# @A300 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 ATA SYSTEM: 53 

### TITLE: FUSELAGE - GENERAL - REINFORCE THE FLOOR CROSSBEAMS AT FR22/FR23 AND FR61/FR62 MODIFICATION No.: 13434D23217 This page transmits Revision No.02 of Service Bulletin No.A300-53-0389 ADDITIONAL WORK **CONF ALL No additional work is required by this revision for aircraft modified by any previous issue. REASON Revision No. 02 issued to: - correct AMM references - add rework areas and figures - incorporate minor changes. CHANGES SUMMARY EFFECTIVITY OPERATOR LIST UPDATED R CONCURRENT REQUIREMENTS CONCURRENT REQUIREMENTS UPDATED R Fig. A-GSAAA FIGURE SOLUTION UPDATED R Fig. A-GSAAA Sheet 02 SHEET ADDED N Fig. A-GSB FIGURE DELETED FOR APPLICABLE MSN D PLANNING INFORMATION EFFECTIVITY EFFECTIVITY RELATED INFORMATION UPDATED R CONCURRENT REQUIREMENTS CONCURRENT SB LIST UPDATED R APPROVAL APPROVAL UPDATED R WEIGHT AND BALANCE WEIGHT UPDATED BALANCE UPDATED R WEIGHT UPDATED BALANCE UPDATED R

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 1 6

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# @A300 SERVICE BULLETIN REVISION TRANSMITTAL SHEET WEIGHT UPDATED BALANCE UPDATED R REFERENCES REFERENCED DOCUMENTATION UPDATED R REFERENCED DOCUMENTATION UPDATED R REFERENCED DOCUMENTATION UPDATED R MATERIAL INFORMATION MATERIAL - PRICE AND AVAILABILITY Price and Availability PRICE AND AVAILABILITY UPDATED MATERIAL SET UPDATED R ACCOMPLISHMENT INSTRUCTIONS TASK 530389- 831-848-001- MODIFICATION Subtask 530389-910-201-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED REFERENCES UPDATED R Subtask 530389-839-201-001 SUBTASK SOLUTION UPDATED R Subtask 530389-910-201-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED REFERENCES UPDATED R Subtask 530389-839-201-001 SUBTASK SOLUTION UPDATED R Subtask 530389-910-201-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED REFERENCES UPDATED R Subtask 530389-839-201-001 SUBTASK SOLUTION UPDATED R Subtask 530389-941-201-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED REFERENCES UPDATED R Subtask 530389-941-201-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED REFERENCES UPDATED R Subtask 530389-941-201-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED REFERENCES UPDATED R Subtask 530389-831-203-001 SUBTASK SOLUTION UPDATED R Subtask 530389-831-207-001 SUBTASK SOLUTION UPDATED R Subtask 530389-831-203-002 SUBTASK SOLUTION UPDATED CONFIGURATION UPDATED FIGURE REFERENCE UPDATED REFERENCED DOCUMENTATION UPDATED R
Subtask 530389-831-207-001 SUBTASK SOLUTION UPDATED R Subtask 530389-831-203-003 SUBTASK SOLUTION UPDATED R Subtask 530389-831-207-001 SUBTASK SOLUTION UPDATED R Subtask 530389-942-201-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED REFERENCES UPDATED R Subtask 530389-942-201-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED REFERENCES UPDATED R

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 2 6

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# @A300 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Subtask 530389-942-201-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED REFERENCES UPDATED R Fig. A-GBGAA FIGURE SOLUTION UPDATED R Fig. A-GBGAA Sheet 02 SHEET UPDATED R Fig. A-GBGAA Sheet 03 SHEET UPDATED R Fig. A-GBGAA Sheet 05 SHEET UPDATED R Fig. A-GBGAA Sheet 08 SHEET ADDED N 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 This Revision is issued to : incorporate the result of the validation report from A300-600 aircraft MSN 0605. REVISION SEQUENCE ORIGINAL: Jan 15/10 REVISION No. : 01 - May 21/10 REVISION No. : 02 - Apr 27/11

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 3 6

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# @A300 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

This Page Intentionally Left Blank

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 4 6

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# @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. ATA SYSTEM: 53 

### TITLE: FUSELAGE - GENERAL - REINFORCE THE FLOOR CROSSBEAMS AT FR22/FR23 AND FR61/FR62 **CONF ALL MODIFICATIONS MODIFICATION CLASSIFICATION MAJOR None MINOR 13434D23217 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 Some operators have reported cracks in the crossbeam at the junction with the cargo door actuator support beam. The damage was located on the outboard row of rivets on the crossbeam at FR23. The laboratory analysis has revealed that the cracks initiated in the fastener hole are propagated vertically. The design of the forward and aft cargo door attachment is similar, the crossbeams at FR22, FR23, FR61 and FR62 should be reinforced to avoid crack initiation. This Service Bulletin details the procedure to install the reinforcement fittings and to relocate the brackets at the floor crossbeams at FR22, FR23, FR61 and FR62. NOTE: It is not necessary to accomplish the Inspection Service Bulletin No. A300-53-0390 before doing this Service Bulletin. This Service Bulletin can be accomplished directly as given in the accomplishment instruction. NOTE: To reach the mod advantages, this Service Bulletin is to be accomplished, if: - Service Bulletin No. A300-53-0320 has been previously accomplished, - none repair has been performed in the affected areas in accordance with SRM, All Operators Telex 53-07, Inspection Service Bulletin No. A300-53-0321 or Repair Approval Sheet (RAS). In case of existing repairs, the operators are requested to contact Airbus Repair Support before accomplishment of this Service Bulletin, for further instructions.
DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 1 6

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# @A300 SERVICE BULLETIN SUMMARY The accomplishment of this Service Bulletin will : - contribute to avoid the development of cracks, - cancel the inspection requirements in accordance with the Inspection Service Bulletin No. A300-53-0390. GENERAL EVALUATION EVALUATION TABLE COMPLIANCE RECOMMENDED (1) CANCELS INSPECTION SB YES POTENTIAL AD NO A/C OPERATION AFFECTED NO RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO COST SAVING NO ETOPS AFFECTED NO STRUCTURAL LIFE EXTN YES VENDOR SB INVOLVED NO NOTE (1): Service Bulletin recommended to be accomplished to prevent significant operational disruptions. MATERIAL PRICE INFORMATION **CONF 001 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 530389D01R02 1 1,410.00 Reinforcement and attachment parts Kit 530389D02R01 1 1,410.00 Reinforcement and attachment parts TOTAL 2,820.00 Component COMPD01 1 See SB Clamp and attachment parts Standard tool TOOLD01 2 See SB Support Struts - FWD and AFT Cargo Compartment Doors **CONF 002 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 530389D01R02 1 1,410.00 Reinforcement and attachment parts Kit 530389D03R01 1 953.00 Reinforcement and attachment parts TOTAL 2,363.00 Component COMPD01 1 See SB Clamp and attachment parts Standard tool TOOLD01 2 See SB Support Struts - FWD and AFT Cargo Compartment Doors

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 2 6

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# @A300 SERVICE BULLETIN SUMMARY **CONF 003 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 530389D01R02 1 1,410.00 Reinforcement and attachment parts Kit 530389D04R02 1 1,020.00 Reinforcement and attachment parts TOTAL 2,430.00 Component COMPD01 1 See SB Clamp and attachment parts Standard tool TOOLD01 2 See SB Support Struts - FWD and AFT Cargo Compartment Doors EFFECTIVITY **CONF ALL This Service Bulletin is applicable to this (these) operator(s) :

50W 69X 72U ABR AFG C2A DHL F2I FLM IAW IRA IRM JLJ KYE KZU MIX MNB MSR NTR P2A RUN SOP TNO TSY The equivalent of this Service Bulletin has been validated on A300-600 aircraft MSN 0605. CONCURRENT REQUIREMENTS NOTE: Accomplishment of this Service Bulletin requires the prior or simultaneous accomplishment of the following Service Bulletin(s) or the equivalent production modification(s): Service Bulletin No. A300-53-0321 REFERENCES / REPERCUSSIONS TFU None OEB None AOT None SIL None LINE MAINTENANCE AFFECTED No LIFE LIMIT None OTHER None NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO

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# @A300 SERVICE BULLETIN SUMMARY MANPOWER **CONF 001 Task 530389-831-848-001: MODIFICATION TOTAL MANHOURS 37.00 ELAPSED TIME (HOURS) 26.00 **CONF 002 Task 530389-831-848-001: MODIFICATION TOTAL MANHOURS 37.00 ELAPSED TIME (HOURS) 26.00 **CONF 003 Task 530389-831-848-001: MODIFICATION TOTAL MANHOURS 35.00 ELAPSED TIME (HOURS) 26.00 APPENDICES **CONF ALL None

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 4 6

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# @A300 SERVICE BULLETIN SUMMARY
**CONF ALL

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2 SEAT TRACK 4 Z130

FR21 FR22 FR23 FR24

SEAT TRACK 6

AREAS TO BE MODIFIED

**FWD**



## A
A_SB_530389_6_SAAA_01_02 

### A

Figure A-GSAAA - Sheet 01
DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 5 6

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# @A300 SERVICE BULLETIN SUMMARY
**CONF ALL

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2 SEAT TRACK 4 

### A

SEAT TRACK 6 FR60 FR61 FR62 FR63 Z150

AREAS TO BE MODIFIED

**FWD**



## A
A_SB_530389_6_SAAA_02_00 Figure A-GSAAA - Sheet 02
DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 6 6

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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 ATA SYSTEM: 53 

### TITLE: FUSELAGE - GENERAL - REINFORCE THE FLOOR CROSSBEAMS AT FR22/FR23 AND FR61/FR62 MODIFICATION No.: 13434D23217 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 The equivalent of this Service Bulletin has been validated on A300-600 aircraft MSN 0605. (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 0019 0041 0045 0047 0053 0055 0075 0079-0080 0082-0085 0090 0094-0095 0100-0101 0105 0107 0116-0117 0123-0126 0128-0129 0133-0137 0139 0141 0147-0152 0154-0157 0160 0170 0173 0175-0176 0180 0183-0185 0187 0189-0190 0196 0199-0200 0203-0204 0208 0210-0212 0216 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.
DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 1 6

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# @A300 SERVICE BULLETIN
OPERATOR MSN 50W 0003 69X 0095 72U 0079 ABR 0148 0152 0184 0189 0199 0208 0219 0220 0234 0236 0250 0259 0274 0289 AFG 0180 0190 C2A 0211 DHL 0084 0085 0141 0149 0249 0265 F2I 0083 0094 0128 0133 0135 0136 0137 0156 0170 0235 0243 FLM 0082 IAW 0239 IRA 0080 0139 0151 0173 0185 0187 0226 0256 0299 0302 IRM 0055 0090 0160 0175 0204 0244 JLJ 0176 KYE 0053 0100 0216 KZU 0041 0101 0117 MIX 0125 0134 0157 0196 0203 0218 MNB 0019 0047 0123 0212 0277 0292 0304 MSR 0200 0255 NTR 0124 0155 0261 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 0019 0041 0045 0047 0053 0055 0075 0079 0080 0082 0084 0085 0090 0094 0095 0100 0101 0105 0107 0116 0117 0123 0124 0125 0126 0128 0129 0133 0134 0135 0136 0137 0139 0141 0147 0148 0149 0150 0151 0152 0154 0155 0156 001

0083 0212 0256 0277 0292 003 0157 0160 0170 0173 0175 0176 0180 0183 0184 0185 0187 0189 0190 0196 0199 0200 0203 0204 0208 0210 0211 0216 0218 0219 0220 0226 0227 0234 0235 0236 0239 0243 0244 0247 0249 0250 0255 0259 0261 0265 0274 0289 0299 0302 0304 002

(5) Configuration definition **CONF 001 Config. 001 is valid for passenger aircraft on which Modification No. 02611D02031 (FUSELAGE STRUCTURE - IMPROVE THE FATIGUE LIFE OF LONGITUDINAL LAP JOINTS OF OUTER SKIN) is not embodied.

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 2 6

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# @A300 SERVICE BULLETIN **CONF 002 Config. 002 is valid for passenger aircraft on which Modification No. 02611D02031 (FUSELAGE STRUCTURE - IMPROVE THE FATIGUE LIFE OF LONGITUDINAL LAP JOINTS OF OUTER SKIN) is embodied. **CONF 003 Config. 003 is valid for all the freighter aircraft given in the effectivity of this Service Bulletin as a standard configuration. (6) Material Effectivity **CONF 001 MATERIAL QTY PER A/C SEE NOTES Kit 530389D01R02 1 Kit 530389D02R01 1 Component COMPD01 1 Consumable CMLD01 As required Standard tool TOOLD01 2 **CONF 002 MATERIAL QTY PER A/C SEE NOTES Kit 530389D01R02 1 Kit 530389D03R01 1 Component COMPD01 1 Consumable CMLD01 As required Standard tool TOOLD01 2 **CONF 003 MATERIAL QTY PER A/C SEE NOTES Kit 530389D01R02 1 Kit 530389D04R02 1 Component COMPD01 1 Consumable CMLD01 As required Standard tool TOOLD01 2 **CONF ALL B. CONCURRENT REQUIREMENTS NOTE: Accomplishment of this Service Bulletin requires the prior or simultaneous accomplishment of the following Service Bulletin(s) or the equivalent production modification(s): Service Bulletin No. A300-53-0321

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 3 6

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# @A300 SERVICE BULLETIN C. REASON (1) History Some operators have reported cracks in the crossbeam at the junction with the cargo door actuator support beam. The damage was located on the outboard row of rivets on the crossbeam at FR23. The laboratory analysis has revealed that the cracks initiated in the fastener hole are propagated vertically. The design of the forward and aft cargo door attachment is similar, the crossbeams at FR22, FR23, FR61 and FR62 should be reinforced to avoid crack initiation. (2) Objective/Action This Service Bulletin details the procedure to install the reinforcement fittings and to relocate the brackets at the floor crossbeams at FR22, FR23, FR61 and FR62. NOTE: It is not necessary to accomplish the Inspection Service Bulletin No. A300-53-0390 before doing this Service Bulletin. This Service Bulletin can be accomplished directly as given in the accomplishment instruction. NOTE: To reach the mod advantages, this Service Bulletin is to be accomplished, if: - Service Bulletin No. A300-53-0320 has been previously accomplished, - none repair has been performed in the affected areas in accordance with SRM, All Operators Telex 53-07, Inspection Service Bulletin No. A300-53-0321 or Repair Approval Sheet (RAS). In case of existing repairs, the operators are requested to contact Airbus Repair Support before accomplishment of this Service Bulletin, for further instructions. (3) Advantages The accomplishment of this Service Bulletin will : - contribute to avoid the development of cracks, - cancel the inspection requirements in accordance with the Inspection Service Bulletin No. A300-53-0390. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to :

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# @A300 SERVICE BULLETIN **CONF 001 Task 530389-831-848-001: MODIFICATION (1) Remove the existing fasteners and brackets from the crossbeam at FR22 and FR23. (2) Rotating Probe Inspection at the crossbeam FR22 and FR23. (3) Install the reinforcement at the crossbeam at FR22 and FR23. (4) Remove the existing fasteners from the crossbeam FR61 and FR62. (5) Rotating Probe Inspection at the crossbeam FR61 and FR62. (6) Install the reinforcement and brackets at the crossbeam at FR61 and FR62. **CONF 002 Task 530389-831-848-001: MODIFICATION (1) Remove the existing fasteners from the crossbeam at FR22 and FR23. (2) Rotating Probe Inspection at the crossbeam at FR22 and FR23. (3) Install the reinforcement at the crossbeam at FR22 and FR23. (4) Remove the existing fasteners from the crossbeam FR61 and FR62. (5) Rotating Probe Inspection at the crossbeam FR61 and FR62. (6) Install the reinforcement and brackets at the crossbeam at FR61 and FR62. **CONF 003 Task 530389-831-848-001: MODIFICATION (1) Remove the existing fasteners and the brackets from the crossbeam at FR22 and FR23. (2) Rotating Probe Inspection at the crossbeam at FR22 and FR23. (3) Install the reinforcement and the brackets at the crossbeam at FR22 and FR23. (4) Remove the existing fasteners from the crossbeam FR61 and FR62. (5) Rotating Probe Inspection at the crossbeam FR61 and FR62. (6) Install the reinforcement and brackets at the crossbeam at FR61 and FR62.

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 5 6

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# @A300 SERVICE BULLETIN **CONF ALL E. COMPLIANCE (1) Classification RECOMMENDED: Service Bulletin recommended to be accomplished to prevent significant operational disruptions. (2) Accomplishment Timescale Accomplishment of this Service Bulletin is recommended at the earliest opportunity where manpower and facilities are available. F. APPROVAL The technical content of this document is approved under 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. Aircraft that listed in this Service Bulletin and have been converted to freighter aircraft may have a difference in the affected area. In this event, the operator should contact the relevant Customer Service to obtain the necessary information about the future/planned Service Bulletins for the converted aircraft. 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. **CONF 001 Task 530389-831-848-001: MODIFICATION Get Access 4.00 On Aircraft Remove the existing fasteners and brackets from the crossbeam at FR22 and FR23. 4.00 Rotating Probe Inspection at the crossbeam FR22 and FR23. 4.00 Install the reinforcement at the crossbeam at FR22 and FR23. 8.00 Remove the existing fasteners from the crossbeam FR61 and FR62. 3.00

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 6 6

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# @A300 SERVICE BULLETIN
Task 530389-831-848-001: MODIFICATION Rotating Probe Inspection at the crossbeam FR61 and FR62. 4.00 Install the reinforcement and brackets at the crossbeam at FR61 and FR62. 6.00 Tests 1.00 Close-Up 3.00 TOTAL MANHOURS 37.00 ELAPSED TIME (HOURS) 26.00 **CONF 002 Task 530389-831-848-001: MODIFICATION Get Access 4.00 On Aircraft Remove the existing fasteners from the crossbeam at FR22 and FR23. 4.00 Rotating Probe Inspection at the crossbeam at FR22 and FR23. 4.00 Install the reinforcement at the crossbeam at FR22 and FR23. 8.00 Remove the existing fasteners from the crossbeam FR61 and FR62. 3.00 Rotating Probe Inspection at the crossbeam FR61 and FR62. 4.00 Install the reinforcement and brackets at the crossbeam at FR61 and FR62. 6.00 Tests 1.00 Close-Up 3.00 TOTAL MANHOURS 37.00 ELAPSED TIME (HOURS) 26.00 **CONF 003 Task 530389-831-848-001: MODIFICATION Get Access 4.00 On Aircraft Remove the existing fasteners and the brackets from the crossbeam at FR22 and FR23. 4.00 Rotating Probe Inspection at the crossbeam at FR22 and FR23. 4.00 Install the reinforcement and the brackets at the crossbeam at FR22 and FR23. 6.00 Remove the existing fasteners from the crossbeam FR61 and FR62. 3.00 Rotating Probe Inspection at the crossbeam FR61 and FR62. 4.00 Install the reinforcement and brackets at the crossbeam at FR61 and FR62. 6.00
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# @A300 SERVICE BULLETIN
Task 530389-831-848-001: MODIFICATION Tests 1.00 Close-Up 3.00 TOTAL MANHOURS 35.00 ELAPSED TIME (HOURS) 26.00 **CONF ALL H. WEIGHT AND BALANCE **CONF 001 The weight and balance estimates given in this Service Bulletin are based on the Manufacturer’s Empty Weight (MEW) and do not include operator item’s. For the definition of MEW and operator’s items refer to Weight and Balance Manual (WBM) Chapter 1-00-07. Manufacturers Empty Weight +0.642 KG (+1.4153 LB) Effect on Balance +17.233 KGM (+124.646 LB.FT ) **CONF 002 The weight and balance estimates given in this Service Bulletin are based on the Manufacturer’s Empty Weight (MEW) and do not include operator item’s. For the definition of MEW and operator’s items refer to Weight and Balance Manual (WBM) Chapter 1-00-07. Manufacturers Empty Weight +0.574 KG (+1.2654 LB) Effect on Balance +16.172 KGM (+116.972 LB.FT ) **CONF 003 The weight and balance estimates given in this Service Bulletin are based on the Manufacturer’s Empty Weight (MEW) and do not include operator item’s. For the definition of MEW and operator’s items refer to Weight and Balance Manual (WBM) Chapter 1-00-07. Manufacturers Empty Weight +0.520 KG (+1.1463 LB) Effect on Balance +15.314 KGM (+110.766 LB.FT ) **CONF ALL I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES **CONF 001 Aircraft Maintenance Manual (AMM) 06-21-53 24-00-00 24-41-00 25-51-00 25-51-11 25-52-11 52-30-00 52-31-11 52-33-11 52-33-18 All Operators Telex (AOT) 53-07 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 8 6

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# @A300 SERVICE BULLETIN Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-33-11 20-33-33 20-55-00 Non Destructive Test Manual (NTM) 51-30-10 Service Bulletin (SB) A300-53-0320 A300-53-0321 A300-53-0390 Standards Manual (SM) Structural Repair Manual (SRM) 51-30-31 51-30-40 51-30-47 51-40-12 51-40-20 Weight and Balance Manual (WBM) Weight and Balance Manual (WBM) Chapter 1-00-07 **CONF 002 Aircraft Maintenance Manual (AMM) 06-21-53 24-00-00 24-41-00 25-51-00 25-51-11 25-52-11 52-30-00 52-31-11 52-33-11 52-33-18 All Operators Telex (AOT) 53-07 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-33-11 20-33-33 20-55-00 Non Destructive Test Manual (NTM) 51-30-10 Service Bulletin (SB) A300-53-0320 A300-53-0321 A300-53-0390 Standards Manual (SM) Structural Repair Manual (SRM) 51-27-11 51-30-31 51-30-40 51-30-47 51-40-12 51-40-20 Weight and Balance Manual (WBM) Weight and Balance Manual (WBM) Chapter 1-00-07 **CONF 003 Aircraft Maintenance Manual (AMM) 06-21-53 24-00-00 24-41-00 25-51-00 25-51-11 25-52-11 52-30-00 52-31-11 52-33-11 52-33-18 All Operators Telex (AOT) 53-07 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-33-11 20-33-33 20-55-00 Non Destructive Test Manual (NTM) 51-30-10 Service Bulletin (SB) A300-53-0320 A300-53-0321 A300-53-0390 Standards Manual (SM) Structural Repair Manual (SRM) 51-30-31 51-30-40 51-30-47 51-40-12 51-40-20 53-13-00 Weight and Balance Manual (WBM) Weight and Balance Manual (WBM) Chapter 1-00-07

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 9 6

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# @A300 SERVICE BULLETIN **CONF ALL K. PUBLICATION AFFECTED **CONF 001 Structural Repair Manual (SRM) 53-13-00 53-17-00 **CONF 002 Structural Repair Manual (SRM) 53-13-00 53-17-00 **CONF 003 Structural Repair Manual (SRM) 53-13-00 53-17-00 **CONF ALL L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 10 6

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# @A300 SERVICE BULLETIN 2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses Kit 530389D01R02 Kit 530389D02R01 Kit 530389D03R01 Kit 530389D04R02 Customers with aircraft shown in the effectivity of this Service Bulletin should send a purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is: AIRBUS Material, Logistics and Suppliers Weg beim Jaeger 150 D-22335 Hamburg Germany For ordering by internet: http://spares.airbus.com For SB Kits by fax: +49 40 50 76 25 90 For Spares by fax : +49 40 50 76 40 12 Component COMPD01 Parts to be procured from: B/E Aerospace Consumables Management GmbH Nordportbogen 6 D-22848 Norderstedt Germany Tel: +49 40 82 22 85 0 Fax: +49 40 82 22 85 31 00 5 (2) Price and Availability

Kit 530389D01R02 Cost 1,410.00 USD Availability 120 calendar days from receipt of order The Kit availability given above is the standard lead time from the date of your purchase order. If you require Kits before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. Kit 530389D02R01 Cost 1,410.00 USD Availability 120 calendar days from receipt of order The Kit availability given above is the standard lead time from the date of your purchase order. If you require Kits before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements.
DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 11 6

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# @A300 SERVICE BULLETIN The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. Kit 530389D03R01 Cost 953.00 USD Availability 120 calendar days from receipt of order The Kit availability given above is the standard lead time from the date of your purchase order. If you require Kits before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. Kit 530389D04R02 Cost 1,020.00 USD Availability 120 calendar days from receipt of order The Kit availability given above is the standard lead time from the date of your purchase order. If you require Kits before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. B. INDUSTRY SUPPORT INFORMATION AIRBUS will provide a 15% reduction to the applicable sales prices given in the paragraph ’Price and Availability’ for orders placed before 31st of December 2015. C. LIST OF COMPONENTS Kit 530389D01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 4 ASNA2528-3 35 NUT 5 ASNA2528-3A 15 NUT 6 EN6115K3-3 19 BOLT 10 EN6115K3X5 16 BOLT 12 EN6115K3AX5 4 BOLT 16 DAN11-6X 7 COLLAR 36 EN6081D4-07 2 RIVET 38 EN6081D6-09 4 RIVET 40 A5327429220000 1 PLATE 41 A5327429220600 1 PLATE 42 A5327415220600 1 ANGLE 43 A5327415220800 1 ANGLE 44 MS21051L3 1 NUT 45 ABS0337-01A 1 RECEPTCL 50 EN6069AD3-05 4 RIVET DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 12 6

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# @A300 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 51 EN6115K3A5 10 BOLT 52 EN6115K3AX3 1 BOLT 53 EN6069D4-05 1 RIVET 55 DAN5-6-6X 7 PIN 56 DAN5-6-6Y 7 PIN 57 DAN11-6Y 7 COLLAR NOTE: If you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin, refer to Standards Manual (SM). The SM will give you the correct part number to part number relationship. Kit 530389D02R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 1 A5378103421000 1 RNFRCMNT 2 A5378103421200 1 RNFRCMNT 3 A5378103421800 1 RNFRCMNT 4 ASNA2528-3 32 NUT 5 ASNA2528-3A 18 NUT 6 EN6115K3-3 10 BOLT 7 EN6115K3-4 4 BOLT 8 EN6115K3-5 2 BOLT 9 EN6115K3X4 2 BOLT 10 EN6115K3X5 14 BOLT 11 EN6115K3AX4 2 BOLT 12 EN6115K3AX5 4 BOLT 13 EN6115K3AX6 2 BOLT 14 EN6115K3A6 10 BOLT 15 DAN5-6-4X 2 PIN 16 DAN11-6X 9 COLLAR 55 DAN5-6-6X 7 PIN NOTE: If you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin, refer to Standards Manual (SM). The SM will give you the correct part number to part number relationship. Kit 530389D03R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 4 ASNA2528-3 32 NUT 5 ASNA2528-3A 14 NUT 6 EN6115K3-3 16 BOLT 9 EN6115K3X4 2 BOLT 10 EN6115K3X5 14 BOLT DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 13 6

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# @A300 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 12 EN6115K3AX5 2 BOLT 13 EN6115K3AX6 2 BOLT 14 EN6115K3A6 10 BOLT 16 DAN11-6X 7 COLLAR 20 A5378103420600 1 RNFRCMNT 21 A5378103422000 1 RNFRCMNT 55 DAN5-6-6X 7 PIN NOTE: If you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin, refer to Standards Manual (SM). The SM will give you the correct part number to part number relationship. Kit 530389D04R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 4 ASNA2528-3 28 NUT 5 ASNA2528-3A 8 NUT 8 EN6115K3-5 2 BOLT 10 EN6115K3X5 6 BOLT 13 EN6115K3AX6 2 BOLT 16 DAN11-6X 7 COLLAR 22 A5378103423400 1 RNFRCMNT 23 MS21076L4N 2 NUT 25 A5377469720000 1 ANGLE 30 EN6115K3X6 10 BOLT 31 EN6115K3X7 10 BOLT 32 EN6115K3AX7 6 BOLT 35 EN6081D3-06 4 RIVET 36 EN6081D4-07 4 RIVET 37 EN6081D5-07 4 RIVET 38 EN6081D6-07 18 RIVET 55 DAN5-6-6X 7 PIN 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.

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 14 6

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# @A300 SERVICE BULLETIN D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Corrosion Inhibiting Brush Consistency 09-013 As required Cleaning Solvent 11-016 As required Solvent General Purpose 11-026 As required Anti-Corrosion Primer (polyurethane) 16-001 As required Polyurethane Topcoat Grey (for Internal Applic.) 16-002 As required Wash Primer 16-020 As required (2) Components Component COMPD01 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 70 NAS1801-3-26 1 SCREW 71 NAS1149D0332K 2 WASHER 72 NSA5527-03-01D 1 SPACER 73 NSA5527-03-08D 1 SPACER 74 MS21042-3 1 NUT 75 MS21919WCH3 1 CLAMP 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: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 15 6

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# @A300 SERVICE BULLETIN (2) Tools Standard tool TOOLD01 ITEM TOOL N ̊ TOOL NAME QTY SEE NOTES 98A52307523000 Support Struts - FWD and AFT Cargo Compartment Doors 2 (1) NOTE (1): The safety equipments are operator supplied. (3) Special Tools Fatigue Technology Incorporated (FTI) has allocated the following tool kit number for cold working, refer to FTI Tooling List No. FTI-A300-53-0389-1. NOTE: For the definition of capital, durable and expandable tools, refer to SIL51-012. - Capital Tool Kit No : FTI-FT20-LB20-CAP . The capital tools provided in this kit are not specific to this Service Bulletin and are normally already available in operator’s stock as a long term investment or can be loaned from FTI. - Durable Tool Kit No : DK-A300530389-1 . The capital tools provided in this kit are not specific to this Service Bulletin and are normally already available in operator’s stock as a long term investment or can be loaned from FTI. - Expendable Tool Kit No : EK-A300530389-1 . The capital tools provided in this kit are not specific to this Service Bulletin and are normally already available in operator’s stock as a long term investment or can be loaned from FTI. Operators interested in obtaining the FTI tool kit should contact: Fatigue Technology Inc. 401 ANDOVER PARK EAST SEATTLE, WA 98188-2868 USA E-mail: sales@fatiguetech.com E-mail: aog@fatiguetech.com Phone: (1) 206 246 2010 Fax: (1) 206 244 9886

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 16 6

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# @A300 SERVICE BULLETIN 3. ACCOMPLISHMENT INSTRUCTIONS Task 530389-831-848-001 - MODIFICATION WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO THIS : - PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS NECESSARY ON ELECTRICAL WIRING AND COMPONENTS - REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER CONTAMINATION. THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION. IF THERE IS CONTAMINATION REFER TO ESPM 20-55-00. Task Associated Data **CONF 001 Zone 130 150 Manpower TOTAL MANHOURS 37.00 ELAPSED TIME (HOURS) 26.00 **CONF 002 Zone 130 150 Manpower TOTAL MANHOURS 37.00 ELAPSED TIME (HOURS) 26.00 **CONF 003 Zone 130 150 Manpower TOTAL MANHOURS 35.00 ELAPSED TIME (HOURS) 26.00 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 17 6

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# @A300 SERVICE BULLETIN **CONF ALL A. GENERAL **CONF 001 (1) Subtask 530389-910-201-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Corrosion Inhibiting Brush Consistency 09-013 As required Cleaning Solvent 11-016 As required Anti-Corrosion Primer (polyurethane) 16-001 As required Polyurethane Topcoat Grey (for Internal Applic.) 16-002 As required Wash Primer 16-020 As required References Aircraft Maintenance Manual (AMM) 06-21-53, Page Block 001 Consumable Material List (CML) Structural Repair Manual (SRM) 51-30-31 51-30-40 51-40-12 51-40-20 (a) If the length of any fastener specified in this Service Bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. (b) For the specification of materials (Mat. No.) given in this Service Bulletin (Refer to the Consumable Materials List (CML)). (c) For the location of access panels (Refer to AMM 06-21-53, Page Block 001). (d) Remove the old sealant with non-metallic scrapers and a stiff brush. (e) Drill and deburr the rivet holes (Refer to SRM 51-30-40).

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 18 6

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# @A300 SERVICE BULLETIN (f) After drilling and cutting, apply Anti-Corrosion Primer (polyurethane) 16-001 As required

and Polyurethane Topcoat Grey (for Internal Applic.) 16-002 As required
and Wash Primer 16-020 As required

and (Refer to SRM 51-40-12) on the affected areas. (g) Clean the reworked surfaces and the surfaces to be sealed with : Cleaning Solvent 11-016 As required (h) Apply Corrosion Inhibiting Brush Consistency 09-013 As required

on all mating surfaces. (i) Install rivets and pins on all mating surfaces with : Corrosion Inhibiting Brush Consistency 09-013 As required (j) For alternative and substitute fasteners (Refer to SRM 51-30-31). (k) For the procedure to use sealant (Refer to SRM 51-40-20). (l) Apply a sealant bead with : Corrosion Inhibiting Brush Consistency 09-013 As required (m) Install only Hi-Lok fasteners with the interference fit in cold expanded holes. (2) Subtask 530389-839-201-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin.

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 19 6

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# @A300 SERVICE BULLETIN **CONF 002 (1) Subtask 530389-910-201-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Corrosion Inhibiting Brush Consistency 09-013 As required Cleaning Solvent 11-016 As required Anti-Corrosion Primer (polyurethane) 16-001 As required Polyurethane Topcoat Grey (for Internal Applic.) 16-002 As required Wash Primer 16-020 As required References Aircraft Maintenance Manual (AMM) 06-21-53, Page Block 001 Consumable Material List (CML) Structural Repair Manual (SRM) 51-30-31 51-30-40 51-40-12 51-40-20 (a) If the length of any fastener specified in this Service Bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. (b) For the specification of materials (Mat. No.) given in this Service Bulletin (Refer to the Consumable Materials List (CML)). (c) For the location of access panels (Refer to AMM 06-21-53, Page Block 001). (d) Remove the old sealant with non-metallic scrapers and a stiff brush. (e) Drill and deburr the rivet holes (Refer to SRM 51-30-40). (f) After drilling and cutting, apply Anti-Corrosion Primer (polyurethane) 16-001 As required

and DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 20 6

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# @A300 SERVICE BULLETIN Polyurethane Topcoat Grey (for Internal Applic.) 16-002 As required
and Wash Primer 16-020 As required

and (Refer to SRM 51-40-12) on the affected areas. (g) Clean the reworked surfaces and the surfaces to be sealed with : Cleaning Solvent 11-016 As required (h) Apply Corrosion Inhibiting Brush Consistency 09-013 As required

on all mating surfaces. (i) Install rivets and pins on all mating surfaces with : Corrosion Inhibiting Brush Consistency 09-013 As required (j) For alternative and substitute fasteners (Refer to SRM 51-30-31). (k) For the procedure to use sealant (Refer to SRM 51-40-20). (l) Apply a sealant bead with : Corrosion Inhibiting Brush Consistency 09-013 As required (m) Install only Hi-Lok fasteners with the interference fit in cold expanded holes. (2) Subtask 530389-839-201-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 003 (1) Subtask 530389-910-201-001 - Standard Practices Manpower Resources Skills NON SPECIFIC

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 21 6

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# @A300 SERVICE BULLETIN Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Corrosion Inhibiting Brush Consistency 09-013 As required Cleaning Solvent 11-016 As required Anti-Corrosion Primer (polyurethane) 16-001 As required Polyurethane Topcoat Grey (for Internal Applic.) 16-002 As required Wash Primer 16-020 As required References Aircraft Maintenance Manual (AMM) 06-21-53, Page Block 001 Consumable Material List (CML) Structural Repair Manual (SRM) 51-30-31 51-30-40 51-40-12 51-40-20 (a) If the length of any fastener specified in this Service Bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. (b) For the specification of materials (Mat. No.) given in this Service Bulletin (Refer to the Consumable Materials List (CML)). (c) For the location of access panels (Refer to AMM 06-21-53, Page Block 001). (d) Remove the old sealant with non-metallic scrapers and a stiff brush. (e) Drill and deburr the rivet holes (Refer to SRM 51-30-40). (f) After drilling and cutting, apply Anti-Corrosion Primer (polyurethane) 16-001 As required

and Polyurethane Topcoat Grey (for Internal Applic.) 16-002 As required
and
DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 22 6

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# @A300 SERVICE BULLETIN Wash Primer 16-020 As required

and (Refer to SRM 51-40-12) on the affected areas. (g) Clean the reworked surfaces and the surfaces to be sealed with : Cleaning Solvent 11-016 As required (h) Apply Corrosion Inhibiting Brush Consistency 09-013 As required

on all mating surfaces. (i) Install rivets and pins on all mating surfaces with : Corrosion Inhibiting Brush Consistency 09-013 As required (j) For alternative and substitute fasteners (Refer to SRM 51-30-31). (k) For the procedure to use sealant (Refer to SRM 51-40-20). (l) Apply a sealant bead with : Corrosion Inhibiting Brush Consistency 09-013 As required (m) Install only Hi-Lok fasteners with the interference fit in cold expanded holes. (2) Subtask 530389-839-201-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF ALL B. PREPARATION **CONF 001 (1) Subtask 530389-941-201-001 - Preparation Manpower Resources Skills NON SPECIFIC

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 23 6

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# @A300 SERVICE BULLETIN Material necessary to do the job Standard tool TOOLD01 ITEM TOOL N ̊ TOOL NAME QTY SEE NOTES 98A52307523000 Support Struts - FWD and AFT Cargo Compartment Doors 2 (1)
NOTE (1): The safety equipments are operator supplied. References Aircraft Maintenance Manual (AMM) 06-21-53, Page Block 001 24-00-00, Page Block 301 24-41-00, Page Block 301 25-51-00, Page Block 401 25-51-11, Page Block 401 25-52-11, Page Block 401 52-30-00, Page Block 301 52-33-18, Page Block 401 52-33-18, Page Block 401 (a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page Block 301). (b) Put access platform(s) in position (c) De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page Block 301). (d) Open the FWD cargo-compartment door 811 (Refer to AMM 52-30-00, Page Block 301). (e) Open the AFT cargo-compartment door 812 (Refer to AMM 52-30-00, Page Block 301). (f) Disconnect the door actuator from the FWD and AFT cargo-compartment doors and install : 98A52307523000 Support Struts - FWD and AFT Cargo Compartment Doors 2
Refer to AMM 52-30-00, Page Block 301. NOTE: Do not use the actuator safety lock(s).

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 24 6

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# @A300 SERVICE BULLETIN (g) Open, safety and tag these circuit breaker(s) : PANEL DESIGNATION FIN LOCATION SEE NOTES 128VU HYDRAULIC/ACCU PRESS CTL AND CARGO PUMP 7GX 803/C11 101VU ELEC HYD PUMP 23GX ALT2 NOTE: The location of the circuit breaker(s) can be different from the location given in the table. (h) Remove and retain the FWD cargo-compartment ceiling panels as necessary (Refer toAMM 25-51-11, Page Block 401 and AMM 06-21-53, Page Block 001). (i) Remove the door actuator lining between FR22 and FR23. (j) Remove the FWD cargo-compartment actuator from the actuator support beam (Refer to AMM 52-33-18, Page Block 401). (k) Remove and retain the AFT cargo-compartment ceiling panels as necessary (Refer to AMM 25-52-11, Page Block 401 and AMM 06-21-53, Page Block 001). (l) Remove the door actuator lining between FR61 and FR62. (m) Remove the AFT cargo-compartment actuator from the actuator support beam (Refer to AMM 52-33-18, Page Block 401). **CONF 002 (1) Subtask 530389-941-201-001 - Preparation Manpower Resources Skills NON SPECIFIC Material necessary to do the job Standard tool TOOLD01 ITEM TOOL N ̊ TOOL NAME QTY SEE NOTES 98A52307523000 Support Struts - FWD and AFT Cargo Compartment Doors 2 (1)
NOTE (1): The safety equipments are operator supplied.

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 25 6

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# @A300 SERVICE BULLETIN
References Aircraft Maintenance Manual (AMM) 06-21-53, Page Block 001 24-00-00, Page Block 301 24-41-00, Page Block 301 25-51-00, Page Block 401 25-51-11, Page Block 401 25-52-11, Page Block 401 52-30-00, Page Block 301 52-33-18, Page Block 401 52-33-18, Page Block 401 (a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page Block 301). (b) Put access platform(s) in position (c) De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page Block 301). (d) Open the FWD cargo-compartment door 811 (Refer to AMM 52-30-00, Page Block 301). (e) Open the AFT cargo-compartment door 812 (Refer to AMM 52-30-00, Page Block 301). (f) Disconnect the door actuator from the FWD and AFT cargo-compartment doors and install : 98A52307523000 Support Struts - FWD and AFT Cargo Compartment Doors 2
Refer to AMM 52-30-00, Page Block 301. NOTE: Do not use the actuator safety lock(s). (g) Open, safety and tag these circuit breaker(s) : PANEL DESIGNATION FIN LOCATION SEE NOTES 128VU HYDRAULIC/ACCU PRESS CTL AND CARGO PUMP 7GX 803/C11 101VU ELEC HYD PUMP 23GX ALT2 NOTE: The location of the circuit breaker(s) can be different from the location given in the table. (h) Remove and retain the FWD cargo-compartment ceiling panels as necessary (Refer toAMM 25-51-11, Page Block 401 and AMM 06-21-53, Page Block 001). (i) Remove the door actuator lining between FR22 and FR23.
DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 26 6

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# @A300 SERVICE BULLETIN (j) Remove the FWD cargo-compartment actuator from the actuator support beam (Refer to AMM 52-33-18, Page Block 401). (k) Remove and retain the AFT cargo-compartment ceiling panels as necessary (Refer to AMM 25-52-11, Page Block 401 and AMM 06-21-53, Page Block 001). (l) Remove the door actuator lining between FR61 and FR62. (m) Remove the AFT cargo-compartment actuator from the actuator support beam (Refer to AMM 52-33-18, Page Block 401). **CONF 003 (1) Subtask 530389-941-201-001 - Preparation Manpower Resources Skills NON SPECIFIC Material necessary to do the job Standard tool TOOLD01 ITEM TOOL N ̊ TOOL NAME QTY SEE NOTES 98A52307523000 Support Struts - FWD and AFT Cargo Compartment Doors 2 (1)
NOTE (1): The safety equipments are operator supplied. References Aircraft Maintenance Manual (AMM) 06-21-53, Page Block 001 24-00-00, Page Block 301 24-41-00, Page Block 301 25-51-00, Page Block 401 25-51-11, Page Block 401 25-52-11, Page Block 401 52-30-00, Page Block 301 52-33-18, Page Block 401 52-33-18, Page Block 401 (a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page Block 301). (b) Put access platform(s) in position (c) De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page Block 301). (d) Open the FWD cargo-compartment door 811 (Refer to AMM 52-30-00, Page Block 301). (e) Open the AFT cargo-compartment door 812 (Refer to AMM 52-30-00, Page Block 301). DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 27 6

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# @A300 SERVICE BULLETIN (f) Disconnect the door actuator from the FWD and AFT cargo-compartment doors and install : 98A52307523000 Support Struts - FWD and AFT Cargo Compartment Doors 2
Refer to AMM 52-30-00, Page Block 301. NOTE: Do not use the actuator safety lock(s). (g) Open, safety and tag these circuit breaker(s) : PANEL DESIGNATION FIN LOCATION SEE NOTES 128VU HYDRAULIC/ACCU PRESS CTL AND CARGO PUMP 7GX 803/C11 101VU ELEC HYD PUMP 23GX ALT2 NOTE: The location of the circuit breaker(s) can be different from the location given in the table. (h) Remove and retain the FWD cargo-compartment ceiling panels as necessary (Refer toAMM 25-51-11, Page Block 401 and AMM 06-21-53, Page Block 001). (i) Remove the door actuator lining between FR22 and FR23. (j) Remove the FWD cargo-compartment actuator from the actuator support beam (Refer to AMM 52-33-18, Page Block 401). (k) Remove and retain the AFT cargo-compartment ceiling panels as necessary (Refer to AMM 25-52-11, Page Block 401 and AMM 06-21-53, Page Block 001). (l) Remove the door actuator lining between FR61 and FR62. (m) Remove the AFT cargo-compartment actuator from the actuator support beam (Refer to AMM 52-33-18, Page Block 401). **CONF ALL C. PROCEDURE NOTE: It is not necessary to accomplish the Inspection Service Bulletin No. A300-53-0390 before doing this Service Bulletin. This Service Bulletin can be accomplished directly as given in the accomplishment instruction. NOTE: To reach the mod advantages, this Service Bulletin is to be accomplished, if: - Service Bulletin No. A300-53-0320 has been previously accomplished, - none repair has been performed in the affected areas in accordance with SRM, All Operators Telex 53-07, Inspection Service Bulletin No. A300-53-0321 or Repair Approval Sheet (RAS). DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 28 6

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# @A300 SERVICE BULLETIN In case of existing repairs, the operators are requested to contact Airbus Repair Support before accomplishment of this Service Bulletin, for further instructions. **CONF 001 (1) Subtask 530389-831-201-001 - Remove the existing fasteners and brackets from the crossbeam at FR22 and FR23. Work Zones and Access Panels Zone Access/Work location 130 Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required References Consumable Material List (CML) Fig. A-GBAAA Removal of the Existing Fasteners from the Crossbeam at FR22 and FR23 Sheet 01 Sheet 02 Sheet 03 Sheet 04 WARNING: BEFORE YOU REMOVE ANY RIVETS FROM THE CROSSBEAM FR22 OR FR23, ENSURE THAT THE FORWARD DOOR ACTUATOR IS DISCONNECTED FROM THE ACTUATOR BEAM. (a) Remove the existing fasteners and brackets from the crossbeam at FR22. 1 Remove the fasteners and the bracket : Refer to Fig. A-GBAAA Sheet 02, Detail B, and Fig. A-GBAAA Sheet 03, Detail D 1 Bracket A5377420420000 Item (17) Discard 2 Clean the fasteners holes and the adjacent area with : Solvent General Purpose 11-026 As required

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 29 6

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# @A300 SERVICE BULLETIN (b) If pins are installed in the actuator beam at FR22, remove them. 1 Remove the existing pins : Refer to Fig. A-GBAAA Sheet 02, Detail B, and Fig. A-GBAAA Sheet 04, Detail F 2 Clean the pin holes and the adjacent area with : Solvent General Purpose 11-026 As required (c) Remove the fasteners from the crossbeam at FR23. 1 Remove the fasteners : Refer to Fig. A-GBAAA Sheet 02, Detail C, and Fig. A-GBAAA Sheet 03, Detail E 2 Clean the fastener holes and the adjacent area with : Solvent General Purpose 11-026 As required (2) Subtask 530389-832-201-001 - Rotating Probe Inspection at the crossbeam FR22 and FR23. Work Zones and Access Panels Zone Access/Work location 130 Manpower Resources Manhours 4.00 Minimum number of person 1 Subtask elapsed time 4.00 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-30-10 PART 1 Fig. A-GBCAA Installation of the Reinforcement at the Crossbeam at FR22 and FR23 Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 (a) Rotating Probe Inspection at the crossbeam at FR22. 1 Do a rotating probe inspection of the fastener holes at FR22 (Refer to NTM 51-30-10 PART 1). Refer to Fig. A-GBCAA Sheet 03, Detail D DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 30 6

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# @A300 SERVICE BULLETIN

a If no crack(s) are found : <1> - Refer to para. (3)(a). b If crack(s) are found : <1> Contact AIRBUS for further instructions. (b) Rotating Probe Inspection at the crossbeam FR23. 1 Do a rotating probe inspection of the fastener holes at FR23 (Refer to NTM 51-30-10 PART 1). Refer to Fig. A-GBCAA Sheet 04, Detail F a If no crack(s) are found : <1> - Refer to para. (3)(c). b If crack(s) are found : <1> Contact AIRBUS for further instructions. (3) Subtask 530389-831-203-001 - Install the reinforcement at the crossbeam at FR22 and FR23. Work Zones and Access Panels Zone Access/Work location 130 Manpower Resources Manhours 8.00 Minimum number of person 2 Subtask elapsed time 4.00 Skills AIRFRAME Material necessary to do the job Kit 530389D02R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 A5378103421000 1 RNFRCMNT 2 A5378103421200 1 RNFRCMNT 3 A5378103421800 1 RNFRCMNT 4 ASNA2528-3 32 NUT 5 ASNA2528-3A 18 NUT 6 EN6115K3-3 10 BOLT 7 EN6115K3-4 4 BOLT 8 EN6115K3-5 2 BOLT 9 EN6115K3X4 2 BOLT 10 EN6115K3X5 14 BOLT DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 31 6

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# @A300 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 11 EN6115K3AX4 2 BOLT 12 EN6115K3AX5 4 BOLT 13 EN6115K3AX6 2 BOLT 14 EN6115K3A6 10 BOLT 15 DAN5-6-4X 2 PIN 16 DAN11-6X 9 COLLAR 55 DAN5-6-6X 7 PIN Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required References Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-33-11 20-33-33 Structural Repair Manual (SRM) 51-30-47 51-40-20 Fig. A-GBCAA Installation of the Reinforcement at the Crossbeam at FR22 and FR23 Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 (a) Install the reinforcement at the crossbeam at FR22. Refer to Fig. A-GBCAA Sheet 02, Detail B, Fig. A-GBCAA Sheet 03, Detail E, and Fig. A-GBCAA Sheet 05 1 At FR22 install temporarily : Refer to Fig. A-GBCAA Sheet 02, Detail B, Fig. A-GBCAA Sheet 03, Detail E 1 Reinforcement A5378103421000 Item 1 1 Reinforcement A5378103421200 Item 2 2 If no ’cold expansion’ drill the fastener holes and open to final dimension. 3 If ’cold expansion’ transfer drill the fastener holes and open to the specific starting hole diameter. 4 Cold expand the specified fastener holes on the reinforcement and structure where no cracks were found. Refer to SRM 51-30-47
DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 32 6

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# @A300 SERVICE BULLETIN Refer to FTI Tooling List No. FTI-A300-53-0389-1 Refer to Fig. A-GBCAA Sheet 03, Detail E, and Fig. A-GBCAA Sheet 05 5 Ream the specified fastener holes on the reinforcement and structure with the correct gage finish reamer. Refer to Fig. A-GBCAA Sheet 03, Detail E, and Fig. A-GBCAA Sheet 05 6 Remove the temporarily installed Item 1 and Item 2. 7 Clean the fastener holes with : Solvent General Purpose 11-026 As required 8 Install the reinforcement, Item 1, and reinforcement, Item 2, with : Refer to Fig. A-GBCAA Sheet 03, Detail E, and Fig. A-GBCAA Sheet 05 Refer to SRM 51-40-20 22 Nut ASNA2528-3 Item 4 4 Nut ASNA2528-3A Item 5 4 Bolt EN6115K3-4 Item 7 2 Bolt EN6115K3-5 Item 8 2 Bolt EN6115K3X4 Item 9 14 Bolt EN6115K3X5 Item 10 4 Bolt EN6115K3AX5 Item 12 2 Pin DAN5-6-4X Item 15 2 Collar DAN11-6X Item 16 (b) If nominal size pins have been removed from the actuator beam at FR22, install new 1st oversize pins. Refer to Fig. A-GBCAA Sheet 02, Detail B, Fig. A-GBCAA Sheet 05 and Fig. AGBCAA Sheet 06, Detail H 1 Install : 7 Pin DAN5-6-6X Item 55 7 Collar DAN11-6X Item 16

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 33 6

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# @A300 SERVICE BULLETIN (c) Install the reinforcement at the crossbeam at FR23. Refer to Fig. A-GBCAA Sheet 04, Detail G, and Fig. A-GBCAA Sheet 05 1 At FR23 install temporarily : 1 Reinforcement A5378103421800 Item 3 2 If no ’cold expansion’ drill the fastener holes and open to final dimension. 3 If ’cold expansion’ transfer drill the fastener holes and open to the specific starting hole diameter. 4 Cold expand the specified fastener holes on the reinforcement and structure where no cracks were found. Refer to SRM 51-30-47 Refer to FTI Tooling List No. FTI-A300-53-0389-1 Refer to Fig. A-GBCAA Sheet 04, Detail G, and Fig. A-GBCAA Sheet 05 5 Ream the specified fastener holes on the reinforcement and structure with the correct gage finish reamer. Refer to Fig. A-GBCAA Sheet 04, Detail G, and Fig. A-GBCAA Sheet 05 6 Remove the temporarily installed Item 3. 7 Clean the fastener holes with : Solvent General Purpose 11-026 As required 8 Install the reinforcement, Item 3, with : Refer to Fig. A-GBCAA Sheet 02, Detail C, Fig. A-GBCAA Sheet 04, Detail G, and Fig. A-GBCAA Sheet 05 Refer to SRM 51-40-20 10 Nut ASNA2528-3 Item 4 14 Nut ASNA2528-3A Item 5 10 Bolt EN6115K3-3 Item 6 2 Bolt EN6115K3AX4 Item 11 2 Bolt EN6115K3AX6 Item 13 10 Bolt EN6115K3A6 Item 14

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 34 6

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# @A300 SERVICE BULLETIN (d) Perform minor amendment of screws, spacers and split conduits (Refer to ESPM 20-33-11 and ESPM 20-33-33). (4) Subtask 530389-831-205-001 - Remove the existing fasteners from the crossbeam FR61 and FR62. Work Zones and Access Panels Zone Access/Work location 150 Manpower Resources Manhours 3.00 Minimum number of person 2 Subtask elapsed time 1.50 Skills AIRFRAME Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required References Consumable Material List (CML) Fig. A-GBNAA Removal of the Existing Rivets from the Crossbeam at FR61 and FR62 Sheet 01 Sheet 02 Sheet 03 Sheet 04 WARNING: BEFORE YOU REMOVE ANY RIVETS FROM THE CROSSBEAM FR61 OR FR62, ENSURE THAT THE AFTER DOOR ACTUATOR IS DISCONNECTED FROM THE ACTUATOR BEAM. (a) Remove the existing fasteners from the crossbeam FR61. 1 Remove the existing fasteners : Refer to Fig. A-GBNAA Sheet 02, Detail B, and Fig. A-GBNAA Sheet 03, Detail D 2 Clean the fasteners holes and the adjacent area with : Solvent General Purpose 11-026 As required

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 35 6

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# @A300 SERVICE BULLETIN (b) If pins are installed in the actuator beam at FR61, remove them. 1 Remove the existing pins : Refer to Fig. A-GBNAA Sheet 02, Detail B, and Fig. A-GBNAA Sheet 04, Detail F 2 Clean the pin holes and the adjacent area with : Solvent General Purpose 11-026 As required (c) Remove the existing fasteners from the crossbeam FR62. 1 Remove the bracket, the receptacle and the fasteners : Refer to Fig. A-GBNAA Sheet 02, Detail C, and Fig. A-GBNAA Sheet 03, Detail E 1 Bracket A2557309120600 Item (43) Discard 1 Nut NAS1068C3 Item (44) Discard 1 Receptacle DAN367-01 Item (45) Discard 2 Clean the fastener holes and the adjacent area with : Solvent General Purpose 11-026 As required (5) Subtask 530389-831-206-001 - Rotating Probe Inspection at the crossbeam FR61 and FR62. Work Zones and Access Panels Zone Access/Work location 150 Manpower Resources Manhours 4.00 Minimum number of person 1 Subtask elapsed time 4.00 Skills AIRFRAME References Consumable Material List (CML) Non Destructive Test Manual (NTM) 51-30-10 PART 1

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 36 6

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# @A300 SERVICE BULLETIN
References Fig. A-GBPAA Installation of the Reinforcement at the Crossbeam at FR61 and FR62 Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 (a) Rotating Probe Inspection at the crossbeam at FR61. 1 Do a rotating probe inspection of the fastener holes at FR61 (Refer to NTM 51-30-10 PART 1). Refer to Fig. A-GBPAA Sheet 03, Detail D a If no crack(s) are found : <1> - Refer to para. (6)(a). b If crack(s) are found : <1> Contact AIRBUS for further instructions. (b) Rotating Probe Inspection at the crossbeam at FR62. 1 Do a rotating probe inspection of the fastener holes at FR62 (Refer to NTM 51-30-10 PART 1). Refer to Fig. A-GBPAA Sheet 04, Detail F a If no crack(s) are found : <1> - Refer to para. (6)(c). b If crack(s) are found : <1> Contact AIRBUS for further instructions. (6) Subtask 530389-831-207-001 - Install the reinforcement and brackets at the crossbeam at FR61 and FR62. Work Zones and Access Panels Zone Access/Work location 150 Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 37 6

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# @A300 SERVICE BULLETIN Material necessary to do the job Kit 530389D01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 4 ASNA2528-3 35 NUT 5 ASNA2528-3A 15 NUT 6 EN6115K3-3 19 BOLT 10 EN6115K3X5 16 BOLT 12 EN6115K3AX5 4 BOLT 16 DAN11-6X 7 COLLAR 36 EN6081D4-07 2 RIVET 38 EN6081D6-09 4 RIVET 40 A5327429220000 1 PLATE 41 A5327429220600 1 PLATE 42 A5327415220600 1 ANGLE 43 A5327415220800 1 ANGLE 44 MS21051L3 1 NUT 45 ABS0337-01A 1 RECEPTCL 50 EN6069AD3-05 4 RIVET 51 EN6115K3A5 10 BOLT 52 EN6115K3AX3 1 BOLT 53 EN6069D4-05 1 RIVET 55 DAN5-6-6X 7 PIN 56 DAN5-6-6Y 7 PIN 57 DAN11-6Y 7 COLLAR Component COMPD01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 70 NAS1801-3-26 1 SCREW 71 NAS1149D0332K 2 WASHER 72 NSA5527-03-01D 1 SPACER 73 NSA5527-03-08D 1 SPACER 74 MS21042-3 1 NUT 75 MS21919WCH3 1 CLAMP Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required References Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-33-11 20-33-33 Structural Repair Manual (SRM) 51-30-47
DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 38 6

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# @A300 SERVICE BULLETIN
References Fig. A-GBPAA Installation of the Reinforcement at the Crossbeam at FR61 and FR62 Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 (a) Install the reinforcement at the crossbeam at FR61. Refer to Fig. A-GBPAA Sheet 02, Detail B, Fig. A-GBPAA Sheet 03, Detail E, and Fig. A-GBPAA Sheet 05 1 At FR61 install temporarily : 1 Reinforcement A5327429220000 Item 40 2 If no ’cold expansion’ drill the fastener holes and open to final dimension. 3 If ’cold expansion’ transfer drill the fastener holes and open to the specific starting hole diameter. 4 Cold expand the specified fastener holes on the reinforcement and structure where no cracks were found. Refer to SRM 51-30-47 Refer to FTI Tooling List No. FTI-A300-53-0389-1 Refer to Fig. A-GBPAA Sheet 03, Detail E, and Fig. A-GBPAA Sheet 05 5 Ream the specified fastener holes on the reinforcement and structure with the correct gage finish reamer. Refer to Fig. A-GBPAA Sheet 03, Detail E, and Fig. A-GBPAA Sheet 05 6 Remove the temporarily installed Item 40. 7 Clean the fastener holes with : Solvent General Purpose 11-026 As required 8 Install the reinforcement, Item 40, with : 27 Nut ASNA2528-3 Item 4 3 Nut ASNA2528-3A Item 5 11 Bolt EN6115K3-3 Item 6 16 Bolt EN6115K3X5 Item 10
DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 39 6

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# @A300 SERVICE BULLETIN
2 Bolt EN6115K3AX5 Item 12 1 Bolt EN6115K3AX3 Item 52 (b) If pins have been removed from the actuator beam at FR61, install new pins. Refer to Fig. A-GBPAA Sheet 02, Detail B, Fig. A-GBPAA Sheet 05 and Fig. AGBPAA Sheet 06, Detail H 1 If nominal size pins have been removed from the actuator beam at FR61, install new 1st oversize pins. a Install : 7 Pin DAN5-6-6X Item 55 7 Collar DAN11-6X Item 16 2 If 1st oversize pins have been removed from the actuator beam at FR61, install new 2nd oversize pins. a Install : 7 Pin DAN5-6-6Y Item 56 7 Collar DAN11-6Y Item 57 (c) Install the reinforcement and brackets at the crossbeam at FR62. Refer to Fig. A-GBPAA Sheet 02, Detail C, Fig. A-GBPAA Sheet 04, Detail G, and Fig. A-GBPAA Sheet 05 1 At FR62 hold in position temporarily : 1 Bracket A5327415220600 Item 42 2 If a plastic cable support interferes with bracket, Item 42, replace the plastic cable support with the following : Refer to ESPM 20-33-11 1 Screw NAS1801-3-26 Item 70 2 Washer NAS1149D0332K Item 71 1 Spacer NSA5527-03-01D Item 72 1 Spacer NSA5527-03-08D Item 73 1 Nut MS21042-3 Item 74 1 Clamp MS21919WCH3 Item 75
DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 40 6

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# @A300 SERVICE BULLETIN NOTE: The screw, Item 70, has to be installed from the AFT of the FR62 and the clamp, Item 75, has to be orientated at 12 o’clock position (Up). 3 At FR62 install temporarily : 1 Reinforcement A5327429220600 Item 41 4 If no ’cold expansion’ drill the fastener holes and open to final dimension. 5 If ’cold expansion’ transfer drill the fastener holes and open to the specific starting hole diameter. 6 Cold expand the specified fastener holes on the reinforcement and structure where no cracks were found. Refer to SRM 51-30-47 Refer to FTI Tooling List No. FTI-A300-53-0389-1 Refer to Fig. A-GBPAA Sheet 04, Detail G, and Fig. A-GBPAA Sheet 05 7 Ream the specified fastener holes on the reinforcement and structure with the correct gage finish reamer. Refer to Fig. A-GBPAA Sheet 04, Detail G, and Fig. A-GBPAA Sheet 05 8 Remove the temporarily installed Item 41. 9 Clean the fastener holes with : Solvent General Purpose 11-026 As required

10 Install the reinforcement, Item 41, with : 8 Nut ASNA2528-3 Item 4 12 Nut ASNA2528-3A Item 5 8 Bolt EN6115K3-3 Item 6 2 Bolt EN6115K3AX5 Item 12 10 Bolt EN6115K3A5 Item 51 11 At FR62 install : 1 Bracket A5327415220600 Item 42 with : 2 Rivet EN6081D6-09 Item 38
DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 41 6

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# @A300 SERVICE BULLETIN
12 At FR62 install : 1 Bracket A5327415220800 Item 43 with : 2 Rivet EN6081D4-07 Item 36 and : 1 Receptacle ABS0337-01A Item 45 with : 2 Rivet EN6069AD3-05 Item 50 13 Put in position at bracket, Item 43, and install : NOTE: It is necessary to drill the hole to dia. 6.5mm (0.25in.) for installation of the nut-plate, Item 44, during the installation of the ceiling panel. 1 Nut-Plate MS21051L3 Item 44 with : 2 Rivet EN6069AD3-05 Item 50 14 Transfer drill the fastener holes and open to final dimension and close the two holes with : 2 Rivet EN6081D6-09 Item 38 1 Rivet EN6069D4-05 Item 53 (d) Perform minor amendment of screws, spacers and split conduits (Refer to ESPM 20-33-11 and ESPM 20-33-33). **CONF 002 (1) Subtask 530389-831-201-002 - Remove the existing fasteners from the crossbeam at FR22 and FR23. Work Zones and Access Panels Zone Access/Work location 130 Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 42 6

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# @A300 SERVICE BULLETIN Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required References Consumable Material List (CML) Fig. A-GBEAA Removal of the Existing Fasteners from the Crossbeam at FR22 and FR23 Sheet 01 Sheet 02 Sheet 03 Sheet 04 WARNING: BEFORE YOU REMOVE ANY RIVETS FROM THE CROSSBEAM FR22 OR FR23, ENSURE THAT THE FORWARD DOOR ACTUATOR IS DISCONNECTED FROM THE ACTUATOR BEAM. (a) Remove the fasteners from the crossbeam at FR22. 1 Remove the fasteners : Refer to Fig. A-GBEAA Sheet 02, Detail B, and Fig. A-GBEAA Sheet 03, Detail D 2 Clean the fasteners holes and the adjacent area with : Solvent General Purpose 11-026 As required (b) If pins are installed in the actuator beam at FR22, remove them. 1 Remove the existing pins : Refer to Fig. A-GBEAA Sheet 02, Detail B, and Fig. A-GBEAA Sheet 04, Detail F 2 Clean the pin holes and the adjacent area with : Solvent General Purpose 11-026 As required (c) Remove the fasteners from the crossbeam at FR23. 1 Remove the fasteners : Refer to Fig. A-GBEAA Sheet 02, Detail C, and Fig. A-GBEAA Sheet 03, Detail E

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 43 6

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# @A300 SERVICE BULLETIN
2 Clean the fastener holes and the adjacent area with : Solvent General Purpose 11-026 As required (2) Subtask 530389-832-201-002 - Rotating Probe Inspection at the crossbeam at FR22 and FR23. Work Zones and Access Panels Zone Access/Work location 130 Manpower Resources Manhours 4.00 Minimum number of person 1 Subtask elapsed time 4.00 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-30-10 PART 1 Fig. A-GBGAA Installation of the Reinforcement at the Crossbeam at FR22 and FR23 Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 (a) Rotating Probe Inspection at the crossbeam at FR22. 1 Do a rotating probe inspection of the fastener holes at FR22 (Refer to NTM 51-30-10 PART 1). Refer to Fig. A-GBGAA Sheet 03, Detail D a If no crack(s) are found : <1> - Refer to para. (3)(a). b If crack(s) are found : <1> Contact AIRBUS for further instructions. (b) Rotating Probe Inspection at the crossbeam at FR23. 1 Do a rotating probe inspection of the fastener holes at FR23 (Refer to NTM 51-30-10 PART 1). Refer to Fig. A-GBGAA Sheet 04, Detail F

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 44 6

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# @A300 SERVICE BULLETIN

a If no crack(s) are found : <1> - Refer to para. (3)(c). b If crack(s) are found : <1> Contact AIRBUS for further instructions. (3) Subtask 530389-831-203-002 - Install the reinforcement at the crossbeam at FR22 and FR23. Work Zones and Access Panels Zone Access/Work location 130 Manpower Resources Manhours 8.00 Minimum number of person 2 Subtask elapsed time 4.00 Skills AIRFRAME Material necessary to do the job Kit 530389D03R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 4 ASNA2528-3 32 NUT 5 ASNA2528-3A 14 NUT 6 EN6115K3-3 16 BOLT 9 EN6115K3X4 2 BOLT 10 EN6115K3X5 14 BOLT 12 EN6115K3AX5 2 BOLT 13 EN6115K3AX6 2 BOLT 14 EN6115K3A6 10 BOLT 16 DAN11-6X 7 COLLAR 20 A5378103420600 1 RNFRCMNT 21 A5378103422000 1 RNFRCMNT 55 DAN5-6-6X 7 PIN Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required References Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-33-11 20-33-33
DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 45 6

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# @A300 SERVICE BULLETIN
References Structural Repair Manual (SRM) 51-27-11 51-30-47 51-40-20 Fig. A-GBGAA Installation of the Reinforcement at the Crossbeam at FR22 and FR23 Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 (a) Install the reinforcement at the crossbeam at FR22. Refer to Fig. A-GBGAA Sheet 02, Detail B, Fig. A-GBGAA Sheet 03, Detail E, Fig. A-GBGAA Sheet 05, Fig. A-GBGAA Sheet 07, Detail J and K and Fig. A-GBGAA Sheet 08, Detail L and M 1 If the reinforcement, Item 20, has been delivered with the old contour, rework the reinforcement to the new contour to avoid any interference with a plastic cable support. Refer to SRM 51-27-11 Refer to Fig. A-GBGAA Sheet 07, Details J and K 2 If the reinforcement, Item 20, has been delivered with the old contour and if it has any interference with a plastic cable support on the inboard side, rework the reinforcement to the new contour. Refer to SRM 51-27-11 Refer to Fig. A-GBGAA Sheet 08, Details L and M 3 At FR22 install temporarily : 1 Reinforcement A5378103420600 Item 20 4 If no ’cold expansion’ drill the fastener holes and open to final dimension. 5 If ’cold expansion’ transfer drill the fastener holes and open to the specific starting hole diameter. 6 Cold expand the specified fastener holes on the reinforcement and structure where no cracks were found. Refer to SRM 51-30-47 Refer to FTI Tooling List No. FTI-A300-53-0389-1 Refer to Fig. A-GBGAA Sheet 03, Detail E, and Fig. A-GBGAA Sheet 05
DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 46 6

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# @A300 SERVICE BULLETIN
7 Ream the specified fastener holes on the reinforcement and structure with the correct gage finish reamer. Refer to Fig. A-GBGAA Sheet 03, Detail E, and Fig. A-GBGAA Sheet 05 8 Remove the temporarily installed Item 20. 9 Clean the fastener holes with : Solvent General Purpose 11-026 As required

10 Install the reinforcement, Item 20, with : 22 Nut ASNA2528-3 Item 4 2 Nut ASNA2528-3A Item 5 6 Bolt EN6115K3-3 Item 6 2 Bolt EN6115K3X4 Item 9 14 Bolt EN6115K3X5 Item 10 2 Bolt EN6115K3AX5 Item 12 (b) If nominal size pins have been removed from the actuator beam at FR22, install new 1st oversize pins. Refer to Fig. A-GBGAA Sheet 02, Detail B, Fig. A-GBGAA Sheet 05 and Fig. AGBGAA Sheet 06, Detail H 1 Install : 7 Pin DAN5-6-6X Item 55 7 Collar DAN11-6X Item 16 (c) Install the reinforcement at the crossbeam at FR23. Refer to Fig. A-GBGAA Sheet 02, Detail C, Fig. A-GBGAA Sheet 04, Detail G, and Fig. A-GBGAA Sheet 05 1 At FR22 install temporarily : 1 Reinforcement A5378103422000 Item 21 2 If no ’cold expansion’ drill the fastener holes and open to final dimension. 3 If ’cold expansion’ transfer drill the fastener holes and open to the specific starting hole diameter.

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 47 6

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# @A300 SERVICE BULLETIN
4 Cold expand the specified fastener holes where no cracks were found. Refer to SRM 51-30-47 Refer to FTI Tooling List No. FTI-A300-53-0389-1 Refer to Fig. A-GBGAA Sheet 04, Detail G, and Fig. A-GBGAA Sheet 05 5 Ream the specified fastener holes on the structure and reinforcement with the correct gage finish reamer. Refer toFig. A-GBGAA Sheet 04, Detail G, and Fig. A-GBGAA Sheet 05 6 Remove the temporarily installed Item 21. 7 Clean the fastener holes with : Solvent General Purpose 11-026 As required 8 Install the reinforcement, Item 21, with : 10 Nut ASNA2528-3 Item 4 12 Nut ASNA2528-3A Item 5 10 Bolt EN6115K3-3 Item 6 2 Bolt EN6115K3AX6 Item 13 10 Bolt EN6115K3A6 Item 14 (d) Perform minor amendment of screws, spacers and split conduits (Refer to ESPM 20-33-11 and ESPM 20-33-33). (4) Subtask 530389-831-205-001 - Remove the existing fasteners from the crossbeam FR61 and FR62. Work Zones and Access Panels Zone Access/Work location 150 Manpower Resources Manhours 3.00 Minimum number of person 2 Subtask elapsed time 1.50 Skills AIRFRAME

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 48 6

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# @A300 SERVICE BULLETIN Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required References Consumable Material List (CML) Fig. A-GBNAA Removal of the Existing Rivets from the Crossbeam at FR61 and FR62 Sheet 01 Sheet 02 Sheet 03 Sheet 04 WARNING: BEFORE YOU REMOVE ANY RIVETS FROM THE CROSSBEAM FR61 OR FR62, ENSURE THAT THE AFTER DOOR ACTUATOR IS DISCONNECTED FROM THE ACTUATOR BEAM. (a) Remove the existing fasteners from the crossbeam FR61. 1 Remove the existing fasteners : Refer to Fig. A-GBNAA Sheet 02, Detail B, and Fig. A-GBNAA Sheet 03, Detail D 2 Clean the fasteners holes and the adjacent area with : Solvent General Purpose 11-026 As required (b) If pins are installed in the actuator beam at FR61, remove them. 1 Remove the existing pins : Refer to Fig. A-GBNAA Sheet 02, Detail B, and Fig. A-GBNAA Sheet 04, Detail F 2 Clean the pin holes and the adjacent area with : Solvent General Purpose 11-026 As required (c) Remove the existing fasteners from the crossbeam FR62. 1 Remove the bracket, the receptacle and the fasteners : Refer to Fig. A-GBNAA Sheet 02, Detail C, and Fig. A-GBNAA Sheet 03, Detail E 1 Bracket A2557309120600 Item (43) Discard 1 Nut NAS1068C3 Item (44) Discard DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 49 6

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# @A300 SERVICE BULLETIN 1 Receptacle DAN367-01 Item (45) Discard 2 Clean the fastener holes and the adjacent area with : Solvent General Purpose 11-026 As required (5) Subtask 530389-831-206-001 - Rotating Probe Inspection at the crossbeam FR61 and FR62. Work Zones and Access Panels Zone Access/Work location 150 Manpower Resources Manhours 4.00 Minimum number of person 1 Subtask elapsed time 4.00 Skills AIRFRAME References Consumable Material List (CML) Non Destructive Test Manual (NTM) 51-30-10 PART 1 Fig. A-GBPAA Installation of the Reinforcement at the Crossbeam at FR61 and FR62 Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 (a) Rotating Probe Inspection at the crossbeam at FR61. 1 Do a rotating probe inspection of the fastener holes at FR61 (Refer to NTM 51-30-10 PART 1). Refer to Fig. A-GBPAA Sheet 03, Detail D a If no crack(s) are found : <1> - Refer to para. (6)(a). b If crack(s) are found : <1> Contact AIRBUS for further instructions. (b) Rotating Probe Inspection at the crossbeam at FR62. 1 Do a rotating probe inspection of the fastener holes at FR62 (Refer to NTM 51-30-10 PART 1). Refer to Fig. A-GBPAA Sheet 04, Detail F DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 50 6

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# @A300 SERVICE BULLETIN

a If no crack(s) are found : <1> - Refer to para. (6)(c). b If crack(s) are found : <1> Contact AIRBUS for further instructions. (6) Subtask 530389-831-207-001 - Install the reinforcement and brackets at the crossbeam at FR61 and FR62. Work Zones and Access Panels Zone Access/Work location 150 Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME Material necessary to do the job Kit 530389D01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 4 ASNA2528-3 35 NUT 5 ASNA2528-3A 15 NUT 6 EN6115K3-3 19 BOLT 10 EN6115K3X5 16 BOLT 12 EN6115K3AX5 4 BOLT 16 DAN11-6X 7 COLLAR 36 EN6081D4-07 2 RIVET 38 EN6081D6-09 4 RIVET 40 A5327429220000 1 PLATE 41 A5327429220600 1 PLATE 42 A5327415220600 1 ANGLE 43 A5327415220800 1 ANGLE 44 MS21051L3 1 NUT 45 ABS0337-01A 1 RECEPTCL 50 EN6069AD3-05 4 RIVET 51 EN6115K3A5 10 BOLT 52 EN6115K3AX3 1 BOLT 53 EN6069D4-05 1 RIVET 55 DAN5-6-6X 7 PIN 56 DAN5-6-6Y 7 PIN 57 DAN11-6Y 7 COLLAR

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 51 6

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# @A300 SERVICE BULLETIN Component COMPD01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 70 NAS1801-3-26 1 SCREW 71 NAS1149D0332K 2 WASHER 72 NSA5527-03-01D 1 SPACER 73 NSA5527-03-08D 1 SPACER 74 MS21042-3 1 NUT 75 MS21919WCH3 1 CLAMP Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required References Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-33-11 20-33-33 Structural Repair Manual (SRM) 51-30-47 Fig. A-GBPAA Installation of the Reinforcement at the Crossbeam at FR61 and FR62 Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 (a) Install the reinforcement at the crossbeam at FR61. Refer to Fig. A-GBPAA Sheet 02, Detail B, Fig. A-GBPAA Sheet 03, Detail E, and Fig. A-GBPAA Sheet 05 1 At FR61 install temporarily : 1 Reinforcement A5327429220000 Item 40 2 If no ’cold expansion’ drill the fastener holes and open to final dimension. 3 If ’cold expansion’ transfer drill the fastener holes and open to the specific starting hole diameter. 4 Cold expand the specified fastener holes on the reinforcement and structure where no cracks were found. Refer to SRM 51-30-47 Refer to FTI Tooling List No. FTI-A300-53-0389-1 Refer to Fig. A-GBPAA Sheet 03, Detail E, and Fig. A-GBPAA Sheet 05

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 52 6

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# @A300 SERVICE BULLETIN
5 Ream the specified fastener holes on the reinforcement and structure with the correct gage finish reamer. Refer to Fig. A-GBPAA Sheet 03, Detail E, and Fig. A-GBPAA Sheet 05 6 Remove the temporarily installed Item 40. 7 Clean the fastener holes with : Solvent General Purpose 11-026 As required 8 Install the reinforcement, Item 40, with : 27 Nut ASNA2528-3 Item 4 3 Nut ASNA2528-3A Item 5 11 Bolt EN6115K3-3 Item 6 16 Bolt EN6115K3X5 Item 10 2 Bolt EN6115K3AX5 Item 12 1 Bolt EN6115K3AX3 Item 52 (b) If pins have been removed from the actuator beam at FR61, install new pins. Refer to Fig. A-GBPAA Sheet 02, Detail B, Fig. A-GBPAA Sheet 05 and Fig. AGBPAA Sheet 06, Detail H 1 If nominal size pins have been removed from the actuator beam at FR61, install new 1st oversize pins. a Install : 7 Pin DAN5-6-6X Item 55 7 Collar DAN11-6X Item 16 2 If 1st oversize pins have been removed from the actuator beam at FR61, install new 2nd oversize pins. a Install : 7 Pin DAN5-6-6Y Item 56 7 Collar DAN11-6Y Item 57 (c) Install the reinforcement and brackets at the crossbeam at FR62. Refer to Fig. A-GBPAA Sheet 02, Detail C, Fig. A-GBPAA Sheet 04, Detail G, and Fig. A-GBPAA Sheet 05
DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 53 6

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# @A300 SERVICE BULLETIN
1 At FR62 hold in position temporarily : 1 Bracket A5327415220600 Item 42 2 If a plastic cable support interferes with bracket, Item 42, replace the plastic cable support with the following : Refer to ESPM 20-33-11 1 Screw NAS1801-3-26 Item 70 2 Washer NAS1149D0332K Item 71 1 Spacer NSA5527-03-01D Item 72 1 Spacer NSA5527-03-08D Item 73 1 Nut MS21042-3 Item 74 1 Clamp MS21919WCH3 Item 75 NOTE: The screw, Item 70, has to be installed from the AFT of the FR62 and the clamp, Item 75, has to be orientated at 12 o’clock position (Up). 3 At FR62 install temporarily : 1 Reinforcement A5327429220600 Item 41 4 If no ’cold expansion’ drill the fastener holes and open to final dimension. 5 If ’cold expansion’ transfer drill the fastener holes and open to the specific starting hole diameter. 6 Cold expand the specified fastener holes on the reinforcement and structure where no cracks were found. Refer to SRM 51-30-47 Refer to FTI Tooling List No. FTI-A300-53-0389-1 Refer to Fig. A-GBPAA Sheet 04, Detail G, and Fig. A-GBPAA Sheet 05 7 Ream the specified fastener holes on the reinforcement and structure with the correct gage finish reamer. Refer to Fig. A-GBPAA Sheet 04, Detail G, and Fig. A-GBPAA Sheet 05 8 Remove the temporarily installed Item 41.

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 54 6

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# @A300 SERVICE BULLETIN
9 Clean the fastener holes with : Solvent General Purpose 11-026 As required

10 Install the reinforcement, Item 41, with : 8 Nut ASNA2528-3 Item 4 12 Nut ASNA2528-3A Item 5 8 Bolt EN6115K3-3 Item 6 2 Bolt EN6115K3AX5 Item 12 10 Bolt EN6115K3A5 Item 51 11 At FR62 install : 1 Bracket A5327415220600 Item 42 with : 2 Rivet EN6081D6-09 Item 38 12 At FR62 install : 1 Bracket A5327415220800 Item 43 with : 2 Rivet EN6081D4-07 Item 36 and : 1 Receptacle ABS0337-01A Item 45 with : 2 Rivet EN6069AD3-05 Item 50 13 Put in position at bracket, Item 43, and install : NOTE: It is necessary to drill the hole to dia. 6.5mm (0.25in.) for installation of the nut-plate, Item 44, during the installation of the ceiling panel. 1 Nut-Plate MS21051L3 Item 44 with : 2 Rivet EN6069AD3-05 Item 50

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 55 6

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# @A300 SERVICE BULLETIN
14 Transfer drill the fastener holes and open to final dimension and close the two holes with : 2 Rivet EN6081D6-09 Item 38 1 Rivet EN6069D4-05 Item 53 (d) Perform minor amendment of screws, spacers and split conduits (Refer to ESPM 20-33-11 and ESPM 20-33-33). **CONF 003 (1) Subtask 530389-831-201-003 - Remove the existing fasteners and the brackets from the crossbeam at FR22 and FR23. Work Zones and Access Panels Zone Access/Work location 130 Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required References Consumable Material List (CML) Structural Repair Manual (SRM) 53-13-00 Fig. A-GBJAA Removal of the Existing Fasteners from the Crossbeam at FR22 and FR23 Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 WARNING: BEFORE YOU REMOVE ANY RIVETS FROM THE CROSSBEAM FR22 OR FR23, ENSURE THAT THE FORWARD DOOR ACTUATOR IS DISCONNECTED FROM THE ACTUATOR BEAM. (a) Remove the existing fasteners and the brackets from the crossbeam at FR22. 1 Remove the existing fasteners and the brackets : Refer to Fig. A-GBJAA Sheet 02, Detail B, and Fig. A-GBJAA Sheet 04, Detail D DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 56 6

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# @A300 SERVICE BULLETIN 1 Bracket A5377469720000 Item (25) Retain 1 Console A2557105700000 Item (26) Retain 1 Bracket A9249602920000 Item (27) Retain 1 Bracket A5377466620000 Item (28) Retain 2 Rework the affected area as shown in Fig. A-GBJAA Sheet 02, Detail B, Fig. A-GBJAA Sheet 03, Detail C, and Section A-A Refer to SRM 53-13-00 3 Clean the fastener holes and the adjacent area with : Solvent General Purpose 11-026 As required (b) If pins are installed in the actuator beam at FR22, remove them. 1 Remove the existing pins : Refer to Fig. A-GBJAA Sheet 02, Detail B, and Fig. A-GBJAA Sheet 05, Detail G 2 Clean the pin holes and the adjacent area with : Solvent General Purpose 11-026 As required (c) Remove the existing fasteners from the crossbeam at FR23. 1 Remove the existing fasteners : Refer to Fig. A-GBJAA Sheet 04, Details E and F 2 Clean the fastener holes and the adjacent area with : Solvent General Purpose 11-026 As required (2) Subtask 530389-832-201-003 - Rotating Probe Inspection at the crossbeam at FR22 and FR23. Work Zones and Access Panels Zone Access/Work location 130

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 57 6

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# @A300 SERVICE BULLETIN Manpower Resources Manhours 4.00 Minimum number of person 1 Subtask elapsed time 4.00 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-30-10 PART 1 Fig. A-GBLAA Installation of the Reinforcement at the Crossbeam at FR22 and FR23 Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 (a) Rotating Probe Inspection at the crossbeam at FR22. 1 Do a rotating probe inspection of the fastener holes at FR22 (Refer to NTM 51-30-10 PART 1). Refer to Fig. A-GBLAA Sheet 03, Detail C a If no crack(s) are found : <1> - Refer to para. (3)(a). b If crack(s) are found : <1> Contact AIRBUS for further instructions. (b) Rotating Probe Inspection at the crossbeam at FR23. 1 Do a rotating probe inspection of the fastener holes at FR23 (Refer to NTM 51-30-10 PART 1). Refer to Fig. A-GBLAA Sheet 04, Detail F a If no crack(s) are found : <1> - Refer to para. (3)(c). b If crack(s) are found : <1> Contact AIRBUS for further instructions. (3) Subtask 530389-831-203-003 - Install the reinforcement and the brackets at the crossbeam at FR22 and FR23. Work Zones and Access Panels Zone Access/Work location 130
DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 58 6

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# @A300 SERVICE BULLETIN Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME Material necessary to do the job Kit 530389D04R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 4 ASNA2528-3 28 NUT 5 ASNA2528-3A 8 NUT 8 EN6115K3-5 2 BOLT 10 EN6115K3X5 6 BOLT 13 EN6115K3AX6 2 BOLT 16 DAN11-6X 7 COLLAR 22 A5378103423400 1 RNFRCMNT 23 MS21076L4N 2 NUT 25 A5377469720000 1 ANGLE 30 EN6115K3X6 10 BOLT 31 EN6115K3X7 10 BOLT 32 EN6115K3AX7 6 BOLT 35 EN6081D3-06 4 RIVET 36 EN6081D4-07 4 RIVET 37 EN6081D5-07 4 RIVET 38 EN6081D6-07 18 RIVET 55 DAN5-6-6X 7 PIN Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required References Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-33-11 20-33-33 Structural Repair Manual (SRM) 51-30-47 Fig. A-GBLAA Installation of the Reinforcement at the Crossbeam at FR22 and FR23 Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 59 6

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# @A300 SERVICE BULLETIN (a) Install the reinforcement and the brackets at the crossbeam at FR22. Refer to Fig. A-GBLAA Sheet 02, Detail B, Fig. A-GBLAA Sheet 03, Detail D, and Fig. A-GBLAA Sheet 05 1 At FR22 install temporarily : 1 Reinforcement A5378103423400 Item 22 1 Bracket A5377469720000 Item 25 1 Bracket A5377466620000 Item (28) Retained at removal 2 If no ’cold expansion’ drill the fastener holes and open to final dimension. 3 If ’cold expansion’ transfer drill the fastener holes and open to the specific starting hole diameter. 4 Cold expand the specified fastener holes where no cracks were found. Refer to SRM 51-30-47 Refer to FTI Tooling List No. FTI-A300-53-0389-1 Refer to Fig. A-GBLAA Sheet 03, Detail D, and Fig. A-GBLAA Sheet 05 5 Ream the specified fastener holes on the structure and reinforcement with the correct gage finish reamer. Refer to Fig. A-GBLAA Sheet 03, Detail D, and Fig. A-GBLAA Sheet 05 6 Remove the temporarily installed Items 22, 25 and 28. 7 Clean the fastener holes with : Solvent General Purpose 11-026 As required 8 Install the reinforcement, Item 22, the bracket, Item 25, and the bracket, Item 28, with : 16 Nut ASNA2528-3 Item 4 6 Nut ASNA2528-3A Item 5 6 Bolt EN6115K3X5 Item 10 2 Bolt EN6115K3AX6 Item 13 10 Bolt EN6115K3X6 Item 30 4 Bolt EN6115K3AX7 Item 32 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 60 6

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# @A300 SERVICE BULLETIN
18 Rivet EN6081D6-07 Item 38 9 At FR22 install temporarily : 2 Console A2557105700000 Item (26) Retained at removal 10 Transfer drill the fastener holes and open to final dimension. 11 Install the temporarily installed Item (26) with : 4 Rivet EN6081D5-07 Item 37 12 At FR22, at Item (26), install : 2 Nut MS21076L4N Item 23 4 Rivet EN6081D3-06 Item 35 13 At FR22 install temporarily : 1 Bracket A9249602920000 Item (27) 14 Transfer drill the fastener holes and open to final dimension. 15 Install the temporarily installed item (27) with : 4 Rivet EN6081D4-07 Item 36 (b) If nominal size pins have been removed from the actuator beam at FR22, install new 1st oversize pins. Refer to Fig. A-GBLAA Sheet 02, Detail B, Fig. A-GBLAA Sheet 05 and Fig. AGBLAA Sheet 06, Detail H 1 Install : 7 Pin DAN5-6-6X Item 55 7 Collar DAN11-6X Item 16 (c) Install the fasteners at the crossbeam at FR23. Refer to Fig. A-GBLAA Sheet 02, Detail C, Fig. A-GBLAA Sheet 04, Details E and G, and Fig. A-GBLAA Sheet 05 1 At FR23, if no ’cold expansion’ drill the fastener holes and open to final dimension. 2 At FR23, if ’cold expansion’ transfer drill the fastener holes and open to the specific starting hole diameter.

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 61 6

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# @A300 SERVICE BULLETIN
3 Cold expand the specified fastener holes where no cracks were found. Refer to SRM 51-30-47 Refer to FTI Tooling List No. FTI-A300-53-0389-1 Refer to Fig. A-GBLAA Sheet 04, Details E and G, and Fig. A-GBLAA Sheet 05 4 Ream the specified fastener holes on the structure and reinforcement with the correct gage finish reamer. 5 Clean the fastener holes with : Refer to Fig. A-GBLAA Sheet 04, Details E and G, and Fig. A-GBLAA Sheet 05 Solvent General Purpose 11-026 As required 6 Install items : 12 Nut ASNA2528-3 Item 4 2 Nut ASNA2528-3A Item 5 2 Bolt EN6115K3-5 Item 8 10 Bolt EN6115K3X7 Item 31 2 Bolt EN6115K3AX7 Item 32 (d) Perform minor amendment of screws, spacers and split conduits (Refer to ESPM 20-33-11 and ESPM 20-33-33). (4) Subtask 530389-831-205-001 - Remove the existing fasteners from the crossbeam FR61 and FR62. Work Zones and Access Panels Zone Access/Work location 150 Manpower Resources Manhours 3.00 Minimum number of person 2 Subtask elapsed time 1.50 Skills AIRFRAME

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 62 6

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# @A300 SERVICE BULLETIN Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required References Consumable Material List (CML) Fig. A-GBNAA Removal of the Existing Rivets from the Crossbeam at FR61 and FR62 Sheet 01 Sheet 02 Sheet 03 Sheet 04 WARNING: BEFORE YOU REMOVE ANY RIVETS FROM THE CROSSBEAM FR61 OR FR62, ENSURE THAT THE AFTER DOOR ACTUATOR IS DISCONNECTED FROM THE ACTUATOR BEAM. (a) Remove the existing fasteners from the crossbeam FR61. 1 Remove the existing fasteners : Refer to Fig. A-GBNAA Sheet 02, Detail B, and Fig. A-GBNAA Sheet 03, Detail D 2 Clean the fasteners holes and the adjacent area with : Solvent General Purpose 11-026 As required (b) If pins are installed in the actuator beam at FR61, remove them. 1 Remove the existing pins : Refer to Fig. A-GBNAA Sheet 02, Detail B, and Fig. A-GBNAA Sheet 04, Detail F 2 Clean the pin holes and the adjacent area with : Solvent General Purpose 11-026 As required (c) Remove the existing fasteners from the crossbeam FR62. 1 Remove the bracket, the receptacle and the fasteners : Refer to Fig. A-GBNAA Sheet 02, Detail C, and Fig. A-GBNAA Sheet 03, Detail E 1 Bracket A2557309120600 Item (43) Discard 1 Nut NAS1068C3 Item (44) Discard DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 63 6

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# @A300 SERVICE BULLETIN 1 Receptacle DAN367-01 Item (45) Discard 2 Clean the fastener holes and the adjacent area with : Solvent General Purpose 11-026 As required (5) Subtask 530389-831-206-001 - Rotating Probe Inspection at the crossbeam FR61 and FR62. Work Zones and Access Panels Zone Access/Work location 150 Manpower Resources Manhours 4.00 Minimum number of person 1 Subtask elapsed time 4.00 Skills AIRFRAME References Consumable Material List (CML) Non Destructive Test Manual (NTM) 51-30-10 PART 1 Fig. A-GBPAA Installation of the Reinforcement at the Crossbeam at FR61 and FR62 Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 (a) Rotating Probe Inspection at the crossbeam at FR61. 1 Do a rotating probe inspection of the fastener holes at FR61 (Refer to NTM 51-30-10 PART 1). Refer to Fig. A-GBPAA Sheet 03, Detail D a If no crack(s) are found : <1> - Refer to para. (6)(a). b If crack(s) are found : <1> Contact AIRBUS for further instructions. (b) Rotating Probe Inspection at the crossbeam at FR62. 1 Do a rotating probe inspection of the fastener holes at FR62 (Refer to NTM 51-30-10 PART 1). Refer to Fig. A-GBPAA Sheet 04, Detail F DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 64 6

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# @A300 SERVICE BULLETIN

a If no crack(s) are found : <1> - Refer to para. (6)(c). b If crack(s) are found : <1> Contact AIRBUS for further instructions. (6) Subtask 530389-831-207-001 - Install the reinforcement and brackets at the crossbeam at FR61 and FR62. Work Zones and Access Panels Zone Access/Work location 150 Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME Material necessary to do the job Kit 530389D01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 4 ASNA2528-3 35 NUT 5 ASNA2528-3A 15 NUT 6 EN6115K3-3 19 BOLT 10 EN6115K3X5 16 BOLT 12 EN6115K3AX5 4 BOLT 16 DAN11-6X 7 COLLAR 36 EN6081D4-07 2 RIVET 38 EN6081D6-09 4 RIVET 40 A5327429220000 1 PLATE 41 A5327429220600 1 PLATE 42 A5327415220600 1 ANGLE 43 A5327415220800 1 ANGLE 44 MS21051L3 1 NUT 45 ABS0337-01A 1 RECEPTCL 50 EN6069AD3-05 4 RIVET 51 EN6115K3A5 10 BOLT 52 EN6115K3AX3 1 BOLT 53 EN6069D4-05 1 RIVET 55 DAN5-6-6X 7 PIN 56 DAN5-6-6Y 7 PIN 57 DAN11-6Y 7 COLLAR

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 65 6

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# @A300 SERVICE BULLETIN Component COMPD01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 70 NAS1801-3-26 1 SCREW 71 NAS1149D0332K 2 WASHER 72 NSA5527-03-01D 1 SPACER 73 NSA5527-03-08D 1 SPACER 74 MS21042-3 1 NUT 75 MS21919WCH3 1 CLAMP Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required References Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-33-11 20-33-33 Structural Repair Manual (SRM) 51-30-47 Fig. A-GBPAA Installation of the Reinforcement at the Crossbeam at FR61 and FR62 Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 (a) Install the reinforcement at the crossbeam at FR61. Refer to Fig. A-GBPAA Sheet 02, Detail B, Fig. A-GBPAA Sheet 03, Detail E, and Fig. A-GBPAA Sheet 05 1 At FR61 install temporarily : 1 Reinforcement A5327429220000 Item 40 2 If no ’cold expansion’ drill the fastener holes and open to final dimension. 3 If ’cold expansion’ transfer drill the fastener holes and open to the specific starting hole diameter. 4 Cold expand the specified fastener holes on the reinforcement and structure where no cracks were found. Refer to SRM 51-30-47 Refer to FTI Tooling List No. FTI-A300-53-0389-1 Refer to Fig. A-GBPAA Sheet 03, Detail E, and Fig. A-GBPAA Sheet 05

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 66 6

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# @A300 SERVICE BULLETIN
5 Ream the specified fastener holes on the reinforcement and structure with the correct gage finish reamer. Refer to Fig. A-GBPAA Sheet 03, Detail E, and Fig. A-GBPAA Sheet 05 6 Remove the temporarily installed Item 40. 7 Clean the fastener holes with : Solvent General Purpose 11-026 As required 8 Install the reinforcement, Item 40, with : 27 Nut ASNA2528-3 Item 4 3 Nut ASNA2528-3A Item 5 11 Bolt EN6115K3-3 Item 6 16 Bolt EN6115K3X5 Item 10 2 Bolt EN6115K3AX5 Item 12 1 Bolt EN6115K3AX3 Item 52 (b) If pins have been removed from the actuator beam at FR61, install new pins. Refer to Fig. A-GBPAA Sheet 02, Detail B, Fig. A-GBPAA Sheet 05 and Fig. AGBPAA Sheet 06, Detail H 1 If nominal size pins have been removed from the actuator beam at FR61, install new 1st oversize pins. a Install : 7 Pin DAN5-6-6X Item 55 7 Collar DAN11-6X Item 16 2 If 1st oversize pins have been removed from the actuator beam at FR61, install new 2nd oversize pins. a Install : 7 Pin DAN5-6-6Y Item 56 7 Collar DAN11-6Y Item 57 (c) Install the reinforcement and brackets at the crossbeam at FR62. Refer to Fig. A-GBPAA Sheet 02, Detail C, Fig. A-GBPAA Sheet 04, Detail G, and Fig. A-GBPAA Sheet 05
DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 67 6

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# @A300 SERVICE BULLETIN
1 At FR62 hold in position temporarily : 1 Bracket A5327415220600 Item 42 2 If a plastic cable support interferes with bracket, Item 42, replace the plastic cable support with the following : Refer to ESPM 20-33-11 1 Screw NAS1801-3-26 Item 70 2 Washer NAS1149D0332K Item 71 1 Spacer NSA5527-03-01D Item 72 1 Spacer NSA5527-03-08D Item 73 1 Nut MS21042-3 Item 74 1 Clamp MS21919WCH3 Item 75 NOTE: The screw, Item 70, has to be installed from the AFT of the FR62 and the clamp, Item 75, has to be orientated at 12 o’clock position (Up). 3 At FR62 install temporarily : 1 Reinforcement A5327429220600 Item 41 4 If no ’cold expansion’ drill the fastener holes and open to final dimension. 5 If ’cold expansion’ transfer drill the fastener holes and open to the specific starting hole diameter. 6 Cold expand the specified fastener holes on the reinforcement and structure where no cracks were found. Refer to SRM 51-30-47 Refer to FTI Tooling List No. FTI-A300-53-0389-1 Refer to Fig. A-GBPAA Sheet 04, Detail G, and Fig. A-GBPAA Sheet 05 7 Ream the specified fastener holes on the reinforcement and structure with the correct gage finish reamer. Refer to Fig. A-GBPAA Sheet 04, Detail G, and Fig. A-GBPAA Sheet 05 8 Remove the temporarily installed Item 41.

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 68 6

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# @A300 SERVICE BULLETIN
9 Clean the fastener holes with : Solvent General Purpose 11-026 As required

10 Install the reinforcement, Item 41, with : 8 Nut ASNA2528-3 Item 4 12 Nut ASNA2528-3A Item 5 8 Bolt EN6115K3-3 Item 6 2 Bolt EN6115K3AX5 Item 12 10 Bolt EN6115K3A5 Item 51 11 At FR62 install : 1 Bracket A5327415220600 Item 42 with : 2 Rivet EN6081D6-09 Item 38 12 At FR62 install : 1 Bracket A5327415220800 Item 43 with : 2 Rivet EN6081D4-07 Item 36 and : 1 Receptacle ABS0337-01A Item 45 with : 2 Rivet EN6069AD3-05 Item 50 13 Put in position at bracket, Item 43, and install : NOTE: It is necessary to drill the hole to dia. 6.5mm (0.25in.) for installation of the nut-plate, Item 44, during the installation of the ceiling panel. 1 Nut-Plate MS21051L3 Item 44 with : 2 Rivet EN6069AD3-05 Item 50

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 69 6

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# @A300 SERVICE BULLETIN
14 Transfer drill the fastener holes and open to final dimension and close the two holes with : 2 Rivet EN6081D6-09 Item 38 1 Rivet EN6069D4-05 Item 53 (d) Perform minor amendment of screws, spacers and split conduits (Refer to ESPM 20-33-11 and ESPM 20-33-33). **CONF ALL D. TEST **CONF 001 (1) Subtask 530389-700-201-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 52-30-00, Page Block 301 52-31-11, Page Block 501 52-33-11, Page Block 501 52-33-18, Page Block 401 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the FWD cargo-compartment door actuator on the support beam (Refer to AMM 52-33-18, Page Block 401). (c) Install the AFT cargo-compartment door actuator on the support beam (Refer to AMM 52-33-18, Page Block 401). (d) Make sure that the applicable cargo-door safety-equipment is removed from the FWD and AFT cargo-compartment doors (Refer to AMM 52-30-00, Page Block 301). (e) Remove the safety clip(s) and tag(s) and close this (these) circuit breaker(s) : PANEL DESIGNATION FIN LOCATION SEE NOTES 128VU HYDRAULIC/ACCU PRESS CTL AND CARGO PUMP 7GX 803/C11 101VU ELEC HYD PUMP 23GX ALT2 NOTE: The location of the circuit breaker(s) can be different from the location given in the table. (f) Adjust the FWD and AFT door actuator and do a functional test (Refer to AMM 52-33-18, Page Block 401). DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 70 6

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# @A300 SERVICE BULLETIN **CONF 002 (1) Subtask 530389-700-201-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 52-30-00, Page Block 301 52-31-11, Page Block 501 52-33-11, Page Block 501 52-33-18, Page Block 401 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the FWD cargo-compartment door actuator on the support beam (Refer to AMM 52-33-18, Page Block 401). (c) Install the AFT cargo-compartment door actuator on the support beam (Refer to AMM 52-33-18, Page Block 401). (d) Make sure that the applicable cargo-door safety-equipment is removed from the FWD and AFT cargo-compartment doors (Refer to AMM 52-30-00, Page Block 301). (e) Remove the safety clip(s) and tag(s) and close this (these) circuit breaker(s) : PANEL DESIGNATION FIN LOCATION SEE NOTES 128VU HYDRAULIC/ACCU PRESS CTL AND CARGO PUMP 7GX 803/C11 101VU ELEC HYD PUMP 23GX ALT2 NOTE: The location of the circuit breaker(s) can be different from the location given in the table. (f) Adjust the FWD and AFT door actuator and do a functional test (Refer to AMM 52-33-18, Page Block 401). **CONF 003 (1) Subtask 530389-700-201-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 52-30-00, Page Block 301 52-31-11, Page Block 501 52-33-11, Page Block 501 52-33-18, Page Block 401
DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 71 6

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# @A300 SERVICE BULLETIN (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the FWD cargo-compartment door actuator on the support beam (Refer to AMM 52-33-18, Page Block 401). (c) Install the AFT cargo-compartment door actuator on the support beam (Refer to AMM 52-33-18, Page Block 401). (d) Make sure that the applicable cargo-door safety-equipment is removed from the FWD and AFT cargo-compartment doors (Refer to AMM 52-30-00, Page Block 301). (e) Remove the safety clip(s) and tag(s) and close this (these) circuit breaker(s) : PANEL DESIGNATION FIN LOCATION SEE NOTES 128VU HYDRAULIC/ACCU PRESS CTL AND CARGO PUMP 7GX 803/C11 101VU ELEC HYD PUMP 23GX ALT2 NOTE: The location of the circuit breaker(s) can be different from the location given in the table. (f) Adjust the FWD and AFT door actuator and do a functional test (Refer to AMM 52-33-18, Page Block 401). **CONF ALL E. CLOSE-UP **CONF 001 (1) Subtask 530389-942-201-001 - Close-up Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) 06-21-53, Page Block 001 25-51-11, Page Block 401 25-52-11, Page Block 401 52-30-00, Page Block 301 (a) Install the retained FWD cargo-compartment ceiling panel (Refer to AMM 25-51-11, Page Block 401 and AMM 06-21-53, Page Block 001). (b) Install the door actuator lining between FR22 and FR23. (c) Install the retained AFT cargo-compartment ceiling panel (Refer to AMM 25-52-11, Page Block 401 and AMM 06-21-53, Page Block 001). (d) Install the door actuator lining between FR61 and F62. DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 72 6

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# @A300 SERVICE BULLETIN (e) Make sure that the work areas are clean and clear of tools and other items of equipment. (f) Close the FWD cargo-compartment door 811 (Refer to AMM 52-30-00, Page Block 301). (g) Close the AFT cargo-compartment door 812 (Refer to 52-30-00, Page Block 301). (h) Remove the access platform(s). **CONF 002 (1) Subtask 530389-942-201-001 - Close-up Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) 06-21-53, Page Block 001 25-51-11, Page Block 401 25-52-11, Page Block 401 52-30-00, Page Block 301 (a) Install the retained FWD cargo-compartment ceiling panel (Refer to AMM 25-51-11, Page Block 401 and AMM 06-21-53, Page Block 001). (b) Install the door actuator lining between FR22 and FR23. (c) Install the retained AFT cargo-compartment ceiling panel (Refer to AMM 25-52-11, Page Block 401 and AMM 06-21-53, Page Block 001). (d) Install the door actuator lining between FR61 and F62. (e) Make sure that the work areas are clean and clear of tools and other items of equipment. (f) Close the FWD cargo-compartment door 811 (Refer to AMM 52-30-00, Page Block 301). (g) Close the AFT cargo-compartment door 812 (Refer to 52-30-00, Page Block 301). (h) Remove the access platform(s). **CONF 003 (1) Subtask 530389-942-201-001 - Close-up Manpower Resources Skills AIRFRAME

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 73 6

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# @A300 SERVICE BULLETIN
References Aircraft Maintenance Manual (AMM) 06-21-53, Page Block 001 25-51-11, Page Block 401 25-52-11, Page Block 401 52-30-00, Page Block 301 (a) Install the retained FWD cargo-compartment ceiling panel (Refer to AMM 25-51-11, Page Block 401 and AMM 06-21-53, Page Block 001). (b) Install the door actuator lining between FR22 and FR23. (c) Install the retained AFT cargo-compartment ceiling panel (Refer to AMM 25-52-11, Page Block 401 and AMM 06-21-53, Page Block 001). (d) Install the door actuator lining between FR61 and F62. (e) Make sure that the work areas are clean and clear of tools and other items of equipment. (f) Close the FWD cargo-compartment door 811 (Refer to AMM 52-30-00, Page Block 301). (g) Close the AFT cargo-compartment door 812 (Refer to 52-30-00, Page Block 301). (h) Remove the access platform(s).

DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 74 6

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# @A300 SERVICE BULLETIN

**CONF 001

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2 SEAT TRACK 4 Z130



### A FR21 FR22 FR23 FR24



### B

**C** SEAT TRACK 6

A_SB_530389_6_BAAA_01_02 **FWD** 

## A
Figure A-GBAAA - Sheet 01 Removal of the Existing Fasteners from the Crossbeam at FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 75 6

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# @A300 SERVICE BULLETIN

**CONF 001



### D FR22

(17)



### E FR23

A_SB_530389_6_BAAA_02_01 

### F



## B

**C**

Figure A-GBAAA - Sheet 02 Removal of the Existing Fasteners from the Crossbeam at FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 76 6

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# @A300 SERVICE BULLETIN

**CONF 001

**NOTE:** EXISTING FASTENER TO BE REMOVED 01 01 (7 POS)

01 (7 POS) 01

01 01 01

VIEW LOOKING FWD

VIEW LOOKING AFT FR22

FR23 01 (6 POS) 01 (6 POS)

01 (17)


## D

**E**

A_SB_530389_6_BAAA_03_02 Figure A-GBAAA - Sheet 03 Removal of the Existing Fasteners from the Crossbeam at FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 77 6

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# @A300 SERVICE BULLETIN

**CONF 001

IF PINS ARE INSTALLED, REMOVE THEM (7 POS)

**NOTE:** FR22 

## F
**FWD**

A_SB_530389_6_BAAA_04_00 02

02 Figure A-GBAAA - Sheet 04 Removal of the Existing Fasteners from the Crossbeam at FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 78 6

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# @A300 SERVICE BULLETIN

**CONF 001

SEAT TRACK 6

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2 SEAT TRACK 4 FR21 FR22 FR23 FR24



### B

**C**

A_SB_530389_6_BCAA_01_02 Z130



### A

**FWD** 

## A
Figure A-GBCAA - Sheet 01 Installation of the Reinforcement at the Crossbeam at FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 79 6

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# @A300 SERVICE BULLETIN

**CONF 001



### D FR22



### E FR23 2 1

3

A_SB_530389_6_BCAA_02_01 

### F **G H** 



## B

**C**

Figure A-GBCAA - Sheet 02 Installation of the Reinforcement at the Crossbeam at FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 80 6

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# @A300 SERVICE BULLETIN

**CONF 001

HOLES TO BE INSPECTED IN ACCORDANCE WITH NTM 51−30−10 01 HOLES TO BE COLD EXPANDED IN ACCORDANCE WITH SRM 51−30−47 02 **NOTE:** 01 01

01 01 01 01 01

01 (6 POS)

(6 POS) 01 

## D VIEW LOOKING FWD FR22

VIEW LOOKING FWD FR22



## E

FOR RIVETS SYMBOLS, REFER TO SHEET 5 2 1

1.6mm (0.06 in.) 02 02 02

POSITION OF SPLIT IN EXPANSION SLEEVE DURING COLD EXPANSION

A_SB_530389_6_BCAA_03_01 Figure A-GBCAA - Sheet 03 Installation of the Reinforcement at the Crossbeam at FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 81 6

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# @A300 SERVICE BULLETIN

**CONF 001

VIEW LOOKING AFT FR23

VIEW LOOKING AFT FR23

FOR RIVETS SYMBOLS, REFER TO SHEET 5 01 01

01 01 01

3 (5 POS)

(5 POS)

HOLES TO BE INSPECTED IN ACCORDANCE WITH NTM 51−30−10 01 HOLES TO BE COLD EXPANDED IN ACCORDANCE WITH SRM 51−30−47 02 **NOTE:** A

B

DIMENSIONS mm (in.) A 40.0 1.57 B 49.0 1.93 

## F

**G**

POSITION OF SPLIT IN EXPANSION SLEEVE DURING COLD EXPANSION 02 02 02

A_SB_530389_6_BCAA_04_02 Figure A-GBCAA - Sheet 04 Installation of the Reinforcement at the Crossbeam at FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 82 6

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# @A300 SERVICE BULLETIN

**CONF 001
HOLE SYMBOL ITEM EN6115K3−3 PIN P/N DESCRIPTION KIT REMARKS 6 ASNA2528−3 COLLAR 4

EN6115K3−4 PIN ASNA2528−3 COLLAR EN6115K3−5 PIN ASNA2528−3 COLLAR EN6115K3X4 PIN ASNA2528−3 COLLAR EN6115K3X5 PIN ASNA2528−3 COLLAR EN6115K3AX4 PIN ASNA2528−3A COLLAR EN6115K3AX5 PIN ASNA2528−3A COLLAR 8 4 9 4 10 4 11 5 12 5 EN6115K3AX6 PIN ASNA2528−3A COLLAR EN6115K3A6 PIN ASNA2528−3A COLLAR DAN5−6−4X PIN DAN11−6X COLLAR 13 5 14 5 15 16 D02

D02
D02
D02
D02
D02
D02
D02
D02
D02 STDN

4−4−N

4−4−N

6−2−N
6−2−N
6−2−N STARTING HOLE DIAMETER MIN. MAX.

4.29 mm (0.169 in) 4.34 mm (0.171 in)

4.29 mm (0.169 in) 4.34 mm (0.171 in)

5.31 mm (0.209 in) 5.38 mm (0.212 in) 5.31 mm (0.209 in) 5.38 mm (0.212 in) 5.31 mm (0.209 in) 5.38 mm (0.212 in) FINAL HOLE DIAMETER MIN. MAX. 4.72 mm (0.185 in) 4.76 mm (0.187 in)

4.72 mm (0.185 in) 4.76 mm (0.187 in) 5.85 mm (0.230 in) 5.89 mm (0.231 in)

5.85 mm (0.230 in) 5.89 mm (0.231 in) 5.85 mm (0.230 in) 5.89 mm (0.231 in) 5.85 mm (0.230 in) 5.89 mm (0.231 in) 5.06 mm (0.199 in) 5.09 mm (0.20 in) 5.06 mm (0.199 in) 5.09 mm (0.20 in)

5.45 mm (0.215 in) 5.49 mm (0.216 in)

A_SB_530389_6_BCAA_05_02 HOLES TO BE COLD EXPANDED IN ACCORDANCE WITH SRM 51−30−47 02 **NOTE:** STDN = STANDARD TOOL DIAMETER NUMBER EN6115K3−3 PIN ASNA2528−3 COLLAR D02 4.72 mm (0.185 in) 4.76 mm (0.187 in) EN6115K3−4 PIN ASNA2528−3 COLLAR 7 4 D02 4.72 mm (0.185 in) 4.76 mm (0.187 in) 02

02

02
02
02

DAN5−6−6X PIN COLLAR DAN11−6X 5.11mm (0.201 in.) 5.15mm (0.203 in.) D02 55 6 4

7 4

16

Figure A-GBCAA - Sheet 05 Installation of the Reinforcement at the Crossbeam at FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 83 6

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# @A300 SERVICE BULLETIN

**CONF 001

FOR RIVET SYMBOLS, REFER TO SHEET 5 03 (7 POS)

IF PINS HAVE BEEN REMOVED, INSTALL NEW PINS 03 **NOTE:** FR22 **FWD**

A_SB_530389_6_BCAA_06_00



## H

Figure A-GBCAA - Sheet 06 Installation of the Reinforcement at the Crossbeam at FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 84 6

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# @A300 SERVICE BULLETIN

**CONF 002

SEAT TRACK 6

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2 SEAT TRACK 4 Z130



### A FR21 FR22 FR23 FR24



### B

**C**

A_SB_530389_6_BEAA_01_02 **FWD** 

## A
Figure A-GBEAA - Sheet 01 Removal of the Existing Fasteners from the Crossbeam at FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 85 6

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# @A300 SERVICE BULLETIN

**CONF 002



### D FR22



### E 

## C **B**

FR23

A_SB_530389_6_BEAA_02_01 

### F

Figure A-GBEAA - Sheet 02 Removal of the Existing Fasteners from the Crossbeam at FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 86 6

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# @A300 SERVICE BULLETIN

**CONF 002

**NOTE:** 01 (7 POS)

01 (7 POS) 01 01

VIEW LOOKING FWD

VIEW LOOKING AFT FR22

FR23 01 (6 POS) 01 (6 POS) 

## D

**E**

A_SB_530389_6_BEAA_03_02 EXISTING FASTENER TO BE REMOVED 01 Figure A-GBEAA - Sheet 03 Removal of the Existing Fasteners from the Crossbeam at FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 87 6

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# @A300 SERVICE BULLETIN

**CONF 002

IF PINS ARE INSTALLED, REMOVE THEM (7 POS)

**NOTE:** FR22 **FWD** 02

02 A_SB_530389_6_BEAA_04_00 

## F

Figure A-GBEAA - Sheet 04 Removal of the Existing Fasteners from the Crossbeam at FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 88 6

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# @A300 SERVICE BULLETIN

**CONF 002

SEAT TRACK 6

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2 SEAT TRACK 4 Z130



### A FR21 FR22 FR23 FR24



### B

**C**

A_SB_530389_6_BGAA_01_02 **FWD** 

## A
Figure A-GBGAA - Sheet 01 Installation of the Reinforcement at the Crossbeam at FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 89 6

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# @A300 SERVICE BULLETIN

**CONF 002 FR22

FR23

21 20



### H

**D E** 

**F G**  **J K** 



## B

**C L**  **M**

A_SB_530389_6_BGAA_02_03 Figure A-GBGAA - Sheet 02 Installation of the Reinforcement at the Crossbeam at FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 90 6

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

# @A300 SERVICE BULLETIN

**CONF 002

VIEW LOOKING FWD FR22

VIEW LOOKING FWD FR22 01

01 (6 POS)

(6 POS) 01 0101

A

FOR RIVETS SYMBOLS, REFER TO SHEET 5 FOR DIMENSION, REFER TO SHEET 5 20 

## D

**E** C

HOLES TO BE INSPECTED IN ACCORDANCE WITH NTM 51−30−10 01 HOLES TO BE COLD EXPANDED IN ACCORDANCE WITH SRM 51−30−47 02 **NOTE:** POSITION OF SPLIT IN EXPANSION SLEEVE DURING COLD EXPANSION 02 02

A_SB_530389_6_BGAA_03_03 Figure A-GBGAA - Sheet 03 Installation of the Reinforcement at the Crossbeam at FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 91 6

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

# @A300 SERVICE BULLETIN

**CONF 002

FOR RIVETS SYMBOLS, REFER TO SHEET 5 FOR DIMENSION, REFER TO SHEET 5 VIEW LOOKING AFT FR23

VIEW LOOKING AFT FR23



## G 01 01 01 (5 POS)

(5 POS) 

## F

21

F

H

HOLES TO BE INSPECTED IN ACCORDANCE WITH NTM 51−30−10 01 HOLES TO BE COLD EXPANDED IN ACCORDANCE WITH SRM 51−30−47 02 **NOTE:** POSITION OF SPLIT IN EXPANSION SLEEVE DURING COLD EXPANSION 02 02

A_SB_530389_6_BGAA_04_02 Figure A-GBGAA - Sheet 04 Installation of the Reinforcement at the Crossbeam at FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 92 6

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

# @A300 SERVICE BULLETIN

**CONF 002

HOLE SYMBOL ITEM EN6115K3−3 PIN P/N DESCRIPTION KIT 6 ASNA2528−3 COLLAR 4 DIMENSIONS mm (in.) A 1.8 0.07 B 4.0 0.16

EN6115K3X4 PIN ASNA2528−3 COLLAR 9 4 EN6115K3X5 PIN ASNA2528−3 COLLAR 10 4 EN6115K3AX5 PIN ASNA2528−3A COLLAR 12 5

EN6115K3AX6 PIN ASNA2528−3A COLLAR EN6115K3A6 PIN ASNA2528−3A COLLAR D03

D03
D03
D03

D03
D03 REMARKS STDN STARTING HOLE DIAMETER MIN. MAX. FINAL HOLE DIAMETER MIN. MAX. 4.72 mm (0.185 in) 4.76 mm (0.187 in)

4.72 mm (0.185 in) 4.76 mm (0.187 in) 5.06 mm (0.199 in) 5.09 mm (0.20 in)

6−2−N
6−2−N 5.31 mm (0.209 in) 5.38 mm (0.212 in) 5.31 mm (0.209 in) 5.38 mm (0.212 in) 5.85 mm (0.230 in) 5.89 mm (0.231 in)

5.45 mm (0.215 in) 5.49 mm (0.216 in)

STDN = STANDARD TOOL DIAMETER NUMBER DAN5−6−6X COLLAR PIN DAN11−6X D03 5.11 mm (0.201 in) 5.15 mm (0.203 in)

HOLES TO BE COLD EXPANDED IN ACCORDANCE WITH SRM 51−30−47 **NOTE:** 55

02 EN6115K3AX6 PIN ASNA2528−3A COLLAR D03 5.85 mm (0.230 in) 5.89 mm (0.231 in) EN6115K3−3 PIN ASNA2528−3 COLLAR D03 4−4−N 4.29 mm (0.169 in) 4.34 mm (0.171 in) 02

02
02 4 6

13 5 13 5 14 5
16 4.72 mm (0.185 in) 4.76 mm (0.187 in)

5.85 mm (0.230 in) 5.89 mm (0.231 in) C 7.5 0.30 D R 8.0 0.31 E 38.1 1.50 F 40.0 1.57 G 45.0 1.77 H 54.0 2.13 J 33.0 1.30 K 41.0 1.61

A_SB_530389_6_BGAA_05_04 Figure A-GBGAA - Sheet 05 Installation of the Reinforcement at the Crossbeam at FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 93 6

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

# @A300 SERVICE BULLETIN

**CONF 002

FOR RIVET SYMBOLS, REFER TO SHEET 5 03 (7 POS)

IF PINS HAVE BEEN REMOVED, INSTALL NEW PINS 03 **NOTE:** FR22 **FWD**

A_SB_530389_6_BGAA_06_00



## H

Figure A-GBGAA - Sheet 06 Installation of the Reinforcement at the Crossbeam at FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 94 6

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

# @A300 SERVICE BULLETIN

**CONF 002

REWORK THE REINFORCEMENT, ITEM 20, TO THE NEW CONTOUR 05 IN ACCORDANCE WITH SRM 51−27−11 D B E G
D D

FOR DIMENSIONS, REFER TO SHEET 5 05 04

REINFORCEMENT, ITEM 20, WITH OLD CONTOUR 04 **NOTE:** 

## J

**K**

A_SB_530389_6_BGAA_07_00 20

20

Figure A-GBGAA - Sheet 07 Installation of the Reinforcement at the Crossbeam at FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 95 6

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

# @A300 SERVICE BULLETIN

**CONF 002

REWORK THE REINFORCEMENT, ITEM 20, TO THE NEW CONTOUR 05 IN ACCORDANCE WITH SRM 51−27−11 D B E G
D D

FOR DIMENSIONS, REFER TO SHEET 5 04

REINFORCEMENT, ITEM 20, WITH OLD CONTOUR 04 **NOTE:** 20



## L

**M** D B

J K
D D 05 20

A_SB_530389_6_BGAA_08_00 Figure A-GBGAA - Sheet 08 Installation of the Reinforcement at the Crossbeam at FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 96 6

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

# @A300 SERVICE BULLETIN

**CONF 003

SEAT TRACK 6

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2 SEAT TRACK 4 Z130



### A FR21 FR22 FR23 FR24



### B

**E**

A_SB_530389_6_BJAA_01_02 **FWD** 

## A
Figure A-GBJAA - Sheet 01 Removal of the Existing Fasteners from the Crossbeam at FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 97 6

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

# @A300 SERVICE BULLETIN

**CONF 003

FR22 (26)

(26) (28)

(27) (25)



### D **C**



## B

A_SB_530389_6_BJAA_02_01 

### G

Figure A-GBJAA - Sheet 02 Removal of the Existing Fasteners from the Crossbeam at FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 98 6

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

# @A300 SERVICE BULLETIN

**CONF 003



### A **A** D

E

E

H

G F B C A

DIMENSIONS mm (in.) A 1.8 0.07 B 2.3 0.09 C R 4.0 0.16 D 5.0 0.20 

## A **A**
DIMENSIONS mm (in.) E R 8.0 0.31 F 66.5 2.62 G 91.8 TO 92.2 3.61 TO 3.63 H 94.1 3.70 REWORKED AREA 

## C

A_SB_530389_6_BJAA_03_01 −Y1959

Figure A-GBJAA - Sheet 03 Removal of the Existing Fasteners from the Crossbeam at FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 99 6

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

# @A300 SERVICE BULLETIN

**CONF 003

FR23

**NOTE:** (8 POS) 01 (8 POS)

01 01

01 01

01 01 (4 POS)

01 01 (28) (25) (26) (26) (27)

01 01 01

VIEW LOOKING AFT FR23 01 (6 POS) 01 (6 POS) VIEW LOOKING FWD FR22



## E **F** 

## F **D** 01

A_SB_530389_6_BJAA_04_02 EXISTING FASTENER TO BE REMOVED 01 Figure A-GBJAA - Sheet 04 Removal of the Existing Fasteners from the Crossbeam at FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 100 6

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

# @A300 SERVICE BULLETIN

**CONF 003

IF PINS ARE INSTALLED, REMOVE THEM (7 POS)

**NOTE:** FR22 **FWD** 02

02 A_SB_530389_6_BJAA_05_00 

## G

Figure A-GBJAA - Sheet 05 Removal of the Existing Fasteners from the Crossbeam at FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 101 6

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

# @A300 SERVICE BULLETIN

**CONF 003

SEAT TRACK 6

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2 SEAT TRACK 4 Z130



### A FR21 FR22 FR23 FR24



### B

**E**

A_SB_530389_6_BLAA_01_02 **FWD** 

## A
Figure A-GBLAA - Sheet 01 Installation of the Reinforcement at the Crossbeam at FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 102 6

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

# @A300 SERVICE BULLETIN

**CONF 003

FR22 22 (26)

(26) (28)

(27) 25 23

23


### C **D** 

## B

A_SB_530389_6_BLAA_02_01 

### H

Figure A-GBLAA - Sheet 02 Installation of the Reinforcement at the Crossbeam at FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 103 6

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

# @A300 SERVICE BULLETIN

**CONF 003

(28) (26) (26) (27)

VIEW LOOKING FWD FR22

HOLES TO BE INSPECTED IN ACCORDANCE WITH NTM 51−30−10 01 HOLES TO BE COLD EXPANDED IN ACCORDANCE WITH SRM 51−30−47 02 **NOTE:**
FOR DIMENSION, REFER TO SHEET 5 VIEW LOOKING FWD FR22 01 01

01 01 (6 POS)

(6 POS) 01 01 01

01 01 01 (4 POS) 01

01 01 01

01

22



## D A 

### A

**A** F
D K

B J 23



## A **A** FOR RIVETS SYMBOLS, REFER TO SHEET 5 

## C

**A**

**A** 25 25 E 01

POSITION OF SPLIT IN EXPANSION SLEEVE DURING COLD EXPANSION 02

02 02

02

A_SB_530389_6_BLAA_03_01 Figure A-GBLAA - Sheet 03 Installation of the Reinforcement at the Crossbeam at FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 104 6

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

# @A300 SERVICE BULLETIN

**CONF 003

FR23

VIEW LOOKING AFT FR23 

## E **F** 

## F

VIEW LOOKING AFT FR23



## G **G**

HOLES TO BE INSPECTED IN ACCORDANCE WITH NTM 51−30−10 01 HOLES TO BE COLD EXPANDED IN ACCORDANCE WITH SRM 51−30−47 02 **NOTE:**
FOR DIMENSION, REFER TO SHEET 5 FOR RIVETS SYMBOLS, REFER TO SHEET 5 G C

H 01

01 01

01 (5 POS)

(5 POS)

POSITION OF SPLIT IN EXPANSION SLEEVE DURING COLD EXPANSION 02

02
A_SB_530389_6_BLAA_04_01 Figure A-GBLAA - Sheet 04 Installation of the Reinforcement at the Crossbeam at FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 105 6

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

# @A300 SERVICE BULLETIN

**CONF 003 HOLE SYMBOL ITEM EN6115K3−5 PIN P/N DESCRIPTION KIT
ASNA2528−3 COLLAR 4 DIMENSIONS mm (in.) A 5.0 0.20 B DIA 8.0 DIA 0.31 C 10.0 0.39 D 11.0 0.43 PIN COLLAR EN6115K3X5
PIN ASNA2528−3
COLLAR 10 4

EN6115K3X6 PIN COLLAR EN6115K3X7 PIN COLLAR EN6115K3AX7 PIN ASNA2528−3A COLLAR 5 8

EN6115K3AX6 ASNA2528−3A 13 5 30 4 ASNA2528−3 31
32 ASNA2528−3

35
36
37
38 RIVET
RIVET
RIVET
RIVET EN6081D3−06
EN6081D4−07
EN6081D5−07
EN6081D6−09 E 11.6 0.46 F 22.0 0.87 G 25.0 0.98 H 27.6 1.09 J 4 K 50.0 1.97 21.5 0.85 D04
D04
D04
D04
D04
D04
D04
D04
D04
D04

STDN = STANDARD TOOL DIAMETER NUMBER REMARKS STDN
4−4−N STARTING HOLE DIAMETER MIN. MAX. 4.29 mm (0.169 in) 4.34 mm (0.171 in) FINAL HOLE DIAMETER MIN. MAX. 4.72 mm (0.185 in) 4.76 mm (0.187 in) 5.06 mm (0.199 in) 5.09 mm (0.20 in) 5.85 mm (0.230 in) 5.89 mm (0.231 in) 5.06 mm (0.199 in) 5.09 mm (0.20 in) 5.06 mm (0.199 in) 5.09 mm (0.20 in) 5.31 mm (0.209 in) 5.38 mm (0.212 in) 5.85 mm (0.230 in) 5.89 mm (0.231 in) 6−2−N

A_SB_530389_6_BLAA_05_03 DAN5−6−6X COLLAR PIN DAN11−6X D04 5.11 mm (0.201 in) 5.15 mm (0.203 in)

HOLES TO BE COLD EXPANDED IN ACCORDANCE WITH SRM 51−30−47 **NOTE:** 55 5.31 mm (0.209 in) 5.38 mm (0.212 in) 6−2−N

02 02

02

02

16

Figure A-GBLAA - Sheet 05 Installation of the Reinforcement at the Crossbeam at FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 106 6

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

# @A300 SERVICE BULLETIN

**CONF 003

(7 POS)

FR22 **FWD**

A_SB_530389_6_BLAA_06_00



## H 03

FOR RIVET SYMBOLS, REFER TO SHEET 5 IF PINS HAVE BEEN REMOVED, INSTALL NEW PINS 03 **NOTE:** Figure A-GBLAA - Sheet 06 Installation of the Reinforcement at the Crossbeam at FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 107 6

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

# @A300 SERVICE BULLETIN

**CONF ALL

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2 SEAT TRACK 4 

### A

**B**

**C** SEAT TRACK 6 FR60 FR61 FR62 FR63 Z150

A_SB_530389_6_BNAA_01_02 **FWD** 

## A
Figure A-GBNAA - Sheet 01 Removal of the Existing Rivets from the Crossbeam at FR61 and FR62 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 108 6

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

# @A300 SERVICE BULLETIN

**CONF ALL



### D FR61

FR62



### E (43) (44) 

## C (45)

A_SB_530389_6_BNAA_02_01 

### F



## B

Figure A-GBNAA - Sheet 02 Removal of the Existing Rivets from the Crossbeam at FR61 and FR62 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 109 6

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

# @A300 SERVICE BULLETIN

**CONF ALL

**NOTE:** 01 (7 POS)

01 01

VIEW LOOKING FWD

VIEW LOOKING AFT FR61

FR62 (7 POS) 01

01 (6 POS)

(6 POS) 01

(43) (44) (45) 

## E **D**

01

A_SB_530389_6_BNAA_03_02 EXISTING FASTENER TO BE REMOVED 01 Figure A-GBNAA - Sheet 03 Removal of the Existing Rivets from the Crossbeam at FR61 and FR62 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 110 6

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

# @A300 SERVICE BULLETIN

**CONF ALL

IF PINS ARE INSTALLED, REMOVE THEM (7 POS)

**NOTE:** FR61 

## F

**FWD**

A_SB_530389_6_BNAA_04_00 02

02 Figure A-GBNAA - Sheet 04 Removal of the Existing Rivets from the Crossbeam at FR61 and FR62 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 111 6

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

# @A300 SERVICE BULLETIN

**CONF ALL

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2 SEAT TRACK 4 

### A

**B**

**C** SEAT TRACK 6 FR60 FR61 FR62 FR63 Z150

A_SB_530389_6_BPAA_01_02 **FWD** 

## A
Figure A-GBPAA - Sheet 01 Installation of the Reinforcement at the Crossbeam at FR61 and FR62 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 112 6

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

# @A300 SERVICE BULLETIN

**CONF ALL



### D FR61



### E 40

FR62



### F **G** 41

43 42 45

44 **NOTE:** DRILL THE HOLE TO DIA. 6.5mm (0.25 in.) FOR INSTALLATION OF THE 01 01 

## B

NUTE−PLATE, ITEM 44, DURING THE INSTALLATION OF THE CEILING PANEL 

## C

A_SB_530389_6_BPAA_02_01 

### H

Figure A-GBPAA - Sheet 02 Installation of the Reinforcement at the Crossbeam at FR61 and FR62 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 113 6

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

# @A300 SERVICE BULLETIN

**CONF ALL

VIEW LOOKING FWD FR61

VIEW LOOKING FWD FR61

FOR RIVETS SYMBOLS, REFER TO SHEET 5 02

02 (6 POS) 02 (6 POS) 02



## D 02 02

C

FOR DIMENSION, REFER TO SHEET 5 40

HOLES TO BE INSPECTED IN ACCORDANCE WITH NTM 51−30−10 02 HOLES TO BE COLD EXPANDED IN ACCORDANCE WITH SRM 51−30−47 03 **NOTE:** POSITION OF SPLIT IN EXPANSION SLEEVE DURING COLD EXPANSION 

## E 03 02

03

A_SB_530389_6_BPAA_03_01 Figure A-GBPAA - Sheet 03 Installation of the Reinforcement at the Crossbeam at FR61 and FR62 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 114 6

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

# @A300 SERVICE BULLETIN

**CONF ALL

FOR RIVET SYMBOLS, REFER TO SHEET 5 FOR DIMENSION, REFER TO SHEET 5 VIEW LOOKING AFT FR62

HOLES CLOSED, ONLY IN THE CROSSBEAM 04 04 02

(5 POS) (5 POS)

02 02 02

A B 

### A

**A** 41

43 42

VIEW LOOKING AFT FR62

45 50 HOLES TO BE INSPECTED IN ACCORDANCE WITH NTM 51−30−10 02 HOLES TO BE COLD EXPANDED IN ACCORDANCE WITH SRM 51−30−47 03 **NOTE:** 

## F

**G**

POSITION OF SPLIT IN EXPANSION SLEEVE DURING COLD EXPANSION 03 03 02

(2 POS) 44

A_SB_530389_6_BPAA_04_03 

## A **A**

Figure A-GBPAA - Sheet 04 Installation of the Reinforcement at the Crossbeam at FR61 and FR62 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 115 6

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

# @A300 SERVICE BULLETIN

**CONF ALL

HOLE SYMBOL ITEM EN6115K3−3 PIN P/N DESCRIPTION KIT 6 ASNA2528−3 COLLAR 4 DIMENSIONS mm (in) A 8.1 0.32 B 9.5 0.37 C 20.0 0.79 D01 REMARKS STDN STARTING HOLE DIAMETER MIN. MAX. FINAL HOLE DIAMETER MIN. MAX. 4.72 mm (0.185 in) 4.76 mm (0.187 in)

EN6115K3X5 PIN ASNA2528−3 COLLAR EN6115K3AX5 PIN ASNA2528−3A COLLAR 10 4 12 5 36
38
50 51 5 52 5 53 RIVET
RIVET
RIVET

RIVET EN6081D4−07
EN6081D6−09
EN6069AD3−05

EN6069AD4−05 EN6115K3A5 COLLAR PIN
EN6115K3AX3 ASNA2528−3A
ASNA2528−3A D01
D01
D01
D01
D01
D01
D01
D01 6−2−N 5.31 mm (0.209 in) 5.38 mm (0.212 in) 5.85 mm (0.230 in) 5.89 mm (0.231 in) 5.06 mm (0.199 in) 5.09 mm (0.20 in)

STDN = STANDARD TOOL DIAMETER NUMBER 5.45 mm (0.215 in) 5.49 mm (0.216 in) 5.85 mm (0.230 in) 5.89 mm (0.231 in) COLLAR PIN EN6115K3−3 PIN ASNA2528−3 COLLAR D01 4−4−N 4.29 mm (0.169 in) 4.34 mm (0.171 in)

DAN5−6−6X COLLAR PIN DAN11−6X D01 5.11 mm (0.201 in) 5.15 mm (0.203 in) DAN5−6−6Y COLLAR PIN DAN11−6Y D01 5.51 mm (0.217 in) 5.55 mm (0.218 in)

HOLES TO BE COLD EXPANDED IN ACCORDANCE WITH SRM 51−30−47 **NOTE:** 03 03

03

55

A_SB_530389_6_BPAA_05_03 6 4

16 56 57 4.72 mm (0.185 in) 4.76 mm (0.187 in)

Figure A-GBPAA - Sheet 05 Installation of the Reinforcement at the Crossbeam at FR61 and FR62 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 116 6

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

# @A300 SERVICE BULLETIN

**CONF ALL

(7 POS)

FR61 **FWD**

A_SB_530389_6_BPAA_06_00 FOR RIVET SYMBOLS, REFER TO SHEET 5 IF REQUIRED, INSTALL 2ND OVERSIZE PINS IF PINS HAVE BEEN REMOVED, INSTALL NEW PINS **NOTE:** 04 05

04 05 

## H

Figure A-GBPAA - Sheet 06 Installation of the Reinforcement at the Crossbeam at FR61 and FR62 DATE: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 117 6

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

# @A300 SERVICE BULLETIN REPORTING SHEET 

### TITLE: FUSELAGE - GENERAL - REINFORCE THE FLOOR CROSSBEAMS AT FR22/FR23 AND FR61/FR62 MODIFICATION No.: 13434D23217 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: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 1 6

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

# @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 4 3 2 1 - Quality rating of the Accomplishment Instructions 4 3 2 1 - Quality rating of the Illustrations 4 3 2 1 - Is this SB easy to understand ? Y / N If you have had difficulties in the accomplishment of this SB please quote 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: Jan 15/10 SERVICE BULLETIN No.: A300-53-0389 REVISION No.: 02 - Apr 27/11 Page: 1 6

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