# A300-600 **A300-600** SERVICE BULLETIN REVISION TRANSMITTAL SHEET

**AIRBUS CUSTOMER SERVICES DIRECTORATE**  **1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE**  **Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F**  **Fax : (33) 5 61 93 42 51** M A N DA TO RY M A N DA TO RY M A N DA TO RY M A N DA TO RY **ATA SYSTEM : 57 TITLE : WINGS - COLD EXPANSION OF THE CENTER SPAR SEALING ANGLES OUTBOARD OF RIB 8**  **ADJACENT TO THE PYLON ATTACHMENT FITTING MODIFICATION No. :**  08609H5276 This page transmits Revision No. 02 of Service Bulletin No. A300-57-6033 A D D I T I O N A L WO R K No additional work is required by this revision for aircraft modified by any previous issue of this Service Bulletin. R E A S O N This revision has been issued to include the embodiment timescales that are reflected in the associated Inspection Service Bulletin A300-57-6027 at Rev 07 in the frame of the Extended Service Goal 2 (ESG2) program. C H A N G E S SUMMARY : - REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

. AD reference revised. Modification classification table added. - EFFECTIVITY

. Effectivity updated. - REFERENCES/REPERCUSSIONS

. TFU’s added. PLANNING INFORMATION : - EFFECTIVITY

. 1.A. Effectivity updated. - COMPLIANCE DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

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# A300-600 **A300-600** SERVICE BULLETIN REVISION TRANSMITTAL SHEET

- Accomplishment Timescale

. 1.E.(2) Accomplishment timescales revised and Extended Service Goal (ESG) thresholds added. - APPROVAL

. 1.F. AD reference revised. - REFERENCES

. 1.J. AD reference removed. MATERIAL INFORMATION : - INDUSTRIAL SUPPORT

. 2.B. Standard sentence revised to latest standard. ACCOMPLISHMENT INSTRUCTIONS : - GENERAL

. 3.A. CAUTION added. - MODIFICATION

. 3.B. Minor corrections. F I L I N G I N S T R U CT I O N S This Service Bulletin has been generated electronically and is reissued as a complete document. Replace the complete Service Bulletin. Put this Revision Transmittal Sheet in front of the Service Bulletin. H I S TO RY O F P R E V I O U S R E V I S I O N S Revision 01 was issued to make the accomplishment of this Service Bulletin mandatory in accordance with Airworthiness Directive (AD) (Consigne de Navigabilite) No.2003-290(B). The Change Notices OA and OB were also incorporated. R E V I S I O N S E Q U E N C E ORIGINAL : Mar 31/93 REVISION No. : 01 - Dec 18/03 REVISION No. : 02 - Sep 19/11

DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

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# A300-600 **A300-600** 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 M A N DA TO RY M A N DA TO RY M A N DA TO RY M A N DA TO RY **ATA SYSTEM : 57 TITLE : WINGS - COLD EXPANSION OF THE CENTER SPAR SEALING ANGLES OUTBOARD OF RIB 8**  **ADJACENT TO THE PYLON ATTACHMENT FITTING MODIFICATION No. :**  08609H5276 R E A S O N / D E S C R I P T I O N /O P E R A T I O N A L C O N S E Q U E N C E S During full scale fatigue tests cracks have been found in the vertical web of a center spar sealing angle, adjacent to Rib 8, at approximately 45,000 simulated flights. At 58,650 flights a crack was subsequently found in the bottom skin, adjacent to the aft pylon attachment fitting. At 72,000 flights another crack was found in a sealing angle of the opposite wing. It was established that the cracking initiated in the vertical web of the sealing angles. There is a possibility of a similar crack appearing on in-service aircraft which will lead to a rupture of the sealing angles, which may be followed by cracking of the bottom skin. The incorporation of this modification reduces the probability of cracks and subsequent difficult and extensive repairs. This Service Bulletin has been issued for the removal of nine bolts from the sealing angle vertical flange, the re-machining of the spot faces of the bolt holes, the cold expansion of the nine bolt holes in the vertical flange, the installation of oversize bolts in the vertical flange and the installation of new oversize bolts at the skin attachment positions if required. Accomplishment of this Service Bulletin has been rendered mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must be used as the reference document for the mandatory accomplishment timescale.

EVALUATION TABLE
COMPLIANCE Mandatory CANCELS INSPECTION SB No
AD Yes A/C OPERATION AFFECTED No RELIABILITY AFFECTED No PAX COMFORT AFFECTED No

DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

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# A300-600 **A300-600** SERVICE BULLETIN SUMMARY

EVALUATION TABLE
COST SAVING Yes ETOPS AFFECTED No STRUCTURAL LIFE EXTN Yes VENDOR SB INVOLVED No KIT PRICE (USD) A01 1,249

MODIFICATION CLASSIFICATION
MAJOR None MINOR 08609H5276
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. **E F**  **F E**  **C T**  **I V**  **I T** **Y** This Service Bulletin is applicable to these operators : AAL AAW ABD CES DLH F2I FDX G8E IRA IRM JAL KAC KAL LAA MON MSR OHY QTR TAR THA NOTE : The intent of this modification has been done in production on aircraft MSN 0645 and subsequent by modification 08608H5275. C O N C U R R E N T R E Q U I R E M E N T S None R E F E R E N C E S/ R E P E R C U S S I O N S TFU : 57.60.08.001, 57.60.08.002 OEB : None AOT : None SIL : None LIFE LIMIT : Extended LINE MAINTENANCE AFFECTED : No DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

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# A300-600 **A300-600** SERVICE BULLETIN SUMMARY

OTHERS : None N A T U R E O F T H E WO R K AIRCRAFT : Yes EQUIPMENT : No HARD : No SOFT : No OBRM : No M A N P OW E R

**TOTAL MANHOURS 42.0 ELAPSED TIME (HOURS) 29.0**  M A T E R I A L I N F O R M A T I O N AIRCRAFT DATA The modification of one aircraft requires one Kit 576033A01 The kit consists of nuts, bolts and washers. A P P E N D I C E S None

DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

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# A300-600 **A300-600** SERVICE BULLETIN SUMMARY

DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

REVISION No. : 02 - Sep 19/11 Page : 4 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

**AIRBUS CUSTOMER SERVICES DIRECTORATE**  **1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE**  **Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F**  **Fax : (33) 5 61 93 42 51** M A N DA TO RY M A N DA TO RY M A N DA TO RY M A N DA TO RY **ATA SYSTEM : 57 TITLE : WINGS - COLD EXPANSION OF THE CENTER SPAR SEALING ANGLES OUTBOARD OF RIB 8**  **ADJACENT TO THE PYLON ATTACHMENT FITTING MODIFICATION No. :**  08609H5276 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. P L** **A N**  **N I**  **N G**  **I N**  **F O**  **R M**  **A T**  **I O**  **N A. E**  **F F**  **E C**  **T I**  **V I**  **T Y**  (1) Models B4-601 B4-603 B4-605R B4-620 B4-622 B4-622R C4-620 (2) Aircraft (a) Effectivity by MSN This Service Bulletin is applicable to aircraft MSN : 0284 0294 0301 0307 0312 0317 0321 0336 0344 0348 0351 0354 0358 0361 0365 0368 0380 0388 0398 0401 0405 0408 0411 0414 0417 0423 0459-0466 0469 0470 0474 0477 0479 0505-0518 0521 0525 0529 0530 0532 0536 0540 0543 0546 0553-0561 0563 0566 0569 0572 0575 0577 0579 0581 0582 0584 0601-0619 0621 0623 0625-0633 0635 0637 0639 0641 0643 (b) Effectivity by Operator The Operator/MSN relationship is provided for information only and is correct at the time of issue in accordance with the information available to AIRBUS. Any future changes resulting from transfer of an aircraft from one operator to another will not be reflected in this list unless the Service Bulletin is revised for another reason.

DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

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# A300-600 **A300-600** SERVICE BULLETIN

OPERATOR MSN AAL 0423 0459 0460 0461 0463 0466 0469 0470 0474 0506 0507 0508 0509 0510 0511 0512 0513 0514 0515 0516 0517 0606 0610 0612 0615 0619 0626 0639 0643 AAW 0354 ABD 0529 0557 CES 0521 0525 0532 DLH 0380 0401 0405 0623 F2I 0284 0294 0301 0307 0312 0317 0321 0336 0348 0351 0408 0618 FDX 0358 0361 0365 0388 0417 0477 0479 0530 0536 0543 0555 0559 0572 0575 0579 0581 0611 0613 0625 0630 0633 G8E 0462 0465 IRA 0632 IRM 0411 0414 0546 0553 0608 JAL 0602 0617 0621 0637 0641 KAC 0344 KAL 0582 0609 0627 0631 LAA 0601 0616 MON 0540 0556 0604 0605 MSR 0561 0607 OHY 0584 0603 QTR 0554 0560 0614 TAR 0505 0558 0563 THA 0368 0398 0464 0518 0566 0569 0577 0628 0629 0635 (c) Effectivity by MSN and Kit/Configuration The Kits and configurations applicable to these MSNs are given at the end of this list 0284 0294 0301 0307 0312 0317 0321 0336 0344 0348 0351 0354 0358 0361 0365 0368 0380 0388 0398 0401 0405 0408 0411 0414 0417 0423 0459-0466 0469-0470 0474 0477 0479 0505-0518 0521 0525 0529-0530 0532 0536 0540 0543 0546 DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

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# A300-600 **A300-600** SERVICE BULLETIN

0553-0561 0563 0566 0569 0572 0575 0577 0579 0581-0582 0584 0601-0619 0621 0623 0625-0633 0635 0637 0639 0641 0643 KIT No. QTY PER A/C CONFIGURATION 576033A01 01 None 01 NOTE : Config. 01 is valid for all the aircraft given in the effectivity of this Service Bulletin. (3) Spares None **B. C O**  **N C**  **U R**  **R E**  **N T**  **R E**  **Q U**  **I R**  **E M**  **E N**  **T S**  None **C. R E**  **A S**  **O N**  (1) History During full scale fatigue tests cracks have been found in the vertical web of a center spar sealing angle, adjacent to Rib 8, at approximately 45,000 simulated flights. At 58,650 flights a crack was subsequently found in the bottom skin, adjacent to the aft pylon attachment fitting. At 72,000 flights another crack was found in a sealing angle of the opposite wing. It was established that the cracking initiated in the vertical web of the sealing angles. There is a possibility of a similar crack appearing on in-service aircraft which will lead to a rupture of the sealing angles, which may be followed by cracking of the bottom skin. The incorporation of this modification reduces the probability of cracks and subsequent difficult and extensive repairs. (2) Objective/Action This Service Bulletin has been issued for the removal of nine bolts from the sealing angle vertical flange, the re-machining of the spot faces, the cold expansion of the nine bolt holes in the vertical flange, the installation of oversize bolts in the vertical flange and the installation of new oversize bolts at the skin attachment positions if required. (3) Advantages The embodiment of this modification reduces the possibility of cracks and the subsequent difficult and extensive repairs. This modification also allows the inspection threshold to be extended (refer to ISB A300-57-6027). (4) Operational/Maintenance Consequences None

DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

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# A300-600 **A300-600** SERVICE BULLETIN

**D. D E**  **S C**  **R I**  **P T**  **I O**  **N** To accomplish this Service Bulletin it is necessary to (LH and RH wing): (1) Defuel and vent the fuel tanks. (2) Make sure that the applicable manhole covers are removed for access. (3) Remove any skin attachment bolts in the forward sealing angle, as necessary, to get access to the bolts in the sealing angle vertical flange. (4) Remove the nine bolts in the vertical flange of the sealing angle, outboard of Rib 8. (5) Inspect all the bolt holes, including the skin bolt holes (refer to ISB A300-57-6027). (6) Inspect the spot faces in the vertical flange for any fatigue damage and repair if necessary. (7) Rework the spot faces of three bolt holes on each side of the sealing angle vertical flange. (8) Cold expand the nine bolt holes in the vertical sealing angle. (9) Install oversize bolts in all the cold expanded bolt holes. (10) Install oversize bolts at the skin attachment positions where bolts have been removed. (11) Repair any damage to the fuel tank sealing. (12) Install the manhole covers. (13) Refuel the fuel tanks. (14) Do a fuel leak test. (15) Close up. **E. C O**  **M P**  **L I**  **A N**  **C E**  (1) Classification Mandatory (2) Accomplishment Timescale Accomplishment of this Service Bulletin has been rendered mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must be used as the reference document for the mandatory accomplishment timescale.

DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

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# A300-600 **A300-600** SERVICE BULLETIN

Embodiment time for SB A300-57-6033. Normal operation Short Range operation FC FH FC FH 9,000 18,600 10,600 15,900 NOTE : Short range operation is for aircraft with an average flight time of less than 1.5 hours. **F. A P**  **P R**  **O V**  **A L**  Approved under EASA Design Organisation Approval No. EASA 21J.031. If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, and which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin. **G. M A**  **N P**  **O W**  **E R**  The manpower estimates given in this Service Bulletin are based on the direct labour 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. Kit 576033A01 Get access 8.0 Modification 25.0 Close up 8.0 Test 1.0 **TOTAL MANHOURS 42.0 ELAPSED TIME (HOURS) 29.0**  **H. W E**  **I G**  **H T**  **A N**  **D B** **A L** **A N**  **C E**  Not changed **I. E L**  **E C**  **T R**  **I C**  **A L**  **L O** **A D**  **D A**  **T**

**A** Not applicable

DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

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# A300-600 **A300-600** SERVICE BULLETIN

**J. R E**  **F E**  **R E**  **N C**  **E S**  Aircraft Maintenance Manual (AMM) : 12-11-28 28-00-00 28-11-22 28-12-00 28-25-00 Structural Repair Manual (SRM) : 51-40-21 51-40-40 51-40-41 51-75-10 51-76-20 51-43-00 Nondestructive Test Manual (NTM) : 51-10-01, Part 6, 51-10-08, Part 6 Inspection Service Bulletin (ISB) A300-57-6027 **K. P U**  **B L**  **I C**  **A T**  **I O**  **N S**  **A F**  **F E**  **C T**  **E D**  None **L. I N**  **T E**  **R C**  **H A**  **N G**  **E A**  **B I**  **L I**  **T Y**  **/ M**  **I X** **A B**  **I L**  **I T** **Y** None

DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

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# A300-600 **A300-600** SERVICE BULLETIN

**2. M A**  **T E**  **R I**  **A L**  **I N**  **F O**  **R M**  **A T**  **I O**  **N A. M**  **A T**  **E R**  **I A**  **L -**  **P R**  **I C**  **E A**  **N D**  **A V** 

**A I**  **L A**  **B I**  **L I**  **T Y**  (1) Material Operators 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 SUPPORT CENTER P.O.Box 630262 22312 HAMBURG GERMANY (2) Price and Availability Kit 576033A01 Cost : 1,249 US dollars 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 the Kit(s) before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. NOTE : The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. **B. I N**  **D U**  **S T**  **R Y**  **S U**  **P P**  **O R** **T I**  **N F**  **O R**  **M A**  **T I**  **O N**  AIRBUS will not provide industry support for accomplishment of this Service Bulletin. **C. L I**  **S T**  **O F**  **C O**  **M P**  **O N**  **E N**  **T S**  Kit 576033A01 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 2 NSA5478BV6-20 6 Bolt 3 NSA5478BV6-21 6 Bolt 4 NSA5478BV6-22 2 Bolt 5 NSA5479BV4-18Y 2 Bolt 6 NSA5479BV6-10Y 2 Bolt 7 NSA5479BV6-14Y 12 Bolt 8 NSA5479BV6-20Y 2 Bolt 9 NSA5472-6K7 16 Nut 10 NSA5472-4K7 2 Nut 11 NSA5353-06B 32 Washer 12 NSA5353-04B 4 Washer 13 NSA5470-6K7 14 Nut 14 NSA5474-6K7 14 Nut DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

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# A300-600 **A300-600** SERVICE BULLETIN

**D. L I**  **S T**  **O F**  **M A**  **T E**  **R I**  **A L**  **S -**  **O P**  **E R**  **A T** **O R**  **S U**  **P P**  **L I**  **E D**  (1) Consumable Materials DESCRIPTION REFERENCE TO CML QTY PER A/C INST/DISP MAT No. Cleaning agent Mat. No. 11-026 As required Sealant Mat. No. 09-005 As required Cetyl Alcohol Mat. No. 06-005 As required SPS Lub-7 Mat. No. 06-004 As required * Primer Mat. No. 16-006 As required Alodine 1200 Mat. No. 13-002 As required NOTE : * Alternative to Cetyl Alcohol Mat.No.06-005. (2) Components None **E. P A**  **R T**  **S T** **O B**  **E R**  **E -**  **I D**  **E N**  **T I**  **F I**  **E D**  **B Y**  **T H**  **E O**  **P E**  **R A**  **T O**  **R** None **F. T O**  **O L**  **I N**  **G -**  **P R**  **I C**  **E A**  **N D**  **A V** 

**A I**  **L A**  **B I**  **L I**  **T Y**  No AIRBUS kit will be provided. Parts required are to be purchased from AIRBUS. The address is: AIRBUS MATERIAL SUPPORT CENTER P.O.Box 630262 22312 HAMBURG GERMANY ITEM PART NUMBER QTY DESCRIPTION STD237B/11 1 Radius Cutter STD237B/13 1 Radius Cutter STD58/62 1 Spot Face Cutter STD58/141 1 Spot Face Cutter CHS442/52 1 Arbor CHS442/53 1 Arbor NOTE : A 550 RPM pneumatic drill and chuck key will also be required (Operator supply). Supply terms for the Cold Expansion Tools listed below are to be negotiated with: FATIGUE TECHNOLOGY INC. 401 Andover Park East Seattle Washington 98188-7605 USA DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

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# A300-600 **A300-600** SERVICE BULLETIN

Cold Expansion Tools ITEM PART NUMBER QTY DESCRIPTION LB-20 1 Puller Unit FT20/200 1 Power Pack CBSD-8-1-N-1 2 Starting Drill CBSD-12-1-N-1 2 Starting Drill CBSR-12-1-N-1 2 Start Reamer CBSR-8-1-N-1 2 Start Reamer CBG-12-1-N-1 2 Combination Gage CBG-8-1-N-1 2 Combination Gage CBMG-12-1-N 2 Mandrel Gage CBMG-8-1-N 2 Mandrel Gage CBS-12-1-N-23F 16 Sleeve CBS-8-1-N-20F 2 Sleeve CBM-12-1-N-1-30-V1 2 Mandrel (Short) CBM-8-1-N-1-30-V1 2 Mandrel (Short) CBM-12-1-N-1-40-V1 2 Mandrel CBM-8-1-N-1-30-V1 2 Mandrel CBCE-42S-1201F 2 Extension Nose Cap CBCE-42S-0801F 2 Extension Nose Cap CBR-12-1-N-1-4062 2 Finsh Reamer CBR-8-1-N-1-2812 2 Finish Reamer LBOA-20 2 Offset Adapter **G. S P**  **E C**  **I A**  **L T** **O O**  **L S**  Refer to para.F.TOOLING

DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

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# A300-600 **A300-600** SERVICE BULLETIN

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DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

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# A300-600 **A300-600** SERVICE BULLETIN

**3. A C**  **C O**  **M P**  **L I**  **S H**  **M E**  **N T**  **I N**  **S T**  **R U**  **C T**  **I O**  **N S**  **A. G E**  **N E**  **R A**  **L** WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING : OBEY THE SAFETY REQUIREMENTS AND PROCEDURES FOR WORKING IN THE FUEL TANKS (REFER TO AMM 28-00-00). CAUTION : ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO THIS: - PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS NECESSARY ON WIRING AND COMPONENTS - REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER CONTAMINATION. THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION. IN CASE OF CONTAMINATION, REFER TO ESPM 20-55-00, CLEANING. (1) Preparation (a) Defuel the aircraft (Refer to AMM 28-25-00, Page block 301). (b) Vent the fuel tanks (Refer to AMM 28-12-00, Page block 301). (c) Make sure that the manhole covers in the area of Rib 8 are removed (refer to AMM 28-11-22, Page block 401). NOTE : Contact AIRBUS for applicable jacking instructions if Modifications/Repairs are to be accomplished at the same time as this Service Bulletin. The address is: AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE NOTE : Contact AIRBUS at the above address for applicable jacking instructions if any REPAIR is to be accomplished as a result of this Service Bulletin. (2) Standard Practices (a) For the removal/installation of fasteners, refer to SRM 51-40-21. (b) For cold expansion, refer to SRM 51-40-41. DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

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# A300-600 **A300-600** SERVICE BULLETIN

(c) For fastener hole and drill data, refer to SRM 51-40-40. (d) For the repair of paint coatings, refer to SRM 51-75-10. (e) For the repair of integral tank sealing, refer to SRM 51-76-20. (f) For torque values, refer to SRM 51-43-00. **B. M O**  **D I**  **F I**  **C A**  **T I**  **O N**  NOTE : The worksteps that follow are applicable to the LH and RH wing unless otherwise stated. Refer to Figure 1 thru to Figure 3 CAUTION : MAKE SURE THAT ONLY ALTERNATE BOLTS ARE REMOVED SO THAT THE ASSEMBLED PARTS CANNOT BE REMOVED. (1) Find the nine bolts, Item (1), in the vertical flange of the sealing angle, outboard of Rib 8. Remove the sealant from the bolt heads. (2) Remove the bolts, Item (1), from the bolt holes one, two, three, five, seven and nine. Discard the bolts from the bolt holes one, two and three. Retain the bolts from bolt holes five, seven and nine. NOTE : Remove any skin attachment bolts which prevent the removal of the bolts from the vertical flange. Removal of the skin attachment bolts must be kept to a minimum. Any fasteners removed from the skin will need to be increased to 2nd oversize see paragraph (22). (3) Do an inspection of the bolt holes that the bolts have been removed from and the spot face corner radii in the vertical flange for cracks. Use the eddy current technique NTM 51-10-01, Part 6, Procedure B for bolt holes and eddy current technique NTM 51-10-08, Part 6 for the spot faces. If any cracks are found report all findings to AIRBUS and repair as detailed in the Inspection Service Bulletin A300-57-6027. (4) Temporarily re-install the bolts, Item (1), in bolt holes five, seven and nine in their initial positions. (5) Remove and discard the bolts, Item (1) from the bolt holes four, six and eight. NOTE : Remove any skin attachment bolts which prevent the removal of the bolts from the vertical flange. Removal of the skin attachment bolts must be kept to a minimum. Any fasteners removed from the skin will need to be increased to 2nd oversize see paragraph (22). (6) Do the eddy current inspection as given in para 3.B.(3) at bolt holes four, six and eight. (7) Machine the spot face of bolt hole two until (refer to Figure 2): - the diameter is 0.813in. (20.65mm). - the corner radius is 0.125in. (3.18mm). DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

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# A300-600 **A300-600** SERVICE BULLETIN

- the maximum increase in depth 0.010in. (0.25mm). - the surface finish is 63 microns. (8) Machine the spot faces of holes one and three (Refer to 2) until: - the diameter is 1.000in.(25.40mm). - the corner radius is 0.125in. (3.18mm). - the maximum increase in depth 0.010in. (0.25mm). - the surface finish is 63 microns. (9) Apply protection treatment to the machined surfaces. Use Epoxide primer (Mat. No. 16-006) and Alodine 1200 (Mat. No. 13-002). (10) Drill and ream the bolt holes in the vertical flange to the cold expansion start hole dimensions shown in Table 1: Table 1 Hole Number (Refer to Figure 1) Max in. Max

mm Min. in. Min.

mm One 0.3770 9.576 0.3750 9.525 Two 0.2520 6.400 0.2500 6.350 Three thru Nine 0.3770 9.576 0.3750 9.525 (11) Do an inspection of the bolt holes for diameter and ovality. Use a combination gage of a type specified in para.F.TOOLING - PRICE AND AVAILABILITY. (12) Cold expand the bolt holes one thru nine in the vertical flange of the sealing angle. Use the tools listed in Figure 3. (13) Ream the cold expanded bolt holes to the final hole diameters shown in Table 2: Table 2 Hole Number (Refer to Figure 1) Max in. Max

mm Min. in. Min.

mm One 0.4082 10.369 0.4062 10.317 Two 0.2832 7.193 0.2812 7.142 Three thru Nine 0.4082 10.368 0.4062 10.317 (14) Deburr all the bolt holes and clean with Cleaning agent (Mat. No. 11-026).

DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

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# A300-600 **A300-600** SERVICE BULLETIN

CAUTION : MAKE SURE THAT ALL THE NUTS USED IN THE WORKSTEPS THAT FOLLOW ARE LUBRICATED. IF THE LUBRICANT IS NOT SUFFICIENT, LUBRICATE THE NUTS WITH CETYL ALCOHOL (Mat. No. 06-005) OR, AS AN ALTERNATIVE, USE SPS LUBE-7 (Mat. No. 06-004). (15) Install the bolts, Item 8, at bolt hole one with the nut, Item 9, and the washer(s), Item 11. (16) Apply Sealant (Mat. No. 09-005) to the bolt, Item 5, and install the bolt at bolt hole two with the nut, Item 10, and the washer(s), Item 12. (17) At bolt holes three, four, six and eight, install the bolt, Item 7, with the nuts, Item 9, and the washers, Item 11. (18) Torque the nuts at bolt hole one and bolt holes three thru eight to 195/230 lb.in.(2.20/2.60 mdaN). Torque the bolt at hole two to 60/70 lb.in.(0.68/0.79 mdaN). (19) Remove and discard the bolts that you temporarily installed at bolt holes five, seven and nine and do the worksteps 3.B.(12) thru (16) at the holes. (20) At the bolt holes five and seven, install the bolts, Item 7, with the nuts, Item 9, and the washer(s), Item 11. At bolt hole nine install the bolt, Item 6, with the nut, Item 9, and the washer(s), Item 11. (21) Torque the nuts at bolt holes five, seven and nine to 195/230 lb.in.(2.20/2.60 mdaN). (22) Oversize the skin attachment holes where bolts have been removed to a maximum diameter of 0.4027in.(10.228mm) and a minimum diameter of 0.4007in.(10.179mm). (23) Clean the skin attachment bolt holes with cleaning agent (Mat. No. 11-026). (24) Install oversize bolts at the skin attachment positions where bolts have been removed. Refer to Figure 2 for Item numbers. (25) Torque the nut, Item 13 to 210/230 lbf (2.36/2.60 mdaN). If Item 14 was used torque the nut to 195/230 lbf (2.20/2.60 mdaN). (26) Repair any damage to the fuel tank sealant. **C. T E**  **S T**  (1) Preparation (a) Make sure that all swarf, tools and equipment have been removed from inside the fuel tanks. (b) Install the manhole covers (refer to AMM 28-11-22, Page block 401). (2) Test (a) Refuel the wing tanks (refer to AMM 12-11-28, Page block 1) (b) Do an inspection of the modification area for fuel leaks. DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

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# A300-600 **A300-600** SERVICE BULLETIN

**D. C L**  **O S**  **E U**  **P** (1) Make sure that the work areas are clean and clear of tools and other items of equipment. **E. D O**  **C U**  **M E**  **N T**  **A**

**T I**  **O N**  Write in the applicable aircraft records that you have done all the work given in the Service Bulletin.

DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

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# A300-600 **A300-600** SERVICE BULLETIN

Figure 1, Sheet 1 Holes to be Cold Expanded

DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

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# A300-600 **A300-600** SERVICE BULLETIN

Figure 2, Sheet 1 Position of New Items

DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

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# A300-600 **A300-600** SERVICE BULLETIN

Figure 3, Sheet 1

Tooling Table DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

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# A300-600 **A300-600** SERVICE BULLETIN REPORTING SHEET

**TITLE : WINGS - COLD EXPANSION OF THE CENTER SPAR SEALING ANGLES OUTBOARD OF RIB 8 ADJACENT TO THE PYLON ATTACHMENT FITTING**  **MODIFICATION No. :** 08609H5276 P l e a s e c o m p l et e t h e a p p ro p r i at e i t e m (A o r B ) : A - SB W I L L B E embodied .................................................................. YES/NO (if NO please comment) If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of embodiement:

............................................................................................................................... ..............................................

............................................................................................................................... .............................................. B - SB H A S B E E N embodied on aircraft: ............................................................................................................

............................................................................................................................... ..............................................

............................................................................................................................... .............................................. Operator comments:..............................................................................................................

..............................

............................................................................................................................... ..............................................

............................................................................................................................... .............................................. From Airline: ...................................................................................................................

..................................... Name/Title: ....................................................................................................................

...................................... Signature:..................... Date: ..................................................... I f o p e rat i o n a l d o c u m e n t at i o n i s affe ct e d ( s e e Pa ra g ra p h 1

. K of t h i s S B ) : If information is needed prior to next normal revision or prior to SB embodiment, please indicate required service(s): Either : Advance data................................................................................... YES/NO Or : Intermediate/Temporary revision ..................................................... YES/NO I m p o r t a n t I n fo r m at i o n : 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. P l e a s e ret u r n t h i s co m p l et e d s h e et to : **AIRBUS CUSTOMER SERVICES DIRECTORATE**  **1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE**  Attn: SEDCC1 Technical Data and Documentation Services FAX: (+33) 5 61 93 28 06 e-mail: sb.reporting@airbus.com Or via your Resident Customer Support Office. Alternatively, SB lists via letters or fax are also accepted.

DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

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# A300-600 **A300-600** SERVICE BULLETIN REPORTING QUALITY

**TITLE : WINGS - COLD EXPANSION OF THE CENTER SPAR SEALING ANGLES OUTBOARD OF RIB 8 ADJACENT TO THE PYLON ATTACHMENT FITTING**  **MODIFICATION No. :** 08609H5276 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 futher 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 X Mod/Inspection X Manpower Operator Supplied X Test X References X Re-identification X Close-up X Publication X Tooling X Illustrations C o m m e n ts :

Operator : Date: Name/Title : Please return this form to: **AIRBUS CUSTOMER SERVICES DIRECTORATE**  **1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE**  Attn: SEMB Service Bulletins Management FAX: (+33) 5 61 93 42 51 Or via your Resident Customer Support Office. DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

REVISION No. : 02 - Sep 19/11 Page : 1 of 1 Printed in France © AIRBUS 2008 All rights reserved