@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.

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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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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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SERVICE BULLETIN

SUMMARY

This Page Intentionally Left Blank

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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

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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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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

First replacement of bolt Before Next Flight None

Repeat TASK

712038-832-801 001

Replace the Forward

Engine Mount Side Link

Clevis Bolts

None 29 Years

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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

Second replacement of Before Next Flight None

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

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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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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)

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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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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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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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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.

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(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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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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- 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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(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.

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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

DATE: Apr 08/14 SERVICE BULLETIN No.: A310-71-2038

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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

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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

DATE: Apr 08/14 SERVICE BULLETIN No.: A310-71-2038

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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

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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

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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

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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:

01 TYPICAL INSTALLATION FOR LH AND RH SIDE OF THE MOUNT

1 CROSS FOR THE FIRST REPLACEMENT, 2 CROSSES FOR THE SECOND AND SO ON

01

01

SIDE LINK

MOUNT

OR

9

1

(1)

8

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)

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)

04 WASHER ITEM 1 OR 9 IS A PART OF THE BOLT ASSY ITEM 1 OR 9

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

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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

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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

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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

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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 8 9.00

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

0 5 10 15 20 25

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

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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

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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

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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

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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

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