# @A310 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.A310-53-2133 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 the rework areas on figures, - incorporate minor changes. CHANGES SUMMARY EFFECTIVITY OPERATOR LIST UPDATED R CONCURRENT REQUIREMENTS CONCURRENT REQUIREMENTS UPDATED R PLANNING INFORMATION EFFECTIVITY EFFECTIVITY RELATED INFORMATION UPDATED R Configuration definition CONFIGURATION LIST 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 REFERENCES REFERENCED DOCUMENTATION UPDATED R REFERENCED DOCUMENTATION UPDATED R
DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 1 6

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# @A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET MATERIAL INFORMATION MATERIAL - PRICE AND AVAILABILITY Price and Availability PRICE AND AVAILABILITY UPDATED MATERIAL SET UPDATED R ACCOMPLISHMENT INSTRUCTIONS TASK 532133- 831-848-001- MODIFICATION Subtask 532133-910-201-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED R Subtask 532133-839-201-001 SUBTASK SOLUTION UPDATED R Subtask 532133-910-201-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED R Subtask 532133-839-201-001 SUBTASK SOLUTION UPDATED R Subtask 532133-941-201-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED REFERENCES UPDATED R Subtask 532133-941-201-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED REFERENCES UPDATED R Subtask 532133-831-204-001 SUBTASK SOLUTION UPDATED CONFIGURATION UPDATED FIGURE REFERENCE UPDATED REFERENCED DOCUMENTATION UPDATED R

Subtask 532133-831-208-001 SUBTASK SOLUTION UPDATED R Subtask 532133-831-204-002 SUBTASK SOLUTION UPDATED CONFIGURATION UPDATED FIGURE REFERENCE UPDATED REFERENCED DOCUMENTATION UPDATED R

Subtask 532133-831-208-001 SUBTASK SOLUTION UPDATED R Subtask 532133-942-201-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED REFERENCES UPDATED R Subtask 532133-942-201-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED REFERENCES UPDATED R Fig. A-GBCAA FIGURE SOLUTION UPDATED R Fig. A-GBCAA Sheet 02 SHEET UPDATED R Fig. A-GBCAA Sheet 03 SHEET UPDATED R Fig. A-GBCAA Sheet 05 SHEET UPDATED R Fig. A-GBCAA Sheet 08 SHEET ADDED N 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

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# @A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET 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

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# @A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

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# @A310 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. That 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 reinforce fittings and 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. A310-53-2134 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. A310-53-2094 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. A310-53-2095 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.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 1 6

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# @A310 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. A310-53-2134. 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 532133D01R02 1 1,140.00 Reinforcement and attachment parts Kit 532133D02R01 1 1,030.00 Reinforcement and attachment parts TOTAL 2,170.00 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 532133D01R02 1 1,140.00 Reinforcement and attachment parts Kit 532133D03R01 1 1,090.00 Reinforcement and attachment parts TOTAL 2,230.00 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.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 2 6

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# @A310 SERVICE BULLETIN SUMMARY EFFECTIVITY **CONF ALL This Service Bulletin is applicable to this (these) operator(s) :

18T 19U 52X 58X 82Z 83V 85Z 98W 99Y AFG AIB AIC BAF BBC CFC DAH DEC DGA F2I FDX G8E GAF HFY I2L IRA IRM IYE JAB JAV K1P KAC KYV KZU MGL MWA PIA QAF R1T RJA ROT RZO SBI SGX SUD THY TSC UBD UZB WHT WTJ 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. A310-53-2095 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 MANPOWER **CONF 001 Task 532133-831-848-001: MODIFICATION TOTAL MANHOURS 34.00 ELAPSED TIME (HOURS) 22.00 **CONF 002 Task 532133-831-848-001: MODIFICATION TOTAL MANHOURS 34.00 ELAPSED TIME (HOURS) 22.00 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 3 6

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# @A310 SERVICE BULLETIN SUMMARY APPENDICES **CONF ALL None

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 4 6

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# @A310 SERVICE BULLETIN SUMMARY
**CONF ALL

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2 SEAT TRACK 4 FR21 FR22 FR23 FR24

SEAT TRACK 6 Z130



### A

B_SB_532133_6_SAAA_01_00 AREAS TO BE MODIFIED

**FWD** 

## A
Figure A-GSAAA - Sheet 01

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# @A310 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
B_SB_532133_6_SAAA_02_00 Figure A-GSAAA - Sheet 02

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 6 6

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# @A310 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 310-203 310-204 310-221 310-222 310-304 310-308 310-322 310-324 310-325 (2) Effectivity by MSN 0162 0191 0201 0217 0224 0230 0233 0237 0241 0245 0248 0251 0254 0257 0260 0264 0267 0273 0278 0281 0283 0288 0291 0293 0297 0303 0309 0313 0316 0318 0320 0326 0331 0333 0335 0338-0339 0342-0343 0345-0346 0353 0355-0357 0359-0360 0362 0364 0367 0369-0370 0372 0375 0378-0379 0386 0389-0390 0392 0394 0397 0399-0400 0406-0407 0410 0413 0416 0418-0419 0421-0422 0425 0427-0429 0431 0434 0436-0437 0439 0441 0444-0449 0452 0454 0456-0458 0467 0472-0473 0475-0476 0478 0480-0492 0494-0500 0502-0503 0519-0520 0522-0524 0526-0527 0531 0534 0537-0539 0541-0542 0544-0545 0547 0549-0552 0562 0564-0565 0567-0568 0571 0573-0574 0576 0585-0588 0590-0595 0597 0599-0600 0620 0622 0624 0636 0638 0640 0642 0644 0646-0654 0656 0658 0660-0661 0663 0665 0667 0669 0671-0672 0674 0676 0678 0680 0682 0684 0686-0687 0689 0691 0693 0697 0700 0702 0704 0706

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# @A310 SERVICE BULLETIN (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. OPERATOR MSN 18T 0473 19U 0399 52X 0410 58X 0431 82Z 0550 0551 83V 0427 85Z 0547 98W 0416 99Y 0489 AFG 0496 0497 AIB 0650 0674 0686 AIC 0392 0406 0407 0413 0428 0429 0538 0544 0654 0665 0669 0680 BAF 0367 0372 BBC 0594 0642 0700 CFC 0425 0441 0444 0446 0482 DAH 0291 0293 DEC 0684 0693 0697 DGA 0418 0421 0422 F2I 0309 0419 0487 FDX 0162 0191 0201 0217 0224 0230 0233 0237 0241 0245 0248 0251 0254 0257 0260 0264 0267 0273 0278 0281 0283 0288 0297 0303 0313 0316 0318 0326 0331 0333 0335 0339 0342 0343 0345 0346 0353 0355 0356 0359 0360 0362 0364 0369 0378 0394 0397 0400 0439 0449 0452 0454 0456 0457 0458 0467 0492 0500 0534 0539 0542 0549 0552 0593 0638 G8E 0475 GAF 0434 0484 0498 0499 0503 0522 0523 HFY 0495 0565 I2L 0486 0640 IRA 0338 0370 0375 0379 0389 0390 0436 0671 IRM 0488 0524 0537 0564 0567 0586 0595 0620 IYE 0568 0702 0704 JAB 0320 JAV 0357 0481 K1P 0648 KAC 0647 0649 0663 KYV 0386 KZU 0592 0622 0646 MGL 0526 MWA 0652 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 2 6

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# @A310 SERVICE BULLETIN
OPERATOR MSN PIA 0585 0587 0590 0653 0656 0660 0676 0678 0682 0687 0689 0691 QAF 0667 R1T 0591 RJA 0445 0490 0491 0531 ROT 0636 0644 RZO 0571 0624 0651 0661 SBI 0520 SGX 0519 0562 SUD 0437 THY 0476 0478 0480 0502 TSC 0447 0472 0483 0485 0527 0541 0545 0588 0597 0599 0600 0658 UBD 0672 UZB 0574 0576 0706 WHT 0448 0573 WTJ 0494 (4) Configuration by MSN MSN CONFIGURATION 0162 0191 0201 0217 0224 0230 0233 0237 0241 0245 0248 0251 0254 0257 0260 0264 0267 0273 0278 0281 0283 0288 0291 0293 0297 0303 0309 0313 0316 0318 0320 0326 0331 0333 0335 0338 0339 0342 0343 0345 0346 0353 0355 0356 0357 0359 0360 0362 0364 0367 0369 0370 0372 0375 0378 0379 0386 0389 0390 0392 0394 0397 0399 0400 0406 0407 0410 0413 0416 0418 0419 0421 0422 0425 0427 0428 0429 0431 0434 0436 0437 0441 0444 0445 001

0439 0446 0447 0448 0449 0452 0454 0456 0457 0458 0467 0472 0473 0475 0476 0478 0480 0481 0482 0483 0484 0485 0486 0487 0488 0489 0490 0491 0492 0494 0495 0496 0497 0498 0499 0500 0502 0503 0519 0520 0522 0523 0524 0526 0527 0531 0534 0537 0538 0539 0541 0542 0544 0545 0547 0549 0550 0551 0552 0562 0564 0565 0567 0568 0571 0573 0574 0576 0585 0586 0587 0588 0590 0591 0592 0593 0594 0595 0597 0599 0600 0620 0622 0624 0636 0638 0640 0642 0644 0646 0647 0648 0649 0650 0651 0652 0653 0654 0656 0658 0660 0661 0663 0665 0667 0669 0671 0672 0674 0676 0678 0680 0682 0684 0686 0687 0689 0691 0693 0697 0700 0702 0704 0706 002

(5) Configuration definition **CONF 001 Config. 001 is valid for aircraft on which Modification No. 05596D04241 (FUSELAGE - FLOOR STRUCTURE - MODIFY CROSSBEAM AND SEAT TRACK JUNCTION POINT) is not embodied.

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# @A310 SERVICE BULLETIN **CONF 002 Config. 002 is valid for aircraft on which Modification No. 05596D04241 (FUSELAGE - FLOOR STRUCTURE - MODIFY CROSSBREED AND SEAT TRACK JUNCTION POINT) is embodied. (6) Material Effectivity **CONF 001 MATERIAL QTY PER A/C SEE NOTES Kit 532133D01R02 1 Kit 532133D02R01 1 Component COMPD01 1 Consumable CMLD01 1 Standard tool TOOLD01 2 **CONF 002 MATERIAL QTY PER A/C SEE NOTES Kit 532133D01R02 1 Kit 532133D03R01 1 Component COMPD01 1 Consumable CMLD01 1 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. A310-53-2095 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. That 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 reinforce fittings and 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. DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 4 6

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# @A310 SERVICE BULLETIN A310-53-2134 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. A310-53-2094 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. A310-53-2095 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. A310-53-2134. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : **CONF 001 Task 532133-831-848-001: MODIFICATION (1) Remove the existing fasteners from the crossbeam at FR22 and FR23. (2) Rotating Probe Inspection at the crossbeam FR22 and FR23. (3) Install the reinforcement and brackets at the crossbeam at FR22 and FR23. (4) Remove the brackets and fasteners from the crossbeam FR61 and FR62. (5) Rotating Probe Inspection at the crossbeam FR61 and FR62. (6) Install the reinforcement and bracket at the crossbeam at FR61 and FR62.

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# @A310 SERVICE BULLETIN
**CONF 002 Task 532133-831-848-001: 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 and brackets at the crossbeam at FR22 and FR23. (4) Remove the brackets and fasteners from the crossbeam FR61 and FR62. (5) Rotating Probe Inspection at the crossbeam FR61 and FR62. (6) Install the reinforcement and bracket at the crossbeam at FR61 and FR62. **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. DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 6 6

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# @A310 SERVICE BULLETIN
**CONF 001 Task 532133-831-848-001: 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 FR22 and FR23. 4.00 Install the reinforcement and brackets at the crossbeam at FR22 and FR23. 6.00 Remove the brackets and fasteners from the crossbeam FR61 and FR62. 4.00 Rotating Probe Inspection at the crossbeam FR61 and FR62. 4.00 Install the reinforcement and bracket at the crossbeam at FR61 and FR62. 4.00 Tests 1.00 Close-Up 3.00 TOTAL MANHOURS 34.00 ELAPSED TIME (HOURS) 22.00 **CONF 002 Task 532133-831-848-001: 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 and brackets at the crossbeam at FR22 and FR23. 6.00 Remove the brackets and fasteners from the crossbeam FR61 and FR62. 4.00 Rotating Probe Inspection at the crossbeam FR61 and FR62. 4.00 Install the reinforcement and bracket at the crossbeam at FR61 and FR62. 4.00 Tests 1.00 Close-Up 3.00 TOTAL MANHOURS 34.00 ELAPSED TIME (HOURS) 22.00

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 7 6

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# @A310 SERVICE BULLETIN
**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 +0.533 KG (+1.1750 LB) Effect on Balance +13.696 KGM (+99.063 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 +0.585 KG (+1.2896 LB) Effect on Balance +14.198 KGM (+102.694 LB.FT ) **CONF ALL I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES **CONF 001 Aircraft Maintenance Manual (AMM) 06-41-53 24-00-00 24-41-00 25-54-10 25-55-10 52-30-00 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) 51-10-01 Service Bulletin (SB) A310-53-2094 A310-53-2095 A310-53-2134 Standards Manual (SM) Structural Repair Manual (SRM) 51-27-11 51-40-12 51-40-30 51-40-32 51-40-40 51-40-41 51-76-00 Weight and Balance Manual (WBM) Weight and Balance Manual (WBM) Chapter 1-00-07

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# @A310 SERVICE BULLETIN
**CONF 002 Aircraft Maintenance Manual (AMM) 06-41-53 24-00-00 24-41-00 25-54-10 25-55-10 52-30-00 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) 51-10-01 Service Bulletin (SB) A310-53-2094 A310-53-2095 A310-53-2134 Standards Manual (SM) Structural Repair Manual (SRM) 51-27-11 51-40-12 51-40-30 51-40-32 51-40-40 51-40-41 51-76-00 Weight and Balance Manual (WBM) Weight and Balance Manual (WBM) Chapter 1-00-07 **CONF ALL K. PUBLICATION AFFECTED **CONF 001 Structural Repair Manual (SRM) 53-13-15 53-17-15 **CONF 002 Structural Repair Manual (SRM) 53-13-15 53-17-15 **CONF ALL L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None

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# @A310 SERVICE BULLETIN

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DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 10 6

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# @A310 SERVICE BULLETIN 2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses Kit 532133D01R02 Kit 532133D02R01 Kit 532133D03R01 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 532133D01R02 Cost 1,140.00 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 532133D02R01 Cost 1,030.00 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.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 11 6

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# @A310 SERVICE BULLETIN The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. Kit 532133D03R01 Cost 1,090.00 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 532133D01R02 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 10 EN6115K3X5 16 BOLT 11 EN6115K3A5 10 BOLT 12 EN6115K3AX5 4 BOLT 17 ABS0337-01A 1 RECEPTCL 22 A5327429220200 1 PLATE 23 A5327429220800 1 PLATE 24 F5347726220000 1 ANGLE 25 EN6069D4-05 2 RIVET 26 EN6081D6-09 4 RIVET 27 EN6069AD3-06 2 RIVET 34 DAN5-6-6X 7 PIN 35 DAN11-6X 7 COLLAR 36 DAN5-6-6Y 7 PIN 37 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.

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 12 6

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# @A310 SERVICE BULLETIN
Kit 532133D02R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 1 A5378103420600 1 RNFRCMNT 2 A5378103421400 1 RNFRCMNT 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 15 LN9198-3215CF 4 RIVET 16 DIN65399-3215CF 3 RIVET 34 DAN5-6-6X 7 PIN 35 DAN11-6X 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 532133D03R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 4 ASNA2528-3 36 NUT 5 ASNA2528-3A 14 NUT 6 EN6115K3-3 4 BOLT 7 EN6115K3-4 16 BOLT 9 EN6115K3X4 2 BOLT 10 EN6115K3X5 2 BOLT 13 EN6115K3AX6 4 BOLT 14 EN6115K3A6 10 BOLT 15 LN9198-3215CF 4 RIVET 16 DIN65399-3215CF 3 RIVET 20 A5378103420800 1 RNFRCMNT 21 A5378103421600 1 RNFRCMNT 30 EN6115K3X6 12 BOLT 34 DAN5-6-6X 7 PIN 35 DAN11-6X 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.

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 13 6

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# @A310 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 50 NAS1801-3-26 1 SCREW 51 NAS1149D0332K 2 WASHER 52 NSA5527-03-01D 1 SPACER 53 NSA5527-03-08D 1 SPACER 54 MS21042-3 1 NUT 55 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.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 14 6

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# @A310 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 FTI Tooling List No. FTI-A310-53-2133-1. NOTE: For the definition of capital, durable and expandable tools, refer to SIL 51-012. - 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-A310532133-1 . 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-A310532133-1 . 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.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 15 6

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# @A310 SERVICE BULLETIN

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DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 16 6

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# @A310 SERVICE BULLETIN 3. ACCOMPLISHMENT INSTRUCTIONS Task 532133-831-848-001 - 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 34.00 ELAPSED TIME (HOURS) 22.00 **CONF 002 Zone 130 150 Manpower TOTAL MANHOURS 34.00 ELAPSED TIME (HOURS) 22.00

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 17 6

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# @A310 SERVICE BULLETIN
**CONF ALL A. GENERAL **CONF 001 (1) Subtask 532133-910-201-001 - Standard Practices Work Zones and Access Panels Zone Access/Work location 130 150 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) 06-41-53, Page Block 001 Consumable Material List (CML) Structural Repair Manual (SRM) 51-40-12 51-40-30 51-40-32 51-40-40 51-76-00 (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 06-41-53, Page Block 001).
DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 18 6

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# @A310 SERVICE BULLETIN (d) Remove the old sealant with non-metallic scrapers and a stiff brush. (e) Drill and deburr the rivet holes (Refer to SRM 51-40-40). (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 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 51-40-30). (k) For the procedure to use sealant (Refer to SRM 51-76-00). (l) Apply a sealant bead with : Corrosion Inhibiting Brush Consistency 09-013 As required (m) Install only Hi-Lok fasteners with interference fit in cold expanded holes. (2) Subtask 532133-839-201-001 - Administrative Manpower Resources Skills NON SPECIFIC
DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 19 6

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# @A310 SERVICE BULLETIN Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 002 (1) Subtask 532133-910-201-001 - Standard Practices Work Zones and Access Panels Zone Access/Work location 130 150 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) 06-41-53, Page Block 001 Consumable Material List (CML) Structural Repair Manual (SRM) 51-40-12 51-40-30 51-40-32 51-40-40 51-76-00 (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 06-41-53, Page Block 001). (d) Remove the old sealant with non-metallic scrapers and a stiff brush. DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 20 6

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# @A310 SERVICE BULLETIN (e) Drill and deburr the rivet holes (Refer to SRM 51-40-40). (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 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 51-40-30). (k) For the procedure to use sealant (Refer to SRM 51-76-00). (l) Apply a sealant bead with : Corrosion Inhibiting Brush Consistency 09-013 As required (m) Install only Hi-Lok fasteners with interference fit in cold expanded holes. (2) Subtask 532133-839-201-001 - 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.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 21 6

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# @A310 SERVICE BULLETIN
**CONF ALL B. PREPARATION **CONF 001 (1) Subtask 532133-941-201-001 - Preparation Work Zones and Access Panels Zone Access/Work location 130 150 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) 06-41-53, Page Block 001 24-00-00, Page Block 301 24-41-00, Page Block 301 25-54-10, Page Block 201 25-54-10, Page Block 201 25-55-10, Page Block 201 52-30-00, Page Block 301 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.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 22 6

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# @A310 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 to AMM 25-54-10, Page Block 201 and AMM 06-41-53, 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 toAMM 25-55-10, Page Block 201 and AMM 06-41-53, Page Block 001). (l) Remove the door actuator lining between FR61 and FR62 for access. (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 532133-941-201-001 - Preparation Work Zones and Access Panels Zone Access/Work location 130 150 Manpower Resources Skills NON SPECIFIC

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 23 6

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# @A310 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) 06-41-53, Page Block 001 24-00-00, Page Block 301 24-41-00, Page Block 301 25-54-10, Page Block 201 25-54-10, Page Block 201 25-55-10, Page Block 201 52-30-00, Page Block 301 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.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 24 6

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# @A310 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 to AMM 25-54-10, Page Block 201 and AMM 06-41-53, 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 toAMM 25-55-10, Page Block 201 and AMM 06-41-53, Page Block 001). (l) Remove the door actuator lining between FR61 and FR62 for access. (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. A310-53-2134 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. A310-53-2094 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. A310-53-2095 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.

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# @A310 SERVICE BULLETIN
**CONF 001 (1) Subtask 532133-831-201-001 - 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 Material necessary to do the job Kit 532133D02R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 16 DIN65399-3215CF 3 RIVET Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Cleaning Solvent 11-016 As required Solvent General Purpose 11-026 As required References Consumable Material List (CML) Fig. A-GBAAA Removal of the Existing Fasteners from the Crossbeam 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 fasteners from the crossbeam at FR22. 1 Remove the existing fasteners : Fig. A-GBAAA Sheet 02, Detail B, and Fig. A-GBAAA Sheet 03, Detail D 2 Clean the fastener holes and the adjacent area with : Cleaning Solvent 11-016 As required

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 26 6

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# @A310 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 brackets and fasteners from the crossbeam at FR23. 1 Remove the existing fasteners and the brackets : Fig. A-GBAAA Sheet 02, Detail C, and Fig. A-GBAAA Sheet 03, Detail E 2 Bracket A9249161420100 Item (3) Retain a Close the three holes with : 3 Rivet DIN65399-3215CF Item 16 NOTE: An inspection of these holes is not necessary. 2 Clean the fastener holes and the adjacent area with : Cleaning Solvent 11-016 As required (2) Subtask 532133-831-202-001 - 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) 51-10-01 PART 6, Procedure A

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 27 6

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# @A310 SERVICE BULLETIN
References Fig. A-GBCAA Installation of the Reinforcement at the Crossbeam 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 51-10-01 PART 6, Procedure A). Refer to Fig. A-GBCAA 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 51-10-01 PART 6, Procedure A). 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 532133-831-204-001 - Install the reinforcement and brackets at the crossbeam at FR22 and FR23. Work Zones and Access Panels Zone Access/Work location 130 Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 28 6

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# @A310 SERVICE BULLETIN Material necessary to do the job Kit 532133D02R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 A5378103420600 1 RNFRCMNT 2 A5378103421400 1 RNFRCMNT 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 15 LN9198-3215CF 4 RIVET 34 DAN5-6-6X 7 PIN 35 DAN11-6X 7 COLLAR 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) 51-27-11 51-40-41 51-76-00 Fig. A-GBCAA Installation of the Reinforcement at the Crossbeam 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-GBCAA Sheet 02, Detail B, Fig. A-GBCAA Sheet 03, Detail E, Fig. A-GBCAA Sheet 05, Fig. A-GBCAA Sheet 07, Detail J and K and Fig. A-GBCAA Sheet 08, Detail L and M

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 29 6

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# @A310 SERVICE BULLETIN
1 If the reinforcement, Item 1, 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-GBCAA Sheet 07, Details J and K 2 If the reinforcement, Item 1, 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-GBCAA Sheet 08, Details L and M 3 At FR22 install temporarily : 1 Reinforcement A5378103420600 Item 1 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 where no cracks were found. Refer to SRM 51-40-41 Refer to FTI Tooling List No. FTI-A310-53-2133-1 Refer to Fig. A-GBCAA Sheet 03, Detail E, and Fig. A-GBCAA Sheet 05 7 Ream the specified 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 8 Remove the temporarily installed item 1. 9 Clean the reamed fastener holes with : Solvent General Purpose 11-026 As required

10 Install the reinforcement, Item 1, with : Refer to SRM 51-76-00 22 Nut ASNA2528-3 Item 4 2 Nut ASNA2528-3A Item 5 6 Bolt EN6115K3-3 Item 6 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 30 6

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# @A310 SERVICE BULLETIN
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-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 34 7 Collar DAN11-6X Item 35 (c) Install the reinforcement and brackets at the crossbeam at FR23. Refer to Fig. A-GBCAA Sheet 02, Detail C, Fig. A-GBCAA Sheet 04, Detail G, and Fig. A-GBCAA Sheet 05 1 At FR23 install temporarily : 1 Reinforcement A5378103421400 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 where no cracks were found. Refer to SRM 51-40-41 Refer to FTI Tooling List No. FTI-A310-53-2133-1 Refer to Fig. A-GBCAA Sheet 04, Detail G, and Fig. A-GBCAA Sheet 05 5 Ream the specified 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 2. 7 Clean the reamed fastener holes with : Solvent General Purpose 11-026 As required

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 31 6

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# @A310 SERVICE BULLETIN
8 Install the reinforcement, Item 2, 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 9 At FR23 put in position and install : 2 Bracket A9249161420100 Item (3) Retained at removal with : 4 Rivet LN9198-3215CF Item 15 (d) Perform minor amendment of screws, spacers and split conduits (Refer to ESPM 20-33-11 and ESPM 20-33-33). (4) Subtask 532133-831-206-001 - Remove the brackets and fasteners from the crossbeam FR61 and FR62. Work Zones and Access Panels Zone Access/Work location 150 Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME Material necessary to do the job Kit 532133D01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 25 EN6069D4-05 2 RIVET 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) DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 32 6

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# @A310 SERVICE BULLETIN
References Fig. A-GBJAA Removal of the Existing Fasteners from the Crossbeam 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-GBJAA Sheet 02, Detail B, and Fig. A-GBJAA Sheet 03, Detail D 2 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 FR61, remove them. 1 Remove the existing pins : Refer to Fig. A-GBJAA Sheet 02, Detail B, and Fig. A-GBJAA Sheet 04, Detail F 2 Clean the pin holes and the adjacent area with : Solvent General Purpose 11-026 As required (c) Remove the brackets and the fasteners from the crossbeam FR62. 1 Remove the brackets and the fasteners : Refer to Fig. A-GBJAA Sheet 02, Detail C, and Fig. A-GBJAA Sheet 03, Detail E 1 Receptacle DAN367-01 Item (17) Discard 1 Bracket A9249193420000 Item (18) Discard and close the two holes with : 2 Rivet EN6069D4-05 Item 25 2 Clean the fastener holes and the adjacent area with : Solvent General Purpose 11-026 As required
DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 33 6

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# @A310 SERVICE BULLETIN (5) Subtask 532133-832-202-001 - 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) 51-10-01 PART 6, Procedure A Fig. A-GBLAA Installation of the Reinforcement at the Crossbeam 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 51-10-01 PART 6, Procedure A). Refer to Fig. A-GBLAA 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 51-10-01 PART 6, Procedure A). Refer to Fig. A-GBLAA 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. DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 34 6

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# @A310 SERVICE BULLETIN (6) Subtask 532133-831-208-001 - Install the reinforcement and bracket at the crossbeam at FR61 and FR62. Work Zones and Access Panels Zone Access/Work location 150 Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME Material necessary to do the job Kit 532133D01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 4 ASNA2528-3 32 NUT 5 ASNA2528-3A 14 NUT 6 EN6115K3-3 16 BOLT 10 EN6115K3X5 16 BOLT 11 EN6115K3A5 10 BOLT 12 EN6115K3AX5 4 BOLT 17 ABS0337-01A 1 RECEPTCL 22 A5327429220200 1 PLATE 23 A5327429220800 1 PLATE 24 F5347726220000 1 ANGLE 26 EN6081D6-09 4 RIVET 27 EN6069AD3-06 2 RIVET 34 DAN5-6-6X 7 PIN 35 DAN11-6X 7 COLLAR 36 DAN5-6-6Y 7 PIN 37 DAN11-6Y 7 COLLAR Component COMPD01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 50 NAS1801-3-26 1 SCREW 51 NAS1149D0332K 2 WASHER 52 NSA5527-03-01D 1 SPACER 53 NSA5527-03-08D 1 SPACER 54 MS21042-3 1 NUT 55 MS21919WCH3 1 CLAMP

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 35 6

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# @A310 SERVICE BULLETIN
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) 51-40-41 51-76-00 Fig. A-GBLAA Installation of the Reinforcement at the Crossbeam 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-GBLAA Sheet 02, Detail B, Fig. A-GBLAA Sheet 03, Detail E, and Fig. A-GBLAA Sheet 05 1 At FR61 install temporarily : 1 Reinforcement A5327429220200 Item 22 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 51-40-41 Refer to FTI Tooling List No. FTI-A310-53-2133-1 Refer to Fig. A-GBLAA Sheet 03, Detail E, and Fig. A-GBLAA Sheet 05 5 Ream the specified holes on the reinforcement and structure with the correct gage finish reamer. Refer to Fig. A-GBLAA Sheet 03, Detail E, and Fig. A-GBLAA Sheet 05 6 Remove the temporarily installed Item 22. 7 Clean the reamed fastener holes with : Solvent General Purpose 11-026 As required

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 36 6

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# @A310 SERVICE BULLETIN
8 Install the reinforcement, Item 22, with : Refer to SRM 51-76-00 24 Nut ASNA2528-3 Item 4 2 Nut ASNA2528-3A Item 5 8 Bolt EN6115K3-3 Item 6 16 Bolt EN6115K3X5 Item 10 2 Bolt EN6115K3AX5 Item 12 (b) If pins have been removed from the actuator beam at FR61, install new pins. Refer to Fig. A-GBLAA Sheet 02, Detail B, Fig. A-GBLAA Sheet 05 and Fig. AGBLAA 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 34 7 Collar DAN11-6X Item 35 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 36 7 Collar DAN11-6Y Item 37 (c) Install the reinforcement and bracket at the crossbeam at FR62. Refer to Fig. A-GBLAA Sheet 02, Detail C, Fig. A-GBLAA Sheet 04, Detail G, and Fig. A-GBLAA Sheet 05 1 At FR62 hold in position temporarily : 1 Bracket F5347726220000 Item 24 2 If a plastic cable support interferes with bracket, Item 24, replace the plastic cable support with the following : Refer to ESPM 20-33-11 1 Screw NAS1801-3-26 Item 50 2 Washer NAS1149D0332K Item 51 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 37 6

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# @A310 SERVICE BULLETIN 1 Spacer NSA5527-03-01D Item 52 1 Spacer NSA5527-03-08D Item 53 1 Nut MS21042-3 Item 54 1 Clamp MS21919WCH3 Item 55 NOTE: The screw, Item 50, has to be installed from the AFT of the FR62 and the clamp, Item 55, has to be orientated at 12 o’clock position (Up). 3 At FR62 install temporarily : 1 Reinforcement A5327429220800 Item 23 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 where no cracks were found. Refer to SRM 51-40-41 Refer to FTI Tooling List No. FTI-A310-53-2133-1 Refer to Fig. A-GBLAA Sheet 04, Detail G, and Fig. A-GBLAA Sheet 05 7 Ream the specified holes on the reinforcement and structure with the correct gage finish reamer. Refer to Fig. A-GBLAA Sheet 04, Detail G, and Fig. A-GBLAA Sheet 05 8 Remove the temporarily installed Item 23. 9 Clean the reamed fastener holes with : Solvent General Purpose 11-026 As required

10 Install the reinforcement, Item 23 with : Refer to SRM 51-76-00 Refer to Fig. A-GBLAA Sheet 04, Detail G 8 Nut ASNA2528-3 Item 4 12 Nut ASNA2528-3A Item 5 8 Bolt EN6115K3-3 Item 6
DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 38 6

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# @A310 SERVICE BULLETIN
10 Bolt EN6115K3A5 Item 11 2 Bolt EN6115K3AX5 Item 12 11 At FR62 install : Refer to Fig. A-GBLAA Sheet 04, Detail G and Section A-A 1 Bracket F5347726220000 Item 24 1 Receptacle ABS0337-01A Item 17 with : 4 Rivet EN6081D6-09 Item 26 2 Rivet EN6069AD3-06 Item 27 (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 532133-831-201-002 - 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 Material necessary to do the job Kit 532133D03R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 16 DIN65399-3215CF 3 RIVET Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Cleaning Solvent 11-016 As required Solvent General Purpose 11-026 As required

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 39 6

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# @A310 SERVICE BULLETIN
References Consumable Material List (CML) Fig. A-GBEAA Removal of the Existing Fasteners from the Crossbeam 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 from the crossbeam at FR22. 1 Remove the existing fasteners : Refer to Fig. A-GBEAA Sheet 02, Detail B, and Fig. A-GBEAA Sheet 03, Detail D 2 Clean the fastener holes and the adjacent area with : Cleaning Solvent 11-016 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 fasteners from the crossbeam at FR23. 1 Remove the existing fasteners and the brackets : Refer to Fig. A-GBEAA Sheet 02, Detail C, and Fig. A-GBEAA Sheet 03, Detail E 2 Bracket A9249161420100 Item (3) Retain a Close the three holes with : 3 Rivet DIN65399-3215CF Item 16 NOTE: An inspection of these holes is not necessary. 2 Clean the fastener holes and the adjacent area with : Cleaning Solvent 11-016 As required
DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 40 6

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# @A310 SERVICE BULLETIN (2) Subtask 532133-831-202-002 - 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) 51-10-01 PART 6, Procedure A Fig. A-GBGAA Installation of the Reinforcement at the Crossbeam 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 51-10-01 PART 6, Procedure A). 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 51-10-01 PART 6, Procedure A). Refer to Fig. A-GBGAA Sheet 04, Detail F a If no crack(s) are found : <1> - Refer to para. (3)(c).

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 41 6

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# @A310 SERVICE BULLETIN
b If crack(s) are found : <1> Contact AIRBUS for further instructions. (3) Subtask 532133-831-204-002 - Install the reinforcement and brackets at the crossbeam at FR22 and FR23. Work Zones and Access Panels Zone Access/Work location 130 Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME Material necessary to do the job Kit 532133D03R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 4 ASNA2528-3 36 NUT 5 ASNA2528-3A 14 NUT 6 EN6115K3-3 4 BOLT 7 EN6115K3-4 16 BOLT 9 EN6115K3X4 2 BOLT 10 EN6115K3X5 2 BOLT 13 EN6115K3AX6 4 BOLT 14 EN6115K3A6 10 BOLT 15 LN9198-3215CF 4 RIVET 20 A5378103420800 1 RNFRCMNT 21 A5378103421600 1 RNFRCMNT 30 EN6115K3X6 12 BOLT 34 DAN5-6-6X 7 PIN 35 DAN11-6X 7 COLLAR 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) 51-27-11 51-40-41 51-76-00 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 42 6

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# @A310 SERVICE BULLETIN
References Fig. A-GBGAA Installation of the Reinforcement at the Crossbeam 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 A5378103420800 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 where no cracks were found. Refer to SRM 51-40-41 Refer to FTI Tooling List No. FTI-A310-53-2133-1 Refer to Fig. A-GBGAA Sheet 03, Detail E, and Fig. A-GBGAA Sheet 05 7 Ream the specified 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 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 43 6

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# @A310 SERVICE BULLETIN
8 Remove the temporarily installed Item 20. 9 Clean the reamed fastener holes with : Solvent General Purpose 11-026 As required

10 Install the reinforcement, Item 20, with : Refer to SRM 51-76-00 24 Nut ASNA2528-3 Item 4 2 Nut ASNA2528-3A Item 5 8 Bolt EN6115K3-4 Item 7 2 Bolt EN6115K3X4 Item 9 2 Bolt EN6115K3X5 Item 10 2 Bolt EN6115K3AX6 Item 13 12 Bolt EN6115K3X6 Item 30 (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 34 7 Collar DAN11-6X Item 35 (c) Install the reinforcement and brackets 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 FR23 install temporarily : 1 Reinforcement A5378103421600 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. 4 Cold expand the specified fastener holes where no cracks were found. Refer to SRM 51-40-41 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 44 6

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# @A310 SERVICE BULLETIN Refer to FTI Tooling List No. FTI-A310-53-2133-1 Refer to Fig. A-GBGAA Sheet 04, Detail G, and Fig. A-GBGAA Sheet 05 5 Ream the specified holes on the reinforcement and structure with the correct gage finish reamer. Refer to Fig. A-GBGAA Sheet 04, Detail G, and Fig. A-GBGAA Sheet 05 6 Remove the temporarily installed Item 21. 7 Clean the reamed fastener holes with : Solvent General Purpose 11-026 As required 8 Install the reinforcement, Item 21, with : (Refer to SRM 51-76-00 12 Nut ASNA2528-3 Item 4 12 Nut ASNA2528-3A Item 5 4 Bolt EN6115K3-3 Item 6 8 Bolt EN6115K3-4 Item 7 2 Bolt EN6115K3AX6 Item 13 10 Bolt EN6115K3A6 Item 14 9 At FR23 put in position and install : 2 Bracket A9249161420100 Item (3) Retained at removal with : 4 Rivet LN9198-3215CF Item 15 (d) Perform minor amendment of screws, spacers and split conduits (Refer to ESPM 20-33-11 and ESPM 20-33-33). (4) Subtask 532133-831-206-001 - Remove the brackets and fasteners from the crossbeam FR61 and FR62. Work Zones and Access Panels Zone Access/Work location 150

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 45 6

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# @A310 SERVICE BULLETIN Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME Material necessary to do the job Kit 532133D01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 25 EN6069D4-05 2 RIVET 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-GBJAA Removal of the Existing Fasteners from the Crossbeam 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-GBJAA Sheet 02, Detail B, and Fig. A-GBJAA Sheet 03, Detail D 2 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 FR61, remove them. 1 Remove the existing pins : Refer to Fig. A-GBJAA Sheet 02, Detail B, and Fig. A-GBJAA Sheet 04, Detail F

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 46 6

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# @A310 SERVICE BULLETIN
2 Clean the pin holes and the adjacent area with : Solvent General Purpose 11-026 As required (c) Remove the brackets and the fasteners from the crossbeam FR62. 1 Remove the brackets and the fasteners : Refer to Fig. A-GBJAA Sheet 02, Detail C, and Fig. A-GBJAA Sheet 03, Detail E 1 Receptacle DAN367-01 Item (17) Discard 1 Bracket A9249193420000 Item (18) Discard and close the two holes with : 2 Rivet EN6069D4-05 Item 25 2 Clean the fastener holes and the adjacent area with : Solvent General Purpose 11-026 As required (5) Subtask 532133-832-202-001 - 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) 51-10-01 PART 6, Procedure A Fig. A-GBLAA Installation of the Reinforcement at the Crossbeam FR61 and FR62 Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 47 6

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# @A310 SERVICE BULLETIN (a) Rotating Probe Inspection at the crossbeam at FR61. 1 Do a rotating probe inspection of the fastener holes at FR61 (Refer to NTM 51-10-01 PART 6, Procedure A). Refer to Fig. A-GBLAA 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 51-10-01 PART 6, Procedure A). Refer to Fig. A-GBLAA 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 532133-831-208-001 - Install the reinforcement and bracket at the crossbeam at FR61 and FR62. Work Zones and Access Panels Zone Access/Work location 150 Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills AIRFRAME Material necessary to do the job Kit 532133D01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 4 ASNA2528-3 32 NUT 5 ASNA2528-3A 14 NUT 6 EN6115K3-3 16 BOLT 10 EN6115K3X5 16 BOLT DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 48 6

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# @A310 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 11 EN6115K3A5 10 BOLT 12 EN6115K3AX5 4 BOLT 17 ABS0337-01A 1 RECEPTCL 22 A5327429220200 1 PLATE 23 A5327429220800 1 PLATE 24 F5347726220000 1 ANGLE 26 EN6081D6-09 4 RIVET 27 EN6069AD3-06 2 RIVET 34 DAN5-6-6X 7 PIN 35 DAN11-6X 7 COLLAR 36 DAN5-6-6Y 7 PIN 37 DAN11-6Y 7 COLLAR Component COMPD01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 50 NAS1801-3-26 1 SCREW 51 NAS1149D0332K 2 WASHER 52 NSA5527-03-01D 1 SPACER 53 NSA5527-03-08D 1 SPACER 54 MS21042-3 1 NUT 55 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) 51-40-41 51-76-00 Fig. A-GBLAA Installation of the Reinforcement at the Crossbeam 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-GBLAA Sheet 02, Detail B, Fig. A-GBLAA Sheet 03, Detail E, and Fig. A-GBLAA Sheet 05

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 49 6

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# @A310 SERVICE BULLETIN
1 At FR61 install temporarily : 1 Reinforcement A5327429220200 Item 22 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 51-40-41 Refer to FTI Tooling List No. FTI-A310-53-2133-1 Refer to Fig. A-GBLAA Sheet 03, Detail E, and Fig. A-GBLAA Sheet 05 5 Ream the specified holes on the reinforcement and structure with the correct gage finish reamer. Refer to Fig. A-GBLAA Sheet 03, Detail E, and Fig. A-GBLAA Sheet 05 6 Remove the temporarily installed Item 22. 7 Clean the reamed fastener holes with : Solvent General Purpose 11-026 As required 8 Install the reinforcement, Item 22, with : Refer to SRM 51-76-00 24 Nut ASNA2528-3 Item 4 2 Nut ASNA2528-3A Item 5 8 Bolt EN6115K3-3 Item 6 16 Bolt EN6115K3X5 Item 10 2 Bolt EN6115K3AX5 Item 12 (b) If pins have been removed from the actuator beam at FR61, install new pins. Refer to Fig. A-GBLAA Sheet 02, Detail B, Fig. A-GBLAA Sheet 05 and Fig. AGBLAA 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 34 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 50 6

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# @A310 SERVICE BULLETIN
7 Collar DAN11-6X Item 35 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 36 7 Collar DAN11-6Y Item 37 (c) Install the reinforcement and bracket at the crossbeam at FR62. Refer to Fig. A-GBLAA Sheet 02, Detail C, Fig. A-GBLAA Sheet 04, Detail G, and Fig. A-GBLAA Sheet 05 1 At FR62 hold in position temporarily : 1 Bracket F5347726220000 Item 24 2 If a plastic cable support interferes with bracket, Item 24, replace the plastic cable support with the following : Refer to ESPM 20-33-11 1 Screw NAS1801-3-26 Item 50 2 Washer NAS1149D0332K Item 51 1 Spacer NSA5527-03-01D Item 52 1 Spacer NSA5527-03-08D Item 53 1 Nut MS21042-3 Item 54 1 Clamp MS21919WCH3 Item 55 NOTE: The screw, Item 50, has to be installed from the AFT of the FR62 and the clamp, Item 55, has to be orientated at 12 o’clock position (Up). 3 At FR62 install temporarily : 1 Reinforcement A5327429220800 Item 23 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 where no cracks were found. Refer to SRM 51-40-41 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 51 6

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# @A310 SERVICE BULLETIN Refer to FTI Tooling List No. FTI-A310-53-2133-1 Refer to Fig. A-GBLAA Sheet 04, Detail G, and Fig. A-GBLAA Sheet 05 7 Ream the specified holes on the reinforcement and structure with the correct gage finish reamer. Refer to Fig. A-GBLAA Sheet 04, Detail G, and Fig. A-GBLAA Sheet 05 8 Remove the temporarily installed Item 23. 9 Clean the reamed fastener holes with : Solvent General Purpose 11-026 As required

10 Install the reinforcement, Item 23 with : Refer to SRM 51-76-00 Refer to Fig. A-GBLAA Sheet 04, Detail G 8 Nut ASNA2528-3 Item 4 12 Nut ASNA2528-3A Item 5 8 Bolt EN6115K3-3 Item 6 10 Bolt EN6115K3A5 Item 11 2 Bolt EN6115K3AX5 Item 12 11 At FR62 install : Refer to Fig. A-GBLAA Sheet 04, Detail G and Section A-A 1 Bracket F5347726220000 Item 24 1 Receptacle ABS0337-01A Item 17 with : 4 Rivet EN6081D6-09 Item 26 2 Rivet EN6069AD3-06 Item 27 (d) Perform minor amendment of screws, spacers and split conduits (Refer to ESPM 20-33-11 and ESPM 20-33-33).

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 52 6

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# @A310 SERVICE BULLETIN
**CONF ALL D. TEST **CONF 001 (1) Subtask 532133-700-201-001 - Testing Work Zones and Access Panels Zone Access/Work location 130 150 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 52-30-00, Page Block 301 52-33-18, Page Block 401 52-33-18, Page Block 501 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the FWD cargo-compartment actuator to the actuator support beam (Refer to AMM 52-33-18, Page Block 401). (c) Install the AFT cargo-compartment actuator to the actuator 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.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 53 6

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# @A310 SERVICE BULLETIN
**CONF 002 (1) Subtask 532133-700-201-001 - Testing Work Zones and Access Panels Zone Access/Work location 130 150 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 52-30-00, Page Block 301 52-33-18, Page Block 401 52-33-18, Page Block 501 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the FWD cargo-compartment actuator to the actuator support beam (Refer to AMM 52-33-18, Page Block 401). (c) Install the AFT cargo-compartment actuator to the actuator 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.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 54 6

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# @A310 SERVICE BULLETIN
**CONF ALL E. CLOSE-UP **CONF 001 (1) Subtask 532133-942-201-001 - Close-up Work Zones and Access Panels Zone Access/Work location 130 150 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001 25-54-10, Page Block 201 25-55-10, Page Block 201 52-30-00, Page Block 301 (a) Install the retained FWD cargo-compartment ceiling panels (Refer to AMM 25-54-10, Page Block 201 and AMM 06-41-53, Page Block 001). (b) Install the door actuator lining between FR22 and FR23. (c) Install the retained AFT cargo-compartment ceiling panels (Refer to AMM 25-55-10, Page Block 201 and AMM 06-41-53, Page Block 001). (d) Install the door actuator lining between FR61 and FR62. (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 AMM 52-30-00, Page Block 301). (h) Remove the access platform(s). **CONF 002 (1) Subtask 532133-942-201-001 - Close-up Work Zones and Access Panels Zone Access/Work location 130 150
DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 55 6

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# @A310 SERVICE BULLETIN Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001 25-54-10, Page Block 201 25-55-10, Page Block 201 52-30-00, Page Block 301 (a) Install the retained FWD cargo-compartment ceiling panels (Refer to AMM 25-54-10, Page Block 201 and AMM 06-41-53, Page Block 001). (b) Install the door actuator lining between FR22 and FR23. (c) Install the retained AFT cargo-compartment ceiling panels (Refer to AMM 25-55-10, Page Block 201 and AMM 06-41-53, Page Block 001). (d) Install the door actuator lining between FR61 and FR62. (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 AMM 52-30-00, Page Block 301). (h) Remove the access platform(s).

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 56 6

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# @A310 SERVICE BULLETIN

**CONF 001

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2 SEAT TRACK 4 FR21 FR22 FR23 FR24



### B

**C** SEAT TRACK 6

B_SB_532133_6_BAAA_01_00 Z130



### A

**FWD** 

## A

Figure A-GBAAA - Sheet 01 Removal of the Existing Fasteners from the Crossbeam FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 57 6

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# @A310 SERVICE BULLETIN

**CONF 001



### D FR22



### E 

## B

FR23 (3)

(3)



## C

B_SB_532133_6_BAAA_02_01 

### F

Figure A-GBAAA - Sheet 02 Removal of the Existing Fasteners from the Crossbeam FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 58 6

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# @A310 SERVICE BULLETIN

**CONF 001

**NOTE:** 01 (7 POS)

01 (7 POS) 01

01 01

VIEW LOOKING FWD

VIEW LOOKING AFT FR22

FR23 01 (6 POS) 01 (6 POS)

01 02 02

HOLE SYMBOL ITEM DIN65399−3215CF RIVET P/N DESCRIPTION KIT REMARKS 16 

## D

**E**

EXISTING FASTENER TO BE REMOVED 02 CLOSED EXISTING HOLES. AN INSPECTION OF THESE HOLES 01 IS NOT NECESSARY B_SB_532133_6_BAAA_03_01 D02

Figure A-GBAAA - Sheet 03 Removal of the Existing Fasteners from the Crossbeam FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 59 6

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# @A310 SERVICE BULLETIN

**CONF 001

IF PINS ARE INSTALLED, REMOVE THEM 03 03 (7 POS)

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

B_SB_532133_6_BAAA_04_00



## F

Figure A-GBAAA - Sheet 04 Removal of the Existing Fasteners from the Crossbeam FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 60 6

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# @A310 SERVICE BULLETIN

**CONF 001

B_SB_532133_6_BCAA_01_00 SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2 SEAT TRACK 4 FR21 FR22 FR23 FR24



### B

**C** SEAT TRACK 6 Z130



### A

**FWD** 

## A

Figure A-GBCAA - Sheet 01 Installation of the Reinforcement at the Crossbeam FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 61 6

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# @A310 SERVICE BULLETIN

**CONF 001 FR22

FR23

2

(3) (3)

### H**J K** 

**D E** 

**F G**  

## C **B** 1



### L **M**

B_SB_532133_6_BCAA_02_04 Figure A-GBCAA - Sheet 02 Installation of the Reinforcement at the Crossbeam FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 62 6

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# @A310 SERVICE BULLETIN

**CONF 001

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

01 01 (7 POS)

(7 POS)

VIEW LOOKING FWD FR22

VIEW LOOKING FWD FR22

FOR RIVETS SYMBOLS, REFER TO SHEET 5 1

A

FOR DIMENSIONS, REFER TO SHEET 5 01

POSITION OF SPLIT IN EXPANSION SLEEVE DURING COLD EXPANSION 02

02 0202 

## D

**E**

B_SB_532133_6_BCAA_03_02 Figure A-GBCAA - Sheet 03 Installation of the Reinforcement at the Crossbeam FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 63 6

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# @A310 SERVICE BULLETIN

**CONF 001

VIEW LOOKING AFT FR23

VIEW LOOKING AFT FR23

FOR RIVETS SYMBOLS, REFER TO SHEET 5 01 01 (6 POS)

(6 POS)

HOLES TO BE INSPECTED IN ACCORDANCE WITH NTM 51−10−01 01 HOLES TO BE COLD EXPANDED IN ACCORDANCE WITH SRM 51−30−47 02 **NOTE:** 2

D F
H J

FOR DIMENSIONS, REFER TO SHEET 5

POSITION OF SPLIT IN EXPANSION SLEEVE DURING COLD EXPANSION 02 02 02 (3)

(3)

B_SB_532133_6_BCAA_04_02 

## F

**G**

Figure A-GBCAA - Sheet 04 Installation of the Reinforcement at the Crossbeam FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 64 6

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# @A310 SERVICE BULLETIN

**CONF 001

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

EN6115K3X4 PIN ASNA2528−3 COLLAR EN6115K3X5 PIN ASNA2528−3 COLLAR 9 4 10 4

EN6115K3AX6 PIN ASNA2528−3A COLLAR 13 5 D02

D02
D02

D02 mmDIMENSIONS (in)

C B A 1.6 0.06 0.16 0.31 4.0 R 8.0

LN9198−3215CF RIVET 15 EN6115K3A6 PIN ASNA2528−3A COLLAR 14 5 D02 EN6115K3AX5 PIN ASNA2528−3A COLLAR 12 5 D02 REMARKS STDN STARTING HOLE DIAMETER MIN. MAX. 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) 5.06 mm (0.199 in) 5.09 mm (0.20 in) 5.45 mm (0.215 in) 5.49 mm (0.216 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) 5.85 mm (0.230 in) 5.89 mm (0.231 in)

HOLES TO BE COLD EXPANDED IN ACCORDANCE WITH SRM 51−30−47 02 **NOTE:** EN6115K3−3 PIN ASNA2528−3 COLLAR D02 4−4−N 4.29 mm (0.169 in) 4.34 mm (0.171 in) 4.72 mm (0.185 in) 4.76 mm (0.187 in)

STDN = STANDARD TOOL DIAMETER NUMBER DAN5−6−6X PIN COLLAR DAN11−6X 5.11mm (0.201 in) 5.15mm (0.203 in) D02 02

02
02 6 4

34 35 D02 E D 1.10 1.50 28.0 38.1 F G 1.77 1.57 40.0 45.0 H 1.93 49.0 J 2.89 73.5 K 1.30 33.0 L 1.61 41.0

B_SB_532133_6_BCAA_05_03 Figure A-GBCAA - Sheet 05 Installation of the Reinforcement at the Crossbeam FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 65 6

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# @A310 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**

B_SB_532133_6_BCAA_06_00



## H

Figure A-GBCAA - Sheet 06 Installation of the Reinforcement at the Crossbeam FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 66 6

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# @A310 SERVICE BULLETIN

**CONF 001

REWORK THE REINFORCEMENT, ITEM 1, TO THE NEW CONTOUR 05 IN ACCORDANCE WITH SRM 51−27−11 C B E G
C C

FOR DIMENSIONS, REFER TO SHEET 5 05 04

REINFORCEMENT, ITEM 1, WITH OLD CONTOUR 04 **NOTE:** 

## J

**K** 1 1

B_SB_532133_6_BCAA_07_00 Figure A-GBCAA - Sheet 07 Installation of the Reinforcement at the Crossbeam FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 67 6

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# @A310 SERVICE BULLETIN

**CONF 001

REWORK THE REINFORCEMENT, ITEM 1, TO THE NEW CONTOUR 05 IN ACCORDANCE WITH SRM 51−27−11 C B E G
C C

FOR DIMENSIONS, REFER TO SHEET 5 04

REINFORCEMENT, ITEM 1, WITH OLD CONTOUR 04 **NOTE:** 1

B K L
C C 05 1 

## L

**M** C

B_SB_532133_6_BCAA_08_00 Figure A-GBCAA - Sheet 08 Installation of the Reinforcement at the Crossbeam FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 68 6

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# @A310 SERVICE BULLETIN

**CONF 002

B_SB_532133_6_BEAA_01_00 SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2 SEAT TRACK 4 FR21 FR22 FR23 FR24



### B

**C** SEAT TRACK 6 Z130



### A

**FWD** 

## A

Figure A-GBEAA - Sheet 01 Removal of the Existing Fasteners from the Crossbeam FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 69 6

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# @A310 SERVICE BULLETIN

**CONF 002



### D FR22



### E 

## B

FR23 (3)

(3)



## C

B_SB_532133_6_BEAA_02_01 

### F

Figure A-GBEAA - Sheet 02 Removal of the Existing Fasteners from the Crossbeam FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 70 6

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# @A310 SERVICE BULLETIN

**CONF 002

**NOTE:** 01 (7 POS)

01 (7 POS) 01

01 01

VIEW LOOKING FWD

VIEW LOOKING AFT FR22

FR23 01 (6 POS) 01 (6 POS)

01 02 02

HOLE SYMBOL ITEM DIN65399−3215CF RIVET P/N DESCRIPTION KIT REMARKS 16 

## D

**E**

B_SB_532133_6_BEAA_03_01 EXISTING FASTENER TO BE REMOVED 02 CLOSED EXISTING HOLES. AN INSPECTION OF THESE HOLES 01 IS NOT NECESSARY D03

Figure A-GBEAA - Sheet 03 Removal of the Existing Fasteners from the Crossbeam FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 71 6

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# @A310 SERVICE BULLETIN

**CONF 002

IF PINS ARE INSTALLED, REMOVE THEM 03 03 (7 POS)

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

B_SB_532133_6_BEAA_04_00



## F

Figure A-GBEAA - Sheet 04 Removal of the Existing Fasteners from the Crossbeam FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 72 6

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# @A310 SERVICE BULLETIN

**CONF 002

B_SB_532133_6_BGAA_01_00 SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2 SEAT TRACK 4 FR21 FR22 FR23 FR24



### B

**C** SEAT TRACK 6 Z130



### A

**FWD** 

## A

Figure A-GBGAA - Sheet 01 Installation of the Reinforcement at the Crossbeam FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 73 6

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# @A310 SERVICE BULLETIN

**CONF 002 FR22

FR23

(3) (3)

21 

### J **K**

**D E** 

**F G**  

## B

**C H**  20



### L **M**

B_SB_532133_6_BGAA_02_03 Figure A-GBGAA - Sheet 02 Installation of the Reinforcement at the Crossbeam FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 74 6

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# @A310 SERVICE BULLETIN

**CONF 002

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

01 01

01 (7 POS)

(7 POS)

VIEW LOOKING FWD FR22

VIEW LOOKING FWD FR22

FOR RIVET SYMBOLS, REFER TO SHEET 5 FOR DIMENSIONS, REFER TO SHEET 5 A
POSITION OF SPLIT IN EXPANSION SLEEVE DURING COLD EXPANSION 02

02 02 02 20 

## D

**E**

B_SB_532133_6_BGAA_03_05 Figure A-GBGAA - Sheet 03 Installation of the Reinforcement at the Crossbeam FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 75 6

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# @A310 SERVICE BULLETIN

**CONF 002

VIEW LOOKING AFT FR23

VIEW LOOKING AFT FR23

FOR RIVETS SYMBOLS, REFER TO SHEET 5 01 01 (6 POS)

(6 POS)

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

FOR DIMENSIONS, REFER TO SHEET 5

POSITION OF SPLIT IN EXPANSION SLEEVE DURING COLD EXPANSION 02

02 21

02 02 (3) (3)

B_SB_532133_6_BGAA_04_02 

## F

**G**

Figure A-GBGAA - Sheet 04 Installation of the Reinforcement at the Crossbeam FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 76 6

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# @A310 SERVICE BULLETIN

**CONF 002

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

EN6115K3X4 PIN ASNA2528−3 COLLAR EN6115K3X5 PIN ASNA2528−3 COLLAR 9 4 10 4

EN6115K3AX6 PIN ASNA2528−3A COLLAR 13 5 D03

D03
D03

D03

LN9198−3215CF RIVET 15 EN6115K3A6 PIN ASNA2528−3A COLLAR 14 5 D03 EN6115K3−4 PIN ASNA2528−3 COLLAR 7 4 D03

EN6115K3X6 PIN ASNA2528−3 COLLAR 4 D03 30 REMARKS STDN STARTING HOLE DIAMETER MIN. MAX. 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) 5.06 mm (0.199 in) 5.09 mm (0.20 in) 5.45 mm (0.215 in) 5.49 mm (0.216 in)

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) 4.72 mm (0.185 in) 4.76 mm (0.187 in)

D03 5.06 mm (0.199 in) 5.09 mm (0.20 in) mmDIMENSIONS (in)

C D B A 1.6 0.06 0.16
0.39 0.31 4.0 R 8.0 R 10.0

HOLES TO BE COLD EXPANDED IN ACCORDANCE WITH SRM 51−30−47 02 **NOTE:** STDN = STANDARD TOOL DIAMETER NUMBER DAN5−6−6X PIN COLLAR DAN11−6X 5.11 mm (0.201 in) 5.15 mm (0.203 in) D03 EN6115K3−3 PIN ASNA2528−3 COLLAR D03 4−4−N 4.29 mm (0.169 in) 4.34 mm (0.171 in) 4.72 mm (0.185 in) 4.76 mm (0.187 in)

EN6115K3−4 PIN ASNA2528−3 COLLAR D03 4.72 mm (0.185 in) 4.76 mm (0.187 in) 4−4−N 4.29 mm (0.169 in) 4.34 mm (0.171 in) 02

02
02

34 35 6 4

7 4 F G E 1.10
1.93 1.57 28.0 40.0 49.0 H 2.01 52.5 J K 2.89 2.34 59.4 73.5 L M 1.61 1.30 33.0 41.0

B_SB_532133_6_BGAA_05_04 Figure A-GBGAA - Sheet 05 Installation of the Reinforcement at the Crossbeam FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 77 6

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# @A310 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**

B_SB_532133_6_BGAA_06_00



## H

Figure A-GBGAA - Sheet 06 Installation of the Reinforcement at the Crossbeam FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 78 6

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

# @A310 SERVICE BULLETIN

**CONF 002

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

FOR DIMENSIONS, REFER TO SHEET 5 20 05 04

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

## J

**K** 20

B_SB_532133_6_BGAA_07_01 Figure A-GBGAA - Sheet 07 Installation of the Reinforcement at the Crossbeam FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 79 6

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

# @A310 SERVICE BULLETIN

**CONF 002

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

FOR DIMENSIONS, REFER TO SHEET 5 20 05 04

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

B L M
D D C 

## L

**M**

B_SB_532133_6_BGAA_08_00 Figure A-GBGAA - Sheet 08 Installation of the Reinforcement at the Crossbeam FR22 and FR23 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 80 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

B_SB_532133_6_BJAA_01_00 SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2 SEAT TRACK 4 

### A

**B**

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

**FWD** 

## A

Figure A-GBJAA - Sheet 01 Removal of the Existing Fasteners from the Crossbeam FR61 and FR62 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 81 6

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

# @A310 SERVICE BULLETIN

**CONF ALL



### D FR61

FR62



### E 

## C (17) 

## B

(18)

B_SB_532133_6_BJAA_02_02 

### F

Figure A-GBJAA - Sheet 02 Removal of the Existing Fasteners from the Crossbeam FR61 and FR62 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 82 6

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

# @A310 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

HOLE SYMBOL ITEM EN6069D4−05 RIVET P/N DESCRIPTION KIT REMARKS 02

25 

## D

**E**

D01

B_SB_532133_6_BJAA_03_01 EXISTING FASTENER TO BE REMOVED 02 CLOSED EXISTING HOLES. AN INSPECTION OF THESE HOLES 01 IS NOT NECESSARY Figure A-GBJAA - Sheet 03 Removal of the Existing Fasteners from the Crossbeam FR61 and FR62 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 83 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

IF PINS ARE INSTALLED, REMOVE THEM 03 03 (7 POS)

**NOTE:** FR61 

## F

**FWD**

B_SB_532133_6_BJAA_04_00 Figure A-GBJAA - Sheet 04 Removal of the Existing Fasteners from the Crossbeam FR61 and FR62 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 84 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

B_SB_532133_6_BLAA_01_00 SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2 SEAT TRACK 4 

### B

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

### A Z150

**FWD** 

## A
Figure A-GBLAA - Sheet 01 Installation of the Reinforcement at the Crossbeam FR61 and FR62 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 85 6

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

# @A310 SERVICE BULLETIN

**CONF ALL



### D FR61



### E FR62



### F **G** 

## B

17 23 22

24 

## C
B_SB_532133_6_BLAA_02_01 

### H

Figure A-GBLAA - Sheet 02 Installation of the Reinforcement at the Crossbeam FR61 and FR62 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 86 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

VIEW LOOKING FWD FR61

VIEW LOOKING FWD FR61

FOR RIVETS SYMBOLS, REFER TO SHEET 5 01 (7 POS) 01 (7 POS) 01 01



## D

HOLES TO BE INSPECTED IN ACCORDANCE WITH NTM 51−10−01 01 HOLES TO BE COLD EXPANDED IN ACCORDANCE WITH SRM 51−30−47 02 **NOTE:**
B_SB_532133_6_BLAA_03_00 22 01 01

POSITION OF SPLIT IN EXPANSION SLEEVE DURING COLD EXPANSION 02

02 02

02 

## E

Figure A-GBLAA - Sheet 03 Installation of the Reinforcement at the Crossbeam FR61 and FR62 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 87 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

VIEW LOOKING AFT FR62 01

(6 POS) (6 POS)

01

VIEW LOOKING AFT FR62 

## F

23

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

### A

**A**

27 17 24

POSITION OF SPLIT IN EXPANSION SLEEVE DURING COLD EXPANSION 02



## G 02

02

(2 POS)

B_SB_532133_6_BLAA_04_02 FOR RIVETS SYMBOLS, REFER TO SHEET 5 FOR DIMENSION, REFER TO SHEET 5 

## A **A**
Figure A-GBLAA - Sheet 04 Installation of the Reinforcement at the Crossbeam FR61 and FR62 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 88 6

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

# @A310 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 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)

B_SB_532133_6_BLAA_05_02 HOLES TO BE COLD EXPANDED IN ACCORDANCE WITH SRM 51−30−47 **NOTE:** EN6115K3X5 PIN ASNA2528−3 COLLAR 10 4

RIVET EN6081D6−09 D01

D01 EN6115K3A5 PIN ASNA2528−3A COLLAR 11 5

26 D01
ASNA2528−3A COLLAR 12 5 6−2−N 5.31mm (0.209 in) 5.38 mm (0.212 in) 5.85 mm (0.230 in) 5.89 mm (0.231 in) D01 5.06 mm (0.199 in) 5.09 mm (0.20 in) 5.45 mm (0.215 in) 5.49 mm (0.216 in) EN6115K3AX5

27 RIVET EN6096AD3−06 D01 PIN EN6115K3−3 PIN ASNA2528−3 COLLAR D01 4−4−N 4.29 mm (0.169 in) 4.34 mm (0.171 in)

STDN = STANDARD TOOL DIAMETER NUMBER 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) 34 35 36 37

02 02

02 6 4 4.72 mm (0.185 in) 4.76 mm (0.187 in)

Figure A-GBLAA - Sheet 05 Installation of the Reinforcement at the Crossbeam FR61 and FR62 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 89 6

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

# @A310 SERVICE BULLETIN

**CONF ALL

(7 POS)

FR61 **FWD**

FOR RIVET SYMBOLS, REFER TO SHEET 5 IF REQUIRED, INSTALL 2ND OVERSIZE PINS IF PINS HAVE BEEN REMOVED, INSTALL NEW PINS **NOTE:**
B_SB_532133_6_BLAA_06_00 03 04 03 04



## H

Figure A-GBLAA - Sheet 06 Installation of the Reinforcement at the Crossbeam FR61 and FR62 DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 90 6

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

# @A310 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.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 1 6

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# @A310 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.: A310-53-2133 REVISION No.: 02 - Apr 27/11 Page: 1 6

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