# @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



# MANDATORYMANDATORYMANDATORY
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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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. 

# MANDATORYMANDATORYMANDATORY
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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @A310 SERVICE BULLETIN SUMMARY

**CONF ALL

B_SB_742003_5_SAAA_01_00 20VU 429VU

104VU 105VU 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

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# @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

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# @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

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# @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



# MANDATORYMANDATORYMANDATORY
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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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. EASA21J.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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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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

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# @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)

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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

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**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
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# @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

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This Page Intentionally Left Blank

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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

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# @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

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# @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.

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# @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

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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

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D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESPure Mineral Vaseline Or PetroLatum 04-012 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

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# @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

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# @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

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**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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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 MineralVaseline 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

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# @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

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# @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

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# @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

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# @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

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# @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 MineralVaseline 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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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 MineralVaseline 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

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# @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

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# @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

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# @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

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# @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

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# @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 MineralVaseline 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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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 MineralVaseline 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

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# @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

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# @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

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# @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

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# @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

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# @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 MineralVaseline 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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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 MineralVaseline 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

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# @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

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# @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

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# @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

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# @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

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# @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 MineralVaseline 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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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 MineralVaseline 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

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# @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

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# @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

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# @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

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# @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

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# @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 MineralVaseline 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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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 MineralVaseline 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

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# @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

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# @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

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# @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

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# @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

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# @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 MineralVaseline 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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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 MineralVaseline 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

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# @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

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# @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

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# @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

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# @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

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# @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 MineralVaseline 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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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 aircraftto 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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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 aircraftto 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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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 aircraftto 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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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 aircraftto 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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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 aircraftto 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

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# @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

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# @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

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# @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

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# @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

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# @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.

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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 aircraftto 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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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 aircraftto 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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @A310 SERVICE BULLETIN

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DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003 REVISION No.: 06 - Jan 27/14 Page: 240 5

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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 aircraftto 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 aircraftto 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 aircraftto 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

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# @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 aircraftto 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 aircraftto 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

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# @A310 SERVICE BULLETIN (c) Restore system and aircraftto 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 aircraftto 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

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# @A310 SERVICE BULLETIN

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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 MineralVaseline 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

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# @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 MineralVaseline 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

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# @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

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# @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 MineralVaseline 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 MineralVaseline 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 MineralVaseline 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

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# @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

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# @A310 SERVICE BULLETIN (e) On the relay box 105VU, do the electrical bonding (Refer to AMM 20-28-11) with : Pure MineralVaseline 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 MineralVaseline 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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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 aircraftto 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 aircraftto normal operating system. DATE: Jul 02/10 SERVICE BULLETIN No.: A310-74-2003 REVISION No.: 06 - Jan 27/14 Page: 309 5

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# @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 aircraftto 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 aircraftto 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

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# @A310 SERVICE BULLETIN (b) Close the access doors (Refer to AMM 52-10-00) (c) Restore system and aircraftto 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 aircraftto 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 aircraftto 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

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# @A310 SERVICE BULLETIN

**CONF ALL

CIRCUIT BREAKER PANEL Q
R S
T U
V5153545255565758596061626364656667686970717273747576777879808182838485 FR20

FR1 FR10 FR13



## AFTER

133VU 

### B 120VU 133VU 

### A



## B **A**

133VU

B_SB_742003_5_BBAB_01_01 813JH14JH

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

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# @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

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# @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

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# @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

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# @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

B_SB_742003_5_BAAC_01_01 VIEW LOOKING FWD 

### 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

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# @A310 SERVICE BULLETIN

**CONF 003

105VU

FR1 FR20 

### A



## AFTER 9

133QA 18JH 17JH

10 11 12 10 11 12

15JH 16JH 10 11 12 10 11 12

B_SB_742003_5_BAAD_01_01 VIEW LOOKING FWD 

### 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

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# @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

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# @A310 SERVICE BULLETIN

**CONF ALL

20VU 429VU

104VU 105VU 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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @A310 SERVICE BULLETIN Appendix 1

**CONF ALL

**ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A310−74−2003**

SB ELAPSED TIME (HOURS) GET ACCESS MH ET PER STEPS

7.00 7.00 1

13 0 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 58 17 18 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 54 55 56 57 19 20 52 53 21

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

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# @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

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# @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

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