Refer to AMM

22-18-34, Page Block 401)

<14>Do the test procedure as specified after the installation of

the LANDING GEAR NORMAL CONTROL MICROSWITCH UNIT

(2GA), (Refer to AMM 32-31-11, Page Block 401)

d Do the tests program after R/I of the panel 105VU:

<1> Do a check of the Electrical Bonding (Refer to AMM 20-28-11, Page

Block 001)

NOTE: For maximun permissible resistance values: Refer to

the Table (Refer to AMM 20-28-11, Page Block 001)

<2> Do the Perform BITE test (Refer to AMM 36-11-00, Page Block

501), (Operational Test)

<3> Do the test procedure as specified after the installation of the

FLIGHT MANAGEMENT COMPUTER (1CK1, 1CK2), (Refer to

AMM 34-68-34, Page Block 401) (if equipped)

<4> Do the Functional Test - ENGINE FIRE CONTROL MODULE, (Refer

to AMM 26-12-20, Page Block 501)

<5> Do the test procedure as specified after the installation of the TCAS

COMPUTER (9005SG), (Refer to AMM 34-44-34, Page Block 401)

(if equipped)

<6> Do the Operational Test TAXI AND TAKEOFF LIGHTS, (Refer to

AMM 33-46-00, Page Block 501)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 163

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

<7> Do the test procedure as specified after the installation of the

THRUST CONTROL COMPUTER 301CJ1 (301CJ2), (Refer to AMM

22-36-34, Page Block 401)

<8> Carry out operational test of the flight compartment and electronics

racks air distribution system (Refer to AMM 21-21-00, Page Block

501)

<9> Do the test procedure as specified after the installation of the DOME

LIGHTS, (Refer to AMM 33-12-11, Page Block 401)

<10>Do the Operational test of the cabin distribution (Refer to AMM

21-22-00, Page Block 501) (if equipped)

<11>Do the test procedure for engine 1 as specified after the installation

of the LOW PRESSURE FUEL FIRE SHUT OFF VALVE, (Refer to

AMM 28-24-31, Page Block 401)

<12>Do the test procedure for engine 2 as specified after the installation

of the LOW PRESSURE FUEL FIRE SHUT OFF VALVE, (Refer to

AMM 28-24-31, Page Block 401)

e Do the test program after Removal/Installation of the panel 429VU

<1> Do the Functional Test of the windshield rain removal system (Refer

to AMM 30-45-00, Page Block 501).

<2> Do the Operational Test of the electrical ground power assisted APU

start (Refer to AMM 49-10-00, Page Block 501).

<3> Do the Operational Test of the APU pump (Refer to AMM 49-31-00,

Page Block 501).

<4> Do the Operational Test of the APU isolation valve (Refer to AMM

49-31-00, Page Block 501).

<5> Do the Operational Test of the ignition system (Refer to AMM

74-00-00, Page Block 501).

<6> Do an engine run (Refer to AMM 71-00-00, Page Block 501).

f Do the test of the AUTO RELIGHT system as follows:

<1> Job Set-Up

- Energize the aircraft electrical network (Refer to AMM 24-41-00,

Page Block 301).

- Make certain that electronics racks ventilation are correct.

- On panel 133VU, open, safety and tag this (these) circuit

breaker(s) related to ENGINES, except 1KG, 1JH, 2JH, 13JH,

14JH, 3KC, 4KC,

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 164

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

- Perform dry motoring (Refer to AMM 71-00-00, Page Block

501).

- Open the 105VU cowl and disconnect/remove relays 2KG and

3KG.

- Open cowl doors (Refer to AMM 71-13-00, Page Block 301).

- On panel 429VU, make sure that the ENG START selector

switch is in OFF position.

- Disconnect N2 RPM (Revolution per minute) indicators 3EP and

4EP (Refer to AMM 77-12-21, Page Block 401).

<2> Procedure

NOTE: This test is described for engine 1 only. For engine

2, refer to information between parentheses.

ACTION RESULT

On panel 9VU, place HP fuel shut off valve control

lever 1 (2) in ON position

On panel 133VU, Open circuit breaker 2GB (2GB)

NOTE: For CONF 007, open 119GB

instead of 2GB for engine 2

On panel 4VU, Connect the pin C of the N2 RPM

indicator 3EP (4EP) plug to the ground.

on engine 1 (2), igniter plugs A and B produce

normal sounds, proving that igniter plugs operate

correctly.

On panel 9VU, place HP (High Pressure) fuel shut

off valve control lever 1 (2) in OFF position

on engine 1 (2), igniter plugs A and B are cut off.

On panel 9VU, place HP fuel shut off valve control

lever 1 (2) in ON position

on engine 1 (2), igniter plugs A and B produce

normal sounds proving that igniter plugs operate

correctly

On panel 133VU, open AUTO RELIGHT ENG 1

(2) circuit breaker 13JH (14JH)

on engine 1 (2) , igniter plugs A and B are cut

off.

On panel 133VU, close AUTO RELIGHT ENG 1

(2) circuit breaker 13JH (14JH)

on engine 1 (2), igniter plugs A and B produce

normal sounds, proving that igniter plugs operate

correctly.

On panel 133VU, open IGNITION SYS A circuit

breaker 1JH

on engine 1 (2), igniter plug A is cut off.

on engine 1 (2), igniter plug B produces normal

sounds, proving that igniter plug operates

correctly.

On panel 133VU, close IGNITION SYS A circuit

breaker 1JH and open IGNITION SYS B circuit

breaker 2JH

on engine 1 (2), igniter plug B is cut off.

on engine 1 (2), igniter plug A produces normal

sounds, proving that igniter plug operates correctly

On panel 133VU, close IGNITION SYS B circuit

breaker 2JH

on engine 1 (2), igniter plugs A and B produce

normal sounds, proving that igniter plugs operate

correctly

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 165

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

ACTION RESULT

On panel 133VU, close circuit breaker 2GB (2GB)

NOTE: For CONF 007, close 119GB

instead of 2GB for engine 2

on engine 1 (2), igniter plugs A and B are cut off.

On panel 133VU, open circuit breaker 2GB (2GB)

NOTE: For CONF 007, open 119GB

instead of 2GB for engine 2

on engine 1 (2), igniter plugs A and B produce

normal sounds, proving that igniter plugs operate

correctly.

On panel 4VU, Disconnect the pin C of the N2

RPM indicator 3EP (4EP) plug from the ground.

on engine 1 (2), igniter plugs A and B are cut off

after 120 seconds.

On panel 133VU, close circuit breaker 2GB (2GB)

NOTE: For CONF 007, close 119GB

instead of 2GB for engine 2

On panel 9VU, place HP fuel shut off valve control

lever 1 (2) in OFF position

Repeat all the steps for engine 2.

<3> Close-up

- Reconnect N2 RPM indicators 3EP and 4EP and perform the

test of the N2 RPM indicators (Refer to AMM 77-12-21, Page

Block 401).

- Re-install the relays 2KG and 3KG (Refer to ESPM 20-46-50)

- Close cowl doors (Refer to AMM 71-13-00, Page Block 301).

- Perform an engine dry motoring (Refer to AMM 71-00-00, Page

Block 501)

- De-energize the aircraft electrical network (Refer to AMM

24-41-00, Page Block 301).

- Restore system and aircraft to normal operating condition

**CONF 002

(1) Subtask 742003-720-001-001 - Test

Manpower Resources

Skills ELECTRICAL

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 166

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 20-28-11, Page Block 001

21-21-00, Page Block 501

21-22-00, Page Block 501

21-23-12, Page Block 401

21-31-11, Page Block 401

22-18-34, Page Block 401

22-36-34, Page Block 401

22-40-00, Page Block 501

23-12-00, Page Block 501

23-71-12, Page Block 401

24-22-15, Page Block 401

24-23-13, Page Block 401

24-31-11, Page Block 401

24-41-00, Page Block 301

26-12-20, Page Block 401

26-12-20, Page Block 501

26-13-20, Page Block 401

26-13-20, Page Block 401

28-22-55, Page Block 401

28-24-31, Page Block 401

28-25-17, Page Block 401

28-28-12, Page Block 401

28-42-38, Page Block 401

28-42-41, Page Block 401

30-45-00, Page Block 501

31-10-00, Page Block 201

31-51-00, Page Block 501

31-69-00, Page Block 501

32-31-11, Page Block 401

33-12-00, Page Block 501

33-12-11, Page Block 401

33-13-00, Page Block 501

33-14-00, Page Block 501

33-46-00, Page Block 501

34-25-00, Page Block 501

34-44-34, Page Block 401

34-68-34, Page Block 401

34-73-34, Page Block 401

36-11-00, Page Block 501

36-11-19, Page Block 401

49-10-00, Page Block 501

49-31-00, Page Block 501

52-51-00, Page Block 501

71-00-00, Page Block 501

71-13-00, Page Block 301

74-00-00, Page Block 501

77-12-21, Page Block 401

Elec. Std. Practices Manual (ESPM) 20-46-50

20-52-10

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 167

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(a) Job Set-up

1 Battery re-connection

- For Job Set-up, refer to Installation of the Batteries (Refer to AMM

24-31-11, Page Block 401)

- Remove the blanking cap from the electrical connectors

- Make sure that the electrical connectors are clean and in correct condition

- Connect the connector on the battery

- Turn the knurled nut a quarter turn

2 Remove all warning notices.

3 Open, safety/lock and tag this (these) circuit breaker(s):

PANEL DESIGNATION FIN LOCATION SEE

NOTES

133 ENGINE 1/FUEL HP

VALVE/WARN

1KC T68

133 ENGINE 2/FUEL HP

VALVE/WARN

2KC R73

133 ENGINE 1/AUTORELIGHT 13JH S69

133 ENGINE 2/AUTORELIGHT 14JH S74

133 STBY GEN AIR VALVE 17XE T83

133 ENGINE 1/LO/PRESS 1ES Q69

4 Energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page Block

301)

5 Do a voltage check at pin 1 of each following circuit breaker to make sure that

there is 28VDC.

PANEL DESIGNATION FIN LOCATION SEE

NOTES

133 ENGINE 1/FUEL HP

VALVE/WARN

1KC T68

133 ENGINE 2/FUEL HP

VALVE/WARN

2KC R73

133 ENGINE 1/AUTORELIGHT 13JH S69

133 ENGINE 2/AUTORELIGHT 14JH S74

133 STBY GEN AIR VALVE 17XE T83

133 ENGINE 1/LO/PRESS 1ES Q69

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 168

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

6 Remove the safety clip(s) and/or tag(s) and close/unlock this (these) circuit

breaker(s):

PANEL DESIGNATION FIN LOCATION SEE

NOTES

133 ENGINE 1/FUEL HP

VALVE/WARN

1KC T68

133 ENGINE 2/FUEL HP

VALVE/WARN

2KC R73

133 ENGINE 1/AUTORELIGHT 13JH S69

133 ENGINE 2/AUTORELIGHT 14JH S74

133 STBY GEN AIR VALVE 17XE T83

133 ENGINE 1/LO/PRESS 1ES Q69

7 Preliminary Tests :

NOTE: If the aircraft is operated in CAT3 conditions, you must also do

the LAND test (Refer to AMM 22-40-00, Page Block 501)

a On each connector which was disconnected:

- Do the checks as defined by ESPM 20-52-10.

NOTE: The Functional test and/or operational test requested by

this ESPM procedure is given hereafter.

b Do the Operational Test of the Annunciator Light Test AMM (Refer to

AMM 33-14-00, Page Block 501).

c Do the Operational Test of the General Illumination, (Refer to AMM

33-12-00, Page Block 501).

d Do the Operational Test of the Instrument and Panel Integral Lighting,

(Refer to AMM 33-13-00, Page Block 501).

e Make certain that the ventillation system operates correctly, (Refer to

AMM 21-21-00, Page Block 501).

f Do the AFS (Automatic Flight System) Test, (Refer to AMM 22-40-00,

Page Block 501)(para 1.A)).

g Do the Operational Test of ECAM/EFIS Display Test, (Refer to AMM

31-51-00, Page Block 501).

h Do the Operational Test of the FWC1 and FWC2, (Refer to AMM

31-51-00, Page Block 501).

(b) Test

1 Procedure

a Do the Operational Test of the circuit breaker monitoring system for panel

133VU (Refer to AMM 31-69-00, Page Block 501).

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 169

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

b Do the tests program after R/I of the panel 20VU:

<1> Do the test procedure as specified after the installation of the FUEL

QUANTITY INDICATOR (6QT), (Refer to AMM 28-42-41, Page

Block 401)

<2> Do the tests program after R/I of the Panel 45VU, (Refer to AMM

31-10-00, Page Block 201)

<3> Do the tests program after R/I of the Panel 76VU (Refer to AMM

31-10-00, Page Block 201)

<4> Do the tests program after R/I of the Panel 424VU (Refer to AMM

31-10-00, Page Block 201)

<5> Do the tests program after R/I of the Panel 425VU (Refer to AMM

31-10-00, Page Block 201)

<6> Do the tests program after R/I of the Panel 430VU (Refer to AMM

31-10-00, Page Block 201)

<7> Do the tests program after R/I of the Panel 433VU (Refer to AMM

31-10-00, Page Block 201)

<8> Do the tests program after R/I of the Panel 435VU (Refer to AMM

31-10-00, Page Block 201)

<9> Do the tests program after R/I of the Panel 438VU (Refer to AMM

31-10-00, Page Block 201)

<10>Do the tests program after R/I of the Panel 431VU (Refer to AMM

31-10-00, Page Block 201)

<11>Do the test of alignment procedure up to step 4 as described in the

IRS operational test (Refer to AMM 34-25-00, Page Block 501) for

each mode selector unit which has been removed for access

<12>Do the test procedure as specified after the installation of the

Cockpit Voice Recorder control unit (1RK) (Refer to AMM 23-71-12,

Page Block 401)

<13>Do the test procedure as specified after the installation of the APU

FIRE CONTROL MODULE (20WG) (Refer to AMM 26-13-20, Page

Block 401)

<14>Do the test procedure as specified after the installation of the

Engine Fire Control Module (39WD) (Refer to AMM 26-12-20, Page

Block 401)

<15>Do the O/T of the VHF3 system (Refer to AMM 23-12-00, Page

Block 501)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 170

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

<16>If CDSS is active for A/C, do the "Operational test of Video

Monitoring System", NOTE: If the SB reference is not specified in

the latest operator’s AMM issue, do these steps:

<a> Job Set-Up

[1] Connect the electrical ground power unit and energize the

aircraft electrical network (Refer to AMM 24-41-00, Page

Block 301).

[2] Make certain that the electronic rack ventilation is correct.

[3] Make certain that the following circuit breaker is closed:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

132VU CKPT/DOOR VIDEO/SPLY 15RA

<b> 2 Operational test of the Video Monitoring System

ACTION RESULT

1. In the cockpit, on panel 512VU:

- push the ’CKPT DOOR VIDEO’ pushbutton

switch

In the cockpit:

- the OFF legend in the ’CKPT DOOR VIDEO’

pushbutton switch goes off.

In the cockpit on the LCD:

- the green LED comes on

- the LCD monitor shows the images from camera

1.

2. In the cockpit, on panel 119VU:

- push the ’VIDEO’ pushbutton one time.

In the cockpit,on the LCD monitor:

- the left half of the LCD monitor screen shows

the images from camera 2

- the right half of the LCD monitor screen shows

the images of camera 3.

3. In the Cockpit, on the panel 119VU:

- push the ’VIDEO’ pushbutton one time.

In the cockpit,on the LCD monitor:

- the LCD monitor shows the images from camera

1.

4. In the cockpit, on the LCD monitor:

- turn the LCD monitor brightness knob clockwise

then counter-clockwise.

In the cockpit,on the LCD monitor:

- the brightness of the images change.

5. In the cockpit, on the LCD monitor:

- turn the LCD monitor contrast knob clockwise

then counter-clockwise.

In the cockpit, on the LCD monitor:

- the contrast of the images change.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 171

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

ACTION RESULT

6. In the cockpit, on the LCD monitor:

- turn the brightness and the contrast knobs to

their center positions.

7. In the cockpit, on the LCD monitor:

- use a flashlight to increase the light on the light

sensor, switch the flashlight on.

In the cockpit,on the LCD monitor:

- the brightness of the images change.

8. In the cockpit, on the LCD monitor:

- decrease the light on the light sensor, switch the

flashlight off.

In the cockpit,on the LCD monitor:

- the brightness of the images change.

9. In the cockpit, on panel 119VU:

- push the ’VIDEO’ pushbutton one time.

In the cockpit,on the LCD monitor:

- the left half of the LCD monitor screen shows

the images from camera 2

- the right half of the LCD monitor screen shows

the images from camera 3

- after five minutes the images go off (Stand-by

mode).

10. In the cockpit, on the panel 119VU:

- before the images on the LCD monitor go off for

30 seconds, push the ’VIDEO’ pushbutton one

time.

In the cockpit,on the LCD monitor:

- the images from camera 2 and camera 3 are

shown(split screen).

- after 5 minutes,the images go off (power-down

mode).

11. In the cockpit entrance area on the keypad

25MQ:

- enter the code to request entry to the cockpit

(Refer to AMM 52-51-00, Page Block 501).

In the cockpit:

- the horn is heard

- on the LCD monitor the image from camera 1 is

shown.

12. In the cockpit on the panel 119VU:

- push the ’VIDEO’ pushbutton one time.

In the cockpit on the LCD monitor:

- the images from camera 2 and 3 are shown

(split screen).

13. In the cockpit entrance area, on the keypad

25MQ:

- after the images from camera 2 and camera 3

are shown on the LCD monitor and before 29

seconds request entry to the cockpit.

In the cockpit on the LCD monitor:

- the images from camera 2 and camera 3 are

shown (split screen).

14. In the cockpit, on the panel 119VU:

- push the ’VIDEO’ pushbutton one time.

In the cockpit,on the LCD monitor:

- the image from camera 1 is shown.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 172

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

ACTION RESULT

15. In the cockpit on the panel 512VU:

- push the ’CKPT DOOR VIDEO’ pushbutton

switch.

In the cockpit on the panel 512VU:

- the ’OFF’ legend in the ’CKPT DOOR VIDEO’

pushbutton switch comes on.

In the cockpit on the LCD monitor:

- the green LED goes off

- the screen goes off.

<c> Close-Up

[1] De-energize the AC-External Power Control (Refer to

AMM 24-41-00, Page Block 301).

[2] Make sure that the work area is clean and clear of tools

and miscellaneous items of equipment.

<17>Do the O/T of the CDLS (Refer to AMM 52-51-00, Page Block 501)

c Do the tests program after R/I of the panel 104VU:

<1> Do a check of the Electrical Bonding (Refer to AMM 20-28-11, Page

Block 001)

NOTE: For maximun permissible resistance values: Refer to

the Table (Refer to AMM 20-28-11, Page Block 001)

<2> Do the test procedure as specified after the installation of the TRIM

TANK ISOLATION VALVE ACTUATOR (48QB), (Refer to AMM

28-22-55, Page Block 401)

<3> Do the test procedure as specified after the installation of the

INBOARD EXTRACT VALVE (74HR), (Refer to AMM 21-23-12,

Page Block 401)

<4> Do the test procedure as specified after the installation of the EFIS

SGU (28FN1, 28FN2, 28FN3), (Refer to AMM 34-73-34, Page Block

401)

<5> Do the test procedure as specified after the installation of the APU

GEN PWR LINE CONTACTOR 3XS, (Refer to AMM 24-23-13, Page

Block 401)

<6> Do the test procedure as specified after the installation of the FUEL

QUANTITY COMPUTER (15QT), (Refer to AMM 28-42-38, Page

Block 401)

<7> Do the test procedure as specified after the installation of the

TRANSFER VALVE ACTUATOR, (Refer to AMM 28-25-17, Page

Block 401) (if equipped)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 173

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

<8> Do the test procedure as specified after the installation of the

ACTUATOR - SELECTOR VALVE, (Refer to AMM 28-28-12, Page

Block 401) (if equipped)

<9> Do the test procedure as specified after the installation of the GEN 1

(2) LINE CONTACTOR 9XU (10XU), (Refer to AMM 24-22-15, Page

Block 401)

<10>Do the test procedure as specified after the installation of the

CABIN PRESSURE CONTROLLER 105HM (106HM), (Refer to

AMM 21-31-11, Page Block 401)

<11>Do the test procedure as specified after the installation of

the PNEUMATIC CONTROLLER 41HA (42HA), (Refer to AMM

36-11-19, Page Block 401) (if equipped)

<12>Do the test procedure as specified after the installation of the APU

FIRE CONTROL MODULE, (Refer to AMM 26-13-20, Page Block

401)

<13>Do the test procedure as specified after the installation of the

FLIGHT CONTROL COMPUTER (301CA1, 301CA2), (Refer to AMM

22-18-34, Page Block 401)

<14>Do the test procedure as specified after the installation of

the LANDING GEAR NORMAL CONTROL MICROSWITCH UNIT

(2GA), (Refer to AMM 32-31-11, Page Block 401)

d Do the tests program after R/I of the panel 105VU:

<1> Do a check of the Electrical Bonding (Refer to AMM 20-28-11, Page

Block 001)

NOTE: For maximun permissible resistance values: Refer to

the Table (Refer to AMM 20-28-11, Page Block 001)

<2> Do the Perform BITE test (Refer to AMM 36-11-00, Page Block

501), (Operational Test)

<3> Do the test procedure as specified after the installation of the

FLIGHT MANAGEMENT COMPUTER (1CK1, 1CK2), (Refer to

AMM 34-68-34, Page Block 401) (if equipped)

<4> Do the Functional Test - ENGINE FIRE CONTROL MODULE, (Refer

to AMM 26-12-20, Page Block 501)

<5> Do the test procedure as specified after the installation of the TCAS

COMPUTER (9005SG), (Refer to AMM 34-44-34, Page Block 401)

(if equipped)

<6> Do the Operational Test TAXI AND TAKEOFF LIGHTS, (Refer to

AMM 33-46-00, Page Block 501)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 174

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

<7> Do the test procedure as specified after the installation of the

THRUST CONTROL COMPUTER 301CJ1 (301CJ2), (Refer to AMM

22-36-34, Page Block 401)

<8> Carry out operational test of the flight compartment and electronics

racks air distribution system (Refer to AMM 21-21-00, Page Block

501)

<9> Do the test procedure as specified after the installation of the DOME

LIGHTS, (Refer to AMM 33-12-11, Page Block 401)

<10>Do the Operational test of the cabin distribution (Refer to AMM

21-22-00, Page Block 501) (if equipped)

<11>Do the test procedure for engine 1 as specified after the installation

of the LOW PRESSURE FUEL FIRE SHUT OFF VALVE, (Refer to

AMM 28-24-31, Page Block 401)

<12>Do the test procedure for engine 2 as specified after the installation

of the LOW PRESSURE FUEL FIRE SHUT OFF VALVE, (Refer to

AMM 28-24-31, Page Block 401)

e Do the test program after Removal/Installation of the panel 429VU

<1> Do the Functional Test of the windshield rain removal system (Refer

to AMM 30-45-00, Page Block 501).

<2> Do the Operational Test of the electrical ground power assisted APU

start (Refer to AMM 49-10-00, Page Block 501).

<3> Do the Operational Test of the APU pump (Refer to AMM 49-31-00,

Page Block 501).

<4> Do the Operational Test of the APU isolation valve (Refer to AMM

49-31-00, Page Block 501).

<5> Do the Operational Test of the ignition system (Refer to AMM

74-00-00, Page Block 501).

<6> Do an engine run (Refer to AMM 71-00-00, Page Block 501).

f Do the test of the AUTO RELIGHT system as follows:

<1> Job Set-Up

- Energize the aircraft electrical network (Refer to AMM 24-41-00,

Page Block 301).

- Make certain that electronics racks ventilation are correct.

- On panel 133VU, open, safety and tag this (these) circuit

breaker(s) related to ENGINES, except 1KG, 1JH, 2JH, 13JH,

14JH, 3KC, 4KC,

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 175

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

- Perform dry motoring (Refer to AMM 71-00-00, Page Block

501).

- Open the 105VU cowl and disconnect/remove relays 2KG and

3KG.

- Open cowl doors (Refer to AMM 71-13-00, Page Block 301).

- On panel 429VU, make sure that the ENG START selector

switch is in OFF position.

- Disconnect N2 RPM (Revolution per minute) indicators 3EP and

4EP (Refer to AMM 77-12-21, Page Block 401).

<2> Procedure

NOTE: This test is described for engine 1 only. For engine

2, refer to information between parentheses.

ACTION RESULT

On panel 9VU, place HP fuel shut off valve control

lever 1 (2) in ON position

On panel 133VU, Open circuit breaker 2GB (2GB)

NOTE: For CONF 007, open 119GB

instead of 2GB for engine 2

On panel 4VU, Connect the pin C of the N2 RPM

indicator 3EP (4EP) plug to the ground.

on engine 1 (2), igniter plugs A and B produce

normal sounds, proving that igniter plugs operate

correctly.

On panel 9VU, place HP (High Pressure) fuel shut

off valve control lever 1 (2) in OFF position

on engine 1 (2), igniter plugs A and B are cut off.

On panel 9VU, place HP fuel shut off valve control

lever 1 (2) in ON position

on engine 1 (2), igniter plugs A and B produce

normal sounds proving that igniter plugs operate

correctly

On panel 133VU, open AUTO RELIGHT ENG 1

(2) circuit breaker 13JH (14JH)

on engine 1 (2) , igniter plugs A and B are cut

off.

On panel 133VU, close AUTO RELIGHT ENG 1

(2) circuit breaker 13JH (14JH)

on engine 1 (2), igniter plugs A and B produce

normal sounds, proving that igniter plugs operate

correctly.

On panel 133VU, open IGNITION SYS A circuit

breaker 1JH

on engine 1 (2), igniter plug A is cut off.

on engine 1 (2), igniter plug B produces normal

sounds, proving that igniter plug operates

correctly.

On panel 133VU, close IGNITION SYS A circuit

breaker 1JH and open IGNITION SYS B circuit

breaker 2JH

on engine 1 (2), igniter plug B is cut off.

on engine 1 (2), igniter plug A produces normal

sounds, proving that igniter plug operates correctly

On panel 133VU, close IGNITION SYS B circuit

breaker 2JH

on engine 1 (2), igniter plugs A and B produce

normal sounds, proving that igniter plugs operate

correctly

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 176

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

ACTION RESULT

On panel 133VU, close circuit breaker 2GB (2GB)

NOTE: For CONF 007, close 119GB

instead of 2GB for engine 2

on engine 1 (2), igniter plugs A and B are cut off.

On panel 133VU, open circuit breaker 2GB (2GB)

NOTE: For CONF 007, open 119GB

instead of 2GB for engine 2

on engine 1 (2), igniter plugs A and B produce

normal sounds, proving that igniter plugs operate

correctly.

On panel 4VU, Disconnect the pin C of the N2

RPM indicator 3EP (4EP) plug from the ground.

on engine 1 (2), igniter plugs A and B are cut off

after 120 seconds.

On panel 133VU, close circuit breaker 2GB (2GB)

NOTE: For CONF 007, close 119GB

instead of 2GB for engine 2

On panel 9VU, place HP fuel shut off valve control

lever 1 (2) in OFF position

Repeat all the steps for engine 2.

<3> Close-up

- Reconnect N2 RPM indicators 3EP and 4EP and perform the

test of the N2 RPM indicators (Refer to AMM 77-12-21, Page

Block 401).

- Re-install the relays 2KG and 3KG (Refer to ESPM 20-46-50)

- Close cowl doors (Refer to AMM 71-13-00, Page Block 301).

- Perform an engine dry motoring (Refer to AMM 71-00-00, Page

Block 501)

- De-energize the aircraft electrical network (Refer to AMM

24-41-00, Page Block 301).

- Restore system and aircraft to normal operating condition

**CONF 003

(1) Subtask 742003-720-001-001 - Test

Manpower Resources

Skills ELECTRICAL

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 177

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 20-28-11, Page Block 001

21-21-00, Page Block 501

21-22-00, Page Block 501

21-23-12, Page Block 401

21-31-11, Page Block 401

22-18-34, Page Block 401

22-36-34, Page Block 401

22-40-00, Page Block 501

23-12-00, Page Block 501

23-71-12, Page Block 401

24-22-15, Page Block 401

24-23-13, Page Block 401

24-31-11, Page Block 401

24-41-00, Page Block 301

26-12-20, Page Block 401

26-12-20, Page Block 501

26-13-20, Page Block 401

26-13-20, Page Block 401

28-22-55, Page Block 401

28-24-31, Page Block 401

28-25-17, Page Block 401

28-28-12, Page Block 401

28-42-38, Page Block 401

28-42-41, Page Block 401

30-45-00, Page Block 501

31-10-00, Page Block 201

31-51-00, Page Block 501

31-69-00, Page Block 501

32-31-11, Page Block 401

33-12-00, Page Block 501

33-12-11, Page Block 401

33-13-00, Page Block 501

33-14-00, Page Block 501

33-46-00, Page Block 501

34-25-00, Page Block 501

34-44-34, Page Block 401

34-68-34, Page Block 401

34-73-34, Page Block 401

36-11-00, Page Block 501

36-11-19, Page Block 401

49-10-00, Page Block 501

49-31-00, Page Block 501

52-51-00, Page Block 501

71-00-00, Page Block 501

71-13-00, Page Block 301

74-00-00, Page Block 501

77-12-21, Page Block 401

Elec. Std. Practices Manual (ESPM) 20-46-50

20-52-10

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 178

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(a) Job Set-up

1 Battery re-connection

- For Job Set-up, refer to Installation of the Batteries (Refer to AMM

24-31-11, Page Block 401)

- Remove the blanking cap from the electrical connectors

- Make sure that the electrical connectors are clean and in correct condition

- Connect the connector on the battery

- Turn the knurled nut a quarter turn

2 Remove all warning notices.

3 Open, safety/lock and tag this (these) circuit breaker(s):

PANEL DESIGNATION FIN LOCATION SEE

NOTES

133 ENGINE 1/FUEL HP

VALVE/WARN

1KC T68

133 ENGINE 2/FUEL HP

VALVE/WARN

2KC R73

133 ENGINE 1/AUTORELIGHT 13JH S69

133 ENGINE 2/AUTORELIGHT 14JH S74

133 STBY GEN AIR VALVE 17XE T83

133 ENGINE 1/LO/PRESS 1ES Q69

4 Energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page Block

301)

5 Do a voltage check at pin 1 of each following circuit breaker to make sure that

there is 28VDC.

PANEL DESIGNATION FIN LOCATION SEE

NOTES

133 ENGINE 1/FUEL HP

VALVE/WARN

1KC T68

133 ENGINE 2/FUEL HP

VALVE/WARN

2KC R73

133 ENGINE 1/AUTORELIGHT 13JH S69

133 ENGINE 2/AUTORELIGHT 14JH S74

133 STBY GEN AIR VALVE 17XE T83

133 ENGINE 1/LO/PRESS 1ES Q69

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 179

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

6 Remove the safety clip(s) and/or tag(s) and close/unlock this (these) circuit

breaker(s):

PANEL DESIGNATION FIN LOCATION SEE

NOTES

133 ENGINE 1/FUEL HP

VALVE/WARN

1KC T68

133 ENGINE 2/FUEL HP

VALVE/WARN

2KC R73

133 ENGINE 1/AUTORELIGHT 13JH S69

133 ENGINE 2/AUTORELIGHT 14JH S74

133 STBY GEN AIR VALVE 17XE T83

133 ENGINE 1/LO/PRESS 1ES Q69

7 Preliminary Tests :

NOTE: If the aircraft is operated in CAT3 conditions, you must also do

the LAND test (Refer to AMM 22-40-00, Page Block 501)

a On each connector which was disconnected:

- Do the checks as defined by ESPM 20-52-10.

NOTE: The Functional test and/or operational test requested by

this ESPM procedure is given hereafter.

b Do the Operational Test of the Annunciator Light Test AMM (Refer to

AMM 33-14-00, Page Block 501).

c Do the Operational Test of the General Illumination, (Refer to AMM

33-12-00, Page Block 501).

d Do the Operational Test of the Instrument and Panel Integral Lighting,

(Refer to AMM 33-13-00, Page Block 501).

e Make certain that the ventillation system operates correctly, (Refer to

AMM 21-21-00, Page Block 501).

f Do the AFS (Automatic Flight System) Test, (Refer to AMM 22-40-00,

Page Block 501)(para 1.A)).

g Do the Operational Test of ECAM/EFIS Display Test, (Refer to AMM

31-51-00, Page Block 501).

h Do the Operational Test of the FWC1 and FWC2, (Refer to AMM

31-51-00, Page Block 501).

(b) Test

1 Procedure

a Do the Operational Test of the circuit breaker monitoring system for panel

133VU (Refer to AMM 31-69-00, Page Block 501).

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 180

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

b Do the tests program after R/I of the panel 20VU:

<1> Do the test procedure as specified after the installation of the FUEL

QUANTITY INDICATOR (6QT), (Refer to AMM 28-42-41, Page

Block 401)

<2> Do the tests program after R/I of the Panel 45VU, (Refer to AMM

31-10-00, Page Block 201)

<3> Do the tests program after R/I of the Panel 76VU (Refer to AMM

31-10-00, Page Block 201)

<4> Do the tests program after R/I of the Panel 424VU (Refer to AMM

31-10-00, Page Block 201)

<5> Do the tests program after R/I of the Panel 425VU (Refer to AMM

31-10-00, Page Block 201)

<6> Do the tests program after R/I of the Panel 430VU (Refer to AMM

31-10-00, Page Block 201)

<7> Do the tests program after R/I of the Panel 433VU (Refer to AMM

31-10-00, Page Block 201)

<8> Do the tests program after R/I of the Panel 435VU (Refer to AMM

31-10-00, Page Block 201)

<9> Do the tests program after R/I of the Panel 438VU (Refer to AMM

31-10-00, Page Block 201)

<10>Do the tests program after R/I of the Panel 431VU (Refer to AMM

31-10-00, Page Block 201)

<11>Do the test of alignment procedure up to step 4 as described in the

IRS operational test (Refer to AMM 34-25-00, Page Block 501) for

each mode selector unit which has been removed for access

<12>Do the test procedure as specified after the installation of the

Cockpit Voice Recorder control unit (1RK) (Refer to AMM 23-71-12,

Page Block 401)

<13>Do the test procedure as specified after the installation of the APU

FIRE CONTROL MODULE (20WG) (Refer to AMM 26-13-20, Page

Block 401)

<14>Do the test procedure as specified after the installation of the

Engine Fire Control Module (39WD) (Refer to AMM 26-12-20, Page

Block 401)

<15>Do the O/T of the VHF3 system (Refer to AMM 23-12-00, Page

Block 501)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 181

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

<16>If CDSS is active for A/C, do the "Operational test of Video

Monitoring System", NOTE: If the SB reference is not specified in

the latest operator’s AMM issue, do these steps:

<a> Job Set-Up

[1] Connect the electrical ground power unit and energize the

aircraft electrical network (Refer to AMM 24-41-00, Page

Block 301).

[2] Make certain that the electronic rack ventilation is correct.

[3] Make certain that the following circuit breaker is closed:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

132VU CKPT/DOOR VIDEO/SPLY 15RA

<b> 2 Operational test of the Video Monitoring System

ACTION RESULT

1. In the cockpit, on panel 512VU:

- push the ’CKPT DOOR VIDEO’ pushbutton

switch

In the cockpit:

- the OFF legend in the ’CKPT DOOR VIDEO’

pushbutton switch goes off.

In the cockpit on the LCD:

- the green LED comes on

- the LCD monitor shows the images from camera

1.

2. In the cockpit, on panel 119VU:

- push the ’VIDEO’ pushbutton one time.

In the cockpit,on the LCD monitor:

- the left half of the LCD monitor screen shows

the images from camera 2

- the right half of the LCD monitor screen shows

the images of camera 3.

3. In the Cockpit, on the panel 119VU:

- push the ’VIDEO’ pushbutton one time.

In the cockpit,on the LCD monitor:

- the LCD monitor shows the images from camera

1.

4. In the cockpit, on the LCD monitor:

- turn the LCD monitor brightness knob clockwise

then counter-clockwise.

In the cockpit,on the LCD monitor:

- the brightness of the images change.

5. In the cockpit, on the LCD monitor:

- turn the LCD monitor contrast knob clockwise

then counter-clockwise.

In the cockpit, on the LCD monitor:

- the contrast of the images change.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 182

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

ACTION RESULT

6. In the cockpit, on the LCD monitor:

- turn the brightness and the contrast knobs to

their center positions.

7. In the cockpit, on the LCD monitor:

- use a flashlight to increase the light on the light

sensor, switch the flashlight on.

In the cockpit,on the LCD monitor:

- the brightness of the images change.

8. In the cockpit, on the LCD monitor:

- decrease the light on the light sensor, switch the

flashlight off.

In the cockpit,on the LCD monitor:

- the brightness of the images change.

9. In the cockpit, on panel 119VU:

- push the ’VIDEO’ pushbutton one time.

In the cockpit,on the LCD monitor:

- the left half of the LCD monitor screen shows

the images from camera 2

- the right half of the LCD monitor screen shows

the images from camera 3

- after five minutes the images go off (Stand-by

mode).

10. In the cockpit, on the panel 119VU:

- before the images on the LCD monitor go off for

30 seconds, push the ’VIDEO’ pushbutton one

time.

In the cockpit,on the LCD monitor:

- the images from camera 2 and camera 3 are

shown(split screen).

- after 5 minutes,the images go off (power-down

mode).

11. In the cockpit entrance area on the keypad

25MQ:

- enter the code to request entry to the cockpit

(Refer to AMM 52-51-00, Page Block 501).

In the cockpit:

- the horn is heard

- on the LCD monitor the image from camera 1 is

shown.

12. In the cockpit on the panel 119VU:

- push the ’VIDEO’ pushbutton one time.

In the cockpit on the LCD monitor:

- the images from camera 2 and 3 are shown

(split screen).

13. In the cockpit entrance area, on the keypad

25MQ:

- after the images from camera 2 and camera 3

are shown on the LCD monitor and before 29

seconds request entry to the cockpit.

In the cockpit on the LCD monitor:

- the images from camera 2 and camera 3 are

shown (split screen).

14. In the cockpit, on the panel 119VU:

- push the ’VIDEO’ pushbutton one time.

In the cockpit,on the LCD monitor:

- the image from camera 1 is shown.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 183

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

ACTION RESULT

15. In the cockpit on the panel 512VU:

- push the ’CKPT DOOR VIDEO’ pushbutton

switch.

In the cockpit on the panel 512VU:

- the ’OFF’ legend in the ’CKPT DOOR VIDEO’

pushbutton switch comes on.

In the cockpit on the LCD monitor:

- the green LED goes off

- the screen goes off.

<c> Close-Up

[1] De-energize the AC-External Power Control (Refer to

AMM 24-41-00, Page Block 301).

[2] Make sure that the work area is clean and clear of tools

and miscellaneous items of equipment.

<17>Do the O/T of the CDLS (Refer to AMM 52-51-00, Page Block 501)

c Do the tests program after R/I of the panel 104VU:

<1> Do a check of the Electrical Bonding (Refer to AMM 20-28-11, Page

Block 001)

NOTE: For maximun permissible resistance values: Refer to

the Table (Refer to AMM 20-28-11, Page Block 001)

<2> Do the test procedure as specified after the installation of the TRIM

TANK ISOLATION VALVE ACTUATOR (48QB), (Refer to AMM

28-22-55, Page Block 401)

<3> Do the test procedure as specified after the installation of the

INBOARD EXTRACT VALVE (74HR), (Refer to AMM 21-23-12,

Page Block 401)

<4> Do the test procedure as specified after the installation of the EFIS

SGU (28FN1, 28FN2, 28FN3), (Refer to AMM 34-73-34, Page Block

401)

<5> Do the test procedure as specified after the installation of the APU

GEN PWR LINE CONTACTOR 3XS, (Refer to AMM 24-23-13, Page

Block 401)

<6> Do the test procedure as specified after the installation of the FUEL

QUANTITY COMPUTER (15QT), (Refer to AMM 28-42-38, Page

Block 401)

<7> Do the test procedure as specified after the installation of the

TRANSFER VALVE ACTUATOR, (Refer to AMM 28-25-17, Page

Block 401) (if equipped)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 184

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

<8> Do the test procedure as specified after the installation of the

ACTUATOR - SELECTOR VALVE, (Refer to AMM 28-28-12, Page

Block 401) (if equipped)

<9> Do the test procedure as specified after the installation of the GEN 1

(2) LINE CONTACTOR 9XU (10XU), (Refer to AMM 24-22-15, Page

Block 401)

<10>Do the test procedure as specified after the installation of the

CABIN PRESSURE CONTROLLER 105HM (106HM), (Refer to

AMM 21-31-11, Page Block 401)

<11>Do the test procedure as specified after the installation of

the PNEUMATIC CONTROLLER 41HA (42HA), (Refer to AMM

36-11-19, Page Block 401) (if equipped)

<12>Do the test procedure as specified after the installation of the APU

FIRE CONTROL MODULE, (Refer to AMM 26-13-20, Page Block

401)

<13>Do the test procedure as specified after the installation of the

FLIGHT CONTROL COMPUTER (301CA1, 301CA2), (Refer to AMM

22-18-34, Page Block 401)

<14>Do the test procedure as specified after the installation of

the LANDING GEAR NORMAL CONTROL MICROSWITCH UNIT

(2GA), (Refer to AMM 32-31-11, Page Block 401)

d Do the tests program after R/I of the panel 105VU:

<1> Do a check of the Electrical Bonding (Refer to AMM 20-28-11, Page

Block 001)

NOTE: For maximun permissible resistance values: Refer to

the Table (Refer to AMM 20-28-11, Page Block 001)

<2> Do the Perform BITE test (Refer to AMM 36-11-00, Page Block

501), (Operational Test)

<3> Do the test procedure as specified after the installation of the

FLIGHT MANAGEMENT COMPUTER (1CK1, 1CK2), (Refer to

AMM 34-68-34, Page Block 401) (if equipped)

<4> Do the Functional Test - ENGINE FIRE CONTROL MODULE, (Refer

to AMM 26-12-20, Page Block 501)

<5> Do the test procedure as specified after the installation of the TCAS

COMPUTER (9005SG), (Refer to AMM 34-44-34, Page Block 401)

(if equipped)

<6> Do the Operational Test TAXI AND TAKEOFF LIGHTS, (Refer to

AMM 33-46-00, Page Block 501)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 185

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

<7> Do the test procedure as specified after the installation of the

THRUST CONTROL COMPUTER 301CJ1 (301CJ2), (Refer to AMM

22-36-34, Page Block 401)

<8> Carry out operational test of the flight compartment and electronics

racks air distribution system (Refer to AMM 21-21-00, Page Block

501)

<9> Do the test procedure as specified after the installation of the DOME

LIGHTS, (Refer to AMM 33-12-11, Page Block 401)

<10>Do the Operational test of the cabin distribution (Refer to AMM

21-22-00, Page Block 501) (if equipped)

<11>Do the test procedure for engine 1 as specified after the installation

of the LOW PRESSURE FUEL FIRE SHUT OFF VALVE, (Refer to

AMM 28-24-31, Page Block 401)

<12>Do the test procedure for engine 2 as specified after the installation

of the LOW PRESSURE FUEL FIRE SHUT OFF VALVE, (Refer to

AMM 28-24-31, Page Block 401)

e Do the test program after Removal/Installation of the panel 429VU

<1> Do the Functional Test of the windshield rain removal system (Refer

to AMM 30-45-00, Page Block 501).

<2> Do the Operational Test of the electrical ground power assisted APU

start (Refer to AMM 49-10-00, Page Block 501).

<3> Do the Operational Test of the APU pump (Refer to AMM 49-31-00,

Page Block 501).

<4> Do the Operational Test of the APU isolation valve (Refer to AMM

49-31-00, Page Block 501).

<5> Do the Operational Test of the ignition system (Refer to AMM

74-00-00, Page Block 501).

<6> Do an engine run (Refer to AMM 71-00-00, Page Block 501).

f Do the test of the AUTO RELIGHT system as follows:

<1> Job Set-Up

- Energize the aircraft electrical network (Refer to AMM 24-41-00,

Page Block 301).

- Make certain that electronics racks ventilation are correct.

- On panel 133VU, open, safety and tag this (these) circuit

breaker(s) related to ENGINES, except 1KG, 1JH, 2JH, 13JH,

14JH, 3KC, 4KC,

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 186

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

- Perform dry motoring (Refer to AMM 71-00-00, Page Block

501).

- Open the 105VU cowl and disconnect/remove relays 2KG and

3KG.

- Open cowl doors (Refer to AMM 71-13-00, Page Block 301).

- On panel 429VU, make sure that the ENG START selector

switch is in OFF position.

- Disconnect N2 RPM (Revolution per minute) indicators 3EP and

4EP (Refer to AMM 77-12-21, Page Block 401).

<2> Procedure

NOTE: This test is described for engine 1 only. For engine

2, refer to information between parentheses.

ACTION RESULT

On panel 9VU, place HP fuel shut off valve control

lever 1 (2) in ON position

On panel 133VU, Open circuit breaker 2GB (2GB)

NOTE: For CONF 007, open 119GB

instead of 2GB for engine 2

On panel 4VU, Connect the pin C of the N2 RPM

indicator 3EP (4EP) plug to the ground.

on engine 1 (2), igniter plugs A and B produce

normal sounds, proving that igniter plugs operate

correctly.

On panel 9VU, place HP (High Pressure) fuel shut

off valve control lever 1 (2) in OFF position

on engine 1 (2), igniter plugs A and B are cut off.

On panel 9VU, place HP fuel shut off valve control

lever 1 (2) in ON position

on engine 1 (2), igniter plugs A and B produce

normal sounds proving that igniter plugs operate

correctly

On panel 133VU, open AUTO RELIGHT ENG 1

(2) circuit breaker 13JH (14JH)

on engine 1 (2) , igniter plugs A and B are cut

off.

On panel 133VU, close AUTO RELIGHT ENG 1

(2) circuit breaker 13JH (14JH)

on engine 1 (2), igniter plugs A and B produce

normal sounds, proving that igniter plugs operate

correctly.

On panel 133VU, open IGNITION SYS A circuit

breaker 1JH

on engine 1 (2), igniter plug A is cut off.

on engine 1 (2), igniter plug B produces normal

sounds, proving that igniter plug operates

correctly.

On panel 133VU, close IGNITION SYS A circuit

breaker 1JH and open IGNITION SYS B circuit

breaker 2JH

on engine 1 (2), igniter plug B is cut off.

on engine 1 (2), igniter plug A produces normal

sounds, proving that igniter plug operates correctly

On panel 133VU, close IGNITION SYS B circuit

breaker 2JH

on engine 1 (2), igniter plugs A and B produce

normal sounds, proving that igniter plugs operate

correctly

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 187

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

ACTION RESULT

On panel 133VU, close circuit breaker 2GB (2GB)

NOTE: For CONF 007, close 119GB

instead of 2GB for engine 2

on engine 1 (2), igniter plugs A and B are cut off.

On panel 133VU, open circuit breaker 2GB (2GB)

NOTE: For CONF 007, open 119GB

instead of 2GB for engine 2

on engine 1 (2), igniter plugs A and B produce

normal sounds, proving that igniter plugs operate

correctly.

On panel 4VU, Disconnect the pin C of the N2

RPM indicator 3EP (4EP) plug from the ground.

on engine 1 (2), igniter plugs A and B are cut off

after 120 seconds.

On panel 133VU, close circuit breaker 2GB (2GB)

NOTE: For CONF 007, close 119GB

instead of 2GB for engine 2

On panel 9VU, place HP fuel shut off valve control

lever 1 (2) in OFF position

Repeat all the steps for engine 2.

<3> Close-up

- Reconnect N2 RPM indicators 3EP and 4EP and perform the

test of the N2 RPM indicators (Refer to AMM 77-12-21, Page

Block 401).

- Re-install the relays 2KG and 3KG (Refer to ESPM 20-46-50)

- Close cowl doors (Refer to AMM 71-13-00, Page Block 301).

- Perform an engine dry motoring (Refer to AMM 71-00-00, Page

Block 501)

- De-energize the aircraft electrical network (Refer to AMM

24-41-00, Page Block 301).

- Restore system and aircraft to normal operating condition

**CONF 006

(1) Subtask 742003-720-001-001 - Test

Manpower Resources

Skills ELECTRICAL

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 188

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 20-28-11, Page Block 001

21-21-00, Page Block 501

21-22-00, Page Block 501

21-23-12, Page Block 401

21-31-11, Page Block 401

22-18-34, Page Block 401

22-36-34, Page Block 401

22-40-00, Page Block 501

23-12-00, Page Block 501

23-71-12, Page Block 401

24-22-15, Page Block 401

24-23-13, Page Block 401

24-31-11, Page Block 401

24-41-00, Page Block 301

26-12-20, Page Block 401

26-12-20, Page Block 501

26-13-20, Page Block 401

26-13-20, Page Block 401

28-22-55, Page Block 401

28-24-31, Page Block 401

28-25-17, Page Block 401

28-28-12, Page Block 401

28-42-38, Page Block 401

28-42-41, Page Block 401

30-45-00, Page Block 501

31-10-00, Page Block 201

31-51-00, Page Block 501

31-69-00, Page Block 501

32-31-11, Page Block 401

33-12-00, Page Block 501

33-12-11, Page Block 401

33-13-00, Page Block 501

33-14-00, Page Block 501

33-46-00, Page Block 501

34-25-00, Page Block 501

34-44-34, Page Block 401

34-68-34, Page Block 401

34-73-34, Page Block 401

36-11-00, Page Block 501

36-11-19, Page Block 401

49-10-00, Page Block 501

49-31-00, Page Block 501

52-51-00, Page Block 501

71-00-00, Page Block 501

71-13-00, Page Block 301

74-00-00, Page Block 501

77-12-21, Page Block 401

Elec. Std. Practices Manual (ESPM) 20-46-50

20-52-10

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 189

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(a) Job Set-up

1 Battery re-connection

- For Job Set-up, refer to Installation of the Batteries (Refer to AMM

24-31-11, Page Block 401)

- Remove the blanking cap from the electrical connectors

- Make sure that the electrical connectors are clean and in correct condition

- Connect the connector on the battery

- Turn the knurled nut a quarter turn

2 Remove all warning notices.

3 Open, safety/lock and tag this (these) circuit breaker(s):

PANEL DESIGNATION FIN LOCATION SEE

NOTES

133 ENGINE 1/FUEL HP

VALVE/WARN

1KC T68

133 ENGINE 2/FUEL HP

VALVE/WARN

2KC R73

133 ENGINE 1/AUTORELIGHT 13JH S69

133 ENGINE 2/AUTORELIGHT 14JH S74

133 STBY GEN AIR VALVE 17XE T83

133 ENGINE 1/LO/PRESS 1ES Q69

4 Energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page Block

301)

5 Do a voltage check at pin 1 of each following circuit breaker to make sure that

there is 28VDC.

PANEL DESIGNATION FIN LOCATION SEE

NOTES

133 ENGINE 1/FUEL HP

VALVE/WARN

1KC T68

133 ENGINE 2/FUEL HP

VALVE/WARN

2KC R73

133 ENGINE 1/AUTORELIGHT 13JH S69

133 ENGINE 2/AUTORELIGHT 14JH S74

133 STBY GEN AIR VALVE 17XE T83

133 ENGINE 1/LO/PRESS 1ES Q69

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 190

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

6 Remove the safety clip(s) and/or tag(s) and close/unlock this (these) circuit

breaker(s):

PANEL DESIGNATION FIN LOCATION SEE

NOTES

133 ENGINE 1/FUEL HP

VALVE/WARN

1KC T68

133 ENGINE 2/FUEL HP

VALVE/WARN

2KC R73

133 ENGINE 1/AUTORELIGHT 13JH S69

133 ENGINE 2/AUTORELIGHT 14JH S74

133 STBY GEN AIR VALVE 17XE T83

133 ENGINE 1/LO/PRESS 1ES Q69

7 Preliminary Tests :

NOTE: If the aircraft is operated in CAT3 conditions, you must also do

the LAND test (Refer to AMM 22-40-00, Page Block 501)

a On each connector which was disconnected:

- Do the checks as defined by ESPM 20-52-10.

NOTE: The Functional test and/or operational test requested by

this ESPM procedure is given hereafter.

b Do the Operational Test of the Annunciator Light Test AMM (Refer to

AMM 33-14-00, Page Block 501).

c Do the Operational Test of the General Illumination, (Refer to AMM

33-12-00, Page Block 501).

d Do the Operational Test of the Instrument and Panel Integral Lighting,

(Refer to AMM 33-13-00, Page Block 501).

e Make certain that the ventillation system operates correctly, (Refer to

AMM 21-21-00, Page Block 501).

f Do the AFS (Automatic Flight System) Test, (Refer to AMM 22-40-00,

Page Block 501)(para 1.A)).

g Do the Operational Test of ECAM/EFIS Display Test, (Refer to AMM

31-51-00, Page Block 501).

h Do the Operational Test of the FWC1 and FWC2, (Refer to AMM

31-51-00, Page Block 501).

(b) Test

1 Procedure

a Do the Operational Test of the circuit breaker monitoring system for panel

133VU (Refer to AMM 31-69-00, Page Block 501).

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 191

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

b Do the tests program after R/I of the panel 20VU:

<1> Do the test procedure as specified after the installation of the FUEL

QUANTITY INDICATOR (6QT), (Refer to AMM 28-42-41, Page

Block 401)

<2> Do the tests program after R/I of the Panel 45VU, (Refer to AMM

31-10-00, Page Block 201)

<3> Do the tests program after R/I of the Panel 76VU (Refer to AMM

31-10-00, Page Block 201)

<4> Do the tests program after R/I of the Panel 424VU (Refer to AMM

31-10-00, Page Block 201)

<5> Do the tests program after R/I of the Panel 425VU (Refer to AMM

31-10-00, Page Block 201)

<6> Do the tests program after R/I of the Panel 430VU (Refer to AMM

31-10-00, Page Block 201)

<7> Do the tests program after R/I of the Panel 433VU (Refer to AMM

31-10-00, Page Block 201)

<8> Do the tests program after R/I of the Panel 435VU (Refer to AMM

31-10-00, Page Block 201)

<9> Do the tests program after R/I of the Panel 438VU (Refer to AMM

31-10-00, Page Block 201)

<10>Do the tests program after R/I of the Panel 431VU (Refer to AMM

31-10-00, Page Block 201)

<11>Do the test of alignment procedure up to step 4 as described in the

IRS operational test (Refer to AMM 34-25-00, Page Block 501) for

each mode selector unit which has been removed for access

<12>Do the test procedure as specified after the installation of the

Cockpit Voice Recorder control unit (1RK) (Refer to AMM 23-71-12,

Page Block 401)

<13>Do the test procedure as specified after the installation of the APU

FIRE CONTROL MODULE (20WG) (Refer to AMM 26-13-20, Page

Block 401)

<14>Do the test procedure as specified after the installation of the

Engine Fire Control Module (39WD) (Refer to AMM 26-12-20, Page

Block 401)

<15>Do the O/T of the VHF3 system (Refer to AMM 23-12-00, Page

Block 501)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 192

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

<16>If CDSS is active for A/C, do the "Operational test of Video

Monitoring System", NOTE: If the SB reference is not specified in

the latest operator’s AMM issue, do these steps:

<a> Job Set-Up

[1] Connect the electrical ground power unit and energize the

aircraft electrical network (Refer to AMM 24-41-00, Page

Block 301).

[2] Make certain that the electronic rack ventilation is correct.

[3] Make certain that the following circuit breaker is closed:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

132VU CKPT/DOOR VIDEO/SPLY 15RA

<b> 2 Operational test of the Video Monitoring System

ACTION RESULT

1. In the cockpit, on panel 512VU:

- push the ’CKPT DOOR VIDEO’ pushbutton

switch

In the cockpit:

- the OFF legend in the ’CKPT DOOR VIDEO’

pushbutton switch goes off.

In the cockpit on the LCD:

- the green LED comes on

- the LCD monitor shows the images from camera

1.

2. In the cockpit, on panel 119VU:

- push the ’VIDEO’ pushbutton one time.

In the cockpit,on the LCD monitor:

- the left half of the LCD monitor screen shows

the images from camera 2

- the right half of the LCD monitor screen shows

the images of camera 3.

3. In the Cockpit, on the panel 119VU:

- push the ’VIDEO’ pushbutton one time.

In the cockpit,on the LCD monitor:

- the LCD monitor shows the images from camera

1.

4. In the cockpit, on the LCD monitor:

- turn the LCD monitor brightness knob clockwise

then counter-clockwise.

In the cockpit,on the LCD monitor:

- the brightness of the images change.

5. In the cockpit, on the LCD monitor:

- turn the LCD monitor contrast knob clockwise

then counter-clockwise.

In the cockpit, on the LCD monitor:

- the contrast of the images change.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 193

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

ACTION RESULT

6. In the cockpit, on the LCD monitor:

- turn the brightness and the contrast knobs to

their center positions.

7. In the cockpit, on the LCD monitor:

- use a flashlight to increase the light on the light

sensor, switch the flashlight on.

In the cockpit,on the LCD monitor:

- the brightness of the images change.

8. In the cockpit, on the LCD monitor:

- decrease the light on the light sensor, switch the

flashlight off.

In the cockpit,on the LCD monitor:

- the brightness of the images change.

9. In the cockpit, on panel 119VU:

- push the ’VIDEO’ pushbutton one time.

In the cockpit,on the LCD monitor:

- the left half of the LCD monitor screen shows

the images from camera 2

- the right half of the LCD monitor screen shows

the images from camera 3

- after five minutes the images go off (Stand-by

mode).

10. In the cockpit, on the panel 119VU:

- before the images on the LCD monitor go off for

30 seconds, push the ’VIDEO’ pushbutton one

time.

In the cockpit,on the LCD monitor:

- the images from camera 2 and camera 3 are

shown(split screen).

- after 5 minutes,the images go off (power-down

mode).

11. In the cockpit entrance area on the keypad

25MQ:

- enter the code to request entry to the cockpit

(Refer to AMM 52-51-00, Page Block 501).

In the cockpit:

- the horn is heard

- on the LCD monitor the image from camera 1 is

shown.

12. In the cockpit on the panel 119VU:

- push the ’VIDEO’ pushbutton one time.

In the cockpit on the LCD monitor:

- the images from camera 2 and 3 are shown

(split screen).

13. In the cockpit entrance area, on the keypad

25MQ:

- after the images from camera 2 and camera 3

are shown on the LCD monitor and before 29

seconds request entry to the cockpit.

In the cockpit on the LCD monitor:

- the images from camera 2 and camera 3 are

shown (split screen).

14. In the cockpit, on the panel 119VU:

- push the ’VIDEO’ pushbutton one time.

In the cockpit,on the LCD monitor:

- the image from camera 1 is shown.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 194

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

ACTION RESULT

15. In the cockpit on the panel 512VU:

- push the ’CKPT DOOR VIDEO’ pushbutton

switch.

In the cockpit on the panel 512VU:

- the ’OFF’ legend in the ’CKPT DOOR VIDEO’

pushbutton switch comes on.

In the cockpit on the LCD monitor:

- the green LED goes off

- the screen goes off.

<c> Close-Up

[1] De-energize the AC-External Power Control (Refer to

AMM 24-41-00, Page Block 301).

[2] Make sure that the work area is clean and clear of tools

and miscellaneous items of equipment.

<17>Do the O/T of the CDLS (Refer to AMM 52-51-00, Page Block 501)

c Do the tests program after R/I of the panel 104VU:

<1> Do a check of the Electrical Bonding (Refer to AMM 20-28-11, Page

Block 001)

NOTE: For maximun permissible resistance values: Refer to

the Table (Refer to AMM 20-28-11, Page Block 001)

<2> Do the test procedure as specified after the installation of the TRIM

TANK ISOLATION VALVE ACTUATOR (48QB), (Refer to AMM

28-22-55, Page Block 401)

<3> Do the test procedure as specified after the installation of the

INBOARD EXTRACT VALVE (74HR), (Refer to AMM 21-23-12,

Page Block 401)

<4> Do the test procedure as specified after the installation of the EFIS

SGU (28FN1, 28FN2, 28FN3), (Refer to AMM 34-73-34, Page Block

401)

<5> Do the test procedure as specified after the installation of the APU

GEN PWR LINE CONTACTOR 3XS, (Refer to AMM 24-23-13, Page

Block 401)

<6> Do the test procedure as specified after the installation of the FUEL

QUANTITY COMPUTER (15QT), (Refer to AMM 28-42-38, Page

Block 401)

<7> Do the test procedure as specified after the installation of the

TRANSFER VALVE ACTUATOR, (Refer to AMM 28-25-17, Page

Block 401) (if equipped)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 195

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

<8> Do the test procedure as specified after the installation of the

ACTUATOR - SELECTOR VALVE, (Refer to AMM 28-28-12, Page

Block 401) (if equipped)

<9> Do the test procedure as specified after the installation of the GEN 1

(2) LINE CONTACTOR 9XU (10XU), (Refer to AMM 24-22-15, Page

Block 401)

<10>Do the test procedure as specified after the installation of the

CABIN PRESSURE CONTROLLER 105HM (106HM), (Refer to

AMM 21-31-11, Page Block 401)

<11>Do the test procedure as specified after the installation of

the PNEUMATIC CONTROLLER 41HA (42HA), (Refer to AMM

36-11-19, Page Block 401) (if equipped)

<12>Do the test procedure as specified after the installation of the APU

FIRE CONTROL MODULE, (Refer to AMM 26-13-20, Page Block

401)

<13>Do the test procedure as specified after the installation of the

FLIGHT CONTROL COMPUTER (301CA1, 301CA2), (Refer to AMM

22-18-34, Page Block 401)

<14>Do the test procedure as specified after the installation of

the LANDING GEAR NORMAL CONTROL MICROSWITCH UNIT

(2GA), (Refer to AMM 32-31-11, Page Block 401)

d Do the tests program after R/I of the panel 105VU:

<1> Do a check of the Electrical Bonding (Refer to AMM 20-28-11, Page

Block 001)

NOTE: For maximun permissible resistance values: Refer to

the Table (Refer to AMM 20-28-11, Page Block 001)

<2> Do the Perform BITE test (Refer to AMM 36-11-00, Page Block

501), (Operational Test)

<3> Do the test procedure as specified after the installation of the

FLIGHT MANAGEMENT COMPUTER (1CK1, 1CK2), (Refer to

AMM 34-68-34, Page Block 401) (if equipped)

<4> Do the Functional Test - ENGINE FIRE CONTROL MODULE, (Refer

to AMM 26-12-20, Page Block 501)

<5> Do the test procedure as specified after the installation of the TCAS

COMPUTER (9005SG), (Refer to AMM 34-44-34, Page Block 401)

(if equipped)

<6> Do the Operational Test TAXI AND TAKEOFF LIGHTS, (Refer to

AMM 33-46-00, Page Block 501)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 196

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

<7> Do the test procedure as specified after the installation of the

THRUST CONTROL COMPUTER 301CJ1 (301CJ2), (Refer to AMM

22-36-34, Page Block 401)

<8> Carry out operational test of the flight compartment and electronics

racks air distribution system (Refer to AMM 21-21-00, Page Block

501)

<9> Do the test procedure as specified after the installation of the DOME

LIGHTS, (Refer to AMM 33-12-11, Page Block 401)

<10>Do the Operational test of the cabin distribution (Refer to AMM

21-22-00, Page Block 501) (if equipped)

<11>Do the test procedure for engine 1 as specified after the installation

of the LOW PRESSURE FUEL FIRE SHUT OFF VALVE, (Refer to

AMM 28-24-31, Page Block 401)

<12>Do the test procedure for engine 2 as specified after the installation

of the LOW PRESSURE FUEL FIRE SHUT OFF VALVE, (Refer to

AMM 28-24-31, Page Block 401)

e Do the test program after Removal/Installation of the panel 429VU

<1> Do the Functional Test of the windshield rain removal system (Refer

to AMM 30-45-00, Page Block 501).

<2> Do the Operational Test of the electrical ground power assisted APU

start (Refer to AMM 49-10-00, Page Block 501).

<3> Do the Operational Test of the APU pump (Refer to AMM 49-31-00,

Page Block 501).

<4> Do the Operational Test of the APU isolation valve (Refer to AMM

49-31-00, Page Block 501).

<5> Do the Operational Test of the ignition system (Refer to AMM

74-00-00, Page Block 501).

<6> Do an engine run (Refer to AMM 71-00-00, Page Block 501).

f Do the test of the AUTO RELIGHT system as follows:

<1> Job Set-Up

- Energize the aircraft electrical network (Refer to AMM 24-41-00,

Page Block 301).

- Make certain that electronics racks ventilation are correct.

- On panel 133VU, open, safety and tag this (these) circuit

breaker(s) related to ENGINES, except 1KG, 1JH, 2JH, 13JH,

14JH, 3KC, 4KC,

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 197

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

- Perform dry motoring (Refer to AMM 71-00-00, Page Block

501).

- Open the 105VU cowl and disconnect/remove relays 2KG and

3KG.

- Open cowl doors (Refer to AMM 71-13-00, Page Block 301).

- On panel 429VU, make sure that the ENG START selector

switch is in OFF position.

- Disconnect N2 RPM (Revolution per minute) indicators 3EP and

4EP (Refer to AMM 77-12-21, Page Block 401).

<2> Procedure

NOTE: This test is described for engine 1 only. For engine

2, refer to information between parentheses.

ACTION RESULT

On panel 9VU, place HP fuel shut off valve control

lever 1 (2) in ON position

On panel 133VU, Open circuit breaker 2GB (2GB)

NOTE: For CONF 007, open 119GB

instead of 2GB for engine 2

On panel 4VU, Connect the pin C of the N2 RPM

indicator 3EP (4EP) plug to the ground.

on engine 1 (2), igniter plugs A and B produce

normal sounds, proving that igniter plugs operate

correctly.

On panel 9VU, place HP (High Pressure) fuel shut

off valve control lever 1 (2) in OFF position

on engine 1 (2), igniter plugs A and B are cut off.

On panel 9VU, place HP fuel shut off valve control

lever 1 (2) in ON position

on engine 1 (2), igniter plugs A and B produce

normal sounds proving that igniter plugs operate

correctly

On panel 133VU, open AUTO RELIGHT ENG 1

(2) circuit breaker 13JH (14JH)

on engine 1 (2) , igniter plugs A and B are cut

off.

On panel 133VU, close AUTO RELIGHT ENG 1

(2) circuit breaker 13JH (14JH)

on engine 1 (2), igniter plugs A and B produce

normal sounds, proving that igniter plugs operate

correctly.

On panel 133VU, open IGNITION SYS A circuit

breaker 1JH

on engine 1 (2), igniter plug A is cut off.

on engine 1 (2), igniter plug B produces normal

sounds, proving that igniter plug operates

correctly.

On panel 133VU, close IGNITION SYS A circuit

breaker 1JH and open IGNITION SYS B circuit

breaker 2JH

on engine 1 (2), igniter plug B is cut off.

on engine 1 (2), igniter plug A produces normal

sounds, proving that igniter plug operates correctly

On panel 133VU, close IGNITION SYS B circuit

breaker 2JH

on engine 1 (2), igniter plugs A and B produce

normal sounds, proving that igniter plugs operate

correctly

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 198

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

ACTION RESULT

On panel 133VU, close circuit breaker 2GB (2GB)

NOTE: For CONF 007, close 119GB

instead of 2GB for engine 2

on engine 1 (2), igniter plugs A and B are cut off.

On panel 133VU, open circuit breaker 2GB (2GB)

NOTE: For CONF 007, open 119GB

instead of 2GB for engine 2

on engine 1 (2), igniter plugs A and B produce

normal sounds, proving that igniter plugs operate

correctly.

On panel 4VU, Disconnect the pin C of the N2

RPM indicator 3EP (4EP) plug from the ground.

on engine 1 (2), igniter plugs A and B are cut off

after 120 seconds.

On panel 133VU, close circuit breaker 2GB (2GB)

NOTE: For CONF 007, close 119GB

instead of 2GB for engine 2

On panel 9VU, place HP fuel shut off valve control

lever 1 (2) in OFF position

Repeat all the steps for engine 2.

<3> Close-up

- Reconnect N2 RPM indicators 3EP and 4EP and perform the

test of the N2 RPM indicators (Refer to AMM 77-12-21, Page

Block 401).

- Re-install the relays 2KG and 3KG (Refer to ESPM 20-46-50)

- Close cowl doors (Refer to AMM 71-13-00, Page Block 301).

- Perform an engine dry motoring (Refer to AMM 71-00-00, Page

Block 501)

- De-energize the aircraft electrical network (Refer to AMM

24-41-00, Page Block 301).

- Restore system and aircraft to normal operating condition

**CONF 007

(1) Subtask 742003-720-001-001 - Test

Manpower Resources

Skills ELECTRICAL

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 199

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 20-28-11, Page Block 001

21-21-00, Page Block 501

21-22-00, Page Block 501

21-23-12, Page Block 401

21-31-11, Page Block 401

22-18-34, Page Block 401

22-36-34, Page Block 401

22-40-00, Page Block 501

23-12-00, Page Block 501

23-71-12, Page Block 401

24-22-15, Page Block 401

24-23-13, Page Block 401

24-31-11, Page Block 401

24-41-00, Page Block 301

26-12-20, Page Block 401

26-12-20, Page Block 501

26-13-20, Page Block 401

26-13-20, Page Block 401

28-22-55, Page Block 401

28-24-31, Page Block 401

28-25-17, Page Block 401

28-28-12, Page Block 401

28-42-38, Page Block 401

28-42-41, Page Block 401

30-45-00, Page Block 501

31-10-00, Page Block 201

31-51-00, Page Block 501

31-69-00, Page Block 501

32-31-11, Page Block 401

33-12-00, Page Block 501

33-12-11, Page Block 401

33-13-00, Page Block 501

33-14-00, Page Block 501

33-46-00, Page Block 501

34-25-00, Page Block 501

34-44-34, Page Block 401

34-68-34, Page Block 401

34-73-34, Page Block 401

36-11-00, Page Block 501

36-11-19, Page Block 401

49-10-00, Page Block 501

49-31-00, Page Block 501

52-51-00, Page Block 501

71-00-00, Page Block 501

71-13-00, Page Block 301

74-00-00, Page Block 501

77-12-21, Page Block 401

Elec. Std. Practices Manual (ESPM) 20-46-50

20-52-10

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 200

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(a) Job Set-up

1 Battery re-connection

- For Job Set-up, refer to Installation of the Batteries (Refer to AMM

24-31-11, Page Block 401)

- Remove the blanking cap from the electrical connectors

- Make sure that the electrical connectors are clean and in correct condition

- Connect the connector on the battery

- Turn the knurled nut a quarter turn

2 Remove all warning notices.

3 Open, safety/lock and tag this (these) circuit breaker(s):

PANEL DESIGNATION FIN LOCATION SEE

NOTES

133 ENGINE 1/FUEL HP

VALVE/WARN

1KC T68

133 ENGINE 2/FUEL HP

VALVE/WARN

2KC R73

133 ENGINE 1/AUTORELIGHT 13JH S69

133 ENGINE 2/AUTORELIGHT 14JH S74

133 STBY GEN AIR VALVE 17XE T83

133 ENGINE 1/LO/PRESS 1ES Q69

4 Energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page Block

301)

5 Do a voltage check at pin 1 of each following circuit breaker to make sure that

there is 28VDC.

PANEL DESIGNATION FIN LOCATION SEE

NOTES

133 ENGINE 1/FUEL HP

VALVE/WARN

1KC T68

133 ENGINE 2/FUEL HP

VALVE/WARN

2KC R73

133 ENGINE 1/AUTORELIGHT 13JH S69

133 ENGINE 2/AUTORELIGHT 14JH S74

133 STBY GEN AIR VALVE 17XE T83

133 ENGINE 1/LO/PRESS 1ES Q69

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 201

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

6 Remove the safety clip(s) and/or tag(s) and close/unlock this (these) circuit

breaker(s):

PANEL DESIGNATION FIN LOCATION SEE

NOTES

133 ENGINE 1/FUEL HP

VALVE/WARN

1KC T68

133 ENGINE 2/FUEL HP

VALVE/WARN

2KC R73

133 ENGINE 1/AUTORELIGHT 13JH S69

133 ENGINE 2/AUTORELIGHT 14JH S74

133 STBY GEN AIR VALVE 17XE T83

133 ENGINE 1/LO/PRESS 1ES Q69

7 Preliminary Tests :

NOTE: If the aircraft is operated in CAT3 conditions, you must also do

the LAND test (Refer to AMM 22-40-00, Page Block 501)

a On each connector which was disconnected:

- Do the checks as defined by ESPM 20-52-10.

NOTE: The Functional test and/or operational test requested by

this ESPM procedure is given hereafter.

b Do the Operational Test of the Annunciator Light Test AMM (Refer to

AMM 33-14-00, Page Block 501).

c Do the Operational Test of the General Illumination, (Refer to AMM

33-12-00, Page Block 501).

d Do the Operational Test of the Instrument and Panel Integral Lighting,

(Refer to AMM 33-13-00, Page Block 501).

e Make certain that the ventillation system operates correctly, (Refer to

AMM 21-21-00, Page Block 501).

f Do the AFS (Automatic Flight System) Test, (Refer to AMM 22-40-00,

Page Block 501)(para 1.A)).

g Do the Operational Test of ECAM/EFIS Display Test, (Refer to AMM

31-51-00, Page Block 501).

h Do the Operational Test of the FWC1 and FWC2, (Refer to AMM

31-51-00, Page Block 501).

(b) Test

1 Procedure

a Do the Operational Test of the circuit breaker monitoring system for panel

133VU (Refer to AMM 31-69-00, Page Block 501).

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 202

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

b Do the tests program after R/I of the panel 20VU:

<1> Do the test procedure as specified after the installation of the FUEL

QUANTITY INDICATOR (6QT), (Refer to AMM 28-42-41, Page

Block 401)

<2> Do the tests program after R/I of the Panel 45VU, (Refer to AMM

31-10-00, Page Block 201)

<3> Do the tests program after R/I of the Panel 76VU (Refer to AMM

31-10-00, Page Block 201)

<4> Do the tests program after R/I of the Panel 424VU (Refer to AMM

31-10-00, Page Block 201)

<5> Do the tests program after R/I of the Panel 425VU (Refer to AMM

31-10-00, Page Block 201)

<6> Do the tests program after R/I of the Panel 430VU (Refer to AMM

31-10-00, Page Block 201)

<7> Do the tests program after R/I of the Panel 433VU (Refer to AMM

31-10-00, Page Block 201)

<8> Do the tests program after R/I of the Panel 435VU (Refer to AMM

31-10-00, Page Block 201)

<9> Do the tests program after R/I of the Panel 438VU (Refer to AMM

31-10-00, Page Block 201)

<10>Do the tests program after R/I of the Panel 431VU (Refer to AMM

31-10-00, Page Block 201)

<11>Do the test of alignment procedure up to step 4 as described in the

IRS operational test (Refer to AMM 34-25-00, Page Block 501) for

each mode selector unit which has been removed for access

<12>Do the test procedure as specified after the installation of the

Cockpit Voice Recorder control unit (1RK) (Refer to AMM 23-71-12,

Page Block 401)

<13>Do the test procedure as specified after the installation of the APU

FIRE CONTROL MODULE (20WG) (Refer to AMM 26-13-20, Page

Block 401)

<14>Do the test procedure as specified after the installation of the

Engine Fire Control Module (39WD) (Refer to AMM 26-12-20, Page

Block 401)

<15>Do the O/T of the VHF3 system (Refer to AMM 23-12-00, Page

Block 501)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 203

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

<16>If CDSS is active for A/C, do the "Operational test of Video

Monitoring System", NOTE: If the SB reference is not specified in

the latest operator’s AMM issue, do these steps:

<a> Job Set-Up

[1] Connect the electrical ground power unit and energize the

aircraft electrical network (Refer to AMM 24-41-00, Page

Block 301).

[2] Make certain that the electronic rack ventilation is correct.

[3] Make certain that the following circuit breaker is closed:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

132VU CKPT/DOOR VIDEO/SPLY 15RA

<b> 2 Operational test of the Video Monitoring System

ACTION RESULT

1. In the cockpit, on panel 512VU:

- push the ’CKPT DOOR VIDEO’ pushbutton

switch

In the cockpit:

- the OFF legend in the ’CKPT DOOR VIDEO’

pushbutton switch goes off.

In the cockpit on the LCD:

- the green LED comes on

- the LCD monitor shows the images from camera

1.

2. In the cockpit, on panel 119VU:

- push the ’VIDEO’ pushbutton one time.

In the cockpit,on the LCD monitor:

- the left half of the LCD monitor screen shows

the images from camera 2

- the right half of the LCD monitor screen shows

the images of camera 3.

3. In the Cockpit, on the panel 119VU:

- push the ’VIDEO’ pushbutton one time.

In the cockpit,on the LCD monitor:

- the LCD monitor shows the images from camera

1.

4. In the cockpit, on the LCD monitor:

- turn the LCD monitor brightness knob clockwise

then counter-clockwise.

In the cockpit,on the LCD monitor:

- the brightness of the images change.

5. In the cockpit, on the LCD monitor:

- turn the LCD monitor contrast knob clockwise

then counter-clockwise.

In the cockpit, on the LCD monitor:

- the contrast of the images change.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 204

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

ACTION RESULT

6. In the cockpit, on the LCD monitor:

- turn the brightness and the contrast knobs to

their center positions.

7. In the cockpit, on the LCD monitor:

- use a flashlight to increase the light on the light

sensor, switch the flashlight on.

In the cockpit,on the LCD monitor:

- the brightness of the images change.

8. In the cockpit, on the LCD monitor:

- decrease the light on the light sensor, switch the

flashlight off.

In the cockpit,on the LCD monitor:

- the brightness of the images change.

9. In the cockpit, on panel 119VU:

- push the ’VIDEO’ pushbutton one time.

In the cockpit,on the LCD monitor:

- the left half of the LCD monitor screen shows

the images from camera 2

- the right half of the LCD monitor screen shows

the images from camera 3

- after five minutes the images go off (Stand-by

mode).

10. In the cockpit, on the panel 119VU:

- before the images on the LCD monitor go off for

30 seconds, push the ’VIDEO’ pushbutton one

time.

In the cockpit,on the LCD monitor:

- the images from camera 2 and camera 3 are

shown(split screen).

- after 5 minutes,the images go off (power-down

mode).

11. In the cockpit entrance area on the keypad

25MQ:

- enter the code to request entry to the cockpit

(Refer to AMM 52-51-00, Page Block 501).

In the cockpit:

- the horn is heard

- on the LCD monitor the image from camera 1 is

shown.

12. In the cockpit on the panel 119VU:

- push the ’VIDEO’ pushbutton one time.

In the cockpit on the LCD monitor:

- the images from camera 2 and 3 are shown

(split screen).

13. In the cockpit entrance area, on the keypad

25MQ:

- after the images from camera 2 and camera 3

are shown on the LCD monitor and before 29

seconds request entry to the cockpit.

In the cockpit on the LCD monitor:

- the images from camera 2 and camera 3 are

shown (split screen).

14. In the cockpit, on the panel 119VU:

- push the ’VIDEO’ pushbutton one time.

In the cockpit,on the LCD monitor:

- the image from camera 1 is shown.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 205

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

ACTION RESULT

15. In the cockpit on the panel 512VU:

- push the ’CKPT DOOR VIDEO’ pushbutton

switch.

In the cockpit on the panel 512VU:

- the ’OFF’ legend in the ’CKPT DOOR VIDEO’

pushbutton switch comes on.

In the cockpit on the LCD monitor:

- the green LED goes off

- the screen goes off.

<c> Close-Up

[1] De-energize the AC-External Power Control (Refer to

AMM 24-41-00, Page Block 301).

[2] Make sure that the work area is clean and clear of tools

and miscellaneous items of equipment.

<17>Do the O/T of the CDLS (Refer to AMM 52-51-00, Page Block 501)

c Do the tests program after R/I of the panel 104VU:

<1> Do a check of the Electrical Bonding (Refer to AMM 20-28-11, Page

Block 001)

NOTE: For maximun permissible resistance values: Refer to

the Table (Refer to AMM 20-28-11, Page Block 001)

<2> Do the test procedure as specified after the installation of the TRIM

TANK ISOLATION VALVE ACTUATOR (48QB), (Refer to AMM

28-22-55, Page Block 401)

<3> Do the test procedure as specified after the installation of the

INBOARD EXTRACT VALVE (74HR), (Refer to AMM 21-23-12,

Page Block 401)

<4> Do the test procedure as specified after the installation of the EFIS

SGU (28FN1, 28FN2, 28FN3), (Refer to AMM 34-73-34, Page Block

401)

<5> Do the test procedure as specified after the installation of the APU

GEN PWR LINE CONTACTOR 3XS, (Refer to AMM 24-23-13, Page

Block 401)

<6> Do the test procedure as specified after the installation of the FUEL

QUANTITY COMPUTER (15QT), (Refer to AMM 28-42-38, Page

Block 401)

<7> Do the test procedure as specified after the installation of the

TRANSFER VALVE ACTUATOR, (Refer to AMM 28-25-17, Page

Block 401) (if equipped)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 206

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

<8> Do the test procedure as specified after the installation of the

ACTUATOR - SELECTOR VALVE, (Refer to AMM 28-28-12, Page

Block 401) (if equipped)

<9> Do the test procedure as specified after the installation of the GEN 1

(2) LINE CONTACTOR 9XU (10XU), (Refer to AMM 24-22-15, Page

Block 401)

<10>Do the test procedure as specified after the installation of the

CABIN PRESSURE CONTROLLER 105HM (106HM), (Refer to

AMM 21-31-11, Page Block 401)

<11>Do the test procedure as specified after the installation of

the PNEUMATIC CONTROLLER 41HA (42HA), (Refer to AMM

36-11-19, Page Block 401) (if equipped)

<12>Do the test procedure as specified after the installation of the APU

FIRE CONTROL MODULE, (Refer to AMM 26-13-20, Page Block

401)

<13>Do the test procedure as specified after the installation of the

FLIGHT CONTROL COMPUTER (301CA1, 301CA2), (Refer to AMM

22-18-34, Page Block 401)

<14>Do the test procedure as specified after the installation of

the LANDING GEAR NORMAL CONTROL MICROSWITCH UNIT

(2GA), (Refer to AMM 32-31-11, Page Block 401)

d Do the tests program after R/I of the panel 105VU:

<1> Do a check of the Electrical Bonding (Refer to AMM 20-28-11, Page

Block 001)

NOTE: For maximun permissible resistance values: Refer to

the Table (Refer to AMM 20-28-11, Page Block 001)

<2> Do the Perform BITE test (Refer to AMM 36-11-00, Page Block

501), (Operational Test)

<3> Do the test procedure as specified after the installation of the

FLIGHT MANAGEMENT COMPUTER (1CK1, 1CK2), (Refer to

AMM 34-68-34, Page Block 401) (if equipped)

<4> Do the Functional Test - ENGINE FIRE CONTROL MODULE, (Refer

to AMM 26-12-20, Page Block 501)

<5> Do the test procedure as specified after the installation of the TCAS

COMPUTER (9005SG), (Refer to AMM 34-44-34, Page Block 401)

(if equipped)

<6> Do the Operational Test TAXI AND TAKEOFF LIGHTS, (Refer to

AMM 33-46-00, Page Block 501)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 207

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

<7> Do the test procedure as specified after the installation of the

THRUST CONTROL COMPUTER 301CJ1 (301CJ2), (Refer to AMM

22-36-34, Page Block 401)

<8> Carry out operational test of the flight compartment and electronics

racks air distribution system (Refer to AMM 21-21-00, Page Block

501)

<9> Do the test procedure as specified after the installation of the DOME

LIGHTS, (Refer to AMM 33-12-11, Page Block 401)

<10>Do the Operational test of the cabin distribution (Refer to AMM

21-22-00, Page Block 501) (if equipped)

<11>Do the test procedure for engine 1 as specified after the installation

of the LOW PRESSURE FUEL FIRE SHUT OFF VALVE, (Refer to

AMM 28-24-31, Page Block 401)

<12>Do the test procedure for engine 2 as specified after the installation

of the LOW PRESSURE FUEL FIRE SHUT OFF VALVE, (Refer to

AMM 28-24-31, Page Block 401)

e Do the test program after Removal/Installation of the panel 429VU

<1> Do the Functional Test of the windshield rain removal system (Refer

to AMM 30-45-00, Page Block 501).

<2> Do the Operational Test of the electrical ground power assisted APU

start (Refer to AMM 49-10-00, Page Block 501).

<3> Do the Operational Test of the APU pump (Refer to AMM 49-31-00,

Page Block 501).

<4> Do the Operational Test of the APU isolation valve (Refer to AMM

49-31-00, Page Block 501).

<5> Do the Operational Test of the ignition system (Refer to AMM

74-00-00, Page Block 501).

<6> Do an engine run (Refer to AMM 71-00-00, Page Block 501).

f Do the test of the AUTO RELIGHT system as follows:

<1> Job Set-Up

- Energize the aircraft electrical network (Refer to AMM 24-41-00,

Page Block 301).

- Make certain that electronics racks ventilation are correct.

- On panel 133VU, open, safety and tag this (these) circuit

breaker(s) related to ENGINES, except 1KG, 1JH, 2JH, 13JH,

14JH, 3KC, 4KC,

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 208

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

- Perform dry motoring (Refer to AMM 71-00-00, Page Block

501).

- Open the 105VU cowl and disconnect/remove relays 2KG and

3KG.

- Open cowl doors (Refer to AMM 71-13-00, Page Block 301).

- On panel 429VU, make sure that the ENG START selector

switch is in OFF position.

- Disconnect N2 RPM (Revolution per minute) indicators 3EP and

4EP (Refer to AMM 77-12-21, Page Block 401).

<2> Procedure

NOTE: This test is described for engine 1 only. For engine

2, refer to information between parentheses.

ACTION RESULT

On panel 9VU, place HP fuel shut off valve control

lever 1 (2) in ON position

On panel 133VU, Open circuit breaker 2GB (2GB)

NOTE: For CONF 007, open 119GB

instead of 2GB for engine 2

On panel 4VU, Connect the pin C of the N2 RPM

indicator 3EP (4EP) plug to the ground.

on engine 1 (2), igniter plugs A and B produce

normal sounds, proving that igniter plugs operate

correctly.

On panel 9VU, place HP (High Pressure) fuel shut

off valve control lever 1 (2) in OFF position

on engine 1 (2), igniter plugs A and B are cut off.

On panel 9VU, place HP fuel shut off valve control

lever 1 (2) in ON position

on engine 1 (2), igniter plugs A and B produce

normal sounds proving that igniter plugs operate

correctly

On panel 133VU, open AUTO RELIGHT ENG 1

(2) circuit breaker 13JH (14JH)

on engine 1 (2) , igniter plugs A and B are cut

off.

On panel 133VU, close AUTO RELIGHT ENG 1

(2) circuit breaker 13JH (14JH)

on engine 1 (2), igniter plugs A and B produce

normal sounds, proving that igniter plugs operate

correctly.

On panel 133VU, open IGNITION SYS A circuit

breaker 1JH

on engine 1 (2), igniter plug A is cut off.

on engine 1 (2), igniter plug B produces normal

sounds, proving that igniter plug operates

correctly.

On panel 133VU, close IGNITION SYS A circuit

breaker 1JH and open IGNITION SYS B circuit

breaker 2JH

on engine 1 (2), igniter plug B is cut off.

on engine 1 (2), igniter plug A produces normal

sounds, proving that igniter plug operates correctly

On panel 133VU, close IGNITION SYS B circuit

breaker 2JH

on engine 1 (2), igniter plugs A and B produce

normal sounds, proving that igniter plugs operate

correctly

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 209

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

ACTION RESULT

On panel 133VU, close circuit breaker 2GB (2GB)

NOTE: For CONF 007, close 119GB

instead of 2GB for engine 2

on engine 1 (2), igniter plugs A and B are cut off.

On panel 133VU, open circuit breaker 2GB (2GB)

NOTE: For CONF 007, open 119GB

instead of 2GB for engine 2

on engine 1 (2), igniter plugs A and B produce

normal sounds, proving that igniter plugs operate

correctly.

On panel 4VU, Disconnect the pin C of the N2

RPM indicator 3EP (4EP) plug from the ground.

on engine 1 (2), igniter plugs A and B are cut off

after 120 seconds.

On panel 133VU, close circuit breaker 2GB (2GB)

NOTE: For CONF 007, close 119GB

instead of 2GB for engine 2

On panel 9VU, place HP fuel shut off valve control

lever 1 (2) in OFF position

Repeat all the steps for engine 2.

<3> Close-up

- Reconnect N2 RPM indicators 3EP and 4EP and perform the

test of the N2 RPM indicators (Refer to AMM 77-12-21, Page

Block 401).

- Re-install the relays 2KG and 3KG (Refer to ESPM 20-46-50)

- Close cowl doors (Refer to AMM 71-13-00, Page Block 301).

- Perform an engine dry motoring (Refer to AMM 71-00-00, Page

Block 501)

- De-energize the aircraft electrical network (Refer to AMM

24-41-00, Page Block 301).

- Restore system and aircraft to normal operating condition

**CONF 008

(1) Subtask 742003-720-001-001 - Test

Manpower Resources

Skills ELECTRICAL

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 210

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 20-28-11, Page Block 001

21-21-00, Page Block 501

21-22-00, Page Block 501

21-23-12, Page Block 401

21-31-11, Page Block 401

22-18-34, Page Block 401

22-36-34, Page Block 401

22-40-00, Page Block 501

23-12-00, Page Block 501

23-71-12, Page Block 401

24-22-15, Page Block 401

24-23-13, Page Block 401

24-31-11, Page Block 401

24-41-00, Page Block 301

26-12-20, Page Block 401

26-12-20, Page Block 501

26-13-20, Page Block 401

26-13-20, Page Block 401

28-22-55, Page Block 401

28-24-31, Page Block 401

28-25-17, Page Block 401

28-28-12, Page Block 401

28-42-38, Page Block 401

28-42-41, Page Block 401

30-45-00, Page Block 501

31-10-00, Page Block 201

31-51-00, Page Block 501

31-69-00, Page Block 501

32-31-11, Page Block 401

33-12-00, Page Block 501

33-12-11, Page Block 401

33-13-00, Page Block 501

33-14-00, Page Block 501

33-46-00, Page Block 501

34-25-00, Page Block 501

34-44-34, Page Block 401

34-68-34, Page Block 401

34-73-34, Page Block 401

36-11-00, Page Block 501

36-11-19, Page Block 401

49-10-00, Page Block 501

49-31-00, Page Block 501

52-51-00, Page Block 501

71-00-00, Page Block 501

71-13-00, Page Block 301

74-00-00, Page Block 501

77-12-21, Page Block 401

Elec. Std. Practices Manual (ESPM) 20-46-50

20-52-10

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 211

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(a) Job Set-up

1 Battery re-connection

- For Job Set-up, refer to Installation of the Batteries (Refer to AMM

24-31-11, Page Block 401)

- Remove the blanking cap from the electrical connectors

- Make sure that the electrical connectors are clean and in correct condition

- Connect the connector on the battery

- Turn the knurled nut a quarter turn

2 Remove all warning notices.

3 Open, safety/lock and tag this (these) circuit breaker(s):

PANEL DESIGNATION FIN LOCATION SEE

NOTES

133 ENGINE 1/FUEL HP

VALVE/WARN

1KC T68

133 ENGINE 2/FUEL HP

VALVE/WARN

2KC R73

133 ENGINE 1/AUTORELIGHT 13JH S69

133 ENGINE 2/AUTORELIGHT 14JH S74

133 STBY GEN AIR VALVE 17XE T83

133 ENGINE 1/LO/PRESS 1ES Q69

4 Energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page Block

301)

5 Do a voltage check at pin 1 of each following circuit breaker to make sure that

there is 28VDC.

PANEL DESIGNATION FIN LOCATION SEE

NOTES

133 ENGINE 1/FUEL HP

VALVE/WARN

1KC T68

133 ENGINE 2/FUEL HP

VALVE/WARN

2KC R73

133 ENGINE 1/AUTORELIGHT 13JH S69

133 ENGINE 2/AUTORELIGHT 14JH S74

133 STBY GEN AIR VALVE 17XE T83

133 ENGINE 1/LO/PRESS 1ES Q69

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 212

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

6 Remove the safety clip(s) and/or tag(s) and close/unlock this (these) circuit

breaker(s):

PANEL DESIGNATION FIN LOCATION SEE

NOTES

133 ENGINE 1/FUEL HP

VALVE/WARN

1KC T68

133 ENGINE 2/FUEL HP

VALVE/WARN

2KC R73

133 ENGINE 1/AUTORELIGHT 13JH S69

133 ENGINE 2/AUTORELIGHT 14JH S74

133 STBY GEN AIR VALVE 17XE T83

133 ENGINE 1/LO/PRESS 1ES Q69

7 Preliminary Tests :

NOTE: If the aircraft is operated in CAT3 conditions, you must also do

the LAND test (Refer to AMM 22-40-00, Page Block 501)

a On each connector which was disconnected:

- Do the checks as defined by ESPM 20-52-10.

NOTE: The Functional test and/or operational test requested by

this ESPM procedure is given hereafter.

b Do the Operational Test of the Annunciator Light Test AMM (Refer to

AMM 33-14-00, Page Block 501).

c Do the Operational Test of the General Illumination, (Refer to AMM

33-12-00, Page Block 501).

d Do the Operational Test of the Instrument and Panel Integral Lighting,

(Refer to AMM 33-13-00, Page Block 501).

e Make certain that the ventillation system operates correctly, (Refer to

AMM 21-21-00, Page Block 501).

f Do the AFS (Automatic Flight System) Test, (Refer to AMM 22-40-00,

Page Block 501)(para 1.A)).

g Do the Operational Test of ECAM/EFIS Display Test, (Refer to AMM

31-51-00, Page Block 501).

h Do the Operational Test of the FWC1 and FWC2, (Refer to AMM

31-51-00, Page Block 501).

(b) Test

1 Procedure

a Do the Operational Test of the circuit breaker monitoring system for panel

133VU (Refer to AMM 31-69-00, Page Block 501).

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 213

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

b Do the tests program after R/I of the panel 20VU:

<1> Do the test procedure as specified after the installation of the FUEL

QUANTITY INDICATOR (6QT), (Refer to AMM 28-42-41, Page

Block 401)

<2> Do the tests program after R/I of the Panel 45VU, (Refer to AMM

31-10-00, Page Block 201)

<3> Do the tests program after R/I of the Panel 76VU (Refer to AMM

31-10-00, Page Block 201)

<4> Do the tests program after R/I of the Panel 424VU (Refer to AMM

31-10-00, Page Block 201)

<5> Do the tests program after R/I of the Panel 425VU (Refer to AMM

31-10-00, Page Block 201)

<6> Do the tests program after R/I of the Panel 430VU (Refer to AMM

31-10-00, Page Block 201)

<7> Do the tests program after R/I of the Panel 433VU (Refer to AMM

31-10-00, Page Block 201)

<8> Do the tests program after R/I of the Panel 435VU (Refer to AMM

31-10-00, Page Block 201)

<9> Do the tests program after R/I of the Panel 438VU (Refer to AMM

31-10-00, Page Block 201)

<10>Do the tests program after R/I of the Panel 431VU (Refer to AMM

31-10-00, Page Block 201)

<11>Do the test of alignment procedure up to step 4 as described in the

IRS operational test (Refer to AMM 34-25-00, Page Block 501) for

each mode selector unit which has been removed for access

<12>Do the test procedure as specified after the installation of the

Cockpit Voice Recorder control unit (1RK) (Refer to AMM 23-71-12,

Page Block 401)

<13>Do the test procedure as specified after the installation of the APU

FIRE CONTROL MODULE (20WG) (Refer to AMM 26-13-20, Page

Block 401)

<14>Do the test procedure as specified after the installation of the

Engine Fire Control Module (39WD) (Refer to AMM 26-12-20, Page

Block 401)

<15>Do the O/T of the VHF3 system (Refer to AMM 23-12-00, Page

Block 501)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 214

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

<16>If CDSS is active for A/C, do the "Operational test of Video

Monitoring System", NOTE: If the SB reference is not specified in

the latest operator’s AMM issue, do these steps:

<a> Job Set-Up

[1] Connect the electrical ground power unit and energize the

aircraft electrical network (Refer to AMM 24-41-00, Page

Block 301).

[2] Make certain that the electronic rack ventilation is correct.

[3] Make certain that the following circuit breaker is closed:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

132VU CKPT/DOOR VIDEO/SPLY 15RA

<b> 2 Operational test of the Video Monitoring System

ACTION RESULT

1. In the cockpit, on panel 512VU:

- push the ’CKPT DOOR VIDEO’ pushbutton

switch

In the cockpit:

- the OFF legend in the ’CKPT DOOR VIDEO’

pushbutton switch goes off.

In the cockpit on the LCD:

- the green LED comes on

- the LCD monitor shows the images from camera

1.

2. In the cockpit, on panel 119VU:

- push the ’VIDEO’ pushbutton one time.

In the cockpit,on the LCD monitor:

- the left half of the LCD monitor screen shows

the images from camera 2

- the right half of the LCD monitor screen shows

the images of camera 3.

3. In the Cockpit, on the panel 119VU:

- push the ’VIDEO’ pushbutton one time.

In the cockpit,on the LCD monitor:

- the LCD monitor shows the images from camera

1.

4. In the cockpit, on the LCD monitor:

- turn the LCD monitor brightness knob clockwise

then counter-clockwise.

In the cockpit,on the LCD monitor:

- the brightness of the images change.

5. In the cockpit, on the LCD monitor:

- turn the LCD monitor contrast knob clockwise

then counter-clockwise.

In the cockpit, on the LCD monitor:

- the contrast of the images change.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 215

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

ACTION RESULT

6. In the cockpit, on the LCD monitor:

- turn the brightness and the contrast knobs to

their center positions.

7. In the cockpit, on the LCD monitor:

- use a flashlight to increase the light on the light

sensor, switch the flashlight on.

In the cockpit,on the LCD monitor:

- the brightness of the images change.

8. In the cockpit, on the LCD monitor:

- decrease the light on the light sensor, switch the

flashlight off.

In the cockpit,on the LCD monitor:

- the brightness of the images change.

9. In the cockpit, on panel 119VU:

- push the ’VIDEO’ pushbutton one time.

In the cockpit,on the LCD monitor:

- the left half of the LCD monitor screen shows

the images from camera 2

- the right half of the LCD monitor screen shows

the images from camera 3

- after five minutes the images go off (Stand-by

mode).

10. In the cockpit, on the panel 119VU:

- before the images on the LCD monitor go off for

30 seconds, push the ’VIDEO’ pushbutton one

time.

In the cockpit,on the LCD monitor:

- the images from camera 2 and camera 3 are

shown(split screen).

- after 5 minutes,the images go off (power-down

mode).

11. In the cockpit entrance area on the keypad

25MQ:

- enter the code to request entry to the cockpit

(Refer to AMM 52-51-00, Page Block 501).

In the cockpit:

- the horn is heard

- on the LCD monitor the image from camera 1 is

shown.

12. In the cockpit on the panel 119VU:

- push the ’VIDEO’ pushbutton one time.

In the cockpit on the LCD monitor:

- the images from camera 2 and 3 are shown

(split screen).

13. In the cockpit entrance area, on the keypad

25MQ:

- after the images from camera 2 and camera 3

are shown on the LCD monitor and before 29

seconds request entry to the cockpit.

In the cockpit on the LCD monitor:

- the images from camera 2 and camera 3 are

shown (split screen).

14. In the cockpit, on the panel 119VU:

- push the ’VIDEO’ pushbutton one time.

In the cockpit,on the LCD monitor:

- the image from camera 1 is shown.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 216

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

ACTION RESULT

15. In the cockpit on the panel 512VU:

- push the ’CKPT DOOR VIDEO’ pushbutton

switch.

In the cockpit on the panel 512VU:

- the ’OFF’ legend in the ’CKPT DOOR VIDEO’

pushbutton switch comes on.

In the cockpit on the LCD monitor:

- the green LED goes off

- the screen goes off.

<c> Close-Up

[1] De-energize the AC-External Power Control (Refer to

AMM 24-41-00, Page Block 301).

[2] Make sure that the work area is clean and clear of tools

and miscellaneous items of equipment.

<17>Do the O/T of the CDLS (Refer to AMM 52-51-00, Page Block 501)

c Do the tests program after R/I of the panel 104VU:

<1> Do a check of the Electrical Bonding (Refer to AMM 20-28-11, Page

Block 001)

NOTE: For maximun permissible resistance values: Refer to

the Table (Refer to AMM 20-28-11, Page Block 001)

<2> Do the test procedure as specified after the installation of the TRIM

TANK ISOLATION VALVE ACTUATOR (48QB), (Refer to AMM

28-22-55, Page Block 401)

<3> Do the test procedure as specified after the installation of the

INBOARD EXTRACT VALVE (74HR), (Refer to AMM 21-23-12,

Page Block 401)

<4> Do the test procedure as specified after the installation of the EFIS

SGU (28FN1, 28FN2, 28FN3), (Refer to AMM 34-73-34, Page Block

401)

<5> Do the test procedure as specified after the installation of the APU

GEN PWR LINE CONTACTOR 3XS, (Refer to AMM 24-23-13, Page

Block 401)

<6> Do the test procedure as specified after the installation of the FUEL

QUANTITY COMPUTER (15QT), (Refer to AMM 28-42-38, Page

Block 401)

<7> Do the test procedure as specified after the installation of the

TRANSFER VALVE ACTUATOR, (Refer to AMM 28-25-17, Page

Block 401) (if equipped)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 217

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

<8> Do the test procedure as specified after the installation of the

ACTUATOR - SELECTOR VALVE, (Refer to AMM 28-28-12, Page

Block 401) (if equipped)

<9> Do the test procedure as specified after the installation of the GEN 1

(2) LINE CONTACTOR 9XU (10XU), (Refer to AMM 24-22-15, Page

Block 401)

<10>Do the test procedure as specified after the installation of the

CABIN PRESSURE CONTROLLER 105HM (106HM), (Refer to

AMM 21-31-11, Page Block 401)

<11>Do the test procedure as specified after the installation of

the PNEUMATIC CONTROLLER 41HA (42HA), (Refer to AMM

36-11-19, Page Block 401) (if equipped)

<12>Do the test procedure as specified after the installation of the APU

FIRE CONTROL MODULE, (Refer to AMM 26-13-20, Page Block

401)

<13>Do the test procedure as specified after the installation of the

FLIGHT CONTROL COMPUTER (301CA1, 301CA2), (Refer to AMM

22-18-34, Page Block 401)

<14>Do the test procedure as specified after the installation of

the LANDING GEAR NORMAL CONTROL MICROSWITCH UNIT

(2GA), (Refer to AMM 32-31-11, Page Block 401)

d Do the tests program after R/I of the panel 105VU:

<1> Do a check of the Electrical Bonding (Refer to AMM 20-28-11, Page

Block 001)

NOTE: For maximun permissible resistance values: Refer to

the Table (Refer to AMM 20-28-11, Page Block 001)

<2> Do the Perform BITE test (Refer to AMM 36-11-00, Page Block

501), (Operational Test)

<3> Do the test procedure as specified after the installation of the

FLIGHT MANAGEMENT COMPUTER (1CK1, 1CK2), (Refer to

AMM 34-68-34, Page Block 401) (if equipped)

<4> Do the Functional Test - ENGINE FIRE CONTROL MODULE, (Refer

to AMM 26-12-20, Page Block 501)

<5> Do the test procedure as specified after the installation of the TCAS

COMPUTER (9005SG), (Refer to AMM 34-44-34, Page Block 401)

(if equipped)

<6> Do the Operational Test TAXI AND TAKEOFF LIGHTS, (Refer to

AMM 33-46-00, Page Block 501)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 218

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

<7> Do the test procedure as specified after the installation of the

THRUST CONTROL COMPUTER 301CJ1 (301CJ2), (Refer to AMM

22-36-34, Page Block 401)

<8> Carry out operational test of the flight compartment and electronics

racks air distribution system (Refer to AMM 21-21-00, Page Block

501)

<9> Do the test procedure as specified after the installation of the DOME

LIGHTS, (Refer to AMM 33-12-11, Page Block 401)

<10>Do the Operational test of the cabin distribution (Refer to AMM

21-22-00, Page Block 501) (if equipped)

<11>Do the test procedure for engine 1 as specified after the installation

of the LOW PRESSURE FUEL FIRE SHUT OFF VALVE, (Refer to

AMM 28-24-31, Page Block 401)

<12>Do the test procedure for engine 2 as specified after the installation

of the LOW PRESSURE FUEL FIRE SHUT OFF VALVE, (Refer to

AMM 28-24-31, Page Block 401)

e Do the test program after Removal/Installation of the panel 429VU

<1> Do the Functional Test of the windshield rain removal system (Refer

to AMM 30-45-00, Page Block 501).

<2> Do the Operational Test of the electrical ground power assisted APU

start (Refer to AMM 49-10-00, Page Block 501).

<3> Do the Operational Test of the APU pump (Refer to AMM 49-31-00,

Page Block 501).

<4> Do the Operational Test of the APU isolation valve (Refer to AMM

49-31-00, Page Block 501).

<5> Do the Operational Test of the ignition system (Refer to AMM

74-00-00, Page Block 501).

<6> Do an engine run (Refer to AMM 71-00-00, Page Block 501).

f Do the test of the AUTO RELIGHT system as follows:

<1> Job Set-Up

- Energize the aircraft electrical network (Refer to AMM 24-41-00,

Page Block 301).

- Make certain that electronics racks ventilation are correct.

- On panel 133VU, open, safety and tag this (these) circuit

breaker(s) related to ENGINES, except 1KG, 1JH, 2JH, 13JH,

14JH, 3KC, 4KC,

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 219

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

- Perform dry motoring (Refer to AMM 71-00-00, Page Block

501).

- Open the 105VU cowl and disconnect/remove relays 2KG and

3KG.

- Open cowl doors (Refer to AMM 71-13-00, Page Block 301).

- On panel 429VU, make sure that the ENG START selector

switch is in OFF position.

- Disconnect N2 RPM (Revolution per minute) indicators 3EP and

4EP (Refer to AMM 77-12-21, Page Block 401).

<2> Procedure

NOTE: This test is described for engine 1 only. For engine

2, refer to information between parentheses.

ACTION RESULT

On panel 9VU, place HP fuel shut off valve control

lever 1 (2) in ON position

On panel 133VU, Open circuit breaker 2GB (2GB)

NOTE: For CONF 007, open 119GB

instead of 2GB for engine 2

On panel 4VU, Connect the pin C of the N2 RPM

indicator 3EP (4EP) plug to the ground.

on engine 1 (2), igniter plugs A and B produce

normal sounds, proving that igniter plugs operate

correctly.

On panel 9VU, place HP (High Pressure) fuel shut

off valve control lever 1 (2) in OFF position

on engine 1 (2), igniter plugs A and B are cut off.

On panel 9VU, place HP fuel shut off valve control

lever 1 (2) in ON position

on engine 1 (2), igniter plugs A and B produce

normal sounds proving that igniter plugs operate

correctly

On panel 133VU, open AUTO RELIGHT ENG 1

(2) circuit breaker 13JH (14JH)

on engine 1 (2) , igniter plugs A and B are cut

off.

On panel 133VU, close AUTO RELIGHT ENG 1

(2) circuit breaker 13JH (14JH)

on engine 1 (2), igniter plugs A and B produce

normal sounds, proving that igniter plugs operate

correctly.

On panel 133VU, open IGNITION SYS A circuit

breaker 1JH

on engine 1 (2), igniter plug A is cut off.

on engine 1 (2), igniter plug B produces normal

sounds, proving that igniter plug operates

correctly.

On panel 133VU, close IGNITION SYS A circuit

breaker 1JH and open IGNITION SYS B circuit

breaker 2JH

on engine 1 (2), igniter plug B is cut off.

on engine 1 (2), igniter plug A produces normal

sounds, proving that igniter plug operates correctly

On panel 133VU, close IGNITION SYS B circuit

breaker 2JH

on engine 1 (2), igniter plugs A and B produce

normal sounds, proving that igniter plugs operate

correctly

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 220

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

ACTION RESULT

On panel 133VU, close circuit breaker 2GB (2GB)

NOTE: For CONF 007, close 119GB

instead of 2GB for engine 2

on engine 1 (2), igniter plugs A and B are cut off.

On panel 133VU, open circuit breaker 2GB (2GB)

NOTE: For CONF 007, open 119GB

instead of 2GB for engine 2

on engine 1 (2), igniter plugs A and B produce

normal sounds, proving that igniter plugs operate

correctly.

On panel 4VU, Disconnect the pin C of the N2

RPM indicator 3EP (4EP) plug from the ground.

on engine 1 (2), igniter plugs A and B are cut off

after 120 seconds.

On panel 133VU, close circuit breaker 2GB (2GB)

NOTE: For CONF 007, close 119GB

instead of 2GB for engine 2

On panel 9VU, place HP fuel shut off valve control

lever 1 (2) in OFF position

Repeat all the steps for engine 2.

<3> Close-up

- Reconnect N2 RPM indicators 3EP and 4EP and perform the

test of the N2 RPM indicators (Refer to AMM 77-12-21, Page

Block 401).

- Re-install the relays 2KG and 3KG (Refer to ESPM 20-46-50)

- Close cowl doors (Refer to AMM 71-13-00, Page Block 301).

- Perform an engine dry motoring (Refer to AMM 71-00-00, Page

Block 501)

- De-energize the aircraft electrical network (Refer to AMM

24-41-00, Page Block 301).

- Restore system and aircraft to normal operating condition

**CONF 009

(1) Subtask 742003-720-001-001 - Test

Manpower Resources

Skills ELECTRICAL

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 221

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 20-28-11, Page Block 001

21-21-00, Page Block 501

21-22-00, Page Block 501

21-23-12, Page Block 401

21-31-11, Page Block 401

22-18-34, Page Block 401

22-36-34, Page Block 401

22-40-00, Page Block 501

23-12-00, Page Block 501

23-71-12, Page Block 401

24-22-15, Page Block 401

24-23-13, Page Block 401

24-31-11, Page Block 401

24-41-00, Page Block 301

26-12-20, Page Block 401

26-12-20, Page Block 501

26-13-20, Page Block 401

26-13-20, Page Block 401

28-22-55, Page Block 401

28-24-31, Page Block 401

28-25-17, Page Block 401

28-28-12, Page Block 401

28-42-38, Page Block 401

28-42-41, Page Block 401

30-45-00, Page Block 501

31-10-00, Page Block 201

31-51-00, Page Block 501

31-69-00, Page Block 501

32-31-11, Page Block 401

33-12-00, Page Block 501

33-12-11, Page Block 401

33-13-00, Page Block 501

33-14-00, Page Block 501

33-46-00, Page Block 501

34-25-00, Page Block 501

34-44-34, Page Block 401

34-68-34, Page Block 401

34-73-34, Page Block 401

36-11-00, Page Block 501

36-11-19, Page Block 401

49-10-00, Page Block 501

49-31-00, Page Block 501

52-51-00, Page Block 501

71-00-00, Page Block 501

71-13-00, Page Block 301

74-00-00, Page Block 501

77-12-21, Page Block 401

Elec. Std. Practices Manual (ESPM) 20-46-50

20-52-10

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 222

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(a) Job Set-up

1 Battery re-connection

- For Job Set-up, refer to Installation of the Batteries (Refer to AMM

24-31-11, Page Block 401)

- Remove the blanking cap from the electrical connectors

- Make sure that the electrical connectors are clean and in correct condition

- Connect the connector on the battery

- Turn the knurled nut a quarter turn

2 Remove all warning notices.

3 Open, safety/lock and tag this (these) circuit breaker(s):

PANEL DESIGNATION FIN LOCATION SEE

NOTES

133 ENGINE 1/FUEL HP

VALVE/WARN

1KC T68

133 ENGINE 2/FUEL HP

VALVE/WARN

2KC R73

133 ENGINE 1/AUTORELIGHT 13JH S69

133 ENGINE 2/AUTORELIGHT 14JH S74

133 STBY GEN AIR VALVE 17XE T83

133 ENGINE 1/LO/PRESS 1ES Q69

4 Energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page Block

301)

5 Do a voltage check at pin 1 of each following circuit breaker to make sure that

there is 28VDC.

PANEL DESIGNATION FIN LOCATION SEE

NOTES

133 ENGINE 1/FUEL HP

VALVE/WARN

1KC T68

133 ENGINE 2/FUEL HP

VALVE/WARN

2KC R73

133 ENGINE 1/AUTORELIGHT 13JH S69

133 ENGINE 2/AUTORELIGHT 14JH S74

133 STBY GEN AIR VALVE 17XE T83

133 ENGINE 1/LO/PRESS 1ES Q69

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 223

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

6 Remove the safety clip(s) and/or tag(s) and close/unlock this (these) circuit

breaker(s):

PANEL DESIGNATION FIN LOCATION SEE

NOTES

133 ENGINE 1/FUEL HP

VALVE/WARN

1KC T68

133 ENGINE 2/FUEL HP

VALVE/WARN

2KC R73

133 ENGINE 1/AUTORELIGHT 13JH S69

133 ENGINE 2/AUTORELIGHT 14JH S74

133 STBY GEN AIR VALVE 17XE T83

133 ENGINE 1/LO/PRESS 1ES Q69

7 Preliminary Tests :

NOTE: If the aircraft is operated in CAT3 conditions, you must also do

the LAND test (Refer to AMM 22-40-00, Page Block 501)

a On each connector which was disconnected:

- Do the checks as defined by ESPM 20-52-10.

NOTE: The Functional test and/or operational test requested by

this ESPM procedure is given hereafter.

b Do the Operational Test of the Annunciator Light Test AMM (Refer to

AMM 33-14-00, Page Block 501).

c Do the Operational Test of the General Illumination, (Refer to AMM

33-12-00, Page Block 501).

d Do the Operational Test of the Instrument and Panel Integral Lighting,

(Refer to AMM 33-13-00, Page Block 501).

e Make certain that the ventillation system operates correctly, (Refer to

AMM 21-21-00, Page Block 501).

f Do the AFS (Automatic Flight System) Test, (Refer to AMM 22-40-00,

Page Block 501)(para 1.A)).

g Do the Operational Test of ECAM/EFIS Display Test, (Refer to AMM

31-51-00, Page Block 501).

h Do the Operational Test of the FWC1 and FWC2, (Refer to AMM

31-51-00, Page Block 501).

(b) Test

1 Procedure

a Do the Operational Test of the circuit breaker monitoring system for panel

133VU (Refer to AMM 31-69-00, Page Block 501).

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 224

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

b Do the tests program after R/I of the panel 20VU:

<1> Do the test procedure as specified after the installation of the FUEL

QUANTITY INDICATOR (6QT), (Refer to AMM 28-42-41, Page

Block 401)

<2> Do the tests program after R/I of the Panel 45VU, (Refer to AMM

31-10-00, Page Block 201)

<3> Do the tests program after R/I of the Panel 76VU (Refer to AMM

31-10-00, Page Block 201)

<4> Do the tests program after R/I of the Panel 424VU (Refer to AMM

31-10-00, Page Block 201)

<5> Do the tests program after R/I of the Panel 425VU (Refer to AMM

31-10-00, Page Block 201)

<6> Do the tests program after R/I of the Panel 430VU (Refer to AMM

31-10-00, Page Block 201)

<7> Do the tests program after R/I of the Panel 433VU (Refer to AMM

31-10-00, Page Block 201)

<8> Do the tests program after R/I of the Panel 435VU (Refer to AMM

31-10-00, Page Block 201)

<9> Do the tests program after R/I of the Panel 438VU (Refer to AMM

31-10-00, Page Block 201)

<10>Do the tests program after R/I of the Panel 431VU (Refer to AMM

31-10-00, Page Block 201)

<11>Do the test of alignment procedure up to step 4 as described in the

IRS operational test (Refer to AMM 34-25-00, Page Block 501) for

each mode selector unit which has been removed for access

<12>Do the test procedure as specified after the installation of the

Cockpit Voice Recorder control unit (1RK) (Refer to AMM 23-71-12,

Page Block 401)

<13>Do the test procedure as specified after the installation of the APU

FIRE CONTROL MODULE (20WG) (Refer to AMM 26-13-20, Page

Block 401)

<14>Do the test procedure as specified after the installation of the

Engine Fire Control Module (39WD) (Refer to AMM 26-12-20, Page

Block 401)

<15>Do the O/T of the VHF3 system (Refer to AMM 23-12-00, Page

Block 501)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 225

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

<16>If CDSS is active for A/C, do the "Operational test of Video

Monitoring System", NOTE: If the SB reference is not specified in

the latest operator’s AMM issue, do these steps:

<a> Job Set-Up

[1] Connect the electrical ground power unit and energize the

aircraft electrical network (Refer to AMM 24-41-00, Page

Block 301).

[2] Make certain that the electronic rack ventilation is correct.

[3] Make certain that the following circuit breaker is closed:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

132VU CKPT/DOOR VIDEO/SPLY 15RA

<b> 2 Operational test of the Video Monitoring System

ACTION RESULT

1. In the cockpit, on panel 512VU:

- push the ’CKPT DOOR VIDEO’ pushbutton

switch

In the cockpit:

- the OFF legend in the ’CKPT DOOR VIDEO’

pushbutton switch goes off.

In the cockpit on the LCD:

- the green LED comes on

- the LCD monitor shows the images from camera

1.

2. In the cockpit, on panel 119VU:

- push the ’VIDEO’ pushbutton one time.

In the cockpit,on the LCD monitor:

- the left half of the LCD monitor screen shows

the images from camera 2

- the right half of the LCD monitor screen shows

the images of camera 3.

3. In the Cockpit, on the panel 119VU:

- push the ’VIDEO’ pushbutton one time.

In the cockpit,on the LCD monitor:

- the LCD monitor shows the images from camera

1.

4. In the cockpit, on the LCD monitor:

- turn the LCD monitor brightness knob clockwise

then counter-clockwise.

In the cockpit,on the LCD monitor:

- the brightness of the images change.

5. In the cockpit, on the LCD monitor:

- turn the LCD monitor contrast knob clockwise

then counter-clockwise.

In the cockpit, on the LCD monitor:

- the contrast of the images change.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 226

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

ACTION RESULT

6. In the cockpit, on the LCD monitor:

- turn the brightness and the contrast knobs to

their center positions.

7. In the cockpit, on the LCD monitor:

- use a flashlight to increase the light on the light

sensor, switch the flashlight on.

In the cockpit,on the LCD monitor:

- the brightness of the images change.

8. In the cockpit, on the LCD monitor:

- decrease the light on the light sensor, switch the

flashlight off.

In the cockpit,on the LCD monitor:

- the brightness of the images change.

9. In the cockpit, on panel 119VU:

- push the ’VIDEO’ pushbutton one time.

In the cockpit,on the LCD monitor:

- the left half of the LCD monitor screen shows

the images from camera 2

- the right half of the LCD monitor screen shows

the images from camera 3

- after five minutes the images go off (Stand-by

mode).

10. In the cockpit, on the panel 119VU:

- before the images on the LCD monitor go off for

30 seconds, push the ’VIDEO’ pushbutton one

time.

In the cockpit,on the LCD monitor:

- the images from camera 2 and camera 3 are

shown(split screen).

- after 5 minutes,the images go off (power-down

mode).

11. In the cockpit entrance area on the keypad

25MQ:

- enter the code to request entry to the cockpit

(Refer to AMM 52-51-00, Page Block 501).

In the cockpit:

- the horn is heard

- on the LCD monitor the image from camera 1 is

shown.

12. In the cockpit on the panel 119VU:

- push the ’VIDEO’ pushbutton one time.

In the cockpit on the LCD monitor:

- the images from camera 2 and 3 are shown

(split screen).

13. In the cockpit entrance area, on the keypad

25MQ:

- after the images from camera 2 and camera 3

are shown on the LCD monitor and before 29

seconds request entry to the cockpit.

In the cockpit on the LCD monitor:

- the images from camera 2 and camera 3 are

shown (split screen).

14. In the cockpit, on the panel 119VU:

- push the ’VIDEO’ pushbutton one time.

In the cockpit,on the LCD monitor:

- the image from camera 1 is shown.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 227

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

ACTION RESULT

15. In the cockpit on the panel 512VU:

- push the ’CKPT DOOR VIDEO’ pushbutton

switch.

In the cockpit on the panel 512VU:

- the ’OFF’ legend in the ’CKPT DOOR VIDEO’

pushbutton switch comes on.

In the cockpit on the LCD monitor:

- the green LED goes off

- the screen goes off.

<c> Close-Up

[1] De-energize the AC-External Power Control (Refer to

AMM 24-41-00, Page Block 301).

[2] Make sure that the work area is clean and clear of tools

and miscellaneous items of equipment.

<17>Do the O/T of the CDLS (Refer to AMM 52-51-00, Page Block 501)

c Do the tests program after R/I of the panel 104VU:

<1> Do a check of the Electrical Bonding (Refer to AMM 20-28-11, Page

Block 001)

NOTE: For maximun permissible resistance values: Refer to

the Table (Refer to AMM 20-28-11, Page Block 001)

<2> Do the test procedure as specified after the installation of the TRIM

TANK ISOLATION VALVE ACTUATOR (48QB), (Refer to AMM

28-22-55, Page Block 401)

<3> Do the test procedure as specified after the installation of the

INBOARD EXTRACT VALVE (74HR), (Refer to AMM 21-23-12,

Page Block 401)

<4> Do the test procedure as specified after the installation of the EFIS

SGU (28FN1, 28FN2, 28FN3), (Refer to AMM 34-73-34, Page Block

401)

<5> Do the test procedure as specified after the installation of the APU

GEN PWR LINE CONTACTOR 3XS, (Refer to AMM 24-23-13, Page

Block 401)

<6> Do the test procedure as specified after the installation of the FUEL

QUANTITY COMPUTER (15QT), (Refer to AMM 28-42-38, Page

Block 401)

<7> Do the test procedure as specified after the installation of the

TRANSFER VALVE ACTUATOR, (Refer to AMM 28-25-17, Page

Block 401) (if equipped)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 228

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

<8> Do the test procedure as specified after the installation of the

ACTUATOR - SELECTOR VALVE, (Refer to AMM 28-28-12, Page

Block 401) (if equipped)

<9> Do the test procedure as specified after the installation of the GEN 1

(2) LINE CONTACTOR 9XU (10XU), (Refer to AMM 24-22-15, Page

Block 401)

<10>Do the test procedure as specified after the installation of the

CABIN PRESSURE CONTROLLER 105HM (106HM), (Refer to

AMM 21-31-11, Page Block 401)

<11>Do the test procedure as specified after the installation of

the PNEUMATIC CONTROLLER 41HA (42HA), (Refer to AMM

36-11-19, Page Block 401) (if equipped)

<12>Do the test procedure as specified after the installation of the APU

FIRE CONTROL MODULE, (Refer to AMM 26-13-20, Page Block

401)

<13>Do the test procedure as specified after the installation of the

FLIGHT CONTROL COMPUTER (301CA1, 301CA2), (Refer to AMM

22-18-34, Page Block 401)

<14>Do the test procedure as specified after the installation of

the LANDING GEAR NORMAL CONTROL MICROSWITCH UNIT

(2GA), (Refer to AMM 32-31-11, Page Block 401)

d Do the tests program after R/I of the panel 105VU:

<1> Do a check of the Electrical Bonding (Refer to AMM 20-28-11, Page

Block 001)

NOTE: For maximun permissible resistance values: Refer to

the Table (Refer to AMM 20-28-11, Page Block 001)

<2> Do the Perform BITE test (Refer to AMM 36-11-00, Page Block

501), (Operational Test)

<3> Do the test procedure as specified after the installation of the

FLIGHT MANAGEMENT COMPUTER (1CK1, 1CK2), (Refer to

AMM 34-68-34, Page Block 401) (if equipped)

<4> Do the Functional Test - ENGINE FIRE CONTROL MODULE, (Refer

to AMM 26-12-20, Page Block 501)

<5> Do the test procedure as specified after the installation of the TCAS

COMPUTER (9005SG), (Refer to AMM 34-44-34, Page Block 401)

(if equipped)

<6> Do the Operational Test TAXI AND TAKEOFF LIGHTS, (Refer to

AMM 33-46-00, Page Block 501)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 229

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

<7> Do the test procedure as specified after the installation of the

THRUST CONTROL COMPUTER 301CJ1 (301CJ2), (Refer to AMM

22-36-34, Page Block 401)

<8> Carry out operational test of the flight compartment and electronics

racks air distribution system (Refer to AMM 21-21-00, Page Block

501)

<9> Do the test procedure as specified after the installation of the DOME

LIGHTS, (Refer to AMM 33-12-11, Page Block 401)

<10>Do the Operational test of the cabin distribution (Refer to AMM

21-22-00, Page Block 501) (if equipped)

<11>Do the test procedure for engine 1 as specified after the installation

of the LOW PRESSURE FUEL FIRE SHUT OFF VALVE, (Refer to

AMM 28-24-31, Page Block 401)

<12>Do the test procedure for engine 2 as specified after the installation

of the LOW PRESSURE FUEL FIRE SHUT OFF VALVE, (Refer to

AMM 28-24-31, Page Block 401)

e Do the test program after Removal/Installation of the panel 429VU

<1> Do the Functional Test of the windshield rain removal system (Refer

to AMM 30-45-00, Page Block 501).

<2> Do the Operational Test of the electrical ground power assisted APU

start (Refer to AMM 49-10-00, Page Block 501).

<3> Do the Operational Test of the APU pump (Refer to AMM 49-31-00,

Page Block 501).

<4> Do the Operational Test of the APU isolation valve (Refer to AMM

49-31-00, Page Block 501).

<5> Do the Operational Test of the ignition system (Refer to AMM

74-00-00, Page Block 501).

<6> Do an engine run (Refer to AMM 71-00-00, Page Block 501).

f Do the test of the AUTO RELIGHT system as follows:

<1> Job Set-Up

- Energize the aircraft electrical network (Refer to AMM 24-41-00,

Page Block 301).

- Make certain that electronics racks ventilation are correct.

- On panel 133VU, open, safety and tag this (these) circuit

breaker(s) related to ENGINES, except 1KG, 1JH, 2JH, 13JH,

14JH, 3KC, 4KC,

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 230

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

- Perform dry motoring (Refer to AMM 71-00-00, Page Block

501).

- Open the 105VU cowl and disconnect/remove relays 2KG and

3KG.

- Open cowl doors (Refer to AMM 71-13-00, Page Block 301).

- On panel 429VU, make sure that the ENG START selector

switch is in OFF position.

- Disconnect N2 RPM (Revolution per minute) indicators 3EP and

4EP (Refer to AMM 77-12-21, Page Block 401).

<2> Procedure

NOTE: This test is described for engine 1 only. For engine

2, refer to information between parentheses.

ACTION RESULT

On panel 9VU, place HP fuel shut off valve control

lever 1 (2) in ON position

On panel 133VU, Open circuit breaker 2GB (2GB)

NOTE: For CONF 007, open 119GB

instead of 2GB for engine 2

On panel 4VU, Connect the pin C of the N2 RPM

indicator 3EP (4EP) plug to the ground.

on engine 1 (2), igniter plugs A and B produce

normal sounds, proving that igniter plugs operate

correctly.

On panel 9VU, place HP (High Pressure) fuel shut

off valve control lever 1 (2) in OFF position

on engine 1 (2), igniter plugs A and B are cut off.

On panel 9VU, place HP fuel shut off valve control

lever 1 (2) in ON position

on engine 1 (2), igniter plugs A and B produce

normal sounds proving that igniter plugs operate

correctly

On panel 133VU, open AUTO RELIGHT ENG 1

(2) circuit breaker 13JH (14JH)

on engine 1 (2) , igniter plugs A and B are cut

off.

On panel 133VU, close AUTO RELIGHT ENG 1

(2) circuit breaker 13JH (14JH)

on engine 1 (2), igniter plugs A and B produce

normal sounds, proving that igniter plugs operate

correctly.

On panel 133VU, open IGNITION SYS A circuit

breaker 1JH

on engine 1 (2), igniter plug A is cut off.

on engine 1 (2), igniter plug B produces normal

sounds, proving that igniter plug operates

correctly.

On panel 133VU, close IGNITION SYS A circuit

breaker 1JH and open IGNITION SYS B circuit

breaker 2JH

on engine 1 (2), igniter plug B is cut off.

on engine 1 (2), igniter plug A produces normal

sounds, proving that igniter plug operates correctly

On panel 133VU, close IGNITION SYS B circuit

breaker 2JH

on engine 1 (2), igniter plugs A and B produce

normal sounds, proving that igniter plugs operate

correctly

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 231

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

ACTION RESULT

On panel 133VU, close circuit breaker 2GB (2GB)

NOTE: For CONF 007, close 119GB

instead of 2GB for engine 2

on engine 1 (2), igniter plugs A and B are cut off.

On panel 133VU, open circuit breaker 2GB (2GB)

NOTE: For CONF 007, open 119GB

instead of 2GB for engine 2

on engine 1 (2), igniter plugs A and B produce

normal sounds, proving that igniter plugs operate

correctly.

On panel 4VU, Disconnect the pin C of the N2

RPM indicator 3EP (4EP) plug from the ground.

on engine 1 (2), igniter plugs A and B are cut off

after 120 seconds.

On panel 133VU, close circuit breaker 2GB (2GB)

NOTE: For CONF 007, close 119GB

instead of 2GB for engine 2

On panel 9VU, place HP fuel shut off valve control

lever 1 (2) in OFF position

Repeat all the steps for engine 2.

<3> Close-up

- Reconnect N2 RPM indicators 3EP and 4EP and perform the

test of the N2 RPM indicators (Refer to AMM 77-12-21, Page

Block 401).

- Re-install the relays 2KG and 3KG (Refer to ESPM 20-46-50)

- Close cowl doors (Refer to AMM 71-13-00, Page Block 301).

- Perform an engine dry motoring (Refer to AMM 71-00-00, Page

Block 501)

- De-energize the aircraft electrical network (Refer to AMM

24-41-00, Page Block 301).

- Restore system and aircraft to normal operating condition

**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 742003-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 232

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 23-12-13, Page Block 401

23-71-12, Page Block 401

25-13-11, Page Block 401

25-13-12, Page Block 401

26-12-20, Page Block 401

26-13-20, Page Block 401

28-42-41, Page Block 401

34-25-25, Page Block 401

52-10-00

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) On overhead panel 20VU, reinstall

1 The Small VUs 45VU, 76VU, 424VU, 425VU, 430VU, 431VU, 433VU, 435VU,

438VU removed in SUBTASK 742003-941-001 001 Job Set-up

2 The Fuel Quantity indicator 6QT (Refer to AMM 28-42-41, Page Block 401)

3 The Mode Selector Units 310FP1, 310FP2 and 310FP3 (Refer to AMM

34-25-25, Page Block 401)

4 the Cockpit Voice Recorder Unit 1RK (Refer to AMM 23-71-12, Page Block

401)

5 The APU Fire Control Module 20WG (Refer to AMM 26-13-20, Page Block

401)

6 The Engine Fire Control modules 39WD and 40WD (Refer to AMM 26-12-20,

Page Block 401)

7 The VHF3 Control Unit 2RC3 (Refer to AMM 23-12-13, Page Block 401)

(c) Install the right side panels, the ceiling panels removed in SUBTASK

742003-941-001 001 Job Set-up (Refer to AMM 25-13-11, Page Block 401)(Refer

to AMM 25-13-12, Page Block 401).

(d) Close the passenger/crew door (Refer to AMM 52-10-00).

(e) Restore system and aircraft to normal operating system.

(f) Remove access platforms.

**CONF 002

(1) Subtask 742003-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 233

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 23-12-13, Page Block 401

23-71-12, Page Block 401

25-13-11, Page Block 401

25-13-12, Page Block 401

26-12-20, Page Block 401

26-13-20, Page Block 401

28-42-41, Page Block 401

34-25-25, Page Block 401

52-10-00

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) On overhead panel 20VU, reinstall

1 The Small VUs 45VU, 76VU, 424VU, 425VU, 430VU, 431VU, 433VU, 435VU,

438VU removed in SUBTASK 742003-941-001 001 Job Set-up

2 The Fuel Quantity indicator 6QT (Refer to AMM 28-42-41, Page Block 401)

3 The Mode Selector Units 310FP1, 310FP2 and 310FP3 (Refer to AMM

34-25-25, Page Block 401)

4 the Cockpit Voice Recorder Unit 1RK (Refer to AMM 23-71-12, Page Block

401)

5 The APU Fire Control Module 20WG (Refer to AMM 26-13-20, Page Block

401)

6 The Engine Fire Control modules 39WD and 40WD (Refer to AMM 26-12-20,

Page Block 401)

7 The VHF3 Control Unit 2RC3 (Refer to AMM 23-12-13, Page Block 401)

(c) Install the right side panels, the ceiling panels removed in SUBTASK

742003-941-001 001 Job Set-up (Refer to AMM 25-13-11, Page Block 401)(Refer

to AMM 25-13-12, Page Block 401).

(d) Close the passenger/crew door (Refer to AMM 52-10-00).

(e) Restore system and aircraft to normal operating system.

(f) Remove access platforms.

**CONF 003

(1) Subtask 742003-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 234

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 23-12-13, Page Block 401

23-71-12, Page Block 401

25-13-11, Page Block 401

25-13-12, Page Block 401

26-12-20, Page Block 401

26-13-20, Page Block 401

28-42-41, Page Block 401

34-25-25, Page Block 401

52-10-00

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) On overhead panel 20VU, reinstall

1 The Small VUs 45VU, 76VU, 424VU, 425VU, 430VU, 431VU, 433VU, 435VU,

438VU removed in SUBTASK 742003-941-001 001 Job Set-up

2 The Fuel Quantity indicator 6QT (Refer to AMM 28-42-41, Page Block 401)

3 The Mode Selector Units 310FP1, 310FP2 and 310FP3 (Refer to AMM

34-25-25, Page Block 401)

4 the Cockpit Voice Recorder Unit 1RK (Refer to AMM 23-71-12, Page Block

401)

5 The APU Fire Control Module 20WG (Refer to AMM 26-13-20, Page Block

401)

6 The Engine Fire Control modules 39WD and 40WD (Refer to AMM 26-12-20,

Page Block 401)

7 The VHF3 Control Unit 2RC3 (Refer to AMM 23-12-13, Page Block 401)

(c) Install the right side panels, the ceiling panels removed in SUBTASK

742003-941-001 001 Job Set-up (Refer to AMM 25-13-11, Page Block 401)(Refer

to AMM 25-13-12, Page Block 401).

(d) Close the passenger/crew door (Refer to AMM 52-10-00).

(e) Restore system and aircraft to normal operating system.

(f) Remove access platforms.

**CONF 006

(1) Subtask 742003-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 235

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 23-12-13, Page Block 401

23-71-12, Page Block 401

25-13-11, Page Block 401

25-13-12, Page Block 401

26-12-20, Page Block 401

26-13-20, Page Block 401

28-42-41, Page Block 401

34-25-25, Page Block 401

52-10-00

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) On overhead panel 20VU, reinstall

1 The Small VUs 45VU, 76VU, 424VU, 425VU, 430VU, 431VU, 433VU, 435VU,

438VU removed in SUBTASK 742003-941-001 001 Job Set-up

2 The Fuel Quantity indicator 6QT (Refer to AMM 28-42-41, Page Block 401)

3 The Mode Selector Units 310FP1, 310FP2 and 310FP3 (Refer to AMM

34-25-25, Page Block 401)

4 the Cockpit Voice Recorder Unit 1RK (Refer to AMM 23-71-12, Page Block

401)

5 The APU Fire Control Module 20WG (Refer to AMM 26-13-20, Page Block

401)

6 The Engine Fire Control modules 39WD and 40WD (Refer to AMM 26-12-20,

Page Block 401)

7 The VHF3 Control Unit 2RC3 (Refer to AMM 23-12-13, Page Block 401)

(c) Install the right side panels, the ceiling panels removed in SUBTASK

742003-941-001 001 Job Set-up (Refer to AMM 25-13-11, Page Block 401)(Refer

to AMM 25-13-12, Page Block 401).

(d) Close the passenger/crew door (Refer to AMM 52-10-00).

(e) Restore system and aircraft to normal operating system.

(f) Remove access platforms.

**CONF 007

(1) Subtask 742003-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 236

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 23-12-13, Page Block 401

23-71-12, Page Block 401

25-13-11, Page Block 401

25-13-12, Page Block 401

26-12-20, Page Block 401

26-13-20, Page Block 401

28-42-41, Page Block 401

34-25-25, Page Block 401

52-10-00

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) On overhead panel 20VU, reinstall

1 The Small VUs 45VU, 76VU, 424VU, 425VU, 430VU, 431VU, 433VU, 435VU,

438VU removed in SUBTASK 742003-941-001 001 Job Set-up

2 The Fuel Quantity indicator 6QT (Refer to AMM 28-42-41, Page Block 401)

3 The Mode Selector Units 310FP1, 310FP2 and 310FP3 (Refer to AMM

34-25-25, Page Block 401)

4 the Cockpit Voice Recorder Unit 1RK (Refer to AMM 23-71-12, Page Block

401)

5 The APU Fire Control Module 20WG (Refer to AMM 26-13-20, Page Block

401)

6 The Engine Fire Control modules 39WD and 40WD (Refer to AMM 26-12-20,

Page Block 401)

7 The VHF3 Control Unit 2RC3 (Refer to AMM 23-12-13, Page Block 401)

(c) Install the right side panels, the ceiling panels removed in SUBTASK

742003-941-001 001 Job Set-up (Refer to AMM 25-13-11, Page Block 401)(Refer

to AMM 25-13-12, Page Block 401).

(d) Close the passenger/crew door (Refer to AMM 52-10-00).

(e) Restore system and aircraft to normal operating system.

(f) Remove access platforms.

**CONF 008

(1) Subtask 742003-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 237

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 23-12-13, Page Block 401

23-71-12, Page Block 401

25-13-11, Page Block 401

25-13-12, Page Block 401

26-12-20, Page Block 401

26-13-20, Page Block 401

28-42-41, Page Block 401

34-25-25, Page Block 401

52-10-00

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) On overhead panel 20VU, reinstall

1 The Small VUs 45VU, 76VU, 424VU, 425VU, 430VU, 431VU, 433VU, 435VU,

438VU removed in SUBTASK 742003-941-001 001 Job Set-up

2 The Fuel Quantity indicator 6QT (Refer to AMM 28-42-41, Page Block 401)

3 The Mode Selector Units 310FP1, 310FP2 and 310FP3 (Refer to AMM

34-25-25, Page Block 401)

4 the Cockpit Voice Recorder Unit 1RK (Refer to AMM 23-71-12, Page Block

401)

5 The APU Fire Control Module 20WG (Refer to AMM 26-13-20, Page Block

401)

6 The Engine Fire Control modules 39WD and 40WD (Refer to AMM 26-12-20,

Page Block 401)

7 The VHF3 Control Unit 2RC3 (Refer to AMM 23-12-13, Page Block 401)

(c) Install the right side panels, the ceiling panels removed in SUBTASK

742003-941-001 001 Job Set-up (Refer to AMM 25-13-11, Page Block 401)(Refer

to AMM 25-13-12, Page Block 401).

(d) Close the passenger/crew door (Refer to AMM 52-10-00).

(e) Restore system and aircraft to normal operating system.

(f) Remove access platforms.

**CONF 009

(1) Subtask 742003-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 238

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 23-12-13, Page Block 401

23-71-12, Page Block 401

25-13-11, Page Block 401

25-13-12, Page Block 401

26-12-20, Page Block 401

26-13-20, Page Block 401

28-42-41, Page Block 401

34-25-25, Page Block 401

52-10-00

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) On overhead panel 20VU, reinstall

1 The Small VUs 45VU, 76VU, 424VU, 425VU, 430VU, 431VU, 433VU, 435VU,

438VU removed in SUBTASK 742003-941-001 001 Job Set-up

2 The Fuel Quantity indicator 6QT (Refer to AMM 28-42-41, Page Block 401)

3 The Mode Selector Units 310FP1, 310FP2 and 310FP3 (Refer to AMM

34-25-25, Page Block 401)

4 the Cockpit Voice Recorder Unit 1RK (Refer to AMM 23-71-12, Page Block

401)

5 The APU Fire Control Module 20WG (Refer to AMM 26-13-20, Page Block

401)

6 The Engine Fire Control modules 39WD and 40WD (Refer to AMM 26-12-20,

Page Block 401)

7 The VHF3 Control Unit 2RC3 (Refer to AMM 23-12-13, Page Block 401)

(c) Install the right side panels, the ceiling panels removed in SUBTASK

742003-941-001 001 Job Set-up (Refer to AMM 25-13-11, Page Block 401)(Refer

to AMM 25-13-12, Page Block 401).

(d) Close the passenger/crew door (Refer to AMM 52-10-00).

(e) Restore system and aircraft to normal operating system.

(f) Remove access platforms.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 239

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 240

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Task 742003-831-802-001 - Modification - ADDITIONAL WORK

**CONF ALL

WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS

INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO

THIS:

- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS

NECESSARY ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00.

NOTE: The accomplishment instructions of this Service Bulletin refer to procedures

included in other AIRBUS documents. When the words ’refer to’ are used and the

operator has an accepted alternative procedure, the accepted alternative procedure

can be used. When the words ’in accordance with’ are included in the instruction,

the procedure in the AIRBUS document must be used.

NOTE: The access and close-up instructions, not comprising return to service tests, in this

Service Bulletin do not constitute or affect the technical intent of the Service

Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or

close-up steps to add flexibility to their maintenance operations as long as the

technical intent of the Service Bulletin is met within the set parameters.

NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms.

Refer to paragraph 1.J., References, for the definition of acronyms.

Task Associated Data

**CONF 001

Zone

210

Manpower

TOTAL MANHOURS 5.50

ELAPSED TIME (HOURS) 5.50

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 241

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 002

Zone

210

Manpower

TOTAL MANHOURS 5.50

ELAPSED TIME (HOURS) 5.50

**CONF 003

Zone

210

Manpower

TOTAL MANHOURS 5.50

ELAPSED TIME (HOURS) 5.50

**CONF 006

Zone

210

Manpower

TOTAL MANHOURS 5.50

ELAPSED TIME (HOURS) 5.50

**CONF 007

Zone

210

Manpower

TOTAL MANHOURS 5.50

ELAPSED TIME (HOURS) 5.50

**CONF 008

Zone

210

Manpower

TOTAL MANHOURS 5.50

ELAPSED TIME (HOURS) 5.50

**CONF 009

Zone

210

Manpower

TOTAL MANHOURS 5.50

ELAPSED TIME (HOURS) 5.50

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 242

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 742003-839-002-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

(a) Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF 002

(1) Subtask 742003-839-002-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

(a) Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF 003

(1) Subtask 742003-839-002-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

(a) Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF 006

(1) Subtask 742003-839-002-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

(a) Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF 007

(1) Subtask 742003-839-002-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

(a) Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 243

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 008

(1) Subtask 742003-839-002-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

(a) Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF 009

(1) Subtask 742003-839-002-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

(a) Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF ALL

B. PREPARATION

**CONF 001

(1) Subtask 742003-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Elec. Std. Practices Manual (ESPM) 20-25-51

20-33-00

20-33-44

20-52-21

(a) Obey the instructions for the general wiring installation (Refer to ESPM 20-33-00).

(b) To install the new wires cut them to the necessary length, crimp the terminals and

connect them.

(c) Do a continuity test of the new and modified wires (Refer to ESPM 20-52-21).

(d) Route the new wires with the wires that are in the aircraft.

(e) For the cable tie application and tooling, refer to ESPM 20-25-51 and ESPM

20-33-44.

(2) Subtask 742003-941-002-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 244

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301

52-10-00

(a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page

Block 301)

(b) Put access platform(s) in position

(c) Open the passenger/crew door(s) (Refer to AMM 52-10-00)

(d) Open, safety/lock and tag this (these) circuit breaker(s):

PANEL DESIGNATION FIN LOCATION SEE

NOTES

21VU ELEC/CBMS REAR PANEL 10WY B13

**CONF 002

(1) Subtask 742003-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Elec. Std. Practices Manual (ESPM) 20-25-51

20-33-00

20-33-44

20-52-21

(a) Obey the instructions for the general wiring installation (Refer to ESPM 20-33-00).

(b) To install the new wires cut them to the necessary length, crimp the terminals and

connect them.

(c) Do a continuity test of the new and modified wires (Refer to ESPM 20-52-21).

(d) Route the new wires with the wires that are in the aircraft.

(e) For the cable tie application and tooling, refer to ESPM 20-25-51 and ESPM

20-33-44.

(2) Subtask 742003-941-002-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301

52-10-00

(a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page

Block 301)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 245

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(b) Put access platform(s) in position

(c) Open the passenger/crew door(s) (Refer to AMM 52-10-00)

(d) Open, safety/lock and tag this (these) circuit breaker(s):

PANEL DESIGNATION FIN LOCATION SEE

NOTES

21VU ELEC/CBMS REAR PANEL 10WY B13

**CONF 003

(1) Subtask 742003-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Elec. Std. Practices Manual (ESPM) 20-25-51

20-33-00

20-33-44

20-52-21

(a) Obey the instructions for the general wiring installation (Refer to ESPM 20-33-00).

(b) To install the new wires cut them to the necessary length, crimp the terminals and

connect them.

(c) Do a continuity test of the new and modified wires (Refer to ESPM 20-52-21).

(d) Route the new wires with the wires that are in the aircraft.

(e) For the cable tie application and tooling, refer to ESPM 20-25-51 and ESPM

20-33-44.

(2) Subtask 742003-941-002-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301

52-10-00

(a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page

Block 301)

(b) Put access platform(s) in position

(c) Open the passenger/crew door(s) (Refer to AMM 52-10-00)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 246

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(d) Open, safety/lock and tag this (these) circuit breaker(s):

PANEL DESIGNATION FIN LOCATION SEE

NOTES

21VU ELEC/CBMS REAR PANEL 10WY B13

**CONF 006

(1) Subtask 742003-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Elec. Std. Practices Manual (ESPM) 20-25-51

20-33-00

20-33-44

20-52-21

(a) Obey the instructions for the general wiring installation (Refer to ESPM 20-33-00).

(b) To install the new wires cut them to the necessary length, crimp the terminals and

connect them.

(c) Do a continuity test of the new and modified wires (Refer to ESPM 20-52-21).

(d) Route the new wires with the wires that are in the aircraft.

(e) For the cable tie application and tooling, refer to ESPM 20-25-51 and ESPM

20-33-44.

(2) Subtask 742003-941-002-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301

52-10-00

(a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page

Block 301)

(b) Put access platform(s) in position

(c) Open the passenger/crew door(s) (Refer to AMM 52-10-00)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 247

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(d) Open, safety/lock and tag this (these) circuit breaker(s):

PANEL DESIGNATION FIN LOCATION SEE

NOTES

21VU ELEC/CBMS REAR PANEL 10WY B13

**CONF 007

(1) Subtask 742003-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Elec. Std. Practices Manual (ESPM) 20-25-51

20-33-00

20-33-44

20-52-21

(a) Obey the instructions for the general wiring installation (Refer to ESPM 20-33-00).

(b) To install the new wires cut them to the necessary length, crimp the terminals and

connect them.

(c) Do a continuity test of the new and modified wires (Refer to ESPM 20-52-21).

(d) Route the new wires with the wires that are in the aircraft.

(e) For the cable tie application and tooling, refer to ESPM 20-25-51 and ESPM

20-33-44.

(2) Subtask 742003-941-002-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301

52-10-00

(a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page

Block 301)

(b) Put access platform(s) in position

(c) Open the passenger/crew door(s) (Refer to AMM 52-10-00)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 248

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(d) Open, safety/lock and tag this (these) circuit breaker(s):

PANEL DESIGNATION FIN LOCATION SEE

NOTES

21VU ELEC/CBMS REAR PANEL 10WY B13

**CONF 008

(1) Subtask 742003-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Elec. Std. Practices Manual (ESPM) 20-25-51

20-33-00

20-33-44

20-52-21

(a) Obey the instructions for the general wiring installation (Refer to ESPM 20-33-00).

(b) To install the new wires cut them to the necessary length, crimp the terminals and

connect them.

(c) Do a continuity test of the new and modified wires (Refer to ESPM 20-52-21).

(d) Route the new wires with the wires that are in the aircraft.

(e) For the cable tie application and tooling, refer to ESPM 20-25-51 and ESPM

20-33-44.

(2) Subtask 742003-941-002-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301

52-10-00

(a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page

Block 301)

(b) Put access platform(s) in position

(c) Open the passenger/crew door(s) (Refer to AMM 52-10-00)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 249

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(d) Open, safety/lock and tag this (these) circuit breaker(s):

PANEL DESIGNATION FIN LOCATION SEE

NOTES

21VU ELEC/CBMS REAR PANEL 10WY B13

**CONF 009

(1) Subtask 742003-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Elec. Std. Practices Manual (ESPM) 20-25-51

20-33-00

20-33-44

20-52-21

(a) Obey the instructions for the general wiring installation (Refer to ESPM 20-33-00).

(b) To install the new wires cut them to the necessary length, crimp the terminals and

connect them.

(c) Do a continuity test of the new and modified wires (Refer to ESPM 20-52-21).

(d) Route the new wires with the wires that are in the aircraft.

(e) For the cable tie application and tooling, refer to ESPM 20-25-51 and ESPM

20-33-44.

(2) Subtask 742003-941-002-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301

52-10-00

(a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page

Block 301)

(b) Put access platform(s) in position

(c) Open the passenger/crew door(s) (Refer to AMM 52-10-00)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 250

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(d) Open, safety/lock and tag this (these) circuit breaker(s):

PANEL DESIGNATION FIN LOCATION SEE

NOTES

21VU ELEC/CBMS REAR PANEL 10WY B13

**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 742003-831-009-001 - Modify the wiring in the Circuit Breaker panel 133VU

Work Zones and Access Panels

Zone Access/Work location

210

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320795 BUNDLE

NSA935401-03 20 TIE

References

Fig. A-FCGAA

ADDITIONAL WORK - Modification

wiring in 133VU

Sheet 01

Sheet 02

Sheet 03

Fig. A-FDGAA

ADDITIONAL WORK - Hook-up Chart in

133VU

Sheet 01

(a) Remove the wires as shown on the wiring diagram Fig. A-FCGAA Sheet 01, Fig. AFCGAA Sheet 02 and as given in the Hook-up Chart lines:

- 1 thru 10 Fig. A-FDGAA Sheet 01

(b) Install the wires as shown on the wiring diagram Fig. A-FCGAA Sheet 01, Fig. AFCGAA Sheet 03 and as given in the Hook-up Chart lines:

- 14 thru 23 Fig. A-FDGAA Sheet 01

supplied in:

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 251

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Bundle A9000095320795

(c) Attach the wires with:

20 Tie-Cable NSA935401-03

**CONF 002

(1) Subtask 742003-831-009-001 - Modify the wiring in the Circuit Breaker panel 133VU

Work Zones and Access Panels

Zone Access/Work location

210

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320795 BUNDLE

NSA935401-03 20 TIE

References

Fig. A-FCGAA

ADDITIONAL WORK - Modification

wiring in 133VU

Sheet 01

Sheet 02

Sheet 03

Fig. A-FDGAA

ADDITIONAL WORK - Hook-up Chart in

133VU

Sheet 01

(a) Remove the wires as shown on the wiring diagram Fig. A-FCGAA Sheet 01, Fig. AFCGAA Sheet 02 and as given in the Hook-up Chart lines:

- 1 thru 10 Fig. A-FDGAA Sheet 01

(b) Install the wires as shown on the wiring diagram Fig. A-FCGAA Sheet 01, Fig. AFCGAA Sheet 03 and as given in the Hook-up Chart lines:

- 14 thru 23 Fig. A-FDGAA Sheet 01

supplied in:

Bundle A9000095320795

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 252

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(c) Attach the wires with:

20 Tie-Cable NSA935401-03

**CONF 003

(1) Subtask 742003-831-009-001 - Modify the wiring in the Circuit Breaker panel 133VU

Work Zones and Access Panels

Zone Access/Work location

210

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320795 BUNDLE

NSA935401-03 20 TIE

References

Fig. A-FCGAA

ADDITIONAL WORK - Modification

wiring in 133VU

Sheet 01

Sheet 02

Sheet 03

Fig. A-FDGAA

ADDITIONAL WORK - Hook-up Chart in

133VU

Sheet 01

(a) Remove the wires as shown on the wiring diagram Fig. A-FCGAA Sheet 01, Fig. AFCGAA Sheet 02 and as given in the Hook-up Chart lines:

- 1 thru 10 Fig. A-FDGAA Sheet 01

(b) Install the wires as shown on the wiring diagram Fig. A-FCGAA Sheet 01, Fig. AFCGAA Sheet 03 and as given in the Hook-up Chart lines:

- 14 thru 23 Fig. A-FDGAA Sheet 01

supplied in:

Bundle A9000095320795

(c) Attach the wires with:

20 Tie-Cable NSA935401-03

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 253

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 006

(1) Subtask 742003-831-009-001 - Modify the wiring in the Circuit Breaker panel 133VU

Work Zones and Access Panels

Zone Access/Work location

210

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320795 BUNDLE

NSA935401-03 20 TIE

References

Fig. A-FCGAA

ADDITIONAL WORK - Modification

wiring in 133VU

Sheet 01

Sheet 02

Sheet 03

Fig. A-FDGAA

ADDITIONAL WORK - Hook-up Chart in

133VU

Sheet 01

(a) Remove the wires as shown on the wiring diagram Fig. A-FCGAA Sheet 01, Fig. AFCGAA Sheet 02 and as given in the Hook-up Chart lines:

- 1 thru 10 Fig. A-FDGAA Sheet 01

(b) Install the wires as shown on the wiring diagram Fig. A-FCGAA Sheet 01, Fig. AFCGAA Sheet 03 and as given in the Hook-up Chart lines:

- 14 thru 23 Fig. A-FDGAA Sheet 01

supplied in:

Bundle A9000095320795

(c) Attach the wires with:

20 Tie-Cable NSA935401-03

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 254

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 007

(1) Subtask 742003-831-009-001 - Modify the wiring in the Circuit Breaker panel 133VU

Work Zones and Access Panels

Zone Access/Work location

210

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320795 BUNDLE

NSA935401-03 20 TIE

References

Fig. A-FCGAA

ADDITIONAL WORK - Modification

wiring in 133VU

Sheet 01

Sheet 02

Sheet 03

Fig. A-FDGAA

ADDITIONAL WORK - Hook-up Chart in

133VU

Sheet 01

(a) Remove the wires as shown on the wiring diagram Fig. A-FCGAA Sheet 01, Fig. AFCGAA Sheet 02 and as given in the Hook-up Chart lines:

- 1 thru 10 Fig. A-FDGAA Sheet 01

(b) Install the wires as shown on the wiring diagram Fig. A-FCGAA Sheet 01, Fig. AFCGAA Sheet 03 and as given in the Hook-up Chart lines:

- 14 thru 23 Fig. A-FDGAA Sheet 01

supplied in:

Bundle A9000095320795

(c) Attach the wires with:

20 Tie-Cable NSA935401-03

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 255

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 008

(1) Subtask 742003-831-009-001 - Modify the wiring in the Circuit Breaker panel 133VU

Work Zones and Access Panels

Zone Access/Work location

210

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320795 BUNDLE

NSA935401-03 20 TIE

References

Fig. A-FCGAA

ADDITIONAL WORK - Modification

wiring in 133VU

Sheet 01

Sheet 02

Sheet 03

Fig. A-FDGAA

ADDITIONAL WORK - Hook-up Chart in

133VU

Sheet 01

(a) Remove the wires as shown on the wiring diagram Fig. A-FCGAA Sheet 01, Fig. AFCGAA Sheet 02 and as given in the Hook-up Chart lines:

- 1 thru 10 Fig. A-FDGAA Sheet 01

(b) Install the wires as shown on the wiring diagram Fig. A-FCGAA Sheet 01, Fig. AFCGAA Sheet 03 and as given in the Hook-up Chart lines:

- 14 thru 23 Fig. A-FDGAA Sheet 01

supplied in:

Bundle A9000095320795

(c) Attach the wires with:

20 Tie-Cable NSA935401-03

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 256

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 009

(1) Subtask 742003-831-009-001 - Modify the wiring in the Circuit Breaker panel 133VU

Work Zones and Access Panels

Zone Access/Work location

210

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095320795 BUNDLE

NSA935401-03 20 TIE

References

Fig. A-FCGAA

ADDITIONAL WORK - Modification

wiring in 133VU

Sheet 01

Sheet 02

Sheet 03

Fig. A-FDGAA

ADDITIONAL WORK - Hook-up Chart in

133VU

Sheet 01

(a) Remove the wires as shown on the wiring diagram Fig. A-FCGAA Sheet 01, Fig. AFCGAA Sheet 02 and as given in the Hook-up Chart lines:

- 1 thru 10 Fig. A-FDGAA Sheet 01

(b) Install the wires as shown on the wiring diagram Fig. A-FCGAA Sheet 01, Fig. AFCGAA Sheet 03 and as given in the Hook-up Chart lines:

- 14 thru 23 Fig. A-FDGAA Sheet 01

supplied in:

Bundle A9000095320795

(c) Attach the wires with:

20 Tie-Cable NSA935401-03

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 257

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

D. TEST

**CONF 001

(1) Subtask 742003-710-001-001 - Operational

Manpower Resources

Skills ELECTRICAL

References

Aircraft Maintenance Manual (AMM) 31-69-00, Page Block 501

(a) Remove the safety clip(s) and/or tag(s) and close/unlock this (these) circuit

breaker(s)

PANEL DESIGNATION FIN LOCATION SEE

NOTES

21VU ELEC/CBMS REAR PANEL 10WY B13

(b) Do the operational test of the circuit breaker monitoring system for panel 133VU

(Refer to AMM 31-69-00, Page Block 501)

**CONF 002

(1) Subtask 742003-710-001-001 - Operational

Manpower Resources

Skills ELECTRICAL

References

Aircraft Maintenance Manual (AMM) 31-69-00, Page Block 501

(a) Remove the safety clip(s) and/or tag(s) and close/unlock this (these) circuit

breaker(s)

PANEL DESIGNATION FIN LOCATION SEE

NOTES

21VU ELEC/CBMS REAR PANEL 10WY B13

(b) Do the operational test of the circuit breaker monitoring system for panel 133VU

(Refer to AMM 31-69-00, Page Block 501)

**CONF 003

(1) Subtask 742003-710-001-001 - Operational

Manpower Resources

Skills ELECTRICAL

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 258

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 31-69-00, Page Block 501

(a) Remove the safety clip(s) and/or tag(s) and close/unlock this (these) circuit

breaker(s)

PANEL DESIGNATION FIN LOCATION SEE

NOTES

21VU ELEC/CBMS REAR PANEL 10WY B13

(b) Do the operational test of the circuit breaker monitoring system for panel 133VU

(Refer to AMM 31-69-00, Page Block 501)

**CONF 006

(1) Subtask 742003-710-001-001 - Operational

Manpower Resources

Skills ELECTRICAL

References

Aircraft Maintenance Manual (AMM) 31-69-00, Page Block 501

(a) Remove the safety clip(s) and/or tag(s) and close/unlock this (these) circuit

breaker(s)

PANEL DESIGNATION FIN LOCATION SEE

NOTES

21VU ELEC/CBMS REAR PANEL 10WY B13

(b) Do the operational test of the circuit breaker monitoring system for panel 133VU

(Refer to AMM 31-69-00, Page Block 501)

**CONF 007

(1) Subtask 742003-710-001-001 - Operational

Manpower Resources

Skills ELECTRICAL

References

Aircraft Maintenance Manual (AMM) 31-69-00, Page Block 501

(a) Remove the safety clip(s) and/or tag(s) and close/unlock this (these) circuit

breaker(s)

PANEL DESIGNATION FIN LOCATION SEE

NOTES

21VU ELEC/CBMS REAR PANEL 10WY B13

(b) Do the operational test of the circuit breaker monitoring system for panel 133VU

(Refer to AMM 31-69-00, Page Block 501)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 259

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 008

(1) Subtask 742003-710-001-001 - Operational

Manpower Resources

Skills ELECTRICAL

References

Aircraft Maintenance Manual (AMM) 31-69-00, Page Block 501

(a) Remove the safety clip(s) and/or tag(s) and close/unlock this (these) circuit

breaker(s)

PANEL DESIGNATION FIN LOCATION SEE

NOTES

21VU ELEC/CBMS REAR PANEL 10WY B13

(b) Do the operational test of the circuit breaker monitoring system for panel 133VU

(Refer to AMM 31-69-00, Page Block 501)

**CONF 009

(1) Subtask 742003-710-001-001 - Operational

Manpower Resources

Skills ELECTRICAL

References

Aircraft Maintenance Manual (AMM) 31-69-00, Page Block 501

(a) Remove the safety clip(s) and/or tag(s) and close/unlock this (these) circuit

breaker(s)

PANEL DESIGNATION FIN LOCATION SEE

NOTES

21VU ELEC/CBMS REAR PANEL 10WY B13

(b) Do the operational test of the circuit breaker monitoring system for panel 133VU

(Refer to AMM 31-69-00, Page Block 501)

**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 742003-942-002-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 260

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 52-10-00

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Close the access doors (Refer to AMM 52-10-00)

(c) Restore system and aircraft to normal operating system.

(d) Remove access platforms.

**CONF 002

(1) Subtask 742003-942-002-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 52-10-00

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Close the access doors (Refer to AMM 52-10-00)

(c) Restore system and aircraft to normal operating system.

(d) Remove access platforms.

**CONF 003

(1) Subtask 742003-942-002-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 52-10-00

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Close the access doors (Refer to AMM 52-10-00)

(c) Restore system and aircraft to normal operating system.

(d) Remove access platforms.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 261

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 006

(1) Subtask 742003-942-002-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 52-10-00

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Close the access doors (Refer to AMM 52-10-00)

(c) Restore system and aircraft to normal operating system.

(d) Remove access platforms.

**CONF 007

(1) Subtask 742003-942-002-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 52-10-00

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Close the access doors (Refer to AMM 52-10-00)

(c) Restore system and aircraft to normal operating system.

(d) Remove access platforms.

**CONF 008

(1) Subtask 742003-942-002-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 52-10-00

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Close the access doors (Refer to AMM 52-10-00)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 262

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(c) Restore system and aircraft to normal operating system.

(d) Remove access platforms.

**CONF 009

(1) Subtask 742003-942-002-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 52-10-00

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Close the access doors (Refer to AMM 52-10-00)

(c) Restore system and aircraft to normal operating system.

(d) Remove access platforms.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 263

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 264

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Task 742003-831-803-001 - Modification - ADDITIONAL WORK

**CONF ALL

WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS

INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO

THIS:

- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS

NECESSARY ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00.

NOTE: The accomplishment instructions of this Service Bulletin refer to procedures

included in other AIRBUS documents. When the words ’refer to’ are used and the

operator has an accepted alternative procedure, the accepted alternative procedure

can be used. When the words ’in accordance with’ are included in the instruction,

the procedure in the AIRBUS document must be used.

NOTE: The access and close-up instructions, not comprising return to service tests, in this

Service Bulletin do not constitute or affect the technical intent of the Service

Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or

close-up steps to add flexibility to their maintenance operations as long as the

technical intent of the Service Bulletin is met within the set parameters.

NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms.

Refer to paragraph 1.J., References, for the definition of acronyms.

Task Associated Data

**CONF 001

Zone

120

Manpower

TOTAL MANHOURS 10.00

ELAPSED TIME (HOURS) 10.00

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 265

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 002

Zone

120

Manpower

TOTAL MANHOURS 10.00

ELAPSED TIME (HOURS) 10.00

**CONF 003

Zone

120

Manpower

TOTAL MANHOURS 10.00

ELAPSED TIME (HOURS) 10.00

**CONF 006

Zone

120

Manpower

TOTAL MANHOURS 10.00

ELAPSED TIME (HOURS) 10.00

**CONF 007

Zone

120

Manpower

TOTAL MANHOURS 10.00

ELAPSED TIME (HOURS) 10.00

**CONF 008

Zone

120

Manpower

TOTAL MANHOURS 10.00

ELAPSED TIME (HOURS) 10.00

**CONF 009

Zone

120

Manpower

TOTAL MANHOURS 10.00

ELAPSED TIME (HOURS) 10.00

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 266

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 742003-839-003-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF 002

(1) Subtask 742003-839-003-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF 003

(1) Subtask 742003-839-003-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF 006

(1) Subtask 742003-839-003-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF 007

(1) Subtask 742003-839-003-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 267

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 008

(1) Subtask 742003-839-003-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF 009

(1) Subtask 742003-839-003-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF ALL

B. PREPARATION

**CONF 001

(1) Subtask 742003-910-003-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Elec. Std. Practices Manual (ESPM) 20-25-51

20-33-00

20-33-44

20-52-21

(a) Obey the instructions for the general wiring installation (Refer to ESPM 20-33-00).

(b) To install the new wires cut them to the necessary length, crimp the terminals and

connect them.

(c) Do a continuity test of the new and modified wires (Refer to ESPM 20-52-21).

(d) Route the new wires with the wires that are in the aircraft.

(e) For the cable tie application and tooling, refer to ESPM 20-25-51 and ESPM

20-33-44.

(2) Subtask 742003-941-003-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 268

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301

24-31-11, Page Block 401

52-10-00

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page

Block 301)

(c) Put access platform(s) in position

(d) Open the passenger/crew door(s) (Refer to AMM 52-10-00)

(e) Make sure that the external connector(s) is (are) not connected to the aircraft

receptacle(s) EXT PW.

(f) Make sure that there is (are) warning notice(s) on external power receptacle to tell

persons not to connect an external power source.

(g) In the cockpit, on the overhead panel 424VU release BAT pushbutton switches.

(h) Put a warning notice on panel 424VU to tell persons not to operate the batteries.

(i) Put a warning notice on the refuel/defuel panel 110VU to tell persons not to operate

the NORMAL BATTERY switch.

(j) Put a warning notice in the cockpit to tell persons not to start the APU.

(k) Put a warning notice in the cockpit to tell persons not to start the ENG1, 2

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 269

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(l) Battery disconnection:

- For Job Set-up, refer to Removal of the Batteries (Refer to AMM 24-31-11,

Page Block 401)

- Turn the knurled nut a quarter turn

- Disconnect the connectors

- Put blanking caps on the disconnected electrical connectors

**CONF 002

(1) Subtask 742003-910-003-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Elec. Std. Practices Manual (ESPM) 20-25-51

20-33-00

20-33-44

20-52-21

(a) Obey the instructions for the general wiring installation (Refer to ESPM 20-33-00).

(b) To install the new wires cut them to the necessary length, crimp the terminals and

connect them.

(c) Do a continuity test of the new and modified wires (Refer to ESPM 20-52-21).

(d) Route the new wires with the wires that are in the aircraft.

(e) For the cable tie application and tooling, refer to ESPM 20-25-51 and ESPM

20-33-44.

(2) Subtask 742003-941-003-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301

24-31-11, Page Block 401

52-10-00

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 270

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page

Block 301)

(c) Put access platform(s) in position

(d) Open the passenger/crew door(s) (Refer to AMM 52-10-00)

(e) Make sure that the external connector(s) is (are) not connected to the aircraft

receptacle(s) EXT PW.

(f) Make sure that there is (are) warning notice(s) on external power receptacle to tell

persons not to connect an external power source.

(g) In the cockpit, on the overhead panel 424VU release BAT pushbutton switches.

(h) Put a warning notice on panel 424VU to tell persons not to operate the batteries.

(i) Put a warning notice on the refuel/defuel panel 110VU to tell persons not to operate

the NORMAL BATTERY switch.

(j) Put a warning notice in the cockpit to tell persons not to start the APU.

(k) Put a warning notice in the cockpit to tell persons not to start the ENG1, 2

(l) Battery disconnection:

- For Job Set-up, refer to Removal of the Batteries (Refer to AMM 24-31-11,

Page Block 401)

- Turn the knurled nut a quarter turn

- Disconnect the connectors

- Put blanking caps on the disconnected electrical connectors

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 271

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 003

(1) Subtask 742003-910-003-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Elec. Std. Practices Manual (ESPM) 20-25-51

20-33-00

20-33-44

20-52-21

(a) Obey the instructions for the general wiring installation (Refer to ESPM 20-33-00).

(b) To install the new wires cut them to the necessary length, crimp the terminals and

connect them.

(c) Do a continuity test of the new and modified wires (Refer to ESPM 20-52-21).

(d) Route the new wires with the wires that are in the aircraft.

(e) For the cable tie application and tooling, refer to ESPM 20-25-51 and ESPM

20-33-44.

(2) Subtask 742003-941-003-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301

24-31-11, Page Block 401

52-10-00

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 272

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page

Block 301)

(c) Put access platform(s) in position

(d) Open the passenger/crew door(s) (Refer to AMM 52-10-00)

(e) Make sure that the external connector(s) is (are) not connected to the aircraft

receptacle(s) EXT PW.

(f) Make sure that there is (are) warning notice(s) on external power receptacle to tell

persons not to connect an external power source.

(g) In the cockpit, on the overhead panel 424VU release BAT pushbutton switches.

(h) Put a warning notice on panel 424VU to tell persons not to operate the batteries.

(i) Put a warning notice on the refuel/defuel panel 110VU to tell persons not to operate

the NORMAL BATTERY switch.

(j) Put a warning notice in the cockpit to tell persons not to start the APU.

(k) Put a warning notice in the cockpit to tell persons not to start the ENG1, 2

(l) Battery disconnection:

- For Job Set-up, refer to Removal of the Batteries (Refer to AMM 24-31-11,

Page Block 401)

- Turn the knurled nut a quarter turn

- Disconnect the connectors

- Put blanking caps on the disconnected electrical connectors

**CONF 006

(1) Subtask 742003-910-003-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Elec. Std. Practices Manual (ESPM) 20-25-51

20-33-00

20-33-44

20-52-21

(a) Obey the instructions for the general wiring installation (Refer to ESPM 20-33-00).

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 273

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(b) To install the new wires cut them to the necessary length, crimp the terminals and

connect them.

(c) Do a continuity test of the new and modified wires (Refer to ESPM 20-52-21).

(d) Route the new wires with the wires that are in the aircraft.

(e) For the cable tie application and tooling, refer to ESPM 20-25-51 and ESPM

20-33-44.

(2) Subtask 742003-941-003-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301

24-31-11, Page Block 401

52-10-00

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page

Block 301)

(c) Put access platform(s) in position

(d) Open the passenger/crew door(s) (Refer to AMM 52-10-00)

(e) Make sure that the external connector(s) is (are) not connected to the aircraft

receptacle(s) EXT PW.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 274

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(f) Make sure that there is (are) warning notice(s) on external power receptacle to tell

persons not to connect an external power source.

(g) In the cockpit, on the overhead panel 424VU release BAT pushbutton switches.

(h) Put a warning notice on panel 424VU to tell persons not to operate the batteries.

(i) Put a warning notice on the refuel/defuel panel 110VU to tell persons not to operate

the NORMAL BATTERY switch.

(j) Put a warning notice in the cockpit to tell persons not to start the APU.

(k) Put a warning notice in the cockpit to tell persons not to start the ENG1, 2

(l) Battery disconnection:

- For Job Set-up, refer to Removal of the Batteries (Refer to AMM 24-31-11,

Page Block 401)

- Turn the knurled nut a quarter turn

- Disconnect the connectors

- Put blanking caps on the disconnected electrical connectors

**CONF 007

(1) Subtask 742003-910-003-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Elec. Std. Practices Manual (ESPM) 20-25-51

20-33-00

20-33-44

20-52-21

(a) Obey the instructions for the general wiring installation (Refer to ESPM 20-33-00).

(b) To install the new wires cut them to the necessary length, crimp the terminals and

connect them.

(c) Do a continuity test of the new and modified wires (Refer to ESPM 20-52-21).

(d) Route the new wires with the wires that are in the aircraft.

(e) For the cable tie application and tooling, refer to ESPM 20-25-51 and ESPM

20-33-44.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 275

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(2) Subtask 742003-941-003-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301

24-31-11, Page Block 401

52-10-00

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page

Block 301)

(c) Put access platform(s) in position

(d) Open the passenger/crew door(s) (Refer to AMM 52-10-00)

(e) Make sure that the external connector(s) is (are) not connected to the aircraft

receptacle(s) EXT PW.

(f) Make sure that there is (are) warning notice(s) on external power receptacle to tell

persons not to connect an external power source.

(g) In the cockpit, on the overhead panel 424VU release BAT pushbutton switches.

(h) Put a warning notice on panel 424VU to tell persons not to operate the batteries.

(i) Put a warning notice on the refuel/defuel panel 110VU to tell persons not to operate

the NORMAL BATTERY switch.

(j) Put a warning notice in the cockpit to tell persons not to start the APU.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 276

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(k) Put a warning notice in the cockpit to tell persons not to start the ENG1, 2

(l) Battery disconnection:

- For Job Set-up, refer to Removal of the Batteries (Refer to AMM 24-31-11,

Page Block 401)

- Turn the knurled nut a quarter turn

- Disconnect the connectors

- Put blanking caps on the disconnected electrical connectors

**CONF 008

(1) Subtask 742003-910-003-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Elec. Std. Practices Manual (ESPM) 20-25-51

20-33-00

20-33-44

20-52-21

(a) Obey the instructions for the general wiring installation (Refer to ESPM 20-33-00).

(b) To install the new wires cut them to the necessary length, crimp the terminals and

connect them.

(c) Do a continuity test of the new and modified wires (Refer to ESPM 20-52-21).

(d) Route the new wires with the wires that are in the aircraft.

(e) For the cable tie application and tooling, refer to ESPM 20-25-51 and ESPM

20-33-44.

(2) Subtask 742003-941-003-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301

24-31-11, Page Block 401

52-10-00

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 277

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page

Block 301)

(c) Put access platform(s) in position

(d) Open the passenger/crew door(s) (Refer to AMM 52-10-00)

(e) Make sure that the external connector(s) is (are) not connected to the aircraft

receptacle(s) EXT PW.

(f) Make sure that there is (are) warning notice(s) on external power receptacle to tell

persons not to connect an external power source.

(g) In the cockpit, on the overhead panel 424VU release BAT pushbutton switches.

(h) Put a warning notice on panel 424VU to tell persons not to operate the batteries.

(i) Put a warning notice on the refuel/defuel panel 110VU to tell persons not to operate

the NORMAL BATTERY switch.

(j) Put a warning notice in the cockpit to tell persons not to start the APU.

(k) Put a warning notice in the cockpit to tell persons not to start the ENG1, 2

(l) Battery disconnection:

- For Job Set-up, refer to Removal of the Batteries (Refer to AMM 24-31-11,

Page Block 401)

- Turn the knurled nut a quarter turn

- Disconnect the connectors

- Put blanking caps on the disconnected electrical connectors

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 278

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 009

(1) Subtask 742003-910-003-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Elec. Std. Practices Manual (ESPM) 20-25-51

20-33-00

20-33-44

20-52-21

(a) Obey the instructions for the general wiring installation (Refer to ESPM 20-33-00).

(b) To install the new wires cut them to the necessary length, crimp the terminals and

connect them.

(c) Do a continuity test of the new and modified wires (Refer to ESPM 20-52-21).

(d) Route the new wires with the wires that are in the aircraft.

(e) For the cable tie application and tooling, refer to ESPM 20-25-51 and ESPM

20-33-44.

(2) Subtask 742003-941-003-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301

24-31-11, Page Block 401

52-10-00

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 279

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page

Block 301)

(c) Put access platform(s) in position

(d) Open the passenger/crew door(s) (Refer to AMM 52-10-00)

(e) Make sure that the external connector(s) is (are) not connected to the aircraft

receptacle(s) EXT PW.

(f) Make sure that there is (are) warning notice(s) on external power receptacle to tell

persons not to connect an external power source.

(g) In the cockpit, on the overhead panel 424VU release BAT pushbutton switches.

(h) Put a warning notice on panel 424VU to tell persons not to operate the batteries.

(i) Put a warning notice on the refuel/defuel panel 110VU to tell persons not to operate

the NORMAL BATTERY switch.

(j) Put a warning notice in the cockpit to tell persons not to start the APU.

(k) Put a warning notice in the cockpit to tell persons not to start the ENG1, 2

(l) Battery disconnection:

- For Job Set-up, refer to Removal of the Batteries (Refer to AMM 24-31-11,

Page Block 401)

- Turn the knurled nut a quarter turn

- Disconnect the connectors

- Put blanking caps on the disconnected electrical connectors

**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 742003-831-010-001 - Modify the wiring in the Relay Box 105VU on bench

Work Zones and Access Panels

Zone Access/Work location

120

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 280

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A03R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095321095 BUNDLE

NSA935401-03 50 TIE

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Pure Mineral Vaseline Or

Petro- Latum

04-012 As required

Electrical Bond Varnish 07-001B As required

References

Aircraft Maintenance Manual (AMM) 20-28-11

Fig. A-FCHAA

ADDITIONAL WORK - Modification

wiring in 105VU

Sheet 01

Fig. A-FDHAA

ADDITIONAL WORK - Hook-up Chart in

105VU

Sheet 01

(a) From the Relay Box 105VU, disconnect the bonding strip, remove the screws, the

clamps and the box front cover

NOTE: Disconnect the connectors and remove the Relay Box 105VU to get

access to the inside of the box.

Put blanking caps on the disconnected electrical connectors.

Reconnect and install all the removed components after

modification.

(b) Remove the wires as shown on the wiring diagram Fig. A-FCHAA Sheet 01 and as

given in the Hook-up Chart lines:

- 1 thru 2 Fig. A-FDHAA Sheet 01

(c) Install the wires as shown on the wiring diagram Fig. A-FCHAA Sheet 01 and as

given in the Hook-up Chart lines:

- 6 thru 7 Fig. A-FDHAA Sheet 01

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 281

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

supplied in:

Bundle A9000095321095

(d) Attach the wires with:

50 Tie-Cable NSA935401-03

(e) On the relay box 105VU, do the electrical bonding (Refer to AMM 20-28-11) with :

Pure Mineral

Vaseline Or PetroLatum

04-012 As required

Electrical Bond

Varnish

07-001B As required

(f) Connect the bonding strip, install the screws, the clamps and the front box.

Reconnect and install the Relay Box 105VU

**CONF 002

(1) Subtask 742003-831-010-001 - Modify the wiring in the Relay Box 105VU on bench

Work Zones and Access Panels

Zone Access/Work location

120

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A03R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095321095 BUNDLE

NSA935401-03 50 TIE

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Pure Mineral Vaseline Or

Petro- Latum

04-012 As required

Electrical Bond Varnish 07-001B As required

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 282

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 20-28-11

Fig. A-FCHAA

ADDITIONAL WORK - Modification

wiring in 105VU

Sheet 01

Fig. A-FDHAA

ADDITIONAL WORK - Hook-up Chart in

105VU

Sheet 01

(a) From the Relay Box 105VU, disconnect the bonding strip, remove the screws, the

clamps and the box front cover

NOTE: Disconnect the connectors and remove the Relay Box 105VU to get

access to the inside of the box.

Put blanking caps on the disconnected electrical connectors.

Reconnect and install all the removed components after

modification.

(b) Remove the wires as shown on the wiring diagram Fig. A-FCHAA Sheet 01 and as

given in the Hook-up Chart lines:

- 1 thru 2 Fig. A-FDHAA Sheet 01

(c) Install the wires as shown on the wiring diagram Fig. A-FCHAA Sheet 01 and as

given in the Hook-up Chart lines:

- 6 thru 7 Fig. A-FDHAA Sheet 01

supplied in:

Bundle A9000095321095

(d) Attach the wires with:

50 Tie-Cable NSA935401-03

(e) On the relay box 105VU, do the electrical bonding (Refer to AMM 20-28-11) with :

Pure Mineral

Vaseline Or PetroLatum

04-012 As required

Electrical Bond

Varnish

07-001B As required

(f) Connect the bonding strip, install the screws, the clamps and the front box.

Reconnect and install the Relay Box 105VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 283

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 003

(1) Subtask 742003-831-010-001 - Modify the wiring in the Relay Box 105VU on bench

Work Zones and Access Panels

Zone Access/Work location

120

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A03R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095321095 BUNDLE

NSA935401-03 50 TIE

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Pure Mineral Vaseline Or

Petro- Latum

04-012 As required

Electrical Bond Varnish 07-001B As required

References

Aircraft Maintenance Manual (AMM) 20-28-11

Fig. A-FCHAA

ADDITIONAL WORK - Modification

wiring in 105VU

Sheet 01

Fig. A-FDHAA

ADDITIONAL WORK - Hook-up Chart in

105VU

Sheet 01

(a) From the Relay Box 105VU, disconnect the bonding strip, remove the screws, the

clamps and the box front cover

NOTE: Disconnect the connectors and remove the Relay Box 105VU to get

access to the inside of the box.

Put blanking caps on the disconnected electrical connectors.

Reconnect and install all the removed components after

modification.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 284

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(b) Remove the wires as shown on the wiring diagram Fig. A-FCHAA Sheet 01 and as

given in the Hook-up Chart lines:

- 1 thru 2 Fig. A-FDHAA Sheet 01

(c) Install the wires as shown on the wiring diagram Fig. A-FCHAA Sheet 01 and as

given in the Hook-up Chart lines:

- 6 thru 7 Fig. A-FDHAA Sheet 01

supplied in:

Bundle A9000095321095

(d) Attach the wires with:

50 Tie-Cable NSA935401-03

(e) On the relay box 105VU, do the electrical bonding (Refer to AMM 20-28-11) with :

Pure Mineral

Vaseline Or PetroLatum

04-012 As required

Electrical Bond

Varnish

07-001B As required

(f) Connect the bonding strip, install the screws, the clamps and the front box.

Reconnect and install the Relay Box 105VU

**CONF 006

(1) Subtask 742003-831-010-001 - Modify the wiring in the Relay Box 105VU on bench

Work Zones and Access Panels

Zone Access/Work location

120

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A03R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095321095 BUNDLE

NSA935401-03 50 TIE

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 285

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Pure Mineral Vaseline Or

Petro- Latum

04-012 As required

Electrical Bond Varnish 07-001B As required

References

Aircraft Maintenance Manual (AMM) 20-28-11

Fig. A-FCHAA

ADDITIONAL WORK - Modification

wiring in 105VU

Sheet 01

Fig. A-FDHAA

ADDITIONAL WORK - Hook-up Chart in

105VU

Sheet 01

(a) From the Relay Box 105VU, disconnect the bonding strip, remove the screws, the

clamps and the box front cover

NOTE: Disconnect the connectors and remove the Relay Box 105VU to get

access to the inside of the box.

Put blanking caps on the disconnected electrical connectors.

Reconnect and install all the removed components after

modification.

(b) Remove the wires as shown on the wiring diagram Fig. A-FCHAA Sheet 01 and as

given in the Hook-up Chart lines:

- 1 thru 2 Fig. A-FDHAA Sheet 01

(c) Install the wires as shown on the wiring diagram Fig. A-FCHAA Sheet 01 and as

given in the Hook-up Chart lines:

- 6 thru 7 Fig. A-FDHAA Sheet 01

supplied in:

Bundle A9000095321095

(d) Attach the wires with:

50 Tie-Cable NSA935401-03

(e) On the relay box 105VU, do the electrical bonding (Refer to AMM 20-28-11) with :

Pure Mineral

Vaseline Or PetroLatum

04-012 As required

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 286

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Electrical Bond

Varnish

07-001B As required

(f) Connect the bonding strip, install the screws, the clamps and the front box.

Reconnect and install the Relay Box 105VU

**CONF 007

(1) Subtask 742003-831-010-001 - Modify the wiring in the Relay Box 105VU on bench

Work Zones and Access Panels

Zone Access/Work location

120

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A03R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095321095 BUNDLE

NSA935401-03 50 TIE

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Pure Mineral Vaseline Or

Petro- Latum

04-012 As required

Electrical Bond Varnish 07-001B As required

References

Aircraft Maintenance Manual (AMM) 20-28-11

Fig. A-FCHAA

ADDITIONAL WORK - Modification

wiring in 105VU

Sheet 01

Fig. A-FDHAA

ADDITIONAL WORK - Hook-up Chart in

105VU

Sheet 01

(a) From the Relay Box 105VU, disconnect the bonding strip, remove the screws, the

clamps and the box front cover

NOTE: Disconnect the connectors and remove the Relay Box 105VU to get

access to the inside of the box.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 287

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Put blanking caps on the disconnected electrical connectors.

Reconnect and install all the removed components after

modification.

(b) Remove the wires as shown on the wiring diagram Fig. A-FCHAA Sheet 01 and as

given in the Hook-up Chart lines:

- 1 thru 2 Fig. A-FDHAA Sheet 01

(c) Install the wires as shown on the wiring diagram Fig. A-FCHAA Sheet 01 and as

given in the Hook-up Chart lines:

- 6 thru 7 Fig. A-FDHAA Sheet 01

supplied in:

Bundle A9000095321095

(d) Attach the wires with:

50 Tie-Cable NSA935401-03

(e) On the relay box 105VU, do the electrical bonding (Refer to AMM 20-28-11) with :

Pure Mineral

Vaseline Or PetroLatum

04-012 As required

Electrical Bond

Varnish

07-001B As required

(f) Connect the bonding strip, install the screws, the clamps and the front box.

Reconnect and install the Relay Box 105VU

**CONF 008

(1) Subtask 742003-831-010-001 - Modify the wiring in the Relay Box 105VU on bench

Work Zones and Access Panels

Zone Access/Work location

120

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills ELECTRICAL

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 288

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Material necessary to do the job

Kit 742003A03R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095321095 BUNDLE

NSA935401-03 50 TIE

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Pure Mineral Vaseline Or

Petro- Latum

04-012 As required

Electrical Bond Varnish 07-001B As required

References

Aircraft Maintenance Manual (AMM) 20-28-11

Fig. A-FCHAA

ADDITIONAL WORK - Modification

wiring in 105VU

Sheet 01

Fig. A-FDHAA

ADDITIONAL WORK - Hook-up Chart in

105VU

Sheet 01

(a) From the Relay Box 105VU, disconnect the bonding strip, remove the screws, the

clamps and the box front cover

NOTE: Disconnect the connectors and remove the Relay Box 105VU to get

access to the inside of the box.

Put blanking caps on the disconnected electrical connectors.

Reconnect and install all the removed components after

modification.

(b) Remove the wires as shown on the wiring diagram Fig. A-FCHAA Sheet 01 and as

given in the Hook-up Chart lines:

- 1 thru 2 Fig. A-FDHAA Sheet 01

(c) Install the wires as shown on the wiring diagram Fig. A-FCHAA Sheet 01 and as

given in the Hook-up Chart lines:

- 6 thru 7 Fig. A-FDHAA Sheet 01

supplied in:

Bundle A9000095321095

(d) Attach the wires with:

50 Tie-Cable NSA935401-03

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 289

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(e) On the relay box 105VU, do the electrical bonding (Refer to AMM 20-28-11) with :

Pure Mineral

Vaseline Or PetroLatum

04-012 As required

Electrical Bond

Varnish

07-001B As required

(f) Connect the bonding strip, install the screws, the clamps and the front box.

Reconnect and install the Relay Box 105VU

**CONF 009

(1) Subtask 742003-831-010-001 - Modify the wiring in the Relay Box 105VU on bench

Work Zones and Access Panels

Zone Access/Work location

120

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills ELECTRICAL

Material necessary to do the job

Kit 742003A03R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

A9000095321095 BUNDLE

NSA935401-03 50 TIE

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Pure Mineral Vaseline Or

Petro- Latum

04-012 As required

Electrical Bond Varnish 07-001B As required

References

Aircraft Maintenance Manual (AMM) 20-28-11

Fig. A-FCHAA

ADDITIONAL WORK - Modification

wiring in 105VU

Sheet 01

Fig. A-FDHAA

ADDITIONAL WORK - Hook-up Chart in

105VU

Sheet 01

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 290

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(a) From the Relay Box 105VU, disconnect the bonding strip, remove the screws, the

clamps and the box front cover

NOTE: Disconnect the connectors and remove the Relay Box 105VU to get

access to the inside of the box.

Put blanking caps on the disconnected electrical connectors.

Reconnect and install all the removed components after

modification.

(b) Remove the wires as shown on the wiring diagram Fig. A-FCHAA Sheet 01 and as

given in the Hook-up Chart lines:

- 1 thru 2 Fig. A-FDHAA Sheet 01

(c) Install the wires as shown on the wiring diagram Fig. A-FCHAA Sheet 01 and as

given in the Hook-up Chart lines:

- 6 thru 7 Fig. A-FDHAA Sheet 01

supplied in:

Bundle A9000095321095

(d) Attach the wires with:

50 Tie-Cable NSA935401-03

(e) On the relay box 105VU, do the electrical bonding (Refer to AMM 20-28-11) with :

Pure Mineral

Vaseline Or PetroLatum

04-012 As required

Electrical Bond

Varnish

07-001B As required

(f) Connect the bonding strip, install the screws, the clamps and the front box.

Reconnect and install the Relay Box 105VU

**CONF ALL

D. TEST

**CONF 001

(1) Subtask 742003-720-002-001 - Functional

Manpower Resources

Skills ELECTRICAL

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 291

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 20-28-11, Page Block 001

21-21-00, Page Block 501

22-40-00, Page Block 501

24-31-00, Page Block 301

24-31-11, Page Block 401

26-12-20, Page Block 501

28-24-31, Page Block 401

31-51-00, Page Block 501

31-53-34, Page Block 401

31-55-22, Page Block 401

33-12-00, Page Block 501

33-13-00, Page Block 501

33-14-00, Page Block 501

33-46-00, Page Block 501

34-44-34, Page Block 401

34-68-34, Page Block 401

36-11-00, Page Block 501

78-31-00, Page Block 501

Elec. Std. Practices Manual (ESPM) 20-52-20

(a) Job Set-up

1 Battery re-connection

- For Job Set-up, refer to Installation of the Batteries (Refer to AMM

24-31-11, Page Block 401)

- Remove the blanking cap from the electrical connectors

- Make sure that the electrical connectors are clean and in correct condition

- Connect the connector on the battery

- Turn the knurled nut a quarter turn

2 Remove all warning notices

3 Energize the aircraft electrical circuits (Refer to AMM 24-31-00, Page Block

301)

4 Preliminary Tests :

NOTE: If the aircraft is operated in CAT3 conditions, you must also do

the LAND test (Refer to AMM 22-40-00, Page Block 501)

a On each connector which was disconnected:

- Do the checks as defined by ESPM 20-52-20

NOTE: The Functional test and/or operational test requested by

this ESPM procedure is given hereafter.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 292

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

b Do the Operational Test of the Annunciator Light Test AMM (Refer to

AMM 33-14-00, Page Block 501)

c Do the Operational Test of the General Illumination, (Refer to AMM

33-12-00, Page Block 501)

d Do the Operational Test of the Instrument and Panel Integral Lighting,

(Refer to AMM 33-13-00, Page Block 501)

e Make certain that the ventillation system operates correctly, (Refer to

AMM 21-21-00, Page Block 501)

f Do the AFS (Automatic Flight System) Test, (Refer to AMM 22-40-00,

Page Block 501)(para 1.A))

g Do the Operational Test of ECAM/EFIS Display Test, (Refer to AMM

31-51-00, Page Block 501)

h Do the Operational Test of the FWC1 and FWC2, (Refer to AMM

31-51-00, Page Block 501)

(b) Procedure

1 Do a check of the Electrical Bonding (Refer to AMM 20-28-11, Page Block

001)

NOTE: For maximun permissible resistance values: Refer to the Table

(Refer to AMM 20-28-11, Page Block 001)

2 Do the Perform BITE test (Refer to AMM 36-11-00, Page Block 501)

(Operational Test)

3 Do the test procedure as specified after the installation of the FLIGHT

MANAGEMENT COMPUTER (1CK1, 1CK2) (Refer to AMM 34-68-34, Page

Block 401)

4 Do the Functional Test - ENGINE FIRE CONTROL MODULE (Refer to AMM

26-12-20, Page Block 501)

5 Do the test procedure as specified after the installation of the TCAS

COMPUTER (9005SG) (Refer to AMM 34-44-34, Page Block 401) (if

equipped)

6 Do the Operational Test TAXI AND TAKEOFF LIGHTS (Refer to AMM

33-46-00, Page Block 501)

7 Do the test procedure as specified after the installation of the FLIGHT

WARNING COMPUTER (1WW1, 1WW2) (Refer to AMM 31-53-34, Page

Block 401)

8 Carry out operational test of the flight compartment and electronics racks air

distribution system (Refer to AMM 21-21-00, Page Block 501)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 293

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

9 Do the test procedure as specified after the installation of the SYSTEM DATA

ANALOG CONVERTER (1WV) (Refer to AMM 31-55-22, Page Block 401)

10 Do the Thrust Reverser Functional and Indicating/Warning Sensors Test

(Refer to AMM 78-31-00, Page Block 501)

11 Do the test procedure for engine 1 as specified after the installation of the

LOW PRESSURE FUEL FIRE SHUT OFF VALVE (Refer to AMM 28-24-31,

Page Block 401)

12 Do the test procedure for engine 2 as specified after the installation of the

LOW PRESSURE FUEL FIRE SHUT OFF VALVE (Refer to AMM 28-24-31,

Page Block 401)

**CONF 002

(1) Subtask 742003-720-002-001 - Functional

Manpower Resources

Skills ELECTRICAL

References

Aircraft Maintenance Manual (AMM) 20-28-11, Page Block 001

21-21-00, Page Block 501

22-40-00, Page Block 501

24-31-00, Page Block 301

24-31-11, Page Block 401

26-12-20, Page Block 501

28-24-31, Page Block 401

31-51-00, Page Block 501

31-53-34, Page Block 401

31-55-22, Page Block 401

33-12-00, Page Block 501

33-13-00, Page Block 501

33-14-00, Page Block 501

33-46-00, Page Block 501

34-44-34, Page Block 401

34-68-34, Page Block 401

36-11-00, Page Block 501

78-31-00, Page Block 501

Elec. Std. Practices Manual (ESPM) 20-52-20

(a) Job Set-up

1 Battery re-connection

- For Job Set-up, refer to Installation of the Batteries (Refer to AMM

24-31-11, Page Block 401)

- Remove the blanking cap from the electrical connectors

- Make sure that the electrical connectors are clean and in correct condition

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 294

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

- Connect the connector on the battery

- Turn the knurled nut a quarter turn

2 Remove all warning notices

3 Energize the aircraft electrical circuits (Refer to AMM 24-31-00, Page Block

301)

4 Preliminary Tests :

NOTE: If the aircraft is operated in CAT3 conditions, you must also do

the LAND test (Refer to AMM 22-40-00, Page Block 501)

a On each connector which was disconnected:

- Do the checks as defined by ESPM 20-52-20

NOTE: The Functional test and/or operational test requested by

this ESPM procedure is given hereafter.

b Do the Operational Test of the Annunciator Light Test AMM (Refer to

AMM 33-14-00, Page Block 501)

c Do the Operational Test of the General Illumination, (Refer to AMM

33-12-00, Page Block 501)

d Do the Operational Test of the Instrument and Panel Integral Lighting,

(Refer to AMM 33-13-00, Page Block 501)

e Make certain that the ventillation system operates correctly, (Refer to

AMM 21-21-00, Page Block 501)

f Do the AFS (Automatic Flight System) Test, (Refer to AMM 22-40-00,

Page Block 501)(para 1.A))

g Do the Operational Test of ECAM/EFIS Display Test, (Refer to AMM

31-51-00, Page Block 501)

h Do the Operational Test of the FWC1 and FWC2, (Refer to AMM

31-51-00, Page Block 501)

(b) Procedure

1 Do a check of the Electrical Bonding (Refer to AMM 20-28-11, Page Block

001)

NOTE: For maximun permissible resistance values: Refer to the Table

(Refer to AMM 20-28-11, Page Block 001)

2 Do the Perform BITE test (Refer to AMM 36-11-00, Page Block 501)

(Operational Test)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 295

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

3 Do the test procedure as specified after the installation of the FLIGHT

MANAGEMENT COMPUTER (1CK1, 1CK2) (Refer to AMM 34-68-34, Page

Block 401)

4 Do the Functional Test - ENGINE FIRE CONTROL MODULE (Refer to AMM

26-12-20, Page Block 501)

5 Do the test procedure as specified after the installation of the TCAS

COMPUTER (9005SG) (Refer to AMM 34-44-34, Page Block 401) (if

equipped)

6 Do the Operational Test TAXI AND TAKEOFF LIGHTS (Refer to AMM

33-46-00, Page Block 501)

7 Do the test procedure as specified after the installation of the FLIGHT

WARNING COMPUTER (1WW1, 1WW2) (Refer to AMM 31-53-34, Page

Block 401)

8 Carry out operational test of the flight compartment and electronics racks air

distribution system (Refer to AMM 21-21-00, Page Block 501)

9 Do the test procedure as specified after the installation of the SYSTEM DATA

ANALOG CONVERTER (1WV) (Refer to AMM 31-55-22, Page Block 401)

10 Do the Thrust Reverser Functional and Indicating/Warning Sensors Test

(Refer to AMM 78-31-00, Page Block 501)

11 Do the test procedure for engine 1 as specified after the installation of the

LOW PRESSURE FUEL FIRE SHUT OFF VALVE (Refer to AMM 28-24-31,

Page Block 401)

12 Do the test procedure for engine 2 as specified after the installation of the

LOW PRESSURE FUEL FIRE SHUT OFF VALVE (Refer to AMM 28-24-31,

Page Block 401)

**CONF 003

(1) Subtask 742003-720-002-001 - Functional

Manpower Resources

Skills ELECTRICAL

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 296

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 20-28-11, Page Block 001

21-21-00, Page Block 501

22-40-00, Page Block 501

24-31-00, Page Block 301

24-31-11, Page Block 401

26-12-20, Page Block 501

28-24-31, Page Block 401

31-51-00, Page Block 501

31-53-34, Page Block 401

31-55-22, Page Block 401

33-12-00, Page Block 501

33-13-00, Page Block 501

33-14-00, Page Block 501

33-46-00, Page Block 501

34-44-34, Page Block 401

34-68-34, Page Block 401

36-11-00, Page Block 501

78-31-00, Page Block 501

Elec. Std. Practices Manual (ESPM) 20-52-20

(a) Job Set-up

1 Battery re-connection

- For Job Set-up, refer to Installation of the Batteries (Refer to AMM

24-31-11, Page Block 401)

- Remove the blanking cap from the electrical connectors

- Make sure that the electrical connectors are clean and in correct condition

- Connect the connector on the battery

- Turn the knurled nut a quarter turn

2 Remove all warning notices

3 Energize the aircraft electrical circuits (Refer to AMM 24-31-00, Page Block

301)

4 Preliminary Tests :

NOTE: If the aircraft is operated in CAT3 conditions, you must also do

the LAND test (Refer to AMM 22-40-00, Page Block 501)

a On each connector which was disconnected:

- Do the checks as defined by ESPM 20-52-20

NOTE: The Functional test and/or operational test requested by

this ESPM procedure is given hereafter.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 297

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

b Do the Operational Test of the Annunciator Light Test AMM (Refer to

AMM 33-14-00, Page Block 501)

c Do the Operational Test of the General Illumination, (Refer to AMM

33-12-00, Page Block 501)

d Do the Operational Test of the Instrument and Panel Integral Lighting,

(Refer to AMM 33-13-00, Page Block 501)

e Make certain that the ventillation system operates correctly, (Refer to

AMM 21-21-00, Page Block 501)

f Do the AFS (Automatic Flight System) Test, (Refer to AMM 22-40-00,

Page Block 501)(para 1.A))

g Do the Operational Test of ECAM/EFIS Display Test, (Refer to AMM

31-51-00, Page Block 501)

h Do the Operational Test of the FWC1 and FWC2, (Refer to AMM

31-51-00, Page Block 501)

(b) Procedure

1 Do a check of the Electrical Bonding (Refer to AMM 20-28-11, Page Block

001)

NOTE: For maximun permissible resistance values: Refer to the Table

(Refer to AMM 20-28-11, Page Block 001)

2 Do the Perform BITE test (Refer to AMM 36-11-00, Page Block 501)

(Operational Test)

3 Do the test procedure as specified after the installation of the FLIGHT

MANAGEMENT COMPUTER (1CK1, 1CK2) (Refer to AMM 34-68-34, Page

Block 401)

4 Do the Functional Test - ENGINE FIRE CONTROL MODULE (Refer to AMM

26-12-20, Page Block 501)

5 Do the test procedure as specified after the installation of the TCAS

COMPUTER (9005SG) (Refer to AMM 34-44-34, Page Block 401) (if

equipped)

6 Do the Operational Test TAXI AND TAKEOFF LIGHTS (Refer to AMM

33-46-00, Page Block 501)

7 Do the test procedure as specified after the installation of the FLIGHT

WARNING COMPUTER (1WW1, 1WW2) (Refer to AMM 31-53-34, Page

Block 401)

8 Carry out operational test of the flight compartment and electronics racks air

distribution system (Refer to AMM 21-21-00, Page Block 501)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 298

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

9 Do the test procedure as specified after the installation of the SYSTEM DATA

ANALOG CONVERTER (1WV) (Refer to AMM 31-55-22, Page Block 401)

10 Do the Thrust Reverser Functional and Indicating/Warning Sensors Test

(Refer to AMM 78-31-00, Page Block 501)

11 Do the test procedure for engine 1 as specified after the installation of the

LOW PRESSURE FUEL FIRE SHUT OFF VALVE (Refer to AMM 28-24-31,

Page Block 401)

12 Do the test procedure for engine 2 as specified after the installation of the

LOW PRESSURE FUEL FIRE SHUT OFF VALVE (Refer to AMM 28-24-31,

Page Block 401)

**CONF 006

(1) Subtask 742003-720-002-001 - Functional

Manpower Resources

Skills ELECTRICAL

References

Aircraft Maintenance Manual (AMM) 20-28-11, Page Block 001

21-21-00, Page Block 501

22-40-00, Page Block 501

24-31-00, Page Block 301

24-31-11, Page Block 401

26-12-20, Page Block 501

28-24-31, Page Block 401

31-51-00, Page Block 501

31-53-34, Page Block 401

31-55-22, Page Block 401

33-12-00, Page Block 501

33-13-00, Page Block 501

33-14-00, Page Block 501

33-46-00, Page Block 501

34-44-34, Page Block 401

34-68-34, Page Block 401

36-11-00, Page Block 501

78-31-00, Page Block 501

Elec. Std. Practices Manual (ESPM) 20-52-20

(a) Job Set-up

1 Battery re-connection

- For Job Set-up, refer to Installation of the Batteries (Refer to AMM

24-31-11, Page Block 401)

- Remove the blanking cap from the electrical connectors

- Make sure that the electrical connectors are clean and in correct condition

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 299

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

- Connect the connector on the battery

- Turn the knurled nut a quarter turn

2 Remove all warning notices

3 Energize the aircraft electrical circuits (Refer to AMM 24-31-00, Page Block

301)

4 Preliminary Tests :

NOTE: If the aircraft is operated in CAT3 conditions, you must also do

the LAND test (Refer to AMM 22-40-00, Page Block 501)

a On each connector which was disconnected:

- Do the checks as defined by ESPM 20-52-20

NOTE: The Functional test and/or operational test requested by

this ESPM procedure is given hereafter.

b Do the Operational Test of the Annunciator Light Test AMM (Refer to

AMM 33-14-00, Page Block 501)

c Do the Operational Test of the General Illumination, (Refer to AMM

33-12-00, Page Block 501)

d Do the Operational Test of the Instrument and Panel Integral Lighting,

(Refer to AMM 33-13-00, Page Block 501)

e Make certain that the ventillation system operates correctly, (Refer to

AMM 21-21-00, Page Block 501)

f Do the AFS (Automatic Flight System) Test, (Refer to AMM 22-40-00,

Page Block 501)(para 1.A))

g Do the Operational Test of ECAM/EFIS Display Test, (Refer to AMM

31-51-00, Page Block 501)

h Do the Operational Test of the FWC1 and FWC2, (Refer to AMM

31-51-00, Page Block 501)

(b) Procedure

1 Do a check of the Electrical Bonding (Refer to AMM 20-28-11, Page Block

001)

NOTE: For maximun permissible resistance values: Refer to the Table

(Refer to AMM 20-28-11, Page Block 001)

2 Do the Perform BITE test (Refer to AMM 36-11-00, Page Block 501)

(Operational Test)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 300

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

3 Do the test procedure as specified after the installation of the FLIGHT

MANAGEMENT COMPUTER (1CK1, 1CK2) (Refer to AMM 34-68-34, Page

Block 401)

4 Do the Functional Test - ENGINE FIRE CONTROL MODULE (Refer to AMM

26-12-20, Page Block 501)

5 Do the test procedure as specified after the installation of the TCAS

COMPUTER (9005SG) (Refer to AMM 34-44-34, Page Block 401) (if

equipped)

6 Do the Operational Test TAXI AND TAKEOFF LIGHTS (Refer to AMM

33-46-00, Page Block 501)

7 Do the test procedure as specified after the installation of the FLIGHT

WARNING COMPUTER (1WW1, 1WW2) (Refer to AMM 31-53-34, Page

Block 401)

8 Carry out operational test of the flight compartment and electronics racks air

distribution system (Refer to AMM 21-21-00, Page Block 501)

9 Do the test procedure as specified after the installation of the SYSTEM DATA

ANALOG CONVERTER (1WV) (Refer to AMM 31-55-22, Page Block 401)

10 Do the Thrust Reverser Functional and Indicating/Warning Sensors Test

(Refer to AMM 78-31-00, Page Block 501)

11 Do the test procedure for engine 1 as specified after the installation of the

LOW PRESSURE FUEL FIRE SHUT OFF VALVE (Refer to AMM 28-24-31,

Page Block 401)

12 Do the test procedure for engine 2 as specified after the installation of the

LOW PRESSURE FUEL FIRE SHUT OFF VALVE (Refer to AMM 28-24-31,

Page Block 401)

**CONF 007

(1) Subtask 742003-720-002-001 - Functional

Manpower Resources

Skills ELECTRICAL

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 301

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 20-28-11, Page Block 001

21-21-00, Page Block 501

22-40-00, Page Block 501

24-31-00, Page Block 301

24-31-11, Page Block 401

26-12-20, Page Block 501

28-24-31, Page Block 401

31-51-00, Page Block 501

31-53-34, Page Block 401

31-55-22, Page Block 401

33-12-00, Page Block 501

33-13-00, Page Block 501

33-14-00, Page Block 501

33-46-00, Page Block 501

34-44-34, Page Block 401

34-68-34, Page Block 401

36-11-00, Page Block 501

78-31-00, Page Block 501

Elec. Std. Practices Manual (ESPM) 20-52-20

(a) Job Set-up

1 Battery re-connection

- For Job Set-up, refer to Installation of the Batteries (Refer to AMM

24-31-11, Page Block 401)

- Remove the blanking cap from the electrical connectors

- Make sure that the electrical connectors are clean and in correct condition

- Connect the connector on the battery

- Turn the knurled nut a quarter turn

2 Remove all warning notices

3 Energize the aircraft electrical circuits (Refer to AMM 24-31-00, Page Block

301)

4 Preliminary Tests :

NOTE: If the aircraft is operated in CAT3 conditions, you must also do

the LAND test (Refer to AMM 22-40-00, Page Block 501)

a On each connector which was disconnected:

- Do the checks as defined by ESPM 20-52-20

NOTE: The Functional test and/or operational test requested by

this ESPM procedure is given hereafter.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 302

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

b Do the Operational Test of the Annunciator Light Test AMM (Refer to

AMM 33-14-00, Page Block 501)

c Do the Operational Test of the General Illumination, (Refer to AMM

33-12-00, Page Block 501)

d Do the Operational Test of the Instrument and Panel Integral Lighting,

(Refer to AMM 33-13-00, Page Block 501)

e Make certain that the ventillation system operates correctly, (Refer to

AMM 21-21-00, Page Block 501)

f Do the AFS (Automatic Flight System) Test, (Refer to AMM 22-40-00,

Page Block 501)(para 1.A))

g Do the Operational Test of ECAM/EFIS Display Test, (Refer to AMM

31-51-00, Page Block 501)

h Do the Operational Test of the FWC1 and FWC2, (Refer to AMM

31-51-00, Page Block 501)

(b) Procedure

1 Do a check of the Electrical Bonding (Refer to AMM 20-28-11, Page Block

001)

NOTE: For maximun permissible resistance values: Refer to the Table

(Refer to AMM 20-28-11, Page Block 001)

2 Do the Perform BITE test (Refer to AMM 36-11-00, Page Block 501)

(Operational Test)

3 Do the test procedure as specified after the installation of the FLIGHT

MANAGEMENT COMPUTER (1CK1, 1CK2) (Refer to AMM 34-68-34, Page

Block 401)

4 Do the Functional Test - ENGINE FIRE CONTROL MODULE (Refer to AMM

26-12-20, Page Block 501)

5 Do the test procedure as specified after the installation of the TCAS

COMPUTER (9005SG) (Refer to AMM 34-44-34, Page Block 401) (if

equipped)

6 Do the Operational Test TAXI AND TAKEOFF LIGHTS (Refer to AMM

33-46-00, Page Block 501)

7 Do the test procedure as specified after the installation of the FLIGHT

WARNING COMPUTER (1WW1, 1WW2) (Refer to AMM 31-53-34, Page

Block 401)

8 Carry out operational test of the flight compartment and electronics racks air

distribution system (Refer to AMM 21-21-00, Page Block 501)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 303

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

9 Do the test procedure as specified after the installation of the SYSTEM DATA

ANALOG CONVERTER (1WV) (Refer to AMM 31-55-22, Page Block 401)

10 Do the Thrust Reverser Functional and Indicating/Warning Sensors Test

(Refer to AMM 78-31-00, Page Block 501)

11 Do the test procedure for engine 1 as specified after the installation of the

LOW PRESSURE FUEL FIRE SHUT OFF VALVE (Refer to AMM 28-24-31,

Page Block 401)

12 Do the test procedure for engine 2 as specified after the installation of the

LOW PRESSURE FUEL FIRE SHUT OFF VALVE (Refer to AMM 28-24-31,

Page Block 401)

**CONF 008

(1) Subtask 742003-720-002-001 - Functional

Manpower Resources

Skills ELECTRICAL

References

Aircraft Maintenance Manual (AMM) 20-28-11, Page Block 001

21-21-00, Page Block 501

22-40-00, Page Block 501

24-31-00, Page Block 301

24-31-11, Page Block 401

26-12-20, Page Block 501

28-24-31, Page Block 401

31-51-00, Page Block 501

31-53-34, Page Block 401

31-55-22, Page Block 401

33-12-00, Page Block 501

33-13-00, Page Block 501

33-14-00, Page Block 501

33-46-00, Page Block 501

34-44-34, Page Block 401

34-68-34, Page Block 401

36-11-00, Page Block 501

78-31-00, Page Block 501

Elec. Std. Practices Manual (ESPM) 20-52-20

(a) Job Set-up

1 Battery re-connection

- For Job Set-up, refer to Installation of the Batteries (Refer to AMM

24-31-11, Page Block 401)

- Remove the blanking cap from the electrical connectors

- Make sure that the electrical connectors are clean and in correct condition

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 304

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

- Connect the connector on the battery

- Turn the knurled nut a quarter turn

2 Remove all warning notices

3 Energize the aircraft electrical circuits (Refer to AMM 24-31-00, Page Block

301)

4 Preliminary Tests :

NOTE: If the aircraft is operated in CAT3 conditions, you must also do

the LAND test (Refer to AMM 22-40-00, Page Block 501)

a On each connector which was disconnected:

- Do the checks as defined by ESPM 20-52-20

NOTE: The Functional test and/or operational test requested by

this ESPM procedure is given hereafter.

b Do the Operational Test of the Annunciator Light Test AMM (Refer to

AMM 33-14-00, Page Block 501)

c Do the Operational Test of the General Illumination, (Refer to AMM

33-12-00, Page Block 501)

d Do the Operational Test of the Instrument and Panel Integral Lighting,

(Refer to AMM 33-13-00, Page Block 501)

e Make certain that the ventillation system operates correctly, (Refer to

AMM 21-21-00, Page Block 501)

f Do the AFS (Automatic Flight System) Test, (Refer to AMM 22-40-00,

Page Block 501)(para 1.A))

g Do the Operational Test of ECAM/EFIS Display Test, (Refer to AMM

31-51-00, Page Block 501)

h Do the Operational Test of the FWC1 and FWC2, (Refer to AMM

31-51-00, Page Block 501)

(b) Procedure

1 Do a check of the Electrical Bonding (Refer to AMM 20-28-11, Page Block

001)

NOTE: For maximun permissible resistance values: Refer to the Table

(Refer to AMM 20-28-11, Page Block 001)

2 Do the Perform BITE test (Refer to AMM 36-11-00, Page Block 501)

(Operational Test)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 305

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

3 Do the test procedure as specified after the installation of the FLIGHT

MANAGEMENT COMPUTER (1CK1, 1CK2) (Refer to AMM 34-68-34, Page

Block 401)

4 Do the Functional Test - ENGINE FIRE CONTROL MODULE (Refer to AMM

26-12-20, Page Block 501)

5 Do the test procedure as specified after the installation of the TCAS

COMPUTER (9005SG) (Refer to AMM 34-44-34, Page Block 401) (if

equipped)

6 Do the Operational Test TAXI AND TAKEOFF LIGHTS (Refer to AMM

33-46-00, Page Block 501)

7 Do the test procedure as specified after the installation of the FLIGHT

WARNING COMPUTER (1WW1, 1WW2) (Refer to AMM 31-53-34, Page

Block 401)

8 Carry out operational test of the flight compartment and electronics racks air

distribution system (Refer to AMM 21-21-00, Page Block 501)

9 Do the test procedure as specified after the installation of the SYSTEM DATA

ANALOG CONVERTER (1WV) (Refer to AMM 31-55-22, Page Block 401)

10 Do the Thrust Reverser Functional and Indicating/Warning Sensors Test

(Refer to AMM 78-31-00, Page Block 501)

11 Do the test procedure for engine 1 as specified after the installation of the

LOW PRESSURE FUEL FIRE SHUT OFF VALVE (Refer to AMM 28-24-31,

Page Block 401)

12 Do the test procedure for engine 2 as specified after the installation of the

LOW PRESSURE FUEL FIRE SHUT OFF VALVE (Refer to AMM 28-24-31,

Page Block 401)

**CONF 009

(1) Subtask 742003-720-002-001 - Functional

Manpower Resources

Skills ELECTRICAL

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 306

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 20-28-11, Page Block 001

21-21-00, Page Block 501

22-40-00, Page Block 501

24-31-00, Page Block 301

24-31-11, Page Block 401

26-12-20, Page Block 501

28-24-31, Page Block 401

31-51-00, Page Block 501

31-53-34, Page Block 401

31-55-22, Page Block 401

33-12-00, Page Block 501

33-13-00, Page Block 501

33-14-00, Page Block 501

33-46-00, Page Block 501

34-44-34, Page Block 401

34-68-34, Page Block 401

36-11-00, Page Block 501

78-31-00, Page Block 501

Elec. Std. Practices Manual (ESPM) 20-52-20

(a) Job Set-up

1 Battery re-connection

- For Job Set-up, refer to Installation of the Batteries (Refer to AMM

24-31-11, Page Block 401)

- Remove the blanking cap from the electrical connectors

- Make sure that the electrical connectors are clean and in correct condition

- Connect the connector on the battery

- Turn the knurled nut a quarter turn

2 Remove all warning notices

3 Energize the aircraft electrical circuits (Refer to AMM 24-31-00, Page Block

301)

4 Preliminary Tests :

NOTE: If the aircraft is operated in CAT3 conditions, you must also do

the LAND test (Refer to AMM 22-40-00, Page Block 501)

a On each connector which was disconnected:

- Do the checks as defined by ESPM 20-52-20

NOTE: The Functional test and/or operational test requested by

this ESPM procedure is given hereafter.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 307

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

b Do the Operational Test of the Annunciator Light Test AMM (Refer to

AMM 33-14-00, Page Block 501)

c Do the Operational Test of the General Illumination, (Refer to AMM

33-12-00, Page Block 501)

d Do the Operational Test of the Instrument and Panel Integral Lighting,

(Refer to AMM 33-13-00, Page Block 501)

e Make certain that the ventillation system operates correctly, (Refer to

AMM 21-21-00, Page Block 501)

f Do the AFS (Automatic Flight System) Test, (Refer to AMM 22-40-00,

Page Block 501)(para 1.A))

g Do the Operational Test of ECAM/EFIS Display Test, (Refer to AMM

31-51-00, Page Block 501)

h Do the Operational Test of the FWC1 and FWC2, (Refer to AMM

31-51-00, Page Block 501)

(b) Procedure

1 Do a check of the Electrical Bonding (Refer to AMM 20-28-11, Page Block

001)

NOTE: For maximun permissible resistance values: Refer to the Table

(Refer to AMM 20-28-11, Page Block 001)

2 Do the Perform BITE test (Refer to AMM 36-11-00, Page Block 501)

(Operational Test)

3 Do the test procedure as specified after the installation of the FLIGHT

MANAGEMENT COMPUTER (1CK1, 1CK2) (Refer to AMM 34-68-34, Page

Block 401)

4 Do the Functional Test - ENGINE FIRE CONTROL MODULE (Refer to AMM

26-12-20, Page Block 501)

5 Do the test procedure as specified after the installation of the TCAS

COMPUTER (9005SG) (Refer to AMM 34-44-34, Page Block 401) (if

equipped)

6 Do the Operational Test TAXI AND TAKEOFF LIGHTS (Refer to AMM

33-46-00, Page Block 501)

7 Do the test procedure as specified after the installation of the FLIGHT

WARNING COMPUTER (1WW1, 1WW2) (Refer to AMM 31-53-34, Page

Block 401)

8 Carry out operational test of the flight compartment and electronics racks air

distribution system (Refer to AMM 21-21-00, Page Block 501)

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 308

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

9 Do the test procedure as specified after the installation of the SYSTEM DATA

ANALOG CONVERTER (1WV) (Refer to AMM 31-55-22, Page Block 401)

10 Do the Thrust Reverser Functional and Indicating/Warning Sensors Test

(Refer to AMM 78-31-00, Page Block 501)

11 Do the test procedure for engine 1 as specified after the installation of the

LOW PRESSURE FUEL FIRE SHUT OFF VALVE (Refer to AMM 28-24-31,

Page Block 401)

12 Do the test procedure for engine 2 as specified after the installation of the

LOW PRESSURE FUEL FIRE SHUT OFF VALVE (Refer to AMM 28-24-31,

Page Block 401)

**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 742003-942-003-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 52-10-00

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Close the access doors (Refer to AMM 52-10-00)

(c) Restore system and aircraft to normal operating system.

(d) Remove access platforms.

**CONF 002

(1) Subtask 742003-942-003-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 52-10-00

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Close the access doors (Refer to AMM 52-10-00)

(c) Restore system and aircraft to normal operating system.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 309

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(d) Remove access platforms.

**CONF 003

(1) Subtask 742003-942-003-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 52-10-00

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Close the access doors (Refer to AMM 52-10-00)

(c) Restore system and aircraft to normal operating system.

(d) Remove access platforms.

**CONF 006

(1) Subtask 742003-942-003-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 52-10-00

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Close the access doors (Refer to AMM 52-10-00)

(c) Restore system and aircraft to normal operating system.

(d) Remove access platforms.

**CONF 007

(1) Subtask 742003-942-003-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 52-10-00

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 310

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

(b) Close the access doors (Refer to AMM 52-10-00)

(c) Restore system and aircraft to normal operating system.

(d) Remove access platforms.

**CONF 008

(1) Subtask 742003-942-003-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 52-10-00

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Close the access doors (Refer to AMM 52-10-00)

(c) Restore system and aircraft to normal operating system.

(d) Remove access platforms.

**CONF 009

(1) Subtask 742003-942-003-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 52-10-00

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Close the access doors (Refer to AMM 52-10-00)

(c) Restore system and aircraft to normal operating system.

(d) Remove access platforms.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 311

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

CIRCUIT BREAKER PANEL

Q

R

S

T

U

V

51

5253

54

55

56

5758

59

60

61

6263

64

65

66

6768

69

70

71

7273

74

75

76

7778

79

80

81

8283

84

85

FR20

FR1

FR10

FR13

AFTER

133VU

B

120VU

133VU A

B

A

133VU

B_SB_742003_5_BBAB_01_01

8

13JH

14JH

Figure A-FBBAB - Sheet 01

Modification equipment in 133VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 312

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

FR20

FR1

FR10

FR13

120VU

133VU A

A

B

B_SB_742003_5_BCAB_01_02

AFTER

67 68 69 70 71 72 73 74 75 76 77 78 79

S AUTO

RELIGHT

AUTO

RELIGHT

B

NEW LABEL

Figure A-FBCAB - Sheet 01

Modification Placard in 133VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 313

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

20VU

A

429VU

A

AFTER

1347VT

1472VC

1470VC

1471VC

1

(1)

3

REAR VIEW

B

6

7

4

5

4

5

4

5

B

B_SB_742003_5_BDAA_01_01

(2)

2

Figure A-FBDAA - Sheet 01

Modification equipment in 429VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 314

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 001

105VU

FR1

FR20

A

AFTER

28KC

29KC

9

17JH

18JH

15JH

16JH

10

11

12

10

11

12

VIEW LOOKING FWD

B

B

A

B_SB_742003_5_BAAA_01_02

Figure A-FBAAA - Sheet 01

Modification equipment in 105VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 315

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 002, 007 thru 008

105VU

FR1

FR20

A

AFTER

9

133QA

18JH

17JH

10

11

12

10

11

12

15JH

16JH

10

11

12

10

11

12

VIEW LOOKING FWD B_SB_742003_5_BAAC_01_01

B

A

B

Figure A-FBAAC - Sheet 01

Modification equipment in 105VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 316

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 003

105VU

FR1

FR20

A

9 AFTER

133QA

18JH

17JH

10

11

12

10

11

12

15JH

16JH

10

11

12

10

11

12

VIEW LOOKING FWD B_SB_742003_5_BAAD_01_01

B

A

B

Figure A-FBAAD - Sheet 01

Modification equipment in 105VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 317

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 006, 009

105VU

FR1

FR20

A

AFTER

9

133QA

18JH

17JH

10

11

12

10

11

12

VIEW LOOKING FWD

B

A

B

31KC

30KC

15JH

16JH

37KC

10

11

12

10

11

12

B_SB_742003_5_BAAF_01_01

Figure A-FBAAF - Sheet 01

Modification equipment in 105VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 318

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

20VU

429VU

105VU 104VU

133VU

80VU FR1

FR20

1M

1M

1M 2M

2M

2M

B_SB_742003_5_BEAA_01_00

Figure A-FBEAA - Sheet 01

Routing

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 319

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

Figure A-FCAAA - Sheet 01

Modification wiring in 133VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 320

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

Figure A-FCAAA - Sheet 02

Modification wiring in 133VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 321

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

Figure A-FCAAA - Sheet 03

Modification wiring in 133VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 322

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

Figure A-FCAAA - Sheet 04

Modification wiring in 133VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 323

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 001 thru 003, 006 thru 007

Figure A-FCBAA - Sheet 01

Modification wiring in 105VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 324

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 001 thru 003, 006 thru 007

Figure A-FCBAA - Sheet 02

Modification wiring in 105VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 325

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 001 thru 003, 006 thru 007

Figure A-FCBAA - Sheet 03

Modification wiring in 105VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 326

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 001 thru 003, 006 thru 007

Figure A-FCBAA - Sheet 04

Modification wiring in 105VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 327

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 008 thru 009

Figure A-FCBAB - Sheet 01

Modification wiring in 105VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 328

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 008 thru 009

Figure A-FCBAB - Sheet 02

Modification wiring in 105VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 329

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 008 thru 009

Figure A-FCBAB - Sheet 03

Modification wiring in 105VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 330

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 008 thru 009

Figure A-FCBAB - Sheet 04

Modification wiring in 105VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 331

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

Figure A-FCCAA - Sheet 01

Modification wiring in 429VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 332

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

Figure A-FCCAA - Sheet 02

Modification wiring in 429VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 333

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 001 thru 003, 006, 008 thru 009

Figure A-FCDAA - Sheet 01

Modification wiring in 104VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 334

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 007

Figure A-FCDAB - Sheet 01

Modification wiring in 104VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 335

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 001 thru 003, 006, 008 thru 009

Figure A-FCEAA - Sheet 01

Modification wiring in 80VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 336

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 001 thru 003, 006, 008 thru 009

Figure A-FCFAA - Sheet 01

Modification wiring in Zones

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 337

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 001 thru 003, 006, 008 thru 009

Figure A-FCFAA - Sheet 02

Modification wiring in Zones

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 338

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 007

Figure A-FCFAB - Sheet 01

Modification wiring in Zones

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 339

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 007

Figure A-FCFAB - Sheet 02

Modification wiring in Zones

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 340

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

END1 LEAD END2

Instructions Zone or

Panel Elec.Ident. Term Terminal P/N

Wire

Ident. Co Rte Gauge

Lenght

mm Inch

Zone or

Panel Elec.Ident. Term Terminal P/N

L

i

n

e

 1 133VU 1EV 3 3169−1386 CF24 133VU 2KC 3 D

 2 133VU 1EV 3 3169−1387 CF24 133VU 54CP 3 D

 3 133VU 1EV 4 3169−1400 CF24 133VU 54CP 4 D

 4 133VU 1EV 4 3169−1401 CF24 133VU 2KC 4 D

 5 133VU 2KC 1 2459−1083 CF10 133VU 17XE 1 D

 6 133VU 1ES 1 2459−1050 CF10 133VU 1KC 1 D

 7

 8

 9

10 133VU 13JH 1 NSA936501TA1003 2459−1050 CF10 2000 80 133VU 1ES 1 NSA936501TA1003 (a) A

11 133VU 13JH 1 NSA936501TA1003 2459−1525 CF10 2000 80 133VU 1KC 1 NSA936501TA1003 (a) A

12 133VU 13JH 3 EN3155−016M2018 3169−1387 CF24 2000 80 133VU 1EV 3 EN3155−016M2018 (a) A

13 133VU 13JH 4 EN3155−016M2018 3169−1400 CF24 2000 80 133VU 1EV 4 EN3155−016M2018 (a) A

14 133VU 13JH 4 EN3155−016M2018 3169−1923 CF24 2000 80 133VU 54CP 4 EN3155−016M2018 (a) A

15 133VU 13JH 3 EN3155−016M2018 3169−1925 CF24 2000 80 133VU 54CP 3 EN3155−016M2018 (a) A

16 133VU 14JH 1 NSA936501TA1003 2459−1083 CF10 2000 80 133VU 17XE 1 NSA936501TA1003 (a) A

17 133VU 14JH 1 NSA936501TA1003 2459−1526 CF10 2000 80 133VU 2KC 1 NSA936501TA1003 (a) A

18 133VU 14JH 3 EN3155−016M2018 3169−1386 CF24 2000 80 133VU 2KC 3 EN3155−016M2018 (a) A

19 133VU 14JH 4 EN3155−016M2018 3169−1401 CF24 2000 80 133VU 2KC 4 EN3155−016M2018 (a) A

20 133VU 14JH 4 EN3155−016M2018 3169−1924 CF24 2000 80 133VU 1EV 4 EN3155−016M2018 (a) A

21 133VU 14JH 3 EN3155−016M2018 3169−1926 CF24 2000 80 133VU 1EV 3 EN3155−016M2018 (a) A

22

23

24

25

 (a) = BUNDLE A9000095320695

 A = ADDED WIRE

 D = DELETED WIRE

Figure A-FDAAA - Sheet 01

Hook-up Chart 133VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 341

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 001 thru 003, 006 thru 007

END1 LEAD END2

Instructions Zone or

Panel Elec.Ident. Term Terminal P/N

Wire

Ident. Co Rte Gauge

Lenght

mm Inch

Zone or

Panel Elec.Ident. Term Terminal P/N

L

i

n

e

 1 105VU 192VT 10C 7431−0025 CF20 105VU 534VC P D

 2 105VU 192VT 10K 7431−0028 CF20 105VU 365VC −D D

 3 105VU 192VT 10E 7431−0029 CF20 105VU 5KG−A 2 D

 4 105VU 192VT 10H 7431−0030 CF20 105VU 5KG−A 4 D

 5 105VU 192VT 10D 7431−0031 CF20 105VU 432VC −Y D

 6 105VU 192VT 10J 7431−0032 CF20 105VU 431VC −Z D

 7 105VU 192VT 11C 7431−0057 CF20 105VU 534VC S D

 8 105VU 192VT 11K 7431−0060 CF20 105VU 365VC −F D

 9 105VU 192VT 11D 7431−0061 CF20 105VU 432VC BB D

10 105VU 192VT 11J 7431−0062 CF20 105VU 431VC AA D

11 105VU 192VT 11E 7431−0067 CF20 105VU 4KG−A 2 D

12 105VU 192VT 11H 7431−0068 CF20 105VU 4KG−A 4 D

13 105VU 2KG−A Z 8011−0106 CF24 105VU 428VC BB D

14 105VU 3KG−A Z 8011−0029 CF24 105VU 391VC −V D

15

16

17

18

19

20

21

22

23

24

25

 D = DELETED WIRE

Figure A-FDBAA - Sheet 01

Hook-up Chart 105VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 342

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 001 thru 003, 006 thru 007

END1 LEAD END2

Instructions Zone or

Panel Elec.Ident. Term Terminal P/N

Wire

Ident. Co Rte Gauge

Lenght

mm Inch

Zone or

Panel Elec.Ident. Term Terminal P/N

L

i

n

e

 1 105VU 192VT 17B EN3155−016M2018 7431−0025 CF20 3000 120 105VU 534VC P EN3155−018M2018 (a) A

 2 105VU 192VT 17K EN3155−016M2018 7431−0028 CF20 3000 120 105VU 365VC −D EN3155−018M2018 (a) A

 3 105VU 192VT 17D EN3155−016M2018 7431−0029 CF20 3000 120 105VU 5KG−A 2 E0078S16RA (a) A

 4 105VU 192VT 17G EN3155−016M2018 7431−0030 CF20 3000 120 105VU 5KG−A 4 E0078S16RA (a) A

 5 105VU 192VT 17C EN3155−016M2018 7431−0031 CF20 3000 120 105VU 432VC −Y EN3155−018M2018 (a) A

 6 105VU 192VT 17H EN3155−016M2018 7431−0032 CF20 3000 120 105VU 431VC −Z EN3155−018M2018 (a) A

 7 105VU 192VT 18B EN3155−016M2018 7431−0057 CF20 3000 120 105VU 534VC S EN3155−018M2018 (a) A

 8 105VU 192VT 18K EN3155−016M2018 7431−0060 CF20 3000 120 105VU 365VC −F EN3155−018M2018 (a) A

 9 105VU 192VT 18C EN3155−016M2018 7431−0061 CF20 3000 120 105VU 432VC BB EN3155−018M2018 (a) A

10 105VU 192VT 18H EN3155−016M2018 7431−0062 CF20 3000 120 105VU 431VC AA EN3155−018M2018 (a) A

11 105VU 192VT 18D EN3155−016M2018 7431−0067 CF20 3000 120 105VU 4KG−A 2 E0078S16RA (a) A

12 105VU 192VT 18G EN3155−016M2018 7431−0068 CF20 3000 120 105VU 4KG−A 4 E0078S16RA (a) A

13 105VU 192VT 7A EN3155−016M2018 7431−0161 CF20 3000 120 105VU 15JH−A Z E0078S16RA (a) A

14 105VU 192VT 17F EN3155−016M2018 7431−0164 CF20 3000 120 105VU 15JH−A 1 E0078S16RA (a) A

15 105VU 192VT 17A EN3155−016M2018 7431−0165 CF20 3000 120 105VU 15JH−A 4 EN3155−016M2018 (a) A

16 105VU 192VT 10C EN3155−016M2018 7431−0166 CF20 3000 120 105VU 15JH−A X E0078S16RA (a) A

17 105VU 192VT 10K EN3155−016M2018 7431−0167 CF20 3000 120 105VU 365VC −J EN3155−018M2018 (a) A

18 105VU 192VT 10D EN3155−016M2018 7431−0168 CF20 3000 120 105VU 17JH−A 2 E0252DK2002 (a) A

19 105VU 192VT 10E EN3155−016M2018 7431−0169 CF20 3000 120 105VU 17JH−A X E0252DK2002 (a) A

20 105VU 192VT 18F EN3155−016M2018 7431−0186 CF20 3000 120 105VU 16JH−A 1 E0078S16RA (a) A

21 105VU 192VT 18A EN3155−016M2018 7431−0187 CF20 3000 120 105VU 16JH−A 4 E0078S16RA (a) A

22 105VU 192VT 11C EN3155−016M2018 7431−0188 CF20 3000 120 105VU 16JH−A X E0078S16RA (a) A

23 105VU 192VT 11K EN3155−016M2018 7431−0189 CF20 3000 120 105VU 534VC E EN3155−018M2018 (a) A

24 105VU 192VT 11D EN3155−016M2018 7431−0190 CF20 3000 120 105VU 18JH−A 2 E0252DK2002 (a) A

25 105VU 192VT 11E EN3155−016M2018 7431−0191 CF20 3000 120 105VU 18JH−A X E0252DK2002 (a) A

 (a) = BUNDLE A9000095320695

 A = ADDED WIRE

Figure A-FDBAA - Sheet 02

Hook-up Chart 105VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 343

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 001 thru 003, 006 thru 007

END1 LEAD END2

Instructions Zone or

Panel Elec.Ident. Term Terminal P/N

Wire

Ident. Co Rte Gauge

Lenght

mm Inch

Zone or

Panel Elec.Ident. Term Terminal P/N

L

i

n

e

 1 105VU 15JH−A B E0078S16RA 7431−0159 CF20 3000 120 105VU 365VC J EN3155−018M2018 (a) A

 2 105VU 15JH−A A E0078S16RA 7431−0160 CF20 3000 120 105VU 534VC −E EN3155−018M2018 (a) A

 3 105VU 15JH−A 5 E0078S16RA 7431−0162 CF20 3000 120 105VU 17JH−A A E0252DK2002 (a) A

 4 105VU 16JH−A B E0078S16RA 7431−0181 CF20 3000 120 105VU 365VC FF EN3155−018M2018 (a) A

 5 105VU 16JH−A A E0078S16RA 7431−0182 CF20 3000 120 105VU 534VC B EN3155−018M2018 (a) A

 6 105VU 16JH−A Z E0078S16RA 7431−0183 CF20 3000 120 105VU 194VT 13D EN3155−016M2018 (a) A

 7 105VU 16JH−A 5 E0078S16RA 7431−0184 CF20 3000 120 105VU 18JH−A A E0252DK2002 (a) A

 8 105VU 193VT 7H EN3155−016M2018 7431−0163 CF20 3000 120 105VU 17JH−A Z E0252DK2002 (a) A

 9 105VU 193VT 1E EN3155−016M2018 7431−0185 CF20 3000 120 105VU 18JH−A Z E0252DK2002 (a) A

10 105VU 193VT 7J EN3155−016M2018 8011−0029 CF24 3000 120 105VU 391VC −V EN3155−018M2018 (a) A

11 105VU 193VT 1C EN3155−016M2018 8011−0106 CF24 3000 120 105VU 428VC BB EN3155−018M2018 (a) A

12 105VU 193VT 1D EN3155−016M2018 8011−0175 CF24 3000 120 105VU 2KG−A Z E0252DK2002 (a) A

13 105VU 193VT 7K EN3155−016M2018 8011−0176 CF24 3000 120 105VU 3KG−A Z E0252DK2002 (a) A

14

15

16

17

18

19

20

21

22

23

24

25

 (a) = BUNDLE A9000095320695

 A = ADDED WIRE

Figure A-FDBAA - Sheet 03

Hook-up Chart 105VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 344

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 008 thru 009

END1 LEAD END2

Instructions Zone or

Panel Elec.Ident. Term Terminal P/N

Wire

Ident. Co Rte Gauge

Lenght

mm Inch

Zone or

Panel Elec.Ident. Term Terminal P/N

L

i

n

e

 1 105VU 192VT 10C 7431−0025 CF20 105VU 534VC P D

 2 105VU 192VT 10K 7431−0028 CF20 105VU 365VC −D D

 3 105VU 192VT 10E 7431−0029 CF20 105VU 5KG−A 2 D

 4 105VU 192VT 10H 7431−0030 CF20 105VU 5KG−A 4 D

 5 105VU 192VT 10D 7431−0031 CF20 105VU 432VC −Y D

 6 105VU 192VT 10J 7431−0032 CF20 105VU 431VC −Z D

 7 105VU 192VT 11C 7431−0057 CF20 105VU 534VC S D

 8 105VU 192VT 11K 7431−0060 CF20 105VU 365VC −F D

 9 105VU 192VT 11D 7431−0061 CF20 105VU 432VC BB D

10 105VU 192VT 11J 7431−0062 CF20 105VU 431VC AA D

11 105VU 192VT 11E 7431−0067 CF20 105VU 4KG−A 2 D

12 105VU 192VT 11H 7431−0068 CF20 105VU 4KG−A 4 D

13 105VU 2KG−A Z 8011−0106 CF24 105VU 428VC BB D

14 105VU 3KG−A Z 8011−0029 CF24 105VU 391VC −V D

15

16

17

18

19

20

21

22

23

24

25

 D = DELETED WIRE

Figure A-FDBAB - Sheet 01

Hook-up Chart 105VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 345

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 008 thru 009

END1 LEAD END2

Instructions Zone or

Panel Elec.Ident. Term Terminal P/N

Wire

Ident. Co Rte Gauge

Lenght

mm Inch

Zone or

Panel Elec.Ident. Term Terminal P/N

L

i

n

e

 1 105VU 192VT 17B EN3155−016M2018 7431−0025 CF20 3000 120 105VU 534VC P EN3155−018M2018 (a) A

 2 105VU 192VT 17K EN3155−016M2018 7431−0028 CF20 3000 120 105VU 365VC −D EN3155−018M2018 (a) A

 3 105VU 192VT 17D EN3155−016M2018 7431−0029 CF20 3000 120 105VU 5KG−A 2 E0078S16RA (a) A

 4 105VU 192VT 17G EN3155−016M2018 7431−0030 CF20 3000 120 105VU 5KG−A 4 E0078S16RA (a) A

 5 105VU 192VT 17C EN3155−016M2018 7431−0031 CF20 3000 120 105VU 432VC −Y EN3155−018M2018 (a) A

 6 105VU 192VT 17H EN3155−016M2018 7431−0032 CF20 3000 120 105VU 431VC −Z EN3155−018M2018 (a) A

 7 105VU 192VT 18B EN3155−016M2018 7431−0057 CF20 3000 120 105VU 534VC S EN3155−018M2018 (a) A

 8 105VU 192VT 18K EN3155−016M2018 7431−0060 CF20 3000 120 105VU 365VC −F EN3155−018M2018 (a) A

 9 105VU 192VT 18C EN3155−016M2018 7431−0061 CF20 3000 120 105VU 432VC BB EN3155−018M2018 (a) A

10 105VU 192VT 18H EN3155−016M2018 7431−0062 CF20 3000 120 105VU 431VC AA EN3155−018M2018 (a) A

11 105VU 192VT 18D EN3155−016M2018 7431−0067 CF20 3000 120 105VU 4KG−A 2 E0078S16RA (a) A

12 105VU 192VT 18G EN3155−016M2018 7431−0068 CF20 3000 120 105VU 4KG−A 4 E0078S16RA (a) A

13 105VU 192VT 7A EN3155−016M2018 7431−0161 CF20 3000 120 105VU 15JH−A Z E0078S16RA (a) A

14 105VU 192VT 17F EN3155−016M2018 7431−0164 CF20 3000 120 105VU 15JH−A 1 E0078S16RA (a) A

15 105VU 192VT 17A EN3155−016M2018 7431−0165 CF20 3000 120 105VU 15JH−A 4 EN3155−016M2018 (a) A

16 105VU 192VT 10C EN3155−016M2018 7431−0166 CF20 3000 120 105VU 15JH−A X E0078S16RA (a) A

17 105VU 192VT 10K EN3155−016M2018 7431−0167 CF20 3000 120 105VU 365VC −J EN3155−018M2018 (a) A

18 105VU 192VT 10D EN3155−016M2018 7431−0168 CF20 3000 120 105VU 17JH−A 2 E0252DK2002 (a) A

19 105VU 192VT 10E EN3155−016M2018 7431−0169 CF20 3000 120 105VU 17JH−A X E0252DK2002 (a) A

20 105VU 192VT 18F EN3155−016M2018 7431−0186 CF20 3000 120 105VU 16JH−A 1 E0078S16RA (a) A

21 105VU 192VT 18A EN3155−016M2018 7431−0187 CF20 3000 120 105VU 16JH−A 4 E0078S16RA (a) A

22 105VU 192VT 11C EN3155−016M2018 7431−0188 CF20 3000 120 105VU 16JH−A X E0078S16RA (a) A

23 105VU 192VT 11K EN3155−016M2018 7431−0189 CF20 3000 120 105VU 534VC E EN3155−018M2018 (a) A

24 105VU 192VT 11D EN3155−016M2018 7431−0190 CF20 3000 120 105VU 18JH−A 2 E0252DK2002 (a) A

25 105VU 192VT 11E EN3155−016M2018 7431−0191 CF20 3000 120 105VU 18JH−A X E0252DK2002 (a) A

 (a) = BUNDLE A9000095320695

 A = ADDED WIRE

Figure A-FDBAB - Sheet 02

Hook-up Chart 105VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 346

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 008 thru 009

END1 LEAD END2

Instructions Zone or

Panel Elec.Ident. Term Terminal P/N

Wire

Ident. Co Rte Gauge

Lenght

mm Inch

Zone or

Panel Elec.Ident. Term Terminal P/N

L

i

n

e

 1 105VU 15JH−A B E0078S16RA 7431−0159 CF20 3000 120 105VU 365VC J EN3155−018M2018 (a) A

 2 105VU 15JH−A A E0078S16RA 7431−0160 CF20 3000 120 105VU 534VC −E EN3155−018M2018 (a) A

 3 105VU 15JH−A 5 E0078S16RA 7431−0162 CF20 3000 120 105VU 17JH−A A E0252DK2002 (a) A

 4 105VU 16JH−A B E0078S16RA 7431−0181 CF20 3000 120 105VU 365VC FF EN3155−018M2018 (a) A

 5 105VU 16JH−A A E0078S16RA 7431−0182 CF20 3000 120 105VU 534VC B EN3155−018M2018 (a) A

 6 105VU 16JH−A Z E0078S16RA 7431−0183 CF20 3000 120 105VU 194VT 13E EN3155−016M2018 (a) A

 7 105VU 16JH−A 5 E0078S16RA 7431−0184 CF20 3000 120 105VU 18JH−A A E0252DK2002 (a) A

 8 105VU 193VT 7H EN3155−016M2018 7431−0163 CF20 3000 120 105VU 17JH−A Z E0252DK2002 (a) A

 9 105VU 193VT 1E EN3155−016M2018 7431−0185 CF20 3000 120 105VU 18JH−A Z E0252DK2002 (a) A

10 105VU 193VT 7J EN3155−016M2018 8011−0029 CF24 3000 120 105VU 391VC −V EN3155−018M2018 (a) A

11 105VU 193VT 1C EN3155−016M2018 8011−0106 CF24 3000 120 105VU 428VC BB EN3155−018M2018 (a) A

12 105VU 193VT 1D EN3155−016M2018 8011−0175 CF24 3000 120 105VU 2KG−A Z E0252DK2002 (a) A

13 105VU 193VT 7K EN3155−016M2018 8011−0176 CF24 3000 120 105VU 3KG−A Z E0252DK2002 (a) A

14

15

16

17

18

19

20

21

22

23

24

25

 (a) = BUNDLE A9000095320695

 A = ADDED WIRE

Figure A-FDBAB - Sheet 03

Hook-up Chart 105VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 347

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

END1 LEAD END2

Instructions Zone or

Panel Elec.Ident. Term Terminal P/N

Wire

Ident. Co Rte Gauge

Lenght

mm Inch

Zone or

Panel Elec.Ident. Term Terminal P/N

L

i

n

e

 1 429VU 3JH−1 AD 7431−0003 BF20 429VU 1470VC W D

 2 429VU 3JH−1 AA 7431−0042 BF20 429VU 1470VC T D

 3 429VU 3JH−2 BD 7431−0005 BF20 429VU 1471VC V D

 4 429VU 3JH−2 BA 7431−0041 BF20 429VU 1471VC Z D

 5

 6

 7

 8 429VU 1347VT 9B EN3155−016M2018 7431−0003 BF20 2000 80 429VU 1470VC W EN3155−018M2018 (a) A

 9 429VU 1347VT 9J EN3155−016M2018 7431−0005 BF20 2000 80 429VU 1471VC V EN3155−018M2018 (a) A

10 429VU 1347VT 2J EN3155−016M2018 7431−0041 BF20 2000 80 429VU 1471VC Z EN3155−018M2018 (a) A

11 429VU 1347VT 9D EN3155−016M2018 7431−0042 BF20 2000 80 429VU 1470VC T EN3155−018M2018 (a) A

12 429VU 1347VT 9H EN3155−016M2018 7431−0149 BF20 2000 80 429VU 3JH−2 BD SOLDERED (a) A

13 429VU 1347VT 9A EN3155−016M2018 7431−0150 BF20 2000 80 429VU 3JH−1 AD SOLDERED (a) A

14 429VU 1347VT 9K EN3155−016M2018 7431−0151 BF20 2000 80 429VU 1471VC AA EN3155−018M2018 (a) A

15 429VU 1347VT 9F EN3155−016M2018 7431−0152 BF20 2000 80 429VU 1470VC −H EN3155−018M2018 (a) A

16 429VU 1347VT 2K EN3155−016M2018 7431−0170 BF20 2000 80 429VU 3JH−2 BA SOLDERED (a) A

17 429VU 1347VT 9C EN3155−016M2018 7431−0171 BF20 2000 80 429VU 3JH−1 AA SOLDERED (a) A

18 429VU 1347VT 2H EN3155−016M2018 7431−0172 BF20 2000 80 429VU 1471VC BB EN3155−018M2018 (a) A

19 429VU 1347VT 9E EN3155−016M2018 7431−0173 BF20 2000 80 429VU 1470VC −P EN3155−018M2018 (a) A

20

21

22

23

24

25

 (a) = BUNDLE A9000095320695

 A = ADDED WIRE

 D = DELETED WIRE

Figure A-FDCAA - Sheet 01

Hook-up Chart 429VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 348

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 001 thru 003, 006, 008 thru 009

END1 LEAD END2

Instructions Zone or

Panel Elec.Ident. Term Terminal P/N

Wire

Ident. Co Rte Gauge

Lenght

mm Inch

Zone or

Panel Elec.Ident. Term Terminal P/N

L

i

n

e

 1 104VU 125GB−A A E0078S16RA 7431−0154 CF20 3000 120 104VU 555VC W EN3155−018M2018 (a) A

 2 104VU 125GB−A 1 E0078S16RA 7431−0155 CF20 3000 120 104VU 555VC V EN3155−018M2018 (a) A

 3

 4

 5

 6

 7

 8

 9

10

11

12

13

14

15

16

17

18

19

20

21

22

23

24

25

 (a) = BUNDLE A9000095320695

 A = ADDED WIRE

Figure A-FDDAA - Sheet 01

Hook-up Chart 104VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 349

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 007

END1 LEAD END2

Instructions Zone or

Panel Elec.Ident. Term Terminal P/N

Wire

Ident. Co Rte Gauge

Lenght

mm Inch

Zone or

Panel Elec.Ident. Term Terminal P/N

L

i

n

e

 1 104VU 125GB−A A E0078S16RA 7431−0154 CF20 3000 120 104VU 555VC W EN3155−018M2018 (a) A

 2 104VU 125GB−A 1 E0078S16RA 7431−0155 CF20 3000 120 104VU 555VC V EN3155−018M2018 (a) A

 3 104VU 188GB−A B E0252DK2002 7431−0176 CF20 5000 200 104VU 554VC C EN3155−018M2018 (a) A

 4 104VU 188GB−A 3 E0252DK2002 7431−0177 CF20 5000 200 104VU 554VC D EN3155−018M2018 (a) A

 5

 6

 7

 8

 9

10

11

12

13

14

15

16

17

18

19

20

21

22

23

24

25

 (a) = BUNDLE A9000095320695

 A = ADDED WIRE

Figure A-FDDAB - Sheet 01

Hook-up Chart 104VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 350

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 001 thru 003, 006, 008 thru 009

END1 LEAD END2

Instructions Zone or

Panel Elec.Ident. Term Terminal P/N

Wire

Ident. Co Rte Gauge

Lenght

mm Inch

Zone or

Panel Elec.Ident. Term Terminal P/N

L

i

n

e

 1 80VU 220GB−A B E0252DK2002 7431−0176 X2M CF20 5000 200 80VU 2315VC −B EN3155−018M2018 (a) A

 2 80VU 220GB−A 3 E0252DK2002 7431−0177 X2M CF20 5000 200 80VU 2315VC −C EN3155−018M2018 (a) A

 3

 4

 5

 6

 7

 8

 9

10

11

12

13

14

15

16

17

18

19

20

21

22

23

24

25

 (a) = BUNDLE A9000095320695

 A = ADDED WIRE

Figure A-FDEAA - Sheet 01

Hook-up Chart 80VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 351

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 001 thru 003, 006, 008 thru 009

END1 LEAD END2

Instructions Zone or

Panel Elec.Ident. Term Terminal P/N

Wire

Ident. Co Rte Gauge

Lenght

mm Inch

Zone or

Panel Elec.Ident. Term Terminal P/N

L

i

n

e

 1 105VU 534VC−A −E EN3155−019F2018 7431−0157 2M CF20 15000 600 429VU 1470VC−A −H EN3155−019F2018 (a) A

 2 105VU 534VC−A B EN3155−019F2018 7431−0179 2M CF20 15000 600 429VU 1470VC−A −P EN3155−019F2018 (a) A

 3 105VU 534VC−A E EN3155−019F2018 7431−0180 2M CF20 20000 800 80VU 2315VC−A −C EN3155−019F2018 (a) A

 4 105VU 365VC−A −J EN3155−019F2018 7431−0158 1M CF20 5000 200 104VU 555VC−A V EN3155−019F2018 (a) A

 5 133VU 13JH 2 NSA936501TA2003 7431−0153 1M CF20 10000 400 104VU 555VC−A W EN3155−019F2018 (a) A

 6 133VU 14JH 2 NSA936501TA2003 7431−0174 2M CF20 10000 400 122 1598VC −G EN3155−019F1616 (a) A

 7 429VU 1471VC−A AA EN3155−019F2018 7431−0156 1M CF20 15000 600 122 365VC−A J EN3155−019F2018 (a) A

 8 429VU 1471VC−A BB EN3155−019F2018 7431−0178 1M CF20 15000 600 122 365VC−A FF EN3155−019F2018 (a) A

 9 80VU 2315VC−A −B EN3155−019F2018 7431−0175 2M CF20 20000 800 122 1598VC−A −G EN3155−018M1616 (a) A

10

11

12

13

14

15

16

17

18

19

20

21

22

23

24

25

 (a) = BUNDLE A9000095320695

 A = ADDED WIRE

Figure A-FDFAA - Sheet 01

Hook-up Chart Zones

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 352

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF 007

END1 LEAD END2

Instructions Zone or

Panel Elec.Ident. Term Terminal P/N

Wire

Ident. Co Rte Gauge

Lenght

mm Inch

Zone or

Panel Elec.Ident. Term Terminal P/N

L

i

n

e

 1 104VU 554VC−A C EN3155−019F2018 7431−0174 1M CF20 10000 400 133VU 14JH 2 NSA936501TA2003 (a) A

 2 104VU 554VC−A D EN3155−019F2018 7431−0180 2M CF20 20000 800 105VU 534VC−A E EN3155−019F2018 (a) A

 3 104VU 555VC−A W EN3155−019F2018 7431−0153 1M CF20 10000 400 133VU 13JH 2 NSA936501TA2003 (a) A

 4 104VU 555VC−A V EN3155−019F2018 7431−0158 1M CF20 5000 200 105VU 365VC−A −J EN3155−019F2018 (a) A

 5 429VU 1470VC−A −H EN3155−019F2018 7431−0157 2M CF20 15000 600 105VU 534VC−A −E EN3155−019F2018 (a) A

 6 429VU 1470VC−A −P EN3155−019F2018 7431−0179 2M CF20 15000 600 105VU 534VC−A B EN3155−019F2018 (a) A

 7 429VU 1471VC−A AA EN3155−019F2018 7431−0156 1M CF20 15000 600 122 365VC−A J EN3155−019F2018 (a) A

 8 429VU 1471VC−A BB EN3155−019F2018 7431−0178 1M CF20 15000 600 122 365VC−A FF EN3155−019F2018 (a) A

 9

10

11

12

13

14

15

16

17

18

19

20

21

22

23

24

25

 (a) = BUNDLE A9000095320695

 A = ADDED WIRE

Figure A-FDFAB - Sheet 01

Hook-up Chart Zones

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 353

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

Figure A-FCGAA - Sheet 01

ADDITIONAL WORK - Modification wiring in 133VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 354

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

Figure A-FCGAA - Sheet 02

ADDITIONAL WORK - Modification wiring in 133VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 355

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

Figure A-FCGAA - Sheet 03

ADDITIONAL WORK - Modification wiring in 133VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 356

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

END1 LEAD END2

Instructions Zone or

Panel Elec.Ident. Term Terminal P/N

Wire

Ident. Co Rte Gauge

Lenght

mm Inch

Zone or

Panel Elec.Ident. Term Terminal P/N

L

i

n

e

 1 133VU 1EV 3 3169−1386 CF24 133VU 2KC 3 D

 2 133VU 1EV 3 3169−1387 CF24 133VU 54CP 3 D

 3 133VU 1EV 4 3169−1400 CF24 133VU 54CP 4 D

 4 133VU 1EV 4 3169−1401 CF24 133VU 2KC 4 D

 5 133VU 13JH 4 3169−1923 CF24 133VU 2CN 4 D

 6 133VU 13JH 4 3169−1924 CF24 133VU 14JH 4 D

 7 133VU 13JH 3 3169−1925 CF24 133VU 2CN 3 D

 8 133VU 13JH 3 3169−1926 CF24 133VU 14JH 3 D

 9 133VU 14JH 3 3169−1334 CF24 133VU 1GW 3 D

10 133VU 14JH 4 3169−1363 CF24 133VU 1GW 4 D

11

12

13

14 133VU 1EV 3 EN3155−016M2018 3169−1387 CF24 2000 80 133VU 13JH 3 EN3155−016M2018 (f) A

15 133VU 1EV 4 EN3155−016M2018 3169−1400 CF24 2000 80 133VU 13JH 4 EN3155−016M2018 (f) A

16 133VU 1EV 4 EN3155−016M2018 3169−1924 CF24 2000 80 133VU 14JH 4 EN3155−016M2018 (f) A

17 133VU 1EV 3 EN3155−016M2018 3169−1926 CF24 2000 80 133VU 14JH 3 EN3155−016M2018 (f) A

18 133VU 13JH 4 EN3155−016M2018 3169−1923 CF24 2000 80 133VU 54CP 4 EN3155−016M2018 (f) A

19 133VU 13JH 3 EN3155−016M2018 3169−1925 CF24 2000 80 133VU 54CP 3 EN3155−016M2018 (f) A

20 133VU 14JH 3 EN3155−016M2018 3169−1386 CF24 2000 80 133VU 2KC 3 EN3155−016M2018 (f) A

21 133VU 14JH 4 EN3155−016M2018 3169−1401 CF24 2000 80 133VU 2KC 4 EN3155−016M2018 (f) A

22 133VU 1GW 3 EN3155−016M2018 3169−1334 CF24 2000 80 133VU 2CN 3 EN3155−016M2018 (f) A

23 133VU 1GW 4 EN3155−016M2018 3169−1363 CF24 2000 80 133VU 2CN 4 EN3155−016M2018 (f) A

24

25

 (f) = BUNDLE A9000095320795

 A = ADDED WIRE

 D = DELETED WIRE

Figure A-FDGAA - Sheet 01

ADDITIONAL WORK - Hook-up Chart in 133VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 357

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

Figure A-FCHAA - Sheet 01

ADDITIONAL WORK - Modification wiring in 105VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 358

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

**CONF ALL

END1 LEAD END2

Instructions Zone or

Panel Elec.Ident. Term Terminal P/N

Wire

Ident. Co Rte Gauge

Lenght

mm Inch

Zone or

Panel Elec.Ident. Term Terminal P/N

L

i

n

e

 1 105VU 193VT 1E 7431−0163 CF20 105VU 17JH−A Z D

 2 105VU 193VT 7H 7431−0185 CF20 105VU 18JH−A Z D

 3

 4

 5

 6 105VU 193VT 7H EN3155−016M2018 7431−0163 CF20 3000 120 105VU 17JH−A Z E0252DK2002 (c) A

 7 105VU 193VT 1E EN3155−016M2018 7431−0185 CF20 3000 120 105VU 18JH−A Z E0252DK2002 (c) A

 8

 9

10

11

12

13

14

15

16

17

18

19

20

21

22

23

24

25

 (c) = BUNDLE A9000095321095

 A = ADDED WIRE

 D = DELETED WIRE

Figure A-FDHAA - Sheet 01

ADDITIONAL WORK - Hook-up Chart in 105VU

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 359

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 360

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

Appendix 1

**CONF ALL

ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A310−74−2003

SB ELAPSED TIME

(HOURS)

GET ACCESS

STEPS MH PER ET

7.00 7.00 1

0 13

1.00 1.00 1

2.00 2.00 1

2.00 2.00 1

8.00 8.00 1

10.00 10.00 1

3.00 3.00 1

0.50 0.50 1

8.00 4.00 2

TEST 33.00 32.50 2

CLOSE−UP 5.00 5.00 1

MODIFICATION

EQUIPMENT 133VU

MODIFICATION

WIRING 133VU

MODIFICATION

EQUIPMENT 105VU

MODIFICATION

WIRING 105VU

MODIFICATION 429VU

MODIFICATION

WIRING 104VU

MODIFICATION

WIRING 80VU

MODIFICATION WIRES

IN ZONES

1 2 3 4 5 6 7 8 9 10 11 12 14 15 16 17 18 58

01

02

MH

ET/S:

PER

MANHOURS

ELAPSED TIME PER STEP

NUMBER OF PERSONS

THIS CHART IS ONLY A PROPOSAL.

OPERATORS MAY DETERMINE THAT ANOTHER WAY

TO DO THE WORK IS MORE SUITABLE FOR THEM.

MANHOURS GIVEN IN VENDOR SERVICE BULLETINS

ARE NOT REFLECTED IN THIS GANTT CHART.

01

02

NOTES:

:

:

TOTAL MANHOURS

SB ELAPSED TIME

79.5

57.5

19 20 21 52 53 54 55 56 57

B_SB_742003_5_AAAA_01_05

Figure A-FAAAA - Sheet 01

Elapsed Time Assumption

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 1

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

REPORTING SHEET

TITLE: IGNITION - IGNITION STARTING AND CONTINUOUS RELIGHT -

INTRODUCE AUTO- RELIGHT FUNCTION FOR CF6-80C2 ENGINES

MODIFICATION No.: 13525S22817

Please complete the appropriate item (A or B):

A - SB WILL BE embodied YES/NO (if NO please comment)

If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of

embodiment:

B - SB HAS BEEN embodied on aircraft:

Operator comments:

From Airline:

Name/Title:

Signature: Date:

If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to

next normal revision or prior to SB embodiment, please indicate required service(s):

Either: Modification Operational Impact (MOI), if available YES/NO

Or : Intermediate revision YES/NO

Important Information: This SB will only be incorporated in your maintenance and operational

documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With

the next feasible revision, this will result in

- Updating of maintenance documentation to show pre and post SB data.

- Updating of maintenance and operational documentation to show post SB data after embodiment.

If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically

include them in the manual revisions. Refer to SIL 00-037 for detailed information.

Please return this completed sheet to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn: SDC32 Technical Data and Documentation Services

FAX: (+33) 5 61 93 28 06

e-mail: sb.reporting@airbus.com

or via your Resident Customer Support Office.

Alternatively, SB lists via letters or fax are also accepted.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 1

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

QUALITY PERCEPTION FORM

Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data

that you provide us will be used to analyse areas of difficulties and to take corrective action to further

improve the quality of our Service Bulletins.

We thank you for the time you have taken in completing this form.

(Please rate on a scale of 1 to 4, with 4 being the highest score)

- Quality rating of this SB 4321

- Quality rating of the Accomplishment Instructions 4321

- Quality rating of the Illustrations 4321

- Is this SB easy to understand ? Y/N

If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a

short description of the issue.

Planning Material Instructions

X Effectivity X Kit content X Preparation

X Reason X List of Materials Operator Supplied X Mod/Inspection

X Manpower X Industry support X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustrations

Comments:

Operator: Date:

Name/Title:

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003

REVISION No.: 06 - Jan 27/14 Page: 1

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.