# @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: 24 

### TITLE: ELECTRIC COMMON INSTALLATION - WINGS - IMPROVE WIRING INSTALLATION MODIFICATION No.: 13492S22794 13497D23225 This page transmits Revision No.02 of Service Bulletin No.A310-24-2105 ADDITIONAL WORK **CONF ALL No additional work is required by this revision for aircraft modified by any previous issue. REASON Revision No.02 issued to: - Update the quantity of placards in KIT D01 and D02. CHANGES - The main changes are: . Quantity update of placards in KIT D01 and D02 . Validity of KIT D01 and D03 in the Material Information paragraph SUMMARY MATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE UPDATED R MATERIAL PRICE INFORMATION TABLE UPDATED R EFFECTIVITY OPERATOR LIST UPDATED R PLANNING INFORMATION EFFECTIVITY EFFECTIVITY RELATED INFORMATION UPDATED R Configuration definition CONF 002 CONFIGURATION DEFINITION UPDATED R

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 1 6

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# @A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
CONF 003 CONFIGURATION DEFINITION UPDATED R CONF 004 CONFIGURATION DEFINITION UPDATED R Material Effectivity MATERIAL EFFECTIVITY UPDATED MATERIAL SET QUANTITY UPDATED MATERIAL SET UPDATED R
MATERIAL EFFECTIVITY UPDATED MATERIAL SET QUANTITY UPDATED MATERIAL SET UPDATED R
MATERIAL INFORMATION LIST OF COMPONENTS Kit 242105D01R08 PART MATERIAL SET UPDATED QUANTITY UPDATED R Kit 242105D02R08 PART MATERIAL SET UPDATED QUANTITY UPDATED R ACCOMPLISHMENT INSTRUCTIONS TASK 242105- 831-848-001- MODIFICATION Subtask 242105-831-213-002 SUBTASK SOLUTION UPDATED QUANTITY UPDATED MATERIAL LIST UPDATED R
Subtask 242105-831-214-002 SUBTASK SOLUTION UPDATED QUANTITY UPDATED MATERIAL LIST UPDATED R
Subtask 242105-831-220-002 SUBTASK SOLUTION UPDATED QUANTITY UPDATED MATERIAL LIST UPDATED R
Subtask 242105-831-211-003 SUBTASK SOLUTION UPDATED QUANTITY UPDATED MATERIAL LIST UPDATED R
Subtask 242105-831-212-003 SUBTASK SOLUTION UPDATED QUANTITY UPDATED MATERIAL LIST UPDATED R
Subtask 242105-831-213-001 SUBTASK SOLUTION UPDATED QUANTITY UPDATED MATERIAL LIST UPDATED R
Subtask 242105-831-214-001 SUBTASK SOLUTION UPDATED QUANTITY UPDATED MATERIAL LIST UPDATED R
Subtask 242105-831-220-001 SUBTASK SOLUTION UPDATED QUANTITY UPDATED MATERIAL LIST UPDATED R
Subtask 242105-831-211-002 SUBTASK SOLUTION UPDATED QUANTITY UPDATED MATERIAL LIST UPDATED R
Subtask 242105-831-213-002 SUBTASK SOLUTION UPDATED QUANTITY UPDATED MATERIAL LIST UPDATED R

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 2 6

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# @A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
Subtask 242105-831-214-002 SUBTASK SOLUTION UPDATED QUANTITY UPDATED MATERIAL LIST UPDATED R
Subtask 242105-831-220-002 SUBTASK SOLUTION UPDATED QUANTITY UPDATED MATERIAL LIST UPDATED R
Subtask 242105-831-211-002 SUBTASK SOLUTION UPDATED QUANTITY UPDATED MATERIAL LIST UPDATED R
Subtask 242105-831-213-002 SUBTASK SOLUTION UPDATED QUANTITY UPDATED MATERIAL LIST UPDATED R
Subtask 242105-831-214-002 SUBTASK SOLUTION UPDATED QUANTITY UPDATED MATERIAL LIST UPDATED R
Subtask 242105-831-220-002 SUBTASK SOLUTION UPDATED QUANTITY UPDATED MATERIAL LIST UPDATED R

FILING 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: Update the effectivity. REVISION SEQUENCE ORIGINAL: Mar 20/13 REVISION No. : 01 - Dec 11/13 REVISION No. : 02 - Jan 05/15

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 3 6

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# @A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

This Page Intentionally Left Blank

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 4 6

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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: 24 

### TITLE: ELECTRIC COMMON INSTALLATION - WINGS - IMPROVE WIRING INSTALLATION **CONF ALL MODIFICATIONS MODIFICATION CLASSIFICATION MAJOR 13492S22794 13497D23225 MINOR None 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 The A310 aircraft operator’s feedback further to the accomplishment of the mandatory Inspection Service Bulletin A310-24-2095 and a review of the wing electrical installation at the AIRBUS final assembly line have shown that the wing electrical installation doesn’t comply with the minimum distance inspection criteria to the surrounding structure in a few wing locations. This Service Bulletin requires: - the installation of new bracket assemblies to improve the electrical harnesses installation and secure the clearance to the structure in identified locations - the installation of protective split sleeve as mechanical protection to the electrical harnesses in areas where the minimum distance to the structure cannot be achieved. Accomplishment of this modification Service Bulletin will improve the wing electrical installation in the identified areas and prevent possible chafing and subsequent damage to the electrical harnesses and surrounding structure. GENERAL EVALUATION EVALUATION TABLE COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 1 6

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# @A310 SERVICE BULLETIN SUMMARY EVALUATION TABLE POTENTIAL AD YES A/C OPERATION AFFECTED NO RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO COST SAVING NO ETOPS AFFECTED NO STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO Kit Price (USD) See SB 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 242105A01R03 1 10,480.00 Protective sleeve, spacer, hardware Kit 242105B01R02 1 36.00 Brackets, nutplate, rivets Kit 242105D02R08 1 8,090.00 Ramp, clamp, spacer, protection sleeve and attachment parts TOTAL 18,606.00 **CONF 002 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 242105A01R03 1 10,480.00 Protective sleeve, spacer, hardware Kit 242105B01R02 1 36.00 Brackets, nutplate, rivets Kit 242105D01R08 1 3,590.00 Ramp, clamp, spacer, protection sleeve and attachment parts Kit 242105D04R00 1 97.00 Clamp and attachment parts TOTAL 14,203.00 **CONF 003 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 242105A01R03 1 10,480.00 Protective sleeve, spacer, hardware Kit 242105B01R02 1 36.00 Brackets, nutplate, rivets Kit 242105D02R08 1 8,090.00 Ramp, clamp, spacer, protection sleeve and attachment parts Kit 242105D04R00 1 97.00 Clamp and attachment parts TOTAL 18,703.00

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 2 6

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# @A310 SERVICE BULLETIN SUMMARY **CONF 004 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 242105A01R03 1 10,480.00 Protective sleeve, spacer, hardware Kit 242105B01R02 1 36.00 Brackets, nutplate, rivets Kit 242105D02R08 1 8,090.00 Ramp, clamp, spacer, protection sleeve and attachment parts Kit 242105D03R01 1 96.00 Clamp and attachment parts Kit 242105D04R00 1 97.00 Clamp and attachment parts TOTAL 18,799.00 EFFECTIVITY **CONF ALL This Service Bulletin is applicable to this (these) operator(s) :

18T 19U 40T 50W 58X 82Z 85Z 98W 99Y AFG AIC BBC CFC DGA F2I FDX GAF HFY IRA IRM IYE K1P KAC KZU MGL PCA PIA QAF R1T RJA ROT RZO SGX SUD THY TSC UBD UZB WHT CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU None OEB None 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

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 3 6

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# @A310 SERVICE BULLETIN SUMMARY MANPOWER **CONF 001 Task 242105-831-848-001: MODIFICATION TOTAL MANHOURS 54.25 ELAPSED TIME (HOURS) 30.75 **CONF 002 Task 242105-831-848-001: MODIFICATION TOTAL MANHOURS 49.50 ELAPSED TIME (HOURS) 29.50 **CONF 003 Task 242105-831-848-001: MODIFICATION TOTAL MANHOURS 54.25 ELAPSED TIME (HOURS) 34.00 **CONF 004 Task 242105-831-848-001: MODIFICATION TOTAL MANHOURS 55.50 ELAPSED TIME (HOURS) 31.25 APPENDICES **CONF ALL Appendix 01 - Elapsed Time Assumption

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 4 6

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# @A310 SERVICE BULLETIN SUMMARY

**CONF 001 thru 003

B_SB_242105_6_SAAB_01_03 ZONES WITH ROUTING TO MODIFY Z573

Z513 Z613

− Z137 Z138 Z673

Z512 Z612

Z524 Z624 Z675

Figure A-GSAAB - Sheet 01

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 5 6

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# @A310 SERVICE BULLETIN SUMMARY

**CONF 004

Z573

Z513 Z613

− Z137 Z138 Z673

ZONES WITH ROUTING TO MODIFY Z512 Z612

Z524 Z624

Z575

B_SB_242105_6_SAAE_01_01 Figure A-GSAAE - Sheet 01

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 6 6

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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: 24 

### TITLE: ELECTRIC COMMON INSTALLATION - WINGS - IMPROVE WIRING INSTALLATION MODIFICATION No.: 13492S22794 13497D23225 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 This modification is applicable by Service Bulletin only. (1) Models 310-203 310-221 310-222 310-304 310-308 310-322 310-324 310-325 (2) Effectivity by MSN 0162 0230 0237 0245 0248 0267 0278 0281 0283 0331 0356 0362 0364 0369 0378 0394 0399 0407 0413 0418-0419 0421-0422 0425 0431 0434 0436-0437 0439 0441 0444-0447 0449 0452 0456-0458 0467 0472-0473 0478 0480 0482-0484 0488-0492 0494-0500 0503 0519-0520 0522-0524 0526-0527 0537 0539 0545 0547 0549-0552 0562 0564-0565 0567-0568 0571 0574 0576 0585-0588 0590-0595 0597 0599-0600 0620 0622 0624 0636 0644 0646-0649 0651 0653 0656 0658 0660-0661 0663 0667 0671-0672 0674 0676 0678 0682 0687 0689 0691 0700 0702 0704 0706

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 1 6

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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 19U 0399 40T 0413 50W 0498 58X 0431 82Z 0550 0551 85Z 0527 98W 0495 99Y 0489 AFG 0496 0497 AIC 0407 BBC 0594 0700 CFC 0425 0441 0444 0446 0482 DGA 0418 0421 0422 F2I 0491 0520 FDX 0162 0230 0237 0245 0248 0267 0278 0281 0283 0331 0356 0362 0364 0369 0378 0394 0439 0449 0452 0456 0457 0458 0467 0492 0500 0539 0549 0552 0593 GAF 0434 0484 0503 0522 0523 HFY 0565 IRA 0436 0671 IRM 0488 0499 0524 0537 0547 0564 0567 0586 0595 0620 IYE 0568 0702 0704 K1P 0648 KAC 0647 0649 0663 KZU 0592 0622 0646 MGL 0526 PCA 0419 PIA 0585 0587 0590 0653 0656 0660 0676 0678 0682 0687 0689 0691 QAF 0667 R1T 0591 RJA 0445 0490 ROT 0636 0644 RZO 0571 0624 0651 0661 SGX 0519 0562 SUD 0437 THY 0478 0480 TSC 0447 0472 0483 0545 0588 0597 0599 0600 0658 UBD 0672 0674 UZB 0574 0576 0706 DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 2 6

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# @A310 SERVICE BULLETIN
OPERATOR MSN WHT 0494 (4) Configuration by MSN MSN CONFIGURATION 0162 0230 0237 0245 0248 0267 0278 0281 0283 0331 0356 0362 0364 0369 0394 002 0378 0439 0449 0452 0456 0457 0458 0467 0489 0492 0500 0539 0549 0568 0574 0576 0591 0594 0624 0636 0644 0660 0672 0674 0676 0678 0682 0687 0689 0700 0702 0704 0706 001
0399 0407 0413 0419 0421 0422 0431 0434 0436 0437 0620 003 0418 0425 0441 0444 0445 0446 0447 0472 0473 0478 0480 0482 0483 0484 0488 0490 0491 0494 0495 0496 0497 0498 0499 0503 0519 0520 0522 0523 0524 0526 0527 0537 0545 0547 0550 0551 0552 0562 0564 0565 0567 0571 0585 0586 0587 0588 0590 0592 0593 0595 0597 0599 0600 0622 0646 0647 0648 0649 0651 0653 0656 0658 0661 0663 0667 0671 0691 004

(5) Configuration definition **CONF 001 Config. 001 is valid for the 310-324 and 310-325 type of aircraft in the effectivity of this Service Bulletin for aircraft without installation of 5082VN and 5084VN on RIB 8 and without installation of wires 2612-5017 and 2612-5016 on 2147VC. **CONF 002 Config. 002 is valid for the 310-203, 310-221, 310-222, 310-324 and 310-325 type of aircraft in the effectivity of this Service Bulletin for aircraft with 5082VN and 5084VN on RIB 8 installed and without installation of wires 2612-5017 and 2612-5016 on 2147VC. **CONF 003 Config. 003 is valid for the 310-304 and 310-322 type of aircraft in the effectivity of this Service Bulletin with 5082VN and 5084VN on RIB 8 installed and without installation of wires 2612-5017 and 2612-5016 on 2147VC. **CONF 004 Config. 004 is valid for the 310-308 and 310-304 type of aircraft in the effectivity of this Service Bulletin with 5082VN and 5084VN on RIB 8 installed and with wires 2612-5017 and 2612-5016 on 2147VC installed. (6) Material Effectivity **CONF 001 MATERIAL QTY PER A/C SEE NOTES Kit 242105A01R03 1 Consumable CMLA01 As required Kit 242105B01R02 1 Consumable CMLB01 As required
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 3 6

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# @A310 SERVICE BULLETIN

MATERIAL QTY PER A/C SEE NOTES Kit 242105D02R08 1 Consumable CMLD01 As required **CONF 002 MATERIAL QTY PER A/C SEE NOTES Kit 242105A01R03 1 Consumable CMLA01 As required Kit 242105B01R02 1 Consumable CMLB01 As required Kit 242105D01R08 1 Kit 242105D04R00 1 Consumable CMLD01 As required **CONF 003 MATERIAL QTY PER A/C SEE NOTES Kit 242105A01R03 1 Consumable CMLA01 As required Kit 242105B01R02 1 Consumable CMLB01 As required Kit 242105D02R08 1 Kit 242105D04R00 1 Consumable CMLD01 As required **CONF 004 MATERIAL QTY PER A/C SEE NOTES Kit 242105A01R03 1 Consumable CMLA01 As required Kit 242105B01R02 1 Consumable CMLB01 As required Kit 242105D02R08 1 Kit 242105D03R01 1 Kit 242105D04R00 1 Consumable CMLD01 As required **CONF ALL B. CONCURRENT REQUIREMENTS None

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 4 6

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# @A310 SERVICE BULLETIN
C. REASON (1) History The A310 aircraft operator’s feedback further to the accomplishment of the mandatory Inspection Service Bulletin A310-24-2095 and a review of the wing electrical installation at the AIRBUS final assembly line have shown that the wing electrical installation doesn’t comply with the minimum distance inspection criteria to the surrounding structure in a few wing locations. (2) Objective/Action This Service Bulletin requires: - the installation of new bracket assemblies to improve the electrical harnesses installation and secure the clearance to the structure in identified locations - the installation of protective split sleeve as mechanical protection to the electrical harnesses in areas where the minimum distance to the structure cannot be achieved. (3) Advantages Accomplishment of this modification Service Bulletin will improve the wing electrical installation in the identified areas and prevent possible chafing and subsequent damage to the electrical harnesses and surrounding structure. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : **CONF 001 Task 242105-831-848-001: MODIFICATION (1) Install Adhesive Clipping Bracket on the LH and RH Wing Leading Edge in the Area of Rib 7 (2) Attach the routes 1E and 1G with the lacing tape in the LH shroud box leading edge. (3) Attach the routes 2E and 2G with the lacing tape in the RH shroud box leading edge. (4) Modify the routing in the LH forward wing to fuselage fairing. (5) Modify the routing in the RH forward wing to fuselage fairing. (6) Modify the routing on the LH shroud box leading edge. (7) Modify the routing on the RH shroud box leading edge.
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 5 6

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# @A310 SERVICE BULLETIN (8) Install new nutplate on the RH wing Leading edge (9) Modify the electrical routing installation at the LH front spar in the area of RIB 2 (10) Modify the electrical routing installation at the RH front spar in the area of RIB 2 (11) Modify the electrical routing installation at the LH front spar in the area of RIB 3. (12) Modify the electrical routing installation at the RH front spar in the area of RIB 3. (13) Modify the electrical routing installation at the LH and RH front spars in the area of RIB 5 and RIB 6. (14) Modify the electrical routing installation at the LH and RH front spars in the area of RIB 7 and RIB 8. (15) Modify the electrical routing installation at the LH front spar in the area of RIB 20 and RIB 21. (16) Modify the electrical routing installation at the RH front spar in the area of RIB 20 and RIB 21. (17) Modify the electrical routing installation at the RH front spar in the area of RIB 28 and RIB 28A. **CONF 002 Task 242105-831-848-001: MODIFICATION (1) Install Adhesive Clipping Bracket on the LH and RH Wing Leading Edge in the Area of Rib 7 (2) Attach the routes 1E and 1G with the lacing tape in the LH shroud box leading edge. (3) Attach the routes 2E and 2G with the lacing tape in the RH shroud box leading edge. (4) Modify the routing in the LH forward wing to fuselage fairing. (5) Modify the routing in the RH forward wing to fuselage fairing. (6) Modify the routing on the LH shroud box leading edge. (7) Modify the routing on the RH shroud box leading edge. (8) Install new nutplate on the RH wing Leading edge (9) Modify the electrical routing installation at the LH front spar in the area of RIB 2. (10) Modify the electrical routing installation at the RH front spar in the area of RIB 2. (11) Modify the electrical routing installation at the LH front spar in the area of RIB 3. (12) Modify the electrical routing installation at the RH front spar in the area of RIB 3.
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 6 6

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# @A310 SERVICE BULLETIN (13) Modify the electrical routing installation at the LH and RH front spars in the area of RIB 5 and RIB 6. (14) Modify the electrical routing installation at the LH and RH front spars in the area of RIB 7 and RIB 8. (15) Modify the electrical routing installation at the RH front spar in the area of RIB 28 and RIB 28A. **CONF 003 Task 242105-831-848-001: MODIFICATION (1) Install Adhesive Clipping Bracket on the LH and RH Wing Leading Edge in the Area of Rib 7 (2) Attach the routes 1E and 1G with the lacing tape in the LH shroud box leading edge. (3) Attach the routes 2E and 2G with the lacing tape in the RH shroud box leading edge. (4) Modify the routing in the LH forward wing to fuselage fairing. (5) Modify the routing in the RH forward wing to fuselage fairing. (6) Modify the routing on the LH shroud box leading edge. (7) Modify the routing on the RH shroud box leading edge. (8) Install new nutplate on the RH wing Leading edge (9) Modify the electrical routing installation at the LH front spar in the area of RIB 2. (10) Modify the electrical routing installation at the RH front spar in the area of RIB 2. (11) Modify the electrical routing installation at the LH front spar in the area of RIB 3. (12) Modify the electrical routing installation at the RH front spar in the area of RIB 3. (13) Modify the electrical routing installation at the LH and RH front spars in the area of RIB 5 and RIB 6. (14) Modify the electrical routing installation at the LH and RH front spars in the area of RIB 7 and RIB 8. (15) Modify the electrical routing installation at the LH front spar in the area of RIB 20 and RIB 21. (16) Modify the electrical routing installation at the RH front spar in the area of RIB 20 and RIB 21. (17) Modify the electrical routing installation at the RH front spar in the area of RIB 28 and RIB 28A.

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 7 6

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# @A310 SERVICE BULLETIN
**CONF 004 Task 242105-831-848-001: MODIFICATION (1) Install Adhesive Clipping Bracket on the LH and RH Wing Leading Edge in the Area of Rib 7 (2) Attach the routes 1E and 1G with the lacing tape in the LH shroud box leading edge. (3) Attach the routes 2E and 2G with the lacing tape in the RH shroud box leading edge. (4) Modify the routing in the LH forward wing to fuselage fairing. (5) Modify the routing in the RH forward wing to fuselage fairing. (6) Modify the routing on the LH shroud box leading edge. (7) Modify the routing on the RH shroud box leading edge. (8) Install new nutplate on the RH wing Leading edge (9) Modify the electrical routing installation at the LH front spar in the area of RIB 2. (10) Modify the electrical routing installation at the RH front spar in the area of RIB 2. (11) Modify the electrical routing installation at the LH front spar in the area of RIB 3. (12) Modify the electrical routing installation at the RH front spar in the area of RIB 3. (13) Modify the electrical routing installation at the LH and RH front spars in the area of RIB 5 and RIB 6. (14) Modify the electrical routing installation at the LH and RH front spars in the area of RIB 7 and RIB 8. (15) Modify the electrical routing installation at the RH front spar in the area of RIB 8. (16) Modify the electrical routing installation at the LH front spar in the area of RIB 20 and RIB 21. (17) Modify the electrical routing installation at the RH front spar in the area of RIB 20 and RIB 21. (18) Modify the electrical routing installation at the RH front spar in the area of RIB 28 and RIB 28A. (19) Modify the electrical routing installation at the LH rear spar in the area of RIB 9.

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 8 6

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# @A310 SERVICE BULLETIN
**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 The technical content of this document is approved under the authority of the Design Organisation Approval No. EASA.21J.031. If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, and which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin. 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. For an explanation of the manhours and elapsed time, refer to Appendix 01 - Elapsed Time Assumption . **CONF 001 Task 242105-831-848-001: MODIFICATION Get Access 8.00 On Aircraft Install Adhesive Clipping Bracket on the LH and RH Wing Leading Edge in the Area of Rib 7 1.00 Attach the routes 1E and 1G with the lacing tape in the LH shroud box leading edge. 0.50 Attach the routes 2E and 2G with the lacing tape in the RH shroud box leading edge. 0.50 Modify the routing in the LH forward wing to fuselage fairing. 2.00 Modify the routing in the RH forward wing to fuselage fairing. 2.00

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 9 6

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# @A310 SERVICE BULLETIN
Task 242105-831-848-001: MODIFICATION Modify the routing on the LH shroud box leading edge. 6.00 Modify the routing on the RH shroud box leading edge. 6.00 Install new nutplate on the RH wing Leading edge 1.00 Modify the electrical routing installation at the LH front spar in the area of RIB 2 1.5 Modify the electrical routing installation at the RH front spar in the area of RIB 2 2.00 Modify the electrical routing installation at the LH front spar in the area of RIB 3. 1.00 Modify the electrical routing installation at the RH front spar in the area of RIB 3. 1.00 Modify the electrical routing installation at the LH and RH front spars in the area of RIB 5 and RIB 6. 2.50 Modify the electrical routing installation at the LH and RH front spars in the area of RIB 7 and RIB 8. 1.00 Modify the electrical routing installation at the LH front spar in the area of RIB 20 and RIB 21. 3.25 Modify the electrical routing installation at the RH front spar in the area of RIB 20 and RIB 21. 2.50 Modify the electrical routing installation at the RH front spar in the area of RIB 28 and RIB 28A. 1.50 Tests 1.00 Close-Up 10.00 TOTAL MANHOURS 54.25 ELAPSED TIME (HOURS) 30.75 **CONF 002 Task 242105-831-848-001: MODIFICATION Get Access 8.00 On Aircraft Install Adhesive Clipping Bracket on the LH and RH Wing Leading Edge in the Area of Rib 7 1.00 Attach the routes 1E and 1G with the lacing tape in the LH shroud box leading edge. 0.50 Attach the routes 2E and 2G with the lacing tape in the RH shroud box leading edge. 0.50 Modify the routing in the LH forward wing to fuselage fairing. 2.00 Modify the routing in the RH forward wing to fuselage fairing. 2.00 Modify the routing on the LH shroud box leading edge. 6.00 Modify the routing on the RH shroud box leading edge. 6.00 Install new nutplate on the RH wing Leading edge 1.00

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 10 6

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# @A310 SERVICE BULLETIN
Task 242105-831-848-001: MODIFICATION Modify the electrical routing installation at the LH front spar in the area of RIB 2. 1.75 Modify the electrical routing installation at the RH front spar in the area of RIB 2. 1.75 Modify the electrical routing installation at the LH front spar in the area of RIB 3. 1.75 Modify the electrical routing installation at the RH front spar in the area of RIB 3. 1.75 Modify the electrical routing installation at the LH and RH front spars in the area of RIB 5 and RIB 6. 2.50 Modify the electrical routing installation at the LH and RH front spars in the area of RIB 7 and RIB 8. 0.50 Modify the electrical routing installation at the RH front spar in the area of RIB 28 and RIB 28A. 1.50 Tests 1.00 Close-Up 10.00 TOTAL MANHOURS 49.50 ELAPSED TIME (HOURS) 29.50 **CONF 003 Task 242105-831-848-001: MODIFICATION Get Access 8.00 On Aircraft Install Adhesive Clipping Bracket on the LH and RH Wing Leading Edge in the Area of Rib 7 1.00 Attach the routes 1E and 1G with the lacing tape in the LH shroud box leading edge. 0.50 Attach the routes 2E and 2G with the lacing tape in the RH shroud box leading edge. 0.50 Modify the routing in the LH forward wing to fuselage fairing. 2.00 Modify the routing in the RH forward wing to fuselage fairing. 2.00 Modify the routing on the LH shroud box leading edge. 6.00 Modify the routing on the RH shroud box leading edge. 6.00 Install new nutplate on the RH wing Leading edge 1.00 Modify the electrical routing installation at the LH front spar in the area of RIB 2. 1.5 Modify the electrical routing installation at the RH front spar in the area of RIB 2. 2.00 Modify the electrical routing installation at the LH front spar in the area of RIB 3. 1.00 Modify the electrical routing installation at the RH front spar in the area of RIB 3. 1.00

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 11 6

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# @A310 SERVICE BULLETIN
Task 242105-831-848-001: MODIFICATION Modify the electrical routing installation at the LH and RH front spars in the area of RIB 5 and RIB 6. 2.50 Modify the electrical routing installation at the LH and RH front spars in the area of RIB 7 and RIB 8. 1.00 Modify the electrical routing installation at the LH front spar in the area of RIB 20 and RIB 21. 3.25 Modify the electrical routing installation at the RH front spar in the area of RIB 20 and RIB 21. 2.50 Modify the electrical routing installation at the RH front spar in the area of RIB 28 and RIB 28A. 1.50 Tests 1.00 Close-Up 10.00 TOTAL MANHOURS 54.25 ELAPSED TIME (HOURS) 34.00 **CONF 004 Task 242105-831-848-001: MODIFICATION Get Access 8.00 On Aircraft Install Adhesive Clipping Bracket on the LH and RH Wing Leading Edge in the Area of Rib 7 1.00 Attach the routes 1E and 1G with the lacing tape in the LH shroud box leading edge. 0.50 Attach the routes 2E and 2G with the lacing tape in the RH shroud box leading edge. 0.50 Modify the routing in the LH forward wing to fuselage fairing. 2.00 Modify the routing in the RH forward wing to fuselage fairing. 2.00 Modify the routing on the LH shroud box leading edge. 6.00 Modify the routing on the RH shroud box leading edge. 6.00 Install new nutplate on the RH wing Leading edge 1.00 Modify the electrical routing installation at the LH front spar in the area of RIB 2. 1.5 Modify the electrical routing installation at the RH front spar in the area of RIB 2. 2.00 Modify the electrical routing installation at the LH front spar in the area of RIB 3. 1.00 Modify the electrical routing installation at the RH front spar in the area of RIB 3. 1.00 Modify the electrical routing installation at the LH and RH front spars in the area of RIB 5 and RIB 6. 2.50 Modify the electrical routing installation at the LH and RH front spars in the area of RIB 7 and RIB 8. 1.00

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 12 6

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# @A310 SERVICE BULLETIN
Task 242105-831-848-001: MODIFICATION Modify the electrical routing installation at the RH front spar in the area of RIB 8. 0.50 Modify the electrical routing installation at the LH front spar in the area of RIB 20 and RIB 21. 3.25 Modify the electrical routing installation at the RH front spar in the area of RIB 20 and RIB 21. 2.50 Modify the electrical routing installation at the RH front spar in the area of RIB 28 and RIB 28A. 1.50 Modify the electrical routing installation at the LH rear spar in the area of RIB 9. 0.75 Tests 1.00 Close-Up 10.00 TOTAL MANHOURS 55.50 ELAPSED TIME (HOURS) 31.25 **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. **CONF 001 Manufacturers Empty Weight +0.668 KG (+1.4726 LB) Effect on Balance +21.454 KGM (+155.176 LB.FT ) **CONF 002 Manufacturers Empty Weight +0.319 KG (+0.7032 LB) Effect on Balance +10.741 KGM (+77.689 LB.FT ) **CONF 003 Manufacturers Empty Weight +0.668 KG (+1.4726 LB) Effect on Balance +21.454 KGM (+155.176 LB.FT ) **CONF 004 Manufacturers Empty Weight +0.018 KG (+0.0396 LB) Effect on Balance +0.621 KGM (+4.491 LB.FT ) **CONF ALL I. ELECTRICAL LOAD DATA Not Changed

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 13 6

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# @A310 SERVICE BULLETIN
J. REFERENCES **CONF 001 Aircraft Maintenance Manual (AMM) 06-21-00 06-31-53 06-41-00 06-41-53 06-41-57 20-21-12 20-23-12 20-27-00 24-00-00 27-50-00 27-61-00 27-80-00 29-00-00 29-10-00 29-14-00 29-25-00 32-12-11 36-11-00 53-15-63 71-00-00 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-25-51 20-33-33 20-33-41 20-33-44 20-55-00 Standards Manual (SM) Structural Repair Manual (SRM) 51-23-00 51-24-00 51-40-20 51-40-21 51-40-30 51-40-40 51-40-50 51-43-00 51-75-10 51-77-10 Weight and Balance Manual (WBM) Weight and Balance Manual (WBM) Chapter 1-00-07 **CONF 002 Aircraft Maintenance Manual (AMM) 06-21-00 06-31-53 06-41-00 06-41-53 06-41-57 20-21-12 20-23-12 20-27-00 24-00-00 27-50-00 27-61-00 27-80-00 29-00-00 29-10-00 29-14-00 29-25-00 32-12-11 36-11-00 53-15-63 71-00-00 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-25-51 20-33-33 20-33-41 20-33-44 20-55-00 Standards Manual (SM) Structural Repair Manual (SRM) 51-23-00 51-24-00 51-40-20 51-40-21 51-40-30 51-40-40 51-40-50 51-43-00 51-75-10 51-77-10 Weight and Balance Manual (WBM) Weight and Balance Manual (WBM) Chapter 1-00-07 **CONF 003 Aircraft Maintenance Manual (AMM) 06-21-00 06-31-53 06-41-00 06-41-53 06-41-57 20-21-12 20-23-12 20-27-00 24-00-00 27-50-00 27-61-00 27-80-00 29-00-00 29-10-00 29-14-00 29-25-00 32-12-11 36-11-00 53-15-63 71-00-00 Consumable Material List (CML)

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 14 6

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# @A310 SERVICE BULLETIN Elec. Std. Practices Manual (ESPM) 20-25-51 20-33-33 20-33-41 20-33-44 20-55-00 Standards Manual (SM) Structural Repair Manual (SRM) 51-23-00 51-24-00 51-40-20 51-40-21 51-40-30 51-40-40 51-40-50 51-43-00 51-75-10 51-77-10 Weight and Balance Manual (WBM) Weight and Balance Manual (WBM) Chapter 1-00-07 **CONF 004 Aircraft Maintenance Manual (AMM) 06-21-00 06-31-53 06-41-00 06-41-53 06-41-57 20-21-12 20-23-12 20-27-00 24-00-00 27-50-00 27-61-00 27-80-00 29-00-00 29-10-00 29-14-00 29-25-00 32-12-11 36-11-00 53-15-63 71-00-00 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-25-51 20-33-33 20-33-41 20-33-44 20-55-00 Standards Manual (SM) Structural Repair Manual (SRM) 51-23-00 51-24-00 51-40-20 51-40-21 51-40-30 51-40-40 51-40-50 51-43-00 51-75-10 51-77-10 Weight and Balance Manual (WBM) Weight and Balance Manual (WBM) Chapter 1-00-07 **CONF ALL K. PUBLICATION AFFECTED

Illustrated Parts Catalog (IPC) 24-92-02 24-92-03 L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 15 6

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# @A310 SERVICE BULLETIN

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# @A310 SERVICE BULLETIN
2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses 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: Kit 242105A01R03 Kit 242105B01R02 Kit 242105D01R08 Kit 242105D02R08 Kit 242105D03R01 Kit 242105D04R00 AIRBUS Material, Logistics and Suppliers Weg beim Jaeger 150 D-22335 HAMBURG GERMANY For ordering by internet: http://spares.airbus.com For ordering by fax: +49 40 50 76 4012 For ordering by E-mail: ifd.spares@airbus.com (2) Price and Availability

Kit 242105A01R03 Cost 10,480.00 USD Availability 90 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 242105B01R02 Cost 36.00 USD Availability 90 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 242105D01R08 Cost 3,590.00 USD Availability 90 calendar days from receipt of order

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 17 6

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# @A310 SERVICE BULLETIN The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 242105D02R08 Cost 8,090.00 USD Availability 90 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 242105D03R01 Cost 96.00 USD Availability 90 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 242105D04R00 Cost 97.00 USD Availability 90 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. B. INDUSTRY SUPPORT INFORMATION AIRBUS will provide a 10% reduction to the applicable kits sales prices given in the paragraph ’Price and Availability’ for orders placed before Dec 31/2015.

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 18 6

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# @A310 SERVICE BULLETIN
C. LIST OF COMPONENTS Kit 242105A01R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 51 NSA8420-5 2 (M) CORD 52 EN6049-007-08-5 56 (M) SLEEVE 53 NSA935401-05 344 TIE 55 A9201346420000 2 GROMMET 56 NAS1801-3-17 12 SCREW 57 NAS1149D0316H 34 WASHER 60 NAS1801-3-13 8 SCREW 61 NSA5527-03-03 8 SPACER 62 NSA935401-13 15 TIE 63 NSA5527-03-01 16 SPACER 64 NSA5527-03-02 10 SPACER 65 A9222505750000 2 SPACER 66 EN6049-007-13-5 56 (M) SLEEVE 67 EN6049-007-19-5 56 (ME) SLEEVE 69 NSA939510BN 4 (M) STRIP 85 NSA5516-08ND 32 CLAMP 86 NSA5516-18ND 32 CLAMP 91 A0041113620000 3 BRACKET 92 A0041113620100 3 BRACKET 93 A0041113720000 3 BRACKET 94 A0041113720100 3 BRACKET 96 NSA5516-10ND 16 CLAMP 97 NAS1801-3-14 6 SCREW 98 NAS1801-3-8 6 SCREW 99 NAS1801-3-16 2 SCREW 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 242105D01R08 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 2 MS21919WCH10 2 CLAMP 3 NAS1149D0332K 5 WASHER 4 NSA5527-03-03D 2 SPACER 6 NAS1801-3-10 2 SCREW 7 NSA5527-03-05D 2 SPACER 9 MS21919WCH3 3 CLAMP 10 MS21919WCH2 2 CLAMP 18 MS21919WCH12 3 CLAMP DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 19 6

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# @A310 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 19 MS21919WCH4 8 CLAMP 20 EN6049-007-05-5 2 (ME) SLEEVE 21 EN6049-007-19-5 2 (ME) SLEEVE 23 NAS1801-3-16 4 SCREW 24 MS21042-3 2 NUT 27 NSA5527-03-15D 2 SPACER 28 NAS1801-3-30 1 SCREW 29 MS21919WCH11 6 CLAMP 30 MS21919WCH5 1 CLAMP 31 NAS1801-3-13 2 SCREW 32 NSA5527-03-07D 4 SPACER 42 A9249252400400 2 RAMP 43 NSA935401-03 32 TIE 100 B9239030000200 15 PLACARD 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 242105D02R08 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 2 MS21919WCH10 2 CLAMP 3 NAS1149D0332K 9 WASHER 4 NSA5527-03-03D 2 SPACER 6 NAS1801-3-10 2 SCREW 7 NSA5527-03-05D 2 SPACER 8 NSA5527-03-01D 4 SPACER 9 MS21919WCH3 15 CLAMP 10 MS21919WCH2 6 CLAMP 11 NAS1801-3-18 4 SCREW 18 MS21919WCH12 5 CLAMP 19 MS21919WCH4 11 CLAMP 20 EN6049-007-05-5 2 (ME) SLEEVE 21 EN6049-007-19-5 2 (ME) SLEEVE 23 NAS1801-3-16 4 SCREW 24 MS21042-3 6 NUT 25 NAS1096-3-24 4 SCREW 26 NAS1096-3-22 4 SCREW 27 NSA5527-03-15D 2 SPACER 28 NAS1801-3-30 1 SCREW 29 MS21919WCH11 5 CLAMP 30 MS21919WCH5 2 CLAMP 31 NAS1801-3-13 2 SCREW
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 20 6

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# @A310 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 32 NSA5527-03-07D 10 SPACER 40 A9249252400000 2 RAMP 41 A9249252400200 2 RAMP 42 A9249252400400 2 RAMP 43 NSA935401-03 56 TIE 100 B9239030000200 19 PLACARD 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 242105D03R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 10 MS21919WCH2 2 CLAMP 15 NAS1801-3-35 1 SCREW 16 NSA5527-03-11D 1 SPACER 100 B9239030000200 1 PLACARD 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 242105D04R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 3 NAS1149D0332K 1 WASHER 6 NAS1801-3-10 1 SCREW 9 MS21919WCH3 1 CLAMP 24 MS21042-3 1 NUT 100 B9239030000200 1 PLACARD 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 242105B01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 102 ABS1546B3C12 2 BRACKET 106 NSA5456-3-8 1 NUTPLATE 111 ANSA2050DCJ3210 2 RIVET

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 21 6

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# @A310 SERVICE BULLETIN
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. D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polyvinylacetat Pvac 05-034 As required Aluminium Foil 05-169 As required Stainless Steel Lockwire 05-289 As required 68 Epoxy Resin 08-051 As required Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required Lint-Free Cotton Cloth 19-003 As required Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Two Part Paste Adhesive 08-078 As required Multi Purpose Thixotropic Paste 09-016J As required Solvent General Purpose 11-026 As required Lint-Free Cotton Cloth 19-003 As required (2) Components None (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING None

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 22 6

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# @A310 SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS Task 242105-831-848-001 - MODIFICATION WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES WARNING: MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE. 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 ELECTRICAL 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. IF THERE IS 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. NOTE: This Service Bulletin is classified mandatory or expected to be classified mandatory by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these accomplishment instructions are Required for Compliance (RC) and must be done to comply with the AD. Other paragraphs are recommended and may be deviated from, done as part of other actions or done with accepted methods different from those given in the Service Bulletin, as long as the RC paragraphs can be done and the aircraft can be put back into a serviceable condition.

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 23 6

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# @A310 SERVICE BULLETIN
Task Associated Data **CONF 001 Zone 120 137 138 500 512 520 524 573 600 612 620 624 673 Access Panel 512HB 513QL 513RR 612HB 613QL 613RR 624KB 672AZ 672BZ Manpower TOTAL MANHOURS 54.25 ELAPSED TIME (HOURS) 30.75 **CONF 002 Zone 120 137 138 500 512 520 573 600 612 620 624 673 Access Panel 512HB 513QL 513RR 612HB 613QL 613RR 624KB 672AZ 672BZ Manpower TOTAL MANHOURS 49.50 ELAPSED TIME (HOURS) 29.50 **CONF 003 Zone 120 137 138 500 512 520 524 573 600 612 620 624 673 Access Panel 512HB 513QL 513RR 612HB 613QL 613RR 624KB 672AZ 672BZ Manpower TOTAL MANHOURS 54.25 ELAPSED TIME (HOURS) 34.00 **CONF 004 Zone 120 137 138 500 512 520 524 573 575 600 612 620 624 673 Access Panel 512HB 513QL 513RR 612HB 613QL 613RR 624KB 672AZ 672BZ Manpower TOTAL MANHOURS 55.50 ELAPSED TIME (HOURS) 31.25

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 24 6

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# @A310 SERVICE BULLETIN
**CONF ALL A. GENERAL **CONF 001 (1) Subtask 242105-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 06-31-53, Page Block 001 06-41-53, Page Block 001 06-41-57, Page Block 001 20-23-12, Page Block 001 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-25-51 20-33-41 20-33-44 Standards Manual (SM) Structural Repair Manual (SRM) 51-40-21 51-40-30 51-40-50 51-43-00 (a) For the specification of materials (Mat. No.) that you must use in this Service Bulletin refer to Consumable Materials List (CML). (b) For the frames (FR) identification (Refer to AMM 06-31-53, Page Block 001). (c) For the identification of zones (Refer to AMM 06-21-00, Page Block 001). (d) For the identification of the access panels (Refer to AMM 06-41-53, Page Block 001 and AMM 06-41-57, Page Block 001). (e) Tag all the parts you must remove and retain to make the subsequent installation easier. (f) Put all the retained hardware in identified plastic bags and attach the bags to the related unit. (g) 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 the Standards Manual (SM). The SM will give you the correct part number to part number relationship. (h) To torque tighten the hydraulic line unions (Refer to AMM 20-23-12, Page Block 001). (i) Use a non-metallic spatula to remove the sealant. DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 25 6

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# @A310 SERVICE BULLETIN (j) Remove/install the fasteners (Refer to SRM 51-40-21). (k) For standard torque value (Refer to SRM 51-43-00). (l) For fasteners spacing and margin (Refer to SRM 51-40-50). (m) For alternative and substitute fasteners (Refer to SRM 51-40-30). (n) For the cable tie application and tooling (Refer to ESPM 20-33-44 and ESPM 20-25-51). (o) For the cable support and tooling (Refer to ESPM 20-33-41). (p) When you install protective electrical conduit : - Deburr the ends after you have cut it to the correct size. - At the lowest part of a cable loop make two cut-outs in the conduit to give drainage. - Cut the conduit before installation to make sure you do not damage the electrical cables. - Where necessary, install cable ties from between 13 mm and 15 mm (0.51 and 0.59 in.) from the cut ends of the conduit, to give support. - Where necessary, attach the conduit to the aircraft structure or to existing cable harnesses, with the cable ties supplied. (q) Install Service Bulletin identification placards at each end of new or modified electrical wires in a position where they can be easily seen and at approximately every 1.50 m (59.0 in.). (2) Subtask 242105-910-401-001 - Standard Practices Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 06-31-53, Page Block 001 06-41-00, Page Block 001 20-21-12, Page Block 001 Consumable Material List (CML) Structural Repair Manual (SRM) 51-23-00 51-24-00 51-40-20 51-40-21 51-40-30 51-40-40 (a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 26 6

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# @A310 SERVICE BULLETIN (b) For the identification of zones, refer to AMM 06-21-00, Page Block 001. (c) For the identification of access panels, refer to AMM 06-41-00, Page Block 001. (d) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to Consumable Material List (CML). (e) To torque tighten the standard threaded fasteners, refer to AMM Task 20-21-12, Page Block 001. (f) Remove and install fasteners in accordance with SRM 51-40-20. (g) Obtain fastener hole diameters and drill data in accordance with SRM 51-40-40. (h) Obtain alternative and substitute fastener data, in accordance with SRM 51-40-30. (i) Remove and install fasteners in accordance with SRM 51-40-20. (j) For the drilling of rivet holes: - Use a soft lead pencil and make marks to show the position of the rivet holes. - Make sure that you have the correct edge clearance before you drill the fastener holes. - If not shown otherwise the tolerance for rivet holes is +0.1 mm (+0.004 in). - Transfer-drill the existing holes with a pilot drill and a drill bush. - Deburr the holes after you have drilled them. - Cut the rivets to the correct length, as necessary. - When you remove fasteners you must be careful that you do not damage the holes in the structure. - Drill new fastener holes with a pilot drill of 2.5 mm (0.098 in) diameter. Increase the hole diameter to the correct size for the fastener which you must install. (k) Apply sealant in accordance with SRM 51-24-00. (l) Apply interfay sealant in accordance with SRM 51-24-00. (m) Renew the protective in accordance with SRM 51-23-00. (3) Subtask 242105-910-201-001 - Standard Practices Work Zones and Access Panels Zone Access/Work location 120

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 27 6

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# @A310 SERVICE BULLETIN
Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required Lint-Free Cotton Cloth 19-003 As required References Consumable Material List (CML) Structural Repair Manual (SRM) 51-77-10 (a) If necessary, clean the work area with: Solvent General Purpose 11-026 As required
Lint-Free Cotton Cloth 19-003 As required (b) Use the curing cycle of the Two Part Paste Adhesive, Mat. No. 08-078, in accordance with SRM 51-77-10. (4) Subtask 242105-839-201-001 - 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 242105-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 06-31-53, Page Block 001 06-41-53, Page Block 001 06-41-57, Page Block 001 20-23-12, Page Block 001 Consumable Material List (CML)

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 28 6

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# @A310 SERVICE BULLETIN

References Elec. Std. Practices Manual (ESPM) 20-25-51 20-33-41 20-33-44 Standards Manual (SM) Structural Repair Manual (SRM) 51-40-21 51-40-30 51-40-50 51-43-00 (a) For the specification of materials (Mat. No.) that you must use in this Service Bulletin refer to Consumable Materials List (CML). (b) For the frames (FR) identification (Refer to AMM 06-31-53, Page Block 001). (c) For the identification of zones (Refer to AMM 06-21-00, Page Block 001). (d) For the identification of the access panels (Refer to AMM 06-41-53, Page Block 001 and AMM 06-41-57, Page Block 001). (e) Tag all the parts you must remove and retain to make the subsequent installation easier. (f) Put all the retained hardware in identified plastic bags and attach the bags to the related unit. (g) 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 the Standards Manual (SM). The SM will give you the correct part number to part number relationship. (h) To torque tighten the hydraulic line unions (Refer to AMM 20-23-12, Page Block 001). (i) Use a non-metallic spatula to remove the sealant. (j) Remove/install the fasteners (Refer to SRM 51-40-21). (k) For standard torque value (Refer to SRM 51-43-00). (l) For fasteners spacing and margin (Refer to SRM 51-40-50). (m) For alternative and substitute fasteners (Refer to SRM 51-40-30). (n) For the cable tie application and tooling (Refer to ESPM 20-33-44 and ESPM 20-25-51). (o) For the cable support and tooling (Refer to ESPM 20-33-41). (p) When you install protective electrical conduit : - Deburr the ends after you have cut it to the correct size.

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 29 6

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# @A310 SERVICE BULLETIN - At the lowest part of a cable loop make two cut-outs in the conduit to give drainage. - Cut the conduit before installation to make sure you do not damage the electrical cables. - Where necessary, install cable ties from between 13 mm and 15 mm (0.51 and 0.59 in.) from the cut ends of the conduit, to give support. - Where necessary, attach the conduit to the aircraft structure or to existing cable harnesses, with the cable ties supplied. (q) Install Service Bulletin identification placards at each end of new or modified electrical wires in a position where they can be easily seen and at approximately every 1.50 m (59.0 in.). (2) Subtask 242105-910-401-001 - Standard Practices Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 06-31-53, Page Block 001 06-41-00, Page Block 001 20-21-12, Page Block 001 Consumable Material List (CML) Structural Repair Manual (SRM) 51-23-00 51-24-00 51-40-20 51-40-21 51-40-30 51-40-40 (a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (b) For the identification of zones, refer to AMM 06-21-00, Page Block 001. (c) For the identification of access panels, refer to AMM 06-41-00, Page Block 001. (d) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to Consumable Material List (CML). (e) To torque tighten the standard threaded fasteners, refer to AMM Task 20-21-12, Page Block 001. (f) Remove and install fasteners in accordance with SRM 51-40-20. (g) Obtain fastener hole diameters and drill data in accordance with SRM 51-40-40. (h) Obtain alternative and substitute fastener data, in accordance with SRM 51-40-30. (i) Remove and install fasteners in accordance with SRM 51-40-20. DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 30 6

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# @A310 SERVICE BULLETIN (j) For the drilling of rivet holes: - Use a soft lead pencil and make marks to show the position of the rivet holes. - Make sure that you have the correct edge clearance before you drill the fastener holes. - If not shown otherwise the tolerance for rivet holes is +0.1 mm (+0.004 in). - Transfer-drill the existing holes with a pilot drill and a drill bush. - Deburr the holes after you have drilled them. - Cut the rivets to the correct length, as necessary. - When you remove fasteners you must be careful that you do not damage the holes in the structure. - Drill new fastener holes with a pilot drill of 2.5 mm (0.098 in) diameter. Increase the hole diameter to the correct size for the fastener which you must install. (k) Apply sealant in accordance with SRM 51-24-00. (l) Apply interfay sealant in accordance with SRM 51-24-00. (m) Renew the protective in accordance with SRM 51-23-00. (3) Subtask 242105-910-201-001 - Standard Practices Work Zones and Access Panels Zone Access/Work location 120 Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required Lint-Free Cotton Cloth 19-003 As required References Consumable Material List (CML) Structural Repair Manual (SRM) 51-77-10

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 31 6

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# @A310 SERVICE BULLETIN (a) If necessary, clean the work area with: Solvent General Purpose 11-026 As required
Lint-Free Cotton Cloth 19-003 As required (b) Use the curing cycle of the Two Part Paste Adhesive, Mat. No. 08-078, in accordance with SRM 51-77-10. (4) Subtask 242105-839-201-001 - 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 242105-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 06-31-53, Page Block 001 06-41-53, Page Block 001 06-41-57, Page Block 001 20-23-12, Page Block 001 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-25-51 20-33-41 20-33-44 Standards Manual (SM) Structural Repair Manual (SRM) 51-40-21 51-40-30 51-40-50 51-43-00 (a) For the specification of materials (Mat. No.) that you must use in this Service Bulletin refer to Consumable Materials List (CML). (b) For the frames (FR) identification (Refer to AMM 06-31-53, Page Block 001). (c) For the identification of zones (Refer to AMM 06-21-00, Page Block 001). (d) For the identification of the access panels (Refer to AMM 06-41-53, Page Block 001 and AMM 06-41-57, Page Block 001).

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 32 6

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# @A310 SERVICE BULLETIN (e) Tag all the parts you must remove and retain to make the subsequent installation easier. (f) Put all the retained hardware in identified plastic bags and attach the bags to the related unit. (g) 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 the Standards Manual (SM). The SM will give you the correct part number to part number relationship. (h) To torque tighten the hydraulic line unions (Refer to AMM 20-23-12, Page Block 001). (i) Use a non-metallic spatula to remove the sealant. (j) Remove/install the fasteners (Refer to SRM 51-40-21). (k) For standard torque value (Refer to SRM 51-43-00). (l) For fasteners spacing and margin (Refer to SRM 51-40-50). (m) For alternative and substitute fasteners (Refer to SRM 51-40-30). (n) For the cable tie application and tooling (Refer to ESPM 20-33-44 and ESPM 20-25-51). (o) For the cable support and tooling (Refer to ESPM 20-33-41). (p) When you install protective electrical conduit : - Deburr the ends after you have cut it to the correct size. - At the lowest part of a cable loop make two cut-outs in the conduit to give drainage. - Cut the conduit before installation to make sure you do not damage the electrical cables. - Where necessary, install cable ties from between 13 mm and 15 mm (0.51 and 0.59 in.) from the cut ends of the conduit, to give support. - Where necessary, attach the conduit to the aircraft structure or to existing cable harnesses, with the cable ties supplied. (q) Install Service Bulletin identification placards at each end of new or modified electrical wires in a position where they can be easily seen and at approximately every 1.50 m (59.0 in.). (2) Subtask 242105-910-401-001 - Standard Practices Manpower Resources Skills AIRFRAME
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 33 6

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# @A310 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 06-31-53, Page Block 001 06-41-00, Page Block 001 20-21-12, Page Block 001 Consumable Material List (CML) Structural Repair Manual (SRM) 51-23-00 51-24-00 51-40-20 51-40-21 51-40-30 51-40-40 (a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (b) For the identification of zones, refer to AMM 06-21-00, Page Block 001. (c) For the identification of access panels, refer to AMM 06-41-00, Page Block 001. (d) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to Consumable Material List (CML). (e) To torque tighten the standard threaded fasteners, refer to AMM Task 20-21-12, Page Block 001. (f) Remove and install fasteners in accordance with SRM 51-40-20. (g) Obtain fastener hole diameters and drill data in accordance with SRM 51-40-40. (h) Obtain alternative and substitute fastener data, in accordance with SRM 51-40-30. (i) Remove and install fasteners in accordance with SRM 51-40-20. (j) For the drilling of rivet holes: - Use a soft lead pencil and make marks to show the position of the rivet holes. - Make sure that you have the correct edge clearance before you drill the fastener holes. - If not shown otherwise the tolerance for rivet holes is +0.1 mm (+0.004 in). - Transfer-drill the existing holes with a pilot drill and a drill bush. - Deburr the holes after you have drilled them. - Cut the rivets to the correct length, as necessary. - When you remove fasteners you must be careful that you do not damage the holes in the structure.

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 34 6

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# @A310 SERVICE BULLETIN - Drill new fastener holes with a pilot drill of 2.5 mm (0.098 in) diameter. Increase the hole diameter to the correct size for the fastener which you must install. (k) Apply sealant in accordance with SRM 51-24-00. (l) Apply interfay sealant in accordance with SRM 51-24-00. (m) Renew the protective in accordance with SRM 51-23-00. (3) Subtask 242105-910-201-001 - Standard Practices Work Zones and Access Panels Zone Access/Work location 120 Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required Lint-Free Cotton Cloth 19-003 As required References Consumable Material List (CML) Structural Repair Manual (SRM) 51-77-10 (a) If necessary, clean the work area with: Solvent General Purpose 11-026 As required
Lint-Free Cotton Cloth 19-003 As required (b) Use the curing cycle of the Two Part Paste Adhesive, Mat. No. 08-078, in accordance with SRM 51-77-10. (4) Subtask 242105-839-201-001 - 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: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 35 6

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# @A310 SERVICE BULLETIN
**CONF 004 (1) Subtask 242105-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 06-31-53, Page Block 001 06-41-53, Page Block 001 06-41-57, Page Block 001 20-23-12, Page Block 001 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-25-51 20-33-41 20-33-44 Standards Manual (SM) Structural Repair Manual (SRM) 51-40-21 51-40-30 51-40-50 51-43-00 (a) For the specification of materials (Mat. No.) that you must use in this Service Bulletin refer to Consumable Materials List (CML). (b) For the frames (FR) identification (Refer to AMM 06-31-53, Page Block 001). (c) For the identification of zones (Refer to AMM 06-21-00, Page Block 001). (d) For the identification of the access panels (Refer to AMM 06-41-53, Page Block 001 and AMM 06-41-57, Page Block 001). (e) Tag all the parts you must remove and retain to make the subsequent installation easier. (f) Put all the retained hardware in identified plastic bags and attach the bags to the related unit. (g) 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 the Standards Manual (SM). The SM will give you the correct part number to part number relationship. (h) To torque tighten the hydraulic line unions (Refer to AMM 20-23-12, Page Block 001). (i) Use a non-metallic spatula to remove the sealant. (j) Remove/install the fasteners (Refer to SRM 51-40-21). (k) For standard torque value (Refer to SRM 51-43-00).
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 36 6

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# @A310 SERVICE BULLETIN (l) For fasteners spacing and margin (Refer to SRM 51-40-50). (m) For alternative and substitute fasteners (Refer to SRM 51-40-30). (n) For the cable tie application and tooling (Refer to ESPM 20-33-44 and ESPM 20-25-51). (o) For the cable support and tooling (Refer to ESPM 20-33-41). (p) When you install protective electrical conduit : - Deburr the ends after you have cut it to the correct size. - At the lowest part of a cable loop make two cut-outs in the conduit to give drainage. - Cut the conduit before installation to make sure you do not damage the electrical cables. - Where necessary, install cable ties from between 13 mm and 15 mm (0.51 and 0.59 in.) from the cut ends of the conduit, to give support. - Where necessary, attach the conduit to the aircraft structure or to existing cable harnesses, with the cable ties supplied. (q) Install Service Bulletin identification placards at each end of new or modified electrical wires in a position where they can be easily seen and at approximately every 1.50 m (59.0 in.). (2) Subtask 242105-910-401-001 - Standard Practices Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 06-31-53, Page Block 001 06-41-00, Page Block 001 20-21-12, Page Block 001 Consumable Material List (CML) Structural Repair Manual (SRM) 51-23-00 51-24-00 51-40-20 51-40-21 51-40-30 51-40-40 (a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (b) For the identification of zones, refer to AMM 06-21-00, Page Block 001. (c) For the identification of access panels, refer to AMM 06-41-00, Page Block 001.
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 37 6

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# @A310 SERVICE BULLETIN (d) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to Consumable Material List (CML). (e) To torque tighten the standard threaded fasteners, refer to AMM Task 20-21-12, Page Block 001. (f) Remove and install fasteners in accordance with SRM 51-40-20. (g) Obtain fastener hole diameters and drill data in accordance with SRM 51-40-40. (h) Obtain alternative and substitute fastener data, in accordance with SRM 51-40-30. (i) Remove and install fasteners in accordance with SRM 51-40-20. (j) For the drilling of rivet holes: - Use a soft lead pencil and make marks to show the position of the rivet holes. - Make sure that you have the correct edge clearance before you drill the fastener holes. - If not shown otherwise the tolerance for rivet holes is +0.1 mm (+0.004 in). - Transfer-drill the existing holes with a pilot drill and a drill bush. - Deburr the holes after you have drilled them. - Cut the rivets to the correct length, as necessary. - When you remove fasteners you must be careful that you do not damage the holes in the structure. - Drill new fastener holes with a pilot drill of 2.5 mm (0.098 in) diameter. Increase the hole diameter to the correct size for the fastener which you must install. (k) Apply sealant in accordance with SRM 51-24-00. (l) Apply interfay sealant in accordance with SRM 51-24-00. (m) Renew the protective in accordance with SRM 51-23-00. (3) Subtask 242105-910-201-001 - Standard Practices Work Zones and Access Panels Zone Access/Work location 120 Manpower Resources Skills NON SPECIFIC

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 38 6

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# @A310 SERVICE BULLETIN
Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required Lint-Free Cotton Cloth 19-003 As required References Consumable Material List (CML) Structural Repair Manual (SRM) 51-77-10 (a) If necessary, clean the work area with: Solvent General Purpose 11-026 As required
Lint-Free Cotton Cloth 19-003 As required (b) Use the curing cycle of the Two Part Paste Adhesive, Mat. No. 08-078, in accordance with SRM 51-77-10. (4) Subtask 242105-839-201-001 - 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 242105-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 27-50-00, Page Block 301 29-10-00, Page Block 301 29-14-00, Page Block 301

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 39 6

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# @A310 SERVICE BULLETIN (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) Depressurize the Yellow Hydraulic System (Refer to AMM 29-10-00, Page Block 301 and AMM 29-14-00, Page Block 301). (e) Do the Job Set-up procedure as specified in the Extension and Retraction of Flaps with Aircraft System (Refer to AMM 27-50-00, Page Block 301). (2) Subtask 242105-010-001-001 - Remove/Open for Access Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-57, Page Block 001 27-50-00, Page Block 301 32-12-11, Page Block 301 53-15-63, Page Block 401 (a) Open the Main Landing Gear (MLG) door (Refer to AMM 32-12-11, Page Block 301). (b) Fully extend the flaps (Refer to AMM 27-50-00, Page Block 301). (c) Remove the access panels 572AB, 672AB, 572AZ, 572BZ, 572CZ, 572DZ, 572EZ, 572FZ, 572GZ, 672AZ, 672BZ, 672CZ, 672DZ, 672EZ, 672FZ and 672GZ (Refer to AMM 06-41-57, Page Block 001).

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 40 6

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# @A310 SERVICE BULLETIN (d) Remove the access panels 512FB, 612FB, 512BB, 612BB, 612DB, 513RR and 613RR (Refer to AMM 06-41-57, Page Block 001). (e) Remove all the necessary fairing panels (Refer to AMM 53-15-63, Page Block 401). (f) If necessary, remove the access panels 571BB, 571CB, 671BB and 671CB (Refer to AMM 06-41-57, Page Block 001). (g) If necessary, remove the access panels 513BL, 513DL, 513CL, 513EL, 513FL, 513ML, 613BR, 613DR, 613CR, 613ER, 613FR and 613HR (Refer to AMM 06-41-57, Page Block 001). (3) Subtask 242105-010-003-001 - Remove the Air Ducts and the Deflector in the LH Wings for access. Work Zones and Access Panels Zone Access/Work location 512 Access Panel 513RR, Panel 513QL Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-57, Page Block 001 36-11-00, Page Block 401 Fig. A-FCAAA Removal of Air Ducts and Reflector in the Wings for access Sheet 01 Sheet 02 Sheet 03 NOTE: This workstep is necessary to be done to access the raceway box to accomplish SUBTASK 242105-831-003 001 Modify the routing in the LH forward wing to fuselage fairing. . NOTE: Two persons are necessary for this access. (a) Remove the Air Ducts : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 Refer to AMM 36-11-00, Page Block 401 1 Duct Assy Item (70) Retain 1 Insulation Item (71) Retain 1 Tube Assy Item (72) Retain 1 Insulation Item (71) Retain 1 Tube Assy Item (73) Retain

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 41 6

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# @A310 SERVICE BULLETIN
NOTE: Retain the hardware. (b) Remove the Deflector : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 1 Shield Item (75) Retain 1 Bracket Item (74) Retain 1 Shield Assy Item (76) Retain NOTE: Retain the hardware. NOTE: Two persons necessary (one on the above and one on the lower side of the panel). (c) Remove the access panel 513QL (Refer to AMM 06-41-57, Page Block 001). (d) Remove the cover of the Raceway Box : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 03 1 Cover Item (77) Retain NOTE: Retain the hardware. (4) Subtask 242105-010-002-001 - Remove the Air Ducts and the Deflector in the RH Wings for access. Work Zones and Access Panels Zone Access/Work location 612 Access Panel 613RR, Panel 613QL Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-57, Page Block 001 36-11-00, Page Block 401 Fig. A-FCAAA Removal of Air Ducts and Reflector in the Wings for access Sheet 01 Sheet 02 Sheet 03 NOTE: Two persons are necessary for this access. (a) Remove the Air Ducts : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 Refer to AMM 36-11-00, Page Block 401
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 42 6

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

# @A310 SERVICE BULLETIN
1 Duct Assy Item (70) Retain 1 Insulation Item (71) Retain 1 Tube Assy Item (72) Retain 1 Insulation Item (71) Retain 1 Tube Assy Item (73) Retain NOTE: Retain the hardware. (b) Remove the Deflector : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 1 Shield Item (75) Retain 1 Bracket Item (74) Retain 1 Shield Assy Item (76) Retain NOTE: Retain the hardware. (c) Remove the access panel 613QL (Refer to AMM 06-41-57, Page Block 001). (d) Remove the cover of the Raceway Box : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 03 1 Cover Item (77) Retain NOTE: Retain the hardware. (5) Subtask 242105-010-004-001 - Remove two Hydraulic Pipes in the RH Wings for access. Work Zones and Access Panels Zone Access/Work location 673 Access Panel 672AZ, Panel 672BZ Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 29-00-00, Page Block 401 Fig. A-FCBAA Removal of Hydraulic Pipes for access Sheet 01 Sheet 02 Sheet 03 Sheet 04
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 43 6

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

# @A310 SERVICE BULLETIN
NOTE: This workstep is necessary before accomplishment of SUBTASK 242105-831-006 001 Modify the routing on the RH shroud box leading edge. . (a) Remove the hardware : Refer to Fig. A-FCBAA Sheet 01 , Fig. A-FCBAA Sheet 02, Fig. A-FCBAA Sheet 03 and Fig. A-FCBAA Sheet 04 1 Tie-Cable Item (62) Discard 1 Block Isolator Item (83) Retain 2 Bolt Item (80) Retain 2 Washer Item (81) Retain 2 Block Clamp Item (82) Retain (b) Remove the two Hydraulic Pipes : Refer to Fig. A-FCBAA Sheet 01 , Fig. A-FCBAA Sheet 02 and Fig. A-FCBAA Sheet 03 Refer to AMM 29-00-00, Page Block 401 1 Hydraulic Pipes Item (78) Retain 1 Hydraulic Pipes Item (79) Retain

(6) Subtask 242105-941-401-001 - Job Set-up Work Zones and Access Panels Zone Access/Work location 612 Access Panel 612HB 512 Access Panel 512HB 624 Access Panel 624KB Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 27-80-00, Page Block 301 29-10-00, Page Block 301 Structural Repair Manual (SRM) 51-40-21 51-40-40 51-75-10 (a) Fully extend slats, refer to AMM 27-80-00, Page Block 301.
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 44 6

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# @A310 SERVICE BULLETIN (b) Depressurize the hydraulic system, refer to AMM 29-10-00, Page Block 301. (c) Make sure the aircraft is electrically grounded, refer to AMM 24-00-00, Page Block 301. (d) In the cockpit, place warning notices in position not to operate the slats. (e) Put access platforms in position at zone(s) 512, 612 and 624. (f) Remove panels 612HB, 512HB and 624KB. (7) Subtask 242105-941-201-002 - JOB SET-UP Work Zones and Access Panels Zone Access/Work location 600 500 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-57, Page Block 001 WARNING: PUT WARNING NOTICES IN THE COCKPIT TO TELL PERSONS NOT TO OPERATE THE FLIGHT CONTROLS. THE MOVEMENT CAN CAUSE INJURY TO PERSONS. (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) Install the safety guard (PN 98A27503003000) on the flap and slat control lever.

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 45 6

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

# @A310 SERVICE BULLETIN (c) Put access platforms in position below the leading-edges of: - the LH wing at Zone 512 - the LH wing at Zone 524 - the RH wing at Zone 612 - the RH wing at Zone 624 (d) On the lower surface of the LH wing, remove the leading-edge access panels 512BB, 512CB, 512DB, 512GB and 512JB, refer to AMM 06-41-57, Page Block 001 as necessary. (e) On the lower surface of the LH wing, remove the leading-edge access panels 524BB, 524CB and 524KB, refer to AMM 06-41-57, Page Block 001 as necessary. (f) On the lower surface of the RH wing, remove the leading-edge access panels 612BB, 612CB, 612DB, 612GB, 612JB, refer to AMM 06-41-57, Page Block 001 as necessary. (g) On the lower surface of the RH wing, remove the leading-edge access panels 624BB and 624CB, refer to AMM 06-41-57, Page Block 001 as necessary. **CONF 002 (1) Subtask 242105-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 27-50-00, Page Block 301 29-10-00, Page Block 301 29-14-00, Page Block 301 (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.

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 46 6

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# @A310 SERVICE BULLETIN - 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) Depressurize the Yellow Hydraulic System (Refer to AMM 29-10-00, Page Block 301 and AMM 29-14-00, Page Block 301). (e) Do the Job Set-up procedure as specified in the Extension and Retraction of Flaps with Aircraft System (Refer to AMM 27-50-00, Page Block 301). (2) Subtask 242105-010-001-001 - Remove/Open for Access Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-57, Page Block 001 27-50-00, Page Block 301 32-12-11, Page Block 301 53-15-63, Page Block 401 (a) Open the Main Landing Gear (MLG) door (Refer to AMM 32-12-11, Page Block 301). (b) Fully extend the flaps (Refer to AMM 27-50-00, Page Block 301). (c) Remove the access panels 572AB, 672AB, 572AZ, 572BZ, 572CZ, 572DZ, 572EZ, 572FZ, 572GZ, 672AZ, 672BZ, 672CZ, 672DZ, 672EZ, 672FZ and 672GZ (Refer to AMM 06-41-57, Page Block 001). (d) Remove the access panels 512FB, 612FB, 512BB, 612BB, 612DB, 513RR and 613RR (Refer to AMM 06-41-57, Page Block 001). (e) Remove all the necessary fairing panels (Refer to AMM 53-15-63, Page Block 401). (f) If necessary, remove the access panels 571BB, 571CB, 671BB and 671CB (Refer to AMM 06-41-57, Page Block 001). (g) If necessary, remove the access panels 513BL, 513DL, 513CL, 513EL, 513FL, 513ML, 613BR, 613DR, 613CR, 613ER, 613FR and 613HR (Refer to AMM 06-41-57, Page Block 001).

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 47 6

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

# @A310 SERVICE BULLETIN (3) Subtask 242105-010-003-001 - Remove the Air Ducts and the Deflector in the LH Wings for access. Work Zones and Access Panels Zone Access/Work location 512 Access Panel 513RR, Panel 513QL Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-57, Page Block 001 36-11-00, Page Block 401 Fig. A-FCAAA Removal of Air Ducts and Reflector in the Wings for access Sheet 01 Sheet 02 Sheet 03 NOTE: This workstep is necessary to be done to access the raceway box to accomplish SUBTASK 242105-831-003 001 Modify the routing in the LH forward wing to fuselage fairing. . NOTE: Two persons are necessary for this access. (a) Remove the Air Ducts : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 Refer to AMM 36-11-00, Page Block 401 1 Duct Assy Item (70) Retain 1 Insulation Item (71) Retain 1 Tube Assy Item (72) Retain 1 Insulation Item (71) Retain 1 Tube Assy Item (73) Retain NOTE: Retain the hardware. (b) Remove the Deflector : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 1 Shield Item (75) Retain 1 Bracket Item (74) Retain 1 Shield Assy Item (76) Retain
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 48 6

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

# @A310 SERVICE BULLETIN
NOTE: Retain the hardware. NOTE: Two persons necessary (one on the above and one on the lower side of the panel). (c) Remove the access panel 513QL (Refer to AMM 06-41-57, Page Block 001). (d) Remove the cover of the Raceway Box : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 03 1 Cover Item (77) Retain NOTE: Retain the hardware. (4) Subtask 242105-010-002-001 - Remove the Air Ducts and the Deflector in the RH Wings for access. Work Zones and Access Panels Zone Access/Work location 612 Access Panel 613RR, Panel 613QL Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-57, Page Block 001 36-11-00, Page Block 401 Fig. A-FCAAA Removal of Air Ducts and Reflector in the Wings for access Sheet 01 Sheet 02 Sheet 03 NOTE: Two persons are necessary for this access. (a) Remove the Air Ducts : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 Refer to AMM 36-11-00, Page Block 401 1 Duct Assy Item (70) Retain 1 Insulation Item (71) Retain 1 Tube Assy Item (72) Retain 1 Insulation Item (71) Retain 1 Tube Assy Item (73) Retain NOTE: Retain the hardware.
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 49 6

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

# @A310 SERVICE BULLETIN (b) Remove the Deflector : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 1 Shield Item (75) Retain 1 Bracket Item (74) Retain 1 Shield Assy Item (76) Retain NOTE: Retain the hardware. (c) Remove the access panel 613QL (Refer to AMM 06-41-57, Page Block 001). (d) Remove the cover of the Raceway Box : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 03 1 Cover Item (77) Retain NOTE: Retain the hardware. (5) Subtask 242105-010-004-001 - Remove two Hydraulic Pipes in the RH Wings for access. Work Zones and Access Panels Zone Access/Work location 673 Access Panel 672AZ, Panel 672BZ Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 29-00-00, Page Block 401 Fig. A-FCBAA Removal of Hydraulic Pipes for access Sheet 01 Sheet 02 Sheet 03 Sheet 04 NOTE: This workstep is necessary before accomplishment of SUBTASK 242105-831-006 001 Modify the routing on the RH shroud box leading edge. . (a) Remove the hardware : Refer to Fig. A-FCBAA Sheet 01 , Fig. A-FCBAA Sheet 02, Fig. A-FCBAA Sheet 03 and Fig. A-FCBAA Sheet 04 1 Tie-Cable Item (62) Discard 1 Block Isolator Item (83) Retain
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 50 6

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# @A310 SERVICE BULLETIN
2 Bolt Item (80) Retain 2 Washer Item (81) Retain 2 Block Clamp Item (82) Retain (b) Remove the two Hydraulic Pipes : Refer to Fig. A-FCBAA Sheet 01 , Fig. A-FCBAA Sheet 02 and Fig. A-FCBAA Sheet 03 Refer to AMM 29-00-00, Page Block 401 1 Hydraulic Pipes Item (78) Retain 1 Hydraulic Pipes Item (79) Retain

(6) Subtask 242105-941-401-001 - Job Set-up Work Zones and Access Panels Zone Access/Work location 612 Access Panel 612HB 512 Access Panel 512HB 624 Access Panel 624KB Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 27-80-00, Page Block 301 29-10-00, Page Block 301 Structural Repair Manual (SRM) 51-40-21 51-40-40 51-75-10 (a) Fully extend slats, refer to AMM 27-80-00, Page Block 301. (b) Depressurize the hydraulic system, refer to AMM 29-10-00, Page Block 301. (c) Make sure the aircraft is electrically grounded, refer to AMM 24-00-00, Page Block 301. (d) In the cockpit, place warning notices in position not to operate the slats. (e) Put access platforms in position at zone(s) 512, 612 and 624. (f) Remove panels 612HB, 512HB and 624KB.

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 51 6

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# @A310 SERVICE BULLETIN (7) Subtask 242105-941-201-003 - JOB SET-UP Work Zones and Access Panels Zone Access/Work location 600 500 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-57, Page Block 001 WARNING: PUT WARNING NOTICES IN THE COCKPIT TO TELL PERSONS NOT TO OPERATE THE FLIGHT CONTROLS. THE MOVEMENT CAN CAUSE INJURY TO PERSONS. (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) Install the safety guard (PN 98A27503003000) on the flap and slat control lever. (c) Put access platforms in position below the leading-edges of: - the LH wing at Zone 512 - the LH wing at Zone 524 - the RH wing at Zone 624 (d) On the lower surface of the LH wing, remove the leading-edge access panels 512BB, 512CB, 512DB, 512GB and 512JB as necessary, refer to AMM 06-41-57, Page Block 001.

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 52 6

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# @A310 SERVICE BULLETIN (e) On the lower surface of the LH wing, remove the leading-edge access panels 524BB, 524CB and 524KB as necessary, refer to AMM 06-41-57, Page Block 001. (f) On the lower surface of the RH wing, remove the leading-edge access panels 624BB and 624CB as necessary, refer to AMM 06-41-57, Page Block 001. **CONF 003 (1) Subtask 242105-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 27-50-00, Page Block 301 29-10-00, Page Block 301 29-14-00, Page Block 301 (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) Depressurize the Yellow Hydraulic System (Refer to AMM 29-10-00, Page Block 301 and AMM 29-14-00, Page Block 301). (e) Do the Job Set-up procedure as specified in the Extension and Retraction of Flaps with Aircraft System (Refer to AMM 27-50-00, Page Block 301).

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 53 6

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

# @A310 SERVICE BULLETIN (2) Subtask 242105-010-001-001 - Remove/Open for Access Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-57, Page Block 001 27-50-00, Page Block 301 32-12-11, Page Block 301 53-15-63, Page Block 401 (a) Open the Main Landing Gear (MLG) door (Refer to AMM 32-12-11, Page Block 301). (b) Fully extend the flaps (Refer to AMM 27-50-00, Page Block 301). (c) Remove the access panels 572AB, 672AB, 572AZ, 572BZ, 572CZ, 572DZ, 572EZ, 572FZ, 572GZ, 672AZ, 672BZ, 672CZ, 672DZ, 672EZ, 672FZ and 672GZ (Refer to AMM 06-41-57, Page Block 001). (d) Remove the access panels 512FB, 612FB, 512BB, 612BB, 612DB, 513RR and 613RR (Refer to AMM 06-41-57, Page Block 001). (e) Remove all the necessary fairing panels (Refer to AMM 53-15-63, Page Block 401). (f) If necessary, remove the access panels 571BB, 571CB, 671BB and 671CB (Refer to AMM 06-41-57, Page Block 001). (g) If necessary, remove the access panels 513BL, 513DL, 513CL, 513EL, 513FL, 513ML, 613BR, 613DR, 613CR, 613ER, 613FR and 613HR (Refer to AMM 06-41-57, Page Block 001). (3) Subtask 242105-010-003-001 - Remove the Air Ducts and the Deflector in the LH Wings for access. Work Zones and Access Panels Zone Access/Work location 512 Access Panel 513RR, Panel 513QL Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-57, Page Block 001 36-11-00, Page Block 401 Fig. A-FCAAA Removal of Air Ducts and Reflector in the Wings for access Sheet 01 Sheet 02 Sheet 03 NOTE: This workstep is necessary to be done to access the raceway box to accomplish SUBTASK 242105-831-003 001 Modify the routing in the LH forward wing to fuselage fairing. . DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 54 6

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

# @A310 SERVICE BULLETIN
NOTE: Two persons are necessary for this access. (a) Remove the Air Ducts : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 Refer to AMM 36-11-00, Page Block 401 1 Duct Assy Item (70) Retain 1 Insulation Item (71) Retain 1 Tube Assy Item (72) Retain 1 Insulation Item (71) Retain 1 Tube Assy Item (73) Retain NOTE: Retain the hardware. (b) Remove the Deflector : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 1 Shield Item (75) Retain 1 Bracket Item (74) Retain 1 Shield Assy Item (76) Retain NOTE: Retain the hardware. NOTE: Two persons necessary (one on the above and one on the lower side of the panel). (c) Remove the access panel 513QL (Refer to AMM 06-41-57, Page Block 001). (d) Remove the cover of the Raceway Box : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 03 1 Cover Item (77) Retain NOTE: Retain the hardware. (4) Subtask 242105-010-002-001 - Remove the Air Ducts and the Deflector in the RH Wings for access. Work Zones and Access Panels Zone Access/Work location 612 Access Panel 613RR, Panel 613QL
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 55 6

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# @A310 SERVICE BULLETIN
Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-57, Page Block 001 36-11-00, Page Block 401 Fig. A-FCAAA Removal of Air Ducts and Reflector in the Wings for access Sheet 01 Sheet 02 Sheet 03 NOTE: Two persons are necessary for this access. (a) Remove the Air Ducts : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 Refer to AMM 36-11-00, Page Block 401 1 Duct Assy Item (70) Retain 1 Insulation Item (71) Retain 1 Tube Assy Item (72) Retain 1 Insulation Item (71) Retain 1 Tube Assy Item (73) Retain NOTE: Retain the hardware. (b) Remove the Deflector : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 1 Shield Item (75) Retain 1 Bracket Item (74) Retain 1 Shield Assy Item (76) Retain NOTE: Retain the hardware. (c) Remove the access panel 613QL (Refer to AMM 06-41-57, Page Block 001). (d) Remove the cover of the Raceway Box : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 03 1 Cover Item (77) Retain NOTE: Retain the hardware. DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 56 6

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# @A310 SERVICE BULLETIN (5) Subtask 242105-010-004-001 - Remove two Hydraulic Pipes in the RH Wings for access. Work Zones and Access Panels Zone Access/Work location 673 Access Panel 672AZ, Panel 672BZ Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 29-00-00, Page Block 401 Fig. A-FCBAA Removal of Hydraulic Pipes for access Sheet 01 Sheet 02 Sheet 03 Sheet 04 NOTE: This workstep is necessary before accomplishment of SUBTASK 242105-831-006 001 Modify the routing on the RH shroud box leading edge. . (a) Remove the hardware : Refer to Fig. A-FCBAA Sheet 01 , Fig. A-FCBAA Sheet 02, Fig. A-FCBAA Sheet 03 and Fig. A-FCBAA Sheet 04 1 Tie-Cable Item (62) Discard 1 Block Isolator Item (83) Retain 2 Bolt Item (80) Retain 2 Washer Item (81) Retain 2 Block Clamp Item (82) Retain (b) Remove the two Hydraulic Pipes : Refer to Fig. A-FCBAA Sheet 01 , Fig. A-FCBAA Sheet 02 and Fig. A-FCBAA Sheet 03 Refer to AMM 29-00-00, Page Block 401 1 Hydraulic Pipes Item (78) Retain 1 Hydraulic Pipes Item (79) Retain

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 57 6

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# @A310 SERVICE BULLETIN (6) Subtask 242105-941-401-001 - Job Set-up Work Zones and Access Panels Zone Access/Work location 612 Access Panel 612HB 512 Access Panel 512HB 624 Access Panel 624KB Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 27-80-00, Page Block 301 29-10-00, Page Block 301 Structural Repair Manual (SRM) 51-40-21 51-40-40 51-75-10 (a) Fully extend slats, refer to AMM 27-80-00, Page Block 301. (b) Depressurize the hydraulic system, refer to AMM 29-10-00, Page Block 301. (c) Make sure the aircraft is electrically grounded, refer to AMM 24-00-00, Page Block 301. (d) In the cockpit, place warning notices in position not to operate the slats. (e) Put access platforms in position at zone(s) 512, 612 and 624. (f) Remove panels 612HB, 512HB and 624KB. (7) Subtask 242105-941-201-004 - Job Set-up Work Zones and Access Panels Zone Access/Work location 600 500 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-57, Page Block 001 WARNING: PUT WARNING NOTICES IN THE COCKPIT TO TELL PERSONS NOT TO OPERATE THE FLIGHT CONTROLS. THE MOVEMENT CAN CAUSE INJURY TO PERSONS.

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 58 6

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# @A310 SERVICE BULLETIN (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) Install the safety guard (PN 98A27503003000) on the flap and slat control lever. (c) Put access platforms in position below the leading-edges of: - the LH wing at Zone 512 - the LH wing at Zone 524 - the RH wing at Zone 612 - the RH wing at Zone 624 (d) On the lower surface of the LH wing, remove the leading-edge access panels 512BB, 512CB, 512DB, 512GB and 512JB as necessary, refer to AMM 06-41-57, Page Block 001. (e) On the lower surface of the LH wing, remove the leading-edge access panels 524BB, 524CB and 524KB as necessary, refer to AMM 06-41-57, Page Block 001. (f) On the lower surface of the RH wing, remove the leading-edge access panels 612BB, 612CB, 612DB, 612GB, 612JB as necessary, refer to AMM 06-41-57, Page Block 001. (g) On the lower surface of the RH wing, remove the leading-edge access panels 624BB and 624CB as necessary, refer to AMM 06-41-57, Page Block 001.

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 59 6

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# @A310 SERVICE BULLETIN
**CONF 004 (1) Subtask 242105-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 27-50-00, Page Block 301 29-10-00, Page Block 301 29-14-00, Page Block 301 (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) Depressurize the Yellow Hydraulic System (Refer to AMM 29-10-00, Page Block 301 and AMM 29-14-00, Page Block 301). (e) Do the Job Set-up procedure as specified in the Extension and Retraction of Flaps with Aircraft System (Refer to AMM 27-50-00, Page Block 301). (2) Subtask 242105-010-001-001 - Remove/Open for Access Manpower Resources Skills NON SPECIFIC

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 60 6

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# @A310 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 06-41-57, Page Block 001 27-50-00, Page Block 301 32-12-11, Page Block 301 53-15-63, Page Block 401 (a) Open the Main Landing Gear (MLG) door (Refer to AMM 32-12-11, Page Block 301). (b) Fully extend the flaps (Refer to AMM 27-50-00, Page Block 301). (c) Remove the access panels 572AB, 672AB, 572AZ, 572BZ, 572CZ, 572DZ, 572EZ, 572FZ, 572GZ, 672AZ, 672BZ, 672CZ, 672DZ, 672EZ, 672FZ and 672GZ (Refer to AMM 06-41-57, Page Block 001). (d) Remove the access panels 512FB, 612FB, 512BB, 612BB, 612DB, 513RR and 613RR (Refer to AMM 06-41-57, Page Block 001). (e) Remove all the necessary fairing panels (Refer to AMM 53-15-63, Page Block 401). (f) If necessary, remove the access panels 571BB, 571CB, 671BB and 671CB (Refer to AMM 06-41-57, Page Block 001). (g) If necessary, remove the access panels 513BL, 513DL, 513CL, 513EL, 513FL, 513ML, 613BR, 613DR, 613CR, 613ER, 613FR and 613HR (Refer to AMM 06-41-57, Page Block 001). (3) Subtask 242105-010-003-001 - Remove the Air Ducts and the Deflector in the LH Wings for access. Work Zones and Access Panels Zone Access/Work location 512 Access Panel 513RR, Panel 513QL Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-57, Page Block 001 36-11-00, Page Block 401 Fig. A-FCAAA Removal of Air Ducts and Reflector in the Wings for access Sheet 01 Sheet 02 Sheet 03 NOTE: This workstep is necessary to be done to access the raceway box to accomplish SUBTASK 242105-831-003 001 Modify the routing in the LH forward wing to fuselage fairing. . NOTE: Two persons are necessary for this access.

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 61 6

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# @A310 SERVICE BULLETIN (a) Remove the Air Ducts : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 Refer to AMM 36-11-00, Page Block 401 1 Duct Assy Item (70) Retain 1 Insulation Item (71) Retain 1 Tube Assy Item (72) Retain 1 Insulation Item (71) Retain 1 Tube Assy Item (73) Retain NOTE: Retain the hardware. (b) Remove the Deflector : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 1 Shield Item (75) Retain 1 Bracket Item (74) Retain 1 Shield Assy Item (76) Retain NOTE: Retain the hardware. NOTE: Two persons necessary (one on the above and one on the lower side of the panel). (c) Remove the access panel 513QL (Refer to AMM 06-41-57, Page Block 001). (d) Remove the cover of the Raceway Box : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 03 1 Cover Item (77) Retain NOTE: Retain the hardware. (4) Subtask 242105-010-002-001 - Remove the Air Ducts and the Deflector in the RH Wings for access. Work Zones and Access Panels Zone Access/Work location 612 Access Panel 613RR, Panel 613QL

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 62 6

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# @A310 SERVICE BULLETIN
Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-57, Page Block 001 36-11-00, Page Block 401 Fig. A-FCAAA Removal of Air Ducts and Reflector in the Wings for access Sheet 01 Sheet 02 Sheet 03 NOTE: Two persons are necessary for this access. (a) Remove the Air Ducts : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 Refer to AMM 36-11-00, Page Block 401 1 Duct Assy Item (70) Retain 1 Insulation Item (71) Retain 1 Tube Assy Item (72) Retain 1 Insulation Item (71) Retain 1 Tube Assy Item (73) Retain NOTE: Retain the hardware. (b) Remove the Deflector : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 1 Shield Item (75) Retain 1 Bracket Item (74) Retain 1 Shield Assy Item (76) Retain NOTE: Retain the hardware. (c) Remove the access panel 613QL (Refer to AMM 06-41-57, Page Block 001). (d) Remove the cover of the Raceway Box : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 03 1 Cover Item (77) Retain NOTE: Retain the hardware. DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 63 6

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# @A310 SERVICE BULLETIN (5) Subtask 242105-010-004-001 - Remove two Hydraulic Pipes in the RH Wings for access. Work Zones and Access Panels Zone Access/Work location 673 Access Panel 672AZ, Panel 672BZ Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 29-00-00, Page Block 401 Fig. A-FCBAA Removal of Hydraulic Pipes for access Sheet 01 Sheet 02 Sheet 03 Sheet 04 NOTE: This workstep is necessary before accomplishment of SUBTASK 242105-831-006 001 Modify the routing on the RH shroud box leading edge. . (a) Remove the hardware : Refer to Fig. A-FCBAA Sheet 01 , Fig. A-FCBAA Sheet 02, Fig. A-FCBAA Sheet 03 and Fig. A-FCBAA Sheet 04 1 Tie-Cable Item (62) Discard 1 Block Isolator Item (83) Retain 2 Bolt Item (80) Retain 2 Washer Item (81) Retain 2 Block Clamp Item (82) Retain (b) Remove the two Hydraulic Pipes : Refer to Fig. A-FCBAA Sheet 01 , Fig. A-FCBAA Sheet 02 and Fig. A-FCBAA Sheet 03 Refer to AMM 29-00-00, Page Block 401 1 Hydraulic Pipes Item (78) Retain 1 Hydraulic Pipes Item (79) Retain

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 64 6

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# @A310 SERVICE BULLETIN (6) Subtask 242105-941-401-001 - Job Set-up Work Zones and Access Panels Zone Access/Work location 612 Access Panel 612HB 512 Access Panel 512HB 624 Access Panel 624KB Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 27-80-00, Page Block 301 29-10-00, Page Block 301 Structural Repair Manual (SRM) 51-40-21 51-40-40 51-75-10 (a) Fully extend slats, refer to AMM 27-80-00, Page Block 301. (b) Depressurize the hydraulic system, refer to AMM 29-10-00, Page Block 301. (c) Make sure the aircraft is electrically grounded, refer to AMM 24-00-00, Page Block 301. (d) In the cockpit, place warning notices in position not to operate the slats. (e) Put access platforms in position at zone(s) 512, 612 and 624. (f) Remove panels 612HB, 512HB and 624KB. (7) Subtask 242105-941-201-005 - JOB SET-UP Work Zones and Access Panels Zone Access/Work location 600 500 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-57, Page Block 001 WARNING: PUT WARNING NOTICES IN THE COCKPIT TO TELL PERSONS NOT TO OPERATE THE FLIGHT CONTROLS. THE MOVEMENT CAN CAUSE INJURY TO PERSONS.

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 65 6

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# @A310 SERVICE BULLETIN (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) Install the safety guard (PN 98A27503003000) on the flap and slat control lever. (c) Put access platforms in position below the leading-edges of: - the LH wing at Zone 512 - the LH wing at Zone 524 - the RH wing at Zone 612 - the RH wing at Zone 624 (d) Put an access platform in position below the trailing-edge access panel of the LH wing at Zone 575. (e) On the lower surface of the LH wing, remove the leading-edge access panels 512BB, 512CB, 512DB, 512GB and 512JB as necessary, refer to AMM 06-41-57, Page Block 001. (f) On the lower surface of the LH wing, remove the leading-edge access panels 524BB, 524CB and 524KB as necessary, refer to AMM 06-41-57, Page Block 001. (g) On the lower surface of the RH wing, remove the leading-edge access panels 612BB, 612CB, 612DB, 612GB, 612JB as necessary, refer to AMM 06-41-57, Page Block 001). (h) On the lower surface of the RH wing, remove the leading-edge access panels 624BB and 624CB as necessary, refer to AMM 06-41-57, Page Block 001.

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 66 6

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# @A310 SERVICE BULLETIN
**CONF ALL C. PROCEDURE CAUTION: The work sequence must be carried out as detailed in this Service Bulletin. **CONF 001 (1) Subtask 242105-831-402-001 - Install Adhesive Clipping Bracket on the LH and RH Wing Leading Edge in the Area of Rib 7 Work Zones and Access Panels Zone Access/Work location 520 Access Panel 512HB 620 Access Panel 612HB Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Kit 242105B01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 102 ABS1546B3C12 2 BRACKET Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Two Part Paste Adhesive 08-078 As required Solvent General Purpose 11-026 As required Lint-Free Cotton Cloth 19-003 As required References Structural Repair Manual (SRM) 51-77-10 Fig. A-UBAAA Installation of the new clip and nutplate Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Install on the LH and RH wing leading edge in the area of Rib 7 the item that follows, refer to Fig. A-UBAAA Sheet 01 and Fig. A-UBAAA Sheet 02: 2 Bracket ABS1546B3C12 Item 102 1 Measure and mark out the location of the new bracket, Item 102.

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 67 6

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# @A310 SERVICE BULLETIN

2 Clean the areas to be bonded, both structure and bracket, Item 102 with a: Lint-Free Cotton Cloth 19-003 As required
made moist with: Solvent General Purpose 11-026 As required
3 Use Scotchbrite to lightly abrade the surface then clean with the general solvent. 4 Mix together: Two Part Paste Adhesive 08-078 As required
in accordance with SRM 51-77-10 5 Put a small amount of adhesive to the center of the base of the bracket, Item 102. The quantity applied must be sufficient to enable slight flow of excess adhesive around the complete periphery of the base. 6 Remove the adhesive paper from the adaptor bearing points and discard it. 7 Position the adaptor on the structure within the area previously marked. Press on the ends of the adaptor so the foam pads adhere to the structure. 8 Press on the center section of the adaptor without exerting pressure on the bracket, Item 102. The over-centering and the adaptor cause the adhesive to flow and keep the bracket, Item 102 in place during curing. 9 Once the adhesive has cured in accordance with SRM 51-77-10, remove the adaptor and discard. (2) Subtask 242105-831-001-001 - Attach the routes 1E and 1G with the lacing tape in the LH shroud box leading edge. Work Zones and Access Panels Zone Access/Work location 137 Work location from Frame 39 to Frame 40 from Stringer 28 to Stringer 30 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON SPECIFIC

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 68 6

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# @A310 SERVICE BULLETIN
Material necessary to do the job Kit 242105A01R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 51 NSA8420-5 1 (M) CORD 53 NSA935401-05 1 TIE 62 NSA935401-13 2 TIE 63 NSA5527-03-01 1 SPACER 65 A9222505750000 1 SPACER References Elec. Std. Practices Manual (ESPM) 20-33-44 Fig. A-FBAAA Modification of the routing between FR39 and FR40 at STGR28 to STGR30 (LH side) Sheet 01 Sheet 02
(a) Install the Bobbin Spacer in accordance with detail A-A (If not already installed on aircraft): Refer to Fig. A-FBAAA Sheet 02

. 1 Install : 1 Spacer-Feeder A9222505750000 Item 65 With : 1 Tie-Cable NSA935401-13 Item 62 2 Attach the routes 1E and 1G with (If not already installed on aircraft) : 1 Spacer NSA5527-03-01 Item 63 1 Tie-Cable NSA935401-05 Item 53 Or 1 Tie-Cable NSA935401-13 Item 62 (b) Install the lacing tape to attach the routes 1E and 1G together (To keep the necessary distance between the two routes) in accordance with detail B-B : Refer to Fig. A-FBAAA Sheet 02 Refer to ESPM 20-33-44 NOTE: Cut the lacing tape to the necessary length. 1 (M) Cord-Fiber Glass NSA8420-5 Item 51

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 69 6

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# @A310 SERVICE BULLETIN (3) Subtask 242105-831-002-001 - Attach the routes 2E and 2G with the lacing tape in the RH shroud box leading edge. Work Zones and Access Panels Zone Access/Work location 138 Work location from Frame 39 to Frame 40 from Stringer 28 to Stringer 30 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON SPECIFIC Material necessary to do the job Kit 242105A01R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 51 NSA8420-5 1 (M) CORD 53 NSA935401-05 1 TIE 62 NSA935401-13 2 TIE 63 NSA5527-03-01 1 SPACER 65 A9222505750000 1 SPACER References Elec. Std. Practices Manual (ESPM) 20-33-44 Fig. A-FBEAA Modification of the routing between FR39 and FR40 at STGR28 to STGR30 (RH side) Sheet 01 Sheet 02
(a) Install the Bobbin Spacer in accordance with detail A-A (If not already installed on aircraft): Refer to Fig. A-FBEAA Sheet 02

. 1 Install : 1 Spacer-Feeder A9222505750000 Item 65 With : 1 Tie-Cable NSA935401-13 Item 62 2 Attach the routes 2E and 2G with (If not already installed on aircraft) : 1 Spacer NSA5527-03-01 Item 63 1 Tie-Cable NSA935401-05 Item 53
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 70 6

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# @A310 SERVICE BULLETIN
Or 1 Tie-Cable NSA935401-13 Item 62 (b) Install the lacing tape to attach the routes 1E and 1G together (To keep the necessary distance between the two routes) in accordance with detail B-B : Refer to Fig. A-FBEAA Sheet 02 Refer to ESPM 20-33-44 NOTE: Cut the lacing tape to the necessary length. 1 (M) Cord-Fiber Glass NSA8420-5 Item 51

(4) Subtask 242105-831-003-001 - Modify the routing in the LH forward wing to fuselage fairing. Work Zones and Access Panels Zone Access/Work location 512 Access Panel 513RR, Panel 513QL Work location from Rib 01 to Rib 04 Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills NON SPECIFIC Material necessary to do the job Kit 242105A01R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 52 EN6049-007-08-5 4 (M) SLEEVE 53 NSA935401-05 51 TIE 62 NSA935401-13 1 TIE 63 NSA5527-03-01 1 SPACER 66 EN6049-007-13-5 4 (M) SLEEVE 67 EN6049-007-19-5 4 (M) SLEEVE 85 NSA5516-08ND 16 CLAMP 86 NSA5516-18ND 16 CLAMP References Elec. Std. Practices Manual (ESPM) 20-25-51 20-33-33 20-33-41 20-33-44

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 71 6

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# @A310 SERVICE BULLETIN

References Fig. A-FBBAA Modification of the routing in the forward wing to fuselage fairing (LH and RH side) Sheet 01 Sheet 02 Sheet 03
NOTE: To ensure the necessary access as described in Preparation SUBTASK 242105-010-003 001 Remove the Air Ducts and the Deflector in the LH Wings for access. . NOTE: Unscrew without removal, all the necessary attachment points. (a) Refer to Fig. A-FBBAA Sheet 02

. In the Raceway Box and as shown on detail B-B, remove: 3 Screw Item (88) Retain 3 Washer Item (89) Retain 6 Clamp Item (87) Retain 6 Spacer Item (90) Retain 12 Clamp Item (84) Discard On detail C-C, remove: 1 Screw Item (88) Retain 1 Washer Item (89) Retain 1 Spacer Item (90) Retain 4 Clamp Item (84) Discard (b) Install the protective sleeve between the Rib 01 and Rib 05 and through the Raceway Box : Refer to Fig. A-FBBAA Sheet 01, Fig. A-FBBAA Sheet 02 and Fig. A-FBBAA Sheet 03 1 Install : Refer to ESPM 20-33-33 4 (M) Sleeve-Protective EN6049-007-08-5 Item 52 NOTE: The size of the sleeve should be chosen in accordance with the bundles size on A/C And/Or DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 72 6

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# @A310 SERVICE BULLETIN 4 (M) Sleeve-Protective EN6049-007-13-5 Item 66 And/Or 4 (M) Sleeve-Protective EN6049-007-19-5 Item 67 2 Attach the Protective Sleeve with : 50 Tie-Cable NSA935401-05 Item 53 (c) In the Raceway Box and as shown on detail B-B, install : Refer to Fig. A-FBBAA Sheet 02 12 Clamp NSA5516-08ND Item 85 Or 12 Clamp NSA5516-18ND Item 86 And 6 Spacer Item (90) Retained at removal And 6 Clamp Item (87) Retained at removal 3 Washer Item (89) Retained at removal 3 Screw Item (88) Retained at removal NOTE: Torque all the attachment points unscrewed at removal. (d) On detail C-C, install: Refer to Fig. A-FBBAA Sheet 02

. 4 Clamp NSA5516-08ND Item 85 Or 4 Clamp NSA5516-18ND Item 86 And 1 Spacer Item (90) Retained at removal And
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 73 6

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# @A310 SERVICE BULLETIN
1 Washer Item (89) Retained at removal 1 Screw Item (88) Retained at removal NOTE: Torque all the attachment points unscrewed at removal. (e) Install the spacer Item 63 on the route 1E and 1G : Refer to Fig. A-FBBAA Sheet 01 and Fig. A-FBBAA Sheet 02 section A-A. Refer to ESPM 20-33-41 1 Install : 1 Spacer NSA5527-03-01 Item 63 attach with : 1 Tie-Cable NSA935401-05 Item 53 or 1 Tie-Cable NSA935401-13 Item 62

(5) Subtask 242105-831-004-001 - Modify the routing in the RH forward wing to fuselage fairing. Work Zones and Access Panels Zone Access/Work location 612 Access Panel 613RR, Panel 613QL Work location from Rib 01 to Rib 04 Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills NON SPECIFIC Material necessary to do the job Kit 242105A01R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 52 EN6049-007-08-5 4 (M) SLEEVE 53 NSA935401-05 51 TIE 62 NSA935401-13 1 TIE 63 NSA5527-03-01 1 SPACER 66 EN6049-007-13-5 4 (M) SLEEVE 67 EN6049-007-19-5 4 (M) SLEEVE DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 74 6

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# @A310 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 85 NSA5516-08ND 16 CLAMP 86 NSA5516-18ND 16 CLAMP References Elec. Std. Practices Manual (ESPM) 20-25-51 20-33-33 20-33-41 20-33-44 Fig. A-FBBAA Modification of the routing in the forward wing to fuselage fairing (LH and RH side) Sheet 01 Sheet 02 Sheet 03
NOTE: To ensure the necessary access as described in Preparation SUBTASK 242105-010-003 001 Remove the Air Ducts and the Deflector in the LH Wings for access. . NOTE: To apply the following modification, unscrew without removal, all the necessary attachment points. (a) Refer to Fig. A-FBBAA Sheet 02

. In the Raceway Box and as shown on detail B-B, remove : 3 Screw Item (88) Retain 3 Washer Item (89) Retain 6 Clamp Item (87) Retain 6 Spacer Item (90) Retain 12 Clamp Item (84) Discard On detail C-C, remove: 1 Screw Item (88) Retain 1 Washer Item (89) Retain 1 Spacer Item (90) Retain 4 Clamp Item (84) Discard (b) Install the protective sleeve between the Rib 01 and Rib 05 and through the Raceway Box : Refer to Fig. A-FBBAA Sheet 01, Fig. A-FBBAA Sheet 02 and Fig. A-FBBAA Sheet 03 DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 75 6

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# @A310 SERVICE BULLETIN

1 Install : Refer to ESPM 20-33-33 4 (M) Sleeve-Protective EN6049-007-08-5 Item 52 NOTE: The size of the sleeve should be chosen in accordance with the bundles size on A/C And/Or 4 (M) Sleeve-Protective EN6049-007-13-5 Item 66 And/Or 4 (M) Sleeve-Protective EN6049-007-19-5 Item 67 2 Attach the Protective Sleeve with : 50 Tie-Cable NSA935401-05 Item 53 (c) In the Raceway Box and as shown on detail B-B, install : Refer to Fig. A-FBBAA Sheet 02 12 Clamp NSA5516-08ND Item 85 Or 12 Clamp NSA5516-18ND Item 86 And 6 Spacer Item (90) Retained at removal And 6 Clamp Item (87) Retained at removal 3 Washer Item (89) Retained at removal 3 Screw Item (88) Retained at removal NOTE: Torque all the attachment points unscrewed at removal. (d) On detail C-C, install: Refer to Fig. A-FBBAA Sheet 02

. 4 Clamp NSA5516-08ND Item 85
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 76 6

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# @A310 SERVICE BULLETIN
Or 4 Clamp NSA5516-18ND Item 86 And 1 Spacer Item (90) Retained at removal And 1 Washer Item (89) Retained at removal 1 Screw Item (88) Retained at removal NOTE: Torque all the attachment points unscrewed at removal. (e) Install the spacer Item 63 on the route 2E and 2G : Refer to Fig. A-FBBAA Sheet 01 and Fig. A-FBBAA Sheet 02 section A-A. Refer to ESPM 20-33-41 1 Install : 1 Spacer NSA5527-03-01 Item 63 attach with : 1 Tie-Cable NSA935401-05 Item 53 or 1 Tie-Cable NSA935401-13 Item 62

(6) Subtask 242105-831-005-001 - Modify the routing on the LH shroud box leading edge. Work Zones and Access Panels Zone Access/Work location 573 Work location from Rib 01 to Rib 06 Manpower Resources Manhours 6.00 Minimum number of person 1 Subtask elapsed time 6.00 Skills NON SPECIFIC

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 77 6

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# @A310 SERVICE BULLETIN
Material necessary to do the job Kit 242105A01R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 52 EN6049-007-08-5 24 (M) SLEEVE 53 NSA935401-05 120 TIE 55 A9201346420000 1 GROMMET 56 NAS1801-3-17 6 SCREW 57 NAS1149D0316H 17 WASHER 60 NAS1801-3-13 4 SCREW 61 NSA5527-03-03 4 SPACER 62 NSA935401-13 4 TIE 63 NSA5527-03-01 6 SPACER 64 NSA5527-03-02 5 SPACER 66 EN6049-007-13-5 24 (M) SLEEVE 67 EN6049-007-19-5 24 (M) SLEEVE 69 NSA939510BN 2 (M) STRIP 91 A0041113620000 3 BRACKET 93 A0041113720000 3 BRACKET 96 NSA5516-10ND 8 CLAMP 97 NAS1801-3-14 3 SCREW 98 NAS1801-3-8 3 SCREW 99 NAS1801-3-16 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES 68 Epoxy Resin 08-051 As required References Aircraft Maintenance Manual (AMM) 20-27-00, Page Block 201 Elec. Std. Practices Manual (ESPM) 20-33-33 20-33-41 Fig. A-FBCAA Modification of the routing in the shroud box (LH and RH side) Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 NOTE: To apply the following modification, unscrew without removal, all the necessary attachment points. (a) As shown on detail E-E and K-K, remove the old brackets : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 06
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 78 6

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# @A310 SERVICE BULLETIN

1 Remove : 6 Screw Item (56) Discard 4 Screw Item (60) Discard 10 Washer Item (57) Discard 10 Bracket Item (58) Retain 20 Tie Item (53) Discard (b) Install the grommet on routes 1M and 2M. Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 05 section B-B and detail D. 1 If necessary remove and retain the clamp and the spacer installed before the hole. NOTE: Retain the hardware. 2 Install : Refer to AMM 20-27-00, Page Block 201 1 Grommet A9201346420000 Item 55 NOTE: Open the grommet Item 55 with a craft knife. 3 Install the clamp and the spacer if retained at removal. NOTE: Use the hardware retained at removal. (c) Install the protective sleeve between the Rib 01 and Rib 06 on routes 1M, 2M, 1S-3R-1V and 2S : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 05 1 Install : Refer to ESPM 20-33-33 24 (M) Sleeve-Protective EN6049-007-08-5 Item 52 And/Or 24 (M) Sleeve-Protective EN6049-007-13-5 Item 66 And/Or 24 (M) Sleeve-Protective EN6049-007-19-5 Item 67
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 79 6

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# @A310 SERVICE BULLETIN
NOTE: The size of the sleeve should be chosen by the operator in accordance with the bundles size. 2 Attach the Protective Sleeve with : 100 Tie-Cable NSA935401-05 Item 53 (d) As shown on detail F-F and L-L, install the spacers between the structure and the brackets. Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 06 1 Install : 10 Bracket Item (58) Retained at removal 6 Spacer NSA5527-03-01 Item 63 4 Spacer NSA5527-03-03 Item 61 6 Screw NAS1801-3-17 Item 56 4 Screw NAS1801-3-13 Item 60 10 Washer NAS1149D0316H Item 57 20 Tie-Cable NSA935401-05 Item 53 (e) Install the spacers between routes 1M and 2M and between routes 2S and 1S-3R-1V. Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 05 detail A-A. 1 Install : Refer to ESPM 20-33-41 4 Spacer NSA5527-03-02 Item 64 4 Tie-Cable NSA935401-13 Item 62 (f) Modify the routing of the routes 1P and 2P. 1 As shown on detail C-C remove the old clamps: Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 04

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 80 6

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# @A310 SERVICE BULLETIN

a Remove : 3 Screw Item (88) Discard 3 Washer Item (81) Discard 6 Clamp Item (95) Discard 3 Spacer Item (90) Discard 2 As shown on detail G-G remove the old brackets : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02 and Fig. A-FBCAA Sheet 03
a Remove : 1 Screw Item (99) Discard 1 Washer Item (57) Discard 2 Clamp Item (95) Discard 1 Spacer Item (90) Discard 3 As shown on detail D-D and H-H install a protection on the hole of the Rib : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 04
a Install : 2 (M) Strip-Protective NSA939510BN Item 69 With : Item 68 Epoxy Resin 08-051 As required 4 As shown on detail D-D install the new brackets : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03, Fig. A-FBCAA Sheet 04 and Fig. A-FBCAA Sheet 05
a Install : 3 Bracket A0041113620000 Item 91 Or 3 Bracket A0041113720000 Item 93 Attach with :

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 81 6

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# @A310 SERVICE BULLETIN
3 Screw NAS1801-3-8 Item 98 3 Washer NAS1149D0316H Item 57 NOTE: Case 01 : If bracket PN A924-40102 is installed, install item 91. Case 02 : If bracket PN NSA5456-03 is installed, install item 93. The new bracket have to be in contact with the Rib. b On the new bracket Item 91 or 93, install : 6 Clamp NSA5516-10ND Item 96 3 Washer NAS1149D0316H Item 57 3 Screw NAS1801-3-14 Item 97 5 As shown on detail H-H install the new brackets : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 05
a Install : 1 Spacer NSA5527-03-02 Item 64 2 Clamp NSA5516-10ND Item 96 1 Washer NAS1149D0316H Item 57 1 Screw NAS1801-3-16 Item 99

(7) Subtask 242105-831-006-001 - Modify the routing on the RH shroud box leading edge. Work Zones and Access Panels Zone Access/Work location 673 Work location from Rib 01 to Rib 06 Manpower Resources Manhours 6.00 Minimum number of person 1 Subtask elapsed time 6.00 Skills NON SPECIFIC

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 82 6

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# @A310 SERVICE BULLETIN
Material necessary to do the job Kit 242105A01R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 52 EN6049-007-08-5 24 (M) SLEEVE 53 NSA935401-05 120 TIE 55 A9201346420000 1 GROMMET 56 NAS1801-3-17 6 SCREW 57 NAS1149D0316H 17 WASHER 60 NAS1801-3-13 4 SCREW 61 NSA5527-03-03 4 SPACER 62 NSA935401-13 4 TIE 63 NSA5527-03-01 6 SPACER 64 NSA5527-03-02 5 SPACER 66 EN6049-007-13-5 24 (M) SLEEVE 67 EN6049-007-19-5 24 (M) SLEEVE 69 NSA939510BN 2 (M) STRIP 92 A0041113620100 3 BRACKET 94 A0041113720100 3 BRACKET 96 NSA5516-10ND 8 CLAMP 97 NAS1801-3-14 3 SCREW 98 NAS1801-3-8 3 SCREW 99 NAS1801-3-16 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES 68 Epoxy Resin 08-051 As required References Aircraft Maintenance Manual (AMM) 20-27-00, Page Block 201 Elec. Std. Practices Manual (ESPM) 20-33-33 20-33-41 Fig. A-FBCAA Modification of the routing in the shroud box (LH and RH side) Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 NOTE: Workstep for removal of hydraulic pipes should be performed before this workstep. NOTE: To apply the following modification, unscrew without removal, all the necessary attachment points.

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 83 6

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# @A310 SERVICE BULLETIN (a) As shown on detail E-E and K-K, remove the old brackets : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 06 1 Remove : 6 Screw Item (56) Discard 4 Screw Item (60) Discard 10 Washer Item (57) Discard 10 Bracket Item (58) Retain 20 Tie Item (53) Discard (b) Install the grommet on routes 1M and 2M. Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 05 section B-B and D. 1 If necessary remove and retain the clamp and the spacer installed before the hole. NOTE: Retain the hardware. 2 Install : Refer to AMM 20-27-00, Page Block 201 1 Grommet A9201346420000 Item 55 NOTE: Open the grommet Item 55 with a craft knife. 3 Install the clamp and the spacer if retained at removal. NOTE: Use the hardware retained at removal. (c) Install the protective sleeve between the Rib 01 and Rib 06 on routes 1M, 2M, 1S-3R-1V and 2S : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 05 1 Install : Refer to ESPM 20-33-33 24 (M) Sleeve-Protective EN6049-007-08-5 Item 52 And/Or

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 84 6

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# @A310 SERVICE BULLETIN 24 (M) Sleeve-Protective EN6049-007-13-5 Item 66 And/Or 24 (M) Sleeve-Protective EN6049-007-19-5 Item 67 NOTE: The size of the sleeve should be choosen by the operator in accordance with the bundles size. 2 Attach the Protective Sleeve with : 100 Tie-Cable NSA935401-05 Item 53 (d) As shown on detail F-F and L-L, install the spacers between the structure and the brackets. Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 06 1 Install : 10 Bracket Item (58) Retained at removal 6 Spacer NSA5527-03-01 Item 63 4 Spacer NSA5527-03-03 Item 61 6 Screw NAS1801-3-17 Item 56 4 Screw NAS1801-3-13 Item 60 10 Washer NAS1149D0316H Item 57 20 Tie-Cable NSA935401-05 Item 53 (e) Install the spacers between routes 1M and 2M and between routes 1S and 2S-3R-2V. Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 05 detail A-A. 1 Install : Refer to ESPM 20-33-41 4 Spacer NSA5527-03-02 Item 64 4 Tie-Cable NSA935401-13 Item 62

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 85 6

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# @A310 SERVICE BULLETIN (f) Modify the routing of the routes 1P and 2P. 1 As shown on detail C-C remove the old clamps: Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 04
a Remove : 3 Screw Item (88) Discard 3 Washer Item (81) Discard 6 Clamp Item (95) Discard 3 Spacer Item (90) Discard 2 As shown on detail G-G remove the old brackets : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02 and Fig. A-FBCAA Sheet 03
a Remove : 1 Screw Item (99) Discard 1 Washer Item (57) Discard 2 Clamp Item (95) Discard 1 Spacer Item (90) Discard 3 As shown on detail D-D and H-H install a protection on the hole of the Rib : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 04
a Install : 2 (M) Strip-Protective NSA939510BN Item 69 With : Item 68 Epoxy Resin 08-051 As required 4 As shown on detail D-D install the new brackets : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03, Fig. A-FBCAA Sheet 04 and Fig. A-FBCAA Sheet 05
a Install : 3 Bracket A0041113620100 Item 92 DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 86 6

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# @A310 SERVICE BULLETIN
Or 3 Bracket A0041113720100 Item 94 Attach with : 3 Screw NAS1801-3-8 Item 98 3 Washer NAS1149D0316H Item 57 NOTE: Case 01 : If bracket PN A924-40102 is installed, install item 92. Case 02 : If bracket PN NSA5456-03 is installed, install item 94. The new bracket have to be in contact with the Rib. b On the new bracket Item 92 or 94, install : 6 Clamp NSA5516-10ND Item 96 3 Washer NAS1149D0316H Item 57 3 Screw NAS1801-3-14 Item 97 5 As shown on detail H-H install the new brackets : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 05
a Install : 1 Spacer NSA5527-03-02 Item 64 2 Clamp NSA5516-10ND Item 96 1 Washer NAS1149D0316H Item 57 1 Screw NAS1801-3-16 Item 99

(8) Subtask 242105-831-401-001 - Install new nutplate on the RH wing Leading edge Work Zones and Access Panels Zone Access/Work location 620 Access Panel 624KB Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 87 6

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# @A310 SERVICE BULLETIN
Material necessary to do the job Kit 242105B01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 106 NSA5456-3-8 1 NUTPLATE 111 ANSA2050DCJ3210 2 RIVET Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Multi Purpose Thixotropic Paste 09-016J As required
References Structural Repair Manual (SRM) 51-77-10 Fig. A-UBAAA Installation of the new clip and nutplate Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Install new nutplate on the RH wing leading edge in the location of Rib 28a, refer to Fig. A-UBAAA Sheet 01 , Fig. A-UBAAA Sheet 03 and Fig. A-UBAAA Sheet 04

. 1 On the center line of existing anchor nut as indicated, make sure the nutplate, Item 106 is in the correct position. 2 Use: 1 Nutplate NSA5456-3-8 Item 106 3 Mark out and drill two 3.2 mm (0.125 in.) holes in the structure. 4 Wet assemble, Items 106 to the structure with: Multi Purpose Thixotropic Paste 09-016J As required

use: 2 Rivet ANSA2050DCJ3210 Item 111

(9) Subtask 242105-831-211-004 - Modify the electrical routing installation at the LH front spar in the area of RIB 2 Work Zones and Access Panels Zone Access/Work location 512 Work location Rib 2

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 88 6

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# @A310 SERVICE BULLETIN
Manpower Resources Manhours 1.5 Minimum number of person 1 Subtask elapsed time 1.5 Skills NON SPECIFIC Material necessary to do the job Kit 242105D02R08 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 18 MS21919WCH12 1 CLAMP 19 MS21919WCH4 2 CLAMP 43 NSA935401-03 16 TIE 100 B9239030000200 4 PLACARD References Elec. Std. Practices Manual (ESPM) 20-33-33 Fig. A-GDEAA Modification of the electrical routing installation at the LH front spar in the area of RIB 2 Sheet 01 Sheet 02 Sheet 03 (a) Modify the electrical routing installation at the LH front spar in the area of RIB 2. 1 Remove these items: Refer to Fig. A-GDEAA Sheet 03, Section A-A. 1 Clamp Item (130) Retain 2 Clamp Item (54) Discard 1 Clamp Item (57) Discard with 1 Washer Item (70) Retain 1 Spacer Item (73) Retain 1 Screw Item (77) Retain 2 Install the electrical wires with the protection sleeves: NOTE: The protection sleeves are previously installed with subtask 242105-831-003-001. Refer to Fig. A-GDEAA Sheet 03, Section B-B.

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 89 6

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# @A310 SERVICE BULLETIN 1 Clamp MS21919WCH12 Item 18 2 Clamp MS21919WCH4 Item 19 1 Clamp Item (130) Retained at removal with 1 Washer Item (70) Retained at removal 1 Spacer Item (73) Retained at removal 1 Screw Item (77) Retained at removal 3 Before installation, cut the protection sleeve to its required length and install with: Refer to ESPM 20-33-33. Refer to Fig. A-GDEAA Sheet 02, View C . 16 Tie NSA935401-03 Item 43 4 Install the Service Bulletin placards: Refer to Fig. A-GDEAA Sheet 03, View D. 4 Placard B9239030000200 Item 100 in a good visible position. (10) Subtask 242105-831-212-004 - Modify the electrical routing installation at the RH front spar in the area of RIB 2 Work Zones and Access Panels Zone Access/Work location 612 Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills NON SPECIFIC

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 90 6

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# @A310 SERVICE BULLETIN
Material necessary to do the job Kit 242105D02R08 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 19 MS21919WCH4 1 CLAMP 29 MS21919WCH11 1 CLAMP 30 MS21919WCH5 1 CLAMP 43 NSA935401-03 16 TIE 100 B9239030000200 4 PLACARD References Elec. Std. Practices Manual (ESPM) 20-33-33 Fig. A-GDFAA Modification of the electrical routing installation at the RH front spar in the area of RIB 2 Sheet 01 Sheet 02 Sheet 03 (a) Modify the electrical routing installation at the RH front spar in the area of RIB 2. 1 Remove these items: Refer to Fig. A-GDFAA Sheet 03, Section A-A. 1 Clamp Item (130) Retain 1 Clamp Item (54) Discard 1 Clamp Item (58) Discard 1 Clamp Item (61) Discard with 1 Washer Item (70) Retain 1 Spacer Item (73) Retain 1 Screw Item (77) Retain 2 Install the electrical wires with the protection sleeves: NOTE: The protection sleeves are previously installed with subtask 242105-831-004-001. Refer to Fig. A-GDFAA Sheet 03, Section B-B. 1 Clamp MS21919WCH4 Item 19 1 Clamp MS21919WCH11 Item 29
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 91 6

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# @A310 SERVICE BULLETIN 1 Clamp MS21919WCH5 Item 30 1 Clamp Item (130) Retained at removal with 1 Washer Item (70) Retained at removal 1 Spacer Item (73) Retained at removal 1 Screw Item (77) Retained at removal 3 Before installation, cut the protection sleeve to its required length and install with: Refer to ESPM 20-33-33. Refer to Fig. A-GDFAA Sheet 02, View C. 16 Tie NSA935401-03 Item 43 4 Install the Service Bulletin placards: Refer to Fig. A-GDFAA Sheet 03, View D. 4 Placard B9239030000200 Item 100 in a good visible position. (11) Subtask 242105-831-213-002 - Modify the electrical routing installation at the LH front spar in the area of RIB 3. Work Zones and Access Panels Zone Access/Work location 512 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON SPECIFIC Material necessary to do the job Kit 242105D02R08 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 18 MS21919WCH12 2 CLAMP DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 92 6

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# @A310 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 19 MS21919WCH4 2 CLAMP 20 EN6049-007-05-5 1 (ME) SLEEVE 21 EN6049-007-19-5 1 (ME) SLEEVE 100 B9239030000200 2 PLACARD References Elec. Std. Practices Manual (ESPM) 20-33-33 Fig. A-GDCAA Modification of the electrical routing installation at the LH front spar in the area of RIB 3 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Modify the electrical routing installation at the LH front spar in the area of RIB 3. 1 Remove these items: Refer to Fig. A-GDCAA Sheet 03, Section A-A. 2 Clamp Item (54) Discard 2 Clamp Item (57) Discard 4 Clamp Item (78) Retain and 2 Washer Item (70) Retain 2 Screw Item (72) Retain 4 Spacer Item (73) Retain 2 Spacer Item (79) Retain or Remove these items: Refer to Fig. A-GDCAA Sheet 03, Section B-B. 2 Clamp Item (54) Discard 2 Clamp Item (57) Discard and 2 Washer Item (70) Retain

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 93 6

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# @A310 SERVICE BULLETIN 2 Spacer Item (73) Retain 2 Screw Item (77) Retain NOTE: The different installations are depending on the installation in the aircraft. 2 Install the electrical wires with protection sleeves: Refer to Fig. A-GDCAA Sheet 04, Section C-C. 1 (ME) Sleeve EN6049-007-05-5 Item 20 1 (ME) Sleeve EN6049-007-19-5 Item 21 with 2 Clamp MS21919WCH12 Item 18 2 Clamp MS21919WCH4 Item 19 4 Clamp Item (78) Retained at removal and 2 Washer Item (70) Retained at removal 2 Screw Item (72) Retained at removal 4 Spacer Item (73) Retained at removal 2 Spacer Item (79) Retained at removal NOTE: Before installation, cut the sleeves, Items 20 and 21, to its required length, refer to Fig. A-GDCAA Sheet 02, View C, refer to ESPM 20-33-33.
or Install the electrical wires with protection sleeves: Refer to Fig. A-GDCAA Sheet 04, Section D-D. 1 (ME) Sleeve EN6049-007-05-5 Item 20 1 (ME) Sleeve EN6049-007-19-5 Item 21

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 94 6

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# @A310 SERVICE BULLETIN
with 2 Clamp MS21919WCH12 Item 18 2 Clamp MS21919WCH4 Item 19 and 2 Washer Item (70) Retained at removal 2 Spacer Item (73) Retained at removal 2 Screw Item (77) Retained at removal NOTE: Before installation, cut the sleeves, Items 20 and 21, to its required length, refer to Fig. A-GDCAA Sheet 02, View C, refer to ESPM 20-33-33. 3 Install the Service Bulletin placards: Refer to Fig. A-GDCAA Sheet 04, View D. 2 Placard B9239030000200 Item 100 in a good visible position. (12) Subtask 242105-831-214-002 - Modify the electrical routing installation at the RH front spar in the area of RIB 3. Work Zones and Access Panels Zone Access/Work location 612 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON SPECIFIC Material necessary to do the job Kit 242105D02R08 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 19 MS21919WCH4 1 CLAMP 20 EN6049-007-05-5 1 (ME) SLEEVE 21 EN6049-007-19-5 1 (ME) SLEEVE 29 MS21919WCH11 2 CLAMP DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 95 6

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# @A310 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 100 B9239030000200 2 PLACARD References Elec. Std. Practices Manual (ESPM) 20-33-33 Fig. A-GDDAA Modification of the electrical routing installation at the RH front spar in the area of RIB 3 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Modify the electrical routing installation at the RH front spar in the area of RIB 3. 1 Remove these items: Refer to Fig. A-GDDAA Sheet 03, Section A-A. 1 Clamp Item (54) Discard 1 Clamp Item (58) Discard 2 Clamp Item (78) Retain and 1 Washer Item (70) Retain 1 Screw Item (72) Retain 2 Spacer Item (73) Retain 1 Spacer Item (79) Retain or Remove these items: Refer to Fig. A-GDDAA Sheet 03, Section B-B. 1 Clamp Item (54) Discard 1 Clamp Item (58) Discard and 1 Washer Item (70) Retain 1 Spacer Item (73) Retain 1 Screw Item (77) Retain

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 96 6

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# @A310 SERVICE BULLETIN
NOTE: The different installations are depending on the installation in the aircraft. 2 Install the electrical wires with protection sleeves: Refer to Fig. A-GDDAA Sheet 04, Section C-C. 1 (ME) Sleeve EN6049-007-05-5 Item 20 1 (ME) Sleeve EN6049-007-19-5 Item 21 with 1 Clamp MS21919WCH4 Item 19 1 Clamp MS21919WCH11 Item 29 2 Clamp Item (78) Retained at removal and 1 Washer Item (70) Retained at removal 1 Screw Item (72) Retained at removal 2 Spacer Item (73) Retained at removal 1 Spacer Item (79) Retained at removal NOTE: Before installation, cut the sleeves, Items 20 and 21, to its required length, refer to Fig. A-GDDAA Sheet 02, View C, refer to ESPM 20-33-33.
or Install the electrical wires with protection sleeves: Refer to Fig. A-GDDAA Sheet 04, Section D-D. 1 (ME) Sleeve EN6049-007-05-5 Item 20 1 (ME) Sleeve EN6049-007-19-5 Item 21 with 1 Clamp MS21919WCH4 Item 19

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 97 6

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# @A310 SERVICE BULLETIN 1 Clamp MS21919WCH11 Item 29 and 1 Washer Item (70) Retained at removal 1 Spacer Item (73) Retained at removal 1 Screw Item (77) Retained at removal 3 Install the Service Bulletin placards: Refer to Fig. A-GDDAA Sheet 04, View D. 2 Placard B9239030000200 Item 100 in a good visible position. (13) Subtask 242105-831-215-002 - Modify the electrical routing installation at the LH and RH front spars in the area of RIB 5 and RIB 6. Work Zones and Access Panels Zone Access/Work location 512 612 Manpower Resources Manhours 2.50 Minimum number of person 2 Subtask elapsed time 1.25 Skills NON SPECIFIC Material necessary to do the job Kit 242105D02R08 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 MS21919WCH10 2 CLAMP 3 NAS1149D0332K 2 WASHER 4 NSA5527-03-03D 2 SPACER 19 MS21919WCH4 2 CLAMP 23 NAS1801-3-16 4 SCREW 24 MS21042-3 2 NUT 31 NAS1801-3-13 2 SCREW 32 NSA5527-03-07D 4 SPACER 42 A9249252400400 2 RAMP

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 98 6

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# @A310 SERVICE BULLETIN

References Fig. A-GEAAA Modification of the electrical routing installation at the LH/RH front spars in the area of RIB 5 and RIB 6 Sheet 01 Sheet 02 Sheet 03 (a) Modify the electrical routing installation at the LH and RH front spar in the area of RIB 5 and RIB 6. 1 Remove these items: Refer to Fig. A-GEAAA Sheet 02, Section A-A. 4 Clamp Item (10) Retain 4 Clamp Item (19) Retain and 4 Washer Item (3) Retain 4 Spacer Item (4) Retain 4 Screw Item (5) Discard 2 Install the electrical wires with: Refer to Fig. A-GEAAA Sheet 03, Section B-B. 2 Ramp A9249252400400 Item 42 and 4 Washer Item (3) Retained at removal 4 Spacer Item (4) Retained at removal 4 Clamp Item (10) Retained at removal 4 Clamp Item (19) Retained at removal 4 Screw NAS1801-3-16 Item 23 4 Spacer NSA5527-03-07D Item 32 3 Install the electrical wires at the ramp, Item 42, with: Refer to Fig. A-GEAAA Sheet 03, Section C-C. DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 99 6

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# @A310 SERVICE BULLETIN 2 Clamp MS21919WCH10 Item 2 2 Clamp MS21919WCH4 Item 19 and 2 Spacer NSA5527-03-03D Item 4 2 Washer NAS1149D0332K Item 3 2 Nut MS21042-3 Item 24 2 Screw NAS1801-3-13 Item 31

(14) Subtask 242105-831-216-001 - Modify the electrical routing installation at the LH and RH front spars in the area of RIB 7 and RIB 8. Work Zones and Access Panels Zone Access/Work location 512 612 Manpower Resources Manhours 1.00 Minimum number of person 2 Subtask elapsed time 0.50 Skills NON SPECIFIC Material necessary to do the job Kit 242105D02R08 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 3 NAS1149D0332K 2 WASHER 6 NAS1801-3-10 2 SCREW 7 NSA5527-03-05D 2 SPACER 10 MS21919WCH2 2 CLAMP 100 B9239030000200 1 PLACARD References Fig. A-GFAAA Modification of the electrical routing installation at the LH/RH front spars in the area of RIB 7 and RIB 8 Sheet 01 Sheet 02
(a) Install additional clamps at the LH and RH front spars in the area of RIB 8. NOTE: Make sure that the work step "Install adhesive clipping brackets", subtask 242105-831-402-001 is done before you start with this work step. DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 100 6

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# @A310 SERVICE BULLETIN

1 Install these items: Refer to Fig. A-GFAAA Sheet 02, View C. 2 Clamp MS21919WCH2 Item 10 with 2 Washer NAS1149D0332K Item 3 2 Screw NAS1801-3-10 Item 6 2 Spacer NSA5527-03-05D Item 7 2 Install the Service Bulletin placards: Refer to Fig. A-GFAAA Sheet 02, View D. 1 Placard B9239030000200 Item 100 in a good visible position. (15) Subtask 242105-831-218-001 - Modify the electrical routing installation at the LH front spar in the area of RIB 20 and RIB 21. Work Zones and Access Panels Zone Access/Work location 524 Manpower Resources Manhours 3.25 Minimum number of person 1 Subtask elapsed time 3.25 Skills NON SPECIFIC Material necessary to do the job Kit 242105D02R08 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 3 NAS1149D0332K 2 WASHER 8 NSA5527-03-01D 2 SPACER 9 MS21919WCH3 6 CLAMP 10 MS21919WCH2 2 CLAMP 11 NAS1801-3-18 2 SCREW 24 MS21042-3 2 NUT 25 NAS1096-3-24 2 SCREW 26 NAS1096-3-22 2 SCREW 32 NSA5527-03-07D 4 SPACER 40 A9249252400000 1 RAMP
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 101 6

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# @A310 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 41 A9249252400200 1 RAMP 100 B9239030000200 2 PLACARD References Fig. A-GGAAA Modification of the electrical routing installation at the LH front spar in the area of RIB 20 and RIB 21 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Modify the electrical routing installation at the LH front spar in the area of RIB 20 and RIB 21. 1 Remove these items: Refer to Fig. A-GGAAA Sheet 02, Section A-A. 12 Clamp Item (9) Retain 4 Clamp Item (10) Retain and 4 Washer Item (3) Retain 4 Spacer Item (8) Retain 4 Spacer Item (22) Retain 4 Screw Item (59) Discard 2 Install the ramp close to RIB 20: Refer to Fig. A-GGAAA Sheet 03, View C and Section B-B. 1 Ramp A9249252400000 Item 40 with 6 Clamp Item (9) Retained at removal 2 Clamp Item (10) Retained at removal and 2 Washer Item (3) Retained at removal

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 102 6

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# @A310 SERVICE BULLETIN 2 Spacer Item (8) Retained at removal 2 Spacer Item (22) Retained at removal 2 Screw NAS1096-3-22 Item 26 2 Spacer NSA5527-03-07D Item 32 3 Install the electrical wires at the ramp, Item 40, close to RIB 20: Refer to Fig. A-GGAAA Sheet 03, View C and Section C-C. 3 Clamp MS21919WCH3 Item 9 1 Clamp MS21919WCH2 Item 10 and 1 Washer NAS1149D0332K Item 3 1 Spacer NSA5527-03-01D Item 8 1 Screw NAS1801-3-18 Item 11 1 Nut MS21042-3 Item 24 4 Install the ramp close to RIB 21: Refer to Fig. A-GGAAA Sheet 03, View C, and Fig. A-GGAAA Sheet 04, Section D-D. 1 Ramp A9249252400200 Item 41 with 6 Clamp Item (9) Retained at removal 2 Clamp Item (10) Retained at removal and 2 Washer Item (3) Retained at removal 2 Spacer Item (8) Retained at removal 2 Spacer Item (22) Retained at removal DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 103 6

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# @A310 SERVICE BULLETIN
2 Screw NAS1096-3-24 Item 25 2 Spacer NSA5527-03-07D Item 32 5 Install the electrical wires at the ramp, Item 41, close to RIB 21: Refer to Fig. A-GGAAA Sheet 03, View C, and Fig. A-GGAAA Sheet 04, Section E-E. 3 Clamp MS21919WCH3 Item 9 1 Clamp MS21919WCH2 Item 10 and 1 Washer NAS1149D0332K Item 3 1 Spacer NSA5527-03-01D Item 8 1 Screw NAS1801-3-18 Item 11 1 Nut MS21042-3 Item 24 6 Install the Service Bulletin placard: Refer to Fig. A-GGAAA Sheet 04, View D. 2 Placard B9239030000200 Item 100 in a good visible position. (16) Subtask 242105-831-219-001 - Modify the electrical routing installation at the RH front spar in the area of RIB 20 and RIB 21. Work Zones and Access Panels Zone Access/Work location 624 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills NON SPECIFIC Material necessary to do the job Kit 242105D02R08 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 3 NAS1149D0332K 2 WASHER 8 NSA5527-03-01D 2 SPACER DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 104 6

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# @A310 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 MS21919WCH3 6 CLAMP 10 MS21919WCH2 2 CLAMP 11 NAS1801-3-18 2 SCREW 24 MS21042-3 2 NUT 25 NAS1096-3-24 2 SCREW 26 NAS1096-3-22 2 SCREW 32 NSA5527-03-07D 2 SPACER 40 A9249252400000 1 RAMP 41 A9249252400200 1 RAMP 100 B9239030000200 2 PLACARD References Fig. A-GHAAA Modification of the electrical routing installation at the RH front spar in the area of RIB 20 and RIB 21 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Modify the electrical routing installation at the RH front spar in the area of RIB 20 and RIB 21. 1 Remove these items: Refer to Fig. A-GHAAA Sheet 02, Section A-A. 12 Clamp Item (9) Retain 4 Clamp Item (10) Retain and 4 Washer Item (3) Retain 4 Spacer Item (8) Retain 4 Screw Item (60) Discard 2 Install the electrical wires close to RIB 20: Refer to Fig. A-GHAAA Sheet 03, View C and Fig. A-GHAAA Sheet 04 Section D-D. 1 Ramp A9249252400200 Item 41 with 6 Clamp Item (9) Retained at removal

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 105 6

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# @A310 SERVICE BULLETIN 2 Clamp Item (10) Retained at removal and 2 Washer Item (3) Retained at removal 2 Spacer Item (8) Retained at removal 2 Screw NAS1096-3-22 Item 26 2 Spacer NSA5527-03-07D Item 32 3 Install the electrical wires at the ramp, Item 41, close to RIB 20: Refer to Fig. A-GHAAA Sheet 03, View C and Fig. A-GHAAA Sheet 04 Section E-E. 3 Clamp MS21919WCH3 Item 9 1 Clamp MS21919WCH2 Item 10 and 1 Washer NAS1149D0332K Item 3 1 Spacer NSA5527-03-01D Item 8 1 Screw NAS1801-3-18 Item 11 1 Nut MS21042-3 Item 24 4 Install the electrical wires close to RIB 21: Refer to Fig. A-GHAAA Sheet 03, View C, and Section B-B. 1 Ramp A9249252400000 Item 40 with 6 Clamp Item (9) Retained at removal 2 Clamp Item (10) Retained at removal and 2 Washer Item (3) Retained at removal

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 106 6

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# @A310 SERVICE BULLETIN 2 Spacer Item (8) Retained at removal 2 Screw NAS1096-3-24 Item 25 2 Spacer NSA5527-03-07D Item 32 5 Install the electrical wires at the ramp, Item 40, close to RIB 21: Refer to Fig. A-GHAAA Sheet 03, View C, and Section C-C. 3 Clamp MS21919WCH3 Item 9 1 Clamp MS21919WCH2 Item 10 and 1 Washer NAS1149D0332K Item 3 1 Spacer NSA5527-03-01D Item 8 1 Screw NAS1801-3-18 Item 11 1 Nut MS21042-3 Item 24 6 Install the Service Bulletin placard: Refer to Fig. A-GHAAA Sheet 04, View D. 2 Placard B9239030000200 Item 100 in a good visible position. (17) Subtask 242105-831-220-002 - Modify the electrical routing installation at the RH front spar in the area of RIB 28 and RIB 28A. Work Zones and Access Panels Zone Access/Work location 624 Manpower Resources Manhours 1.50 Minimum number of person 1 Subtask elapsed time 1.50 Skills NON SPECIFIC

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 107 6

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# @A310 SERVICE BULLETIN
Material necessary to do the job Kit 242105D02R08 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 3 NAS1149D0332K 1 WASHER 9 MS21919WCH3 3 CLAMP 27 NSA5527-03-15D 2 SPACER 28 NAS1801-3-30 1 SCREW 100 B9239030000200 2 PLACARD References Fig. A-GJAAA Modification of the electrical routing installation at the RH front spar in the area of RIB 28 and RIB 28A Sheet 01 Sheet 02 Sheet 03 (a) Modify electrical routing installation at the RH front spar in the area of RIB 28 and 28A. 1 Remove these items: Refer to Fig. A-GJAAA Sheet 02, View C. 3 Clamp Item (9) Discard and 1 Washer Item (3) Discard 3 Spacer Item (8) Discard 1 Screw Item (56) Discard 2 Install these items: NOTE: Make sure that the subtask 242105-831-401-001, "Install new nutplate on the RH wing leading edge", is done before you start with this work step. Refer to Fig. A-GJAAA Sheet 03, View E. 3 Clamp MS21919WCH3 Item 9 with 1 Washer NAS1149D0332K Item 3 2 Spacer NSA5527-03-15D Item 27 1 Screw NAS1801-3-30 Item 28
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 108 6

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# @A310 SERVICE BULLETIN
3 Install the Service Bulletin placard: Refer to Fig. A-GJAAA Sheet 03, View F. 2 Placard B9239030000200 Item 100 in a good visible position. **CONF 002 (1) Subtask 242105-831-402-001 - Install Adhesive Clipping Bracket on the LH and RH Wing Leading Edge in the Area of Rib 7 Work Zones and Access Panels Zone Access/Work location 520 Access Panel 512HB 620 Access Panel 612HB Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Kit 242105B01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 102 ABS1546B3C12 2 BRACKET Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Two Part Paste Adhesive 08-078 As required Solvent General Purpose 11-026 As required Lint-Free Cotton Cloth 19-003 As required References Structural Repair Manual (SRM) 51-77-10 Fig. A-UBAAA Installation of the new clip and nutplate Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Install on the LH and RH wing leading edge in the area of Rib 7 the item that follows, refer to Fig. A-UBAAA Sheet 01 and Fig. A-UBAAA Sheet 02: 2 Bracket ABS1546B3C12 Item 102

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 109 6

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# @A310 SERVICE BULLETIN

1 Measure and mark out the location of the new bracket, Item 102. 2 Clean the areas to be bonded, both structure and bracket, Item 102 with a: Lint-Free Cotton Cloth 19-003 As required
made moist with: Solvent General Purpose 11-026 As required
3 Use Scotchbrite to lightly abrade the surface then clean with the general solvent. 4 Mix together: Two Part Paste Adhesive 08-078 As required
in accordance with SRM 51-77-10 5 Put a small amount of adhesive to the center of the base of the bracket, Item 102. The quantity applied must be sufficient to enable slight flow of excess adhesive around the complete periphery of the base. 6 Remove the adhesive paper from the adaptor bearing points and discard it. 7 Position the adaptor on the structure within the area previously marked. Press on the ends of the adaptor so the foam pads adhere to the structure. 8 Press on the center section of the adaptor without exerting pressure on the bracket, Item 102. The over-centering and the adaptor cause the adhesive to flow and keep the bracket, Item 102 in place during curing. 9 Once the adhesive has cured in accordance with SRM 51-77-10, remove the adaptor and discard. (2) Subtask 242105-831-001-001 - Attach the routes 1E and 1G with the lacing tape in the LH shroud box leading edge. Work Zones and Access Panels Zone Access/Work location 137 Work location from Frame 39 to Frame 40 from Stringer 28 to Stringer 30 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON SPECIFIC

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 110 6

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# @A310 SERVICE BULLETIN
Material necessary to do the job Kit 242105A01R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 51 NSA8420-5 1 (M) CORD 53 NSA935401-05 1 TIE 62 NSA935401-13 2 TIE 63 NSA5527-03-01 1 SPACER 65 A9222505750000 1 SPACER References Elec. Std. Practices Manual (ESPM) 20-33-44 Fig. A-FBAAA Modification of the routing between FR39 and FR40 at STGR28 to STGR30 (LH side) Sheet 01 Sheet 02
(a) Install the Bobbin Spacer in accordance with detail A-A (If not already installed on aircraft): Refer to Fig. A-FBAAA Sheet 02

. 1 Install : 1 Spacer-Feeder A9222505750000 Item 65 With : 1 Tie-Cable NSA935401-13 Item 62 2 Attach the routes 1E and 1G with (If not already installed on aircraft) : 1 Spacer NSA5527-03-01 Item 63 1 Tie-Cable NSA935401-05 Item 53 Or 1 Tie-Cable NSA935401-13 Item 62 (b) Install the lacing tape to attach the routes 1E and 1G together (To keep the necessary distance between the two routes) in accordance with detail B-B : Refer to Fig. A-FBAAA Sheet 02 Refer to ESPM 20-33-44 NOTE: Cut the lacing tape to the necessary length. 1 (M) Cord-Fiber Glass NSA8420-5 Item 51

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 111 6

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# @A310 SERVICE BULLETIN (3) Subtask 242105-831-002-001 - Attach the routes 2E and 2G with the lacing tape in the RH shroud box leading edge. Work Zones and Access Panels Zone Access/Work location 138 Work location from Frame 39 to Frame 40 from Stringer 28 to Stringer 30 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON SPECIFIC Material necessary to do the job Kit 242105A01R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 51 NSA8420-5 1 (M) CORD 53 NSA935401-05 1 TIE 62 NSA935401-13 2 TIE 63 NSA5527-03-01 1 SPACER 65 A9222505750000 1 SPACER References Elec. Std. Practices Manual (ESPM) 20-33-44 Fig. A-FBEAA Modification of the routing between FR39 and FR40 at STGR28 to STGR30 (RH side) Sheet 01 Sheet 02
(a) Install the Bobbin Spacer in accordance with detail A-A (If not already installed on aircraft): Refer to Fig. A-FBEAA Sheet 02

. 1 Install : 1 Spacer-Feeder A9222505750000 Item 65 With : 1 Tie-Cable NSA935401-13 Item 62 2 Attach the routes 2E and 2G with (If not already installed on aircraft) : 1 Spacer NSA5527-03-01 Item 63 1 Tie-Cable NSA935401-05 Item 53
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 112 6

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# @A310 SERVICE BULLETIN
Or 1 Tie-Cable NSA935401-13 Item 62 (b) Install the lacing tape to attach the routes 1E and 1G together (To keep the necessary distance between the two routes) in accordance with detail B-B : Refer to Fig. A-FBEAA Sheet 02 Refer to ESPM 20-33-44 NOTE: Cut the lacing tape to the necessary length. 1 (M) Cord-Fiber Glass NSA8420-5 Item 51

(4) Subtask 242105-831-003-001 - Modify the routing in the LH forward wing to fuselage fairing. Work Zones and Access Panels Zone Access/Work location 512 Access Panel 513RR, Panel 513QL Work location from Rib 01 to Rib 04 Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills NON SPECIFIC Material necessary to do the job Kit 242105A01R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 52 EN6049-007-08-5 4 (M) SLEEVE 53 NSA935401-05 51 TIE 62 NSA935401-13 1 TIE 63 NSA5527-03-01 1 SPACER 66 EN6049-007-13-5 4 (M) SLEEVE 67 EN6049-007-19-5 4 (M) SLEEVE 85 NSA5516-08ND 16 CLAMP 86 NSA5516-18ND 16 CLAMP References Elec. Std. Practices Manual (ESPM) 20-25-51 20-33-33 20-33-41 20-33-44

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 113 6

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# @A310 SERVICE BULLETIN

References Fig. A-FBBAA Modification of the routing in the forward wing to fuselage fairing (LH and RH side) Sheet 01 Sheet 02 Sheet 03
NOTE: To ensure the necessary access as described in Preparation SUBTASK 242105-010-003 001 Remove the Air Ducts and the Deflector in the LH Wings for access. . NOTE: Unscrew without removal, all the necessary attachment points. (a) Refer to Fig. A-FBBAA Sheet 02

. In the Raceway Box and as shown on detail B-B, remove: 3 Screw Item (88) Retain 3 Washer Item (89) Retain 6 Clamp Item (87) Retain 6 Spacer Item (90) Retain 12 Clamp Item (84) Discard On detail C-C, remove: 1 Screw Item (88) Retain 1 Washer Item (89) Retain 1 Spacer Item (90) Retain 4 Clamp Item (84) Discard (b) Install the protective sleeve between the Rib 01 and Rib 05 and through the Raceway Box : Refer to Fig. A-FBBAA Sheet 01, Fig. A-FBBAA Sheet 02 and Fig. A-FBBAA Sheet 03 1 Install : Refer to ESPM 20-33-33 4 (M) Sleeve-Protective EN6049-007-08-5 Item 52 NOTE: The size of the sleeve should be chosen in accordance with the bundles size on A/C And/Or DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 114 6

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# @A310 SERVICE BULLETIN 4 (M) Sleeve-Protective EN6049-007-13-5 Item 66 And/Or 4 (M) Sleeve-Protective EN6049-007-19-5 Item 67 2 Attach the Protective Sleeve with : 50 Tie-Cable NSA935401-05 Item 53 (c) In the Raceway Box and as shown on detail B-B, install : Refer to Fig. A-FBBAA Sheet 02 12 Clamp NSA5516-08ND Item 85 Or 12 Clamp NSA5516-18ND Item 86 And 6 Spacer Item (90) Retained at removal And 6 Clamp Item (87) Retained at removal 3 Washer Item (89) Retained at removal 3 Screw Item (88) Retained at removal NOTE: Torque all the attachment points unscrewed at removal. (d) On detail C-C, install: Refer to Fig. A-FBBAA Sheet 02

. 4 Clamp NSA5516-08ND Item 85 Or 4 Clamp NSA5516-18ND Item 86 And 1 Spacer Item (90) Retained at removal And
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 115 6

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# @A310 SERVICE BULLETIN
1 Washer Item (89) Retained at removal 1 Screw Item (88) Retained at removal NOTE: Torque all the attachment points unscrewed at removal. (e) Install the spacer Item 63 on the route 1E and 1G : Refer to Fig. A-FBBAA Sheet 01 and Fig. A-FBBAA Sheet 02 section A-A. Refer to ESPM 20-33-41 1 Install : 1 Spacer NSA5527-03-01 Item 63 attach with : 1 Tie-Cable NSA935401-05 Item 53 or 1 Tie-Cable NSA935401-13 Item 62

(5) Subtask 242105-831-004-001 - Modify the routing in the RH forward wing to fuselage fairing. Work Zones and Access Panels Zone Access/Work location 612 Access Panel 613RR, Panel 613QL Work location from Rib 01 to Rib 04 Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills NON SPECIFIC Material necessary to do the job Kit 242105A01R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 52 EN6049-007-08-5 4 (M) SLEEVE 53 NSA935401-05 51 TIE 62 NSA935401-13 1 TIE 63 NSA5527-03-01 1 SPACER 66 EN6049-007-13-5 4 (M) SLEEVE 67 EN6049-007-19-5 4 (M) SLEEVE DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 116 6

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# @A310 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 85 NSA5516-08ND 16 CLAMP 86 NSA5516-18ND 16 CLAMP References Elec. Std. Practices Manual (ESPM) 20-25-51 20-33-33 20-33-41 20-33-44 Fig. A-FBBAA Modification of the routing in the forward wing to fuselage fairing (LH and RH side) Sheet 01 Sheet 02 Sheet 03
NOTE: To ensure the necessary access as described in Preparation SUBTASK 242105-010-003 001 Remove the Air Ducts and the Deflector in the LH Wings for access. . NOTE: To apply the following modification, unscrew without removal, all the necessary attachment points. (a) Refer to Fig. A-FBBAA Sheet 02

. In the Raceway Box and as shown on detail B-B, remove : 3 Screw Item (88) Retain 3 Washer Item (89) Retain 6 Clamp Item (87) Retain 6 Spacer Item (90) Retain 12 Clamp Item (84) Discard On detail C-C, remove: 1 Screw Item (88) Retain 1 Washer Item (89) Retain 1 Spacer Item (90) Retain 4 Clamp Item (84) Discard (b) Install the protective sleeve between the Rib 01 and Rib 05 and through the Raceway Box : Refer to Fig. A-FBBAA Sheet 01, Fig. A-FBBAA Sheet 02 and Fig. A-FBBAA Sheet 03 DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 117 6

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# @A310 SERVICE BULLETIN

1 Install : Refer to ESPM 20-33-33 4 (M) Sleeve-Protective EN6049-007-08-5 Item 52 NOTE: The size of the sleeve should be chosen in accordance with the bundles size on A/C And/Or 4 (M) Sleeve-Protective EN6049-007-13-5 Item 66 And/Or 4 (M) Sleeve-Protective EN6049-007-19-5 Item 67 2 Attach the Protective Sleeve with : 50 Tie-Cable NSA935401-05 Item 53 (c) In the Raceway Box and as shown on detail B-B, install : Refer to Fig. A-FBBAA Sheet 02 12 Clamp NSA5516-08ND Item 85 Or 12 Clamp NSA5516-18ND Item 86 And 6 Spacer Item (90) Retained at removal And 6 Clamp Item (87) Retained at removal 3 Washer Item (89) Retained at removal 3 Screw Item (88) Retained at removal NOTE: Torque all the attachment points unscrewed at removal. (d) On detail C-C, install: Refer to Fig. A-FBBAA Sheet 02

. 4 Clamp NSA5516-08ND Item 85
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 118 6

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# @A310 SERVICE BULLETIN
Or 4 Clamp NSA5516-18ND Item 86 And 1 Spacer Item (90) Retained at removal And 1 Washer Item (89) Retained at removal 1 Screw Item (88) Retained at removal NOTE: Torque all the attachment points unscrewed at removal. (e) Install the spacer Item 63 on the route 2E and 2G : Refer to Fig. A-FBBAA Sheet 01 and Fig. A-FBBAA Sheet 02 section A-A. Refer to ESPM 20-33-41 1 Install : 1 Spacer NSA5527-03-01 Item 63 attach with : 1 Tie-Cable NSA935401-05 Item 53 or 1 Tie-Cable NSA935401-13 Item 62

(6) Subtask 242105-831-005-001 - Modify the routing on the LH shroud box leading edge. Work Zones and Access Panels Zone Access/Work location 573 Work location from Rib 01 to Rib 06 Manpower Resources Manhours 6.00 Minimum number of person 1 Subtask elapsed time 6.00 Skills NON SPECIFIC

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 119 6

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# @A310 SERVICE BULLETIN
Material necessary to do the job Kit 242105A01R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 52 EN6049-007-08-5 24 (M) SLEEVE 53 NSA935401-05 120 TIE 55 A9201346420000 1 GROMMET 56 NAS1801-3-17 6 SCREW 57 NAS1149D0316H 17 WASHER 60 NAS1801-3-13 4 SCREW 61 NSA5527-03-03 4 SPACER 62 NSA935401-13 4 TIE 63 NSA5527-03-01 6 SPACER 64 NSA5527-03-02 5 SPACER 66 EN6049-007-13-5 24 (M) SLEEVE 67 EN6049-007-19-5 24 (M) SLEEVE 69 NSA939510BN 2 (M) STRIP 91 A0041113620000 3 BRACKET 93 A0041113720000 3 BRACKET 96 NSA5516-10ND 8 CLAMP 97 NAS1801-3-14 3 SCREW 98 NAS1801-3-8 3 SCREW 99 NAS1801-3-16 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES 68 Epoxy Resin 08-051 As required References Aircraft Maintenance Manual (AMM) 20-27-00, Page Block 201 Elec. Std. Practices Manual (ESPM) 20-33-33 20-33-41 Fig. A-FBCAA Modification of the routing in the shroud box (LH and RH side) Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 NOTE: To apply the following modification, unscrew without removal, all the necessary attachment points. (a) As shown on detail E-E and K-K, remove the old brackets : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 06
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 120 6

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# @A310 SERVICE BULLETIN

1 Remove : 6 Screw Item (56) Discard 4 Screw Item (60) Discard 10 Washer Item (57) Discard 10 Bracket Item (58) Retain 20 Tie Item (53) Discard (b) Install the grommet on routes 1M and 2M. Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 05 section B-B and detail D. 1 If necessary remove and retain the clamp and the spacer installed before the hole. NOTE: Retain the hardware. 2 Install : Refer to AMM 20-27-00, Page Block 201 1 Grommet A9201346420000 Item 55 NOTE: Open the grommet Item 55 with a craft knife. 3 Install the clamp and the spacer if retained at removal. NOTE: Use the hardware retained at removal. (c) Install the protective sleeve between the Rib 01 and Rib 06 on routes 1M, 2M, 1S-3R-1V and 2S : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 05 1 Install : Refer to ESPM 20-33-33 24 (M) Sleeve-Protective EN6049-007-08-5 Item 52 And/Or 24 (M) Sleeve-Protective EN6049-007-13-5 Item 66 And/Or 24 (M) Sleeve-Protective EN6049-007-19-5 Item 67
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 121 6

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# @A310 SERVICE BULLETIN
NOTE: The size of the sleeve should be chosen by the operator in accordance with the bundles size. 2 Attach the Protective Sleeve with : 100 Tie-Cable NSA935401-05 Item 53 (d) As shown on detail F-F and L-L, install the spacers between the structure and the brackets. Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 06 1 Install : 10 Bracket Item (58) Retained at removal 6 Spacer NSA5527-03-01 Item 63 4 Spacer NSA5527-03-03 Item 61 6 Screw NAS1801-3-17 Item 56 4 Screw NAS1801-3-13 Item 60 10 Washer NAS1149D0316H Item 57 20 Tie-Cable NSA935401-05 Item 53 (e) Install the spacers between routes 1M and 2M and between routes 2S and 1S-3R-1V. Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 05 detail A-A. 1 Install : Refer to ESPM 20-33-41 4 Spacer NSA5527-03-02 Item 64 4 Tie-Cable NSA935401-13 Item 62 (f) Modify the routing of the routes 1P and 2P. 1 As shown on detail C-C remove the old clamps: Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 04

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 122 6

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# @A310 SERVICE BULLETIN

a Remove : 3 Screw Item (88) Discard 3 Washer Item (81) Discard 6 Clamp Item (95) Discard 3 Spacer Item (90) Discard 2 As shown on detail G-G remove the old brackets : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02 and Fig. A-FBCAA Sheet 03
a Remove : 1 Screw Item (99) Discard 1 Washer Item (57) Discard 2 Clamp Item (95) Discard 1 Spacer Item (90) Discard 3 As shown on detail D-D and H-H install a protection on the hole of the Rib : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 04
a Install : 2 (M) Strip-Protective NSA939510BN Item 69 With : Item 68 Epoxy Resin 08-051 As required 4 As shown on detail D-D install the new brackets : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03, Fig. A-FBCAA Sheet 04 and Fig. A-FBCAA Sheet 05
a Install : 3 Bracket A0041113620000 Item 91 Or 3 Bracket A0041113720000 Item 93 Attach with :

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 123 6

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# @A310 SERVICE BULLETIN
3 Screw NAS1801-3-8 Item 98 3 Washer NAS1149D0316H Item 57 NOTE: Case 01 : If bracket PN A924-40102 is installed, install item 91. Case 02 : If bracket PN NSA5456-03 is installed, install item 93. The new bracket have to be in contact with the Rib. b On the new bracket Item 91 or 93, install : 6 Clamp NSA5516-10ND Item 96 3 Washer NAS1149D0316H Item 57 3 Screw NAS1801-3-14 Item 97 5 As shown on detail H-H install the new brackets : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 05
a Install : 1 Spacer NSA5527-03-02 Item 64 2 Clamp NSA5516-10ND Item 96 1 Washer NAS1149D0316H Item 57 1 Screw NAS1801-3-16 Item 99

(7) Subtask 242105-831-006-001 - Modify the routing on the RH shroud box leading edge. Work Zones and Access Panels Zone Access/Work location 673 Work location from Rib 01 to Rib 06 Manpower Resources Manhours 6.00 Minimum number of person 1 Subtask elapsed time 6.00 Skills NON SPECIFIC

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 124 6

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# @A310 SERVICE BULLETIN
Material necessary to do the job Kit 242105A01R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 52 EN6049-007-08-5 24 (M) SLEEVE 53 NSA935401-05 120 TIE 55 A9201346420000 1 GROMMET 56 NAS1801-3-17 6 SCREW 57 NAS1149D0316H 17 WASHER 60 NAS1801-3-13 4 SCREW 61 NSA5527-03-03 4 SPACER 62 NSA935401-13 4 TIE 63 NSA5527-03-01 6 SPACER 64 NSA5527-03-02 5 SPACER 66 EN6049-007-13-5 24 (M) SLEEVE 67 EN6049-007-19-5 24 (M) SLEEVE 69 NSA939510BN 2 (M) STRIP 92 A0041113620100 3 BRACKET 94 A0041113720100 3 BRACKET 96 NSA5516-10ND 8 CLAMP 97 NAS1801-3-14 3 SCREW 98 NAS1801-3-8 3 SCREW 99 NAS1801-3-16 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES 68 Epoxy Resin 08-051 As required References Aircraft Maintenance Manual (AMM) 20-27-00, Page Block 201 Elec. Std. Practices Manual (ESPM) 20-33-33 20-33-41 Fig. A-FBCAA Modification of the routing in the shroud box (LH and RH side) Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 NOTE: Workstep for removal of hydraulic pipes should be performed before this workstep. NOTE: To apply the following modification, unscrew without removal, all the necessary attachment points.

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 125 6

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# @A310 SERVICE BULLETIN (a) As shown on detail E-E and K-K, remove the old brackets : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 06 1 Remove : 6 Screw Item (56) Discard 4 Screw Item (60) Discard 10 Washer Item (57) Discard 10 Bracket Item (58) Retain 20 Tie Item (53) Discard (b) Install the grommet on routes 1M and 2M. Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 05 section B-B and D. 1 If necessary remove and retain the clamp and the spacer installed before the hole. NOTE: Retain the hardware. 2 Install : Refer to AMM 20-27-00, Page Block 201 1 Grommet A9201346420000 Item 55 NOTE: Open the grommet Item 55 with a craft knife. 3 Install the clamp and the spacer if retained at removal. NOTE: Use the hardware retained at removal. (c) Install the protective sleeve between the Rib 01 and Rib 06 on routes 1M, 2M, 1S-3R-1V and 2S : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 05 1 Install : Refer to ESPM 20-33-33 24 (M) Sleeve-Protective EN6049-007-08-5 Item 52 And/Or

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 126 6

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# @A310 SERVICE BULLETIN 24 (M) Sleeve-Protective EN6049-007-13-5 Item 66 And/Or 24 (M) Sleeve-Protective EN6049-007-19-5 Item 67 NOTE: The size of the sleeve should be choosen by the operator in accordance with the bundles size. 2 Attach the Protective Sleeve with : 100 Tie-Cable NSA935401-05 Item 53 (d) As shown on detail F-F and L-L, install the spacers between the structure and the brackets. Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 06 1 Install : 10 Bracket Item (58) Retained at removal 6 Spacer NSA5527-03-01 Item 63 4 Spacer NSA5527-03-03 Item 61 6 Screw NAS1801-3-17 Item 56 4 Screw NAS1801-3-13 Item 60 10 Washer NAS1149D0316H Item 57 20 Tie-Cable NSA935401-05 Item 53 (e) Install the spacers between routes 1M and 2M and between routes 1S and 2S-3R-2V. Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 05 detail A-A. 1 Install : Refer to ESPM 20-33-41 4 Spacer NSA5527-03-02 Item 64 4 Tie-Cable NSA935401-13 Item 62

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 127 6

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# @A310 SERVICE BULLETIN (f) Modify the routing of the routes 1P and 2P. 1 As shown on detail C-C remove the old clamps: Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 04
a Remove : 3 Screw Item (88) Discard 3 Washer Item (81) Discard 6 Clamp Item (95) Discard 3 Spacer Item (90) Discard 2 As shown on detail G-G remove the old brackets : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02 and Fig. A-FBCAA Sheet 03
a Remove : 1 Screw Item (99) Discard 1 Washer Item (57) Discard 2 Clamp Item (95) Discard 1 Spacer Item (90) Discard 3 As shown on detail D-D and H-H install a protection on the hole of the Rib : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 04
a Install : 2 (M) Strip-Protective NSA939510BN Item 69 With : Item 68 Epoxy Resin 08-051 As required 4 As shown on detail D-D install the new brackets : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03, Fig. A-FBCAA Sheet 04 and Fig. A-FBCAA Sheet 05
a Install : 3 Bracket A0041113620100 Item 92 DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 128 6

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# @A310 SERVICE BULLETIN
Or 3 Bracket A0041113720100 Item 94 Attach with : 3 Screw NAS1801-3-8 Item 98 3 Washer NAS1149D0316H Item 57 NOTE: Case 01 : If bracket PN A924-40102 is installed, install item 92. Case 02 : If bracket PN NSA5456-03 is installed, install item 94. The new bracket have to be in contact with the Rib. b On the new bracket Item 92 or 94, install : 6 Clamp NSA5516-10ND Item 96 3 Washer NAS1149D0316H Item 57 3 Screw NAS1801-3-14 Item 97 5 As shown on detail H-H install the new brackets : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 05
a Install : 1 Spacer NSA5527-03-02 Item 64 2 Clamp NSA5516-10ND Item 96 1 Washer NAS1149D0316H Item 57 1 Screw NAS1801-3-16 Item 99

(8) Subtask 242105-831-401-001 - Install new nutplate on the RH wing Leading edge Work Zones and Access Panels Zone Access/Work location 620 Access Panel 624KB Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 129 6

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# @A310 SERVICE BULLETIN
Material necessary to do the job Kit 242105B01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 106 NSA5456-3-8 1 NUTPLATE 111 ANSA2050DCJ3210 2 RIVET Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Multi Purpose Thixotropic Paste 09-016J As required
References Structural Repair Manual (SRM) 51-77-10 Fig. A-UBAAA Installation of the new clip and nutplate Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Install new nutplate on the RH wing leading edge in the location of Rib 28a, refer to Fig. A-UBAAA Sheet 01 , Fig. A-UBAAA Sheet 03 and Fig. A-UBAAA Sheet 04

. 1 On the center line of existing anchor nut as indicated, make sure the nutplate, Item 106 is in the correct position. 2 Use: 1 Nutplate NSA5456-3-8 Item 106 3 Mark out and drill two 3.2 mm (0.125 in.) holes in the structure. 4 Wet assemble, Items 106 to the structure with: Multi Purpose Thixotropic Paste 09-016J As required

use: 2 Rivet ANSA2050DCJ3210 Item 111

(9) Subtask 242105-831-211-003 - Modify the electrical routing installation at the LH front spar in the area of RIB 2. Work Zones and Access Panels Zone Access/Work location 512 Work location Rib 2

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 130 6

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# @A310 SERVICE BULLETIN
Manpower Resources Manhours 1.75 Minimum number of person 1 Subtask elapsed time 1.75 Skills NON SPECIFIC Material necessary to do the job Kit 242105D01R08 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 18 MS21919WCH12 2 CLAMP 19 MS21919WCH4 2 CLAMP 43 NSA935401-03 16 TIE 100 B9239030000200 4 PLACARD References Elec. Std. Practices Manual (ESPM) 20-33-33 Fig. A-GDAAB Modification of the electrical routing installation at the LH front spar in the area of RIB 2 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Modify the electrical routing installation at the LH front spar in the area of RIB 2. 1 Remove these items: Refer to Fig. A-GDAAB Sheet 03, Section A-A. 2 Clamp Item (54) Discard 2 Clamp Item (57) Discard 2 Clamp Item (78) Retain with 1 Washer Item (70) Retain 1 Screw Item (72) Retain 1 Spacer Item (73) Retain 1 Spacer Item (79) Retain or Remove these items: Refer to Fig. A-GDAAB Sheet 03, Section B-B. DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 131 6

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# @A310 SERVICE BULLETIN 2 Clamp Item (54) Discard 2 Clamp Item (57) Discard with 1 Washer Item (70) Retain 1 Spacer Item (73) Retain 1 Screw Item (77) Retain NOTE: The different installations are depending on the installation in the aircraft. 2 Install the electrical wires with the protection sleeves: NOTE: The protection sleeves are previously installed with subtask 242105-831-003-001. Refer to Fig. A-GDAAB Sheet 03, Section C-C. 2 Clamp MS21919WCH12 Item 18 2 Clamp MS21919WCH4 Item 19 2 Clamp Item (78) Retained at removal with 1 Washer Item (70) Retained at removal 1 Screw Item (72) Retained at removal 1 Spacer Item (73) Retained at removal 1 Spacer Item (79) Retained at removal or Install the electrical wires with the protection sleeves: NOTE: The protection sleeves are previously installed with subtask 242105-831-003-001. Refer to Fig. A-GDAAB Sheet 04, Section D-D.

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 132 6

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# @A310 SERVICE BULLETIN 2 Clamp MS21919WCH12 Item 18 2 Clamp MS21919WCH4 Item 19 2 Clamp Item (78) Retained at removal with 1 Washer Item (70) Retained at removal 1 Spacer Item (73) Retained at removal 1 Screw Item (77) Retain 3 Before installation, cut the protection sleeve to its required length and install with: Refer to ESPM 20-33-33. Refer to Fig. A-GDAAB Sheet 02, View C. 16 Tie NSA935401-03 Item 43 4 Install the Service Bulletin placards: Refer to Fig. A-GDAAB Sheet 04, View D. 4 Placard B9239030000200 Item 100 in a good visible position. (10) Subtask 242105-831-212-003 - Modify the electrical routing installation at the RH front spar in the area of RIB 2. Work Zones and Access Panels Zone Access/Work location 612 Manpower Resources Manhours 1.75 Minimum number of person 1 Subtask elapsed time 1.75 Skills NON SPECIFIC

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 133 6

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# @A310 SERVICE BULLETIN
Material necessary to do the job Kit 242105D01R08 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 19 MS21919WCH4 1 CLAMP 29 MS21919WCH11 2 CLAMP 30 MS21919WCH5 1 CLAMP 43 NSA935401-03 16 TIE 100 B9239030000200 4 PLACARD References Elec. Std. Practices Manual (ESPM) 20-33-33 Fig. A-GDBAB Modification of the electrical routing installation at the RH front spar in the area of RIB 2 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Modify the electrical routing installation at the RH front spar in the area of RIB 2. 1 Remove these items: Refer to Fig. A-GDBAB Sheet 03, Section A-A. 1 Clamp Item (54) Discard 2 Clamp Item (58) Discard 1 Clamp Item (61) Discard 2 Clamp Item (78) Retain with 1 Washer Item (70) Retain 1 Screw Item (72) Retain 1 Spacer Item (73) Retain 1 Spacer Item (79) Retain or Remove these items: Refer to Fig. A-GDBAB Sheet 03, Section B-B. 1 Clamp Item (54) Discard

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 134 6

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# @A310 SERVICE BULLETIN 2 Clamp Item (58) Discard 1 Clamp Item (61) Discard with 1 Washer Item (70) Retain 1 Spacer Item (73) Retain 1 Screw Item (77) Retain NOTE: The different installations are depending on the installation in the aircraft. 2 Install the electrical wires with the protection sleeves: NOTE: The protection sleeves are previously installed with subtask 242105-831-004-001. Refer to Fig. A-GDBAB Sheet 04, Section C-C. 1 Clamp MS21919WCH4 Item 19 2 Clamp MS21919WCH11 Item 29 1 Clamp MS21919WCH5 Item 30 2 Clamp Item (78) Retained at removal with 1 Washer Item (70) Retained at removal 1 Screw Item (72) Retained at removal 1 Spacer Item (73) Retained at removal 1 Spacer Item (79) Retained at removal or Install the electrical wires with the previously installed protection sleeves: NOTE: The protection sleeves are previously installed with subtask 242105-831-004-001.

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 135 6

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# @A310 SERVICE BULLETIN
Refer to Fig. A-GDBAB Sheet 04, Section D-D. 1 Clamp MS21919WCH4 Item 19 2 Clamp MS21919WCH11 Item 29 1 Clamp MS21919WCH5 Item 30 with 1 Washer Item (70) Retained at removal 1 Spacer Item (73) Retained at removal 1 Screw Item (77) Retain 3 Before installation, cut the protection sleeve to its required length and install with: Refer to ESPM 20-33-33. Refer to Fig. A-GDBAB Sheet 02, View C. 16 Tie NSA935401-03 Item 43 4 Install the Service Bulletin placards: Refer to Fig. A-GDBAB Sheet 04, View D. 4 Placard B9239030000200 Item 100 in a good visible position. (11) Subtask 242105-831-213-001 - Modify the electrical routing installation at the LH front spar in the area of RIB 3. Work Zones and Access Panels Zone Access/Work location 512 Manpower Resources Manhours 1.75 Minimum number of person 1 Subtask elapsed time 1.75 Skills NON SPECIFIC

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 136 6

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# @A310 SERVICE BULLETIN
Material necessary to do the job Kit 242105D01R08 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 18 MS21919WCH12 1 CLAMP 19 MS21919WCH4 1 CLAMP 20 EN6049-007-05-5 1 (ME) SLEEVE 21 EN6049-007-19-5 1 (ME) SLEEVE 100 B9239030000200 2 PLACARD References Elec. Std. Practices Manual (ESPM) 20-33-33 Fig. A-GDCAA Modification of the electrical routing installation at the LH front spar in the area of RIB 3 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Modify the electrical routing installation at the LH front spar in the area of RIB 3. 1 Remove these items: Refer to Fig. A-GDCAA Sheet 03, Section A-A. 1 Clamp Item (54) Discard 1 Clamp Item (57) Discard 2 Clamp Item (78) Retain and 1 Washer Item (70) Retain 1 Screw Item (72) Retain 2 Spacer Item (73) Retain 1 Spacer Item (79) Retain or Remove these items: Refer to Fig. A-GDCAA Sheet 03, Section B-B. 1 Clamp Item (54) Discard 1 Clamp Item (57) Discard

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 137 6

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# @A310 SERVICE BULLETIN
and 1 Washer Item (70) Retain 1 Spacer Item (73) Retain 1 Screw Item (77) Retain NOTE: The different installations are depending on the installation in the aircraft. 2 Install the electrical wires with protection sleeves: Refer to Fig. A-GDCAA Sheet 04, Section C-C. 1 (ME) Sleeve EN6049-007-05-5 Item 20 1 (ME) Sleeve EN6049-007-19-5 Item 21 with 1 Clamp MS21919WCH12 Item 18 1 Clamp MS21919WCH4 Item 19 2 Clamp Item (78) Retained at removal and 1 Washer Item (70) Retained at removal 1 Screw Item (72) Retained at removal 2 Spacer Item (73) Retained at removal 1 Spacer Item (79) Retained at removal NOTE: Before installation, cut the sleeves, Items 20 and 21, to its required length, refer to Fig. A-GDCAA Sheet 02, View C, refer to ESPM 20-33-33.
or Install the electrical wires with protection sleeves: Refer to Fig. A-GDCAA Sheet 04, Section D-D.

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 138 6

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# @A310 SERVICE BULLETIN 1 (ME) Sleeve EN6049-007-05-5 Item 20 1 (ME) Sleeve EN6049-007-19-5 Item 21 with 1 Clamp MS21919WCH12 Item 18 1 Clamp MS21919WCH4 Item 19 and 1 Washer Item (70) Retained at removal 1 Spacer Item (73) Retained at removal 1 Screw Item (77) Retained at removal NOTE: Before installation, cut the sleeves, Items 20 and 21, to its required length, refer to Fig. A-GDCAA Sheet 02, View C, refer to ESPM 20-33-33. 3 Install the Service Bulletin placards: Refer to Fig. A-GDCAA Sheet 04, View D. 2 Placard B9239030000200 Item 100 in a good visible position. (12) Subtask 242105-831-214-001 - Modify the electrical routing installation at the RH front spar in the area of RIB 3. Work Zones and Access Panels Zone Access/Work location 612 Manpower Resources Manhours 1.75 Minimum number of person 1 Subtask elapsed time 1.75 Skills NON SPECIFIC

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 139 6

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# @A310 SERVICE BULLETIN
Material necessary to do the job Kit 242105D01R08 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 19 MS21919WCH4 2 CLAMP 20 EN6049-007-05-5 1 (ME) SLEEVE 21 EN6049-007-19-5 1 (ME) SLEEVE 29 MS21919WCH11 4 CLAMP 100 B9239030000200 2 PLACARD References Elec. Std. Practices Manual (ESPM) 20-33-33 Fig. A-GDDAA Modification of the electrical routing installation at the RH front spar in the area of RIB 3 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Modify the electrical routing installation at the RH front spar in the area of RIB 3. 1 Remove these items: Refer to Fig. A-GDDAA Sheet 03, Section A-A. 2 Clamp Item (54) Discard 2 Clamp Item (58) Discard 4 Clamp Item (78) Retain and 2 Washer Item (70) Retain 2 Screw Item (72) Retain 4 Spacer Item (73) Retain 2 Spacer Item (79) Retain or Remove these items: Refer to Fig. A-GDDAA Sheet 03, Section B-B. 2 Clamp Item (54) Discard 2 Clamp Item (58) Discard

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 140 6

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# @A310 SERVICE BULLETIN
and 2 Washer Item (70) Retain 2 Spacer Item (73) Retain 2 Screw Item (77) Retain NOTE: The different installations are depending on the installation in the aircraft. 2 Install the electrical wires with protection sleeves: Refer to Fig. A-GDDAA Sheet 04, Section C-C. 1 (ME) Sleeve EN6049-007-05-5 Item 20 1 (ME) Sleeve EN6049-007-19-5 Item 21 with 2 Clamp MS21919WCH4 Item 19 2 Clamp MS21919WCH11 Item 29 2 Clamp Item (78) Retained at removal and 2 Washer Item (70) Retained at removal 2 Screw Item (72) Retained at removal 4 Spacer Item (73) Retained at removal 2 Spacer Item (79) Retained at removal NOTE: Before installation, cut the sleeves, Items 20 and 21, to its required length, refer to Fig. A-GDDAA Sheet 02, View C, refer to ESPM 20-33-33).
or Install the electrical wires with protection sleeves: Refer to Fig. A-GDDAA Sheet 04, Section D-D.

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 141 6

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# @A310 SERVICE BULLETIN 1 (ME) Sleeve EN6049-007-05-5 Item 20 1 (ME) Sleeve EN6049-007-19-5 Item 21 with 2 Clamp MS21919WCH4 Item 19 2 Clamp MS21919WCH11 Item 29 and 2 Washer Item (70) Retained at removal 2 Spacer Item (73) Retained at removal 2 Screw Item (77) Retained at removal 3 Install the Service Bulletin placards: Refer to Fig. A-GDDAA Sheet 04, View D. 2 Placard B9239030000200 Item 100 in a good visible position. (13) Subtask 242105-831-215-001 - Modify the electrical routing installation at the LH and RH front spars in the area of RIB 5 and RIB 6. Work Zones and Access Panels Zone Access/Work location 512 612 Manpower Resources Manhours 2.50 Minimum number of person 2 Subtask elapsed time 1.25 Skills NON SPECIFIC Material necessary to do the job Kit 242105D01R08 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 MS21919WCH10 2 CLAMP 3 NAS1149D0332K 2 WASHER 4 NSA5527-03-03D 2 SPACER DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 142 6

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# @A310 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 19 MS21919WCH4 2 CLAMP 23 NAS1801-3-16 4 SCREW 24 MS21042-3 2 NUT 31 NAS1801-3-13 2 SCREW 32 NSA5527-03-07D 4 SPACER 42 A9249252400400 2 RAMP References Fig. A-GEAAA Modification of the electrical routing installation at the LH/RH front spars in the area of RIB 5 and RIB 6 Sheet 01 Sheet 02 Sheet 03 (a) Modify the electrical routing installation at the LH and RH front spar in the area of RIB 5 and RIB 6. 1 Remove these items: Refer to Fig. A-GEAAA Sheet 02, Section A-A. 4 Clamp Item (10) Retain 4 Clamp Item (19) Retain and 4 Washer Item (3) Retain 4 Spacer Item (4) Retain 4 Screw Item (5) Discard 2 Install the electrical wires with: Refer to Fig. A-GEAAA Sheet 03, Section B-B. 2 Ramp A9249252400400 Item 42 and 4 Washer Item (3) Retained at removal 4 Spacer Item (4) Retained at removal 4 Clamp Item (10) Retained at removal

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 143 6

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# @A310 SERVICE BULLETIN 4 Clamp Item (19) Retained at removal 4 Screw NAS1801-3-16 Item 23 4 Spacer NSA5527-03-07D Item 32 3 Install the electrical wires at the ramp, Item 42, with: Refer to Fig. A-GEAAA Sheet 03, Section C-C. 2 Clamp MS21919WCH10 Item 2 2 Clamp MS21919WCH4 Item 19 and 2 Spacer NSA5527-03-03D Item 4 2 Washer NAS1149D0332K Item 3 2 Nut MS21042-3 Item 24 2 Screw NAS1801-3-13 Item 31

(14) Subtask 242105-831-216-002 - Modify the electrical routing installation at the LH and RH front spars in the area of RIB 7 and RIB 8. Work Zones and Access Panels Zone Access/Work location 512 612 Manpower Resources Manhours 0.50 Minimum number of person 2 Subtask elapsed time 0.25 Skills NON SPECIFIC Material necessary to do the job Kit 242105D01R08 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 3 NAS1149D0332K 2 WASHER 6 NAS1801-3-10 2 SCREW 7 NSA5527-03-05D 2 SPACER 10 MS21919WCH2 2 CLAMP 100 B9239030000200 1 PLACARD

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 144 6

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# @A310 SERVICE BULLETIN

References Fig. A-GFAAA Modification of the electrical routing installation at the LH/RH front spars in the area of RIB 7 and RIB 8 Sheet 01 Sheet 02
(a) Install additional clamps at the LH and RH front spars in the area of RIB 8. NOTE: Make sure that the work step "Install adhesive clipping brackets", subtask 242105-831-402-001, is done before you start with this work step. 1 Install these items: Refer to Fig. A-GFAAA Sheet 02, View C. 2 Clamp MS21919WCH2 Item 10 with 2 Washer NAS1149D0332K Item 3 2 Screw NAS1801-3-10 Item 6 2 Spacer NSA5527-03-05D Item 7 2 Install the Service Bulletin placards: Refer to Fig. A-GFAAA Sheet 02, View D. 1 Placard B9239030000200 Item 100 in a good visible position. (15) Subtask 242105-831-220-001 - Modify the electrical routing installation at the RH front spar in the area of RIB 28 and RIB 28A. Work Zones and Access Panels Zone Access/Work location 624 Manpower Resources Manhours 1.50 Minimum number of person 1 Subtask elapsed time 1.50 Skills NON SPECIFIC

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 145 6

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# @A310 SERVICE BULLETIN
Material necessary to do the job Kit 242105D01R08 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 3 NAS1149D0332K 1 WASHER 9 MS21919WCH3 3 CLAMP 27 NSA5527-03-15D 2 SPACER 28 NAS1801-3-30 1 SCREW 100 B9239030000200 2 PLACARD References Fig. A-GJAAA Modification of the electrical routing installation at the RH front spar in the area of RIB 28 and RIB 28A Sheet 01 Sheet 02 Sheet 03 (a) Modify electrical routing installation at the RH front spar in the area of RIB 28 and 28A. 1 Remove these items: Refer to Fig. A-GJAAA Sheet 02, View C. 3 Clamp Item (9) Discard and 1 Washer Item (3) Discard 3 Spacer Item (8) Discard 1 Screw Item (56) Discard 2 Install these items: NOTE: Make sure that the work step "Install Adhesive Clipping Bracket on the LH and RH Wing Leading Edge in the Area of Rib 7" is done before you start with this work step. Refer to Fig. A-GJAAA Sheet 03, View E. 3 Clamp MS21919WCH3 Item 9 with 1 Washer NAS1149D0332K Item 3 2 Spacer NSA5527-03-15D Item 27 1 Screw NAS1801-3-30 Item 28
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 146 6

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# @A310 SERVICE BULLETIN
3 Install the Service Bulletin placard: Refer to Fig. A-GJAAA Sheet 03, View F. 2 Placard B9239030000200 Item 100 in a good visible position. **CONF 003 (1) Subtask 242105-831-402-001 - Install Adhesive Clipping Bracket on the LH and RH Wing Leading Edge in the Area of Rib 7 Work Zones and Access Panels Zone Access/Work location 520 Access Panel 512HB 620 Access Panel 612HB Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Kit 242105B01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 102 ABS1546B3C12 2 BRACKET Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Two Part Paste Adhesive 08-078 As required Solvent General Purpose 11-026 As required Lint-Free Cotton Cloth 19-003 As required References Structural Repair Manual (SRM) 51-77-10 Fig. A-UBAAA Installation of the new clip and nutplate Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Install on the LH and RH wing leading edge in the area of Rib 7 the item that follows, refer to Fig. A-UBAAA Sheet 01 and Fig. A-UBAAA Sheet 02: 2 Bracket ABS1546B3C12 Item 102

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 147 6

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# @A310 SERVICE BULLETIN

1 Measure and mark out the location of the new bracket, Item 102. 2 Clean the areas to be bonded, both structure and bracket, Item 102 with a: Lint-Free Cotton Cloth 19-003 As required
made moist with: Solvent General Purpose 11-026 As required
3 Use Scotchbrite to lightly abrade the surface then clean with the general solvent. 4 Mix together: Two Part Paste Adhesive 08-078 As required
in accordance with SRM 51-77-10 5 Put a small amount of adhesive to the center of the base of the bracket, Item 102. The quantity applied must be sufficient to enable slight flow of excess adhesive around the complete periphery of the base. 6 Remove the adhesive paper from the adaptor bearing points and discard it. 7 Position the adaptor on the structure within the area previously marked. Press on the ends of the adaptor so the foam pads adhere to the structure. 8 Press on the center section of the adaptor without exerting pressure on the bracket, Item 102. The over-centering and the adaptor cause the adhesive to flow and keep the bracket, Item 102 in place during curing. 9 Once the adhesive has cured in accordance with SRM 51-77-10, remove the adaptor and discard. (2) Subtask 242105-831-001-001 - Attach the routes 1E and 1G with the lacing tape in the LH shroud box leading edge. Work Zones and Access Panels Zone Access/Work location 137 Work location from Frame 39 to Frame 40 from Stringer 28 to Stringer 30 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON SPECIFIC

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 148 6

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# @A310 SERVICE BULLETIN
Material necessary to do the job Kit 242105A01R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 51 NSA8420-5 1 (M) CORD 53 NSA935401-05 1 TIE 62 NSA935401-13 2 TIE 63 NSA5527-03-01 1 SPACER 65 A9222505750000 1 SPACER References Elec. Std. Practices Manual (ESPM) 20-33-44 Fig. A-FBAAA Modification of the routing between FR39 and FR40 at STGR28 to STGR30 (LH side) Sheet 01 Sheet 02
(a) Install the Bobbin Spacer in accordance with detail A-A (If not already installed on aircraft): Refer to Fig. A-FBAAA Sheet 02

. 1 Install : 1 Spacer-Feeder A9222505750000 Item 65 With : 1 Tie-Cable NSA935401-13 Item 62 2 Attach the routes 1E and 1G with (If not already installed on aircraft) : 1 Spacer NSA5527-03-01 Item 63 1 Tie-Cable NSA935401-05 Item 53 Or 1 Tie-Cable NSA935401-13 Item 62 (b) Install the lacing tape to attach the routes 1E and 1G together (To keep the necessary distance between the two routes) in accordance with detail B-B : Refer to Fig. A-FBAAA Sheet 02 Refer to ESPM 20-33-44 NOTE: Cut the lacing tape to the necessary length. 1 (M) Cord-Fiber Glass NSA8420-5 Item 51

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 149 6

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# @A310 SERVICE BULLETIN (3) Subtask 242105-831-002-001 - Attach the routes 2E and 2G with the lacing tape in the RH shroud box leading edge. Work Zones and Access Panels Zone Access/Work location 138 Work location from Frame 39 to Frame 40 from Stringer 28 to Stringer 30 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON SPECIFIC Material necessary to do the job Kit 242105A01R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 51 NSA8420-5 1 (M) CORD 53 NSA935401-05 1 TIE 62 NSA935401-13 2 TIE 63 NSA5527-03-01 1 SPACER 65 A9222505750000 1 SPACER References Elec. Std. Practices Manual (ESPM) 20-33-44 Fig. A-FBEAA Modification of the routing between FR39 and FR40 at STGR28 to STGR30 (RH side) Sheet 01 Sheet 02
(a) Install the Bobbin Spacer in accordance with detail A-A (If not already installed on aircraft): Refer to Fig. A-FBEAA Sheet 02

. 1 Install : 1 Spacer-Feeder A9222505750000 Item 65 With : 1 Tie-Cable NSA935401-13 Item 62 2 Attach the routes 2E and 2G with (If not already installed on aircraft) : 1 Spacer NSA5527-03-01 Item 63 1 Tie-Cable NSA935401-05 Item 53
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 150 6

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# @A310 SERVICE BULLETIN
Or 1 Tie-Cable NSA935401-13 Item 62 (b) Install the lacing tape to attach the routes 1E and 1G together (To keep the necessary distance between the two routes) in accordance with detail B-B : Refer to Fig. A-FBEAA Sheet 02 Refer to ESPM 20-33-44 NOTE: Cut the lacing tape to the necessary length. 1 (M) Cord-Fiber Glass NSA8420-5 Item 51

(4) Subtask 242105-831-003-001 - Modify the routing in the LH forward wing to fuselage fairing. Work Zones and Access Panels Zone Access/Work location 512 Access Panel 513RR, Panel 513QL Work location from Rib 01 to Rib 04 Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills NON SPECIFIC Material necessary to do the job Kit 242105A01R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 52 EN6049-007-08-5 4 (M) SLEEVE 53 NSA935401-05 51 TIE 62 NSA935401-13 1 TIE 63 NSA5527-03-01 1 SPACER 66 EN6049-007-13-5 4 (M) SLEEVE 67 EN6049-007-19-5 4 (M) SLEEVE 85 NSA5516-08ND 16 CLAMP 86 NSA5516-18ND 16 CLAMP References Elec. Std. Practices Manual (ESPM) 20-25-51 20-33-33 20-33-41 20-33-44

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 151 6

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# @A310 SERVICE BULLETIN

References Fig. A-FBBAA Modification of the routing in the forward wing to fuselage fairing (LH and RH side) Sheet 01 Sheet 02 Sheet 03
NOTE: To ensure the necessary access as described in Preparation SUBTASK 242105-010-003 001 Remove the Air Ducts and the Deflector in the LH Wings for access. . NOTE: Unscrew without removal, all the necessary attachment points. (a) Refer to Fig. A-FBBAA Sheet 02

. In the Raceway Box and as shown on detail B-B, remove: 3 Screw Item (88) Retain 3 Washer Item (89) Retain 6 Clamp Item (87) Retain 6 Spacer Item (90) Retain 12 Clamp Item (84) Discard On detail C-C, remove: 1 Screw Item (88) Retain 1 Washer Item (89) Retain 1 Spacer Item (90) Retain 4 Clamp Item (84) Discard (b) Install the protective sleeve between the Rib 01 and Rib 05 and through the Raceway Box : Refer to Fig. A-FBBAA Sheet 01, Fig. A-FBBAA Sheet 02 and Fig. A-FBBAA Sheet 03 1 Install : Refer to ESPM 20-33-33 4 (M) Sleeve-Protective EN6049-007-08-5 Item 52 NOTE: The size of the sleeve should be chosen in accordance with the bundles size on A/C And/Or DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 152 6

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# @A310 SERVICE BULLETIN 4 (M) Sleeve-Protective EN6049-007-13-5 Item 66 And/Or 4 (M) Sleeve-Protective EN6049-007-19-5 Item 67 2 Attach the Protective Sleeve with : 50 Tie-Cable NSA935401-05 Item 53 (c) In the Raceway Box and as shown on detail B-B, install : Refer to Fig. A-FBBAA Sheet 02 12 Clamp NSA5516-08ND Item 85 Or 12 Clamp NSA5516-18ND Item 86 And 6 Spacer Item (90) Retained at removal And 6 Clamp Item (87) Retained at removal 3 Washer Item (89) Retained at removal 3 Screw Item (88) Retained at removal NOTE: Torque all the attachment points unscrewed at removal. (d) On detail C-C, install: Refer to Fig. A-FBBAA Sheet 02

. 4 Clamp NSA5516-08ND Item 85 Or 4 Clamp NSA5516-18ND Item 86 And 1 Spacer Item (90) Retained at removal And
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 153 6

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# @A310 SERVICE BULLETIN
1 Washer Item (89) Retained at removal 1 Screw Item (88) Retained at removal NOTE: Torque all the attachment points unscrewed at removal. (e) Install the spacer Item 63 on the route 1E and 1G : Refer to Fig. A-FBBAA Sheet 01 and Fig. A-FBBAA Sheet 02 section A-A. Refer to ESPM 20-33-41 1 Install : 1 Spacer NSA5527-03-01 Item 63 attach with : 1 Tie-Cable NSA935401-05 Item 53 or 1 Tie-Cable NSA935401-13 Item 62

(5) Subtask 242105-831-004-001 - Modify the routing in the RH forward wing to fuselage fairing. Work Zones and Access Panels Zone Access/Work location 612 Access Panel 613RR, Panel 613QL Work location from Rib 01 to Rib 04 Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills NON SPECIFIC Material necessary to do the job Kit 242105A01R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 52 EN6049-007-08-5 4 (M) SLEEVE 53 NSA935401-05 51 TIE 62 NSA935401-13 1 TIE 63 NSA5527-03-01 1 SPACER 66 EN6049-007-13-5 4 (M) SLEEVE 67 EN6049-007-19-5 4 (M) SLEEVE DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 154 6

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# @A310 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 85 NSA5516-08ND 16 CLAMP 86 NSA5516-18ND 16 CLAMP References Elec. Std. Practices Manual (ESPM) 20-25-51 20-33-33 20-33-41 20-33-44 Fig. A-FBBAA Modification of the routing in the forward wing to fuselage fairing (LH and RH side) Sheet 01 Sheet 02 Sheet 03
NOTE: To ensure the necessary access as described in Preparation SUBTASK 242105-010-003 001 Remove the Air Ducts and the Deflector in the LH Wings for access. . NOTE: To apply the following modification, unscrew without removal, all the necessary attachment points. (a) Refer to Fig. A-FBBAA Sheet 02

. In the Raceway Box and as shown on detail B-B, remove : 3 Screw Item (88) Retain 3 Washer Item (89) Retain 6 Clamp Item (87) Retain 6 Spacer Item (90) Retain 12 Clamp Item (84) Discard On detail C-C, remove: 1 Screw Item (88) Retain 1 Washer Item (89) Retain 1 Spacer Item (90) Retain 4 Clamp Item (84) Discard (b) Install the protective sleeve between the Rib 01 and Rib 05 and through the Raceway Box : Refer to Fig. A-FBBAA Sheet 01, Fig. A-FBBAA Sheet 02 and Fig. A-FBBAA Sheet 03 DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 155 6

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# @A310 SERVICE BULLETIN

1 Install : Refer to ESPM 20-33-33 4 (M) Sleeve-Protective EN6049-007-08-5 Item 52 NOTE: The size of the sleeve should be chosen in accordance with the bundles size on A/C And/Or 4 (M) Sleeve-Protective EN6049-007-13-5 Item 66 And/Or 4 (M) Sleeve-Protective EN6049-007-19-5 Item 67 2 Attach the Protective Sleeve with : 50 Tie-Cable NSA935401-05 Item 53 (c) In the Raceway Box and as shown on detail B-B, install : Refer to Fig. A-FBBAA Sheet 02 12 Clamp NSA5516-08ND Item 85 Or 12 Clamp NSA5516-18ND Item 86 And 6 Spacer Item (90) Retained at removal And 6 Clamp Item (87) Retained at removal 3 Washer Item (89) Retained at removal 3 Screw Item (88) Retained at removal NOTE: Torque all the attachment points unscrewed at removal. (d) On detail C-C, install: Refer to Fig. A-FBBAA Sheet 02

. 4 Clamp NSA5516-08ND Item 85
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 156 6

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# @A310 SERVICE BULLETIN
Or 4 Clamp NSA5516-18ND Item 86 And 1 Spacer Item (90) Retained at removal And 1 Washer Item (89) Retained at removal 1 Screw Item (88) Retained at removal NOTE: Torque all the attachment points unscrewed at removal. (e) Install the spacer Item 63 on the route 2E and 2G : Refer to Fig. A-FBBAA Sheet 01 and Fig. A-FBBAA Sheet 02 section A-A. Refer to ESPM 20-33-41 1 Install : 1 Spacer NSA5527-03-01 Item 63 attach with : 1 Tie-Cable NSA935401-05 Item 53 or 1 Tie-Cable NSA935401-13 Item 62

(6) Subtask 242105-831-005-001 - Modify the routing on the LH shroud box leading edge. Work Zones and Access Panels Zone Access/Work location 573 Work location from Rib 01 to Rib 06 Manpower Resources Manhours 6.00 Minimum number of person 1 Subtask elapsed time 6.00 Skills NON SPECIFIC

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 157 6

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# @A310 SERVICE BULLETIN
Material necessary to do the job Kit 242105A01R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 52 EN6049-007-08-5 24 (M) SLEEVE 53 NSA935401-05 120 TIE 55 A9201346420000 1 GROMMET 56 NAS1801-3-17 6 SCREW 57 NAS1149D0316H 17 WASHER 60 NAS1801-3-13 4 SCREW 61 NSA5527-03-03 4 SPACER 62 NSA935401-13 4 TIE 63 NSA5527-03-01 6 SPACER 64 NSA5527-03-02 5 SPACER 66 EN6049-007-13-5 24 (M) SLEEVE 67 EN6049-007-19-5 24 (M) SLEEVE 69 NSA939510BN 2 (M) STRIP 91 A0041113620000 3 BRACKET 93 A0041113720000 3 BRACKET 96 NSA5516-10ND 8 CLAMP 97 NAS1801-3-14 3 SCREW 98 NAS1801-3-8 3 SCREW 99 NAS1801-3-16 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES 68 Epoxy Resin 08-051 As required References Aircraft Maintenance Manual (AMM) 20-27-00, Page Block 201 Elec. Std. Practices Manual (ESPM) 20-33-33 20-33-41 Fig. A-FBCAA Modification of the routing in the shroud box (LH and RH side) Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 NOTE: To apply the following modification, unscrew without removal, all the necessary attachment points. (a) As shown on detail E-E and K-K, remove the old brackets : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 06
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 158 6

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# @A310 SERVICE BULLETIN

1 Remove : 6 Screw Item (56) Discard 4 Screw Item (60) Discard 10 Washer Item (57) Discard 10 Bracket Item (58) Retain 20 Tie Item (53) Discard (b) Install the grommet on routes 1M and 2M. Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 05 section B-B and detail D. 1 If necessary remove and retain the clamp and the spacer installed before the hole. NOTE: Retain the hardware. 2 Install : Refer to AMM 20-27-00, Page Block 201 1 Grommet A9201346420000 Item 55 NOTE: Open the grommet Item 55 with a craft knife. 3 Install the clamp and the spacer if retained at removal. NOTE: Use the hardware retained at removal. (c) Install the protective sleeve between the Rib 01 and Rib 06 on routes 1M, 2M, 1S-3R-1V and 2S : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 05 1 Install : Refer to ESPM 20-33-33 24 (M) Sleeve-Protective EN6049-007-08-5 Item 52 And/Or 24 (M) Sleeve-Protective EN6049-007-13-5 Item 66 And/Or 24 (M) Sleeve-Protective EN6049-007-19-5 Item 67
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 159 6

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# @A310 SERVICE BULLETIN
NOTE: The size of the sleeve should be chosen by the operator in accordance with the bundles size. 2 Attach the Protective Sleeve with : 100 Tie-Cable NSA935401-05 Item 53 (d) As shown on detail F-F and L-L, install the spacers between the structure and the brackets. Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 06 1 Install : 10 Bracket Item (58) Retained at removal 6 Spacer NSA5527-03-01 Item 63 4 Spacer NSA5527-03-03 Item 61 6 Screw NAS1801-3-17 Item 56 4 Screw NAS1801-3-13 Item 60 10 Washer NAS1149D0316H Item 57 20 Tie-Cable NSA935401-05 Item 53 (e) Install the spacers between routes 1M and 2M and between routes 2S and 1S-3R-1V. Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 05 detail A-A. 1 Install : Refer to ESPM 20-33-41 4 Spacer NSA5527-03-02 Item 64 4 Tie-Cable NSA935401-13 Item 62 (f) Modify the routing of the routes 1P and 2P. 1 As shown on detail C-C remove the old clamps: Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 04

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 160 6

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# @A310 SERVICE BULLETIN

a Remove : 3 Screw Item (88) Discard 3 Washer Item (81) Discard 6 Clamp Item (95) Discard 3 Spacer Item (90) Discard 2 As shown on detail G-G remove the old brackets : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02 and Fig. A-FBCAA Sheet 03
a Remove : 1 Screw Item (99) Discard 1 Washer Item (57) Discard 2 Clamp Item (95) Discard 1 Spacer Item (90) Discard 3 As shown on detail D-D and H-H install a protection on the hole of the Rib : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 04
a Install : 2 (M) Strip-Protective NSA939510BN Item 69 With : Item 68 Epoxy Resin 08-051 As required 4 As shown on detail D-D install the new brackets : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03, Fig. A-FBCAA Sheet 04 and Fig. A-FBCAA Sheet 05
a Install : 3 Bracket A0041113620000 Item 91 Or 3 Bracket A0041113720000 Item 93 Attach with :

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 161 6

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# @A310 SERVICE BULLETIN
3 Screw NAS1801-3-8 Item 98 3 Washer NAS1149D0316H Item 57 NOTE: Case 01 : If bracket PN A924-40102 is installed, install item 91. Case 02 : If bracket PN NSA5456-03 is installed, install item 93. The new bracket have to be in contact with the Rib. b On the new bracket Item 91 or 93, install : 6 Clamp NSA5516-10ND Item 96 3 Washer NAS1149D0316H Item 57 3 Screw NAS1801-3-14 Item 97 5 As shown on detail H-H install the new brackets : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 05
a Install : 1 Spacer NSA5527-03-02 Item 64 2 Clamp NSA5516-10ND Item 96 1 Washer NAS1149D0316H Item 57 1 Screw NAS1801-3-16 Item 99

(7) Subtask 242105-831-006-001 - Modify the routing on the RH shroud box leading edge. Work Zones and Access Panels Zone Access/Work location 673 Work location from Rib 01 to Rib 06 Manpower Resources Manhours 6.00 Minimum number of person 1 Subtask elapsed time 6.00 Skills NON SPECIFIC

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 162 6

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# @A310 SERVICE BULLETIN
Material necessary to do the job Kit 242105A01R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 52 EN6049-007-08-5 24 (M) SLEEVE 53 NSA935401-05 120 TIE 55 A9201346420000 1 GROMMET 56 NAS1801-3-17 6 SCREW 57 NAS1149D0316H 17 WASHER 60 NAS1801-3-13 4 SCREW 61 NSA5527-03-03 4 SPACER 62 NSA935401-13 4 TIE 63 NSA5527-03-01 6 SPACER 64 NSA5527-03-02 5 SPACER 66 EN6049-007-13-5 24 (M) SLEEVE 67 EN6049-007-19-5 24 (M) SLEEVE 69 NSA939510BN 2 (M) STRIP 92 A0041113620100 3 BRACKET 94 A0041113720100 3 BRACKET 96 NSA5516-10ND 8 CLAMP 97 NAS1801-3-14 3 SCREW 98 NAS1801-3-8 3 SCREW 99 NAS1801-3-16 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES 68 Epoxy Resin 08-051 As required References Aircraft Maintenance Manual (AMM) 20-27-00, Page Block 201 Elec. Std. Practices Manual (ESPM) 20-33-33 20-33-41 Fig. A-FBCAA Modification of the routing in the shroud box (LH and RH side) Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 NOTE: Workstep for removal of hydraulic pipes should be performed before this workstep. NOTE: To apply the following modification, unscrew without removal, all the necessary attachment points.

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 163 6

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# @A310 SERVICE BULLETIN (a) As shown on detail E-E and K-K, remove the old brackets : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 06 1 Remove : 6 Screw Item (56) Discard 4 Screw Item (60) Discard 10 Washer Item (57) Discard 10 Bracket Item (58) Retain 20 Tie Item (53) Discard (b) Install the grommet on routes 1M and 2M. Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 05 section B-B and D. 1 If necessary remove and retain the clamp and the spacer installed before the hole. NOTE: Retain the hardware. 2 Install : Refer to AMM 20-27-00, Page Block 201 1 Grommet A9201346420000 Item 55 NOTE: Open the grommet Item 55 with a craft knife. 3 Install the clamp and the spacer if retained at removal. NOTE: Use the hardware retained at removal. (c) Install the protective sleeve between the Rib 01 and Rib 06 on routes 1M, 2M, 1S-3R-1V and 2S : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 05 1 Install : Refer to ESPM 20-33-33 24 (M) Sleeve-Protective EN6049-007-08-5 Item 52 And/Or

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 164 6

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# @A310 SERVICE BULLETIN 24 (M) Sleeve-Protective EN6049-007-13-5 Item 66 And/Or 24 (M) Sleeve-Protective EN6049-007-19-5 Item 67 NOTE: The size of the sleeve should be choosen by the operator in accordance with the bundles size. 2 Attach the Protective Sleeve with : 100 Tie-Cable NSA935401-05 Item 53 (d) As shown on detail F-F and L-L, install the spacers between the structure and the brackets. Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 06 1 Install : 10 Bracket Item (58) Retained at removal 6 Spacer NSA5527-03-01 Item 63 4 Spacer NSA5527-03-03 Item 61 6 Screw NAS1801-3-17 Item 56 4 Screw NAS1801-3-13 Item 60 10 Washer NAS1149D0316H Item 57 20 Tie-Cable NSA935401-05 Item 53 (e) Install the spacers between routes 1M and 2M and between routes 1S and 2S-3R-2V. Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 05 detail A-A. 1 Install : Refer to ESPM 20-33-41 4 Spacer NSA5527-03-02 Item 64 4 Tie-Cable NSA935401-13 Item 62

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 165 6

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# @A310 SERVICE BULLETIN (f) Modify the routing of the routes 1P and 2P. 1 As shown on detail C-C remove the old clamps: Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 04
a Remove : 3 Screw Item (88) Discard 3 Washer Item (81) Discard 6 Clamp Item (95) Discard 3 Spacer Item (90) Discard 2 As shown on detail G-G remove the old brackets : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02 and Fig. A-FBCAA Sheet 03
a Remove : 1 Screw Item (99) Discard 1 Washer Item (57) Discard 2 Clamp Item (95) Discard 1 Spacer Item (90) Discard 3 As shown on detail D-D and H-H install a protection on the hole of the Rib : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 04
a Install : 2 (M) Strip-Protective NSA939510BN Item 69 With : Item 68 Epoxy Resin 08-051 As required 4 As shown on detail D-D install the new brackets : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03, Fig. A-FBCAA Sheet 04 and Fig. A-FBCAA Sheet 05
a Install : 3 Bracket A0041113620100 Item 92 DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 166 6

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# @A310 SERVICE BULLETIN
Or 3 Bracket A0041113720100 Item 94 Attach with : 3 Screw NAS1801-3-8 Item 98 3 Washer NAS1149D0316H Item 57 NOTE: Case 01 : If bracket PN A924-40102 is installed, install item 92. Case 02 : If bracket PN NSA5456-03 is installed, install item 94. The new bracket have to be in contact with the Rib. b On the new bracket Item 92 or 94, install : 6 Clamp NSA5516-10ND Item 96 3 Washer NAS1149D0316H Item 57 3 Screw NAS1801-3-14 Item 97 5 As shown on detail H-H install the new brackets : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 05
a Install : 1 Spacer NSA5527-03-02 Item 64 2 Clamp NSA5516-10ND Item 96 1 Washer NAS1149D0316H Item 57 1 Screw NAS1801-3-16 Item 99

(8) Subtask 242105-831-401-001 - Install new nutplate on the RH wing Leading edge Work Zones and Access Panels Zone Access/Work location 620 Access Panel 624KB Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 167 6

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# @A310 SERVICE BULLETIN
Material necessary to do the job Kit 242105B01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 106 NSA5456-3-8 1 NUTPLATE 111 ANSA2050DCJ3210 2 RIVET Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Multi Purpose Thixotropic Paste 09-016J As required
References Structural Repair Manual (SRM) 51-77-10 Fig. A-UBAAA Installation of the new clip and nutplate Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Install new nutplate on the RH wing leading edge in the location of Rib 28a, refer to Fig. A-UBAAA Sheet 01 , Fig. A-UBAAA Sheet 03 and Fig. A-UBAAA Sheet 04

. 1 On the center line of existing anchor nut as indicated, make sure the nutplate, Item 106 is in the correct position. 2 Use: 1 Nutplate NSA5456-3-8 Item 106 3 Mark out and drill two 3.2 mm (0.125 in.) holes in the structure. 4 Wet assemble, Items 106 to the structure with: Multi Purpose Thixotropic Paste 09-016J As required

use: 2 Rivet ANSA2050DCJ3210 Item 111

(9) Subtask 242105-831-211-002 - Modify the electrical routing installation at the LH front spar in the area of RIB 2. Work Zones and Access Panels Zone Access/Work location 512 Work location Rib 2

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 168 6

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# @A310 SERVICE BULLETIN
Manpower Resources Manhours 1.5 Minimum number of person 1 Subtask elapsed time 1.5 Skills NON SPECIFIC Material necessary to do the job Kit 242105D02R08 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 18 MS21919WCH12 2 CLAMP 19 MS21919WCH4 2 CLAMP 43 NSA935401-03 16 TIE 100 B9239030000200 4 PLACARD References Elec. Std. Practices Manual (ESPM) 20-33-33 Fig. A-GDAAB Modification of the electrical routing installation at the LH front spar in the area of RIB 2 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Modify the electrical routing installation at the LH front spar in the area of RIB 2. 1 Remove these items: Refer to Fig. A-GDAAB Sheet 03, Section A-A. 2 Clamp Item (54) Discard 2 Clamp Item (57) Discard 2 Clamp Item (78) Retain with 1 Washer Item (70) Retain 1 Screw Item (72) Retain 1 Spacer Item (73) Retain 1 Spacer Item (79) Retain or Remove these items: Refer to Fig. A-GDAAB Sheet 03, Section B-B. DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 169 6

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# @A310 SERVICE BULLETIN 2 Clamp Item (54) Discard 2 Clamp Item (57) Discard with 1 Washer Item (70) Retain 1 Spacer Item (73) Retain 1 Screw Item (77) Retain NOTE: The different installations are depending on the installation in the aircraft. 2 Install the electrical wires with the protection sleeves: NOTE: The protection sleeves are previously installed with subtask 242105-831-003-001. Refer to Fig. A-GDAAB Sheet 04, Section C-C. 2 Clamp MS21919WCH12 Item 18 2 Clamp MS21919WCH4 Item 19 2 Clamp Item (78) Retained at removal with 1 Washer Item (70) Retained at removal 1 Screw Item (72) Retained at removal 1 Spacer Item (73) Retained at removal 1 Spacer Item (79) Retained at removal or Install the electrical wires with the protection sleeves: NOTE: The protection sleeves are previously installed with subtask 242105-831-003-001. Refer to Fig. A-GDAAB Sheet 04, Section D-D.

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 170 6

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# @A310 SERVICE BULLETIN 2 Clamp MS21919WCH12 Item 18 2 Clamp MS21919WCH4 Item 19 2 Clamp Item (78) Retained at removal with 1 Washer Item (70) Retained at removal 1 Spacer Item (73) Retained at removal 1 Screw Item (77) Retain 3 Before installation, cut the protection sleeve to its required length and install with: Refer to ESPM 20-33-33. Refer to Fig. A-GDAAB Sheet 02, View C. 16 Tie NSA935401-03 Item 43 4 Install the Service Bulletin placards: Refer to Fig. A-GDAAB Sheet 04, View D. 4 Placard B9239030000200 Item 100 in a good visible position. (10) Subtask 242105-831-212-002 - Modify the electrical routing installation at the RH front spar in the area of RIB 2. Work Zones and Access Panels Zone Access/Work location 612 Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills NON SPECIFIC

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 171 6

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# @A310 SERVICE BULLETIN
Material necessary to do the job Kit 242105D02R08 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 19 MS21919WCH4 1 CLAMP 29 MS21919WCH11 2 CLAMP 30 MS21919WCH5 1 CLAMP 43 NSA935401-03 8 TIE 100 B9239030000200 4 PLACARD References Elec. Std. Practices Manual (ESPM) 20-33-33 Fig. A-GDBAB Modification of the electrical routing installation at the RH front spar in the area of RIB 2 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Modify the electrical routing installation at the RH front spar in the area of RIB 2. 1 Remove these items: Refer to Fig. A-GDBAB Sheet 03, Section A-A. 1 Clamp Item (54) Discard 2 Clamp Item (58) Discard 1 Clamp Item (61) Discard 2 Clamp Item (78) Retain with 1 Washer Item (70) Retain 1 Screw Item (72) Retain 1 Spacer Item (73) Retain 1 Spacer Item (79) Retain or Remove these items: Refer to Fig. A-GDBAB Sheet 03, Section B-B. 1 Clamp Item (54) Discard

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 172 6

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# @A310 SERVICE BULLETIN 2 Clamp Item (58) Discard 1 Clamp Item (61) Discard with 1 Washer Item (70) Retain 1 Spacer Item (73) Retain 1 Screw Item (77) Retain NOTE: The different installations are depending on the installation in the aircraft. 2 Install the electrical wires with the protection sleeves: NOTE: The protection sleeves are previously installed with subtask 242105-831-004-001. Refer to Fig. A-GDBAB Sheet 04, Section C-C. 1 Clamp MS21919WCH4 Item 19 2 Clamp MS21919WCH11 Item 29 1 Clamp MS21919WCH5 Item 30 2 Clamp Item (78) Retained at removal with 1 Washer Item (70) Retained at removal 1 Screw Item (72) Retained at removal 1 Spacer Item (73) Retained at removal 1 Spacer Item (79) Retained at removal or Install the electrical wires with the protection sleeves: NOTE: The protection sleeves are previously installed with subtask 242105-831-004-001.

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 173 6

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# @A310 SERVICE BULLETIN
Refer to Fig. A-GDBAB Sheet 04, Section D-D. 1 Clamp MS21919WCH4 Item 19 2 Clamp MS21919WCH11 Item 29 1 Clamp MS21919WCH5 Item 30 with 1 Washer Item (70) Retained at removal 1 Spacer Item (73) Retained at removal 1 Screw Item (77) Retain 3 Before installation, cut the protection sleeve to its required length and install with: Refer to ESPM 20-33-33. Refer to Fig. A-GDBAB Sheet 02, View C. 8 Tie NSA935401-03 Item 43 4 Install the Service Bulletin placards: Refer to Fig. A-GDBAB Sheet 04, View D. 4 Placard B9239030000200 Item 100 in a good visible position. (11) Subtask 242105-831-213-002 - Modify the electrical routing installation at the LH front spar in the area of RIB 3. Work Zones and Access Panels Zone Access/Work location 512 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON SPECIFIC

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 174 6

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# @A310 SERVICE BULLETIN
Material necessary to do the job Kit 242105D02R08 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 18 MS21919WCH12 2 CLAMP 19 MS21919WCH4 2 CLAMP 20 EN6049-007-05-5 1 (ME) SLEEVE 21 EN6049-007-19-5 1 (ME) SLEEVE 100 B9239030000200 2 PLACARD References Elec. Std. Practices Manual (ESPM) 20-33-33 Fig. A-GDCAA Modification of the electrical routing installation at the LH front spar in the area of RIB 3 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Modify the electrical routing installation at the LH front spar in the area of RIB 3. 1 Remove these items: Refer to Fig. A-GDCAA Sheet 03, Section A-A. 2 Clamp Item (54) Discard 2 Clamp Item (57) Discard 4 Clamp Item (78) Retain and 2 Washer Item (70) Retain 2 Screw Item (72) Retain 4 Spacer Item (73) Retain 2 Spacer Item (79) Retain or Remove these items: Refer to Fig. A-GDCAA Sheet 03, Section B-B. 2 Clamp Item (54) Discard 2 Clamp Item (57) Discard

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 175 6

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# @A310 SERVICE BULLETIN
and 2 Washer Item (70) Retain 2 Spacer Item (73) Retain 2 Screw Item (77) Retain NOTE: The different installations are depending on the installation in the aircraft. 2 Install the electrical wires with protection sleeves: Refer to Fig. A-GDCAA Sheet 04, Section C-C. 1 (ME) Sleeve EN6049-007-05-5 Item 20 1 (ME) Sleeve EN6049-007-19-5 Item 21 with 2 Clamp MS21919WCH12 Item 18 2 Clamp MS21919WCH4 Item 19 4 Clamp Item (78) Retained at removal and 2 Washer Item (70) Retained at removal 2 Screw Item (72) Retained at removal 4 Spacer Item (73) Retained at removal 2 Spacer Item (79) Retained at removal NOTE: Before installation, cut the sleeves, Items 20 and 21, to its required length, refer to Fig. A-GDCAA Sheet 02, View C, refer to ESPM 20-33-33.
or Install the electrical wires with protection sleeves: Refer to Fig. A-GDCAA Sheet 04, Section D-D.

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 176 6

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# @A310 SERVICE BULLETIN 1 (ME) Sleeve EN6049-007-05-5 Item 20 1 (ME) Sleeve EN6049-007-19-5 Item 21 with 2 Clamp MS21919WCH12 Item 18 2 Clamp MS21919WCH4 Item 19 and 2 Washer Item (70) Retained at removal 2 Spacer Item (73) Retained at removal 2 Screw Item (77) Retained at removal NOTE: Before installation, cut the sleeves, Items 20 and 21, to its required length, refer to Fig. A-GDCAA Sheet 02, View C, refer to ESPM 20-33-33. 3 Install the Service Bulletin placards: Refer to Fig. A-GDCAA Sheet 04, View D. 2 Placard B9239030000200 Item 100 in a good visible position. (12) Subtask 242105-831-214-002 - Modify the electrical routing installation at the RH front spar in the area of RIB 3. Work Zones and Access Panels Zone Access/Work location 612 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON SPECIFIC

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 177 6

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# @A310 SERVICE BULLETIN
Material necessary to do the job Kit 242105D02R08 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 19 MS21919WCH4 1 CLAMP 20 EN6049-007-05-5 1 (ME) SLEEVE 21 EN6049-007-19-5 1 (ME) SLEEVE 29 MS21919WCH11 2 CLAMP 100 B9239030000200 2 PLACARD References Elec. Std. Practices Manual (ESPM) 20-33-33 Fig. A-GDDAA Modification of the electrical routing installation at the RH front spar in the area of RIB 3 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Modify the electrical routing installation at the RH front spar in the area of RIB 3. 1 Remove these items: Refer to Fig. A-GDDAA Sheet 03, Section A-A. 1 Clamp Item (54) Discard 1 Clamp Item (58) Discard 2 Clamp Item (78) Retain and 1 Washer Item (70) Retain 1 Screw Item (72) Retain 2 Spacer Item (73) Retain 1 Spacer Item (79) Retain or Remove these items: Refer to Fig. A-GDDAA Sheet 03, Section B-B. 1 Clamp Item (54) Discard 1 Clamp Item (58) Discard

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 178 6

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# @A310 SERVICE BULLETIN
and 1 Washer Item (70) Retain 1 Spacer Item (73) Retain 1 Screw Item (77) Retain NOTE: The different installations are depending on the installation in the aircraft. 2 Install the electrical wires with protection sleeves: Refer to Fig. A-GDDAA Sheet 04, Section C-C. 1 (ME) Sleeve EN6049-007-05-5 Item 20 1 (ME) Sleeve EN6049-007-19-5 Item 21 with 1 Clamp MS21919WCH4 Item 19 1 Clamp MS21919WCH11 Item 29 2 Clamp Item (78) Retained at removal and 1 Washer Item (70) Retained at removal 1 Screw Item (72) Retained at removal 2 Spacer Item (73) Retained at removal 1 Spacer Item (79) Retained at removal NOTE: Before installation, cut the sleeves, Items 20 and 21, to its required length, refer to Fig. A-GDDAA Sheet 02, View C, refer to ESPM 20-33-33.
or Install the electrical wires with protection sleeves: Refer to Fig. A-GDDAA Sheet 04, Section D-D.

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 179 6

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# @A310 SERVICE BULLETIN 1 (ME) Sleeve EN6049-007-05-5 Item 20 1 (ME) Sleeve EN6049-007-19-5 Item 21 with 1 Clamp MS21919WCH4 Item 19 1 Clamp MS21919WCH11 Item 29 and 1 Washer Item (70) Retained at removal 1 Spacer Item (73) Retained at removal 1 Screw Item (77) Retained at removal 3 Install the Service Bulletin placards: Refer to Fig. A-GDDAA Sheet 04, View D. 2 Placard B9239030000200 Item 100 in a good visible position. (13) Subtask 242105-831-215-002 - Modify the electrical routing installation at the LH and RH front spars in the area of RIB 5 and RIB 6. Work Zones and Access Panels Zone Access/Work location 512 612 Manpower Resources Manhours 2.50 Minimum number of person 2 Subtask elapsed time 1.25 Skills NON SPECIFIC Material necessary to do the job Kit 242105D02R08 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 MS21919WCH10 2 CLAMP 3 NAS1149D0332K 2 WASHER 4 NSA5527-03-03D 2 SPACER DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 180 6

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# @A310 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 19 MS21919WCH4 2 CLAMP 23 NAS1801-3-16 4 SCREW 24 MS21042-3 2 NUT 31 NAS1801-3-13 2 SCREW 32 NSA5527-03-07D 4 SPACER 42 A9249252400400 2 RAMP References Fig. A-GEAAA Modification of the electrical routing installation at the LH/RH front spars in the area of RIB 5 and RIB 6 Sheet 01 Sheet 02 Sheet 03 (a) Modify the electrical routing installation at the LH and RH front spar in the area of RIB 5 and RIB 6. 1 Remove these items: Refer to Fig. A-GEAAA Sheet 02, Section A-A. 4 Clamp Item (10) Retain 4 Clamp Item (19) Retain and 4 Washer Item (3) Retain 4 Spacer Item (4) Retain 4 Screw Item (5) Discard 2 Install the electrical wires with: Refer to Fig. A-GEAAA Sheet 03, Section B-B. 2 Ramp A9249252400400 Item 42 and 4 Washer Item (3) Retained at removal 4 Spacer Item (4) Retained at removal 4 Clamp Item (10) Retained at removal

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 181 6

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# @A310 SERVICE BULLETIN 4 Clamp Item (19) Retained at removal 4 Screw NAS1801-3-16 Item 23 4 Spacer NSA5527-03-07D Item 32 3 Install the electrical wires at the ramp, Item 42, with: Refer to Fig. A-GEAAA Sheet 03, Section C-C. 2 Clamp MS21919WCH10 Item 2 2 Clamp MS21919WCH4 Item 19 and 2 Spacer NSA5527-03-03D Item 4 2 Washer NAS1149D0332K Item 3 2 Nut MS21042-3 Item 24 2 Screw NAS1801-3-13 Item 31

(14) Subtask 242105-831-216-001 - Modify the electrical routing installation at the LH and RH front spars in the area of RIB 7 and RIB 8. Work Zones and Access Panels Zone Access/Work location 512 612 Manpower Resources Manhours 1.00 Minimum number of person 2 Subtask elapsed time 0.50 Skills NON SPECIFIC Material necessary to do the job Kit 242105D02R08 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 3 NAS1149D0332K 2 WASHER 6 NAS1801-3-10 2 SCREW 7 NSA5527-03-05D 2 SPACER 10 MS21919WCH2 2 CLAMP 100 B9239030000200 1 PLACARD

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 182 6

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# @A310 SERVICE BULLETIN

References Fig. A-GFAAA Modification of the electrical routing installation at the LH/RH front spars in the area of RIB 7 and RIB 8 Sheet 01 Sheet 02
(a) Install additional clamps at the LH and RH front spars in the area of RIB 8. NOTE: Make sure that the work step "Install adhesive clipping brackets", subtask 242105-831-402-001 is done before you start with this work step. 1 Install these items: Refer to Fig. A-GFAAA Sheet 02, View C. 2 Clamp MS21919WCH2 Item 10 with 2 Washer NAS1149D0332K Item 3 2 Screw NAS1801-3-10 Item 6 2 Spacer NSA5527-03-05D Item 7 2 Install the Service Bulletin placards: Refer to Fig. A-GFAAA Sheet 02, View D. 1 Placard B9239030000200 Item 100 in a good visible position. (15) Subtask 242105-831-218-001 - Modify the electrical routing installation at the LH front spar in the area of RIB 20 and RIB 21. Work Zones and Access Panels Zone Access/Work location 524 Manpower Resources Manhours 3.25 Minimum number of person 1 Subtask elapsed time 3.25 Skills NON SPECIFIC

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 183 6

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# @A310 SERVICE BULLETIN
Material necessary to do the job Kit 242105D02R08 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 3 NAS1149D0332K 2 WASHER 8 NSA5527-03-01D 2 SPACER 9 MS21919WCH3 6 CLAMP 10 MS21919WCH2 2 CLAMP 11 NAS1801-3-18 2 SCREW 24 MS21042-3 2 NUT 25 NAS1096-3-24 2 SCREW 26 NAS1096-3-22 2 SCREW 32 NSA5527-03-07D 4 SPACER 40 A9249252400000 1 RAMP 41 A9249252400200 1 RAMP 100 B9239030000200 2 PLACARD References Fig. A-GGAAA Modification of the electrical routing installation at the LH front spar in the area of RIB 20 and RIB 21 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Modify the electrical routing installation at the LH front spar in the area of RIB 20 and RIB 21. 1 Remove these items: Refer to Fig. A-GGAAA Sheet 02, Section A-A. 12 Clamp Item (9) Retain 4 Clamp Item (10) Retain and 4 Washer Item (3) Retain 4 Spacer Item (8) Retain 4 Spacer Item (22) Retain 4 Screw Item (59) Discard 2 Install the ramp close to RIB 20: Refer to Fig. A-GGAAA Sheet 03, View C and Section B-B. 1 Ramp A9249252400000 Item 40
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 184 6

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# @A310 SERVICE BULLETIN
with 6 Clamp Item (9) Retained at removal 2 Clamp Item (10) Retained at removal and 2 Washer Item (3) Retained at removal 2 Spacer Item (8) Retained at removal 2 Spacer Item (22) Retained at removal 2 Screw NAS1096-3-22 Item 26 2 Spacer NSA5527-03-07D Item 32 3 Install the electrical wires at the ramp, Item 40, close to RIB 20: Refer to Fig. A-GGAAA Sheet 03, View C and Section C-C. 3 Clamp MS21919WCH3 Item 9 1 Clamp MS21919WCH2 Item 10 and 1 Washer NAS1149D0332K Item 3 1 Spacer NSA5527-03-01D Item 8 1 Screw NAS1801-3-18 Item 11 1 Nut MS21042-3 Item 24 4 Install the ramp close to RIB 21: Refer to Fig. A-GGAAA Sheet 03, View C, and Fig. A-GGAAA Sheet 04, Section D-D. 1 Ramp A9249252400200 Item 41 with 6 Clamp Item (9) Retained at removal

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 185 6

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# @A310 SERVICE BULLETIN 2 Clamp Item (10) Retained at removal and 2 Washer Item (3) Retained at removal 2 Spacer Item (8) Retained at removal 2 Spacer Item (22) Retained at removal 2 Screw NAS1096-3-24 Item 25 2 Spacer NSA5527-03-07D Item 32 5 Install the electrical wires at the ramp, Item 41, close to RIB 21: Refer to Fig. A-GGAAA Sheet 03, View C, and Fig. A-GGAAA Sheet 04, Section E-E. 3 Clamp MS21919WCH3 Item 9 1 Clamp MS21919WCH2 Item 10 and 1 Washer NAS1149D0332K Item 3 1 Spacer NSA5527-03-01D Item 8 1 Screw NAS1801-3-18 Item 11 1 Nut MS21042-3 Item 24 6 Install the Service Bulletin placard: Refer to Fig. A-GGAAA Sheet 04, View D. 2 Placard B9239030000200 Item 100 in a good visible position. (16) Subtask 242105-831-219-001 - Modify the electrical routing installation at the RH front spar in the area of RIB 20 and RIB 21. Work Zones and Access Panels Zone Access/Work location 624

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 186 6

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# @A310 SERVICE BULLETIN
Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills NON SPECIFIC Material necessary to do the job Kit 242105D02R08 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 3 NAS1149D0332K 2 WASHER 8 NSA5527-03-01D 2 SPACER 9 MS21919WCH3 6 CLAMP 10 MS21919WCH2 2 CLAMP 11 NAS1801-3-18 2 SCREW 24 MS21042-3 2 NUT 25 NAS1096-3-24 2 SCREW 26 NAS1096-3-22 2 SCREW 32 NSA5527-03-07D 2 SPACER 40 A9249252400000 1 RAMP 41 A9249252400200 1 RAMP 100 B9239030000200 2 PLACARD References Fig. A-GHAAA Modification of the electrical routing installation at the RH front spar in the area of RIB 20 and RIB 21 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Modify the electrical routing installation at the RH front spar in the area of RIB 20 and RIB 21. 1 Remove these items: Refer to Fig. A-GHAAA Sheet 02, Section A-A. 12 Clamp Item (9) Retain 4 Clamp Item (10) Retain and 4 Washer Item (3) Retain 4 Spacer Item (8) Retain 4 Screw Item (60) Discard

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 187 6

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# @A310 SERVICE BULLETIN

2 Install the electrical wires close to RIB 20: Refer to Fig. A-GHAAA Sheet 03, View C and Fig. A-GHAAA Sheet 04 Section D-D. 1 Ramp A9249252400200 Item 41 with 6 Clamp Item (9) Retained at removal 2 Clamp Item (10) Retained at removal and 2 Washer Item (3) Retained at removal 2 Spacer Item (8) Retained at removal 2 Screw NAS1096-3-22 Item 26 2 Spacer NSA5527-03-07D Item 32 3 Install the electrical wires at the ramp, Item 41, close to RIB 20: Refer to Fig. A-GHAAA Sheet 03, View C and Fig. A-GHAAA Sheet 04 Section E-E. 3 Clamp MS21919WCH3 Item 9 1 Clamp MS21919WCH2 Item 10 and 1 Washer NAS1149D0332K Item 3 1 Spacer NSA5527-03-01D Item 8 1 Screw NAS1801-3-18 Item 11 1 Nut MS21042-3 Item 24 4 Install the electrical wires close to RIB 21: Refer to Fig. A-GHAAA Sheet 03, View C, and Section B-B. 1 Ramp A9249252400000 Item 40 with
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 188 6

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# @A310 SERVICE BULLETIN 6 Clamp Item (9) Retained at removal 2 Clamp Item (10) Retained at removal and 2 Washer Item (3) Retained at removal 2 Spacer Item (8) Retained at removal 2 Screw NAS1096-3-24 Item 25 2 Spacer NSA5527-03-07D Item 32 5 Install the electrical wires at the ramp, Item 40, close to RIB 21: Refer to Fig. A-GHAAA Sheet 03, View C, and Section C-C. 3 Clamp MS21919WCH3 Item 9 1 Clamp MS21919WCH2 Item 10 and 1 Washer NAS1149D0332K Item 3 1 Spacer NSA5527-03-01D Item 8 1 Screw NAS1801-3-18 Item 11 1 Nut MS21042-3 Item 24 6 Install the Service Bulletin placard: Refer to Fig. A-GHAAA Sheet 04, View D. 2 Placard B9239030000200 Item 100 in a good visible position. (17) Subtask 242105-831-220-002 - Modify the electrical routing installation at the RH front spar in the area of RIB 28 and RIB 28A. Work Zones and Access Panels Zone Access/Work location 624

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 189 6

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# @A310 SERVICE BULLETIN
Manpower Resources Manhours 1.50 Minimum number of person 1 Subtask elapsed time 1.50 Skills NON SPECIFIC Material necessary to do the job Kit 242105D02R08 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 3 NAS1149D0332K 1 WASHER 9 MS21919WCH3 3 CLAMP 27 NSA5527-03-15D 2 SPACER 28 NAS1801-3-30 1 SCREW 100 B9239030000200 2 PLACARD References Fig. A-GJAAA Modification of the electrical routing installation at the RH front spar in the area of RIB 28 and RIB 28A Sheet 01 Sheet 02 Sheet 03 (a) Modify electrical routing installation at the RH front spar in the area of RIB 28 and 28A. 1 Remove these items: Refer to Fig. A-GJAAA Sheet 02, View C. 3 Clamp Item (9) Discard and 1 Washer Item (3) Discard 3 Spacer Item (8) Discard 1 Screw Item (56) Discard 2 Install these items: NOTE: Make sure that the subtask 242105-831-401-001, "Install new nutplate on the RH wing leading edge", is done before you start with this work step. Refer to Fig. A-GJAAA Sheet 03, View E. 3 Clamp MS21919WCH3 Item 9 with DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 190 6

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# @A310 SERVICE BULLETIN
1 Washer NAS1149D0332K Item 3 2 Spacer NSA5527-03-15D Item 27 1 Screw NAS1801-3-30 Item 28 3 Install the Service Bulletin placard: Refer to Fig. A-GJAAA Sheet 03, View F. 2 Placard B9239030000200 Item 100 in a good visible position. **CONF 004 (1) Subtask 242105-831-402-001 - Install Adhesive Clipping Bracket on the LH and RH Wing Leading Edge in the Area of Rib 7 Work Zones and Access Panels Zone Access/Work location 520 Access Panel 512HB 620 Access Panel 612HB Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Kit 242105B01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 102 ABS1546B3C12 2 BRACKET Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Two Part Paste Adhesive 08-078 As required Solvent General Purpose 11-026 As required Lint-Free Cotton Cloth 19-003 As required References Structural Repair Manual (SRM) 51-77-10

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 191 6

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# @A310 SERVICE BULLETIN

References Fig. A-UBAAA Installation of the new clip and nutplate Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Install on the LH and RH wing leading edge in the area of Rib 7 the item that follows, refer to Fig. A-UBAAA Sheet 01 and Fig. A-UBAAA Sheet 02: 2 Bracket ABS1546B3C12 Item 102 1 Measure and mark out the location of the new bracket, Item 102. 2 Clean the areas to be bonded, both structure and bracket, Item 102 with a: Lint-Free Cotton Cloth 19-003 As required
made moist with: Solvent General Purpose 11-026 As required
3 Use Scotchbrite to lightly abrade the surface then clean with the general solvent. 4 Mix together: Two Part Paste Adhesive 08-078 As required
in accordance with SRM 51-77-10 5 Put a small amount of adhesive to the center of the base of the bracket, Item 102. The quantity applied must be sufficient to enable slight flow of excess adhesive around the complete periphery of the base. 6 Remove the adhesive paper from the adaptor bearing points and discard it. 7 Position the adaptor on the structure within the area previously marked. Press on the ends of the adaptor so the foam pads adhere to the structure. 8 Press on the center section of the adaptor without exerting pressure on the bracket, Item 102. The over-centering and the adaptor cause the adhesive to flow and keep the bracket, Item 102 in place during curing. 9 Once the adhesive has cured in accordance with SRM 51-77-10, remove the adaptor and discard.

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 192 6

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# @A310 SERVICE BULLETIN (2) Subtask 242105-831-001-001 - Attach the routes 1E and 1G with the lacing tape in the LH shroud box leading edge. Work Zones and Access Panels Zone Access/Work location 137 Work location from Frame 39 to Frame 40 from Stringer 28 to Stringer 30 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON SPECIFIC Material necessary to do the job Kit 242105A01R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 51 NSA8420-5 1 (M) CORD 53 NSA935401-05 1 TIE 62 NSA935401-13 2 TIE 63 NSA5527-03-01 1 SPACER 65 A9222505750000 1 SPACER References Elec. Std. Practices Manual (ESPM) 20-33-44 Fig. A-FBAAA Modification of the routing between FR39 and FR40 at STGR28 to STGR30 (LH side) Sheet 01 Sheet 02
(a) Install the Bobbin Spacer in accordance with detail A-A (If not already installed on aircraft): Refer to Fig. A-FBAAA Sheet 02

. 1 Install : 1 Spacer-Feeder A9222505750000 Item 65 With : 1 Tie-Cable NSA935401-13 Item 62 2 Attach the routes 1E and 1G with (If not already installed on aircraft) : 1 Spacer NSA5527-03-01 Item 63 1 Tie-Cable NSA935401-05 Item 53
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 193 6

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# @A310 SERVICE BULLETIN
Or 1 Tie-Cable NSA935401-13 Item 62 (b) Install the lacing tape to attach the routes 1E and 1G together (To keep the necessary distance between the two routes) in accordance with detail B-B : Refer to Fig. A-FBAAA Sheet 02 Refer to ESPM 20-33-44 NOTE: Cut the lacing tape to the necessary length. 1 (M) Cord-Fiber Glass NSA8420-5 Item 51

(3) Subtask 242105-831-002-001 - Attach the routes 2E and 2G with the lacing tape in the RH shroud box leading edge. Work Zones and Access Panels Zone Access/Work location 138 Work location from Frame 39 to Frame 40 from Stringer 28 to Stringer 30 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON SPECIFIC Material necessary to do the job Kit 242105A01R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 51 NSA8420-5 1 (M) CORD 53 NSA935401-05 1 TIE 62 NSA935401-13 2 TIE 63 NSA5527-03-01 1 SPACER 65 A9222505750000 1 SPACER References Elec. Std. Practices Manual (ESPM) 20-33-44 Fig. A-FBEAA Modification of the routing between FR39 and FR40 at STGR28 to STGR30 (RH side) Sheet 01 Sheet 02

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 194 6

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# @A310 SERVICE BULLETIN (a) Install the Bobbin Spacer in accordance with detail A-A (If not already installed on aircraft): Refer to Fig. A-FBEAA Sheet 02

. 1 Install : 1 Spacer-Feeder A9222505750000 Item 65 With : 1 Tie-Cable NSA935401-13 Item 62 2 Attach the routes 2E and 2G with (If not already installed on aircraft) : 1 Spacer NSA5527-03-01 Item 63 1 Tie-Cable NSA935401-05 Item 53 Or 1 Tie-Cable NSA935401-13 Item 62 (b) Install the lacing tape to attach the routes 1E and 1G together (To keep the necessary distance between the two routes) in accordance with detail B-B : Refer to Fig. A-FBEAA Sheet 02 Refer to ESPM 20-33-44 NOTE: Cut the lacing tape to the necessary length. 1 (M) Cord-Fiber Glass NSA8420-5 Item 51

(4) Subtask 242105-831-003-001 - Modify the routing in the LH forward wing to fuselage fairing. Work Zones and Access Panels Zone Access/Work location 512 Access Panel 513RR, Panel 513QL Work location from Rib 01 to Rib 04 Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills NON SPECIFIC

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 195 6

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# @A310 SERVICE BULLETIN
Material necessary to do the job Kit 242105A01R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 52 EN6049-007-08-5 4 (M) SLEEVE 53 NSA935401-05 51 TIE 62 NSA935401-13 1 TIE 63 NSA5527-03-01 1 SPACER 66 EN6049-007-13-5 4 (M) SLEEVE 67 EN6049-007-19-5 4 (M) SLEEVE 85 NSA5516-08ND 16 CLAMP 86 NSA5516-18ND 16 CLAMP References Elec. Std. Practices Manual (ESPM) 20-25-51 20-33-33 20-33-41 20-33-44 Fig. A-FBBAA Modification of the routing in the forward wing to fuselage fairing (LH and RH side) Sheet 01 Sheet 02 Sheet 03
NOTE: To ensure the necessary access as described in Preparation SUBTASK 242105-010-003 001 Remove the Air Ducts and the Deflector in the LH Wings for access. . NOTE: Unscrew without removal, all the necessary attachment points. (a) Refer to Fig. A-FBBAA Sheet 02

. In the Raceway Box and as shown on detail B-B, remove: 3 Screw Item (88) Retain 3 Washer Item (89) Retain 6 Clamp Item (87) Retain 6 Spacer Item (90) Retain 12 Clamp Item (84) Discard On detail C-C, remove: 1 Screw Item (88) Retain 1 Washer Item (89) Retain
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 196 6

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# @A310 SERVICE BULLETIN 1 Spacer Item (90) Retain 4 Clamp Item (84) Discard (b) Install the protective sleeve between the Rib 01 and Rib 05 and through the Raceway Box : Refer to Fig. A-FBBAA Sheet 01, Fig. A-FBBAA Sheet 02 and Fig. A-FBBAA Sheet 03 1 Install : Refer to ESPM 20-33-33 4 (M) Sleeve-Protective EN6049-007-08-5 Item 52 NOTE: The size of the sleeve should be chosen in accordance with the bundles size on A/C And/Or 4 (M) Sleeve-Protective EN6049-007-13-5 Item 66 And/Or 4 (M) Sleeve-Protective EN6049-007-19-5 Item 67 2 Attach the Protective Sleeve with : 50 Tie-Cable NSA935401-05 Item 53 (c) In the Raceway Box and as shown on detail B-B, install : Refer to Fig. A-FBBAA Sheet 02 12 Clamp NSA5516-08ND Item 85 Or 12 Clamp NSA5516-18ND Item 86 And 6 Spacer Item (90) Retained at removal And 6 Clamp Item (87) Retained at removal 3 Washer Item (89) Retained at removal

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 197 6

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# @A310 SERVICE BULLETIN 3 Screw Item (88) Retained at removal NOTE: Torque all the attachment points unscrewed at removal. (d) On detail C-C, install: Refer to Fig. A-FBBAA Sheet 02

. 4 Clamp NSA5516-08ND Item 85 Or 4 Clamp NSA5516-18ND Item 86 And 1 Spacer Item (90) Retained at removal And 1 Washer Item (89) Retained at removal 1 Screw Item (88) Retained at removal NOTE: Torque all the attachment points unscrewed at removal. (e) Install the spacer Item 63 on the route 1E and 1G : Refer to Fig. A-FBBAA Sheet 01 and Fig. A-FBBAA Sheet 02 section A-A. Refer to ESPM 20-33-41 1 Install : 1 Spacer NSA5527-03-01 Item 63 attach with : 1 Tie-Cable NSA935401-05 Item 53 or 1 Tie-Cable NSA935401-13 Item 62

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 198 6

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# @A310 SERVICE BULLETIN (5) Subtask 242105-831-004-001 - Modify the routing in the RH forward wing to fuselage fairing. Work Zones and Access Panels Zone Access/Work location 612 Access Panel 613RR, Panel 613QL Work location from Rib 01 to Rib 04 Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills NON SPECIFIC Material necessary to do the job Kit 242105A01R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 52 EN6049-007-08-5 4 (M) SLEEVE 53 NSA935401-05 51 TIE 62 NSA935401-13 1 TIE 63 NSA5527-03-01 1 SPACER 66 EN6049-007-13-5 4 (M) SLEEVE 67 EN6049-007-19-5 4 (M) SLEEVE 85 NSA5516-08ND 16 CLAMP 86 NSA5516-18ND 16 CLAMP References Elec. Std. Practices Manual (ESPM) 20-25-51 20-33-33 20-33-41 20-33-44 Fig. A-FBBAA Modification of the routing in the forward wing to fuselage fairing (LH and RH side) Sheet 01 Sheet 02 Sheet 03
NOTE: To ensure the necessary access as described in Preparation SUBTASK 242105-010-003 001 Remove the Air Ducts and the Deflector in the LH Wings for access. . NOTE: To apply the following modification, unscrew without removal, all the necessary attachment points. (a) Refer to Fig. A-FBBAA Sheet 02

. In the Raceway Box and as shown on detail B-B, remove :

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 199 6

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# @A310 SERVICE BULLETIN 3 Screw Item (88) Retain 3 Washer Item (89) Retain 6 Clamp Item (87) Retain 6 Spacer Item (90) Retain 12 Clamp Item (84) Discard On detail C-C, remove: 1 Screw Item (88) Retain 1 Washer Item (89) Retain 1 Spacer Item (90) Retain 4 Clamp Item (84) Discard (b) Install the protective sleeve between the Rib 01 and Rib 05 and through the Raceway Box : Refer to Fig. A-FBBAA Sheet 01, Fig. A-FBBAA Sheet 02 and Fig. A-FBBAA Sheet 03 1 Install : Refer to ESPM 20-33-33 4 (M) Sleeve-Protective EN6049-007-08-5 Item 52 NOTE: The size of the sleeve should be chosen in accordance with the bundles size on A/C And/Or 4 (M) Sleeve-Protective EN6049-007-13-5 Item 66 And/Or 4 (M) Sleeve-Protective EN6049-007-19-5 Item 67 2 Attach the Protective Sleeve with : 50 Tie-Cable NSA935401-05 Item 53 (c) In the Raceway Box and as shown on detail B-B, install : Refer to Fig. A-FBBAA Sheet 02 12 Clamp NSA5516-08ND Item 85
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 200 6

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# @A310 SERVICE BULLETIN
Or 12 Clamp NSA5516-18ND Item 86 And 6 Spacer Item (90) Retained at removal And 6 Clamp Item (87) Retained at removal 3 Washer Item (89) Retained at removal 3 Screw Item (88) Retained at removal NOTE: Torque all the attachment points unscrewed at removal. (d) On detail C-C, install: Refer to Fig. A-FBBAA Sheet 02

. 4 Clamp NSA5516-08ND Item 85 Or 4 Clamp NSA5516-18ND Item 86 And 1 Spacer Item (90) Retained at removal And 1 Washer Item (89) Retained at removal 1 Screw Item (88) Retained at removal NOTE: Torque all the attachment points unscrewed at removal. (e) Install the spacer Item 63 on the route 2E and 2G : Refer to Fig. A-FBBAA Sheet 01 and Fig. A-FBBAA Sheet 02 section A-A. Refer to ESPM 20-33-41

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 201 6

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# @A310 SERVICE BULLETIN

1 Install : 1 Spacer NSA5527-03-01 Item 63 attach with : 1 Tie-Cable NSA935401-05 Item 53 or 1 Tie-Cable NSA935401-13 Item 62

(6) Subtask 242105-831-005-001 - Modify the routing on the LH shroud box leading edge. Work Zones and Access Panels Zone Access/Work location 573 Work location from Rib 01 to Rib 06 Manpower Resources Manhours 6.00 Minimum number of person 1 Subtask elapsed time 6.00 Skills NON SPECIFIC Material necessary to do the job Kit 242105A01R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 52 EN6049-007-08-5 24 (M) SLEEVE 53 NSA935401-05 120 TIE 55 A9201346420000 1 GROMMET 56 NAS1801-3-17 6 SCREW 57 NAS1149D0316H 17 WASHER 60 NAS1801-3-13 4 SCREW 61 NSA5527-03-03 4 SPACER 62 NSA935401-13 4 TIE 63 NSA5527-03-01 6 SPACER 64 NSA5527-03-02 5 SPACER 66 EN6049-007-13-5 24 (M) SLEEVE 67 EN6049-007-19-5 24 (M) SLEEVE 69 NSA939510BN 2 (M) STRIP 91 A0041113620000 3 BRACKET 93 A0041113720000 3 BRACKET 96 NSA5516-10ND 8 CLAMP 97 NAS1801-3-14 3 SCREW 98 NAS1801-3-8 3 SCREW 99 NAS1801-3-16 1 SCREW
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 202 6

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# @A310 SERVICE BULLETIN
Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES 68 Epoxy Resin 08-051 As required References Aircraft Maintenance Manual (AMM) 20-27-00, Page Block 201 Elec. Std. Practices Manual (ESPM) 20-33-33 20-33-41 Fig. A-FBCAA Modification of the routing in the shroud box (LH and RH side) Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 NOTE: To apply the following modification, unscrew without removal, all the necessary attachment points. (a) As shown on detail E-E and K-K, remove the old brackets : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 06 1 Remove : 6 Screw Item (56) Discard 4 Screw Item (60) Discard 10 Washer Item (57) Discard 10 Bracket Item (58) Retain 20 Tie Item (53) Discard (b) Install the grommet on routes 1M and 2M. Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 05 section B-B and detail D. 1 If necessary remove and retain the clamp and the spacer installed before the hole. NOTE: Retain the hardware. 2 Install : Refer to AMM 20-27-00, Page Block 201 1 Grommet A9201346420000 Item 55
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 203 6

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# @A310 SERVICE BULLETIN
NOTE: Open the grommet Item 55 with a craft knife. 3 Install the clamp and the spacer if retained at removal. NOTE: Use the hardware retained at removal. (c) Install the protective sleeve between the Rib 01 and Rib 06 on routes 1M, 2M, 1S-3R-1V and 2S : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 05 1 Install : Refer to ESPM 20-33-33 24 (M) Sleeve-Protective EN6049-007-08-5 Item 52 And/Or 24 (M) Sleeve-Protective EN6049-007-13-5 Item 66 And/Or 24 (M) Sleeve-Protective EN6049-007-19-5 Item 67 NOTE: The size of the sleeve should be chosen by the operator in accordance with the bundles size. 2 Attach the Protective Sleeve with : 100 Tie-Cable NSA935401-05 Item 53 (d) As shown on detail F-F and L-L, install the spacers between the structure and the brackets. Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 06 1 Install : 10 Bracket Item (58) Retained at removal 6 Spacer NSA5527-03-01 Item 63 4 Spacer NSA5527-03-03 Item 61 6 Screw NAS1801-3-17 Item 56 4 Screw NAS1801-3-13 Item 60 10 Washer NAS1149D0316H Item 57
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 204 6

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# @A310 SERVICE BULLETIN
20 Tie-Cable NSA935401-05 Item 53 (e) Install the spacers between routes 1M and 2M and between routes 2S and 1S-3R-1V. Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 05 detail A-A. 1 Install : Refer to ESPM 20-33-41 4 Spacer NSA5527-03-02 Item 64 4 Tie-Cable NSA935401-13 Item 62 (f) Modify the routing of the routes 1P and 2P. 1 As shown on detail C-C remove the old clamps: Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 04
a Remove : 3 Screw Item (88) Discard 3 Washer Item (81) Discard 6 Clamp Item (95) Discard 3 Spacer Item (90) Discard 2 As shown on detail G-G remove the old brackets : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02 and Fig. A-FBCAA Sheet 03
a Remove : 1 Screw Item (99) Discard 1 Washer Item (57) Discard 2 Clamp Item (95) Discard 1 Spacer Item (90) Discard 3 As shown on detail D-D and H-H install a protection on the hole of the Rib : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 04
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 205 6

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# @A310 SERVICE BULLETIN

a Install : 2 (M) Strip-Protective NSA939510BN Item 69 With : Item 68 Epoxy Resin 08-051 As required 4 As shown on detail D-D install the new brackets : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03, Fig. A-FBCAA Sheet 04 and Fig. A-FBCAA Sheet 05
a Install : 3 Bracket A0041113620000 Item 91 Or 3 Bracket A0041113720000 Item 93 Attach with : 3 Screw NAS1801-3-8 Item 98 3 Washer NAS1149D0316H Item 57 NOTE: Case 01 : If bracket PN A924-40102 is installed, install item 91. Case 02 : If bracket PN NSA5456-03 is installed, install item 93. The new bracket have to be in contact with the Rib. b On the new bracket Item 91 or 93, install : 6 Clamp NSA5516-10ND Item 96 3 Washer NAS1149D0316H Item 57 3 Screw NAS1801-3-14 Item 97 5 As shown on detail H-H install the new brackets : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 05
a Install : 1 Spacer NSA5527-03-02 Item 64 2 Clamp NSA5516-10ND Item 96

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 206 6

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# @A310 SERVICE BULLETIN
1 Washer NAS1149D0316H Item 57 1 Screw NAS1801-3-16 Item 99

(7) Subtask 242105-831-006-001 - Modify the routing on the RH shroud box leading edge. Work Zones and Access Panels Zone Access/Work location 673 Work location from Rib 01 to Rib 06 Manpower Resources Manhours 6.00 Minimum number of person 1 Subtask elapsed time 6.00 Skills NON SPECIFIC Material necessary to do the job Kit 242105A01R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 52 EN6049-007-08-5 24 (M) SLEEVE 53 NSA935401-05 120 TIE 55 A9201346420000 1 GROMMET 56 NAS1801-3-17 6 SCREW 57 NAS1149D0316H 17 WASHER 60 NAS1801-3-13 4 SCREW 61 NSA5527-03-03 4 SPACER 62 NSA935401-13 4 TIE 63 NSA5527-03-01 6 SPACER 64 NSA5527-03-02 5 SPACER 66 EN6049-007-13-5 24 (M) SLEEVE 67 EN6049-007-19-5 24 (M) SLEEVE 69 NSA939510BN 2 (M) STRIP 92 A0041113620100 3 BRACKET 94 A0041113720100 3 BRACKET 96 NSA5516-10ND 8 CLAMP 97 NAS1801-3-14 3 SCREW 98 NAS1801-3-8 3 SCREW 99 NAS1801-3-16 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES 68 Epoxy Resin 08-051 As required

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 207 6

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# @A310 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 20-27-00, Page Block 201 Elec. Std. Practices Manual (ESPM) 20-33-33 20-33-41 Fig. A-FBCAA Modification of the routing in the shroud box (LH and RH side) Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 NOTE: Workstep for removal of hydraulic pipes should be performed before this workstep. NOTE: To apply the following modification, unscrew without removal, all the necessary attachment points. (a) As shown on detail E-E and K-K, remove the old brackets : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 06 1 Remove : 6 Screw Item (56) Discard 4 Screw Item (60) Discard 10 Washer Item (57) Discard 10 Bracket Item (58) Retain 20 Tie Item (53) Discard (b) Install the grommet on routes 1M and 2M. Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 05 section B-B and D. 1 If necessary remove and retain the clamp and the spacer installed before the hole. NOTE: Retain the hardware. 2 Install : Refer to AMM 20-27-00, Page Block 201 1 Grommet A9201346420000 Item 55 NOTE: Open the grommet Item 55 with a craft knife.

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 208 6

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# @A310 SERVICE BULLETIN
3 Install the clamp and the spacer if retained at removal. NOTE: Use the hardware retained at removal. (c) Install the protective sleeve between the Rib 01 and Rib 06 on routes 1M, 2M, 1S-3R-1V and 2S : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 05 1 Install : Refer to ESPM 20-33-33 24 (M) Sleeve-Protective EN6049-007-08-5 Item 52 And/Or 24 (M) Sleeve-Protective EN6049-007-13-5 Item 66 And/Or 24 (M) Sleeve-Protective EN6049-007-19-5 Item 67 NOTE: The size of the sleeve should be choosen by the operator in accordance with the bundles size. 2 Attach the Protective Sleeve with : 100 Tie-Cable NSA935401-05 Item 53 (d) As shown on detail F-F and L-L, install the spacers between the structure and the brackets. Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 06 1 Install : 10 Bracket Item (58) Retained at removal 6 Spacer NSA5527-03-01 Item 63 4 Spacer NSA5527-03-03 Item 61 6 Screw NAS1801-3-17 Item 56 4 Screw NAS1801-3-13 Item 60 10 Washer NAS1149D0316H Item 57 20 Tie-Cable NSA935401-05 Item 53
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 209 6

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# @A310 SERVICE BULLETIN (e) Install the spacers between routes 1M and 2M and between routes 1S and 2S-3R-2V. Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 05 detail A-A. 1 Install : Refer to ESPM 20-33-41 4 Spacer NSA5527-03-02 Item 64 4 Tie-Cable NSA935401-13 Item 62 (f) Modify the routing of the routes 1P and 2P. 1 As shown on detail C-C remove the old clamps: Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 04
a Remove : 3 Screw Item (88) Discard 3 Washer Item (81) Discard 6 Clamp Item (95) Discard 3 Spacer Item (90) Discard 2 As shown on detail G-G remove the old brackets : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02 and Fig. A-FBCAA Sheet 03
a Remove : 1 Screw Item (99) Discard 1 Washer Item (57) Discard 2 Clamp Item (95) Discard 1 Spacer Item (90) Discard 3 As shown on detail D-D and H-H install a protection on the hole of the Rib : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 04

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 210 6

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# @A310 SERVICE BULLETIN

a Install : 2 (M) Strip-Protective NSA939510BN Item 69 With : Item 68 Epoxy Resin 08-051 As required 4 As shown on detail D-D install the new brackets : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03, Fig. A-FBCAA Sheet 04 and Fig. A-FBCAA Sheet 05
a Install : 3 Bracket A0041113620100 Item 92 Or 3 Bracket A0041113720100 Item 94 Attach with : 3 Screw NAS1801-3-8 Item 98 3 Washer NAS1149D0316H Item 57 NOTE: Case 01 : If bracket PN A924-40102 is installed, install item 92. Case 02 : If bracket PN NSA5456-03 is installed, install item 94. The new bracket have to be in contact with the Rib. b On the new bracket Item 92 or 94, install : 6 Clamp NSA5516-10ND Item 96 3 Washer NAS1149D0316H Item 57 3 Screw NAS1801-3-14 Item 97 5 As shown on detail H-H install the new brackets : Refer to Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 02, Fig. A-FBCAA Sheet 03 and Fig. A-FBCAA Sheet 05
a Install : 1 Spacer NSA5527-03-02 Item 64 2 Clamp NSA5516-10ND Item 96

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 211 6

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# @A310 SERVICE BULLETIN
1 Washer NAS1149D0316H Item 57 1 Screw NAS1801-3-16 Item 99

(8) Subtask 242105-831-401-001 - Install new nutplate on the RH wing Leading edge Work Zones and Access Panels Zone Access/Work location 620 Access Panel 624KB Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Kit 242105B01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 106 NSA5456-3-8 1 NUTPLATE 111 ANSA2050DCJ3210 2 RIVET Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Multi Purpose Thixotropic Paste 09-016J As required
References Structural Repair Manual (SRM) 51-77-10 Fig. A-UBAAA Installation of the new clip and nutplate Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Install new nutplate on the RH wing leading edge in the location of Rib 28a, refer to Fig. A-UBAAA Sheet 01 , Fig. A-UBAAA Sheet 03 and Fig. A-UBAAA Sheet 04

. 1 On the center line of existing anchor nut as indicated, make sure the nutplate, Item 106 is in the correct position. 2 Use: 1 Nutplate NSA5456-3-8 Item 106 3 Mark out and drill two 3.2 mm (0.125 in.) holes in the structure.

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 212 6

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# @A310 SERVICE BULLETIN

4 Wet assemble, Items 106 to the structure with: Multi Purpose Thixotropic Paste 09-016J As required

use: 2 Rivet ANSA2050DCJ3210 Item 111

(9) Subtask 242105-831-211-002 - Modify the electrical routing installation at the LH front spar in the area of RIB 2. Work Zones and Access Panels Zone Access/Work location 512 Work location Rib 2 Manpower Resources Manhours 1.5 Minimum number of person 1 Subtask elapsed time 1.5 Skills NON SPECIFIC Material necessary to do the job Kit 242105D02R08 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 18 MS21919WCH12 2 CLAMP 19 MS21919WCH4 2 CLAMP 43 NSA935401-03 16 TIE 100 B9239030000200 4 PLACARD References Elec. Std. Practices Manual (ESPM) 20-33-33 Fig. A-GDAAB Modification of the electrical routing installation at the LH front spar in the area of RIB 2 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Modify the electrical routing installation at the LH front spar in the area of RIB 2. 1 Remove these items: Refer to Fig. A-GDAAB Sheet 03, Section A-A. 2 Clamp Item (54) Discard 2 Clamp Item (57) Discard 2 Clamp Item (78) Retain
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 213 6

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# @A310 SERVICE BULLETIN
with 1 Washer Item (70) Retain 1 Screw Item (72) Retain 1 Spacer Item (73) Retain 1 Spacer Item (79) Retain or Remove these items: Refer to Fig. A-GDAAB Sheet 03, Section B-B. 2 Clamp Item (54) Discard 2 Clamp Item (57) Discard with 1 Washer Item (70) Retain 1 Spacer Item (73) Retain 1 Screw Item (77) Retain NOTE: The different installations are depending on the installation in the aircraft. 2 Install the electrical wires with the protection sleeves: NOTE: The protection sleeves are previously installed with subtask 242105-831-003-001. Refer to Fig. A-GDAAB Sheet 04, Section C-C. 2 Clamp MS21919WCH12 Item 18 2 Clamp MS21919WCH4 Item 19 2 Clamp Item (78) Retained at removal with 1 Washer Item (70) Retained at removal 1 Screw Item (72) Retained at removal DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 214 6

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# @A310 SERVICE BULLETIN 1 Spacer Item (73) Retained at removal 1 Spacer Item (79) Retained at removal or Install the electrical wires with the protection sleeves: NOTE: The protection sleeves are previously installed with subtask 242105-831-003-001. Refer to Fig. A-GDAAB Sheet 04, Section D-D. 2 Clamp MS21919WCH12 Item 18 2 Clamp MS21919WCH4 Item 19 2 Clamp Item (78) Retained at removal with 1 Washer Item (70) Retained at removal 1 Spacer Item (73) Retained at removal 1 Screw Item (77) Retain 3 Before installation, cut the protection sleeve to its required length and install with: Refer to ESPM 20-33-33. Refer to Fig. A-GDAAB Sheet 02, View C. 16 Tie NSA935401-03 Item 43 4 Install the Service Bulletin placards: Refer to Fig. A-GDAAB Sheet 04, View D. 4 Placard B9239030000200 Item 100 in a good visible position.

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 215 6

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# @A310 SERVICE BULLETIN (10) Subtask 242105-831-212-002 - Modify the electrical routing installation at the RH front spar in the area of RIB 2. Work Zones and Access Panels Zone Access/Work location 612 Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills NON SPECIFIC Material necessary to do the job Kit 242105D02R08 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 19 MS21919WCH4 1 CLAMP 29 MS21919WCH11 2 CLAMP 30 MS21919WCH5 1 CLAMP 43 NSA935401-03 8 TIE 100 B9239030000200 4 PLACARD References Elec. Std. Practices Manual (ESPM) 20-33-33 Fig. A-GDBAB Modification of the electrical routing installation at the RH front spar in the area of RIB 2 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Modify the electrical routing installation at the RH front spar in the area of RIB 2. 1 Remove these items: Refer to Fig. A-GDBAB Sheet 03, Section A-A. 1 Clamp Item (54) Discard 2 Clamp Item (58) Discard 1 Clamp Item (61) Discard 2 Clamp Item (78) Retain with 1 Washer Item (70) Retain 1 Screw Item (72) Retain DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 216 6

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# @A310 SERVICE BULLETIN 1 Spacer Item (73) Retain 1 Spacer Item (79) Retain or Remove these items: Refer to Fig. A-GDBAB Sheet 03, Section B-B. 1 Clamp Item (54) Discard 2 Clamp Item (58) Discard 1 Clamp Item (61) Discard with 1 Washer Item (70) Retain 1 Spacer Item (73) Retain 1 Screw Item (77) Retain NOTE: The different installations are depending on the installation in the aircraft. 2 Install the electrical wires with the protection sleeves: NOTE: The protection sleeves are previously installed with subtask 242105-831-004-001. Refer to Fig. A-GDBAB Sheet 04, Section C-C. 1 Clamp MS21919WCH4 Item 19 2 Clamp MS21919WCH11 Item 29 1 Clamp MS21919WCH5 Item 30 2 Clamp Item (78) Retained at removal with 1 Washer Item (70) Retained at removal 1 Screw Item (72) Retained at removal

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 217 6

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# @A310 SERVICE BULLETIN 1 Spacer Item (73) Retained at removal 1 Spacer Item (79) Retained at removal or Install the electrical wires with the protection sleeves: NOTE: The protection sleeves are previously installed with subtask 242105-831-004-001. Refer to Fig. A-GDBAB Sheet 04, Section D-D. 1 Clamp MS21919WCH4 Item 19 2 Clamp MS21919WCH11 Item 29 1 Clamp MS21919WCH5 Item 30 with 1 Washer Item (70) Retained at removal 1 Spacer Item (73) Retained at removal 1 Screw Item (77) Retain 3 Before installation, cut the protection sleeve to its required length and install with: Refer to ESPM 20-33-33. Refer to Fig. A-GDBAB Sheet 02, View C. 8 Tie NSA935401-03 Item 43 4 Install the Service Bulletin placards: Refer to Fig. A-GDBAB Sheet 04, View D. 4 Placard B9239030000200 Item 100 in a good visible position.

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 218 6

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# @A310 SERVICE BULLETIN (11) Subtask 242105-831-213-002 - Modify the electrical routing installation at the LH front spar in the area of RIB 3. Work Zones and Access Panels Zone Access/Work location 512 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON SPECIFIC Material necessary to do the job Kit 242105D02R08 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 18 MS21919WCH12 2 CLAMP 19 MS21919WCH4 2 CLAMP 20 EN6049-007-05-5 1 (ME) SLEEVE 21 EN6049-007-19-5 1 (ME) SLEEVE 100 B9239030000200 2 PLACARD References Elec. Std. Practices Manual (ESPM) 20-33-33 Fig. A-GDCAA Modification of the electrical routing installation at the LH front spar in the area of RIB 3 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Modify the electrical routing installation at the LH front spar in the area of RIB 3. 1 Remove these items: Refer to Fig. A-GDCAA Sheet 03, Section A-A. 2 Clamp Item (54) Discard 2 Clamp Item (57) Discard 4 Clamp Item (78) Retain and 2 Washer Item (70) Retain 2 Screw Item (72) Retain

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 219 6

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# @A310 SERVICE BULLETIN 4 Spacer Item (73) Retain 2 Spacer Item (79) Retain or Remove these items: Refer to Fig. A-GDCAA Sheet 03, Section B-B. 2 Clamp Item (54) Discard 2 Clamp Item (57) Discard and 2 Washer Item (70) Retain 2 Spacer Item (73) Retain 2 Screw Item (77) Retain NOTE: The different installations are depending on the installation in the aircraft. 2 Install the electrical wires with protection sleeves: Refer to Fig. A-GDCAA Sheet 04, Section C-C. 1 (ME) Sleeve EN6049-007-05-5 Item 20 1 (ME) Sleeve EN6049-007-19-5 Item 21 with 2 Clamp MS21919WCH12 Item 18 2 Clamp MS21919WCH4 Item 19 4 Clamp Item (78) Retained at removal and 2 Washer Item (70) Retained at removal 2 Screw Item (72) Retained at removal 4 Spacer Item (73) Retained at removal DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 220 6

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# @A310 SERVICE BULLETIN 2 Spacer Item (79) Retained at removal NOTE: Before installation, cut the sleeves, Items 20 and 21, to its required length, refer to Fig. A-GDCAA Sheet 02, View C, refer to ESPM 20-33-33.
or Install the electrical wires with protection sleeves: Refer to Fig. A-GDCAA Sheet 04, Section D-D. 1 (ME) Sleeve EN6049-007-05-5 Item 20 1 (ME) Sleeve EN6049-007-19-5 Item 21 with 2 Clamp MS21919WCH12 Item 18 2 Clamp MS21919WCH4 Item 19 and 2 Washer Item (70) Retained at removal 2 Spacer Item (73) Retained at removal 2 Screw Item (77) Retained at removal NOTE: Before installation, cut the sleeves, Items 20 and 21, to its required length, refer to Fig. A-GDCAA Sheet 02, View C, refer to ESPM 20-33-33. 3 Install the Service Bulletin placards: Refer to Fig. A-GDCAA Sheet 04, View D. 2 Placard B9239030000200 Item 100 in a good visible position. (12) Subtask 242105-831-214-002 - Modify the electrical routing installation at the RH front spar in the area of RIB 3. Work Zones and Access Panels Zone Access/Work location 612

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 221 6

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# @A310 SERVICE BULLETIN
Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON SPECIFIC Material necessary to do the job Kit 242105D02R08 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 19 MS21919WCH4 1 CLAMP 20 EN6049-007-05-5 1 (ME) SLEEVE 21 EN6049-007-19-5 1 (ME) SLEEVE 29 MS21919WCH11 2 CLAMP 100 B9239030000200 2 PLACARD References Elec. Std. Practices Manual (ESPM) 20-33-33 Fig. A-GDDAA Modification of the electrical routing installation at the RH front spar in the area of RIB 3 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Modify the electrical routing installation at the RH front spar in the area of RIB 3. 1 Remove these items: Refer to Fig. A-GDDAA Sheet 03, Section A-A. 1 Clamp Item (54) Discard 1 Clamp Item (58) Discard 2 Clamp Item (78) Retain and 1 Washer Item (70) Retain 1 Screw Item (72) Retain 2 Spacer Item (73) Retain 1 Spacer Item (79) Retain or Remove these items:
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 222 6

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# @A310 SERVICE BULLETIN
Refer to Fig. A-GDDAA Sheet 03, Section B-B. 1 Clamp Item (54) Discard 1 Clamp Item (58) Discard and 1 Washer Item (70) Retain 1 Spacer Item (73) Retain 1 Screw Item (77) Retain NOTE: The different installations are depending on the installation in the aircraft. 2 Install the electrical wires with protection sleeves: Refer to Fig. A-GDDAA Sheet 04, Section C-C. 1 (ME) Sleeve EN6049-007-05-5 Item 20 1 (ME) Sleeve EN6049-007-19-5 Item 21 with 1 Clamp MS21919WCH4 Item 19 1 Clamp MS21919WCH11 Item 29 2 Clamp Item (78) Retained at removal and 1 Washer Item (70) Retained at removal 1 Screw Item (72) Retained at removal 2 Spacer Item (73) Retained at removal 1 Spacer Item (79) Retained at removal NOTE: Before installation, cut the sleeves, Items 20 and 21, to its required length, refer to Fig. A-GDDAA Sheet 02, View C, refer to ESPM 20-33-33.

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 223 6

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# @A310 SERVICE BULLETIN

or Install the electrical wires with protection sleeves: Refer to Fig. A-GDDAA Sheet 04, Section D-D. 1 (ME) Sleeve EN6049-007-05-5 Item 20 1 (ME) Sleeve EN6049-007-19-5 Item 21 with 1 Clamp MS21919WCH4 Item 19 1 Clamp MS21919WCH11 Item 29 and 1 Washer Item (70) Retained at removal 1 Spacer Item (73) Retained at removal 1 Screw Item (77) Retained at removal 3 Install the Service Bulletin placards: Refer to Fig. A-GDDAA Sheet 04, View D. 2 Placard B9239030000200 Item 100 in a good visible position. (13) Subtask 242105-831-215-002 - Modify the electrical routing installation at the LH and RH front spars in the area of RIB 5 and RIB 6. Work Zones and Access Panels Zone Access/Work location 512 612 Manpower Resources Manhours 2.50 Minimum number of person 2 Subtask elapsed time 1.25 Skills NON SPECIFIC

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 224 6

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# @A310 SERVICE BULLETIN
Material necessary to do the job Kit 242105D02R08 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 MS21919WCH10 2 CLAMP 3 NAS1149D0332K 2 WASHER 4 NSA5527-03-03D 2 SPACER 19 MS21919WCH4 2 CLAMP 23 NAS1801-3-16 4 SCREW 24 MS21042-3 2 NUT 31 NAS1801-3-13 2 SCREW 32 NSA5527-03-07D 4 SPACER 42 A9249252400400 2 RAMP References Fig. A-GEAAA Modification of the electrical routing installation at the LH/RH front spars in the area of RIB 5 and RIB 6 Sheet 01 Sheet 02 Sheet 03 (a) Modify the electrical routing installation at the LH and RH front spar in the area of RIB 5 and RIB 6. 1 Remove these items: Refer to Fig. A-GEAAA Sheet 02, Section A-A. 4 Clamp Item (10) Retain 4 Clamp Item (19) Retain and 4 Washer Item (3) Retain 4 Spacer Item (4) Retain 4 Screw Item (5) Discard 2 Install the electrical wires with: Refer to Fig. A-GEAAA Sheet 03, Section B-B. 2 Ramp A9249252400400 Item 42 and 4 Washer Item (3) Retained at removal

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 225 6

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# @A310 SERVICE BULLETIN 4 Spacer Item (4) Retained at removal 4 Clamp Item (10) Retained at removal 4 Clamp Item (19) Retained at removal 4 Screw NAS1801-3-16 Item 23 4 Spacer NSA5527-03-07D Item 32 3 Install the electrical wires at the ramp, Item 42, with: Refer to Fig. A-GEAAA Sheet 03, Section C-C. 2 Clamp MS21919WCH10 Item 2 2 Clamp MS21919WCH4 Item 19 and 2 Spacer NSA5527-03-03D Item 4 2 Washer NAS1149D0332K Item 3 2 Nut MS21042-3 Item 24 2 Screw NAS1801-3-13 Item 31

(14) Subtask 242105-831-216-001 - Modify the electrical routing installation at the LH and RH front spars in the area of RIB 7 and RIB 8. Work Zones and Access Panels Zone Access/Work location 512 612 Manpower Resources Manhours 1.00 Minimum number of person 2 Subtask elapsed time 0.50 Skills NON SPECIFIC

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 226 6

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# @A310 SERVICE BULLETIN
Material necessary to do the job Kit 242105D02R08 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 3 NAS1149D0332K 2 WASHER 6 NAS1801-3-10 2 SCREW 7 NSA5527-03-05D 2 SPACER 10 MS21919WCH2 2 CLAMP 100 B9239030000200 1 PLACARD References Fig. A-GFAAA Modification of the electrical routing installation at the LH/RH front spars in the area of RIB 7 and RIB 8 Sheet 01 Sheet 02
(a) Install additional clamps at the LH and RH front spars in the area of RIB 8. NOTE: Make sure that the work step "Install adhesive clipping brackets", subtask 242105-831-402-001 is done before you start with this work step. 1 Install these items: Refer to Fig. A-GFAAA Sheet 02, View C. 2 Clamp MS21919WCH2 Item 10 with 2 Washer NAS1149D0332K Item 3 2 Screw NAS1801-3-10 Item 6 2 Spacer NSA5527-03-05D Item 7 2 Install the Service Bulletin placards: Refer to Fig. A-GFAAA Sheet 02, View D. 1 Placard B9239030000200 Item 100 in a good visible position. (15) Subtask 242105-831-217-001 - Modify the electrical routing installation at the RH front spar in the area of RIB 8. Work Zones and Access Panels Zone Access/Work location 612

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 227 6

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# @A310 SERVICE BULLETIN
Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON SPECIFIC Material necessary to do the job Kit 242105D04R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 3 NAS1149D0332K 1 WASHER 6 NAS1801-3-10 1 SCREW 9 MS21919WCH3 1 CLAMP 24 MS21042-3 1 NUT 100 B9239030000200 1 PLACARD References Fig. A-GCCAA Modify the Electrical Routing Installation at the RH Front Spar Sheet 01
(a) Install one additional clamp at the RH front spar in the area of RIB 8. 1 Install these items: Refer to Fig. A-GCCAA Sheet 01 , View B. 1 Clamp MS21919WCH3 Item 9 with 1 Washer NAS1149D0332K Item 3 1 Screw NAS1801-3-10 Item 6 1 Nut MS21042-3 Item 24 2 Install the Service Bulletin placard: Refer to Fig. A-GCCAA Sheet 01 , View C. 1 Placard B9239030000200 Item 100 in a good visible position.

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 228 6

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# @A310 SERVICE BULLETIN (16) Subtask 242105-831-218-001 - Modify the electrical routing installation at the LH front spar in the area of RIB 20 and RIB 21. Work Zones and Access Panels Zone Access/Work location 524 Manpower Resources Manhours 3.25 Minimum number of person 1 Subtask elapsed time 3.25 Skills NON SPECIFIC Material necessary to do the job Kit 242105D02R08 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 3 NAS1149D0332K 2 WASHER 8 NSA5527-03-01D 2 SPACER 9 MS21919WCH3 6 CLAMP 10 MS21919WCH2 2 CLAMP 11 NAS1801-3-18 2 SCREW 24 MS21042-3 2 NUT 25 NAS1096-3-24 2 SCREW 26 NAS1096-3-22 2 SCREW 32 NSA5527-03-07D 4 SPACER 40 A9249252400000 1 RAMP 41 A9249252400200 1 RAMP 100 B9239030000200 2 PLACARD References Fig. A-GGAAA Modification of the electrical routing installation at the LH front spar in the area of RIB 20 and RIB 21 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Modify the electrical routing installation at the LH front spar in the area of RIB 20 and RIB 21. 1 Remove these items: Refer to Fig. A-GGAAA Sheet 02, Section A-A. 12 Clamp Item (9) Retain 4 Clamp Item (10) Retain and
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 229 6

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# @A310 SERVICE BULLETIN
4 Washer Item (3) Retain 4 Spacer Item (8) Retain 4 Spacer Item (22) Retain 4 Screw Item (59) Discard 2 Install the ramp close to RIB 20: Refer to Fig. A-GGAAA Sheet 03, View C and Section B-B. 1 Ramp A9249252400000 Item 40 with 6 Clamp Item (9) Retained at removal 2 Clamp Item (10) Retained at removal and 2 Washer Item (3) Retained at removal 2 Spacer Item (8) Retained at removal 2 Spacer Item (22) Retained at removal 2 Screw NAS1096-3-22 Item 26 2 Spacer NSA5527-03-07D Item 32 3 Install the electrical wires at the ramp, Item 40, close to RIB 20: Refer to Fig. A-GGAAA Sheet 03, View C and Section C-C. 3 Clamp MS21919WCH3 Item 9 1 Clamp MS21919WCH2 Item 10 and 1 Washer NAS1149D0332K Item 3 1 Spacer NSA5527-03-01D Item 8 1 Screw NAS1801-3-18 Item 11 DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 230 6

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# @A310 SERVICE BULLETIN
1 Nut MS21042-3 Item 24 4 Install the ramp close to RIB 21: Refer to Fig. A-GGAAA Sheet 03, View C, and Fig. A-GGAAA Sheet 04, Section D-D. 1 Ramp A9249252400200 Item 41 with 6 Clamp Item (9) Retained at removal 2 Clamp Item (10) Retained at removal and 2 Washer Item (3) Retained at removal 2 Spacer Item (8) Retained at removal 2 Spacer Item (22) Retained at removal 2 Screw NAS1096-3-24 Item 25 2 Spacer NSA5527-03-07D Item 32 5 Install the electrical wires at the ramp, Item 41, close to RIB 21: Refer to Fig. A-GGAAA Sheet 03, View C, and Fig. A-GGAAA Sheet 04, Section E-E. 3 Clamp MS21919WCH3 Item 9 1 Clamp MS21919WCH2 Item 10 and 1 Washer NAS1149D0332K Item 3 1 Spacer NSA5527-03-01D Item 8 1 Screw NAS1801-3-18 Item 11 1 Nut MS21042-3 Item 24

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 231 6

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# @A310 SERVICE BULLETIN
6 Install the Service Bulletin placard: Refer to Fig. A-GGAAA Sheet 04, View D. 2 Placard B9239030000200 Item 100 in a good visible position. (17) Subtask 242105-831-219-001 - Modify the electrical routing installation at the RH front spar in the area of RIB 20 and RIB 21. Work Zones and Access Panels Zone Access/Work location 624 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills NON SPECIFIC Material necessary to do the job Kit 242105D02R08 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 3 NAS1149D0332K 2 WASHER 8 NSA5527-03-01D 2 SPACER 9 MS21919WCH3 6 CLAMP 10 MS21919WCH2 2 CLAMP 11 NAS1801-3-18 2 SCREW 24 MS21042-3 2 NUT 25 NAS1096-3-24 2 SCREW 26 NAS1096-3-22 2 SCREW 32 NSA5527-03-07D 2 SPACER 40 A9249252400000 1 RAMP 41 A9249252400200 1 RAMP 100 B9239030000200 2 PLACARD References Fig. A-GHAAA Modification of the electrical routing installation at the RH front spar in the area of RIB 20 and RIB 21 Sheet 01 Sheet 02 Sheet 03 Sheet 04

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 232 6

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# @A310 SERVICE BULLETIN (a) Modify the electrical routing installation at the RH front spar in the area of RIB 20 and RIB 21. 1 Remove these items: Refer to Fig. A-GHAAA Sheet 02, Section A-A. 12 Clamp Item (9) Retain 4 Clamp Item (10) Retain and 4 Washer Item (3) Retain 4 Spacer Item (8) Retain 4 Screw Item (60) Discard 2 Install the electrical wires close to RIB 20: Refer to Fig. A-GHAAA Sheet 03, View C and Fig. A-GHAAA Sheet 04 Section D-D. 1 Ramp A9249252400200 Item 41 with 6 Clamp Item (9) Retained at removal 2 Clamp Item (10) Retained at removal and 2 Washer Item (3) Retained at removal 2 Spacer Item (8) Retained at removal 2 Screw NAS1096-3-22 Item 26 2 Spacer NSA5527-03-07D Item 32 3 Install the electrical wires at the ramp, Item 41, close to RIB 20: Refer to Fig. A-GHAAA Sheet 03, View C and Fig. A-GHAAA Sheet 04 Section E-E. 3 Clamp MS21919WCH3 Item 9

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 233 6

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# @A310 SERVICE BULLETIN 1 Clamp MS21919WCH2 Item 10 and 1 Washer NAS1149D0332K Item 3 1 Spacer NSA5527-03-01D Item 8 1 Screw NAS1801-3-18 Item 11 1 Nut MS21042-3 Item 24 4 Install the electrical wires close to RIB 21: Refer to Fig. A-GHAAA Sheet 03, View C, and Section B-B. 1 Ramp A9249252400000 Item 40 with 6 Clamp Item (9) Retained at removal 2 Clamp Item (10) Retained at removal and 2 Washer Item (3) Retained at removal 2 Spacer Item (8) Retained at removal 2 Screw NAS1096-3-24 Item 25 2 Spacer NSA5527-03-07D Item 32 5 Install the electrical wires at the ramp, Item 40, close to RIB 21: Refer to Fig. A-GHAAA Sheet 03, View C, and Section C-C. 3 Clamp MS21919WCH3 Item 9 1 Clamp MS21919WCH2 Item 10 and 1 Washer NAS1149D0332K Item 3 1 Spacer NSA5527-03-01D Item 8

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 234 6

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# @A310 SERVICE BULLETIN
1 Screw NAS1801-3-18 Item 11 1 Nut MS21042-3 Item 24 6 Install the Service Bulletin placard: Refer to Fig. A-GHAAA Sheet 04, View D. 2 Placard B9239030000200 Item 100 in a good visible position. (18) Subtask 242105-831-220-002 - Modify the electrical routing installation at the RH front spar in the area of RIB 28 and RIB 28A. Work Zones and Access Panels Zone Access/Work location 624 Manpower Resources Manhours 1.50 Minimum number of person 1 Subtask elapsed time 1.50 Skills NON SPECIFIC Material necessary to do the job Kit 242105D02R08 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 3 NAS1149D0332K 1 WASHER 9 MS21919WCH3 3 CLAMP 27 NSA5527-03-15D 2 SPACER 28 NAS1801-3-30 1 SCREW 100 B9239030000200 2 PLACARD References Fig. A-GJAAA Modification of the electrical routing installation at the RH front spar in the area of RIB 28 and RIB 28A Sheet 01 Sheet 02 Sheet 03 (a) Modify electrical routing installation at the RH front spar in the area of RIB 28 and 28A. 1 Remove these items: Refer to Fig. A-GJAAA Sheet 02, View C. 3 Clamp Item (9) Discard

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 235 6

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# @A310 SERVICE BULLETIN
and 1 Washer Item (3) Discard 3 Spacer Item (8) Discard 1 Screw Item (56) Discard 2 Install these items: NOTE: Make sure that the subtask 242105-831-401-001, "Install new nutplate on the RH wing leading edge", is done before you start with this work step. Refer to Fig. A-GJAAA Sheet 03, View E. 3 Clamp MS21919WCH3 Item 9 with 1 Washer NAS1149D0332K Item 3 2 Spacer NSA5527-03-15D Item 27 1 Screw NAS1801-3-30 Item 28 3 Install the Service Bulletin placard: Refer to Fig. A-GJAAA Sheet 03, View F. 2 Placard B9239030000200 Item 100 in a good visible position. (19) Subtask 242105-831-221-001 - Modify the electrical routing installation at the LH rear spar in the area of RIB 9. Work Zones and Access Panels Zone Access/Work location 575 Manpower Resources Manhours 0.75 Minimum number of person 1 Subtask elapsed time 0.75 Skills NON SPECIFIC

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 236 6

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# @A310 SERVICE BULLETIN
Material necessary to do the job Kit 242105D03R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 10 MS21919WCH2 2 CLAMP 15 NAS1801-3-35 1 SCREW 16 NSA5527-03-11D 1 SPACER 100 B9239030000200 1 PLACARD References Fig. A-GBCAA Modify the Electrical Routing Installation at the LH Rear Spar Sheet 01 Sheet 02 (a) Install one additional clamp at the LH rear spar in the area of RIB 9. 1 Remove these items: Refer to Fig. A-GBCAA Sheet 02, Section A-A. 1 Clamp Item (10) Discard with 1 Washer Item (3) Retain 1 Spacer Item (4) Retain 1 Screw Item (15) Discard 2 Install these items: Refer to Fig. A-GBCAA Sheet 02, Section B-B. 2 Clamp MS21919WCH2 Item 10 with 1 Washer Item (3) Retained at removal 1 Spacer Item (4) Retained at removal 1 Screw NAS1801-3-35 Item 15 1 Spacer NSA5527-03-11D Item 16 3 Install the Service Bulletin placard: Refer to Fig. A-GBCAA Sheet 02, View B. DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 237 6

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# @A310 SERVICE BULLETIN

1 Placard B9239030000200 Item 100 in a good visible position. **CONF ALL D. TEST **CONF 001 (1) Subtask 242105-700-001-001 - Tests Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polyvinylacetat Pvac 05-034 As required Aluminium Foil 05-169 As required Stainless Steel Lockwire 05-289 As required References Aircraft Maintenance Manual (AMM) 27-50-00, Page Block 501 27-61-00, Page Block 501 36-11-00, Page Block 601 71-00-00, Page Block 501 (a) Procedure : 1 Do the following leak test after the installation of the bleed air ducts :
a There are two possible procedures to find the location of a pneumatic joint air leak. <1> You can apply the following developer, dry around the pneumatic joint : Polyvinylacetat Pvac 05-034 As required
NOTE: Apply dry developer only on the connections of the removed pneumatic components. Do not apply dry developer on all the pneumatic components. b You can install the following aluminium foil around the pneumatic joint locations. Aluminium Foil 05-169 As required

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 238 6

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# @A310 SERVICE BULLETIN Use the steps that follow to apply aluminium foil to the pneumatic joint locations : <1> Wind the foil wrap around the joint one time. <2> Twist the seam of the foil wrap tight as shown. <3> Make the foil wrap as tight as possible on the tube but do not rip the wrap. <4> Attach the foil wrap with the following stainless steel lockwire at both sides of the pneumatic joint : Stainless Steel Lockwire 05-289 As required

c Pressurize the pneumatic system : <1> Start the related engine (Refer to AMM 71-00-00, Page Block 501) and keep it at idle for 5 minutes. <2> After 5 minutes, shut down the engine (Refer to AMM 71-00-00, Page Block 501). NOTE: You can use the following alternative methods to pressurize the pneumatic system : - Pressurize the pneumatic system via the HP ground connectors (Refer to AMM 36-11-00, Page Block 601), - Pressurize the pneumatic system with the APU (Refer to AMM 36-11-00, Page Block 601. d Make sure that there are no leaks at the junction between the ducts. 2 Do the following leak test after the installation of the hydraulic pipes :
a Perform 3 times the functional test of the speed brakes (Refer to AMM 27-61-00, Page Block 501) to bleed the spoilers/speed brakes (including associated return/supply pipes and valve block). b Make sure that there are no leaks at the junction between the pipes. (b) Close-Up : 1 Remove the safety clips and tags and close the circuit breakers as specified after the Extension and Retraction of Flaps with Aircraft System (Refer to AMM 27-50-00, Page Block 501).

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 239 6

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# @A310 SERVICE BULLETIN
**CONF 002 (1) Subtask 242105-700-001-001 - Tests Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polyvinylacetat Pvac 05-034 As required Aluminium Foil 05-169 As required Stainless Steel Lockwire 05-289 As required References Aircraft Maintenance Manual (AMM) 27-50-00, Page Block 501 27-61-00, Page Block 501 36-11-00, Page Block 601 71-00-00, Page Block 501 (a) Procedure : 1 Do the following leak test after the installation of the bleed air ducts :
a There are two possible procedures to find the location of a pneumatic joint air leak. <1> You can apply the following developer, dry around the pneumatic joint : Polyvinylacetat Pvac 05-034 As required
NOTE: Apply dry developer only on the connections of the removed pneumatic components. Do not apply dry developer on all the pneumatic components. b You can install the following aluminium foil around the pneumatic joint locations. Aluminium Foil 05-169 As required Use the steps that follow to apply aluminium foil to the pneumatic joint locations : <1> Wind the foil wrap around the joint one time. <2> Twist the seam of the foil wrap tight as shown.

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 240 6

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# @A310 SERVICE BULLETIN <3> Make the foil wrap as tight as possible on the tube but do not rip the wrap. <4> Attach the foil wrap with the following stainless steel lockwire at both sides of the pneumatic joint : Stainless Steel Lockwire 05-289 As required

c Pressurize the pneumatic system : <1> Start the related engine (Refer to AMM 71-00-00, Page Block 501) and keep it at idle for 5 minutes. <2> After 5 minutes, shut down the engine (Refer to AMM 71-00-00, Page Block 501). NOTE: You can use the following alternative methods to pressurize the pneumatic system : - Pressurize the pneumatic system via the HP ground connectors (Refer to AMM 36-11-00, Page Block 601), - Pressurize the pneumatic system with the APU (Refer to AMM 36-11-00, Page Block 601. d Make sure that there are no leaks at the junction between the ducts. 2 Do the following leak test after the installation of the hydraulic pipes :
a Perform 3 times the functional test of the speed brakes (Refer to AMM 27-61-00, Page Block 501) to bleed the spoilers/speed brakes (including associated return/supply pipes and valve block). b Make sure that there are no leaks at the junction between the pipes. (b) Close-Up : 1 Remove the safety clips and tags and close the circuit breakers as specified after the Extension and Retraction of Flaps with Aircraft System (Refer to AMM 27-50-00, Page Block 501). **CONF 003 (1) Subtask 242105-700-001-001 - Tests Manpower Resources Skills NON SPECIFIC

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 241 6

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# @A310 SERVICE BULLETIN
Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polyvinylacetat Pvac 05-034 As required Aluminium Foil 05-169 As required Stainless Steel Lockwire 05-289 As required References Aircraft Maintenance Manual (AMM) 27-50-00, Page Block 501 27-61-00, Page Block 501 36-11-00, Page Block 601 71-00-00, Page Block 501 (a) Procedure : 1 Do the following leak test after the installation of the bleed air ducts :
a There are two possible procedures to find the location of a pneumatic joint air leak. <1> You can apply the following developer, dry around the pneumatic joint : Polyvinylacetat Pvac 05-034 As required
NOTE: Apply dry developer only on the connections of the removed pneumatic components. Do not apply dry developer on all the pneumatic components. b You can install the following aluminium foil around the pneumatic joint locations. Aluminium Foil 05-169 As required Use the steps that follow to apply aluminium foil to the pneumatic joint locations : <1> Wind the foil wrap around the joint one time. <2> Twist the seam of the foil wrap tight as shown. <3> Make the foil wrap as tight as possible on the tube but do not rip the wrap. <4> Attach the foil wrap with the following stainless steel lockwire at both sides of the pneumatic joint : Stainless Steel Lockwire 05-289 As required

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 242 6

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# @A310 SERVICE BULLETIN

c Pressurize the pneumatic system : <1> Start the related engine (Refer to AMM 71-00-00, Page Block 501) and keep it at idle for 5 minutes. <2> After 5 minutes, shut down the engine (Refer to AMM 71-00-00, Page Block 501). NOTE: You can use the following alternative methods to pressurize the pneumatic system : - Pressurize the pneumatic system via the HP ground connectors (Refer to AMM 36-11-00, Page Block 601), - Pressurize the pneumatic system with the APU (Refer to AMM 36-11-00, Page Block 601. d Make sure that there are no leaks at the junction between the ducts. 2 Do the following leak test after the installation of the hydraulic pipes :
a Perform 3 times the functional test of the speed brakes (Refer to AMM 27-61-00, Page Block 501) to bleed the spoilers/speed brakes (including associated return/supply pipes and valve block). b Make sure that there are no leaks at the junction between the pipes. (b) Close-Up : 1 Remove the safety clips and tags and close the circuit breakers as specified after the Extension and Retraction of Flaps with Aircraft System (Refer to AMM 27-50-00, Page Block 501). **CONF 004 (1) Subtask 242105-700-001-001 - Tests Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polyvinylacetat Pvac 05-034 As required Aluminium Foil 05-169 As required Stainless Steel Lockwire 05-289 As required

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 243 6

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# @A310 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 27-50-00, Page Block 501 27-61-00, Page Block 501 36-11-00, Page Block 601 71-00-00, Page Block 501 (a) Procedure : 1 Do the following leak test after the installation of the bleed air ducts :
a There are two possible procedures to find the location of a pneumatic joint air leak. <1> You can apply the following developer, dry around the pneumatic joint : Polyvinylacetat Pvac 05-034 As required
NOTE: Apply dry developer only on the connections of the removed pneumatic components. Do not apply dry developer on all the pneumatic components. b You can install the following aluminium foil around the pneumatic joint locations. Aluminium Foil 05-169 As required Use the steps that follow to apply aluminium foil to the pneumatic joint locations : <1> Wind the foil wrap around the joint one time. <2> Twist the seam of the foil wrap tight as shown. <3> Make the foil wrap as tight as possible on the tube but do not rip the wrap. <4> Attach the foil wrap with the following stainless steel lockwire at both sides of the pneumatic joint : Stainless Steel Lockwire 05-289 As required

c Pressurize the pneumatic system : <1> Start the related engine (Refer to AMM 71-00-00, Page Block 501) and keep it at idle for 5 minutes. <2> After 5 minutes, shut down the engine (Refer to AMM 71-00-00, Page Block 501). NOTE: You can use the following alternative methods to pressurize the pneumatic system : DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 244 6

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# @A310 SERVICE BULLETIN - Pressurize the pneumatic system via the HP ground connectors (Refer to AMM 36-11-00, Page Block 601), - Pressurize the pneumatic system with the APU (Refer to AMM 36-11-00, Page Block 601. d Make sure that there are no leaks at the junction between the ducts. 2 Do the following leak test after the installation of the hydraulic pipes :
a Perform 3 times the functional test of the speed brakes (Refer to AMM 27-61-00, Page Block 501) to bleed the spoilers/speed brakes (including associated return/supply pipes and valve block). b Make sure that there are no leaks at the junction between the pipes. (b) Close-Up : 1 Remove the safety clips and tags and close the circuit breakers as specified after the Extension and Retraction of Flaps with Aircraft System (Refer to AMM 27-50-00, Page Block 501). **CONF ALL E. CLOSE-UP **CONF 001 (1) Subtask 242105-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 27-50-00, Page Block 301 29-14-00, Page Block 301 (a) Restore the systems and the aircraft to normal operating condition. (b) Make sure that the work areas are clean and clear of tools and other items of equipment. (c) Do the close-up procedure as specified in the Extension and Retraction of Flaps with Aircraft System (Refer to AMM 27-50-00, Page Block 301). (2) Subtask 242105-410-002-001 - Install the two Hydraulic Pipes in the RH Wings removed for access. Work Zones and Access Panels Zone Access/Work location 673

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 245 6

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# @A310 SERVICE BULLETIN
Manpower Resources Skills NON SPECIFIC Material necessary to do the job Kit 242105A01R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 62 NSA935401-13 1 TIE References Aircraft Maintenance Manual (AMM) 29-00-00, Page Block 401 Fig. A-FCBAA Removal of Hydraulic Pipes for access Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Install the two Hydraulic Pipes : Refer to Fig. A-FCBAA Sheet 01 , Fig. A-FCBAA Sheet 02 and Fig. A-FCBAA Sheet 03 Refer to AMM 29-00-00, Page Block 401 1 Hydraulic Pipes Item (78) Retained at removal 1 Hydraulic Pipes Item (79) Retained at removal (b) Install the hardware : Refer to Fig. A-FCBAA Sheet 01 , Fig. A-FCBAA Sheet 02, Fig. A-FCBAA Sheet 03 and Fig. A-FCBAA Sheet 04 1 Block Isolator Item (83) Retained at removal With : 1 Tie-Cable NSA935401-13 Item 62 And : 2 Block Clamp Item (82) Retained at removal With : 2 Washer Item (81) Retained at removal

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 246 6

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# @A310 SERVICE BULLETIN
2 Bolt Item (80) Retained at removal (3) Subtask 242105-410-003-001 - Install the Air Ducts and the Deflector in the RH Wings removed for access. Work Zones and Access Panels Zone Access/Work location 512 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-57, Page Block 001 36-11-00, Page Block 401 Fig. A-FCAAA Removal of Air Ducts and Reflector in the Wings for access Sheet 01 Sheet 02 Sheet 03 NOTE: Two persons are necessary. (a) Install the cover of the Raceway Box : Refer to Fig. A-FCAAA Sheet 03 1 Cover Item (77) Retained at removal NOTE: Use the hardware retain at removal. (b) Install the access panel 613QL (Refer to AMM 06-41-57, Page Block 001). (c) Install the Deflector : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 1 Shield Assy Item (76) Retained at removal 1 Bracket Item (74) Retained at removal 1 Shield Item (75) Retained at removal NOTE: Use the hardware retain at removal. (d) Install : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 247 6

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# @A310 SERVICE BULLETIN Refer to AMM 36-11-00, Page Block 401 1 Tube Assy Item (73) Retained at removal 1 Insulation Item (71) Retained at removal 1 Tube Assy Item (72) Retained at removal 1 Insulation Item (71) Retained at removal 1 Duct Assy Item (70) Retained at removal NOTE: Use the hardware retain at removal. (4) Subtask 242105-410-004-001 - Install the Air Ducts and the Deflector in the LH Wings removed for access. Work Zones and Access Panels Zone Access/Work location 612 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-57, Page Block 001 36-11-00, Page Block 401 Fig. A-FCAAA Removal of Air Ducts and Reflector in the Wings for access Sheet 01 Sheet 02 Sheet 03 NOTE: Two persons are necessary. (a) Install the cover of the Raceway Box : Refer to Fig. A-FCAAA Sheet 03 1 Cover Item (77) Retained at removal NOTE: Use the hardware retain at removal. (b) Install the access panel 513QL (Refer to AMM 06-41-57, Page Block 001). (c) Install the Deflector : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 248 6

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# @A310 SERVICE BULLETIN 1 Shield Assy Item (76) Retained at removal 1 Bracket Item (74) Retained at removal 1 Shield Item (75) Retained at removal NOTE: Use the hardware retain at removal. (d) Install : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 Refer to AMM 36-11-00, Page Block 401 1 Tube Assy Item (73) Retained at removal 1 Insulation Item (71) Retained at removal 1 Tube Assy Item (72) Retained at removal 1 Insulation Item (71) Retained at removal 1 Duct Assy Item (70) Retained at removal NOTE: Use the hardware retain at removal. (5) Subtask 242105-410-001-001 - Install/Close Items Removed/Opened for access Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-57, Page Block 001 27-50-00, Page Block 301 27-80-00, Page Block 301 29-10-00, Page Block 301 29-14-00, Page Block 301 29-25-00, Page Block 301 32-12-11, Page Block 301 53-15-63, Page Block 401 (a) Pressurize the Yellow Hydraulic System (Refer to AMM 29-10-00, Page Block 301 and AMM 29-14-00, Page Block 301).

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 249 6

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# @A310 SERVICE BULLETIN (b) If necessary, install the removed access panels 513BL, 513DL, 513CL, 513EL, 513FL, 513ML, 613BR, 613DR, 613CR, 613ER, 613FR and 613HR (Refer to AMM 06-41-57, Page Block 001). (c) Install all the removed fairing panels (Refer to AMM 53-15-63, Page Block 401). (d) Install the access panels 572AB, 672AB, 572AZ, 572BZ, 572CZ, 572DZ, 572EZ, 572FZ, 572GZ, 672AZ, 672BZ, 672CZ, 672DZ, 672EZ, 672FZ and 672GZ (Refer to AMM 06-41-57, Page Block 001). (e) Install the access panels 512FB, 612FB, 512BB, 612BB, 612DB, 513RR and 613RR (Refer to AMM 06-41-57, Page Block 001). (f) If necessary, install the removed access panels 571BB, 571CB, 671BB and 671CB (Refer to AMM 06-41-57, Page Block 001). (g) Fully retract the flaps (Refer to AMM 27-50-00, Page Block 301). (h) Close the Main Landing Gear (MLG) door (Refer to AMM 32-12-11, Page Block 301). (i) Remove the access platform(s). (6) Subtask 242105-942-402-001 - Close-up Work Zones and Access Panels Zone Access/Work location 612 Access Panel 612HB 512 Access Panel 512HB 624 Access Panel 624KB Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 201 27-80-00, Page Block 301 29-10-00, Page Block 301 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Replace the access panels 612HB, 512HB and 624KB. (c) Remove the access platforms. (d) Remove the warning notices from the cockpit. (e) Energize the aircraft, refer to AMM 24-00-00, Page Block 201. (f) Energize the hydraulic systems, refer to AMM 29-10-00, Page Block 301. (g) Fully retract the slats, refer to AMM 27-80-00, Page Block 301. DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 250 6

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# @A310 SERVICE BULLETIN (7) Subtask 242105-942-201-002 - CLOSE-UP Work Zones and Access Panels Zone Access/Work location 600 500 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-57, Page Block 001 24-00-00, Page Block 301 (a) On the lower surface of the LH wing, install the removed leading-edge access panels 512BB, 512CB, 512DB, 512GB and 512JB, refer to AMM 06-41-57, Page Block 001. (b) On the lower surface of the LH wing, install the removed leading-edge access panels 524BB, 524CB and 524KB, refer to AMM 06-41-57, Page Block 001. (c) On the lower surface of the RH wing, install the removed leading-edge access panels 612BB, 612CB, 612DB, 612GB and 612JB, refer to AMM 06-41-57, Page Block 001. (d) On the lower surface of the RH wing, install the removed leading-edge access panels 624BB and 624CB, refer to AMM 06-41-57, Page Block 001. (e) Remove the access platforms below the leading-edges of: - the LH wing at Zone 512 - the LH wing at Zone 524 - the RH wing at Zone 612 - the RH wing at Zone 624 (f) Remove the warning notices from the cockpit to tell persons not to operate the flight controls. (g) Remove the safety guard from the flap and slat control lever. (h) Remove the aircraft ground connection, refer to AMM 24-00-00, Page Block 301. **CONF 002 (1) Subtask 242105-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 251 6

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# @A310 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 27-50-00, Page Block 301 29-14-00, Page Block 301 (a) Restore the systems and the aircraft to normal operating condition. (b) Make sure that the work areas are clean and clear of tools and other items of equipment. (c) Do the close-up procedure as specified in the Extension and Retraction of Flaps with Aircraft System (Refer to AMM 27-50-00, Page Block 301). (2) Subtask 242105-410-002-001 - Install the two Hydraulic Pipes in the RH Wings removed for access. Work Zones and Access Panels Zone Access/Work location 673 Manpower Resources Skills NON SPECIFIC Material necessary to do the job Kit 242105A01R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 62 NSA935401-13 1 TIE References Aircraft Maintenance Manual (AMM) 29-00-00, Page Block 401 Fig. A-FCBAA Removal of Hydraulic Pipes for access Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Install the two Hydraulic Pipes : Refer to Fig. A-FCBAA Sheet 01 , Fig. A-FCBAA Sheet 02 and Fig. A-FCBAA Sheet 03 Refer to AMM 29-00-00, Page Block 401 1 Hydraulic Pipes Item (78) Retained at removal 1 Hydraulic Pipes Item (79) Retained at removal

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 252 6

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# @A310 SERVICE BULLETIN (b) Install the hardware : Refer to Fig. A-FCBAA Sheet 01 , Fig. A-FCBAA Sheet 02, Fig. A-FCBAA Sheet 03 and Fig. A-FCBAA Sheet 04 1 Block Isolator Item (83) Retained at removal With : 1 Tie-Cable NSA935401-13 Item 62 And : 2 Block Clamp Item (82) Retained at removal With : 2 Washer Item (81) Retained at removal 2 Bolt Item (80) Retained at removal (3) Subtask 242105-410-003-001 - Install the Air Ducts and the Deflector in the RH Wings removed for access. Work Zones and Access Panels Zone Access/Work location 512 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-57, Page Block 001 36-11-00, Page Block 401 Fig. A-FCAAA Removal of Air Ducts and Reflector in the Wings for access Sheet 01 Sheet 02 Sheet 03 NOTE: Two persons are necessary. (a) Install the cover of the Raceway Box : Refer to Fig. A-FCAAA Sheet 03 1 Cover Item (77) Retained at removal NOTE: Use the hardware retain at removal.

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 253 6

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# @A310 SERVICE BULLETIN (b) Install the access panel 613QL (Refer to AMM 06-41-57, Page Block 001). (c) Install the Deflector : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 1 Shield Assy Item (76) Retained at removal 1 Bracket Item (74) Retained at removal 1 Shield Item (75) Retained at removal NOTE: Use the hardware retain at removal. (d) Install : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 Refer to AMM 36-11-00, Page Block 401 1 Tube Assy Item (73) Retained at removal 1 Insulation Item (71) Retained at removal 1 Tube Assy Item (72) Retained at removal 1 Insulation Item (71) Retained at removal 1 Duct Assy Item (70) Retained at removal NOTE: Use the hardware retain at removal. (4) Subtask 242105-410-004-001 - Install the Air Ducts and the Deflector in the LH Wings removed for access. Work Zones and Access Panels Zone Access/Work location 612 Manpower Resources Skills NON SPECIFIC

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 254 6

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# @A310 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 06-41-57, Page Block 001 36-11-00, Page Block 401 Fig. A-FCAAA Removal of Air Ducts and Reflector in the Wings for access Sheet 01 Sheet 02 Sheet 03 NOTE: Two persons are necessary. (a) Install the cover of the Raceway Box : Refer to Fig. A-FCAAA Sheet 03 1 Cover Item (77) Retained at removal NOTE: Use the hardware retain at removal. (b) Install the access panel 513QL (Refer to AMM 06-41-57, Page Block 001). (c) Install the Deflector : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 1 Shield Assy Item (76) Retained at removal 1 Bracket Item (74) Retained at removal 1 Shield Item (75) Retained at removal NOTE: Use the hardware retain at removal. (d) Install : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 Refer to AMM 36-11-00, Page Block 401 1 Tube Assy Item (73) Retained at removal 1 Insulation Item (71) Retained at removal 1 Tube Assy Item (72) Retained at removal 1 Insulation Item (71) Retained at removal
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 255 6

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# @A310 SERVICE BULLETIN
1 Duct Assy Item (70) Retained at removal NOTE: Use the hardware retain at removal. (5) Subtask 242105-410-001-001 - Install/Close Items Removed/Opened for access Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-57, Page Block 001 27-50-00, Page Block 301 27-80-00, Page Block 301 29-10-00, Page Block 301 29-14-00, Page Block 301 29-25-00, Page Block 301 32-12-11, Page Block 301 53-15-63, Page Block 401 (a) Pressurize the Yellow Hydraulic System (Refer to AMM 29-10-00, Page Block 301 and AMM 29-14-00, Page Block 301). (b) If necessary, install the removed access panels 513BL, 513DL, 513CL, 513EL, 513FL, 513ML, 613BR, 613DR, 613CR, 613ER, 613FR and 613HR (Refer to AMM 06-41-57, Page Block 001). (c) Install all the removed fairing panels (Refer to AMM 53-15-63, Page Block 401). (d) Install the access panels 572AB, 672AB, 572AZ, 572BZ, 572CZ, 572DZ, 572EZ, 572FZ, 572GZ, 672AZ, 672BZ, 672CZ, 672DZ, 672EZ, 672FZ and 672GZ (Refer to AMM 06-41-57, Page Block 001). (e) Install the access panels 512FB, 612FB, 512BB, 612BB, 612DB, 513RR and 613RR (Refer to AMM 06-41-57, Page Block 001). (f) If necessary, install the removed access panels 571BB, 571CB, 671BB and 671CB (Refer to AMM 06-41-57, Page Block 001). (g) Fully retract the flaps (Refer to AMM 27-50-00, Page Block 301). (h) Close the Main Landing Gear (MLG) door (Refer to AMM 32-12-11, Page Block 301). (i) Remove the access platform(s). (6) Subtask 242105-942-402-001 - Close-up Work Zones and Access Panels Zone Access/Work location 612 Access Panel 612HB 512 Access Panel 512HB
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 256 6

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# @A310 SERVICE BULLETIN

624 Access Panel 624KB Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 201 27-80-00, Page Block 301 29-10-00, Page Block 301 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Replace the access panels 612HB, 512HB and 624KB. (c) Remove the access platforms. (d) Remove the warning notices from the cockpit. (e) Energize the aircraft, refer to AMM 24-00-00, Page Block 201. (f) Energize the hydraulic systems, refer to AMM 29-10-00, Page Block 301. (g) Fully retract the slats, refer to AMM 27-80-00, Page Block 301. (7) Subtask 242105-942-201-003 - CLOSE-UP Work Zones and Access Panels Zone Access/Work location 600 500 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-57, Page Block 001 24-00-00, Page Block 301 (a) On the lower surface of the LH wing, install the removed leading-edge access panels 512BB, 512CB, 512DB, 512GB and 512JB, refer to AMM 06-41-57, Page Block 001. (b) On the lower surface of the RH wing, install the removed leading-edge access panels 612BB, 612CB, 612DB, 612GB and 612JB, refer to AMM 06-41-57, Page Block 001. (c) On the lower surface of the RH wing, install the removed leading-edge access panels 624BB and 624CB, refer to AMM 06-41-57, Page Block 001.

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 257 6

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# @A310 SERVICE BULLETIN (d) Remove the access platforms below the leading-edges of: - the LH wing at Zone 512 - the RH wing at Zone 612 - the RH wing at Zone 624 (e) Remove the warning notices from the cockpit to tell persons not to operate the flight controls. (f) Remove the safety guard from the flap and slat control lever. (g) Remove the aircraft ground connection, refer to AMM 24-00-00, Page Block 301. **CONF 003 (1) Subtask 242105-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 27-50-00, Page Block 301 29-14-00, Page Block 301 (a) Restore the systems and the aircraft to normal operating condition. (b) Make sure that the work areas are clean and clear of tools and other items of equipment. (c) Do the close-up procedure as specified in the Extension and Retraction of Flaps with Aircraft System (Refer to AMM 27-50-00, Page Block 301). (2) Subtask 242105-410-002-001 - Install the two Hydraulic Pipes in the RH Wings removed for access. Work Zones and Access Panels Zone Access/Work location 673 Manpower Resources Skills NON SPECIFIC Material necessary to do the job Kit 242105A01R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 62 NSA935401-13 1 TIE

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 258 6

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# @A310 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 29-00-00, Page Block 401 Fig. A-FCBAA Removal of Hydraulic Pipes for access Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Install the two Hydraulic Pipes : Refer to Fig. A-FCBAA Sheet 01 , Fig. A-FCBAA Sheet 02 and Fig. A-FCBAA Sheet 03 Refer to AMM 29-00-00, Page Block 401 1 Hydraulic Pipes Item (78) Retained at removal 1 Hydraulic Pipes Item (79) Retained at removal (b) Install the hardware : Refer to Fig. A-FCBAA Sheet 01 , Fig. A-FCBAA Sheet 02, Fig. A-FCBAA Sheet 03 and Fig. A-FCBAA Sheet 04 1 Block Isolator Item (83) Retained at removal With : 1 Tie-Cable NSA935401-13 Item 62 And : 2 Block Clamp Item (82) Retained at removal With : 2 Washer Item (81) Retained at removal 2 Bolt Item (80) Retained at removal (3) Subtask 242105-410-003-001 - Install the Air Ducts and the Deflector in the RH Wings removed for access. Work Zones and Access Panels Zone Access/Work location 512

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 259 6

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# @A310 SERVICE BULLETIN
Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-57, Page Block 001 36-11-00, Page Block 401 Fig. A-FCAAA Removal of Air Ducts and Reflector in the Wings for access Sheet 01 Sheet 02 Sheet 03 NOTE: Two persons are necessary. (a) Install the cover of the Raceway Box : Refer to Fig. A-FCAAA Sheet 03 1 Cover Item (77) Retained at removal NOTE: Use the hardware retain at removal. (b) Install the access panel 613QL (Refer to AMM 06-41-57, Page Block 001). (c) Install the Deflector : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 1 Shield Assy Item (76) Retained at removal 1 Bracket Item (74) Retained at removal 1 Shield Item (75) Retained at removal NOTE: Use the hardware retain at removal. (d) Install : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 Refer to AMM 36-11-00, Page Block 401 1 Tube Assy Item (73) Retained at removal 1 Insulation Item (71) Retained at removal 1 Tube Assy Item (72) Retained at removal
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 260 6

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# @A310 SERVICE BULLETIN
1 Insulation Item (71) Retained at removal 1 Duct Assy Item (70) Retained at removal NOTE: Use the hardware retain at removal. (4) Subtask 242105-410-004-001 - Install the Air Ducts and the Deflector in the LH Wings removed for access. Work Zones and Access Panels Zone Access/Work location 612 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-57, Page Block 001 36-11-00, Page Block 401 Fig. A-FCAAA Removal of Air Ducts and Reflector in the Wings for access Sheet 01 Sheet 02 Sheet 03 NOTE: Two persons are necessary. (a) Install the cover of the Raceway Box : Refer to Fig. A-FCAAA Sheet 03 1 Cover Item (77) Retained at removal NOTE: Use the hardware retain at removal. (b) Install the access panel 513QL (Refer to AMM 06-41-57, Page Block 001). (c) Install the Deflector : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 1 Shield Assy Item (76) Retained at removal 1 Bracket Item (74) Retained at removal 1 Shield Item (75) Retained at removal NOTE: Use the hardware retain at removal.
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 261 6

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# @A310 SERVICE BULLETIN (d) Install : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 Refer to AMM 36-11-00, Page Block 401 1 Tube Assy Item (73) Retained at removal 1 Insulation Item (71) Retained at removal 1 Tube Assy Item (72) Retained at removal 1 Insulation Item (71) Retained at removal 1 Duct Assy Item (70) Retained at removal NOTE: Use the hardware retain at removal. (5) Subtask 242105-410-001-001 - Install/Close Items Removed/Opened for access Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-57, Page Block 001 27-50-00, Page Block 301 27-80-00, Page Block 301 29-10-00, Page Block 301 29-14-00, Page Block 301 29-25-00, Page Block 301 32-12-11, Page Block 301 53-15-63, Page Block 401 (a) Pressurize the Yellow Hydraulic System (Refer to AMM 29-10-00, Page Block 301 and AMM 29-14-00, Page Block 301). (b) If necessary, install the removed access panels 513BL, 513DL, 513CL, 513EL, 513FL, 513ML, 613BR, 613DR, 613CR, 613ER, 613FR and 613HR (Refer to AMM 06-41-57, Page Block 001). (c) Install all the removed fairing panels (Refer to AMM 53-15-63, Page Block 401). (d) Install the access panels 572AB, 672AB, 572AZ, 572BZ, 572CZ, 572DZ, 572EZ, 572FZ, 572GZ, 672AZ, 672BZ, 672CZ, 672DZ, 672EZ, 672FZ and 672GZ (Refer to AMM 06-41-57, Page Block 001). (e) Install the access panels 512FB, 612FB, 512BB, 612BB, 612DB, 513RR and 613RR (Refer to AMM 06-41-57, Page Block 001). DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 262 6

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# @A310 SERVICE BULLETIN (f) If necessary, install the removed access panels 571BB, 571CB, 671BB and 671CB (Refer to AMM 06-41-57, Page Block 001). (g) Fully retract the flaps (Refer to AMM 27-50-00, Page Block 301). (h) Close the Main Landing Gear (MLG) door (Refer to AMM 32-12-11, Page Block 301). (i) Remove the access platform(s). (6) Subtask 242105-942-402-001 - Close-up Work Zones and Access Panels Zone Access/Work location 612 Access Panel 612HB 512 Access Panel 512HB 624 Access Panel 624KB Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 201 27-80-00, Page Block 301 29-10-00, Page Block 301 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Replace the access panels 612HB, 512HB and 624KB. (c) Remove the access platforms. (d) Remove the warning notices from the cockpit. (e) Energize the aircraft, refer to AMM 24-00-00, Page Block 201. (f) Energize the hydraulic systems, refer to AMM 29-10-00, Page Block 301. (g) Fully retract the slats, refer to AMM 27-80-00, Page Block 301. (7) Subtask 242105-942-201-004 - CLOSE-UP Work Zones and Access Panels Zone Access/Work location 600 500 Manpower Resources Skills NON SPECIFIC

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 263 6

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# @A310 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 06-41-57, Page Block 001 24-00-00, Page Block 301 (a) On the lower surface of the LH wing, install the removed leading-edge access panels 512BB, 512CB, 512DB, 512GB and 512JB, refer to AMM 06-41-57, Page Block 001. (b) On the lower surface of the LH wing, install the removed leading-edge access panels 524BB, 524CB and 524KB, refer to AMM 06-41-57, Page Block 001. (c) On the lower surface of the RH wing, install the removed leading-edge access panels 612BB, 612CB, 612DB, 612GB and 612JB, refer to AMM 06-41-57, Page Block 001. (d) On the lower surface of the RH wing, install the removed leading-edge access panels 624BB and 624CB, refer to AMM 06-41-57, Page Block 001. (e) Remove the access platforms below the leading-edges of: - the LH wing at Zone 512 - the LH wing at Zone 524 - the RH wing at Zone 612 - the RH wing at Zone 624 (f) Remove the warning notices from the cockpit to tell persons not to operate the flight controls. (g) Remove the safety guard from the flap and slat control lever. (h) Remove the aircraft ground connection, refer to AMM 24-00-00, Page Block 301. **CONF 004 (1) Subtask 242105-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 27-50-00, Page Block 301 29-14-00, Page Block 301 (a) Restore the systems and the aircraft to normal operating condition. (b) Make sure that the work areas are clean and clear of tools and other items of equipment. (c) Do the close-up procedure as specified in the Extension and Retraction of Flaps with Aircraft System (Refer to AMM 27-50-00, Page Block 301). DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 264 6

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# @A310 SERVICE BULLETIN (2) Subtask 242105-410-002-001 - Install the two Hydraulic Pipes in the RH Wings removed for access. Work Zones and Access Panels Zone Access/Work location 673 Manpower Resources Skills NON SPECIFIC Material necessary to do the job Kit 242105A01R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 62 NSA935401-13 1 TIE References Aircraft Maintenance Manual (AMM) 29-00-00, Page Block 401 Fig. A-FCBAA Removal of Hydraulic Pipes for access Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Install the two Hydraulic Pipes : Refer to Fig. A-FCBAA Sheet 01 , Fig. A-FCBAA Sheet 02 and Fig. A-FCBAA Sheet 03 Refer to AMM 29-00-00, Page Block 401 1 Hydraulic Pipes Item (78) Retained at removal 1 Hydraulic Pipes Item (79) Retained at removal (b) Install the hardware : Refer to Fig. A-FCBAA Sheet 01 , Fig. A-FCBAA Sheet 02, Fig. A-FCBAA Sheet 03 and Fig. A-FCBAA Sheet 04 1 Block Isolator Item (83) Retained at removal With : 1 Tie-Cable NSA935401-13 Item 62 And : 2 Block Clamp Item (82) Retained at removal DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 265 6

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# @A310 SERVICE BULLETIN
With : 2 Washer Item (81) Retained at removal 2 Bolt Item (80) Retained at removal (3) Subtask 242105-410-003-001 - Install the Air Ducts and the Deflector in the RH Wings removed for access. Work Zones and Access Panels Zone Access/Work location 512 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-57, Page Block 001 36-11-00, Page Block 401 Fig. A-FCAAA Removal of Air Ducts and Reflector in the Wings for access Sheet 01 Sheet 02 Sheet 03 NOTE: Two persons are necessary. (a) Install the cover of the Raceway Box : Refer to Fig. A-FCAAA Sheet 03 1 Cover Item (77) Retained at removal NOTE: Use the hardware retain at removal. (b) Install the access panel 613QL (Refer to AMM 06-41-57, Page Block 001). (c) Install the Deflector : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 1 Shield Assy Item (76) Retained at removal 1 Bracket Item (74) Retained at removal 1 Shield Item (75) Retained at removal NOTE: Use the hardware retain at removal.
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 266 6

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

# @A310 SERVICE BULLETIN (d) Install : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 Refer to AMM 36-11-00, Page Block 401 1 Tube Assy Item (73) Retained at removal 1 Insulation Item (71) Retained at removal 1 Tube Assy Item (72) Retained at removal 1 Insulation Item (71) Retained at removal 1 Duct Assy Item (70) Retained at removal NOTE: Use the hardware retain at removal. (4) Subtask 242105-410-004-001 - Install the Air Ducts and the Deflector in the LH Wings removed for access. Work Zones and Access Panels Zone Access/Work location 612 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-57, Page Block 001 36-11-00, Page Block 401 Fig. A-FCAAA Removal of Air Ducts and Reflector in the Wings for access Sheet 01 Sheet 02 Sheet 03 NOTE: Two persons are necessary. (a) Install the cover of the Raceway Box : Refer to Fig. A-FCAAA Sheet 03 1 Cover Item (77) Retained at removal NOTE: Use the hardware retain at removal. (b) Install the access panel 513QL (Refer to AMM 06-41-57, Page Block 001).
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 267 6

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

# @A310 SERVICE BULLETIN (c) Install the Deflector : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 1 Shield Assy Item (76) Retained at removal 1 Bracket Item (74) Retained at removal 1 Shield Item (75) Retained at removal NOTE: Use the hardware retain at removal. (d) Install : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 Refer to AMM 36-11-00, Page Block 401 1 Tube Assy Item (73) Retained at removal 1 Insulation Item (71) Retained at removal 1 Tube Assy Item (72) Retained at removal 1 Insulation Item (71) Retained at removal 1 Duct Assy Item (70) Retained at removal NOTE: Use the hardware retain at removal. (5) Subtask 242105-410-001-001 - Install/Close Items Removed/Opened for access Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-57, Page Block 001 27-50-00, Page Block 301 27-80-00, Page Block 301 29-10-00, Page Block 301 29-14-00, Page Block 301 29-25-00, Page Block 301 32-12-11, Page Block 301 53-15-63, Page Block 401
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 268 6

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

# @A310 SERVICE BULLETIN (a) Pressurize the Yellow Hydraulic System (Refer to AMM 29-10-00, Page Block 301 and AMM 29-14-00, Page Block 301). (b) If necessary, install the removed access panels 513BL, 513DL, 513CL, 513EL, 513FL, 513ML, 613BR, 613DR, 613CR, 613ER, 613FR and 613HR (Refer to AMM 06-41-57, Page Block 001). (c) Install all the removed fairing panels (Refer to AMM 53-15-63, Page Block 401). (d) Install the access panels 572AB, 672AB, 572AZ, 572BZ, 572CZ, 572DZ, 572EZ, 572FZ, 572GZ, 672AZ, 672BZ, 672CZ, 672DZ, 672EZ, 672FZ and 672GZ (Refer to AMM 06-41-57, Page Block 001). (e) Install the access panels 512FB, 612FB, 512BB, 612BB, 612DB, 513RR and 613RR (Refer to AMM 06-41-57, Page Block 001). (f) If necessary, install the removed access panels 571BB, 571CB, 671BB and 671CB (Refer to AMM 06-41-57, Page Block 001). (g) Fully retract the flaps (Refer to AMM 27-50-00, Page Block 301). (h) Close the Main Landing Gear (MLG) door (Refer to AMM 32-12-11, Page Block 301). (i) Remove the access platform(s). (6) Subtask 242105-942-402-001 - Close-up Work Zones and Access Panels Zone Access/Work location 612 Access Panel 612HB 512 Access Panel 512HB 624 Access Panel 624KB Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 201 27-80-00, Page Block 301 29-10-00, Page Block 301 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Replace the access panels 612HB, 512HB and 624KB. (c) Remove the access platforms. (d) Remove the warning notices from the cockpit. (e) Energize the aircraft, refer to AMM 24-00-00, Page Block 201.
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 269 6

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

# @A310 SERVICE BULLETIN (f) Energize the hydraulic systems, refer to AMM 29-10-00, Page Block 301. (g) Fully retract the slats, refer to AMM 27-80-00, Page Block 301. (7) Subtask 242105-942-201-005 - CLOSE-UP Work Zones and Access Panels Zone Access/Work location 600 500 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-57, Page Block 001 24-00-00, Page Block 301 (a) On the lower surface of the LH wing, install the removed leading-edge access panels 512BB, 512CB, 512DB, 512GB and 512JB, refer to AMM 06-41-57, Page Block 001. (b) On the lower surface of the LH wing, install the removed leading-edge access panels 524BB, 524CB and 524KB, refer to AMM 06-41-57, Page Block 001. (c) On the lower surface of the RH wing, install the removed leading-edge access panels 612BB, 612CB, 612DB, 612GB and 612JB, refer to AMM 06-41-57, Page Block 001. (d) On the lower surface of the RH wing, install the removed leading-edge access panels 624BB and 624CB, refer to AMM 06-41-57, Page Block 001. (e) On the lower surface of the LH wing, install the removed trailing-edge access panel 575DB, refer to AMM 06-41-57, Page Block 001. (f) Remove the access platforms below the leading-edges of: - the LH wing at Zone 512 - the LH wing at Zone 524 - the RH wing at Zone 612 - the RH wing at Zone 624 (g) Remove the access platform from the position below the trailing-edge access panel of the LH wing at Zone 575. (h) Remove the warning notices from the cockpit to tell persons not to operate the flight controls. (i) Remove the safety guard from the flap and slat control lever.
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 270 6

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

# @A310 SERVICE BULLETIN (j) Remove the aircraft ground connection, refer to AMM 24-00-00, Page Block 301.

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 271 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

ONLY ONE CONFIGURATION SHOWN. EQUIPMENT MAY DIFFER DEPENDING ON AIRCRAFT CONFIGURATION. 

### A

NOTE: Z612

Z512 

### A E

B 613RR

RH SIDE SHOWN LH SIDE SYMMETRICAL 

## A

VIEW FROM ACCESS PANEL 613RR 

### C

D



## B 613QL

513RR 513QL RH LH

RH LH

B_SB_242105_5_CAAA_01_01 Figure A-FCAAA - Sheet 01 Removal of Air Ducts and Reflector in the Wings for access
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 272 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

B_SB_242105_5_CAAA_02_00 (70) (71) (72) (71) (73)

(74) (75) (76)



## D C

Figure A-FCAAA - Sheet 02 Removal of Air Ducts and Reflector in the Wings for access
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 273 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

ONLY ONE CONFIGURATION SHOWN. EQUIPMENT MAY DIFFER DEPENDING ON AIRCRAFT CONFIGURATION. NOTE: VIEW FROM ACCESS PANEL 613QL (77) 

## E

B_SB_242105_5_CAAA_03_00 Figure A-FCAAA - Sheet 03 Removal of Air Ducts and Reflector in the Wings for access
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 274 6

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

# @A310 SERVICE BULLETIN

**CONF ALL



### B Z673 

### A



## A

B_SB_242105_5_CBAA_01_00 RIB01 RIB03

Figure A-FCBAA - Sheet 01 Removal of Hydraulic Pipes for access
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 275 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

ONLY ONE CONFIGURATION SHOWN. EQUIPMENT MAY DIFFER DEPENDING ON AIRCRAFT CONFIGURATION. NOTE: 

## B
INBD 

### C

B_SB_242105_5_CBAA_02_00 Figure A-FCBAA - Sheet 02 Removal of Hydraulic Pipes for access
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 276 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

ONLY ONE CONFIGURATION SHOWN. EQUIPMENT MAY DIFFER DEPENDING ON AIRCRAFT CONFIGURATION. NOTE: INBD HYDRAULIC PIPES TO BE REMOVED FOR ACCESS (TWO HYDRAULIC PIPES) (79)

(78)



## C D

RIB02 RIB01

B_SB_242105_5_CBAA_03_01 Figure A-FCBAA - Sheet 03 Removal of Hydraulic Pipes for access
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 277 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

ONLY ONE CONFIGURATION SHOWN. EQUIPMENT MAY DIFFER DEPENDING ON AIRCRAFT CONFIGURATION. NOTE: INBD 

## D (80) (81) (62) 62

(83) (82)

B_SB_242105_5_CBAA_04_00 Figure A-FCBAA - Sheet 04 Removal of Hydraulic Pipes for access
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 278 6

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

# @A310 SERVICE BULLETIN

**CONF ALL



### B FR40 FR39

STGR28

STGR29

STGR30

VIEW LOOKING INSIDE FR40 FR39

1E 1G 

### A Z137



## A

B
B_SB_242105_5_BAAA_01_01 

### C

Figure A-FBAAA - Sheet 01 Modification of the routing between FR39 and FR40 at STGR28 to STGR30 (LH side)
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 279 6

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

# @A310 SERVICE BULLETIN

**CONF ALL



### A

A B

B



## C

65 63 62

53 OR 62 51

ONLY ONE CONFIGURATION SHOWN. EQUIPMENT MAY DIFFER DEPENDING ON AIRCRAFT CONFIGURATION. NOTE: 

## A A B B

B_SB_242105_5_BAAA_02_01 Figure A-FBAAA - Sheet 02 Modification of the routing between FR39 and FR40 at STGR28 to STGR30 (LH side)
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 280 6

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

# @A310 SERVICE BULLETIN

**CONF ALL FR40 FR39

STGR28

STGR29

STGR30

VIEW LOOKING INSIDE 

### B

A
Z138

FR40 FR39

2E 2G 

## A

B
B_SB_242105_5_BEAA_01_01 

### C

Figure A-FBEAA - Sheet 01 Modification of the routing between FR39 and FR40 at STGR28 to STGR30 (RH side)
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 281 6

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

# @A310 SERVICE BULLETIN

**CONF ALL



## C

65 63 62

53 OR 62 51

ONLY ONE CONFIGURATION SHOWN. EQUIPMENT MAY DIFFER DEPENDING ON AIRCRAFT CONFIGURATION. NOTE: 

## A A B B B

B A

A

B_SB_242105_5_BEAA_02_01 Figure A-FBEAA - Sheet 02 Modification of the routing between FR39 and FR40 at STGR28 to STGR30 (RH side)
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 282 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

Z612

Z512 

### A

LH SIDE SHOWN RH SIDE SYMMETRICAL RIB01 RIB02
RIB03 RIB04 RIB05 

### A



## A

B_SB_242105_5_BBAA_01_03 

### B

Figure A-FBBAA - Sheet 01 Modification of the routing in the forward wing to fuselage fairing (LH and RH side)
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 283 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

1S

−3R (LH) 2S

−3R (RH) 2M (RH) 1M (LH) 1M (LH) 2M (RH) 1S (LH) 2S (RH) 1G (LH) 2G (RH) STGR28

STGR29

STGR30
STGR31

LOWER WING SURFACE UPPER WING SURFACE RIB01 RIB02 RIB03 RIB04

LH SIDE SHOWN RH SIDE SYMMETRICAL 1E (LH) 2E (RH) 15

−20 mm (0.591

−0.787 in)

200 mm (7.874 in) 

### B

B B

B B B

A

A 200 mm (7.874 in) 53

53 52 66 67 OR OR

1S (LH) 2S (RH)



## B 53 OR 62 63 

## A A
(84) 85 86

(84) 85 86 (90) (90) OR

OR 

## B B (87)

(87)

(88) (89) 

### C (84) 85 86 OR

(84) 85 86 OR

(84) 85 86 OR (84) 85 86 OR (90)



## C C C

C

(88) (89)

B_SB_242105_5_BBAA_02_02 Figure A-FBBAA - Sheet 02 Modification of the routing in the forward wing to fuselage fairing (LH and RH side)
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 284 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

ONLY ONE CONFIGURATION SHOWN. EQUIPMENT MAY DIFFER DEPENDING ON AIRCRAFT CONFIGURATION. NOTE: EXAMPLE OF PROTECTIVE SLEEVE INSTALLATION FWD 

## C

B_SB_242105_5_BBAA_03_00 Figure A-FBBAA - Sheet 03 Modification of the routing in the forward wing to fuselage fairing (LH and RH side)
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 285 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

Z573 

### A

RIB01 RIB06

LH SIDE SHOWN RH SIDE SYMMETRICAL 

### B



## A

B_SB_242105_5_BCAA_01_03 Z673



### A

Figure A-FBCAA - Sheet 01 Modification of the routing in the shroud box (LH and RH side)
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 286 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

ONLY ONE CONFIGURATION SHOWN. EQUIPMENT MAY DIFFER DEPENDING ON AIRCRAFT CONFIGURATION. NOTE: 

### C



## B

B_SB_242105_5_BCAA_02_02 INBD

Figure A-FBCAA - Sheet 02 Modification of the routing in the shroud box (LH and RH side)
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 287 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

68 69 ONLY ONE CONFIGURATION SHOWN. EQUIPMENT MAY DIFFER DEPENDING NOTE: 1M (LH) 2M(RH) 2M (LH) 1M(RH)

2S (LH) 1S(RH) 1P (LH) 2P(RH)

1S 2S

−3R

−2V(RH) −3R

−1V(LH) 2P (LH) 1P (RH) 1M (LH) 2M(RH) 2M (LH) 1M(RH)

2S (LH) 1S(RH) 1S 2S

−3R

−2V(RH) −3R

−1V(LH)

2P (LH) 1P (RH)
1P (LH) 2P(RH) 

### G G H

H C

C D

D D

D C

C C

C D

D K

K B

B K

K E

E F

F E

E F

F L

L K

K L

L L

L A

A A

A RIB01 RIB02 RIB03 RIB04 RIB05 RIB06
20 mm (0.787 in) 20 mm (0.787 in)

52 66 67 52 66 67 OR OR 52 66 67 OR OR

52 66 67 OR OR OR OR 53

53 53 53

F W D 

### F E G

ON AIRCRAFT CONFIGURATION. 

## BEFORE AFTER (57) (99)
(95) (95)

(90) 96 96 57 99



## G G H H C

64

B_SB_242105_5_BCAA_03_02 Figure A-FBCAA - Sheet 03 Modification of the routing in the shroud box (LH and RH side)
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 288 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

(81) (88) (90)

(95) 

## BEFORE

AFTER

57 97

57 98 96 68 69 

### H 93 94 LH RH (81) (88) (90)

(95) CASE 1 CASE 2 

## OR

C C

D D
IF BRACKET PN A924

−40102 IS INSTALLED, INSTALL ITEM 91. 01 02 NOTE: 02

IF BRACKET PN NSA5456

−03 IS INSTALLED, INSTALL ITEM 93. 91 92

57 97

57 98 96 68 69 LH RH 01



### H 

## OR

CASE 1 CASE 2

B_SB_242105_5_BCAA_04_01 Figure A-FBCAA - Sheet 04 Modification of the routing in the shroud box (LH and RH side)
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 289 6

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# @A310 SERVICE BULLETIN

**CONF ALL

EXISTING HOLE RIB03 RIB02

TO INSTALL THE GROMMET YOU HAVE TO OPEN IT WITH A CRAFT KNIFE (IF NECESSARY). 03 THE BRACKET HAVE TO BE IN CONTACT WITH THE RIB. 04 THE MATERIAL OF THE BRACKET WILL BE DIFFERENT FOR THIS SERVICE BULLETIN. 05 NOTE:

ONLY ONE CONFIGURATION SHOWN. EQUIPMENT MAY DIFFER DEPENDING ON AIRCRAFT CONFIGURATION. EXAMPLE OF PTFE CONDUITS OUT FROM PROTECTIVE SLEEVE

EXAMPLE OF WIRES CHANGING ROUTES

EXAMPLE OF VN WIRE ROUTING OUT FROM PROTECTIVE SLEEVE EXAMPLE OF ROUTING WITH NEW BRACKETS 03

04 05 

### D



## D E

F

G H 55 64 62


## A A
B B

B_SB_242105_5_BCAA_05_02 Figure A-FBCAA - Sheet 05 Modification of the routing in the shroud box (LH and RH side)
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 290 6

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

# @A310 SERVICE BULLETIN

**CONF ALL 

## BEFORE

AFTER TYPICAL

TYPICAL TYPICAL TYPICALWY 260WY 260

60 57 (58) 61 (60) (57) (58)WY 260WY 260

(56)

56 (57)

57 (58) (58)

63 (53) (53)

(53) (53)

(53) (53)

53 53 53

53 53 53 

## E E

F F K K

L L
B_SB_242105_5_BCAA_06_00 Figure A-FBCAA - Sheet 06 Modification of the routing in the shroud box (LH and RH side)
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 291 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

B_SB_242105_7_BAAA_01_00 RIB7

LH WING SHOWN RH WING SIMILAR RH WING ONLY RIB27



## A B B
A A

C

D

F W D INBD F W D INBD

Figure A-UBAAA - Sheet 01 Installation of the new clip and nutplate
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 292 6

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

# @A310 SERVICE BULLETIN

**CONF ALL RIB7

102 50.8mm (2.00in)

U P INBD VIEW LOOKING AFT ON FRONT SPAR LOCATE TO DIMENSION SHOWN AND TO MATCH EXISTING ROUTE OF CABLES

B_SB_242105_7_BAAA_02_00 

## C
Figure A-UBAAA - Sheet 02 Installation of the new clip and nutplate
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 293 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

VIEW LOOKING AFT ON FRONT SPAR RIB28

B_SB_242105_7_BAAA_03_00 

## D E

U P INBD

Figure A-UBAAA - Sheet 03 Installation of the new clip and nutplate
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 294 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

FRONT SPAR

POSITION ON CL OF EXISTING ANCHOR NUT

F W D INBD PLAN VIEW ON FRONT SPAR RIB28

B_SB_242105_7_BAAA_04_00 

## E

F F

111 106 (2 POSITIONS) 6.35 mm (0.250 in)

25.4 mm (1.00 in)

Figure A-UBAAA - Sheet 04 Installation of the new clip and nutplate
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 295 6

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

# @A310 SERVICE BULLETIN

**CONF 001

RIB2 RIB3 Z512

FRONT SPAR

RIB8 

### B



## A

B_SB_242105_6_DEAA_01_00 

### A

Figure A-GDEAA - Sheet 01 Modification of the electrical routing installation at the LH front spar in the area of RIB 2
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 296 6

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

# @A310 SERVICE BULLETIN

**CONF 001 RIB3 RIB2



### A

A B

B

INBD 

## B

TYPICAL NOTE: PROTECTIVE SLEEVE INSTALLATION 01 

## C C

C

20.0 mm (0.79 in)

20.0 mm (0.79 in) 150.0 mm

(5.91 in)

43 01

B_SB_242105_6_DEAA_02_00 Figure A-GDEAA - Sheet 02 Modification of the electrical routing installation at the LH front spar in the area of RIB 2
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 297 6

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

# @A310 SERVICE BULLETIN

**CONF 001 FRONT SPAR

613VB /1M 621VB /1M 611VB /1M 

## BEFORE

AFTER 

## A A (57) (70) (77) (54) 619VB /2M

(73)

(54)

(130) 619VB /2S

611VB /1MG 615VB /1S 623VB /1S 641VB /1S

19 (73)



## B B

19

611VB /1MG 18 (130)
615VB /1S 623VB /1S 641VB /1S 619VB /2S

611VB /1M 613VB /1M 621VB /1M 619VB /2M

MOD 13497 MOD 13492 SB24

−2105 100

TYPICAL 

## D

NOTE: 02 03 INSTALL PLACARD WITH CABLE TIES, ITEM , IN A GOOD 100 VISIBLE POSITION 03

PROTECTIVE SLEEVE FRONT SPAR

(70) (77) 

### D
D

D D 02

02

02

B_SB_242105_6_DEAA_03_02 Figure A-GDEAA - Sheet 03 Modification of the electrical routing installation at the LH front spar in the area of RIB 2
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 298 6

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

# @A310 SERVICE BULLETIN

**CONF 001



## A RIB2 RIB3 FRONT SPAR

RIB8 

### B A Z612

B_SB_242105_6_DFAA_01_00 Figure A-GDFAA - Sheet 01 Modification of the electrical routing installation at the RH front spar in the area of RIB 2
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 299 6

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

# @A310 SERVICE BULLETIN

**CONF 001



## B RIB3 RIB2

INBD

B_SB_242105_6_DFAA_02_00 TYPICAL NOTE: PROTECTIVE SLEEVE INSTALLATION 01 

## C 43 

### A

A B

B C

C

20.0 mm (0.79 in) 20.0 mm (0.79 in) 150.0 mm (5.91 in) 01

Figure A-GDFAA - Sheet 02 Modification of the electrical routing installation at the RH front spar in the area of RIB 2
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 300 6

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

# @A310 SERVICE BULLETIN

**CONF 001 

## BEFORE

AFTER 

## A A (58) (70) (77) (73) (54)

FRONT SPAR

30 (73)

(70) (77) 19

29 (130) (130)

(61) 620VB /1S 620VB /1M

612VB /2M 614VB /2M 622VB /2M 616VB /2S 624VB /2S 642VB /2S 612VB /2MG

612VB /2M 614VB /2M 622VB /2M 616VB /2S 624VB /2S 642VB /2S 620VB /1S 620VB /1M

612VB /2MG FRONT SPAR



## B B MOD 13497 MOD 13492 SB24

−2105 100

TYPICAL 

## D

NOTE: 02 03 INSTALL PLACARD WITH CABLE TIES, ITEM , IN A GOOD 100 VISIBLE POSITION 03

PROTECTIVE SLEEVE 

### D
D

D D 02

02 02

B_SB_242105_6_DFAA_03_02 Figure A-GDFAA - Sheet 03 Modification of the electrical routing installation at the RH front spar in the area of RIB 2
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 301 6

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

# @A310 SERVICE BULLETIN

**CONF 002 thru 004



### A

RIB2 RIB3 Z512

FRONT SPAR

RIB8 

### B



## A

B_SB_242105_6_DAAB_01_00 Figure A-GDAAB - Sheet 01 Modification of the electrical routing installation at the LH front spar in the area of RIB 2
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 302 6

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

# @A310 SERVICE BULLETIN

**CONF 002 thru 004

B_SB_242105_6_DAAB_02_01 RIB3 RIB2



### B

B

INBD 

## B

TYPICAL NOTE: PROTECTIVE SLEEVE INSTALLATION 01 

## C C

C

20.0 mm (0.79 in)

20.0 mm (0.79 in) 150.0 mm

(5.91 in)

43 01 OR

OR 

### A

A C

C D

D OR

OR

Figure A-GDAAB - Sheet 02 Modification of the electrical routing installation at the LH front spar in the area of RIB 2
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 303 6

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

# @A310 SERVICE BULLETIN

**CONF 002 thru 004

FRONT SPAR

(57) 611VB /1M 613VB /1M 621VB /1M (54) 619VB /2M

(73) (70) (77)



## B B (54)

(57) 615VB /1S 623VB /1S 641VB /1S

619VB /2S FRONT SPAR

613VB /1M 621VB /1M 611VB /1M



## A A (57) 

## BEFORE

(70) (72) (54) 619VB /2M
(73) (54)

(57)

(79) (78)
(78) 611VB /1MG 619VB /2S

611VB /1MG 615VB /1S 623VB /1S 641VB /1S

B_SB_242105_6_DAAB_03_01 OR 

## BEFORE

Figure A-GDAAB - Sheet 03 Modification of the electrical routing installation at the LH front spar in the area of RIB 2
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 304 6

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

# @A310 SERVICE BULLETIN

**CONF 002 thru 004

FRONT SPAR OR 

## AFTER

FRONT SPAR

18 611VB /1M 613VB /1M 621VB /1M 

## AFTER
19 619VB /2M

(73)

(70) (72) 19 

### D D

D D 02

(79) (78)
(78) 18

02

611VB /1MG 611VB /1MG 615VB /1S 623VB /1S 641VB /1S

619VB /2S 02

MOD 13497 MOD 13492 SB24

−2105 100

TYPICAL 

## D

NOTE: 02 03 INSTALL PLACARD WITH CABLE TIES, ITEM , IN A GOOD 100 VISIBLE POSITION 03

PROTECTIVE SLEEVE 

## C C

D D 02 02

02 19 19

18 18 (73) (70) (77) 

### D D

D D 619VB /2S 619VB /2M

615VB /1S 623VB /1S 641VB /1S 611VB /1M 613VB /1M 621VB /1M

B_SB_242105_6_DAAB_04_02 Figure A-GDAAB - Sheet 04 Modification of the electrical routing installation at the LH front spar in the area of RIB 2
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 305 6

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

# @A310 SERVICE BULLETIN

**CONF 002 thru 004



## A

B_SB_242105_6_DBAB_01_00 RIB2 RIB3 FRONT SPAR

RIB8 

### B A Z612

Figure A-GDBAB - Sheet 01 Modification of the electrical routing installation at the RH front spar in the area of RIB 2
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 306 6

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

# @A310 SERVICE BULLETIN

**CONF 002 thru 004

B_SB_242105_6_DBAB_02_01 

### B

B OR

OR 

### A

A C

C D

D OR

OR



## B RIB3 RIB2

INBD

TYPICAL NOTE: PROTECTIVE SLEEVE INSTALLATION 01 

## C 43 

### C

C

20.0 mm (0.79 in) 20.0 mm (0.79 in) 150.0 mm (5.91 in) 01

Figure A-GDBAB - Sheet 02 Modification of the electrical routing installation at the RH front spar in the area of RIB 2
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 307 6

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

# @A310 SERVICE BULLETIN

**CONF 002 thru 004 FRONT SPAR



## A A (58) 

## BEFORE

(70) (72) (61) (73)

(73)

(70) (77) (54)

(58)

(79) (78)
(78)

(54)

(58) (58) 620VB /1S 620VB /1M
612VB /2M 614VB /2M 622VB /2M

616VB /2S 624VB /2S 642VB /2S

612VB /2MG 612VB /2MG

612VB /2M 614VB /2M 622VB /2M

616VB /2S 624VB /2S 642VB /2S

B_SB_242105_6_DBAB_03_01 FRONT SPAR



## B B OR 

## BEFORE 620VB /1M 620VB /1S (61)

Figure A-GDBAB - Sheet 03 Modification of the electrical routing installation at the RH front spar in the area of RIB 2
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 308 6

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

# @A310 SERVICE BULLETIN

**CONF 002 thru 004 FRONT SPAR

29 

## AFTER

19

(73)

(70) (72) 30 

### D

D

D D

(79) (78)
(78) 29 02 02

02 612VB /2M 614VB /2M 622VB /2M

616VB /2S 624VB /2S 642VB /2S 620VB /1S 620VB /1M

612VB /2MG 612VB /2MG

FRONT SPAR

02 02

02 

## C C
OR 

## AFTER

MOD 13497 MOD 13492 SB24

−2105 100

TYPICAL 

## D

NOTE: 02 03 INSTALL PLACARD WITH CABLE TIES, ITEM , IN A GOOD 100 VISIBLE POSITION 03

PROTECTIVE SLEEVE 

## D D 30

29 19

29 (70) (77) (73) 

### D

D D D 612VB /2M 614VB /2M 622VB /2M 620VB /1M

620VB /1S

616VB /2S 624VB /2S 642VB /2S

B_SB_242105_6_DBAB_04_02 Figure A-GDBAB - Sheet 04 Modification of the electrical routing installation at the RH front spar in the area of RIB 2
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 309 6

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

# @A310 SERVICE BULLETIN

**CONF ALL



### A

RIB2 RIB3 Z512

FRONT SPAR

RIB8 

### B



## A

B_SB_242105_6_DCAA_01_00 Figure A-GDCAA - Sheet 01 Modification of the electrical routing installation at the LH front spar in the area of RIB 3
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 310 6

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

# @A310 SERVICE BULLETIN

**CONF ALL RIB3 RIB2

INBD 

## B

20.0 mm (0.79 in)

TYPICAL NOTE: PROTECTIVE SLEEVE INSTALLATION 01 

## C 01 20 21 OR

B_SB_242105_6_DCAA_02_01 

### A

A B

B C

C D

D OR OR OR OR 

### C C

OR OR OR OR 

### A

A B

B C

C D

D

Figure A-GDCAA - Sheet 02 Modification of the electrical routing installation at the LH front spar in the area of RIB 3
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 311 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

FRONT SPAR
611VB /1M 613VB /1M 621VB /1M

(54) (57) 

## BEFORE (73)

(70) (72) 611VB /1MG 615VB /1S 623VB /1S 641VB /1S
(79) (78) (73) 611VB /1MG



## A A

B B TYPICAL

TYPICAL B_SB_242105_6_DCAA_03_01 FRONT SPAR 

## BEFORE OR

(70) (77) (54) (73)

(57) 615VB /1S 623VB /1S 641VB /1S 611VB /1M 613VB /1M 621VB /1M

Figure A-GDCAA - Sheet 03 Modification of the electrical routing installation at the LH front spar in the area of RIB 3
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 312 6

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

# @A310 SERVICE BULLETIN

**CONF ALL 

## AFTER

613VB /1M 621VB /1M 611VB /1M

NOTE: 02 FRONT SPAR

MOD 13497 MOD 13492 SB24

−2105 100

TYPICAL 

## D

INSTALL PLACARD WITH CABLE TIES, ITEM , IN A GOOD 100 VISIBLE POSITION 

### D

D (73)

20 19 (79) (73) (70) (72) (78) 18
21

02 611VB /1MG 615VB /1S 623VB /1S 641VB /1S

611VB /1MG



## AFTER OR

B_SB_242105_6_DCAA_04_00 FRONT SPAR 

## C C

D D TYPICAL 19 20 21 18 (73)

(70) (77) 615VB /1S 623VB /1S 641VB /1S 611VB /1M 613VB /1M 621VB /1M TYPICAL



### D

D

Figure A-GDCAA - Sheet 04 Modification of the electrical routing installation at the LH front spar in the area of RIB 3
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 313 6

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

# @A310 SERVICE BULLETIN

**CONF ALL



## A RIB2 RIB3 FRONT SPAR

RIB8 

### B A Z612

B_SB_242105_6_DDAA_01_00 Figure A-GDDAA - Sheet 01 Modification of the electrical routing installation at the RH front spar in the area of RIB 3
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 314 6

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

# @A310 SERVICE BULLETIN

**CONF ALL



## B

20.0 mm (0.79 in)

TYPICAL NOTE: PROTECTIVE SLEEVE INSTALLATION 01 

## C 01 20 21 OR RIB3 RIB2



### C C

INBD

B_SB_242105_6_DDAA_02_01 

### A

A B

B OR OR 

### C

C D

D OR

OR OR OR OR

OR 

### A

A B

B C

C D

D

Figure A-GDDAA - Sheet 02 Modification of the electrical routing installation at the RH front spar in the area of RIB 3
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 315 6

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

# @A310 SERVICE BULLETIN

**CONF ALL 

## BEFORE



## A A

B B FRONT SPAR

(54) (58) (73)

(70) (72) (79) (78) (73) 616VB /2S 624VB /2S 642VB /2S 612VB /2M 614VB /2M 622VB /2M

612VB /2MG

612VB /2MG

B_SB_242105_6_DDAA_03_01 

## BEFORE FRONT SPAR

(58) (73)

(70) (77) (54) 612VB /2M 614VB /2M 622VB /2M
616VB /2S 624VB /2S 642VB /2S OR TYPICAL

TYPICAL
Figure A-GDDAA - Sheet 03 Modification of the electrical routing installation at the RH front spar in the area of RIB 3
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 316 6

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

# @A310 SERVICE BULLETIN

**CONF ALL 

## AFTER

NOTE: 02 MOD 13497 MOD 13492 SB24

−2105 100

TYPICAL 

## D

INSTALL PLACARD WITH CABLE TIES, ITEM , IN A GOOD 100 VISIBLE POSITION 02 FRONT SPAR



### D

D (73)

20 19 (79) (73) (70) (72) (78) 29
21 616VB /2S 624VB /2S 642VB /2S 612VB /2M 614VB /2M 622VB /2M

612VB /2MG

612VB /2MG



## AFTER OR

B_SB_242105_6_DDAA_04_00 

## C C TYPICAL
FRONT SPAR



## D D TYPICAL 29 21

19 20 (73)

(70) (77) 612VB /2M 614VB /2M 622VB /2M
616VB /2S 624VB /2S 642VB /2S 

### D D

Figure A-GDDAA - Sheet 04 Modification of the electrical routing installation at the RH front spar in the area of RIB 3
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 317 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

RIB5 RIB6 FRONT SPAR

RIB8 

### B



## A

B_SB_242105_6_EAAA_01_00 

### C

LH SHOWN RH SYMMETRICAL Z512 

### A Z612



### A

Figure A-GEAAA - Sheet 01 Modification of the electrical routing installation at the LH/RH front spars in the area of RIB 5 and RIB 6
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 318 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

F W D FRONT SPAR

SUB SPAR RIB5 RIB6

INBD 

## B

BEFORE

SUB SPAR (19)

(3) (4) (5) 616VB /2S 624VB /2S 642VB /2S

620VB /1S (10) RH RH RH LH LH LH 615VB /1S 623VB /1S 641VB /1S



## A A RH 619VB /2S LH TYPICAL 

### A

A A

A

B_SB_242105_6_EAAA_02_02 LH SHOWN RH SYMMETRICAL

Figure A-GEAAA - Sheet 02 Modification of the electrical routing installation at the LH/RH front spars in the area of RIB 5 and RIB 6
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 319 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

SUB SPAR

(19) (3) (4) 23 F W D

616VB /2S 624VB /2S 642VB /2S

620VB /1S FRONT SPAR

SUB SPAR RIB5 RIB6

INBD

(10) 

## AFTER

RH RH RH LH LH LH 615VB /1S 623VB /1S 641VB /1S 

## C

RH 619VB /2S LH 42 32



## B B TYPICAL SUB SPAR RH RH RH LH LH LH

RH LH 24 2 3 3119 4 42 615VB /1S 623VB /1S 641VB /1S 616VB /2S 624VB /2S 642VB /2S

619VB /2S 620VB /1S 

## C C

B_SB_242105_6_EAAA_03_01 

### C

C B

B B

B

Figure A-GEAAA - Sheet 03 Modification of the electrical routing installation at the LH/RH front spars in the area of RIB 5 and RIB 6
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 320 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

LH SHOWN RH SYMMETRICAL Z512 

### A Z612



### A

B_SB_242105_6_FAAA_01_00 RIB2 RIB3 RIB5 RIB6 FRONT SPAR

RIB8



### B 

## A

Figure A-GFAAA - Sheet 01 Modification of the electrical routing installation at the LH/RH front spars in the area of RIB 7 and RIB 8
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 321 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

B_SB_242105_6_FAAA_02_00 FRONT SPAR

SUB SPAR F W D INBD

3 6 7 RIB8

NOTE: 01 TO 5029VN LH AND / OR 5037VN LH

02 BRACKET INSTALLED IN PREVIOUS WORK STEPS 10 02 MOD 13497 MOD 13492 SB24

−2105 100



## D 01 

## B C

D



## C
INSTALL PLACARD WITH CABLE TIES, ITEM , IN A GOOD 100 VISIBLE POSITION LH 614VB /2M 613VB /1M RH

TO 5028VN RH AND / OR 5036VN RH

Figure A-GFAAA - Sheet 02 Modification of the electrical routing installation at the LH/RH front spars in the area of RIB 7 and RIB 8
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 322 6

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

# @A310 SERVICE BULLETIN

**CONF 004



### A

RIB2 RIB3 RIB5 RIB6 FRONT SPAR

RIB8 Z612



### B

642VB /2S 642VB /2S

5082VN 5084VN 6 9

24 FRONT SPAR 

## A

MOD 13497 MOD 13492 SB24

−2105 100 01



## C C

NOTE: INSTALL PLACARD AND CABLE TIE, ITEM , IN A GOOD 01 100 VISIBLE POSITION 02

INSTALL CLAMP, ITEM , DO NOT DISCONNECT THE ELECTRICAL WIRE(S) 02 9 

## B

B_SB_242105_6_CCAA_01_04 3

Figure A-GCCAA - Sheet 01 Modify the Electrical Routing Installation at the RH Front Spar
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 323 6

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

# @A310 SERVICE BULLETIN

**CONF 001, 003 thru 004

RIB31 FRONT SPAR Z524

RIB20 

### A

B_SB_242105_6_GAAA_01_00 

## A B C RIB21

Figure A-GGAAA - Sheet 01 Modification of the electrical routing installation at the LH front spar in the area of RIB 20 and RIB 21
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 324 6

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

# @A310 SERVICE BULLETIN

**CONF 001, 003 thru 004

B_SB_242105_6_GAAA_02_00 SUB SPAR F W D

(8) (9)

(9) (9) (10)

(59) (22) INBD RIB21

(3) 643VB /2S 635VB /1S

635VB /1M 643VB /2M RIB20



## B

A A A

A A

A A

A A

A

TYPICAL 

## BEFORE

Figure A-GGAAA - Sheet 02 Modification of the electrical routing installation at the LH front spar in the area of RIB 20 and RIB 21
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 325 6

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

# @A310 SERVICE BULLETIN

**CONF 001, 003 thru 004

SUB SPAR F W D

(8) (9)

(9) (9) (10)

26

(22) INBD RIB21

(3) 643VB /2S 635VB /1S

635VB /1M 643VB /2M RIB20

B_SB_242105_6_GAAA_03_00 

## AFTER

4032



## B B TYPICAL 

### B

B D

D B

B D

D C

C E

E



## C C 643VB /2S 635VB /1S

643VB /2M
635VB /1M 9
8 10
24

40 9 9 3 11 

## C D D

Figure A-GGAAA - Sheet 03 Modification of the electrical routing installation at the LH front spar in the area of RIB 20 and RIB 21
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 326 6

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

# @A310 SERVICE BULLETIN

**CONF 001, 003 thru 004

(8) (9)

(9) (9) (10)

25

(22) (3) 643VB /2S 635VB /1S

635VB /1M 643VB /2M 41 32

643VB /2S 635VB /1S

643VB /2M
635VB /1M 9
8 10
24

41 9 9 3 11

B_SB_242105_6_GAAA_04_00 

## D D

E E TYPICAL

MOD 13497 MOD 13492 SB24

−2105 100 01

NOTE: INSTALL PLACARD AND CABLE TIE, ITEM , IN A GOOD 01 100 VISIBLE POSITION 

## D

Figure A-GGAAA - Sheet 04 Modification of the electrical routing installation at the LH front spar in the area of RIB 20 and RIB 21
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 327 6

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

# @A310 SERVICE BULLETIN

**CONF 001, 003 thru 004

B_SB_242105_6_HAAA_01_00 RIB31 FRONT SPAR RIB20



## A B C RIB21 Z624



### A

Figure A-GHAAA - Sheet 01 Modification of the electrical routing installation at the RH front spar in the area of RIB 20 and RIB 21
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 328 6

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

# @A310 SERVICE BULLETIN

**CONF 001, 003 thru 004

F W D 

## B

A A TYPICAL 

## BEFORE

B_SB_242105_6_HAAA_02_00 SUB SPAR

(8) (9)

(9) (9) (10)

(60) (22) RIB21

(3) RIB20 

### A

A A

A A

A A

A

INBD

636VB /2S 644VB /1S

636VB /2M 644VB /1M

Figure A-GHAAA - Sheet 02 Modification of the electrical routing installation at the RH front spar in the area of RIB 20 and RIB 21
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 329 6

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

# @A310 SERVICE BULLETIN

**CONF 001, 003 thru 004 

## AFTER



## C C

B_SB_242105_6_HAAA_03_00 SUB SPAR F W D

(8) (9)

(9) (9) (10)

25 INBD RIB21

(3) RIB20

40 32 

### B

B D

D B

B D

D C

C E

E

9
8 10
24

40 9 9 3 11 

## C D D



## B B TYPICAL 636VB /2S 644VB /1S

636VB /2M 644VB /1M 636VB /2S 644VB /1S

644VB /1M 636VB /2M

Figure A-GHAAA - Sheet 03 Modification of the electrical routing installation at the RH front spar in the area of RIB 20 and RIB 21
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 330 6

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

# @A310 SERVICE BULLETIN

**CONF 001, 003 thru 004

MOD 13497 MOD 13492 SB24

−2105 100 01

NOTE: INSTALL PLACARD AND CABLE TIE, ITEM , IN A GOOD 01 100 VISIBLE POSITION 

## D

B_SB_242105_6_HAAA_04_00 (8) (9)

(9) (9) (10)

26 (3) 41 32



## D D TYPICAL 9
8 10
24

41 9 9 3 11



## E E 636VB /2S 644VB /1S

636VB /2M 644VB /1M

636VB /2S 644VB /1S

636VB /2M 644VB /1M

Figure A-GHAAA - Sheet 04 Modification of the electrical routing installation at the RH front spar in the area of RIB 20 and RIB 21
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 331 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

RIB31 FRONT SPAR



## A Z624



### A

B_SB_242105_6_JAAA_01_00 RIB28A RIB28



### B D

Figure A-GJAAA - Sheet 01 Modification of the electrical routing installation at the RH front spar in the area of RIB 28 and RIB 28A
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 332 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

INBD 640VB /1S 636VB /2S

636VB /2M

(9) (56) (3) (9)

(8) 636VB /2S

636VB /2M 640VB /1S 

## BEFORE RIB28A RIB28

B_SB_242105_6_JAAA_02_00 

## B

C C

Figure A-GJAAA - Sheet 02 Modification of the electrical routing installation at the RH front spar in the area of RIB 28 and RIB 28A
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 333 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

INBD 640VB /1S 636VB /2S 636VB /2M

9 3 28 9

27 636VB /2S

636VB /2M 640VB /1S 

## AFTER RIB28A RIB28



## D

E NOTE: 01 MOD 13497 MOD 13492 SB24

−2105 100 01

INSTALL PLACARD WITH CABLE TIES, ITEM , IN A GOOD 100 VISIBLE POSITION 

## F TYPICAL

B_SB_242105_6_JAAA_03_01 

### E

F F

F

Figure A-GJAAA - Sheet 03 Modification of the electrical routing installation at the RH front spar in the area of RIB 28 and RIB 28A
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 334 6

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

# @A310 SERVICE BULLETIN

**CONF 004

B_SB_242105_6_BCAA_01_00 

### A

Z575

RIB9 

### A

A



## A
INBD F W D REAR SPAR


### B

B 629VB /1S 629VB /2S 629VB /3R

629VB /1M 629VB /2M

Figure A-GBCAA - Sheet 01 Modify the Electrical Routing Installation at the LH Rear Spar
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 335 6

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

# @A310 SERVICE BULLETIN

**CONF 004

REAR SPAR (4)

(10) (3) 629VB /1S 629VB /2S 629VB /3R

629VB /1M 629VB /2M

REAR SPAR (4)

10 (3) 15 10

16 2147VC

2147VC 629VB /2S

629VB /1S 629VB /3R 629VB /2M

629VB /1M 

## BEFORE

AFTER (15)

MOD 13497 MOD 13492 SB24

−2105 100 01



## B B 

## A A

B B NOTE: INSTALL PLACARD AND CABLE TIE, ITEM , IN A GOOD 01 100 VISIBLE POSITION 02

INSTALL CLAMP, ITEM , WITHOUT DISCONNECTING OF THE WIRE 02 10 02

(PART OF ) 2612

−5017 2612

−5016

B_SB_242105_6_BCAA_02_04 TO 9GJ

TO 9GJ 5039VN 5041VN

5039VN

5041VN

Figure A-GBCAA - Sheet 02 Modify the Electrical Routing Installation at the LH Rear Spar
DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 336 6

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