@A300-600

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: 28

TITLE: FUEL - TANK LEVEL SENSING - NEW OUTER TANK SENSOR

HARNESS INSTALLATION

MODIFICATION No.: 13671H5745

This page transmits Revision No.01 of Service Bulletin No.A300-28-6109

ADDITIONAL WORK

**CONF ALL

No additional work is required by this revision for aircraft modified by any previous issue.

REASON

Revision No. 01 issued to:

- update CML references

- update effectivity

- amend flowchart to include outer tank harness FINs

CHANGES

NOTE: Revision bars against references not identified in the CHANGES paragraph appear due

to format changes introduced by new authorities’ rules.

SUMMARY

REASON/DESCRIPTION/OPERATIONAL

CONSEQUENCES

REASON UPDATED R

EFFECTIVITY OPERATOR LIST UPDATED R

PLANNING INFORMATION

EFFECTIVITY EFFECTIVITY RELATED INFORMATION

UPDATED

R

Configuration definition

CONF 001 CONFIGURATION DEFINITION UPDATED R

Material Effectivity MATERIAL EFFECTIVITY ADDED N

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-6109

REVISION No.: 01 - Dec 20/13 Page: 1

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

MATERIAL EFFECTIVITY DELETED FOR

APPLICABLE MSN

D

REASON

History HISTORY UPDATED R

Objective/Action OBJECTIVE/ACTION UPDATED R

COMPLIANCE

Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED R

MANPOWER MANPOWER UPDATED R

MANPOWER UPDATED

CONFIGURATION UPDATED

R

REFERENCES REFERENCED DOCUMENTATION UPDATED R

MATERIAL INFORMATION

MATERIAL - PRICE AND AVAILABILITY

Procurement Addresses PROCUREMENT ADDRESSES UPDATED R

LIST OF MATERIALS - OPERATOR

SUPPLIED

Consumable Materials

Consumable CMLB01 CONSUMABLE MATERIAL SET UPDATED

CONSUMABLE UPDATED

R

Components

Component COMPB01 PART MATERIAL SET UPDATED

NOTE UPDATED

R

ACCOMPLISHMENT INSTRUCTIONS

TASK 286109- 831-895-001-

MODIFICATION

TASK SOLUTION UPDATED

NOTE UPDATED

R

Subtask 286109-910-401-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

R

Subtask 286109-941-401-001 SUBTASK SOLUTION UPDATED R

Subtask 286109-832-401-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

R

Subtask 286109-833-401-001 SUBTASK SOLUTION UPDATED

NOTE UPDATED

CONSUMABLE UPDATED

WARNING UPDATED

MATERIAL LIST UPDATED

R

Subtask 286109-831-401-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

REFERENCED DOCUMENTATION UPDATED

MATERIAL LIST UPDATED

R

Subtask 286109-760-401-001 SUBTASK SOLUTION UPDATED R

Subtask 286109-710-401-001 SUBTASK SOLUTION UPDATED R

Subtask 286109-942-401-001 SUBTASK SOLUTION UPDATED R

Fig. A-UDAAA

Fig. A-UDAAA Sheet 01 SHEET UPDATED R

Fig. A-UFBAA

Fig. A-UFBAA Sheet 01 SHEET UPDATED R

Fig. A-UFBAA Sheet 02 SHEET UPDATED R

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-6109

REVISION No.: 01 - Dec 20/13 Page: 2

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

APPENDIX 01: Elapsed Time Assumption

Fig. A-UAAAA

Fig. A-UAAAA Sheet 01 SHEET UPDATED R

FILLING INSTRUCTIONS

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

Replace the complete document.

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

HISTORY OF PREVIOUS REVISIONS

No previous revision

REVISION SEQUENCE

ORIGINAL: Mar 05/13

REVISION No. : 01 - Dec 20/13

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-6109

REVISION No.: 01 - Dec 20/13 Page: 3

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REVISION TRANSMITTAL SHEET

This Page Intentionally Left Blank

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-6109

REVISION No.: 01 - Dec 20/13 Page: 4

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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: 28

TITLE: FUEL - TANK LEVEL SENSING - NEW OUTER TANK SENSOR

HARNESS INSTALLATION

**CONF ALL

MODIFICATIONS

MODIFICATION CLASSIFICATION

MAJOR 13671H5745

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

During maintenance work on a number of A300-600 aircraft, damage to the surge tank overflow sensor

harness has been reported, approximately 30.0 cm (12.0 in.) inboard of the overflow sensor RIB 27.

Investigations have shown that the damage has been caused by contact of the harness against the

Magnetic Fuel Level Indicator (MFLI) canister. The cause of the contact is due to incorrect installation of

the harness. As the MFLI is integral to the access panel in this location any potential contact is hidden.

Harness chafing against the MFLI has previously been seen in this location. Modification 04489 was

introduced in production to improve the harness installation and prevent contact of the harness with the

MFLI. As part of SFAR88 activities embodiment of the Modification 04489 was required by embodiment

of mandatory Modification Service Bulletin A300-28-6020.

The configuration of the Post-Mod 04489 installation is considered to be subject to human error, given

the subsequent in-service findings leading to variability of installation and potentially resulting in contact

with the MFLI canister.

To avoid the possibility of incorrect harness installation, the angle brackets attached to stringer 15

between RIBS 26 and 27 are to be replaced by new brackets to provide adequate clearance of the

cable from the MFLI canister. The new brackets contain error-proofing measures that ensure consistent

installation.

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-6109

REVISION No.: 01 - Dec 20/13 Page: 1

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SERVICE BULLETIN

SUMMARY

Prior to modification, if a harness is found to be damaged during inspection, depending upon the nature

and extent of the damage a repair is available within this Service Bulletin Damage that falls outside the

limits identified in this Service Bulletin will require specific repair instructions from Airbus.

Accomplishment of this Service Bulletin will ensure that the fuel level sensor harness is correctly routed

and that adequate clearance to the MFLI canister can be maintained.

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO

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

DEFUEL / VENTILATION YES

NOTE (1): Service Bulletin must be accomplished.

MATERIAL PRICE INFORMATION

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Component COMPB01 1 See SB Bracket, Rivet, Nut, P-Clip, Sleeve

EFFECTIVITY

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

ABD ABR AHK BCS CES F2I FDX GBG I2L IRA IRM KAC KAL

MGC MNB MON MSR MXU OHY QTR SUD TAR THA TMA UPS URS

UZB

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 YES

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-6109

REVISION No.: 01 - Dec 20/13 Page: 2

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@A300-600

SERVICE BULLETIN

SUMMARY

HARD NO

SOFT NO

OBRM NO

MANPOWER

Task 286109-831-895-001: MODIFICATION

TOTAL MANHOURS 15.00

ELAPSED TIME (HOURS) 7.50

APPENDICES

APPENDIX 01: Elapsed Time Assumption

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-6109

REVISION No.: 01 - Dec 20/13 Page: 3

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@A300-600

SERVICE BULLETIN

SUMMARY

**CONF ALL

B

THIS DOES NOT AFFECT THE MODIFICATION.

NOTE:

01 ON SOME AIRCRAFT THIS P−CLIP HAS NOT BEEN INSTALLED,

STGR15

TYPICAL

P CLIP INSTALLATION

B

B

STGR15

MFLI SUPPORT

CANISTER (REF)

RIB 27

DATUM

RIB 26

DATUM

F

W

D

ON NEW BRACKET

A

01

VIEW OF LH WING SHOWN

RH WING SIMILAR

RIB26 RIB27

A

INBD

PLAN VIEW

FWD

D_SB_286109_7_SBAA_01_00

Figure A-USBAA - Sheet 01

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-6109

REVISION No.: 01 - Dec 20/13 Page: 4

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Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

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: 28

TITLE: FUEL - TANK LEVEL SENSING - NEW OUTER TANK SENSOR

HARNESS INSTALLATION

MODIFICATION No.: 13671H5745

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

(1) Models

B4-603 B4-605R B4-620 B4-622 B4-622R C4-605R/FC4-620 F4-605R

F4-622R

(2) Effectivity by MSN

0294 0344 0358 0361 0365 0380 0388 0401 0405 0408 0411 0414 0417 0464 0477

0479 0505 0518 0521 0525 0529-0530 0532 0536 0543 0546 0553-0561 0563 0572

0575 0577 0579 0581 0584 0602-0605 0607-0608 0611 0613-0614 0617-0618 0621

0623 0625-0626 0629-0633 0637 0641 0643 0657 0659 0662 0664 0666 0668 0670

0673 0677 0679 0681 0683 0688 0694 0696 0699 0701 0703 0705 0707 0709 0711

0713 0715 0717 0719 0721-0730 0732-0746 0748-0750 0752-0764 0766-0775

0777-0794 0797 0799-0840 0845-0878

(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.

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-6109

REVISION No.: 01 - Dec 20/13 Page: 1

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@A300-600

SERVICE BULLETIN

OPERATOR MSN

ABD 0529 0557

ABR 0683 0770

AHK 0855 0856 0857 0858 0859 0860 0870 0871

BCS 0602 0617 0621 0637 0641 0670 0679 0703 0711 0724 0729 0730

0737 0740 0753 0783

CES 0532 0707 0725 0732 0741 0746 0754 0763

F2I 0294 0518

FDX 0358 0361 0365 0388 0417 0477 0479 0530 0536 0543 0555 0559

0572 0575 0579 0581 0611 0613 0625 0630 0633 0657 0659 0664

0668 0688 0709 0713 0715 0726 0728 0735 0736 0738 0742 0745

0748 0752 0757 0759 0760 0761 0766 0768 0769 0771 0772 0774

0777 0778 0779 0780 0781 0789 0790 0791 0792 0793 0794 0799

0800 0801 0802 0803 0804 0873 0874 0875 0876 0877 0878

GBG 0626 0643

I2L 0677

IRA 0632 0696 0723 0727

IRM 0380 0401 0405 0408 0411 0414 0546 0553 0608 0618 0623 0701

0750 0762 0773 0838

KAC 0344 0673 0694 0699 0719 0721

KAL 0631 0662

MGC 0743

MNB 0521 0525 0734 0739 0755 0756 0758

MON 0556 0604 0605

MSR 0561 0607

MXU 0767 0788 0797 0836 0837

OHY 0584 0603 0744 0749 0764

QTR 0554 0560 0614

SUD 0666 0775

TAR 0505 0558 0563

THA 0464 0577 0629 0681 0705 0782 0784 0785 0786 0787

TMA 0872

UPS 0805 0806 0807 0808 0809 0810 0811 0812 0813 0814 0815 0816

0817 0818 0819 0820 0821 0822 0823 0824 0825 0826 0827 0828

0829 0830 0831 0832 0833 0834 0835 0839 0840 0845 0846 0847

0848 0849 0850 0851 0852 0853 0854 0861 0862 0863 0864 0865

0866 0867 0868 0869

URS 0733

UZB 0717 0722

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-6109

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SERVICE BULLETIN

(4) Configuration by MSN

MSN CONFIGURATION

0294 0344 0358 0361 0365 0380 0388 0401 0405 0408 0411

0414 0417 0464 0477 0479 0505 0518 0521 0525 0529 0530

0532 0536 0543 0546 0553 0554 0555 0556 0557 0558 0559

0560 0561 0563 0572 0575 0577 0579 0581 0584 0602 0603

0604 0605 0607 0608 0611 0613 0614 0617 0618 0621 0623

0625 0626 0629 0630 0631 0632 0633 0637 0641 0643 0657

0659 0662 0664 0666 0668 0670 0673 0677 0679 0681 0683

0688 0694 0696 0699 0701 0703 0705 0707 0709 0711 0713

0715 0717 0719 0721 0722 0723 0724 0725 0726 0727 0728

0729 0730 0732 0733 0734 0735 0736 0737 0738 0739 0740

0741 0742 0743 0744 0745 0746 0748 0749 0750 0752 0753

0754 0755 0756 0757 0758 0759 0760 0761 0762 0763 0764

0766 0767 0768 0769 0770 0771 0772 0773 0774 0775 0777

0778 0779 0780 0781 0782 0783 0784 0785 0786 0787 0788

0789 0790 0791 0792 0793 0794 0797 0799 0800 0801 0802

0803 0804 0805 0806 0807 0808 0809 0810 0811 0812 0813

0814 0815 0816 0817 0818 0819 0820 0821 0822 0823 0824

0825 0826 0827 0828 0829 0830 0831 0832 0833 0834 0835

0836 0837 0838 0839 0840 0845 0846 0847 0848 0849 0850

0851 0852 0853 0854 0855 0856 0857 0858 0859 0860 0861

0862 0863 0864 0865 0866 0867 0868 0869 0870 0871 0872

0873 0874 0875 0876 0877 0878

001

(5) Configuration definition

**CONF 001

Config. 001 is valid for all the aircraft given in the effectivity of this Service Bulletin as a

standard configuration.

(6) Material Effectivity

MATERIAL QTY PER A/C SEE NOTES

Component COMPB01 1

Consumable CMLB01 1

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

During maintenance work on a number of A300-600 aircraft, damage to the surge tank

overflow sensor harness has been reported, approximately 30.0 cm (12.0 in.) inboard of

the overflow sensor RIB 27. Investigations have shown that the damage has been

caused by contact of the harness against the Magnetic Fuel Level Indicator (MFLI)

canister. The cause of the contact is due to incorrect installation of the harness. As the

MFLI is integral to the access panel in this location any potential contact is hidden.

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-6109

REVISION No.: 01 - Dec 20/13 Page: 3

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@A300-600

SERVICE BULLETIN

Harness chafing against the MFLI has previously been seen in this location. Modification

04489 was introduced in production to improve the harness installation and prevent

contact of the harness with the MFLI. As part of SFAR88 activities embodiment of the

Modification 04489 was required by embodiment of mandatory Modification Service

Bulletin A300-28-6020.

The configuration of the Post-Mod 04489 installation is considered to be subject to

human error, given the subsequent in-service findings leading to variability of installation

and potentially resulting in contact with the MFLI canister.

(2) Objective/Action

To avoid the possibility of incorrect harness installation, the angle brackets attached to

stringer 15 between RIBS 26 and 27 are to be replaced by new brackets to provide

adequate clearance of the cable from the MFLI canister. The new brackets contain errorproofing measures that ensure consistent installation.

Prior to modification, if a harness is found to be damaged during inspection, depending

upon the nature and extent of the damage a repair is available within this Service

Bulletin Damage that falls outside the limits identified in this Service Bulletin will require

specific repair instructions from Airbus.

(3) Advantages

Accomplishment of this Service Bulletin will ensure that the fuel level sensor harness is

correctly routed and that adequate clearance to the MFLI canister can be maintained.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

Task 286109-831-895-001: MODIFICATION

(1) Inspect the Sensor Harness for Damage

(2) Repair of Damage to the Sensor Harness

(3) Install New Brackets and Re-Route the Sensor Harness

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.

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-6109

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SERVICE BULLETIN

F. APPROVAL

The technical content of this document is approved under the authority of Design

Organization 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.

Task 286109-831-895-001: MODIFICATION

Get Access 2.00

On Aircraft

Inspect the Sensor Harness for Damage 1.00

Repair of Damage to the Sensor Harness 2.00

Install New Brackets and Re-Route the Sensor

Harness

6.00

Tests 2.00

Close-Up 2.00

TOTAL MANHOURS 15.00

ELAPSED TIME (HOURS) 7.50

NOTE: For an explanation of the manhours and elapsed time, refer to the Gantt

Chart, Fig. A-UAAAA, given in, APPENDIX 01: Elapsed Time Assumption .

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

Aircraft Maintenance Manual (AMM) 06-21-00 06-31-53 06-41-00

20-21-12 24-00-00 28-10-00

28-11-22 28-43-21 28-46-00

Aircraft Schematic Manual (ASM) 28-46-00

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-25-31 20-25-41 20-33-00

20-52-21 20-55-00

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-6109

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SERVICE BULLETIN

Process and Material Specification (PMS) Process and Material Specification

(PMS) 01-06-12

Standards Manual (SM)

Structural Repair Manual (SRM) 51-26-10 51-40-12 51-40-20

51-40-21 51-40-40 51-75-10

51-76-20

K. PUBLICATION AFFECTED

Illustrated Parts Catalog (IPC) 28-22-18 28-46-11

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-6109

REVISION No.: 01 - Dec 20/13 Page: 6

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2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

AIRBUS Material, Logistics and Suppliers do not stock standard hardware as competitive

multiple suppliers ensure access to minimum prices AIRBUS recommends Customers

with aircraft shown in the effectivity of this Service Bulletin to send a purchase order to

B/E Aerospace. The address is:

Component COMPB01 B/E AEROSPACE INC

CONSUMABLES MANAGEMENT

10000 NW 15th Terrace Miami

FL 3317

US

Tel EMEA: +49 (0) 40 822 285 31500

Tel US: +1 305 925 2600

Tel ASIA: +1 310 900 1300

Fax EMEA: +49 (0) 40 822 285 31010

Fax US: +1 305 507 7191

Fax ASIA: +1 310 819 1200

SITA: MIAMMCR

E-Mail: AOGdesk_CMG@beaerospace.com

Internet: http://www.beconsumables.com

or, alternatively any other source on the open

market.

(2) Price and Availability

No AIRBUS kit will be provided.

Operator supplied standard hardware parts required to accomplish this Service Bulletin

are to be supplied from the Operator’s stock.

B. INDUSTRY SUPPORT INFORMATION

AIRBUS will not provide industry support for accomplishment of this Service Bulletin.

C. LIST OF COMPONENTS

No Kit

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-6109

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D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Anti-Corrosion Primer 04DAB2 As required

Corrosion Sealant 06AAC1 As required

Polysulfide Sealant 06ABB1 As required

Solvent 08BAA9 As required

Conversion Coating 10ABC1 As required

(2) Components

Component COMPB01

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

NOTES

1 NSA5516-02NF 4 CLIP

2 A28450078200 4 BRACKET

3 MS21071L3 4 NUT

4 NAS1303-3 4 BOLT

5 NSA5474-3K7 4 NUT

6 MS20426AD3 8 RIVET

7 NAS1303-2 4 BOLT

NSA937201MH 0.4 (M) SLEEVE (1)

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.

NOTE (1): If sleeve Part Number NSA937201MH is not available, use an equivalent

heat-shrink sleeve that can be used inside fuel tanks, e.g. ASNE0126.

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

(1) Tooling - Price and Availability

None

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-6109

REVISION No.: 01 - Dec 20/13 Page: 8

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@A300-600

SERVICE BULLETIN

(2) Tools

To accomplish this Service Bulletin it will be necessary to use the tools listed in AMM

28-43-21, Page Block 401.

(3) Special Tools

None

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-6109

REVISION No.: 01 - Dec 20/13 Page: 9

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This Page Intentionally Left Blank

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-6109

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SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

Task 286109-831-895-001 - MODIFICATION

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

INCLUDED IN THE REFERENCED PROCEDURES.

WARNING: MAKE SURE THAT THE SAFETY DEVICES AND THE WARNING NOTICES ARE

IN POSITION BEFORE YOU START A TASK ON OR NEAR:

- THE FLIGHT CONTROLS

- THE FLIGHT CONTROL SURFACES

- THE LANDING GEAR AND THE RELATED DOORS

- COMPONENTS THAT MOVE.

MOVEMENTS OF COMPONENTS CAN KILL OR INJURE PERSONS.

WARNING: MAKE SURE THAT THE GROUND SAFETY LOCKS ARE CORRECTLY

INSTALLED ON THE LANDING GEAR. THIS PREVENTS UNWANTED

MOVEMENT OF THE LANDING GEAR.

WARNING: THIS PROCEDURE USES A FUEL SYSTEM ITEM THAT IS IN A CATEGORY

KNOWN AS A CRITICAL DESIGN CONFIGURATION CONTROL LIMITATION

(CDCCL) CDCCL IDENTIFIES AN ITEM THAT CAN BE THE SOURCE OF A

POSSIBLE FUEL TANK IGNITION. YOU MUST KEEP ALL CDCCL ITEMS IN

THE APPROVED CONFIGURATION. DAMAGE, WEAR OR CHANGES TO A

CDCCL ITEM CAN CAUSE A POSSIBLE FUEL TANK EXPLOSION.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

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

THIS:

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

NECESSARY ON WIRING AND COMPONENTS

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

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,

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-6109

REVISION No.: 01 - Dec 20/13 Page: 11

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SERVICE BULLETIN

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.

Task Associated Data

Zone

550 650

Access

Panel 550PB 550QB 650PB 650QB

Manpower

TOTAL MANHOURS 15.00

ELAPSED TIME (HOURS) 7.50

A. GENERAL

NOTE: The purpose of flow charts is to supplement the information given in the

Procedure and Compliance paragraphs and not to serve as the primary

source for tasks or compliance times given in this Service Bulletin.

(1) Subtask 286109-910-401-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001

06-31-53, Page Block 001

06-41-00, Page Block 001

20-21-12, Page Block 001

Consumable Material List (CML)

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

20-52-21

Process and Material Specification

(PMS)

Process and Material Specification (PMS)

01-06-12

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-6109

REVISION No.: 01 - Dec 20/13 Page: 12

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@A300-600

SERVICE BULLETIN

References

Structural Repair Manual (SRM) 51-26-10

51-40-21

51-40-40

51-75-10

51-76-20

(a) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to

Consumable Materials List (CML).

(b) For the Frame (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 access panels, refer to AMM 06-41-00, Page Block 001.

(e) To torque tighten electrical component fasteners, refer to AMM 20-21-12, Page

Block 001.

(f) To torque tighten the standard threaded fasteners, refer to AMM 20-21-12, Page

Block 001.

(g) Remove and install fasteners in accordance with SRM 51-40-21.

(h) Obtain fastener hole diameters and drill and ’deburr’ data in accordance with SRM

51-40-40.

(i) Apply sealant in accordance with SRM 51-76-20.

(j) Renew the protective finish in accordance with SRM 51-75-10.

(k) Obtain bending data in accordance with SRM 51-26-10.

(l) Obey the instructions for the general installation of electrical wire harnesses, refer

to ESPM 20-33-00.

(m) Do a continuity test of the new and modified wires, refer to ESPM 20-52-21.

(n) Tag all the parts you must remove and retain to make subsequent installation

easier.

(o) Put all the retained hardware in identified plastic bags and attach the bags to the

related unit.

(p) For part marking, refer to PMS 01-06-12.

(2) Subtask 286109-839-401-001 - 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 05/13 SERVICE BULLETIN No.: A300-28-6109

REVISION No.: 01 - Dec 20/13 Page: 13

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B. PREPARATION

(1) Subtask 286109-941-401-001 - Job Set-up

Work Zones and Access Panels

Zone Access/Work location

550 Access Panel 550PB

Work location from Rib 25 to Rib 26

550 Access Panel 550QB

Work location from Rib 26 to Rib 27

650 Access Panel 650PB

Work location from Rib 25 to Rib 26

650 Access Panel 650QB

Work location from Rib 26 to Rib 27

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301

28-10-00, Page Block 301

28-11-22, Page Block 401

NOTE: The worksteps that follow are applicable to LH and RH wings.

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

you start a maintenance task:

- The following items shall be considered as the basic Aircraft configuration

before you start a maintenance task:

- Parking brake applied.

- 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.

- 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.

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-6109

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SERVICE BULLETIN

(c) Drain and vent the outer fuel tanks, refer to AMM 28-10-00, Page Block 301.

(d) Put access platforms in position at the outer wing stations.

(e) Remove and retain manhole covers 550QB and (650QB) for inspection, refer to

AMM 28-11-22, Page Block 401.

NOTE: Remove manhole covers with care, the MFLI is attached to the man

hole cover.

(f) If a repair is required, remove and retain manhole covers 550PB and (650PB), refer

to AMM 28-11-22, Page Block 401.

C. PROCEDURE

(1) Subtask 286109-832-401-001 - Inspect the Sensor Harness for Damage

Work Zones and Access Panels

Zone Access/Work location

550 Access Panel 550PB

Work location from Rib 25 to Rib 26

550 Access Panel 550QB

Work location from Rib 26 to Rib 27

650 Access Panel 650PB

Work location from Rib 25 to Rib 26

650 Access Panel 650QB

Work location from Rib 26 to Rib 27

Manpower Resources

Manhours 1.00

Minimum number of person 2

Subtask elapsed time 0.50

Skills ELECTRICAL

References

Fig. A-UCAAA

Harness Installation

Sheet 01

Sheet 02

Fig. A-UFBAA

Harness Inspection

Sheet 01

Sheet 02

NOTE: The worksteps that follow are applicable to LH and RH wings.

Refer to Fig. A-UCAAA Sheet 01 and Fig. A-UCAAA Sheet 02.

(a) Do a visual inspection of the harness, refer to Fig. A-UFBAA Sheet 01 and Fig. AUFBAA Sheet 02:

- if no damage is found and if there is no previous repair (other than the addition

of a sleeve) go to SUBTASK 286109-831-401 001 Install New Brackets and

Re-Route the Sensor Harness

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-6109

REVISION No.: 01 - Dec 20/13 Page: 15

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SERVICE BULLETIN

- if there is damage and there has been no previous repair (other than the

addition of a sleeve) to the harness, do the repair SUBTASK 286109-833-401

001 Repair of Damage to the Sensor Harness and do SUBTASK

286109-831-401 001 Install New Brackets and Re-Route the Sensor Harness

- if there has been a previous repair or if the harness conductor is exposed,

please contact AIRBUS for repair instructions.

(2) Subtask 286109-833-401-001 - Repair of Damage to the Sensor Harness

Work Zones and Access Panels

Zone Access/Work location

550 Access Panel 550PB

Work location from Rib 25 to Rib 26

550 Access Panel 550QB

Work location from Rib 26 to Rib 27

650 Access Panel 650PB

Work location from Rib 25 to Rib 26

650 Access Panel 650QB

Work location from Rib 26 to Rib 27

Manpower Resources

Manhours 2.00

Minimum number of person 2

Subtask elapsed time 1.00

Skills ELECTRICAL

Material necessary to do the job

Component COMPB01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

NSA937201MH 0.4 (M) SLEEVE (1)

NOTE (1): If sleeve Part Number NSA937201MH is not available, use an equivalent

heat-shrink sleeve that can be used inside fuel tanks, e.g. ASNE0126.

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant 06ABB1 As required

References

Elec. Std. Practices Manual (ESPM) 20-25-31

20-25-41

20-55-00

Fig. A-UCAAA

Harness Installation

Sheet 01

Sheet 02

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-6109

REVISION No.: 01 - Dec 20/13 Page: 16

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References

Fig. A-UFBAA

Harness Inspection

Sheet 01

Sheet 02

NOTE: The worksteps that follow are applicable to the LH and RH wings, as

required.

NOTE: This repair method is not applicable to cable conductors that are

corroded or broken or where the damage exceeds the limits defined in

ESPM 20-53-21 or for the repair method given in ESPM 20-53-29, Para.

2.B.

Refer to Fig. A-UCAAA Sheet 01, Fig. A-UCAAA Sheet 02, Fig. A-UFBAA Sheet 01 and

Fig. A-UFBAA Sheet 02.

(a) Disconnect the connector from the sensor 695QJ (696QJ).

(b) Disconnect all P-Clips between Ribs 26 and 27.

(c) In the outer fuel tank remove:

4 Nut Item (3) Discard

4 Bolt Item (7) Discard

4 P-Clip Item (1) Discard

4 Bolt Item (4) Discard

4 Nut Item (5) Discard

4 Bracket Item (2) Discard

NOTE: It is possible that the P Clip, Item (1), adjacent to Rib 27 has not

been installed.

(d) Feed the harness through the stringer cut out in Rib 26 and feed the cable out

through the man hole cover 550PB or (650PB).

(e) Move connectors to a safe working location outside the tank in an area free of fuel

or flammable vapors.

(f) Clean all traces of fuel or other contamination from the harness and cables, refer to

ESPM 20-55-00.

(g) Record the wire/pin positions. Disconnect all the wires from the electrical

connectors of the sensor 695QJ (696QJ) LH/RH, refer to ESPM 20-25-41.

WARNING: THE FUEL TANK MUST BE FULLY VENTED, CLEAR OF ANY FUEL,

DRY AND A CONSTANT SUPPLY OF CLEAN FILTERED AIR FROM A

COMPRESSOR BEFORE YOU USE THE HEAT-SHRINK TOOL INSIDE

OR NEAR THE FUEL TANK.

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-6109

REVISION No.: 01 - Dec 20/13 Page: 17

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SERVICE BULLETIN

(h) Install over the damaged cable insulation:

0.2 (M) Heat Shrink Sleeve NSA937201MH

(i) Shrink the Sleeve over the damaged cable insulation, refer to ESPM 20-25-31.

Make sure the sleeve extends 50.0 mm (1.968 in.) either side of the damaged area.

WARNING: THE FUEL TANK MUST BE FULLY VENTED, CLEAR OF ANY FUEL,

DRY AND A CONSTANT SUPPLY OF CLEAN FILTERED AIR FROM A

COMPRESSOR BEFORE YOU USE THE HEAT-SHRINK TOOL INSIDE

OR NEAR THE FUEL TANK.

(j) Install over the damaged braid:

0.2 (M) Heat Shrink Sleeve NSA937201MH

(k) Shrink the Sleeve over the damaged braid, refer to ESPM 20-25-31. Make sure the

sleeve extends 50.0 mm (1.968 in.) either side of the damaged area.

(l) Apply:

Polysulfide Sealant 06ABB1 As required

to each end of the sleeve to prevent movement.

(m) Reconnect the wires to the electrical connectors of the sensor 695QJ (696QJ)

LH/RH, refer to ESPM 20-25-41.

(3) Subtask 286109-831-401-001 - Install New Brackets and Re-Route the Sensor

Harness

Work Zones and Access Panels

Zone Access/Work location

550 Access Panel 550PB

Work location from Rib 25 to Rib 26

550 Access Panel 550QB

Work location from Rib 26 to Rib 27

650 Access Panel 650PB

Work location from Rib 25 to Rib 26

650 Access Panel 650QB

Work location from Rib 26 to Rib 27

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills ELECTRICAL

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-6109

REVISION No.: 01 - Dec 20/13 Page: 18

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SERVICE BULLETIN

Material necessary to do the job

Component COMPB01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 NSA5516-02NF 4 CLIP

2 A28450078200 4 BRACKET

3 MS21071L3 4 NUT

4 NAS1303-3 4 BOLT

5 NSA5474-3K7 4 NUT

6 MS20426AD3 8 RIVET

7 NAS1303-2 4 BOLT

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Anti-Corrosion Primer 04DAB2 As required

Corrosion Sealant 06AAC1 As required

Solvent 08BAA9 As required

Conversion Coating 10ABC1 As required

References

Process and Material Specification

(PMS)

Process and Material Specification (PMS)

01-06-12

Structural Repair Manual (SRM) 51-40-12

51-40-20

Fig. A-UDAAA

Bracket Manufacture

Sheet 01

Fig. A-UCAAA

Harness Installation

Sheet 01

Sheet 02

NOTE: The worksteps that follow are applicable to LH and RH wings.

(a) Refer to Fig. A-UDAAA Sheet 01 locally manufacture

4 Bracket A28450078200 Item 2

(b) Apply:

Conversion Coating 10ABC1 As required

and

Anti-Corrosion

Primer

04DAB2 As required

to the Brackets, Item 2 in accordance with SRM 51-40-12.

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-6109

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(c) On the Brackets, Item 2, install:

4 Anchor Nut MS21071L3 Item 3

with

8 Rivet MS20426AD3 Item 6

(d) Clean the surfaces of the Brackets, Item 2, and Stringer 15 with:

Solvent 08BAA9 As required

(e) Paint the Anchor Nuts, Item 3, Rivets, Item 6, heads and tails with:

Anti-Corrosion

Primer

04DAB2 As required

(f) Part mark new Brackets, Item 2, refer to PMS 01-06-12.

(g) Wet install manufactured Brackets to Stringer 15 in accordance with SRM 51-40-20,

use:

Corrosion Sealant 06AAC1 As required

in accordance with SRM 51-40-20.

(h) Install:

4 Nut NSA5474-3K7 Item 5

and

4 Bolt NAS1303-3 Item 4

(i) As shown in Fig. A-UCAAA Sheet 01 and Fig. A-UCAAA Sheet 02, re-route the

harness and install:

4 P-Clip NSA5516-02NF Item 1

to the Brackets with:

4 Bolt NAS1303-2 Item 7

(j) Reconnect the electrical connector to the sensor 695QJ (696QJ) LH/RH.

(k) Make sure that a final clearance check is performed to confirm a minimum

clearance of not less than 6.0 mm (0.24 in.) between the harness and structure and

that the harness runs parallel to Stringer 15 where new brackets will be installed.

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-6109

REVISION No.: 01 - Dec 20/13 Page: 20

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SERVICE BULLETIN

D. TEST

(1) Subtask 286109-760-401-001 - Continuity Check of the Harness

Work Zones and Access Panels

Zone Access/Work location

550

650

Manpower Resources

Skills ELECTRICAL

References

Aircraft Schematic Manual (ASM) 28-46-00

NOTE: The worksteps that follow are applicable to the LH and RH wings.

(a) Do a continuity check of the Harness, refer to ASM 28-46-00.

(2) Subtask 286109-710-401-001 - Operational Test of Level Indicating

Work Zones and Access Panels

Zone Access/Work location

550

650

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 28-46-00, Page Block 501

(a) Do the Operational Test of the High Level Indicating, refer to AMM 28-46-00, Page

Block 501.

E. CLOSE-UP

(1) Subtask 286109-942-401-001 - Close-Up

Work Zones and Access Panels

Zone Access/Work location

550 Access Panel 550PB

Work location from Rib 25 to Rib 26

550 Access Panel 550QB

Work location from Rib 26 to Rib 27

650 Access Panel 650PB

Work location from Rib 25 to Rib 26

650 Access Panel 650QB

Work location from Rib 26 to Rib 27

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-6109

REVISION No.: 01 - Dec 20/13 Page: 21

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Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 28-11-22, Page Block 401

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Install the retained the manhole covers: 550QB and (650QB), refer to AMM

28-11-22, Page Block 401.

(c) If removed, install the retained manhole covers: 550PB and (650PB), refer to AMM

28-11-22, Page Block 401.

(d) Remove the access platform(s).

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-6109

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SERVICE BULLETIN

**CONF ALL

MFLI SUPPORT

CANISTER (REF)

PLAN VIEW SHOWING P CLIPS

AND CLEATS TO BE DISCARDED

PLAN VIEW SHOWING INSTALLATION

OF NEW P CLIPS AND CLEATS

SENSOR UNIT

HARNESS (REF)

THIS DOES NOT AFFECT THE MODIFICATION.

01

NOTE:

01 ON SOME AIRCRAFT THIS P−CLIP HAS NOT BEEN INSTALLED,

STGR15

AFTER

BEFORE

A

B

RIB 27

DATUM

RIB 26

DATUM

F

W

D

02

02 02

STGR15

MFLI SUPPORT

CANISTER (REF)

RIB 27

DATUM

RIB 26

DATUM

F

W

D

INBD

INBD

VIEW OF LH WING SHOWN

RH WING SIMILAR

RIB26 RIB27

A B

D D

C C

01

ASSEMBLED IN VARIOUS ORIENTATIONS.

IT IS POSSIBLE THAT THE P−CLIPS SHOWN AT ’C’ COULD BE

D_SB_286109_7_CAAA_01_01

Figure A-UCAAA - Sheet 01

Harness Installation

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-6109

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**CONF ALL

C

TYPICAL

TYPICAL

STGR15

5

1

2

3 6

4

(1) (7) (4) (5)

(3) (2)

FWD

FWD D

AFTER

BEFORE

7

D_SB_286109_7_CAAA_02_01

Figure A-UCAAA - Sheet 02

Harness Installation

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-6109

REVISION No.: 01 - Dec 20/13 Page: 24

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**CONF ALL

ALCLAD CLOSE TOLERANCE SHEET 18 SWG (0.048 inch/ 1.22 mm THICK)

BRITISH STANDARD SPEC. L110.

AMERICAN STANDARD SPEC. QQA250/5 T42 OR 2024/T42

MATERIAL :

38.1 mm

(1.5 in)

26.67 mm

(1.05 in)

 1 HOLE

4.826 mm

(0.190 in) DIA

15.24 mm

(0.6 in)

2 HOLES

2.46 ± 0.03 mm

10.16 mm

(0.4 in)

7.62 mm

(0.3 in)

HOLE

4.826 mm

(0.190 in) DIA

0.15 mm

(0.006 in) RAD

4.318 mm

(0.170 in) 17.78 mm

(0.7 in)

NOTE:

01 HOLE DIA TOLERANCES: +0.051 mm (+0.002 in) −0.000 mm (−0.000 in)

GENERAL MANUFACTURE TOLERANCES ± 0.254 mm (0.010 in).

01

01

(0.097 ± 0.001 in) DIA

3.0 mm

(0.12 in) RAD

3.0 mm

(0.12 in) RAD

CSK 4.47 ± 0.01 mm

(0.176 ± 0.006 in) DIA

CSK DEPTH 0.889 mm (0.35 in)

ALODINE 1200 (MAT. No.10ABC1)

EPOXY PRIMER (MAT. No.04DAB2)

PROTECTIVE TREATMENT :

D_SB_286109_7_DAAA_01_03

Figure A-UDAAA - Sheet 01

Bracket Manufacture

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-6109

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**CONF ALL

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN.

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

HAS THERE

PREVIOUSLY BEEN

A REPAIR?

REPORT TO AIRBUS

FOR FURTHER INSTRUCTIONS

INSTALL MODIFIED

BRACKETS

IS THE

BRAID

DAMAGED?

YES NO

IS THE

INSULATION

DAMAGED?

NO YES

CONTACT AIRBUS FOR

REPAIR INSTRUCTION

APPLY REPAIR IN

ACCORDANCE WITH M SB.

VALID FOR BRAID AND

IS THE

CONDUCTOR

EXPOSED?

YES NO

1.

WITH ESPM 20−53−29 PARAGRAPH 2.B

ON DAMAGED CABLES

’HEAT−SHRINK SLEEVE INSULATING’

2.

ACCORDANCE WITH M SB

NO

FOR BRAID AND

COATING DAMAGE

QUESTION

ACTION

FINDING

CARRY OUT REPAIR IN ACCORDANCE

IN ADDITION APPLY REPAIR IN

INSPECTION OF OUTER TANK

HARNESS FIN 625QT1 (625QT2)

BETWEEN RIBS 26 AND 27

YES

BULLETIN AT REVISION 00, IS AN ALTERNATIVE MEANS OF COMPLIANCE TO THIS SERVICE BULLETIN AT REVISION 01.

MSNs 0855, 0856, 0857, 0858, 0859, 0860, 0870, 0871), PERFORMED DURING ACCOMPLISHMENT OF THIS SERVICE

NOTE:

SLEEVE INSTALLATION PROPOSED AS PER TECHNICAL ADAPTION REF. TA−SEMBL−2013−975507 (LIMITED TO

D_SB_286109_7_FBAA_01_04

Figure A-UFBAA - Sheet 01

Harness Inspection

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-6109

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**CONF ALL

BRAID

COATING

INSULATION

CONDUCTOR

THE COATING CAN HAVE

BLACK COLOR

SINGLE: WHITE OR

DOUBLE (ONLY CF−C):

DARK AND WHITE

PLOYMIDE TAPES

AMBER COLOR

Cu Ni OR Ni ALLOY

ACCORDING TO GAUGE

METAL COLOR

HARNESS LAYOUT FOR DAMAGE ASSESSMENT

A DIFFERENT COLOR

STGR15

MFLI SUPPORT

CANISTER (REF) RIB 26

DATUM

INBD

INSTALL HEAT SHRINK

SLEEVE WITH 50 mm

COVERAGE EITHER SIDE

OF DAMAGED ZONE

D_SB_286109_7_FBAA_02_01

Figure A-UFBAA - Sheet 02

Harness Inspection

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-6109

REVISION No.: 01 - Dec 20/13 Page: 27

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SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-6109

REVISION No.: 01 - Dec 20/13 Page: 28

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SERVICE BULLETIN

APPENDIX 01: Elapsed Time Assumption

**CONF ALL

For an explanation of the manhours and elapsed time, refer to the Gantt Chart shown below:

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-6109

REVISION No.: 01 - Dec 20/13 Page: 1

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SERVICE BULLETIN

APPENDIX 01: Elapsed Time Assumption

**CONF ALL

ELAPSED TIME ASSUMPTION SERVICE BULLETIN No. A300−28−6109

GET ACCESS

MH ET/S

TOTAL MANHOURS

SB ELAPSED TIME

15.00

7.50

STEPS

2.00 1.00

0

REPAIR DAMAGE TO SENSOR HARNESS 2.00 1.00

TEST 2.00 1.00

MH

ET/S:

PER

MANHOURS

ELAPSED TIME PER STEP

NUMBER OF PERSONS

01

02

THIS CHART IS ONLY A PROPOSAL.

OPERATORS MAY DETERMINE THAT ANOTHER WAY

TO DO THE WORK IS MORE SUITABLE FOR THEM.

01

02

NOTES:

PER

2

2

2

CLOSE UP 2.00 1.00 2

:

:

SB ELAPSED TIME

(HOURS)

2 4 6 8

IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS

ARE NOT REFLECTED IN THIS GANTT CHART.

INSPECT SENSOR HARNESS 1.00 0.50 2

INSTALL NEW BRACKETS AND RE−ROUTE 6.00 3.00 2

SENSOR HARNESS

D_SB_286109_7_AAAA_01_01

Figure A-UAAAA - Sheet 01

Elapsed Time Assumption

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-6109

REVISION No.: 01 - Dec 20/13 Page: 2

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SERVICE BULLETIN

REPORTING SHEET

TITLE: FUEL - TANK LEVEL SENSING - NEW OUTER TANK SENSOR

HARNESS INSTALLATION

MODIFICATION No.: 13671H5745

Please complete the appropriate item (A or B):

A - SB WILL BE embodied YES/NO (if NO please comment)

If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of

embodiment:

B - SB HAS BEEN embodied on aircraft:

Operator comments:

From Airline:

Name/Title:

Signature: Date:

If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to

next normal revision or prior to SB embodiment, please indicate required service(s):

Either: Modification Operational Impact (MOI), if available YES/NO

Or : Intermediate revision YES/NO

Important Information: This SB will only be incorporated in your maintenance and operational

documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With

the next feasible revision, this will result in

- Updating of maintenance documentation to show pre and post SB data.

- Updating of maintenance and operational documentation to show post SB data after embodiment.

If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically

include them in the manual revisions. Refer to SIL 00-037 for detailed information.

Please return this completed sheet to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn: SDC32 Technical Data and Documentation Services

FAX: (+33) 5 61 93 28 06

e-mail: sb.reporting@airbus.com

or via your Resident Customer Support Office.

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

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-6109

REVISION No.: 01 - Dec 20/13 Page: 1

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SERVICE BULLETIN

QUALITY PERCEPTION FORM

Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data

that you provide us will be used to analyse areas of difficulties and to take corrective action to further

improve the quality of our Service Bulletins.

We thank you for the time you have taken in completing this form.

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

- Quality rating of this SB 4321

- Quality rating of the Accomplishment Instructions 4321

- Quality rating of the Illustrations 4321

- Is this SB easy to understand ? Y/N

If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a

short description of the issue.

Planning Material Instructions

X Effectivity X Kit content X Preparation

X Reason X List of Materials Operator Supplied X Mod/Inspection

X Manpower X Industry support X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustrations

Comments:

Operator: Date:

Name/Title:

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-6109

REVISION No.: 01 - Dec 20/13 Page: 1

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