# @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



# MANDATORYMANDATORYMANDATORY
ATA SYSTEM: 57 

### TITLE: WINGS - REPLACE SLAT EXTENSION BOLT AT TRACK 6 MODIFICATION No.: 07771B9338 This page transmits Revision No.05 of Service Bulletin No.A310-57-2043 ADDITIONAL WORK **CONF ALL No additional work is required by this revision for aircraft modified by any previous issue. REASON Compliance has been changed to Mandatory. CHANGES Layout changes due to computerization of this revision are identified. For more information refer to the Table below. SUMMARY MODIFICATIONS Minor editorial or document structure change N REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES Paragraph has been amended Paragraph has been removed Reference to NTM 51-90-00 has been removed. Paragraph has been updated N

GENERAL EVALUATION Minor editorial or document structure change N MATERIAL PRICE INFORMATION Minor editorial or document structure change N EFFECTIVITY Minor editorial or document structure change N CONCURRENT REQUIREMENTS Minor editorial or document structure change N REFERENCES / REPERCUSSIONS Minor editorial or document structure change N NATURE OF THE WORK Minor editorial or document structure change N MANPOWER Minor editorial or document structure change N APPENDICES Minor editorial or document structure change N Fig. A-USAAA Minor editorial or document structure change N Fig. A-USAAA Sheet 01 Minor editorial or document structure change N DATE: Apr 15/89 SERVICE BULLETIN No.: A310-57-2043 REVISION No.: 05 - Sep 29/10 Page: 1 7

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# @A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET PLANNING INFORMATION EFFECTIVITY Minor editorial or document structure change N Configuration definition Minor editorial or document structure change N CONF 001 Minor editorial or document structure change N Minor editorial or document structure change N Material Effectivity Minor editorial or document structure change N CONCURRENT REQUIREMENTS Minor editorial or document structure change N REASON Minor editorial or document structure change N History Paragraph has been amended N Objective/Action Paragraph has been removed N Advantages Reference to NTM 51-90-00 has been removed. Paragraph has been updated N Operational/Maintenance Consequences Minor editorial or document structure change N DESCRIPTION Minor editorial or document structure change N COMPLIANCE Compliance has changed from Recommended to Mandatory N Classification Minor editorial or document structure change N Accomplishment Timescale Standard sentence has been amended to state that the Service Bulletin has been rendered Mandatory N Approval statement has been updated to the latest standard N APPROVAL Minor editorial or document structure change N Minor editorial or document structure change N MANPOWER Minor editorial or document structure change N WEIGHT AND BALANCE Minor editorial or document structure change N ELECTRICAL LOAD DATA Minor editorial or document structure change N Minor editorial or document structure change N REFERENCES Minor editorial or document structure change N Minor editorial or document structure change N PUBLICATION AFFECTED Minor editorial or document structure change N Minor editorial or document structure change N INTERCHANGEABILITY/MIXABILITY Minor editorial or document structure change N SPARES Minor editorial or document structure change N MATERIAL INFORMATION MATERIAL - PRICE AND AVAILABILITY Minor editorial or document structure change N Procurement Addresses Minor editorial or document structure change N Price and Availability Minor editorial or document structure change N INDUSTRY SUPPORT INFORMATION Industry Support Information has been added N LIST OF COMPONENTS Minor editorial or document structure change N Kit 572043B01R00 Minor editorial or document structure change N LIST OF MATERIALS - OPERATOR SUPPLIED Minor editorial or document structure change N
DATE: Apr 15/89 SERVICE BULLETIN No.: A310-57-2043 REVISION No.: 05 - Sep 29/10 Page: 2 7

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# @A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Consumable Materials Minor editorial or document structure change N Consumable CMLB01 Minor editorial or document structure change N Components Minor editorial or document structure change N Equipment Minor editorial or document structure change N PARTS TO BE RE-IDENTIFIED BY OPERATOR Minor editorial or document structure change N TOOLING Minor editorial or document structure change N ACCOMPLISHMENT INSTRUCTIONS TASK 572043- 831-895-001- MODIFICATION WARNING and CAUTION have been updated N Task associated data - 001 Minor editorial or document structure change N Subtask 572043-839-401-001 Minor editorial or document structure change N Subtask 572043-910-401-001 Standard Practices have been added N Subtask 572043-941-401-001 AMM reference has been changed from 27-80-23 to 27-80-14 N Subtask 572043-831-401-001 Note has been added N Subtask 572043-710-401-001 Minor editorial or document structure change N Subtask 572043-942-401-001 Minor editorial or document structure change N Fig. A-UBAAA Minor editorial or document structure change N Fig. A-UBAAA Sheet 01 Minor editorial or document structure change N Fig. A-UBCAA Minor editorial or document structure change N Fig. A-UBCAA Sheet 01 Minor editorial or document structure change N FILLING INSTRUCTIONS This Service Bulletin has been generated electronically and is reissued as a complete document. Replace the complete document. Put this Revision Transmittal Sheet in front of the Service Bulletin. HISTORY OF PREVIOUS REVISIONS NOTE: This is only applicable for Revision No. 05 and subsequent. If information is required for Revisions issued previous to this, please check your copies of Revision Transmittal Sheets or contact AIRBUS. REVISION SEQUENCE ORIGINAL: Apr 15/89 REVISION No. : 05 - Sep 29/10

DATE: Apr 15/89 SERVICE BULLETIN No.: A310-57-2043 REVISION No.: 05 - Sep 29/10 Page: 3 7

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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. 

# MANDATORYMANDATORYMANDATORY
ATA SYSTEM: 57 

### TITLE: WINGS - REPLACE SLAT EXTENSION BOLT AT TRACK 6 **CONF ALL MODIFICATIONS MODIFICATION CLASSIFICATION MAJOR 07771B9338 MINOR None NOTE: As per EASA IR 21, a minor change is one that has no appreciable effect on the mass, balance, structural strength, reliability, operational characteristics affecting the airworthiness of the product. All other changes are major changes. REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES The slat extension eccentric bolt A57864512208 used at track 6 is manufactured by SONACA for the A310 aircraft and by FOKKER for the A300/A300-600 aircraft. The two bolts are identical in appearance and FOKKER bolts may have been installed on some A310-200 aircraft in production. The life limit of the SONACA bolt is better than the FOKKER bolt and is equivalent to the A310 ESG life. There is a probability of fatigue cracking of the FOKKER bolt on A310 aircraft. However, due to lower loads, the life limit of the FOKKER bolt is above the aircraft operation limit for the A300B2/B4/C4/F4 and A300F4-600. The difference between the FOKKER and SONACA bolts cannot be distinguished by visual inspection. To remedy this, the SONACA bolt part number is changed to A5784307920000. This modification consists of installing a new bolt and washer at slat 2 track 6 at or before 14,000 FC or 19,000 Flight Hours (FH), whichever occurs first. If the aircraft has exceeded 14,000 flights or 19,000 FH the removed bolt must be visually inspected for cracks through out the whole length of the external surface. If cracks are found at the bolt at track 6, then the eccentric bolt at track 5 also must be replaced and AIRBUS informed. This modification is subject to airworthiness authority monitoring.

DATE: Apr 15/89 SERVICE BULLETIN No.: A310-57-2043 REVISION No.: 05 - Sep 29/10 Page: 1 7

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# @A310 SERVICE BULLETIN SUMMARY GENERAL EVALUATION EVALUATION TABLE COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO POTENTIAL AD YES A/C OPERATION AFFECTED NO RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO COST SAVING NO ETOPS AFFECTED NO STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO NOTE (1): Service Bulletin must be accomplished. MATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit572043B01R00 1 1,365.00 Bolt, Nut and Cotter Pin EFFECTIVITY This Service Bulletin is applicable to this (these) operator(s) :

BAF DAH F2I FDX IRA JAB JAV KYV This modification is embodied prior to delivery on A/C 0415 and subsequent. CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU None OEB None AOT None SIL None LINE MAINTENANCE AFFECTED No LIFE LIMIT None OTHER None NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO MANPOWER Task 572043-831-895-001: MODIFICATION TOTAL MANHOURS 6.00 DATE: Apr 15/89 SERVICE BULLETIN No.: A310-57-2043 REVISION No.: 05 - Sep 29/10 Page: 2 7

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# @A310 SERVICE BULLETIN SUMMARY Task 572043-831-895-001: MODIFICATION ELAPSED TIME (HOURS) 4.00 APPENDICES None

DATE: Apr 15/89 SERVICE BULLETIN No.: A310-57-2043 REVISION No.: 05 - Sep 29/10 Page: 3 7

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# @A310 SERVICE BULLETIN SUMMARY

**CONF ALL

SLAT NO.1

TRACK NO.4

TRACK NO.5

TRACK NO.6

TRACK NO.7 SLAT NO.2

SLAT NO.3 

## A SLAT NO.2

TRACK NO.6 WASHER

ECCENTRIC BOLT 

### A **A A** 

B_SB_572043_7_SAAA_01_00 

## A **A**

Figure A-USAAA - Sheet 01
DATE: Apr 15/89 SERVICE BULLETIN No.: A310-57-2043 REVISION No.: 05 - Sep 29/10 Page: 4 7

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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



# MANDATORYMANDATORYMANDATORY
ATA SYSTEM: 57 

### TITLE: WINGS - REPLACE SLAT EXTENSION BOLT AT TRACK 6 MODIFICATION No.: 07771B9338 This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with any information contained in it. It is delivered on the express condition that said document and the information contained in it shall be treated as confidential, shall not be used for any purpose other than that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall not be duplicated in any manner (except for the purposes of performing the tasks described hereunder and provided that any recipient of such document shall comply with the conditions herein), without AIRBUS prior written consent. 1. PLANNING INFORMATION **CONF ALL A. EFFECTIVITY (1) Models 310-203 310-221 310-222 (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 0379 0386 0389-0390 0394 0397 0400 (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 BAF 0367 0372 DAH 0291 0293 DATE: Apr 15/89 SERVICE BULLETIN No.: A310-57-2043 REVISION No.: 05 - Sep 29/10 Page: 1 7

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# @A310 SERVICE BULLETIN

OPERATOR MSN F2I 0309 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 0394 0397 0400 IRA 0338 0370 0375 0379 0389 0390 JAB 0320 JAV 0357 KYV 0386 (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 0379 0386 0389 0390 0394 0397 0400 001

(5) Configuration definition **CONF 001 Config. 001 is valid for all the aircraft given in the effectivity of this Service Bulletin as a standard configuration. (6) Material Effectivity MATERIAL QTY PER A/C SEE NOTES Consumable CMLB01 As required Kit572043B01R00 1 B. CONCURRENT REQUIREMENTS None C. REASON (1) History The slat extension eccentric bolt A57864512208 used at track 6 is manufactured by SONACA for the A310 aircraft and by FOKKER for the A300/A300-600 aircraft. The two bolts are identical in appearance and FOKKER bolts may have been installed on some A310-200 aircraft in production. The life limit of the SONACA bolt is better than the FOKKER bolt and is equivalent to the A310 ESG life. There is a probability of fatigue cracking of the FOKKER bolt on A310 aircraft. However, due to lower loads, the life limit of the FOKKER bolt is above the aircraft operation limit for the A300B2/B4/C4/F4 and A300F4-600.

DATE: Apr 15/89 SERVICE BULLETIN No.: A310-57-2043 REVISION No.: 05 - Sep 29/10 Page: 2 7

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# @A310 SERVICE BULLETIN (2) Objective/Action The difference between the FOKKER and SONACA bolts cannot be distinguished by visual inspection. To remedy this, the SONACA bolt part number is changed to A5784307920000. (3) Advantages This modification consists of installing a new bolt and washer at slat 2 track 6 at or before 14,000 FC or 19,000 Flight Hours (FH), whichever occurs first. If the aircraft has exceeded 14,000 flights or 19,000 FH the removed bolt must be visually inspected for cracks through out the whole length of the external surface. If cracks are found at the bolt at track 6, then the eccentric bolt at track 5 also must be replaced and AIRBUS informed. This modification is subject to airworthiness authority monitoring. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : Task 572043-831-895-001: MODIFICATION (1) MODIFICATION E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished. (2) Accomplishment Timescale Accomplishment of this Service Bulletin will be 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. F. APPROVAL 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.

DATE: Apr 15/89 SERVICE BULLETIN No.: A310-57-2043 REVISION No.: 05 - Sep 29/10 Page: 3 7

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# @A310 SERVICE BULLETIN
G. MANPOWER The manpower estimates given in this Service Bulletin are based on the direct labor cost to do the work. These estimates assume that the work will be done by experienced personnel, and may need to be revised upwards to suit operator’s circumstances. The estimates do not include the time to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, drying times for paints, sealants, etc., and general administration work are also not included. Task 572043-831-895-001: MODIFICATION Get Access 0.50 On Aircraft MODIFICATION 4.00 Tests 0.50 Close-Up 1.00 TOTAL MANHOURS 6.00 ELAPSED TIME (HOURS) 4.00 H. WEIGHT AND BALANCE Not Changed I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES

Aircraft Maintenance Manual (AMM) 20-21-11 24-41-00 27-80-00 27-80-12 27-80-14 29-10-00 ATA Common Support Data Dictionary (CSDD), Chapter 2 Elec. Std. Practices Manual (ESPM) 20-55-00 Standards Manual (SM) Structural Repair Manual (SRM) 51-21-10 51-40-21 51-76-10 K. PUBLICATION AFFECTED

Illustrated Parts Catalog (IPC) 57-43-11 L. INTERCHANGEABILITY/MIXABILITY DESCRIPTION OLD PART N ̊ NEW PART N ̊ INT MIXABILITY SEE NOTES Bolt-Eccentric A5786451220800 A5784307920000 01 Not Applicable Washer A5786452220000 A5784394920000 01 Not Applicable NOTE: For definitions of interchangeability codes in column INT., refer to ATA Common Support Data Dictionary (CSDD), Chapter 2.
DATE: Apr 15/89 SERVICE BULLETIN No.: A310-57-2043 REVISION No.: 05 - Sep 29/10 Page: 4 7

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# @A310 SERVICE BULLETIN
M. SPARES None

DATE: Apr 15/89 SERVICE BULLETIN No.: A310-57-2043 REVISION No.: 05 - Sep 29/10 Page: 5 7

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# @A310 SERVICE BULLETIN

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# @A310 SERVICE BULLETIN
2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses 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 : Kit572043B01R00 AIRBUS Material, Logistics and Suppliers Weg beim Jaeger 150 D-22335 Hamburg Germany For ordering by internet: http://spares.airbus.com For ordering modification kits by fax: +49 40 50 76 25 90 For ordering of single spares by fax: +49 40 50 76 40 13 (2) Price and Availability

Kit572043B01R00 Cost 1,365.00 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 not provide industry support for accomplishment of this Service Bulletin. C. LIST OF COMPONENTS Kit 572043B01R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 1 A5784307920000 1 BOLT (1) A5786451220800 01 2 A5784394920000 1 WASHER (2) A5786452220000 01 3 MS24665-374 1 PIN NOTE: For definitions of interchangeability codes in column INT., refer to ATA Common Support Data Dictionary (CSDD), Chapter 2.

DATE: Apr 15/89 SERVICE BULLETIN No.: A310-57-2043 REVISION No.: 05 - Sep 29/10 Page: 7 7

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# @A310 SERVICE BULLETIN
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. D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Synth.ester Based Grease High Pressure 04-004 As required Corrosion Inhibiting Brush Consistency 09-013 As required (2) Components None (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING None

DATE: Apr 15/89 SERVICE BULLETIN No.: A310-57-2043 REVISION No.: 05 - Sep 29/10 Page: 8 7

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# @A310 SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS Task 572043-831-895-001 - 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 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, CLEANING. Task Associated Data Manpower TOTAL MANHOURS 6.00 ELAPSED TIME (HOURS) 4.00 A. GENERAL (1) Subtask 572043-839-401-001 - ADMINISTRATIVE Manpower Resources Skills UTILITY (a) Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. (2) Subtask 572043-910-401-001 - STANDARD PRACTICES Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) 20-21-11 Structural Repair Manual (SRM) 51-21-10 51-40-21 51-76-10 (a) Tightening Torques of Standard Threaded Fasteners (Refer to AMM 20-21-11). DATE: Apr 15/89 SERVICE BULLETIN No.: A310-57-2043 REVISION No.: 05 - Sep 29/10 Page: 9 7

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# @A310 SERVICE BULLETIN (b) Protective Treatment of Metallic Structure (Refer to SRM 51-21-10). (c) Removal/Installation of Fasteners in Metallic Structure (Refer to SRM 51-40-21). (d) Repair of Sealing (Refer to SRM 51-76-10). B. PREPARATION (1) Subtask 572043-941-401-001 - JOB SET-UP Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) 24-41-00, Page Block 301 27-80-00, Page Block 301 27-80-14, Page Block 401 29-10-00, Page Block 301 (a) Fully extend the slats (Refer to AMM 27-80-00, Page Block 301). (b) Release the pressure in the Green hydraulic system (Refer to AMM 29-10-00, Page Block 301). (c) Remove electrical power from the aircraft electrical system (Refer to AMM 24-41-00, Page Block 301). (d) Open safety and tag slat circuit breakers (Refer to AMM 27-80-14, Page Block 401). C. PROCEDURE (1) Subtask 572043-831-401-001 - MODIFICATION Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 4.00 Skills AIRFRAME Material necessary to do the job Kit 572043B01R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 A5784307920000 1 BOLT 2 A5784394920000 1 WASHER 3 MS24665-374 1 PIN

DATE: Apr 15/89 SERVICE BULLETIN No.: A310-57-2043 REVISION No.: 05 - Sep 29/10 Page: 10 7

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# @A310 SERVICE BULLETIN

Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Synth.ester Based Grease High Pressure. 04-004 As required Corrosion Inhibiting Brush Consistency 09-013 As required
References Fig. A-UBAAA Removal and Installation of Eccentric Bolt Sheet 01 Fig. A-UBCAA Eccentric Bolt - Areas of Special Attention for Crack Detection Sheet 01
Use these instructions for the left and right wings. (a) Fig. A-UBAAA Sheet 01 and Fig. A-UBCAA Sheet 01 1 Remove the fairing plate and mounting bracket from track 6. 2 Retain the fairing plate and mounting bracket, nuts, bolts and washers. 3 Remove from the eccentric bolt, Item (1) the item that follows: 1 Cotter Pin Item (3) Discard 4 Remove and retain the nut from the eccentric bolt. 5 Remove and retain the lockplates, nuts and bolts that lock the head of the eccentric bolt. 6 Mark the position of the red groove (found on the head of the eccentric bolt) on to the knuckle assembly. 7 Remove the items that follow: 1 Bolt-Eccentric A5786451220800 Item (1) Discard 1 Washer A5786452220000 Item (2) Discard NOTE: The removed eccentric bolt, after examination, must be destroyed and must not be reused on the aircraft. NOTE: If the aircraft has exceeded 14,000 flights or 19,000 FH the removed bolt must be visually inspected for cracks through out the whole length of the external surface. (Refer to Fig. A-UBCAA Sheet 01 If cracks are found, then the eccentric bolt at track 5 must be DATE: Apr 15/89 SERVICE BULLETIN No.: A310-57-2043 REVISION No.: 05 - Sep 29/10 Page: 11 7

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# @A310 SERVICE BULLETIN replaced and AIRBUS informed. 8 Remove the old sealing compound from around the knuckle assembly and related parts. 9 Use Synth.ester Based Grease High Pressure. 04-004 As required

to install the 1 Bolt-Eccentric A5784307920000 Item 1 and the 1 Washer A5784394920000 Item 2 10 Align the red groove (found on the head of the eccentric bolt) with the mark made on the knuckle assembly at paragraph (a) 6. 11 Install the nut to the eccentric bolt and torque tighten to 500lb. in. (5.65 m.daN). 12 Drill a 3.4mm diameter hole through the eccentric bolt using the locking hole in the nut as an aid. 13 Install to the eccentric bolt the item that follows: 1 Pin-Cotter MS24665-374 Item 3 14 Apply Corrosion Inhibiting Brush Consistency 09-013 As required to the head of the eccentric bolt, Item 1 and the washer, Item 2. 15 Install the lockplates, bolts and nuts and apply Corrosion Inhibiting Brush Consistency. 09-013 As required

16 Install the fairing plate and mounting bracket. D. TEST (1) Subtask 572043-710-401-001 - OPERATIONAL TEST Manpower Resources Skills AIRFRAME

DATE: Apr 15/89 SERVICE BULLETIN No.: A310-57-2043 REVISION No.: 05 - Sep 29/10 Page: 12 7

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# @A310 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 27-80-12, Page Block 401 (a) Do the test after installation of slats 2 and 3 complete with tracks (Refer to AMM 27-80-12, Page Block 401). E. CLOSE-UP (1) Subtask 572043-942-401-001 - CLOSE-UP Manpower Resources Skills AIRFRAME (a) Make sure the work areas are clean and clear of tools and other items of equipment.

DATE: Apr 15/89 SERVICE BULLETIN No.: A310-57-2043 REVISION No.: 05 - Sep 29/10 Page: 13 7

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# @A310 SERVICE BULLETIN

**CONF ALL

SLAT NO.2 (REF)

SLAT NO.1

TRACK NO.4

TRACK NO.5

TRACK NO.6

TRACK NO.7 SLAT NO.2

SLAT NO.3 DRILL A 3.4MM DIAMETER HOLE THROUGH BOLT USING THE DRILLED HOLE IN THE NUT AS AN AID TORQUE TIGHTEN NUT TO 500 LB.IN. (5.64M.DAN)

APPLY SEALING COMPOUND TO ITEM 2 AFTER INSTALLATION

TRACK NO.6 (REF)

APPLY SEALING COMPOUND TO ITEM 1 AND LOCKPLATE AFTER INSTALLATION

SHOWING INSTALLATION OF ECCENTRIC BOLT AND WASHER TO TRACK NO.6

AND SLAT KNUCKLE ASSEMBLY KNUCKLE (REF) NUT

TRACK NO.6 (REF)
LINK ASSEMBLY (REF) SLAT NO.2 ATTACHMENT (REF)

SHOWING INSTALLATION OF COTTER PIN AND NUT

RED GROOVE ON HEAD OF ECCENTRIC BOLT
TRACK NO.6 (REF)

LOCKPLATE WITH ATTACHING NUTS AND BOLTS

SHOWING POSITIONING GROOVE AND INSTALLATION OF LOCKPLATE SLAT NO.2 ATTACHMENT (REF)

KNUCKLE (REF)

KNUCKLE (REF) TRACK NO.6 (REF)

FAIRING PLATE MOUNTING BRACKET
SHOWING LOCATION OF FAIRING PLATE AND MOUNTING BRACKET 

## A **A**

**A A** 

**D**



## A **A C** 

**D B** 

**C** 

## B

B_SB_572043_7_BAAA_01_01 Figure A-UBAAA - Sheet 01 Removal and Installation of Eccentric Bolt DATE: Apr 15/89 SERVICE BULLETIN No.: A310-57-2043 REVISION No.: 05 - Sep 29/10 Page: 14 7

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# @A310 SERVICE BULLETIN

**CONF ALL

20mm

IS NECESSARY DURING BOLT INSPECTION. ARROWS SHOW AREAS WHERE SPECIAL ATTENTION **NOTE:** B_SB_572043_7_BCAA_01_00 Figure A-UBCAA - Sheet 01 Eccentric Bolt - Areas of Special Attention for Crack Detection DATE: Apr 15/89 SERVICE BULLETIN No.: A310-57-2043 REVISION No.: 05 - Sep 29/10 Page: 15 7

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# @A310 SERVICE BULLETIN REPORTING SHEET 

### TITLE: WINGS - REPLACE SLAT EXTENSION BOLT AT TRACK 6 MODIFICATION No.: 07771B9338 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: Apr 15/89 SERVICE BULLETIN No.: A310-57-2043 REVISION No.: 05 - Sep 29/10 Page: 1 7

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

# @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: Apr 15/89 SERVICE BULLETIN No.: A310-57-2043 REVISION No.: 05 - Sep 29/10 Page: 1 7

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