@A300

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 SBs A300-28-0058 and 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.: A300-28-0091

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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 SB. Damage that falls outside the limits

identified in this SB will require specific repair instructions from Airbus.

Accomplishment of this Service Bulletin ensures 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) :

001 50W 69X 72U ABR AFG C2A DHL F2I FLM GST IAW IRA

IRM KYE KZU MIX MNB MNG MSR NTR P2A RUN SOP TNO TSY

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

HARD NO

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SERVICE BULLETIN

SUMMARY

SOFT NO

OBRM NO

MANPOWER

Task 280091-831-895-001: MODIFICATION

TOTAL MANHOURS 15.00

ELAPSED TIME (HOURS) 7.50

APPENDICES

APPENDIX 01: Elapsed Time Assumption

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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

A_SB_280091_7_SBAA_01_00

PLAN VIEW

FWD

Figure A-USBAA - Sheet 01

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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

B2-1C B2-203 B2K-3C B4-103 B4-120 B4-203 B4-2C C4-203

F4-203

(2) Effectivity by MSN

0003 0041 0045 0047 0053 0055 0075 0079-0080 0082-0085 0090 0094-0095 0101

0105 0107 0116-0117 0123-0126 0128-0129 0133 0135-0137 0139 0141 0147

0149-0152 0154-0157 0160 0170 0173 0175-0176 0180 0183-0185 0187 0189

0199-0200 0203-0204 0210-0212 0218-0220 0226-0227 0234-0236 0239 0243-0244

0247 0249-0250 0255-0256 0259 0261 0265 0274 0277 0289 0292 0299 0302 0304

(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.

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SERVICE BULLETIN

OPERATOR MSN

001 0125

50W 0003

69X 0095

72U 0079

ABR 0152 0184 0189 0199 0219 0220 0234 0236 0250 0259 0274 0289

AFG 0180

C2A 0261

DHL 0084 0085 0141 0149 0249 0265

F2I 0083 0094 0128 0133 0135 0136 0137 0156 0170 0235 0243

FLM 0082 0176

GST 0277 0292

IAW 0239

IRA 0080 0139 0151 0173 0185 0187 0226 0256 0299 0302

IRM 0055 0090 0160 0175 0204 0244

KYE 0053 0211

KZU 0041 0101 0117

MIX 0157 0203 0218

MNB 0123 0212 0304

MNG 0047

MSR 0200 0255

NTR 0124 0155

P2A 0116 0150

RUN 0075 0105 0107 0147 0154 0183

SOP 0126

TNO 0045 0210 0227 0247

TSY 0129

(4) Configuration by MSN

MSN CONFIGURATION

0003 0041 0045 0047 0053 0055 0075 0079 0080 0082 0083

0084 0085 0090 0094 0095 0101 0105 0107 0116 0117 0123

0124 0125 0126 0128 0129 0133 0135 0136 0137 0139 0141

0147 0149 0150 0151 0152 0154 0155 0156 0157 0160 0170

0173 0175 0176 0180 0183 0184 0185 0187 0189 0199 0200

0203 0204 0210 0211 0212 0218 0219 0220 0226 0227 0234

0235 0236 0239 0243 0244 0247 0249 0250 0255 0256 0259

0261 0265 0274 0277 0289 0292 0299 0302 0304

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.

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SERVICE BULLETIN

(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.

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 SBs

A300-28-0058 and 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 SB. Damage

that falls outside the limits identified in this SB will require specific repair instructions

from Airbus.

(3) Advantages

Accomplishment of this Service Bulletin ensures 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

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SERVICE BULLETIN

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

Task 280091-831-895-001: 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. It is expected that an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA) will be issued

to confirm this classification. The accomplishment timescale, which has not yet been

defined, will be given in the AD.

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.

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

Chart given in Appendix 01.

Task 280091-831-895-001: MODIFICATION

Get Access 2.00

On Aircraft

Inspect the Sensor Harness for Damage 1.00

Repair of Damage to the Sensor Harness 2.00

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SERVICE BULLETIN

Task 280091-831-895-001: MODIFICATION

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

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

Aircraft Maintenance Manual (AMM) 06-21-00 20-21-12 24-00-00

28-10-00 28-11-14 28-43-21

28-46-00 53-00-00

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 20-53-21 20-53-29

20-55-00

Process and Material Specification (PMS) Process and Material Specification

(PMS) 01-06-12

Standards Manual (SM)

Structural Repair Manual (SRM) 51-30-29 51-30-38 51-40-12

51-40-20 51-40-40

K. PUBLICATION AFFECTED

Illustrated Parts Catalog (IPC) 28-22-10 28-46-11

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

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SERVICE BULLETIN

2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

Component COMPB01 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:

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

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SERVICE BULLETIN

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Sealant 09-005 As required

Sealant (Thiokol) 09-554 As required

Solvent 11-026 As required

Conversion Coating 13-002 As required

Anti-Corrosion Primer 16-006 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

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.

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

(1) Tooling - Price and Availability

None

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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

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SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

Task 280091-831-895-001 - 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.

Task Associated Data

Zone

550 650

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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 280091-910-401-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

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

06-21-00, Page Block 001

20-21-12, Page Block 001

53-00-00, 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

Structural Repair Manual (SRM) 51-30-29

51-30-38

51-40-12

51-40-20

51-40-40

(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 53-00-00, 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 06-21-00, 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 51-30-29.

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

51-30-38.

(i) Apply sealant in accordance with SRM 51-40-20.

(j) Renew the protective finish in accordance with SRM 51-40-12.

(k) For bending (Refer to SRM 51-40-40).

(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 Process and Material Specification (PMS) 01-06-12).

(2) Subtask 280091-839-401-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

B. PREPARATION

(1) Subtask 280091-941-401-001 - 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

28-11-14, Page Block 401

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

(a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page

Block 301).

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

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

(d) Remove and retain manhole covers 550QB and (650QB) (Refer to AMM 28-11-14,

Page Block 401) for inspection.

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

hole cover.

(e) If a repair is required remove and retain manhole covers 550PB and (650PB)

(Refer to AMM 28-11-14, Page Block 401).

C. PROCEDURE

(1) Subtask 280091-832-401-001 - 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

Elec. Std. Practices Manual (ESPM) 20-53-21

20-53-29

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

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(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 280091-831-401 001 Install New Brackets and

Re-Route the Sensor Harness

- 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 280091-833-401

001 Repair of Damage to the Sensor Harness and do SUBTASK

280091-831-401 001 Install New Brackets and Re-Route the Sensor Harness

- if there has been a previous repair or if damage exceeds the limits given in

ESPM 20-53-21 for the repair method given in ESPM 20-53-29, Para. 2.B,

please contact AIRBUS for repair instructions:

AIRBUS

CUSTOMER SERVICE DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Attn: SEEE5 Fuel Systems B22-2A2 - Laurent Aris

TEL: +33 56 71 91 098

FAX: +33 56 19 33 614

e-mail: laurent.aris@airbus.com

(2) Subtask 280091-833-401-001 - 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

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-0091

REVISION No.: 00 - Mar 05/13 Page: 15

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SERVICE BULLETIN

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant (Thiokol) 09-554 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

Fig. A-UFBAA

Harness Inspection

Sheet 01

Sheet 02

NOTE: The worksteps that follow are applicable to 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 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 95QJ (96QJ).

(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.

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-0091

REVISION No.: 00 - Mar 05/13 Page: 16

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SERVICE BULLETIN

(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 connector

of the sensor 95QJ (96QJ) LH/RH (Refer to ESPM 20-25-41).

(h) Install:

0.2 (M) Heat Shrink Sleeve NSA937201MH

(MH Yellow size to suit cable diameter) over the damaged braid, make sure the

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

(i) Shrink the Sleeve in to place (Refer to ESPM 20-25-31).

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:

0.2 (M) Heat Shrink Sleeve NSA937201MH

(MH Yellow size to suit harness diameter) over the damaged insulation, make sure

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

(k) Shrink the Sleeve in to place (Refer to ESPM 20-25-31).

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.

(l) Apply:

Sealant (Thiokol) 09-554 As required

to each end of the sleeve to prevent movement.

(m) Reconnect the wires to the electrical connector of the sensor 95QJ (96QJ) LH/RH

(Refer to ESPM 20-25-41).

(3) Subtask 280091-831-401-001 - 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

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-0091

REVISION No.: 00 - Mar 05/13 Page: 17

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SERVICE BULLETIN

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 AIRFRAME

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

Corrosion Sealant 09-005 As required

Solvent 11-026 As required

Conversion Coating 13-002 As required

Anti-Corrosion Primer 16-006 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

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-0091

REVISION No.: 00 - Mar 05/13 Page: 18

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SERVICE BULLETIN

(b) Apply:

Conversion Coating 13-002 As required

and

Anti-Corrosion

Primer

16-006 As required

to the Brackets, Item 2 (Refer to SRM 51-40-12).

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

4 Anchor Nut MS21071L3 Item 3

with

8 Rivet MS20426AD3 Item 6

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

Solvent 11-026 As required

(e) Paint the Anchor Nut, Item 3, Rivet, Item 6, heads and tails with:

Anti-Corrosion

Primer

16-006 As required

(f) Part mark new Bracket, Item 2 (Refer to Process and Material Specification (PMS)

01-06-12).

(g) Wet install manufactured Bracket, Item 2, with attached Anchor Nut, Item 3, to

Stringer 15 use:

Corrosion Sealant 09-005 As required

(Refer to 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 Bracket with:

4 Bolt NAS1303-2 Item 7

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-0091

REVISION No.: 00 - Mar 05/13 Page: 19

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SERVICE BULLETIN

(j) Reconnect the electrical connector to the sensor 95QJ (96QJ) 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.

D. TEST

(1) Subtask 280091-760-401-001 - 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 LH and RH wings.

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

(2) Subtask 280091-710-401-001 - Operational Test of High 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 280091-942-401-001 - 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

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-0091

REVISION No.: 00 - Mar 05/13 Page: 20

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SERVICE BULLETIN

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 NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 28-11-14, Page Block 401

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

(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

28-11-14, Page Block 401).

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

28-11-14, Page Block 401).

(d) Remove the access platform(s).

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-0091

REVISION No.: 00 - Mar 05/13 Page: 21

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@A300

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

A_SB_280091_7_CAAA_01_01

Figure A-UCAAA - Sheet 01

Harness Installation

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-0091

REVISION No.: 00 - Mar 05/13 Page: 22

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SERVICE BULLETIN

**CONF ALL

C

TYPICAL

TYPICAL

STGR15

5

1

2

3 6

4

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

(3) (2)

FWD

FWD D

AFTER

BEFORE

7

A_SB_280091_7_CAAA_02_01

Figure A-UCAAA - Sheet 02

Harness Installation

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-0091

REVISION No.: 00 - Mar 05/13 Page: 23

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@A300

SERVICE BULLETIN

**CONF ALL

ALODINE 1200 (MAT. No.13−002)

EPOXY PRIMER (MAT. No.16−006)

ALCAD 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

PROTECTIVE TREATMENT :

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

4.318 TO 4.623 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

(0.170 TO 0.182 in) DIA

3.0 mm

(0.12 in) RAD

3.0 mm

(0.12 in) RAD

CSK 4.318 TO 4.623 mm

(0.170 TO 0.182 in) DIA

CSK DEPTH 0.889 mm (0.35 in)

A_SB_280091_7_DAAA_01_00

Figure A-UDAAA - Sheet 01

Bracket Manufacture

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-0091

REVISION No.: 00 - Mar 05/13 Page: 24

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@A300

SERVICE BULLETIN

**CONF ALL

NO

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

INSPECTION OF OUTER TANK

HARNESS PN 708−614−1/2/3 OR 4

OR 762−001−2/3/4 OR 5.

BETWEEN RIBS 26 AND 27

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

YES

FOR BRAID AND

COATING DAMAGE

QUESTION

ACTION

FINDING

CARRY OUT REPAIR IN ACCORDANCE

IN ADDITION APPLY REPAIR IN

A_SB_280091_7_FBAA_01_00

Figure A-UFBAA - Sheet 01

Harness Inspection

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-0091

REVISION No.: 00 - Mar 05/13 Page: 25

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@A300

SERVICE BULLETIN

**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

MLI SUPPORT

CANISTER (REF) RIB 26

DATUM

INBD

INSTALL HEAT SHRINK

SLEEVE WITH 50 mm

COVERAGE EITHER SIDE

OF DAMAGED ZONE

A_SB_280091_7_FBAA_02_00

Figure A-UFBAA - Sheet 02

Harness Inspection

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-0091

REVISION No.: 00 - Mar 05/13 Page: 26

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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.: A300-28-0091

REVISION No.: 00 - Mar 05/13 Page: 1

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SERVICE BULLETIN

APPENDIX 01: Elapsed Time Assumption

**CONF ALL

ELAPSED TIME ASSUMPTION SERVICE BULLETIN No. A300−28−0091

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

A_SB_280091_7_AAAA_01_01

Figure A-UAAAA - Sheet 01

Elapsed Time Assumption

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-0091

REVISION No.: 00 - Mar 05/13 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.: A300-28-0091

REVISION No.: 00 - Mar 05/13 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.: A300-28-0091

REVISION No.: 00 - Mar 05/13 Page: 1

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