@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: REPLACEMENT OF CF6-80A3 FORWARD ENGINE MOUNT BOLTS

**CONF ALL

MODIFICATIONS

None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

The side, sway and thrust link 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 at the next engine removal. Replacement is then repeated at the interval of 11 years and 2

months.

This Service Bulletin details the replacement plan for all side, sway and thrust link bolts of the

CF6-80A3 front engine mount. New bolts will have to be marked by one or two or three cross(es)

depending on the number of replacement already done, to differentiate them from the old ones.

Accomplishment of this Service Bulletin will replace the FWD engine mounts bolts (side, sway and

thrust link 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 Side Link Bolt, Center Sway Link Bolt,

Thrust Link Bolt, Washer, Nut, PinCotter.

EFFECTIVITY

This Service Bulletin is applicable to this (these) operator(s) :

DAH F2I FDX IRA

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 NO

EQUIPMENT YES

HARD NO

SOFT NO

OBRM NO

MANPOWER

Task 712037-832-801-001: Replace Forward Engine Mount Bolts

TOTAL MANHOURS 139.00

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

B

TO BE REPLACED BY NEW

TO BE REPLACED BY NEW

AND CROSS MARKED

AND CROSS MARKED

A

B_SB_712037_5_SAAA_01_01

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: REPLACEMENT OF CF6-80A3 FORWARD 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 only applicable on aircraft equipped with CF6-80A3

engines.

(1) Models

310-203

(2) Effectivity by MSN

0191 0201 0230 0233 0237 0241 0245 0248 0254 0257 0264 0273 0281 0283 0291

0293 0297 0309 0316 0326 0335 0338 0353 0355-0356 0359-0360 0362 0364

0369-0370 0375 0379 0389-0390 0394 0397 0400 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

DAH 0291 0293

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SERVICE BULLETIN

OPERATOR MSN

F2I 0309

FDX 0191 0201 0230 0233 0237 0241 0245 0248 0254 0257 0264 0273

0281 0283 0297 0316 0326 0335 0353 0355 0356 0359 0360 0362

0364 0369 0394 0397 0400 0454

IRA 0338 0370 0375 0379 0389 0390

(4) Configuration by MSN

MSN CONFIGURATION

0191 0201 0230 0233 0237 0241 0245 0248 0254 0257 0264

0273 0281 0283 0291 0293 0297 0309 0316 0326 0335 0338

0353 0355 0356 0359 0360 0362 0364 0369 0370 0375 0379

0389 0390 0394 0397 0400 0454

001

(5) Configuration definition

**CONF 001

Config. 01 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

Consumable CMLA01 1

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

The side, sway and thrust link 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 at the next engine removal.

Replacement is then repeated at the interval of 11 years and 2 months.

(2) Objective/Action

This Service Bulletin details the replacement plan for all side, sway and thrust link bolts

of the CF6-80A3 front engine mount. New bolts will have to be marked by one or two or

three cross(es) depending on the number of replacement already done, to differentiate

them from the old ones.

(3) Advantages

Accomplishment of this Service Bulletin will replace the FWD engine mounts bolts (side,

sway and thrust link bolts) before they reach their life limit.

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SERVICE BULLETIN

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

Task 712037-832-801-001: Replace Forward Engine Mount Bolts

(1) Remove the LH Power Plant

(2) Do a check and Replace by new LH Engine Mount Bolts

(3) Install the LH Power Plant

(4) Remove the RH Power Plant

(5) Do a check and Replace by new RH Engine Mount Bolts

(6) Install the RH Power Plant

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

(2) Accomplishment Timescale

This Service Bulletin must be accomplished at the next engine removal without

exceeding 18 months from the issue date of this SB and must be repeated at the

interval of 11 years and 2 months.

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/or intervals and/or date) given above but reference should be made to the AD for

confirmation of the mandated accomplishment timescale.

F. APPROVAL

The technical content of this document is approved under the authority of 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.

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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 712037-832-801-001: Replace Forward Engine Mount Bolts

Get Access 2.00

On Aircraft

Remove the LH Power Plant 32.00

Install the LH Power Plant 32.00

Remove the RH Power Plant 32.00

Install the RH Power Plant 32.00

On Bench

Do a check and Replace by new LH Engine Mount

Bolts

2.00

Do a check and Replace by new RH Engine Mount

Bolts

2.00

Tests 3.00

Close-Up 2.00

TOTAL MANHOURS 139.00

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

71-21-00

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-55-00

Standards Manual (SM)

K. PUBLICATION AFFECTED

Maintenance Planning Document (MPD) 712103-G1-1

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

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M. SPARES

None

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SERVICE BULLETIN

2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

Equipment BFEA01 Vendor parts are to be procured from GE

Aircraft Engines, 1 Neumann Way, M/D

S160, Cincinnati, OH 45215 USA.

(2) Price and Availability

No AIRBUS kit will be provided.

B. INDUSTRY SUPPORT INFORMATION

Procurement 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

To accomplish this Service Bulletin it is necessary to use the expendable parts listed in

AMM tasks mentioned in AMM 71-00-00 and AMM 71-21-00.

(2) Components

None

(3) Equipment

Equipment BFEA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

1 9021M88P01 22 BOLT (1)

2 9204M98P02 26 WASHER

3 9629M48P06 22 NUT

4 9205M81P01 4 BOLT

5 9204M98P03 4 WASHER

6 9195M80P02 4 NUT (1)

7 9021M88P03 4 BOLT (1)

12 9205M82P01 4 BOLT

13 9131M74P08 4 NUT (1)

14 AN960C1016 4 WASHER

15 MS9245-65 4 PIN

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ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

16 9021M88P02 22 BOLT (1)

17 9195M80P03 4 NUT (1)

18 9021M88P04 4 BOLT (1)

19 9131M74P28 4 NUT (1)

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 (1): Order either the one or the other Part Number:

- item 1 or item 16,

- item 6 or item 17,

- item 7 or item 18,

- item 13 or item 19.

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

(1) Tooling - Price and Availability

To accomplish this Service Bulletin it is necessary to use the tools listed in the (Refer to

AMM 71-00-00).

(2) Tools

None

(3) Special Tools

None

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3. ACCOMPLISHMENT INSTRUCTIONS

Task 712037-832-801-001 - Replace Forward Engine Mount 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.

IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00.

Task Associated Data

Zone

454 464

Manpower

TOTAL MANHOURS 139.00

ELAPSED TIME (HOURS) 23.00

A. GENERAL

(1) Subtask 712037-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

(2) Subtask 712037-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001

Consumable Material List (CML)

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(a) For the specification of materials (Mat. No.) given in this Service Bulletin refer to

Consumable Materials List (CML).

(b) For the identification of Zones (Refer to AMM 06-21-00, Page Block 001) .

B. PREPARATION

(1) Subtask 712037-940-001-001 - Job Set-Up on the LH Engine

Work Zones and Access Panels

Zone Access/Work location

454

Manpower Resources

Skills ENGINE

References

Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301

71-00-00, Page Block 401

(a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page

Block 301).

(b) Put access platform(s) in position at zone 454.

(c) Put the warning notices in position to tell persons not to operate the flight controls.

(d) Do the Job Set-up of the removal of the LH power plant (Refer to AMM 71-00-00,

Page Block 401) .

(2) Subtask 712037-941-001-001 - Job Set-Up on the RH Engine

Work Zones and Access Panels

Zone Access/Work location

464

Manpower Resources

Skills ENGINE

References

Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301

71-00-00, Page Block 401

(a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page

Block 301).

(b) Put access platform(s) in position at zone 464.

(c) Put the warning notices in position to tell persons not to operate the flight controls.

(d) Do the Job Set-up of the removal of the RH power plant (Refer to AMM 71-00-00,

Page Block 401) .

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C. PROCEDURE

(1) Subtask 712037-010-001-001 - 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).

(2) Subtask 712037-832-001-001 - Do a check and Replace by new LH Engine Mount

Bolts

Work Zones and Access Panels

Zone Access/Work location

454

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 9021M88P01 11 BOLT (1)

2 9204M98P02 13 WASHER

3 9629M48P06 11 NUT

4 9205M81P01 2 BOLT

5 9204M98P03 2 WASHER

6 9195M80P02 2 NUT (1)

7 9021M88P03 2 BOLT (1)

12 9205M82P01 2 BOLT

13 9131M74P08 2 NUT (1)

14 AN960C1016 2 WASHER

15 MS9245-65 2 PIN

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ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

16 9021M88P02 11 BOLT (1)

17 9195M80P03 2 NUT (1)

18 9021M88P04 2 BOLT (1)

19 9131M74P28 2 NUT (1)

NOTE (1): Order either the one or the other Part Number:

- item 1 or item 16,

- item 6 or item 17,

- item 7 or item 18,

- item 13 or item 19.

References

Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401

71-21-00, Page Block 401

Fig. A-FBAAA

Replacement of side, center sway and

thrust links bolts

Sheet 01

Sheet 02

Sheet 03

Fig. A-FFAAA

Flow Chart

Sheet 01

Fig. A-FBBAA

Area where Bolts are to be replaced and

marked

Sheet 01

(a) Do the replacement at the accomplishment timescale given in the Planning

Information Paragraph E.(2) : Refer to Fig. A-FBBAA Sheet 01 and Fig. A-FFAAA

Sheet 01.

1 Remove the fasteners of the left side link:

Refer to Fig. A-FBAAA Sheet 02 and AMM 71-21-00, Page Block 401

3 Side Link Bolt 9021M88P01 Item (1) Discard

or

3 Side Link Bolt 9021M88P02 Item (16) Discard

4 Washer 9204M98P02 Item (2) Discard

3 Nut 9629M48P06 Item (3) Discard

1 Side Link Bolt 9205M81P01 Item (4) Discard

1 Washer 9204M98P03 Item (5) Discard

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1 Nut 9195M80P02 Item (6) Discard

or

1 Nut 9195M80P03 Item (17) Discard

1 Side Link Bolt 9021M88P03 Item (7) Discard

or

1 Side Link Bolt 9021M88P04 Item (18) Discard

2 Do a check of the removed side link bolts and:

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.

- If there are two crosses on the head of the removed bolts, then mark

three crosses on the head of the new bolts, and so on.

3 Install the new marked fasteners of the left side link:

Refer to Fig. A-FBAAA Sheet 02, AMM 71-21-00, Page Block 401 and

Appendix 02 - GE SPM Dot Peen Marking

3 Side Link Bolt 9021M88P01 Item 1

or

3 Side Link Bolt 9021M88P02 Item 16

4 Washer 9204M98P02 Item 2

3 Nut 9629M48P06 Item 3

1 Side Link Bolt 9205M81P01 Item 4

1 Washer 9204M98P03 Item 5

1 Nut 9195M80P02 Item 6

or

1 Nut 9195M80P03 Item 17

1 Side Link Bolt 9021M88P03 Item 7

or

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1 Side Link Bolt 9021M88P04 Item 18

4 Remove the fasteners of the right side link:

Refer to Fig. A-FBAAA Sheet 02 and AMM 71-21-00, Page Block 401

3 Side Link Bolt 9021M88P01 Item (1) Discard

or

3 Side Link Bolt 9021M88P02 Item (16) Discard

4 Washer 9204M98P02 Item (2) Discard

3 Nut 9629M48P06 Item (3) Discard

1 Side Link Bolt 9205M81P01 Item (4) Discard

1 Washer 9204M98P03 Item (5) Discard

1 Nut 9195M80P02 Item (6) Discard

or

1 Nut 9195M80P03 Item (17) Discard

1 Side Link Bolt 9021M88P03 Item (7) Discard

or

1 Side Link Bolt 9021M88P04 Item (18) Discard

5 Do a check of the removed side link bolts and:

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.

- If there are two crosses on the head of the removed bolts, then mark

three crosses on the head of the new bolts, and so on.

6 Install the new marked fasteners of the right side link:

Refer to Fig. A-FBAAA Sheet 02, AMM 71-21-00, Page Block 401 and

Appendix 02 - GE SPM Dot Peen Marking

3 Side Link Bolt 9021M88P01 Item 1

or

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3 Side Link Bolt 9021M88P02 Item 16

4 Washer 9204M98P02 Item 2

3 Nut 9629M48P06 Item 3

1 Side Link Bolt 9205M81P01 Item 4

1 Washer 9204M98P03 Item 5

1 Nut 9195M80P02 Item 6

or

1 Nut 9195M80P03 Item 17

1 Side Link Bolt 9021M88P03 Item 7

or

1 Side Link Bolt 9021M88P04 Item 18

7 Remove the fasteners of the center sway link:

Refer to Fig. A-FBAAA Sheet 02 and AMM 71-21-00, Page Block 401

5 Side Link Bolt 9021M88P01 Item (1) Discard

or

5 Side Link Bolt 9021M88P02 Item (16) Discard

5 Washer 9204M98P02 Item (2) Discard

5 Nut 9629M48P06 Item (3) Discard

8 Do a check of the removed center sway link bolts and:

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.

- If there are two crosses on the head of the removed bolts, then mark

three crosses on the head of the new bolts, and so on.

9 Install the new marked fasteners of the center sway link:

Refer to Fig. A-FBAAA Sheet 02, AMM 71-21-00, Page Block 401 and

Appendix 02 - GE SPM Dot Peen Marking

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5 Side Link Bolt 9021M88P01 Item 1

or

5 Side Link Bolt 9021M88P02 Item 16

5 Washer 9204M98P02 Item 2

5 Nut 9629M48P06 Item 3

10 Remove the fasteners of the thrust link:

Refer to Fig. A-FBAAA Sheet 03 and AMM 71-21-00, Page Block 401

2 Thrust Link Bolt 9205M82P01 Item (12) Discard

2 Nut 9131M74P08 Item (13) Discard

or

2 Nut 9131M74P28 Item (19) Discard

2 Washer AN960C1016 Item (14) Discard

2 Pin-Cotter MS9245-65 Item (15) Discard

11 Do a check of the removed thrust link bolts and:

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.

- If there are two crosses on the head of the removed bolts, then mark

three crosses on the head of the new bolts, and so on.

12 Install the new marked fasteners of the thrust link:

Refer to Fig. A-FBAAA Sheet 03, AMM 71-21-00, Page Block 401 and

Appendix 02 - GE SPM Dot Peen Marking

2 Thrust Link Bolt 9205M82P01 Item 12

2 Nut 9131M74P08 Item 13

or

2 Nut 9131M74P28 Item 19

2 Washer AN960C1016 Item 14

DATE: Sep 30/11 SERVICE BULLETIN No.: A310-71-2037

REVISION No.: 00 - Sep 30/11 Page: 16

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2 Pin-Cotter MS9245-65 Item 15

(b) Repeat this subtask at the interval given in the Planning Information Paragraph

E.(2).

(3) Subtask 712037-400-001-001 - Install the LH Power Plant

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).

(4) Subtask 712037-010-002-001 - 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).

(5) Subtask 712037-832-002-001 - Do a check and Replace by new RH Engine Mount

Bolts

Work Zones and Access Panels

Zone Access/Work location

464

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills ENGINE

DATE: Sep 30/11 SERVICE BULLETIN No.: A310-71-2037

REVISION No.: 00 - Sep 30/11 Page: 17

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Material necessary to do the job

Equipment BFEA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 9021M88P01 11 BOLT (1)

2 9204M98P02 13 WASHER

3 9629M48P06 11 NUT

4 9205M81P01 2 BOLT

5 9204M98P03 2 WASHER

6 9195M80P02 2 NUT (1)

7 9021M88P03 2 BOLT (1)

12 9205M82P01 2 BOLT

13 9131M74P08 2 NUT (1)

14 AN960C1016 2 WASHER

15 MS9245-65 2 PIN

16 9021M88P02 11 BOLT (1)

17 9195M80P03 2 NUT (1)

18 9021M88P04 2 BOLT (1)

19 9131M74P28 2 NUT (1)

NOTE (1): Order either the one or the other Part Number:

- item 1 or item 16,

- item 6 or item 17,

- item 7 or item 18,

- item 13 or item 19.

References

Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401

71-21-00, Page Block 401

Fig. A-FBAAA

Replacement of side, center sway and

thrust links bolts

Sheet 01

Sheet 02

Sheet 03

Fig. A-FFAAA

Flow Chart

Sheet 01

Fig. A-FBBAA

Area where Bolts are to be replaced and

marked

Sheet 01

DATE: Sep 30/11 SERVICE BULLETIN No.: A310-71-2037

REVISION No.: 00 - Sep 30/11 Page: 18

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(a) Do the replacement at the accomplishment timescale given in the Planning

Information Paragraph E.(2) : Refer to Fig. A-FBBAA Sheet 01 and Fig. A-FFAAA

Sheet 01.

1 Remove the fasteners of the left side link :

Refer to Fig. A-FBAAA Sheet 02 and AMM 71-21-00, Page Block 401

3 Side Link Bolt 9021M88P01 Item (1) Discard

or

3 Side Link Bolt 9021M88P02 Item (16) Discard

4 Washer 9204M98P02 Item (2) Discard

3 Nut 9629M48P06 Item (3) Discard

1 Side Link Bolt 9205M81P01 Item (4) Discard

1 Washer 9204M98P03 Item (5) Discard

1 Nut 9195M80P02 Item (6) Discard

or

1 Nut 9195M80P03 Item (17) Discard

1 Side Link Bolt 9021M88P03 Item (7) Discard

or

1 Side Link Bolt 9021M88P04 Item (18) Discard

2 Do a check of the removed side link bolts and:

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.

- If there are two crosses on the head of the removed bolts, then mark

three crosses on the head of the new bolts, and so on.

3 Install the new marked fasteners of the left side link:

Refer to Fig. A-FBAAA Sheet 02, AMM 71-21-00, Page Block 401 and

Appendix 02 - GE SPM Dot Peen Marking

3 Side Link Bolt 9021M88P01 Item 1

DATE: Sep 30/11 SERVICE BULLETIN No.: A310-71-2037

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or

3 Side Link Bolt 9021M88P02 Item 16

4 Washer 9204M98P02 Item 2

3 Nut 9629M48P06 Item 3

1 Side Link Bolt 9205M81P01 Item 4

1 Washer 9204M98P03 Item 5

1 Nut 9195M80P02 Item 6

or

1 Nut 9195M80P03 Item 17

1 Side Link Bolt 9021M88P03 Item 7

or

1 Side Link Bolt 9021M88P04 Item 18

4 Remove the fasteners of the right side link :

Refer to Fig. A-FBAAA Sheet 02 and AMM 71-21-00, Page Block 401

3 Side Link Bolt 9021M88P01 Item (1) Discard

or

3 Side Link Bolt 9021M88P02 Item (16) Discard

4 Washer 9204M98P02 Item (2) Discard

3 Nut 9629M48P06 Item (3) Discard

1 Side Link Bolt 9205M81P01 Item (4) Discard

1 Washer 9204M98P03 Item (5) Discard

1 Nut 9195M80P02 Item (6) Discard

or

1 Nut 9195M80P03 Item (17) Discard

1 Side Link Bolt 9021M88P03 Item (7) Discard

or

1 Side Link Bolt 9021M88P04 Item (18) Discard

DATE: Sep 30/11 SERVICE BULLETIN No.: A310-71-2037

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5 Do a check of the removed side link bolts and:

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.

- If there are two crosses on the head of the removed bolts, then mark

three crosses on the head of the new bolts, and so on.

6 Install the new marked fasteners of the right side link:

Refer to Fig. A-FBAAA Sheet 02, AMM 71-21-00, Page Block 401 and

Appendix 02 - GE SPM Dot Peen Marking

3 Side Link Bolt 9021M88P01 Item 1

or

3 Side Link Bolt 9021M88P02 Item 16

4 Washer 9204M98P02 Item 2

3 Nut 9629M48P06 Item 3

1 Side Link Bolt 9205M81P01 Item 4

1 Washer 9204M98P03 Item 5

1 Nut 9195M80P02 Item 6

or

1 Nut 9195M80P03 Item 17

1 Side Link Bolt 9021M88P03 Item 7

or

1 Side Link Bolt 9021M88P04 Item 18

7 Remove the fasteners of the center sway link:

Refer to Fig. A-FBAAA Sheet 02 and AMM 71-21-00, Page Block 401

5 Side Link Bolt 9021M88P01 Item (1) Discard

or

5 Side Link Bolt 9021M88P02 Item (16) Discard

DATE: Sep 30/11 SERVICE BULLETIN No.: A310-71-2037

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5 Washer 9204M98P02 Item (2) Discard

5 Nut 9629M48P06 Item (3) Discard

8 Do a check of the removed center sway link bolts and:

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.

- If there are two crosses on the head of the removed bolts, then mark

three crosses on the head of the new bolts, and so on.

9 Install the new marked fasteners of the center sway link:

Refer to Fig. A-FBAAA Sheet 02, AMM 71-21-00, Page Block 401 and

Appendix 02 - GE SPM Dot Peen Marking

5 Side Link Bolt 9021M88P01 Item 1

or

5 Side Link Bolt 9021M88P02 Item 16

5 Washer 9204M98P02 Item 2

5 Nut 9629M48P06 Item 3

10 Remove the fasteners of the thrust link:

Refer to Fig. A-FBAAA Sheet 03 and AMM 71-21-00, Page Block 401

2 Thrust Link Bolt 9205M82P01 Item (12) Discard

2 Nut 9131M74P08 Item (13) Discard

or

2 Nut 9131M74P28 Item (19) Discard

2 Washer AN960C1016 Item (14) Discard

2 Pin-Cotter MS9245-65 Item (15) Discard

11 Do a check of the removed thrust link bolts and:

Refer to Appendix 02 - GE SPM Dot Peen Marking

DATE: Sep 30/11 SERVICE BULLETIN No.: A310-71-2037

REVISION No.: 00 - Sep 30/11 Page: 22

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- 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.

- If there are two crosses on the head of the removed bolts, then mark

three crosses on the head of the new bolts, and so on.

12 Install the new marked fasteners of the thrust link:

Refer to Fig. A-FBAAA Sheet 03, AMM 71-21-00, Page Block 401 and

Appendix 02 - GE SPM Dot Peen Marking

2 Thrust Link Bolt 9205M82P01 Item 12

2 Nut 9131M74P08 Item 13

or

2 Nut 9131M74P28 Item 19

2 Washer AN960C1016 Item 14

2 Pin-Cotter MS9245-65 Item 15

(b) Repeat this subtask at the interval given in the Planning Information Paragraph

E.(2).

(6) Subtask 712037-400-002-001 - Install the RH Power Plant

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 power plant (Refer to AMM 71-00-00, Page Block 401).

D. TEST

(1) Subtask 712037-710-001-001 - Testing

Work Zones and Access Panels

Zone Access/Work location

454

464

DATE: Sep 30/11 SERVICE BULLETIN No.: A310-71-2037

REVISION No.: 00 - Sep 30/11 Page: 23

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SERVICE BULLETIN

Manpower Resources

Skills ENGINE

References

Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401

(a) Job Set-Up

1 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) .

(b) Procedure

1 Do the test procedure as specified after the installation of the power plant

(Refer to AMM 71-00-00, Page Block 401) .

E. CLOSE-UP

(1) Subtask 712037-942-001-001 - Close-up on the LH Engine

Work Zones and Access Panels

Zone Access/Work location

454

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401

(a) Do the Close-up procedure of the LH Power plant as per 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.

(2) Subtask 712037-942-002-001 - Close-Up on the RH Engine

Work Zones and Access Panels

Zone Access/Work location

464

Manpower Resources

Skills NON SPECIFIC

DATE: Sep 30/11 SERVICE BULLETIN No.: A310-71-2037

REVISION No.: 00 - Sep 30/11 Page: 24

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SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401

(a) Do the Close-up procedure of the RH Power plant as per AMM 71-00-00, Page

Block 401.

(b) Make sure that the work areas are clean and clear of tools and others 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: Sep 30/11 SERVICE BULLETIN No.: A310-71-2037

REVISION No.: 00 - Sep 30/11 Page: 25

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SERVICE BULLETIN

**CONF ALL

Z464

Z454

A

A

B

B

A

TO BE REPLACED BY NEW

AND CROSS MARKED

TO BE REPLACED BY NEW

AND CROSS MARKED

B_SB_712037_5_BBAA_01_02

Figure A-FBBAA - Sheet 01

Area where Bolts are to be replaced and marked

DATE: Sep 30/11 SERVICE BULLETIN No.: A310-71-2037

REVISION No.: 00 - Sep 30/11 Page: 26

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SERVICE BULLETIN

**CONF ALL

B_SB_712037_5_FAAA_01_04

DO THE REPLACEMENT OF THE FORWARD ENGINE

MOUNT BOLTS AT THE THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2).

1 CROSS (X) FOR THE FIRST REPLACEMENT

FIRST DO THE CROSS MARK ON NEW BOLTS:

2 CROSSES (X) FOR THE SECOND REPLACEMENT

ETC...

THEN REPLACE OLD FORWARD ENGINE MOUNT BOLTS BY NEW ONES

(REFER TO SUBTASK 712037−832−001−001 AND SUBTASK

712037−832−002−001)

REPEAT REPLACEMENT OF THE FORWARD ENGINE

MOUNT BOLTS AT THE INTERVAL GIVEN IN PLANNING

INFORMATION PARAGRAPH E.(2).

REMOVE THE POWER PLANT

AS PER AMM 71−00−00 PAGE BLOCK 401

QUESTION

ACTION

FINDING

Figure A-FFAAA - Sheet 01

Flow Chart

DATE: Sep 30/11 SERVICE BULLETIN No.: A310-71-2037

REVISION No.: 00 - Sep 30/11 Page: 27

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SERVICE BULLETIN

**CONF ALL

B_SB_712037_5_BAAA_01_00

Z464

Z454

A

A

C

E D

F

B

B

A

Figure A-FBAAA - Sheet 01

Replacement of side, center sway and thrust links bolts

DATE: Sep 30/11 SERVICE BULLETIN No.: A310-71-2037

REVISION No.: 00 - Sep 30/11 Page: 28

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SERVICE BULLETIN

**CONF ALL

(3)

3

(6)

6

(3)

3

(1)

1

(4)

4

(7)

7

(1)

1

(2)

2

(2)

2

(5)

5

(2)

2

(3)

3

(6)

6

(3)

3

(1)

1

(4)

4

(7)

7

(1)

1

(2)

2

(2)

2

(5)

5

(2)

2

RIGHT SIDE LINK

FLANGE

LEFT SIDE LINK

FLANGE

FAN FRAME FAN FRAME

(3)

3

(1)

1

(2)

2

FLANGE

FAN FRAME

CENTER SWAY LINK

3 CROSSES FOR THE THIRD AND SO ON

MARKING EXAMPLE

x xx

EXAMPLE FIRST REPLACEMENT EXAMPLE SECOND REPLACEMENT

C D

E

1 CROSS FOR THE FIRST REPLACEMENT, 2 CROSSES FOR THE SECOND,

NOTE:

B_SB_712037_5_BAAA_02_01

Figure A-FBAAA - Sheet 02

Replacement of side, center sway and thrust links bolts

DATE: Sep 30/11 SERVICE BULLETIN No.: A310-71-2037

REVISION No.: 00 - Sep 30/11 Page: 29

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**CONF ALL

MARKING EXAMPLE

EXAMPLE FIRST REPLACEMENT EXAMPLE SECOND REPLACEMENT

x xx

(12)

12

(14)

14

13

(13)

(15)

15

FAN

FRAME

SIDE LINK

MOUNT FAN FRAME LINK

RIGHT AND LEFT

BUSHING

F

B_SB_712037_5_BAAA_03_01

3 CROSSES FOR THE THIRD AND SO ON

1 CROSS FOR THE FIRST REPLACEMENT, 2 CROSSES FOR THE SECOND,

NOTE:

Figure A-FBAAA - Sheet 03

Replacement of side, center sway and thrust links bolts

DATE: Sep 30/11 SERVICE BULLETIN No.: A310-71-2037

REVISION No.: 00 - Sep 30/11 Page: 30

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SERVICE BULLETIN

Appendix 01 - Elapsed Time Assumption

**CONF ALL

(1) The following chart is only a proposal. Operators may determine that another way to do the work

is more suitable for them.

DATE: Sep 30/11 SERVICE BULLETIN No.: A310-71-2037

REVISION No.: 00 - Sep 30/11 Page: 1

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Appendix 01 - Elapsed Time Assumption

**CONF ALL

ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A310−71−2037

TOTAL MANHOURS

SB ELAPSED TIME

139.00

23.00

MH

ET/S:

PER

MANHOURS

ELAPSED TIME PER STEP

NUMBER OF PERSONS

01

02

THIS CHART IS ONLY A PROPOSAL.

OPERATORS MAY DETERMINE THAT ANOTHER WAY

TO DO THE WORK IS MORE SUITABLE FOR THEM.

MANHOURS GIVEN IN VENDOR SERVICE BULLETINS

ARE NOT REFLECTED IN THIS GANTT CHART.

01

02

NOTES:

:

:

SB ELAPSED TIME

(HOURS)

STEPS MH PER ET/S

0 15

GET ACCESS ON THE 1.00 1.00 1

CLOSE−UP ON THE 1.00 1.00 1

5 10

1.00 1.00 1

REPLACEMENT OF THE FWD 2.00 2.00 1

ENGINE MOUNT BOLTS (LH)

2.00 2.00 1

1.00 1.00 1

LH ENGINE

RH ENGINE

CLOSE−UP ON THE

LH ENGINE

REPLACEMENT OF THE FWD

ENGINE MOUNT BOLTS (RH)

GET ACCESS ON THE

RH ENGINE

25

TESTS 3.00 3.00 1

INSTALLATION OF LH ENGINE 32.00 4 8.00

32.00 4 8.00

REMOVAL OF LH ENGINE 32.00 4 8.00

REMOVAL OF RH ENGINE 32.00 4 8.00

20

INSTALLATION OF RH ENGINE

B_SB_712037_5_AAAA_01_04

Figure A-FAAAA - Sheet 01

Elapsed Time Assumption

DATE: Sep 30/11 SERVICE BULLETIN No.: A310-71-2037

REVISION No.: 00 - Sep 30/11 Page: 2

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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: Sep 30/11 SERVICE BULLETIN No.: A310-71-2037

REVISION No.: 00 - Sep 30/11 Page: 1

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SERVICE BULLETIN

Appendix 02 - GE SPM Dot Peen Marking

**CONF ALL

B_SB_712037_5_ABAA_01_00

Figure A-FABAA - Sheet 01

GE SPM Dot Peen Marking

DATE: Sep 30/11 SERVICE BULLETIN No.: A310-71-2037

REVISION No.: 00 - Sep 30/11 Page: 2

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REPORTING SHEET

TITLE: REPLACEMENT OF CF6-80A3 FORWARD 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: Sep 30/11 SERVICE BULLETIN No.: A310-71-2037

REVISION No.: 00 - Sep 30/11 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: Sep 30/11 SERVICE BULLETIN No.: A310-71-2037

REVISION No.: 00 - Sep 30/11 Page: 1

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