# @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. 

# MANDATORY MANDATORY MANDATORY
ATA SYSTEM: 71 

### TITLE: POWER PLANT - GENERAL - REPLACEMENT OF CF6-80A3 SIDE LINK CLEVIS ENGINE MOUNT BOLTS **CONF ALL MODIFICATIONS None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES The side link clevis bolts of the CF6-80A3 front engine mount have a time limitation from their installation, calculated with the fatigue lives of the bolts and the yearly fleet leader data. They must be replaced by new ones at the next engine removal without exceeding 18 months from Service Bulletin issue date. Replacement by brand new bolts is then to be repeated at an interval of 29 years. This Service Bulletin details the replacement plan for all side link clevis bolts of the CF6-80A3 front engine mount before they achieve their fatigue life limitation. New bolts will have to be marked by one or several cross(es) depending on the number of replacements already done, to differentiate them from the old ones. Accomplishment of this Service Bulletin will replace the FWD engine mounts bolts (side link clevis bolts) before they reach their life limit. 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.

DATE: Apr 08/14 SERVICE BULLETIN No.: A310-71-2038 REVISION No.: 00 - Apr 08/14 Page: 1 5

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# @A310 SERVICE BULLETIN SUMMARY MATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Equipment BFEA01 1 See SB Bolt, Nut, Bushing. EFFECTIVITY This Service Bulletin is applicable to this (these) operator(s) :

FDX CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU None OEB None AOT None SIL None LINE MAINTENANCE AFFECTED No LIFE LIMIT None NATURE OF THE WORK AIRCRAFT NO EQUIPMENT YES HARD NO SOFT NO OBRM NO MANPOWER Task 712038-832-801-001: Replace the Forward Engine Mount Side Link Clevis Bolts TOTAL MANHOURS 142.00 ELAPSED TIME (HOURS) 23.00 APPENDICES Appendix 01 - Elapsed Time Assumption Appendix 02 - GE SPM Dot Peen Marking

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# @A310 SERVICE BULLETIN SUMMARY

**CONF ALL

Z464

Z454 

### A

**A B** 



## A

**B** LH SHOWN RH SYMMETRICAL TO BE REPLACED BY NEW AND CROSS MARKED

B_SB_712038_5_SAAA_01_00 Figure A-FSAAA - Sheet 01
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# @A310 SERVICE BULLETIN SUMMARY

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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



# MANDATORY MANDATORY MANDATORY
ATA SYSTEM: 71 

### TITLE: POWER PLANT - GENERAL - REPLACEMENT OF CF6-80A3 SIDE LINK CLEVIS ENGINE MOUNT BOLTS MODIFICATION No.: None 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 NOTE: This Service Bulletin is applicable only to aircraft equipped with GE CF6-80A3 engines. (1) Models 310-203 (2) Effectivity by MSN 0230 0237 0245 0248 0281 0283 0316 0356 0362 0364 0369 0394 0454 (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 FDX 0230 0237 0245 0248 0281 0283 0316 0356 0362 0364 0369 0394 0454 DATE: Apr 08/14 SERVICE BULLETIN No.: A310-71-2038 REVISION No.: 00 - Apr 08/14 Page: 1 5

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# @A310 SERVICE BULLETIN (4) Configuration by MSN MSN CONFIGURATION 0230 0237 0245 0248 0281 0283 0316 0356 0362 0364 0369 0394 0454 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 Equipment BFEA01 1 B. CONCURRENT REQUIREMENTS None C. REASON (1) History The side link clevis bolts of the CF6-80A3 front engine mount have a time limitation from their installation, calculated with the fatigue lives of the bolts and the yearly fleet leader data. They must be replaced by new ones at the next engine removal without exceeding 18 months from Service Bulletin issue date. Replacement by brand new bolts is then to be repeated at an interval of 29 years. (2) Objective/Action This Service Bulletin details the replacement plan for all side link clevis bolts of the CF6-80A3 front engine mount before they achieve their fatigue life limitation. New bolts will have to be marked by one or several cross(es) depending on the number of replacements already done, to differentiate them from the old ones. (3) Advantages Accomplishment of this Service Bulletin will replace the FWD engine mounts bolts (side link clevis bolts) before they reach their life limit. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to :

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# @A310 SERVICE BULLETIN Task 712038-832-801-001: Replace the Forward Engine Mount Side Link Clevis Bolts (1) On Bench, Replace the LH Forward Engine Mount Side Link Clevis Bolts (2) On Bench, Replace the RH Forward Engine Mount Side Link Clevis Bolts E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished. (2) Accomplishment Timescale This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA) will be issued to confirm this classification. It is anticipated that the AD will confirm the thresholds and intervals given below but reference should be made to the AD for confirmation of the mandated accomplishment timescale. Table 1, Config.001: Replace the Forward Engine Mount Side Link Clevis Bolts Condition Action Compliance Time Repetitive interval All Aircraft Do TASK 712038-832-801 001 Replace the Forward Engine Mount Side Link Clevis Bolts No later than 18 months from SB issue date None

Do one cross mark on the head of the new bolt, refer to SUBTASK 712038-832-001 002 On Bench, Replace the LH Forward Engine Mount Side Link Clevis Bolts and/or SUBTASK 712038-832-002 002 On Bench, Replace the RH Forward Engine Mount Side Link Clevis Bolts and Before Next Flight None First replacement of bolt

Repeat TASK 712038-832-801 001 Replace the Forward Engine Mount Side Link Clevis Bolts None 29 Years

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# @A310 SERVICE BULLETIN
Table 1, Config.001: Replace the Forward Engine Mount Side Link Clevis Bolts Condition Action Compliance Time Repetitive interval Do two cross marks on the head of the new bolt, refer to SUBTASK 712038-832-001 002 On Bench, Replace the LH Forward Engine Mount Side Link Clevis Bolts and/or SUBTASK 712038-832-002 002 On Bench, Replace the RH Forward Engine Mount Side Link Clevis Bolts and Before Next Flight None Second replacement of bolt

Repeat TASK 712038-832-801 001 Replace the Forward Engine Mount Side Link Clevis Bolts None 29 Years

F. APPROVAL The technical content of this document is approved under the authority of Design Organization Approval No. EASA.21J.031. If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, and which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin. G. MANPOWER The manpower estimates given in this Service Bulletin are based on the direct labor cost to do the work. These estimates assume that the work will be done by experienced personnel, and may need to be revised upwards to suit operator’s circumstances. The estimates do not include the time to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, drying times for paints, sealants, etc., and general administration work are also not included. For an explanation of the manhours and elapsed time, refer to the Gantt Chart given in Appendix 01 - Elapsed Time Assumption . Task 712038-832-801-001: Replace the Forward Engine Mount Side Link Clevis Bolts Get Access 66.00 On Bench On Bench, Replace the LH Forward Engine Mount Side Link Clevis Bolts 2.00 On Bench, Replace the RH Forward Engine Mount Side Link Clevis Bolts 2.00 Close-Up 72.00 TOTAL MANHOURS 142.00 DATE: Apr 08/14 SERVICE BULLETIN No.: A310-71-2038 REVISION No.: 00 - Apr 08/14 Page: 4 5

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# @A310 SERVICE BULLETIN
Task 712038-832-801-001: Replace the Forward Engine Mount Side Link Clevis Bolts ELAPSED TIME (HOURS) 23.00 H. WEIGHT AND BALANCE Not Changed I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES

Aircraft Maintenance Manual (AMM) 06-21-00 24-00-00 71-00-00 Elec. Std. Practices Manual (ESPM) 20-55-00 Standards Manual (SM) Structural Repair Manual (SRM) 51-40-00 51-40-20 51-40-30 K. PUBLICATION AFFECTED

Aircraft Maintenance Manual (AMM) 71-21-00 L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None

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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 Vendor parts are to be procured from GENERAL ELECTRIC: Equipment BFEA01 GENERAL ELECTRIC CO ENGINE BUSINESS GROUP 1 NEWMANN WAY PO BOX 156301 OH 45215-1915 CINCINNATI USA (2) Price and Availability No AIRBUS kit will be provided. Procurement terms for the equipment must be negotiated with the equipment supplier. B. INDUSTRY SUPPORT INFORMATION Industry Support terms for the equipment must be negotiated with the equipment supplier. C. LIST OF COMPONENTS No Kit D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials None (2) Components NOTE: To accomplish this Service Bulletin it is necessary to use the expendable parts listed in the subsequent referenced AMM task: - AMM 71-00-00, Page Block 401 (3) Equipment Equipment BFEA01 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 1 9205M84P04 4 BOLT (1) 2 9204M95P01 8 BUSHING 3 9629M48P18 4 NUT 8 J626P04 4 NUT 9 9205M84P05 4 BOLT (1) DATE: Apr 08/14 SERVICE BULLETIN No.: A310-71-2038 REVISION No.: 00 - Apr 08/14 Page: 7 5

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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. NOTE: The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE (1) : Order either the one or the other Part Number: - item 1 or item 9. E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING (1) Tooling - Price and Availability None (2) Tools NOTE: To accomplish this Service Bulletin it is necessary to use the tools listed in the subsequent referenced AMM task: - AMM 71-00-00, Page Block 401 (3) Special Tools None

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# @A310 SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS Task 712038-832-801-001 - Replace the Forward Engine Mount Side Link Clevis Bolts 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. NOTE: The accomplishment instructions of this Service Bulletin refer to procedures included in other AIRBUS documents. When the words ’refer to’ are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words ’in accordance with’ are included in the instruction, the procedure in the AIRBUS document must be used. NOTE: The access and close-up instructions, not comprising return to service tests, in this Service Bulletin do not constitute or affect the technical intent of the Service Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or close-up steps to add flexibility to their maintenance operations as long as the technical intent of the Service Bulletin is met within the set parameters. NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms. Refer to paragraph 1.J., References, for the definition of acronyms. NOTE: The purpose of flow charts is to supplement the information given in the Procedure and Compliance paragraphs and not to serve as the primary source for tasks or compliance times given in this Service Bulletin. NOTE: This Service Bulletin is mandated or expected to be mandated by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these accomplishment instructions are Required for Compliance (RC) and must be done to comply with the AD. Other paragraphs are recommended and may be deviated from, done as part of other actions or done with accepted methods different from those given in the Service Bulletin, as long as the RC paragraphs can be done and the aircraft can be put back into a serviceable condition.

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# @A310 SERVICE BULLETIN
Task Associated Data Zone 454 464 Manpower TOTAL MANHOURS 142.00 ELAPSED TIME (HOURS) 23.00 A. GENERAL (1) Subtask 712038-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 Structural Repair Manual (SRM) 51-40-00 51-40-20 51-40-30 (a) For the identification of Zones, refer to AMM 06-21-00, Page Block 001. (b) Remove and install fasteners in accordance with SRM 51-40-20. (c) Obtain alternative and substitute fastener data, in accordance with SRM 51-40-30. (d) If alternative and substitute fasteners have to be used, you must make sure that the associated nut/collar are compatible in accordance with SRM 51-40-00 "Mating Part" column. (2) Subtask 712038-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. B. PREPARATION (1) Subtask 712038-941-001-001 - Job Set-up on the LH and RH Engines Work Zones and Access Panels Zone Access/Work location 454 464 Manpower Resources Skills ENGINE

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# @A310 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 71-00-00, Page Block 401 (a) The following items shall be considered as the basic Aircraft configuration before you start a maintenance task: - Aircraft on the ground resting on landing gear (the ground safety locks and the wheel chocks are in position on the landing gear). - Engine shut down, thrust reversers closed and locked. - Aircraft in clean configuration. - Parking brake applied. - Aircraft electrical network de-energized. - Hydraulic systems depressurized. - Access to the cockpit and cabin is available. - All circuit breakers are in closed position. - All controls in NORM, AUTO or OFF position. (b) Make sure that the aircraft is electrically grounded, refer to AMM 24-00-00, Page Block 301. (c) Put access platform(s) in position at zone 454 and 464. (d) Put the warning notices in position to tell persons not to operate the flight controls. (e) Do the Job Set-up procedure as specified in the removal of the power plant on LH and RH sides, refer to AMM 71-00-00, Page Block 401. (2) Subtask 712038-010-001-001 - Remove the LH Power Plant Work Zones and Access Panels Zone Access/Work location 454 Manpower Resources Manhours 32.00 Minimum number of person 4 Subtask elapsed time 8.00 Skills ENGINE References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 (a) Remove the LH power plant, refer to AMM 71-00-00, Page Block 401. DATE: Apr 08/14 SERVICE BULLETIN No.: A310-71-2038 REVISION No.: 00 - Apr 08/14 Page: 11 5

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# @A310 SERVICE BULLETIN (3) Subtask 712038-010-002-001 - Remove the RH Power Plant Work Zones and Access Panels Zone Access/Work location 464 Manpower Resources Manhours 32.00 Minimum number of person 4 Subtask elapsed time 8.00 Skills ENGINE References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 (a) Remove the RH power plant, refer to AMM 71-00-00, Page Block 401. C. PROCEDURE (1) Subtask 712038-832-001-002 - On Bench, Replace the LH Forward Engine Mount Side Link Clevis Bolts Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills ENGINE Material necessary to do the job Equipment BFEA01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 9205M84P04 2 BOLT (1) 2 9204M95P01 4 BUSHING 3 9629M48P18 2 NUT 8 J626P04 2 NUT 9 9205M84P05 2 BOLT (1) NOTE: The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE (1) : Order either the one or the other Part Number: - item 1 or item 9. References Structural Repair Manual (SRM) 51-40-20

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# @A310 SERVICE BULLETIN

References Fig. A-FBAAA Area where Bolts are to be replaced and marked Sheet 01 Fig. A-FBBAA Replacement of Forward Engine Mount Side Link Clevis Bolts Sheet 01 Sheet 02 Fig. A-FFAAA Flow Chart Sheet 01 Fig. A-FRAAA Inspection Report Sheet 01 (a) Do the replacement of the LH Forward Engine Mount Side Link Clevis Bolts at the threshold given in the Planning Information Paragraph E.(2) : Refer to Fig. A-FBAAA

. Refer to Fig. A-FFAAA

. 1 Remove the fasteners from the Forward Engine Mount: Refer to Fig. A-FBBAA

. In accordance with SRM 51-40-20. 2 Side Link Clevis Bolt Item (1) Discard 4 Bushing Item (2) Discard 2 Nut Item (3) Discard 2 Nut Item (8) Discard 2 Bolt Item (4) Retain 2 Washer Item (5) Retain 2 Bracket Item (6) Retain 2 Bracket Item (7) Retain NOTE: PN of Side Link Clevis Bolt Item (1) include the associated washer. 2 Do a check of the removed side link clevis bolts: Refer to Appendix 02 - GE SPM Dot Peen Marking . - If there is no cross on the head of the removed bolts, then mark one cross on the head of the new bolts.
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# @A310 SERVICE BULLETIN
- If there is one cross on the head of the removed bolts, then mark two crosses on the head of the new bolts. 3 Install the new marked fasteners on the Forward Engine Mount: Refer to Fig. A-FBBAA

. Refer to Appendix 02 - GE SPM Dot Peen Marking . In accordance with SRM 51-40-20. 2 Side Link Clevis Bolts 9205M84P04 Item 1 or 2 Side Link Clevis Bolt 9205M84P05 Item 9 4 Bushing 9204M95P01 Item 2 2 Nut 9629M48P18 Item 3 2 Nut J626P04 Item 8 2 Bolt Item (4) Retained at removal 2 Washer Item (5) Retained at removal 2 Bracket Item (6) Retained at removal 2 Bracket Item (7) Retained at removal NOTE (01) : PN of Side Link Clevis Bolt Item 1 or 9 include the associated washer. NOTE (02) : Tighten the nut Item 3 to a torque value comprised between 11.42 m.daN (1010.62 lbf.in) and 12.77 m.daN (1130.09 lbf.in). NOTE (03) : Tighten the nut item 8 to a torque value comprised between 0.62 m.daN (54.87 lbf.in) and 0.79 m.daN (69.91 lbf.in). (b) Report accomplishment of this SB to AIRBUS, refer to Fig. A-FRAAA

. (c) Repeat the replacement of the LH Forward Engine Mount Side Link Clevis Bolts at the interval given in the Planning Information Paragraph E.(2).

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# @A310 SERVICE BULLETIN (2) Subtask 712038-832-002-002 - On Bench, Replace the RH Forward Engine Mount Side Link Clevis Bolts Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills ENGINE Material necessary to do the job Equipment BFEA01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 9205M84P04 2 BOLT (1) 2 9204M95P01 4 BUSHING 3 9629M48P18 2 NUT 8 J626P04 2 NUT 9 9205M84P05 2 BOLT (1) NOTE: The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE (1) : Order either the one or the other Part Number: - item 1 or item 9. References Structural Repair Manual (SRM) 51-40-20 Fig. A-FBAAA Area where Bolts are to be replaced and marked Sheet 01 Fig. A-FBBAA Replacement of Forward Engine Mount Side Link Clevis Bolts Sheet 01 Sheet 02 Fig. A-FFAAA Flow Chart Sheet 01 Fig. A-FRAAA Inspection Report Sheet 01 (a) Do the replacement of the RH Forward Engine Mount Side Link Clevis Bolts at the threshold given in the Planning Information Paragraph E.(2) : Refer to Fig. A-FBAAA

. Refer to Fig. A-FFAAA

. 1 Remove the fasteners from the Forward Engine Mount: Refer to Fig. A-FBBAA

. DATE: Apr 08/14 SERVICE BULLETIN No.: A310-71-2038 REVISION No.: 00 - Apr 08/14 Page: 15 5

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# @A310 SERVICE BULLETIN
In accordance with SRM 51-40-20. 2 Bolt Item (1) Discard 4 Bushing Item (2) Discard 2 Nut Item (3) Discard 2 Nut Item (8) Discard 2 Bolt Item (4) Retain 2 Washer Item (5) Retain 2 Bracket Item (6) Retain 2 Bracket Item (7) Retain NOTE: PN of Side Link Clevis Bolt Item (1) include the associated washer. 2 Do a check of the removed side link clevis bolts: Refer to Appendix 02 - GE SPM Dot Peen Marking . - If there is no cross on the head of the removed bolts, then mark one cross on the head of the new bolts. - If there is one cross on the head of the removed bolts, then mark two crosses on the head of the new bolts. 3 Install the new marked fasteners on the Forward Engine Mount: Refer to Fig. A-FBBAA Refer to Appendix 02 - GE SPM Dot Peen Marking . In accordance with SRM 51-40-20. 2 Side Link Clevis Bolts 9205M84P04 Item 1 or 2 Side Link Clevis Bolt 9205M84P05 Item 9 4 Bushing 9204M95P01 Item 2 2 Nut 9629M48P18 Item 3 2 Nut J626P04 Item 8

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# @A310 SERVICE BULLETIN
2 Bolt Item (4) Retained at removal 2 Washer Item (5) Retained at removal 2 Bracket Item (6) Retained at removal 2 Bracket Item (7) Retained at removal NOTE (01) : PN of Side Link Clevis Bolt Item 1 or 9 include the associated washer. NOTE (02) : Tighten the nut Item 3 to a torque value comprised between 11.42 m.daN (1010.62 lbf.in) and 12.77 m.daN (1130.09 lbf.in). NOTE (03) : Tighten the nut item 8 to a torque value comprised between 0.62 m.daN (54.87 lbf.in) and 0.79 m.daN (69.91 lbf.in). (b) Report accomplishment of this SB to AIRBUS, refer to Fig. A-FRAAA

. (c) Repeat the replacement of the RH Forward Engine Mount Side Link Clevis Bolts at the interval given in the Planning Information Paragraph E.(2). D. TEST (1) Subtask 712038-710-001-001 - Testing Work Zones and Access Panels Zone Access/Work location 454 464 Manpower Resources Skills ENGINE References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 NOTE: This Service Bulletin requires the accomplishment of the following Tests which are given in subtasks included in the topic Close-up. The manhours for the tests are included in the referenced Service Bulletin subtasks. - Remove the safety clips and tags and close the circuit breakers as specified after the installation of the power plant, refer to AMM 71-00-00, Page Block 401. - Do the test procedure as specified after the installation of the power plant, refer to AMM 71-00-00, Page Block 401. DATE: Apr 08/14 SERVICE BULLETIN No.: A310-71-2038 REVISION No.: 00 - Apr 08/14 Page: 17 5

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# @A310 SERVICE BULLETIN
E. CLOSE-UP (1) Subtask 712038-400-001-001 - Install the LH Power Plant Work Zones and Access Panels Zone Access/Work location 454 Manpower Resources Manhours 32.00 Minimum number of person 4 Subtask elapsed time 8.00 Skills ENGINE References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 (a) Install the LH power plant, refer to AMM 71-00-00, Page Block 401. (2) Subtask 712038-400-002-001 - Install the RH Power Plant Work Zones and Access Panels Zone Access/Work location 464 Manpower Resources Manhours 32.00 Minimum number of person 4 Subtask elapsed time 8.00 Skills ENGINE References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 (a) Install the RH power plant, refer to AMM 71-00-00, Page Block 401. (3) Subtask 712038-942-002-001 - Close-up for the LH and RH Engines Work Zones and Access Panels Zone Access/Work location 454 464 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401

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# @A310 SERVICE BULLETIN (a) Do the Close-up procedure as specified after the installation of the Power Plant on LH and RH sides, refer to AMM 71-00-00, Page Block 401. (b) Make sure that the work areas are clean and clear of tools and other items of equipment. (c) Remove the WARNING NOTICES. (d) Remove the access platforms. (e) Restore the systems and the aircraft to normal operating conditions.

DATE: Apr 08/14 SERVICE BULLETIN No.: A310-71-2038 REVISION No.: 00 - Apr 08/14 Page: 19 5

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# @A310 SERVICE BULLETIN

**CONF ALL

Z464

Z454 

### A

**A B** 



## A

**B** LH SHOWN RH SYMMETRICAL TO BE REPLACED BY NEW AND CROSS MARKED

B_SB_712038_5_BAAA_01_00 Figure A-FBAAA - Sheet 01 Area where Bolts are to be replaced and marked DATE: Apr 08/14 SERVICE BULLETIN No.: A310-71-2038 REVISION No.: 00 - Apr 08/14 Page: 20 5

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# @A310 SERVICE BULLETIN

**CONF ALL

Z464

Z454 

### A

**A**



## B **B**



## A **C**

LH SHOWN

RH SYMMETRICAL
B_SB_712038_5_BBAA_01_00 Figure A-FBBAA - Sheet 01 Replacement of Forward Engine Mount Side Link Clevis Bolts DATE: Apr 08/14 SERVICE BULLETIN No.: A310-71-2038 REVISION No.: 00 - Apr 08/14 Page: 21 5

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# @A310 SERVICE BULLETIN

**CONF ALL

(4) (5) (6) (7) (8)

2 (2)

3 (3) 2 (2)

MARKING EXAMPLE 

## C

x xx EXAMPLE FIRST REPLACEMENT EXAMPLE SECOND REPLACEMENT

**NOTE:** TYPICAL INSTALLATION FOR LH AND RH SIDE OF THE MOUNT 01 1 CROSS FOR THE FIRST REPLACEMENT, 2 CROSSES FOR THE SECOND AND SO ON 01

01 SIDE LINK MOUNT OR 9 1 (1) 8

TIGHTEN THE NUT ITEM 3 TO A TORQUE VALUE COMPRISED BETWEEN 11.42 m.daN (1010.62 lbf.in) 02 AND 12.77 m.daN (1130.09 lbf.in) TIGHTEN THE NUT ITEM 8 TO A TORQUE VALUE COMPRISED BETWEEN 0.62 m.daN (54.87 lbf.in) 03 AND 0.79 m.daN (69.91 lbf.in) WASHER ITEM 1 OR 9 IS A PART OF THE BOLT ASSY ITEM 1 OR 9 04 03

02 OR 9 1 (1) 04

B_SB_712038_5_BBAA_02_03 Figure A-FBBAA - Sheet 02 Replacement of Forward Engine Mount Side Link Clevis Bolts DATE: Apr 08/14 SERVICE BULLETIN No.: A310-71-2038 REVISION No.: 00 - Apr 08/14 Page: 22 5

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# @A310 SERVICE BULLETIN

**CONF ALL

**NOTE:** − DO THE REPLACEMENT OF THE FORWARD ENGINE MOUNT SIDE LINK CLEVIS BOLTS AT THE

THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2).

DO THE CROSS MARK ON THE HEAD OF THE NEW ENGINE MOUNT BOLTS: 1 CROSS (X) FOR THE FIRST REPLACEMENT 2 CROSSES (XX) FOR THE SECOND REPLACEMENT... THEN REPLACE OLD FORWARD ENGINE MOUNT SIDE LINK CLEVIS BOLTS, BUSHING AND NUT BY NEW ONES (REFER TO SUBTASK 712038−832−001−002 AND SUBTASK 712038−832−002−002)

REPORT SB ACCOMPLISHMENT TO AIRBUS

REPEAT REPLACEMENT OF THE FORWARD ENGINE MOUNT SIDE LINK CLEVIS BOLTS AT THE INTERVAL GIVEN IN PLANNING INFORMATION PARAGRAPH E.(2).

QUESTION ACTION FINDING

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN. REFER TO TASK 712038−832−801−001

REFER TO TASK 712038−832−801−001 −

B_SB_712038_5_FAAA_01_00 Figure A-FFAAA - Sheet 01 Flow Chart DATE: Apr 08/14 SERVICE BULLETIN No.: A310-71-2038 REVISION No.: 00 - Apr 08/14 Page: 23 5

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# @A310 SERVICE BULLETIN

**CONF ALL **INSPECTION REPORT** SERVICE BULLETIN No : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A310−71−2038

DATE OF INSPECTION : RETURN TO : AIRBUS CUSTOMER SERVICES ENGINEERING − SEEE6 NACELLE SYSTEMS

INSPECTION METHOD : 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE FAX +33 (0)5 61 93 36 14 DETAILED INSPECTION

FIRST REPLACEMENT OF BOLT ? SECOND REPLACEMENT OF BOLT ? YES YES NO NO

B_SB_712038_5_RAAA_01_00 Figure A-FRAAA - Sheet 01 Inspection Report DATE: Apr 08/14 SERVICE BULLETIN No.: A310-71-2038 REVISION No.: 00 - Apr 08/14 Page: 24 5

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# @A310 SERVICE BULLETIN Appendix 01 - Elapsed Time Assumption **CONF ALL (1) For an explanation of the manhours and elapsed time, refer to the following Gantt Chart.

DATE: Apr 08/14 SERVICE BULLETIN No.: A310-71-2038 REVISION No.: 00 - Apr 08/14 Page: 1 5

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# @A310 SERVICE BULLETIN Appendix 01 - Elapsed Time Assumption

**CONF ALL

**ELAPSED TIME ASSUMPTION SERVICE BULLETIN No A310−71−2038** 01 02

SB ELAPSED TIME (HOURS) GET ACCESS 66.00 9.00 8

SIDE LINK CLEVIS BOLTS (LH) REPLACEMENT OF THE FWD ENGINE MOUNT 2.00 2.00 1

SIDE LINK CLEVIS BOLTS (RH) REPLACEMENT OF THE FWD ENGINE MOUNT

CLOSE−UP 72.00 12.00 8 MH ET/S

TOTAL MANHOURS (MH) ELAPSED TIME (ET) 142.00 23.00 STEPS

5 10 15 20 25 0 PER

2.00 2.00 1

MH ET/S: PER MANHOURS ELAPSED TIME PER STEP NUMBER OF PERSONS THIS CHART IS ONLY A PROPOSAL. OPERATORS MAY DETERMINE THAT ANOTHER WAY TO DO THE WORK IS MORE SUITABLE FOR THEM 01

02 **NOTE:**

MANHOUR GIVEN IN VENDOR SERVICE BULLETINS ARE NOT REFLECTED IN THIS GANTT CHART : : B_SB_712038_5_AAAA_01_02 Figure A-FAAAA - Sheet 01 Elapsed Time Assumption DATE: Apr 08/14 SERVICE BULLETIN No.: A310-71-2038 REVISION No.: 00 - Apr 08/14 Page: 2 5

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# @A310 SERVICE BULLETIN Appendix 02 - GE SPM Dot Peen Marking **CONF ALL (1) The following document is extracted from GENERAL ELECTRIC Standard Practices Manual and explain how to cross mark the bolts in a compliant way.

DATE: Apr 08/14 SERVICE BULLETIN No.: A310-71-2038 REVISION No.: 00 - Apr 08/14 Page: 1 5

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# @A310 SERVICE BULLETIN Appendix 02 - GE SPM Dot Peen Marking

**CONF ALL

B_SB_712038_5_ABAA_01_00 Figure A-FABAA - Sheet 01 GE SPM Dot Peen Marking DATE: Apr 08/14 SERVICE BULLETIN No.: A310-71-2038 REVISION No.: 00 - Apr 08/14 Page: 2 5

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# @A310 SERVICE BULLETIN REPORTING SHEET 

### TITLE: POWER PLANT - GENERAL - REPLACEMENT OF CF6-80A3 SIDE LINK CLEVIS ENGINE MOUNT BOLTS MODIFICATION No.: None 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 08/14 SERVICE BULLETIN No.: A310-71-2038 REVISION No.: 00 - Apr 08/14 Page: 1 5

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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 4321 - Quality rating of the Accomplishment Instructions 4321 - Quality rating of the Illustrations 4321 - Is this SB easy to understand ? Y/N If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a short description of the issue. Planning Material Instructions X Effectivity X Kit content X Preparation X Reason X List of Materials Operator Supplied X Mod/Inspection X Manpower X Industry support X Test X References X Re-identification X Close-Up X Publication X Tooling X Illustrations Comments:

Operator: Date: Name/Title: Please return this form to: AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Attn : SEM4 Service Bulletins Management FAX : (33) 5 61 93 42 51 Or via your Resident Customer Support Office.

DATE: Apr 08/14 SERVICE BULLETIN No.: A310-71-2038 REVISION No.: 00 - Apr 08/14 Page: 1 5

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