@A310

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 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

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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

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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

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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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SERVICE BULLETIN

SUMMARY

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

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

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 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

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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

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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

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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

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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

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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

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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

MANDATORY MANDATORY MANDATORY

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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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This Page Intentionally Left Blank

DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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**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

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(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

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(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

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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

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(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

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(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

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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

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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

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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

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(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

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(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

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- 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

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(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

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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

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(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

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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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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

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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

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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

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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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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

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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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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

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

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

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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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(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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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.

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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.

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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

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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

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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

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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

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

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

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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

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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

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

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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

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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

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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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.

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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

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(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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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.

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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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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

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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

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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

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@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

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@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

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@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

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@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

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@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

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@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

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@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

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@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

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@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

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@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

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@A310

SERVICE BULLETIN

**CONF ALL

ONLY ONE CONFIGURATION SHOWN.

EQUIPMENT MAY DIFFER DEPENDING ON AIRCRAFT CONFIGURATION.

NOTE:

INBD

D

(80)

(81)

(62)

62

(82) (83)

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

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@A310

SERVICE BULLETIN

**CONF ALL

B

FR40

FR39

STGR28

STGR29

STGR30

VIEW LOOKING INSIDE

FR39 FR40

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

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@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

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@A310

SERVICE BULLETIN

**CONF ALL

FR40

FR39

STGR28

STGR29

STGR30

VIEW LOOKING INSIDE

B

A

Z138

FR40 FR39

2G 2E

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

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@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

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@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

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@A310

SERVICE BULLETIN

**CONF ALL

1S−3R (LH)

2S−3R (RH)

2M (RH)

1M (LH)

1M (LH)

2M (RH)

1S (LH)

1G (LH) 2S (RH)

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

B B OR

(87)

(87)

(88)

(89)

C

(84)

85 OR 86

(84)

85 OR 86

(84)

85 OR 86

(84)

85 OR 86 (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

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@A310

SERVICE BULLETIN

**CONF ALL

ONLY ONE CONFIGURATION SHOWN.

EQUIPMENT MAY DIFFER DEPENDING ON AIRCRAFT CONFIGURATION.

NOTE:

EXAMPLE OF PROTECTIVE SLEEVE INSTALLATION

C FWD

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

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@A310

SERVICE BULLETIN

**CONF ALL

A Z573

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

H G

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

01 IF BRACKET PN A924−40102 IS INSTALLED, INSTALL ITEM 91.

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

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

SERVICE BULLETIN

**CONF ALL

EXISTING HOLE

RIB03

RIB02

03 TO INSTALL THE GROMMET YOU HAVE TO OPEN IT WITH A CRAFT KNIFE (IF NECESSARY).

04 THE BRACKET HAVE TO BE IN CONTACT WITH THE RIB.

05 THE MATERIAL OF THE BRACKET WILL BE DIFFERENT FOR THIS SERVICE BULLETIN.

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

TYPICAL WY 260

WY 260

60

57

(58)

61

(60)

(57)

(58)WY 260

WY 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

RIB2 RIB3

A

A

B

B

INBD

B

TYPICAL

NOTE:

01 PROTECTIVE SLEEVE INSTALLATION

C

C

C

20.0 mm

(0.79 in)

20.0 mm

150.0 mm (0.79 in)

(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

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@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:

01 PROTECTIVE SLEEVE INSTALLATION

43 C

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 /1M 620VB /1S

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 /1M 620VB /1S

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

RIB2 RIB3

B

B

INBD

B

TYPICAL

NOTE:

01 PROTECTIVE SLEEVE INSTALLATION

C

C

C

20.0 mm

(0.79 in)

20.0 mm

150.0 mm (0.79 in)

(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:

01 PROTECTIVE SLEEVE INSTALLATION

43 C

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 /1M 620VB /1S

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

612VB /2M D

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

RIB2 RIB3

INBD

B

20.0 mm

(0.79 in)

TYPICAL

NOTE:

01 PROTECTIVE SLEEVE INSTALLATION

C

01

20 OR 21

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

OR BEFORE

(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

OR AFTER

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:

01 PROTECTIVE SLEEVE INSTALLATION

C

01

20 OR 21

RIB3 RIB2

C C

INBD

B_SB_242105_6_DDAA_02_01

A

A

B

OR B

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)

(70) (73)

(72)

(78)

29

21

616VB /2S

624VB /2S

642VB /2S

612VB /2M

614VB /2M

622VB /2M

612VB /2MG

612VB /2MG

OR AFTER

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

31

19

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:

01 INSTALL PLACARD AND CABLE TIE, ITEM , IN A GOOD 100

VISIBLE POSITION

02

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

40

32

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:

01 INSTALL PLACARD AND CABLE TIE, ITEM , IN A GOOD 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:

01 INSTALL PLACARD AND CABLE TIE, ITEM , IN A GOOD 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

RIB28A BEFORE 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

RIB28A AFTER 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:

01 INSTALL PLACARD AND CABLE TIE, ITEM , IN A GOOD 100

VISIBLE POSITION

02

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