# @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. 

# MANDATORYMANDATORYMANDATORY
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 REVISION No.: 00 - Mar 05/13 Page: 1 7

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# @A300 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
DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-0091 REVISION No.: 00 - Mar 05/13 Page: 2 7

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# @A300 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

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-0091 REVISION No.: 00 - Mar 05/13 Page: 3 7

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# @A300 SERVICE BULLETIN SUMMARY

**CONF ALL



### B

THIS DOES NOT AFFECT THE MODIFICATION. **NOTE:** ON SOME AIRCRAFT THIS P−CLIP HAS NOT BEEN INSTALLED, 01 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

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-0091 REVISION No.: 00 - Mar 05/13 Page: 4 7

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# @A300 SERVICE BULLETIN
AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51



# MANDATORYMANDATORYMANDATORY
ATA SYSTEM: 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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# @A300 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.

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-0091 REVISION No.: 00 - Mar 05/13 Page: 2 7

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# @A300 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 provideadequate 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

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-0091 REVISION No.: 00 - Mar 05/13 Page: 3 7

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# @A300 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

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-0091 REVISION No.: 00 - Mar 05/13 Page: 4 7

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# @A300 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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# @A300 SERVICE BULLETIN

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# @A300 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

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-0091 REVISION No.: 00 - Mar 05/13 Page: 7 7

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# @A300 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

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-0091 REVISION No.: 00 - Mar 05/13 Page: 8 7

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# @A300 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.: A300-28-0091 REVISION No.: 00 - Mar 05/13 Page: 9 7

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# @A300 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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# @A300 SERVICE BULLETIN

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.

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-0091 REVISION No.: 00 - Mar 05/13 Page: 12 7

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# @A300 SERVICE BULLETIN (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 DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-0091 REVISION No.: 00 - Mar 05/13 Page: 13 7

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# @A300 SERVICE BULLETIN
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

DATE: Mar 05/13 SERVICE BULLETIN No.: A300-28-0091 REVISION No.: 00 - Mar 05/13 Page: 14 7

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# @A300 SERVICE BULLETIN (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
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# @A300 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 7

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# @A300 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 7

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# @A300 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 7

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# @A300 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 7

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# @A300 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 7

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# @A300 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 7

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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:** ON SOME AIRCRAFT THIS P−CLIP HAS NOT BEEN INSTALLED, 01 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 7

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# @A300 SERVICE BULLETIN

**CONF ALL



## C TYPICAL

TYPICAL STGR15 5 1

2
3 6 4 (5) (4) (1) (7)

(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 7

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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:** HOLE DIA TOLERANCES: +0.051 mm (+0.002 in) −0.000 mm (−0.000 in) 01 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 7

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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 7

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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 7

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# @A300 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 7

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# @A300 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 7

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# @A300 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 7

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# @A300 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 7

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