SB_28_2140_04

@ A310SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

6 DATE : Dec 03/99 SERVICE BULLETIN No. : A310—28—2140

REVISION No. : 04 — Mar 31/04 Page : 1 of 3

Printed in FRANCE © AIRBUS, 2004 All rights reserved

AIRBUSCUSTOMER SERVICES DIRECTORATE1 Rond Point Maurice Bellonte31707 BLAGNAC CEDEX FRANCETel : (33) 5 61 93 33 33Telex : AIRBU 530526FFax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORYATA SYSTEM : 28

TITLE : FUEL - WING ELECTRIC/ELECTRONIC COMMON INSTALLATION - REROUTE THE WIREHARNESS 636VB IN THE RH WING

MODIFICATION No. : 12173D21810

This page transmits Revision No. 04 of Service Bulletin No. A310-28-2140.

ADDITIONAL WORK

If this Service Bulletin has been accomplished before Revision 02, it isnecessary to do the additional work as described in this Service Bulletin.

REASON

This Revision has been issued to :

— advise operators that this Service Bulletin has been rendered mandatory byAirworthiness Directive (AD) No. F-2004-005 and remove aircraft MSNs 0285,0340, 0433, 0435 and 0440 from the effectivity.

CHANGES

SUMMARY

— REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

Mandatory sentence added.

— EVALUATION TABLE

Compliance changed from Recommended to Mandatory and AD No. F-2004-005added.

PLANNING INFORMATION

— EFFECTIVITY

Aircraft MSNs 0285, 0340, 0433, 0435 and 0440 removed from theeffectivity.

— REASON



DATE : Dec 03/99 SERVICE BULLETIN No. : A310—28—2140

REVISION No. : 04 — Mar 31/04 Page :


. History

Mandatory sentence added.

— COMPLIANCE

. Classification

Changed from Recommended to Mandatory.

. Accomplishment Timescale

Mandatory sentence with Airworthiness Directive (AD)) No. F-2004-005added.

— REFERENCES

Electrical Standard Practices Manual (ESPM) 20-55-00 added.

Airworthiness Directive (AD)) No. F-2004-005 added.

MATERIAL INFORMATION

— INDUSTRY SUPPORT INFORMATION

Sentence added.

ACCOMPLISHMENT INSTRUCTIONS

— GENERAL

CAUTION for protection of wiring added.

NOTE : Layout changes due to computerization of this revision are notidentified.

FILING INSTRUCTIONS

This Service Bulletin has been generated electronically and is reissued as acomplete document. Replace the complete document.

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

HISTORY OF PREVIOUS REVISIONS

Revision 01 was issued to inform the operators that the conduits are to beinstalled in a horizontal and not in a vertical line and one larger conduithas to be installed.

Revision 02 was issued to add additional work for the new routing of theconduit with the wires to 2212VC and to the pylon, and to remove aircraftMSN 0424 and 0528 from the effectivity.

Revision 03 was issued to correct some minor discrepancies and to update theeffectivity.

2






REVISION SEQUENCE

ORIGINAL : Dec 03/99

REVISION No. : 01 — Apr 04/00REVISION No. : 02 — May 24/02REVISION No. : 03 — Nov 21/02REVISION No. : 04 — Mar 31/04

3


SUMMARY





This summary is for information onlyand is not approved for modification of the aircraft




REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

An analysis of the wire routing within the framework of the fuel system safetyprogram has shown that the route 2M has to be rerouted to ensure segregation.

The existing routing of the wire routes 2M and 2S located in one conduit is tobe changed so that each wire route 2M and 2S is in one conduit.

This modification assures the proper segregation of the wire routing for thefuel quantity indication system and the 115V anti-collision white strobe lightsin order to avoid interaction in the case of wire damage.

Accomplishment of this Service Bulletin is mandatory as per the latest issue ofConsigne de Navigabilite (CN) (Airworthiness Directive (AD)) No. F-2004-005.

ADDITIONAL WORK

Revision No. 02 requires additional work which consists in the new routing ofthe conduit with the wires to 2212VC and to the pylon.

NOTE : Operators which are accomplishing this Service Bulletin for the firsttime do not have to do the additional work.

EVALUATION TABLE

COMPLIANCE Mandatory CANCELS INSPECTION SB No

AD F-2004-005 A/C OPERATION AFFECTED No

RELIABILITY AFFECTED No PAX COMFORT AFFECTED No

COST SAVING No ETOPS AFFECTED No


SUMMARY




EFFECTIVITY

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

62Z 82Z A1L AFL AIB AIC AJM AMV ARG AUA AWW BAF BBC BOE CFC CNW CSA DAH DGA DLHEGN F2I FDX G2X G8E GAF HLF I2L ICB IRA IRM IYE JAV KAC KYV KZK LAA LLB MGL MPDMWA P2C PIA PRZ QAF QSC R1T RJA ROT RZO S2A SIA TAP THY TSC UAE UZB

This Service Bulletin has been validated on A310 aircraft MSN 0651 .

CONCURRENT REQUIREMENTS

None

REFERENCES/REPERCUSSIONS

TFU : NoneOEB : NoneAOT : NoneSIL : NoneLIFE LIMIT : NoneLINE MAINTENANCE AFFECTED : NoOTHERS : None

NATURE OF THE WORK

AIRCRAFT : YESEQUIPMENT : NO

HARD : NOSOFT : NOOBRM : NO

MANPOWER

Kit 282140D01R04

Kit 282140B01R00

STRUCTURAL LIFE EXTN No VENDOR SB INVOLVED No

KIT PRICE(USD)D01R04

317 KIT PRICE (USD)B01R00 35

TOTAL MANHOURS 30.00

ELAPSED TIME (HOURS) 17.50

TOTAL MANHOURS 1.00


EVALUATION TABLE

2


SUMMARY




ADDITIONAL WORK

MATERIAL INFORMATION

AIRCRAFT DATA

Kit 282140D01

Sleeves, conduits, clamps, spacer and associated hardware.

Kit 282140B01R00

Bracket

APPENDICES

None



3


SUMMARY




4









This document contains AIRBUS PROPRIETARY INFORMATION and shall at all timesremain the property of AIRBUS; no intellectual property right or licence isgranted by AIRBUS in connection with any information contained in it. It isdelivered on the express condition that the said document and the informationcontained in it shall be treated as confidential, shall not be used for anypurpose other than that for which it is hereby delivered. It shall not bedisclosed in whole or in part to third parties and shall not be duplicated inany manner (except for the purposes of performing the tasks described hereunderand provided that any recipient of such document shall comply with theconditions herein), without AIRBUS prior written consent.

1. PLANNING INFORMATION

A. EFFECTIVITY

(1) Models

310-203 310-204 310-222 310-304 310-308 310-322 310-324 310-325

(2) Aircraft

(a) Effectivity by MSN

This Service Bulletin is applicable to aircraft MSN :

0162 0172 0191 0201 0217 0224 0230 0233 0237 0241 0245 02480251 0254 0257 0260 0264 0267 0273 0276 0278 0281 0283 02880291 0293 0295 0297 0300 0303 0306 0309 0311 0313 0316 03180320 0326 0331 0333 0335 0338-0339 0342-0343 0345-03470349-0350 0352-0353 0355-0357 0359-0360 0362-0364 03670369-0370 0372 0375 0378-0379 0386 0389-0390 0392 0394 03970399-0400 0404 0406-0407 0409-0410 0412-0413 0416 0418-04190421-0422 0425 0427-0432 0434 0436-0437 0439 0441-04490451-0458 0467-0468 0472-0473 0475-0476 0478 0480-05040519-0520 0522-0524 0526-0527 0531 0534-0535 0537-05390541-0542 0544-0545 0547-0552 0562 0564-0565 0567-05680570-0571 0573-0574 0576 0585-0595 0597-0600 0620 0622 0624





0634 0636 0638 0640 0642 0644 0646-0654 0656 0658 0660-06610663 0665 0667 0669 0671-0672 0674 0676 0678 0680 0682 06840686-0687 0689 0691 0693 0695 0697-0698 0700 0702 0704 0706

(b) Effectivity by Operator

The Operator/MSN relationship is provided for information onlyand is correct at the time of issue in accordance with theinformation available to AIRBUS. Any future changes resultingfrom transfer of an aircraft from one operator to another willnot be reflected in this list unless the Service Bulletin isrevised for another reason.

OPERATOR MSN

62Z 0431

82Z 0550

A1L 0648

AFL 0442 0475 0592 0593 0622 0646 0660 0687 0689

AIB 0276 0300 0404 0432 0449 0452 0453 0456 0457 04580467 0492 0674 0676 0682

AIC 0392 0406 0407 0413 0428 0429 0447 0481 0501 05190538 0544 0548 0589 0598 0634 0695

AJM 0686

AMV 0437

ARG 0640

AUA 0624

AWW 0409 0410

BAF 0367 0372

BBC 0594 0650 0698 0700

BOE 0363 0493 0570

CFC 0425 0441 0444 0446 0482

CNW 0311 0320 0419

CSA 0564 0567 0672

DAH 0291 0293

DGA 0418 0421 0422

DLH 0488 0524 0527 0547 0595 0599

EGN 0486 0504

F2I 0551 0638

FDX 0162 0191 0201 0217 0224 0230 0233 0237 0241 02450248 0251 0254 0257 0260 0264 0267 0273 0278 02810283 0288 0297 0303 0313 0316 0318 0326 0331 03330335 0339 0342 0343 0345 0346 0349 0353 0355 03560359 0360 0362 0364 0369 0394 0397 0400 0454 05390542

2





This Service Bulletin has been validated on A310 aircraft MSN0651 .

G2X 0378 0549

G8E 0439

GAF 0434 0484 0498 0499 0503 0522 0523

HLF 0427 0430 0468 0487 0520

I2L 0309 0352

ICB 0502 0552

IRA 0338 0370 0375 0379 0389 0390 0436

IRM 0537 0586

IYE 0535 0568 0702 0704

JAV 0357

KAC 0647 0649 0663

KYV 0172 0386

KZK 0399 0412

LAA 0295 0306

LLB 0562

MGL 0526

MPD 0451 0455 0489 0642

MWA 0652 0671

P2C 0443 0500

PIA 0585 0587 0590 0653 0656 0678 0691

PRZ 0534

QAF 0473

QSC 0620

R1T 0591

RJA 0416 0445 0490 0491 0531 0573 0661

ROT 0636 0644

RZO 0448 0571 0651

S2A 0347 0350

SIA 0654 0665 0669 0680 0684 0693 0697

TAP 0472 0483 0494 0495 0541 0565

THY 0476 0478 0480 0496 0497

TSC 0485 0545 0588 0597 0600 0658

UAE 0667

UZB 0574 0576 0706

OPERATOR MSN

3





(c) Effectivity by MSN and Kit/Configuration

The kits and configurations applicable to these MSNs are givenat the end of this list:0162 0172 0191 0201 0217 0224 0230 0233 0237 0241 0245 02480251 0254 0257 0260 0264 0267 0273 0276 0278 0281 0283 02880291 0293 0295 0297 0300 0303 0306 0309 0311 0313 0316 03180320 0326 0331 0333 0335 0338-0339 0342-0343 0345-03470349-0350 0352-0353 0355-0357 0359-0360 0362-0364 03670369-0370 0372 0375 0378-0379 0386 0389-0390 0392 0394 03970399-0400 0404 0406-0407 0409-0410 0412-0413 0416 0418-04190421-0422 0425 0427-0432 0434 0436-0437 0439 0441-04490451-0458 0467-0468 0472-0473 0475-0476 0478 0480-05040519-0520 0522-0524 0526-0527 0531 0534-0535 0537-05390541-0542 0544-0545 0547-0552 0562 0564-0565 0567-05680570-0571 0573-0574 0576 0585-0595 0597-0600 0620 0622 06240634 0636 0638 0640 0642 0644 0646-0654 0656 0658 0660-06610663 0665 0667 0669 0671-0672 0674 0676 0678 0680 0682 06840686-0687 0689 0691 0693 0695 0697-0698 0700 0702 0704 0706

(3) Spares

None

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

An analysis of the wire routing within the framework of the fuelsystem safety program has shown that the route 2M has to bererouted to ensure segregation.

Accomplishment of this Service Bulletin is mandatory as per thelatest issue of Consigne de Navigabilite (CN) (AirworthinessDirective (AD)) No. F-2004-005.

(2) Objective/Action

The existing routing of the wire routes 2M and 2S located in oneconduit is to be changed so that each wire route 2M and 2S is inone conduit.

ADDITIONAL WORK

KIT No. QTY PER A/C CONFIGURATION

282140D01R04 1 None

282140B01R00 1 None

4





Revision No. 02 requires additional work which consists in the newrouting of the conduit with the wires to 2212VC and to the pylon.

NOTE : Operators which are accomplishing this Service Bulletin forthe first time do not have to do the additional work.

(3) Advantages

Separation of the fuel quantity indication wires and the 115Vanti-collision white strobe light wires in order to avoidinteraction in case of wire damage.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

(1) Kit 282140D01R04

(a) Remove components at the RH wing for new routing of wireroutes 2M and 2S.

(b) Segregate the wires of routes 2M and 2S and put them throughindividual conduits for each route.

(c) Test

(2) Kit 282140B01R00

(a) Replace a bracket.

(3) ADDITIONAL WORK

(a) New routing of the conduit with the wires to 2212VC and to thepylon.

E. COMPLIANCE

(1) Classification

Mandatory

(2) Accomplishment Timescale


ADDITIONAL WORK

5






F. APPROVAL

The technical content of this Service Bulletin has been approved underthe authority of the DGAC Design Organisation Approval No. F.JA.02.

If an aircraft listed in the effectivity has a modification or repairembodied that is not of AIRBUS origin, and which affects the content ofthis Service Bulletin, the operator is responsible for obtainingapproval by its airworthiness authority for any adaptation necessarybefore incorporation of the Service Bulletin.

G. MANPOWER

The manpower estimates given in this Service Bulletin are based on thedirect labor cost to do the work. These estimates assume that the workwill be done by experienced personnel, and may need to be revisedupwards to suit operators' circumstances. The estimates do not includethe time to prepare, plan or inspect the work. Manufacture andprocurement of parts and tools, drying time for paints, sealants, etc.and general administration work are also not included.

Kit 282140D01R04

Kit 282140B01R00

ADDITIONAL WORK

Get Access 2.00

Modification 20.00

Test 6.00

Close-up 2.00



Get Access 0.25

Modification 0.50

Close-up 0.25

TOTAL MANHOURS 1.00


Get Access 2.00

Modification 1.50

Test 6.00

Close-up 2.00

6





H. WEIGHT AND BALANCE

Kit 282140D01R04

Manufacturers Empty Weight : +0.37 kg (+0.83 lb)

Effect on Balance : +9.42 kgm (+68.13 lb.ft)

Kit 282140B01R00

Not changed

I. ELECTRICAL LOAD DATA

Not changed

J. REFERENCES

K. PUBLICATIONS AFFECTED

L. INTERCHANGEABILITY/MIXABILITY

None



Aircraft Maintenance Manual (AMM) : 22-30-00 24-00-00 27-80-0027-81-00 27-86-13 28-25-1228-42-44 30-11-00 33-41-0033-48-00 36-11-00

Elec. Std. Practices Manual (ESPM) : 20-53-20 20-55-00

Aircraft Wiring Manual (AWM) : 27-81-05 27-81-07 28-42-07

Airworthiness Directive (AD) No. : F-2004-005

Consumable Material List CML)

Service Bulletin (SB) : A310-36-2015

Standards Manual (SM) :

Illustrated Parts Catalog (IPC) : 24-92-02

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This Page Intentionally Left Blank

8





2. MATERIAL INFORMATION

A. MATERIAL — PRICE AND AVAILABILITY

(1) Material

Customers with aircraft shown in the effectivity of this ServiceBulletin should send a purchase order to AIRBUS. Quote the numberof this Service Bulletin. The address is :

AIRBUSMATERIEL SUPPORT CENTERP.O. BOX 63026222312 HAMBURGGERMANY

(2) Price and Availability

Kit 282140D01R04

Cost : 321 US Dollars

Availability : 150 calendar days from receipt of order

The Kit availability given above is the standard lead time from thedate of your purchase order. If you require the Kit(s) before thistime, please include a retrofit planning schedule with your orderso that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relationto the economic conditions at the issue date of the ServiceBulletin.

Kit 282140B01R00

Cost : 35 US Dollars

Availability : 150 calendar days from receipt of order

The Kit availability given above is the standard lead time from thedate of your purchase order. If you require the Kit(s) before thistime, please include a retrofit planning schedule with your orderso that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relationto the economic conditions at the issue date of the ServiceBulletin.

B. INDUSTRY SUPPORT INFORMATION

Refer to paragraph 2.A.(2): "Price and Availability".

C. LIST OF COMPONENTS

Kit 282140D01R04

9





Kit 282140B01R00

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find partnumbers for the hardware components in the related kit(s) whichyou can not identify in the LIST OF COMPONENTS of this ServiceBulletin. The SM will give you the correct part number to partnumber relationship.

D. LIST OF MATERIALS — OPERATOR SUPPLIED

(1) Consumable Materials

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP

NSA935401-04 15 EA TIENSA935401-03 10 EA TIE

1 B9229062120400 1 EA SLEEVE2 B9229062120600 3 EA SLEEVE3 B9229062120000 1 EA SLEEVE4 B9229062120800 2 EA SLEEVE5 B9229062120200 1 EA SLEEVE8 NSA935807C10 7 EA CLAMP9 NSA935805-09 1.5 ME CONDUIT10 NSA935805-10 1.5 ME CONDUIT12 NSA935807-16 7 EA CLAMP13 NSA935808-01 4 EA WASHER14 NAS1096-3-23 1 EA SCREW15 NSA5527-03-02D 7 EA SPACER16 NSA5527-03-05D 6 EA SPACER17 NAS1149D0332K 4 EA WASHER18 NAS1291C3M 1 EA NUT20 NSA935807C09 7 EA CLAMP21 NAS1096-3-25 1 EA SCREW23 NSA5527-03-01D 6 EA SPACER25 NAS1096-3-33 5 EA SCREW


30 A5725802500000 1 EA BRACKET (30) A572469560000031 NAS1303-12 2 EA BOLT32 NSA5474-3K7 2 EA NUT

DESCRIPTION REFERENCE TO CMLMAT. No.

QTY PER A/C INST DISP

Special material 05-002 As requiredCorrosion preventive 15-008A As required

10





(2) Components

ADDITIONAL WORK

E. PARTS TO BE RE—IDENTIFIED BY THE OPERATOR

None

F. TOOLING — PRICE AND AVAILABILITY

None

G. SPECIAL TOOLS

None


23 NSA5527-03-01D 1 EA SPACER

11





This Page Intentionally Left Blank

12





3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL

WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND CAUTIONS INCLUDEDIN THE REFERENCED PROCEDURES.

CAUTION : ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICALWIRING IN A SATISFACTORY CONDITION (ELECTRICALLY ANDMECHANICALLY SERVICEABLE).

WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYSKEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEANAS POSSIBLE. TO DO THIS :

— PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC. ASNECESSARY ON ELECTRICAL WIRING AND COMPONENTS.

— REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHERCONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION ANDDAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

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

(1) Preparation

(a) Make sure that the aircraft is electrically grounded, refer toAMM 24-00-00 Page block 301.

(b) Fully extend the slats, refer to AMM 27-80-00 Page block 301.

(c) Open, safety and tag the circuit breakers, refer to AMM27-80-00 Page block 301.

(d) Put access platform(s) in position.

(e) Open the access panels 612AT, 612KB, 612JB, 623AB and 623BB.

(f) Remove the bleed air duct if necessary, refer to AMM 36-11-00Page block 401.

(2) Standard Practices

(a) Refer to the AIRBUS Standards Manual (SM) if you find partnumbers for the hardware components in the related kit(s)which you can not identify in the LIST OF COMPONENTS of thisService Bulletin. The SM will give you the correct part numberto part number relationship.

(b) For material specifications (Mat. No.) given in this ServiceBulletin, refer to the Consumable Material List (CML ).

(c) Install screws and nuts with special material (Mat No. 05-002)

13





.

B. MODIFICATION

(1) Kit 282140D01R04

(a) Removal of components for new routing of routes 2M and 2S

Refer to Figure 1

1 Disconnect the plugs 38VC-A, 40VC-A and 5006VC-A from thereceptacles.

2 Loosen the backshells from the receptacles 38VC, 40VC and5006VC and disconnect these wires :

WIRE NUMBER ROUTE RECEPTACLE TERMINAL

2233-5031 2M 38VC Z

2825-5001 2M 38VC -A

3132-5005 2M 38VC -C

3348-5052 2M 38VC -D

3011-5004 2M 38VC -E

2233-5005 2M 38VC -F

3011-5006 2M 38VC -G

3011-5007 2M 38VC -H

2781-5159 2M 38VC -K

2781-5160 2M 38VC -M

2825-5077 2M 38VC -N

2825-5080 2M 38VC -P

3341-5001 2M 38VC -R

3341-5004 2M 38VC -S

3611-5075R 2S 40VC R

3611-5074B 2S 40VC S

3611-5073R 2S 40VC T

3611-5072B 2S 40VC U

3611-5071R 2S 40VC V

3155-5202 2S 40VC W

3621-5015 2S 40VC X

3621-5014 2S 40VC Z

14





NOTE : The connector 2212VC is only affected if ServiceBulletin A310-36-2015 or modification 7633S8497 isembodied.

NOTE : The list of wires routed in 2S and 2M may includeadditional wires which are not actually installed inthe aircraft. This depends on the differentmodifications embodied in the aircraft.

3 Remove these items as shown in Figure 1 , Sheet 3 , DetailB :

4 Remove these items as shown in Figure 1 , Sheet 4 , DetailC :

5 Remove these items as shown in Figure 1 , Sheet 5 , DetailD :

3611-5076B 2S 40VC -A

2781-5154R 2S 40VC -D

2781-5155B 2S 40VC -E

2781-5156B 2S 40VC -F

2781-5157R 2S 40VC -G

2781-5158Y 2S 40VC -H

2842-5061 2S 40VC -J

2842-5062 2S 40VC -K

2842-5063 2S 40VC -M

2842-5064 2S 40VC -N

2842-5065 2S 40VC -P

2842-5071 2S 5006VC A

2842-5058 2S 5006VC B

2 clamp Item (12) discard1 washer Item (13) discard1 screw Item (14) discard1 spacer Item (15) discard1 spacer Item (16) discard1 washer Item (17) discard1 nut Item (18) discard

2 clamp Item (12) discard1 washer Item (13) discard1 spacer Item (15) discard1 spacer Item (16) discard1 screw Item (21) discard

WIRE NUMBER ROUTE RECEPTACLE TERMINAL

15





6 Temporarily secure the conduit as shown in Figure 1 , Sheet5 , Detail D.

7 Remove these items as shown in Figure 1 , Sheet 6 , DetailE :

8 Remove these items as shown in Figure 1 , Sheet 7 , DetailF :

9 Remove these items as shown in Figure 1 , Sheet 8 , DetailG :

10 Remove these items as shown in Figure 1 , Sheet 1 , DetailH :

11 Install these items as shown in Figure 1 , Sheet 2 , DetailH :

12 Remove the receptacle identification sleeves 38VC, 40VC and5006VC and the protection conduits, item (10), from theelectrical wires of routes 2M and 2S.

4 clamp Item (12) discard2 washer Item (13) discard2 spacer Item (15) discard2 spacer Item (16) discard2 screw Item (21) discard

2 clamp Item (12) discard2 spacer Item (15) discard1 washer Item (17) discard1 screw Item (21) discard

2 clamp Item (12) discard1 washer Item (13) discard1 screw Item (14) discard1 spacer Item (15) discard1 spacer Item (16) discard

2 clamp Item (12) discard1 washer Item (13) discard1 screw Item (14) discard1 spacer Item (15) discard1 spacer Item (16) discard

2 clamp Item (8) retain1 washer Item (105) retain1 screw Item (110) retain

1 clamp Item (8) retained1 washer Item (105) retained1 screw Item (110) retained

16





13 Check the cable harnesses for damage and replace damagedwires as necessary, refer to ESPM 20-53-20.

(2) Kit 282140B01R00

(a) Removal and installation of a bracket

Refer to Figure 2 , Sheet 1

1 Remove these items as shown in the figure :

2 Put in position :

3 Transfer drill the holes and install the bracket, item 30,with these items :

(3) Kit 282140D01R04

(a) New routing of routes 2M and 2S

Refer to Figure 1

1 Install these identification sleeves to the cable harnessesnear the pressure seals 44VP and 52VP as shown in Figure 1, Sheet 2 , Detail A:

2 Cut :

into 3 pieces with the half length as the removed conduitfor new routing of 2S.

3 Cut :

into 3 pieces with the half length as the removed conduitfor new routing of 2M.

1 bracket Item (30) discard2 bolt Item (31) discard2 nut Item (32) discard

1 bracket A5725802500000 Item 30

2 bolt NAS1303-12 Item 312 nut NAS5474-3K7 Item 32

1 sleeve B9229062120600 Item 21 sleeve B9229062120800 Item 4

1 conduit NSA935805-09 Item 9

1 conduit NSA935805-10 Item 10

17





4 Put the wires of routes 2M and 2S through the separateconduits according to the routes, refer to para.3.B.(1)(a)2.

5 Install the conduits, item 9 and item 10, with the wires ofthe routes 2S and 2M and conduit with the wires to 2212VCand to the pylon for the new routing, as shown in Figure 1, Sheet 2 , Detail A.

6 For the wire routing use :

7 Install these items as shown in Figure 1 , Sheet 3 , DetailB :

8 Install these items as shown in Figure 1 , Sheet 4 , DetailC :

9 Install the conduit and these items as shown in Figure 1 ,Sheet 5 , Detail D :

10 cable tie NSA935401-0315 cable tie NSA935401-04

1 clamp NSA935807C10 Item 81 clamp NSA935807-16 Item 121 washer NSA935808-01 Item 131 screw NAS1096-3-23 Item 141 spacer NSA5527-03-02D Item 151 spacer NSA5527-03-05D Item 161 washer NAS1149D0332K Item 171 nut NAS1291C3M Item 181 clamp NSA935807C09 Item 20

1 clamp Item (8) retained

1 clamp NSA935807C10 Item 81 clamp NSA935807-16 Item 121 washer NSA935808-01 Item 131 spacer NSA5527-03-02D Item 151 clamp NSA935807C09 Item 202 spacer NSA5527-03-01D Item 231 screw NAS1096-3-33 Item 25

2 clamp NSA935807C10 Item 82 clamp NSA935807-16 Item 122 spacer NSA5527-03-02D Item 152 spacer NSA5527-03-05D Item 162 washer NAS1149D0332K Item 172 clamps NSA935807C09 Item 202 spacer NSA5527-03-01D Item 232 screw NAS1096-3-33 Item 25

18





10 Install these items as shown in Figure 1 , Sheet 6 , DetailE:

11 Install these items as shown in Figure 1 , Sheet 7 , DetailF :

12 Install these items as shown in Figure 1 , Sheet 8 , DetailG :

13 Install these identification sleeves to the cable harnessesnear the receptacles 38VC, 40VC and 5006VC as shown inFigure 1 , Sheet 2 , Detail A :

14 Connect the wires as shown in the connection table, referto para. 3.B.(1)(a)2.

15 Connect the plugs 38VC-A, 40VC-A and 5006VC-A to thereceptacles 38VC, 40VC and 5006VC.

16 For aircraft equipped with SB A310-36-2015 or modification7633S8497, connect the receptacle 2212VC.

1 clamp NSA935807C10 Item 81 clamp NSA935807-16 Item 121 spacer NSA5527-03-02D Item 151 spacer NSA5527-03-05D Item 161 washer NAS1149D0332K Item 171 clamp NSA935807C09 Item 201 spacer NSA5527-03-01D Item 231 screw NAS1096-3-33 Item 25

1 clamp NSA935807C10 Item 81 clamp NSA935807-16 Item 121 washer NSA935808-01 Item 131 spacer NSA5527-03-02D Item 151 spacer NSA5527-03-05D Item 161 clamp NSA935807C09 Item 201 spacer NSA5527-03-01D Item 231 screw NAS1096-3-33 Item 25

1 clamp NSA935807C10 Item 81 clamp NSA935807-16 Item 121 washer NSA935808-01 Item 131 spacer NSA5527-03-02D Item 151 spacer NSA5527-03-05D Item 161 clamp NSA935807C09 Item 201 screw NAS1096-3-25 Item 21

1 sleeve B9229062120400 Item 12 sleeve B9229062120600 Item 21 sleeve B9229062120000 Item 31 sleeve B9229062120800 Item 41 sleeve B9229062120200 Item 5

19





17 Apply corrosion preventive (Mat No. 15-008A) to themodified area.

(4) ADDITIONAL WORK

(a) Removal of components for new routing of the wires to 2212VCand to the pylon

Refer to Figure 3

1 Remove these items as shown in Figure 3 , Sheet 2 , DetailB :

2 Remove the conduit with the wires to 2212 VC and to thepylon

3 Install these items as shown in Figure 3 , Sheet 2 , DetailB :

4 Remove these items as shown in Figure 3 , Sheet 3 , DetailC :

(b) New routing of the wires to 2212VC and to the pylon

Refer to Figure 3 , Sheet 3

1 Install the conduit with the wires to 2212 VC and to thepylon with these items as shown in Figure 3 , Sheet 3 ,Detail C :

2 clamp Item (8) retain1 washer Item (105) retain1 screw Item (110) retain

1 clamp Item (8) retained1 washer Item (105) retained1 screw Item (110) retained

1 clamp Item (8) retain1 clamp Item (12) retain1 washer Item (13) retain1 spacer Item (15) retain1 spacer Item (16) discard1 clamp Item (20) retain1 spacer Item (23) retain1 screw Item (25) retain

2 clamp Item (8) retained1 clamp Item (12) retained1 washer Item (13) retained1 spacer Item (15) retained1 clamp Item (20) retained1 spacer Item (23) retained1 screw Item (25) retained

20





2 Connect the wires as shown in the connection table, referto para. 3.B.(1)(a)2.

3 Connect the plugs 38VC-A, 40VC-A and 5006VC-A to thereceptacles 38VC, 40VC and 5006VC.

4 For aircraft equipped with SB A310-36-2015 or modification7633S8497, connect the receptacle 2212VC.

5 Apply corrosion preventive (Mat No. 15-008A) to themodified area.

C. TEST

(1) De-energize the aircraft electrical network.

(2) Do a continuity test between the connectors 32CV-B and 40VC, referto AWM 27-81-05.

(3) Do a continuity test between the connectors 36CV-B and 38VC, referto AWM 27-81-07.

(4) Do a continuity test between the connectors 10QT-A and 5006VC,refer to AWM 28-42-07.

(5) Do an operational test of the autothrottle, refer to AMM 22-30-00Page block 501.

(6) Do an operational test of the mechanical and electrical control ofthe slats, refer to AMM 27-81-00 Page block 501.

(7) Do an operational test of the wing tip brake, refer to AMM 27-86-13Page block 501.

(8) Do an operational test of the refuel/defuel valve, refer to AMM28-25-12 Page block 401.

(9) Do an operational test of the cadensicon sensor, refer to AMM28-42-44 Page block 401.

(10) Do an operational test of the wing ice protection, refer to AMM30-11-00 Page block 501.

(11) Do an operational test of the navigation lights, refer to AMM33-41-00 Page block 501.

(12) Do an operational test of the anti-collision lights, refer to AMM33-48-00 Page block 501.

(13) Install the bleed air duct if removed, refer to AMM 36-11-00 Pageblock 401.

1 spacer NSA5527-03-01D Item 23

21





(14) Do a pneumatic test, refer to AMM 36-11-00 Page block 501.

(15) Do a bite test, refer to AMM 36-11-00 Page block 501.

D. CLOSE UP

(1) Make sure that the work areas are clean and clear of tools andother items of equipment.

(2) Fully retract the slats, refer to AMM 27-80-00 Page block 301.

(3) Close the access panels 612AT, 612KB, 612JB, 623AB and 623BB.

(4) Remove the access platform.

E. DOCUMENTATION

Write in the applicable aircraft records that you have done all the workgiven in this Service Bulletin.

22





Figure 1 Sheet 1New Routing of Routes 2M and 2S

23






24






25






26






27






28






29






30





Figure 2 Sheet 1Replacement of a Bracket

31





Figure 3 Sheet 1New Routing of the Conduit with the Wires to 2212VC and to the Pylon

32






33






34

@ A310SERVICE BULLETINREPORTING SHEET






Please complete the appropriate item (A or B):

A - SB WILL BE embodied . . . . . . . . . . . . . YES/NO (if NO please comment)If YES, aircraft concerned (as per SB effectivity by default) and planned dates(month/year) of embodiment: . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

B - SB HAS BEEN embodied on aircraft: . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Operator comments: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

From Airline: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Name/Title: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Signature: . . . . . . . . . . . . . . Date: . . . . . . . . . . . . .

If operational documentation is affected (see Paragraph 1.K of this SB): Ifinformation is needed prior to next normal revision or prior to SB embodiment,please indicate required service(s):Either: Advance Data . . . . . . . . . . . . . . . . . . . . . YES/NOOr : Intermediate/Temporary revision. . . . . . . . . . . . YES/NO

Important Information: This SB will only be incorporated in your maintenance andoperational documentation if this sheet is returned to Airbus and signed by aduly authorised representative. With the next feasible revision, this willresult in

- updating of maintenance documentation to show pre and post SB data.- updating of maintenance and operational documentation to show post SB dataafter embodiment.

If this SB requires previous or simultaneous accomplishment of other SBs,Airbus shall automatically include them in the manual revisions. Refer to SIL00-037 for detailed information.

Please return this completed sheet to:

AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE

Attn: SDC32 Technical Data and Documentation Services FAX: (+33) 5 61 93 28 06 or via your Resident Customer Support Office.

Alternatively, SB lists via letters or fax are also accepted.


QUALITY PERCEPTION FORM




Use this form to tell us what is your perception of the quality of this ServiceBulletin. The reported data that you provide us will be used to analyse areas ofdifficulties and to take corrective action to further improve the quality of ourService Bulletins.We thank you for the time you have taken in completing this form.

(Please rate on a scale of 1 to 4, with 4 being the highest score)

- Quality rating of this SB 4 3 2 1

- Quality rating of the Accomplishment Instructions 4 3 2 1

- Quality rating of the Illustrations 4 3 2 1

- Is this SB easy to understand ? Y / N

If you have had difficulties in the accomplishment of this SB please quote belowthe area(s) and give a short description of the issue.

Planning Material Instructions

X Effectivity X Kit content X PreparationX Reason X List of Materials X Mod/InspectionX Manpower Operator Supplied X TestX References X Re-identification X Close-UpX Publication X Tooling X Illustrations

Comments :

Operator : Date:

Name/Title :

Please return this form to :

AIRBUSCUSTOMER SERVICES DIRECTORATE1 Rond Point Maurice Bellonte31707 BLAGNACAttn : SET1 Service Bulletins ManagementFAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

SB_28_2140_04

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