@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: 53

TITLE: FUSELAGE - TAIL CONE - THS SUPPORT STRUTS AT FR91 -

INSPECTION FOR CRACKS

**CONF ALL

MODIFICATIONS

None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

The Trimmable Horizontal Stabilizer (THS) is supported and articulated at Frame (FR)91. Any lateral

movement is prevented by four diagonal support struts.

During routine maintenance done on several aircraft in this area, support struts have been found

cracked.

The affected area is the strut end and typical cracks are longitudinal. On some aircraft several cracks

per support strut and support strut end have been found.

This Service Bulletin gives the instruction to do a repetitive inspection of the affected area on all A310

aircraft, to prevent a support strut rupture.

After the inspection (depending on aircraft records and general visual inspection results), it is necessary

to install a clamping device which will ensure the rod body end insert is kept in place.

This installation is temporary pending the definition of a new strut which will be introduced through

another Mandatory Modification Service Bulletin.

The accomplishment of this Service Bulletin will detect potential damage at the support strut end and

limit the risk of THS lateral movement.

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

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SERVICE BULLETIN

SUMMARY

EVALUATION TABLE

COST SAVING NO ETOPS AFFECTED NO

STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO

NOTE (1): Service Bulletin must be accomplished.

MATERIAL PRICE INFORMATION

**CONF 001

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Component COMPD01 1 See SB Strut

Component COMPD02 1 See SB Cotter-pin

**CONF 002

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Component COMPD01 1 See SB Strut

Component COMPD02 1 See SB Cotter-pin

EFFECTIVITY

**CONF ALL

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

18T 19U 40T 52X 58X 82Z 85Z 98W 99Y AFG AIC BAF BBC

C9L CFC DGA FDX GAF HFY IRA IRM IYE JAV K1P KAC KZU

MGL PCA PIA QAF R1T RJA ROT RZO SBI SGX SUD THY TSC

UBD UZB WHT

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU 53.19.89.001

OEB None

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER None

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SERVICE BULLETIN

SUMMARY

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

MANPOWER

**CONF 001

Task 532137-832-848-001: Inspection

TOTAL MANHOURS 7.50

ELAPSED TIME (HOURS) 5.00

**CONF 002

Task 532137-832-848-001: Inspection

TOTAL MANHOURS 7.00

ELAPSED TIME (HOURS) 4.50

APPENDICES

**CONF ALL

Appendix 01 - Elapsed Time Assumptions

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SERVICE BULLETIN

SUMMARY

**CONF ALL

FR91

Z310

A

B

B

B

B

A

TYPICAL

B

AREA TO BE

INSPECTED

AREA TO BE

INSPECTED

B_SB_532137_6_SAAA_01_01

Figure A-GSAAA - Sheet 01

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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: 53

TITLE: FUSELAGE - TAIL CONE - THS SUPPORT STRUTS AT FR91 -

INSPECTION FOR CRACKS

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

(1) Models

310-203 310-221 310-222 310-304 310-308 310-322 310-324 310-325

(2) Effectivity by MSN

0162 0230 0237 0245 0248 0267 0278 0281 0283 0316 0331 0356-0357 0362 0364

0367 0369 0372 0378 0394 0399 0407 0410 0413 0418-0419 0421-0422 0425 0431

0434 0436-0437 0439 0441 0444-0447 0449 0452 0454 0456-0458 0467 0472-0473

0478 0480-0484 0488-0492 0494-0500 0502-0503 0519-0520 0522-0524 0526-0527

0537 0539 0545 0547 0549-0552 0562 0564-0565 0567-0568 0571 0574 0576

0585-0588 0590-0595 0597 0599-0600 0620 0622 0624 0636 0644 0646-0649

0651-0653 0656 0658 0660-0661 0663 0667 0671-0672 0674 0676 0678 0682 0687

0689 0691 0700 0702 0704 0706

(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.

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@A310

SERVICE BULLETIN

OPERATOR MSN

18T 0473

19U 0399

40T 0413

52X 0410

58X 0431

82Z 0550 0551

85Z 0527

98W 0495

99Y 0489

AFG 0496 0497

AIC 0407

BAF 0367 0372

BBC 0594 0700

C9L 0652

CFC 0425 0441 0444 0446 0482

DGA 0418 0421 0422

FDX 0162 0230 0237 0245 0248 0267 0278 0281 0283 0316 0331 0356

0362 0364 0369 0378 0394 0439 0449 0452 0454 0456 0457 0458

0467 0492 0500 0539 0549 0552 0593

GAF 0434 0484 0498 0503 0522 0523

HFY 0565

IRA 0436 0671

IRM 0488 0499 0524 0537 0547 0564 0567 0586 0595 0620

IYE 0568 0702 0704

JAV 0357 0481

K1P 0648

KAC 0647 0649 0663

KZU 0592 0622 0646

MGL 0526

PCA 0419

PIA 0585 0587 0590 0653 0656 0660 0676 0678 0682 0687 0689 0691

QAF 0667

R1T 0591

RJA 0445 0490 0491

ROT 0636 0644

RZO 0571 0624 0651 0661

SBI 0520

SGX 0519 0562

SUD 0437

THY 0478 0480 0502

TSC 0447 0472 0483 0545 0588 0597 0599 0600 0658

UBD 0672 0674

UZB 0574 0576 0706

WHT 0494

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SERVICE BULLETIN

(4) Configuration by MSN

MSN CONFIGURATION

0162 0230 0237 0245 0248 0267 0278 0281 0283 0316 0331

0356 0357 0362 0364 0367 0369 0372 0378 0394 0399 0407

0410 0413 0418 0419 0421 0422 0425 0431 0434 0436 0437

0439 0441 0444 0445 0446 0447 0449 0452 0454 0456 0457

0458 0467 0472 0473 0478 0480 0481 0482 0483 0484 0488

0489 0490 0491 0492 0494 0495 0496 0497 0498

001

0499 0500 0502 0503 0519 0520 0522 0523 0524 0526 0527

0537 0539 0545 0547 0549 0550 0551 0552 0562 0564 0565

0567 0568 0571 0574 0576 0585 0586 0587 0588 0590 0591

0592 0593 0594 0595 0597 0599 0600 0620 0622 0624 0636

0644 0646 0647 0648 0649 0651 0652 0653 0656 0658 0660

0661 0663 0667 0671 0672 0674 0676 0678 0682 0687 0689

0691 0700 0702 0704 0706

002

(5) Configuration definition

**CONF 001

Config. 001 is valid for all the aircraft on which Mod.No.06101D5165 is not embodied.

**CONF 002

Config. 002 is valid for all the aircraft on which Mod.No.06101D5165 is embodied.

(6) Material Effectivity

**CONF 001

MATERIAL QTY PER A/C SEE NOTES

Consumable CMLD01 1

Component COMPD01 1

Component COMPD02 1

**CONF 002

MATERIAL QTY PER A/C SEE NOTES

Consumable CMLD01 1

Component COMPD01 1

Component COMPD02 1

**CONF ALL

B. CONCURRENT REQUIREMENTS

None

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SERVICE BULLETIN

C. REASON

(1) History

The Trimmable Horizontal Stabilizer (THS) is supported and articulated at Frame (FR)91.

Any lateral movement is prevented by four diagonal support struts.

During routine maintenance done on several aircraft in this area, support struts have

been found cracked.

The affected area is the strut end and typical cracks are longitudinal. On some aircraft

several cracks per support strut and support strut end have been found.

(2) Objective/Action

This Service Bulletin gives the instruction to do a repetitive inspection of the affected

area on all A310 aircraft, to prevent a support strut rupture.

After the inspection (depending on aircraft records and general visual inspection results),

it is necessary to install a clamping device which will ensure the rod body end insert is

kept in place.

This installation is temporary pending the definition of a new strut which will be

introduced through another Mandatory Modification Service Bulletin.

(3) Advantages

The accomplishment of this Service Bulletin will detect potential damage at the support

strut end and limit the risk of THS lateral movement.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

**CONF 001

Task 532137-832-848-001: Inspection

(1) Identify the support struts installed

(2) Do a High Frequency Eddy Current (HFEC) inspection of the THS support strut ends

(3) Do a HFEC inspection of the strut ends after removal of the clamps

(4) Remove the clamps from the THS support struts

(5) Install the clamps on the THS support struts

(6) Replace the THS support struts

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SERVICE BULLETIN

**CONF 002

Task 532137-832-848-001: Inspection

(1) Do a HFEC inspection of the Trimmable Horizontal Stabilizer (THS) support strut

ends

(2) Do a HFEC inspection of the strut ends after removal of the clamps

(3) Remove the clamps from the THS support struts

(4) Install the clamps on the THS support struts

(5) Replace the THS support struts

**CONF ALL

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

(2) Accomplishment Timescale

**CONF 001

Table 1,Config. 001 - High Frequency Eddy Current (HFEC) inspection of the THS support strut ends

Condition Action Compliance time Repetitive interval

All aircraft pre-mod

06101

High Frequency Eddy

Current (HFEC)

inspection of the THS

support strut ends

24 months from SB

issuance date

NOTE: Do the

GVI of

the struts

within 12

months

from SB

issuance

date

24 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

intervals given above but reference should be made to the AD for confirmation of the

mandated accomplishment timescale.

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SERVICE BULLETIN

**CONF 002

Table 1, Config. 002 - High Frequency Eddy Current (HFEC) inspection of the THS support strut ends

Condition Action Compliance time Repetitive interval

From MSN 0499 to

MSN 0706

High Frequency Eddy

Current (HFEC)

inspection of the THS

support strut ends

12 months from SB

issuance date

24 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

intervals given above but reference should be made to the AD for confirmation of the

mandated accomplishment timescale.

**CONF ALL

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.

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 Assumptions .

NOTE: The minimum manhours necessary to accomplish this Service Bulletin are

those for the Inspection. Depending on the inspection result, additional

manhours can apply.

**CONF 001

Task 532137-832-848-001: Inspection

Get Access 0.50

On Aircraft

Identify the support struts installed 0.50

Do a High Frequency Eddy Current (HFEC) inspection

of the THS support strut ends

2.00

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SERVICE BULLETIN

Task 532137-832-848-001: Inspection

Do a HFEC inspection of the strut ends after removal

of the clamps

2.00

Remove the clamps from the THS support struts 0.50

Install the clamps on the THS support struts 0.50

Replace the THS support struts 1.00

Close-Up 0.50

TOTAL MANHOURS 7.50

ELAPSED TIME (HOURS) 5.00

**CONF 002

Task 532137-832-848-001: Inspection

Get Access 0.50

On Aircraft

Do a HFEC inspection of the Trimmable Horizontal

Stabilizer (THS) support strut ends

2.00

Do a HFEC inspection of the strut ends after removal

of the clamps

2.00

Remove the clamps from the THS support struts 0.50

Install the clamps on the THS support struts 0.50

Replace the THS support struts 1.00

Close-Up 0.50

TOTAL MANHOURS 7.00

ELAPSED TIME (HOURS) 4.50

**CONF ALL

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

**CONF 001

Aircraft Maintenance Manual (AMM) 06-21-00 06-31-00 06-41-00

20-21-12 24-00-00 53-10-47

55-10-11

Consumable Material List (CML)

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

Illustrated Parts Catalog (IPC) 53-19-89

Non Destructive Test Manual (NTM) 53-19-47

Service Bulletin (SB) A310-53-2136

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SERVICE BULLETIN

Standards Manual (SM)

Structural Repair Manual (SRM) 51-24-00 51-40-20

**CONF 002

Aircraft Maintenance Manual (AMM) 06-21-00 06-31-00 06-41-00

20-21-12 24-00-00 53-10-47

55-10-11

Consumable Material List (CML)

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

Illustrated Parts Catalog (IPC) 53-19-89

Non Destructive Test Manual (NTM) 53-19-47

Service Bulletin (SB) A310-53-2136

Standards Manual (SM)

Structural Repair Manual (SRM) 51-24-00 51-40-20

**CONF ALL

K. PUBLICATION AFFECTED

Impact on scheduled maintenance: Refer to MPD

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

This Service Bulletin is the subject of an AIRBUS monitored retrofit campaign.

Customers with aircraft shown in the effectivity of this Service Bulletin should send a

purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is:

Component COMPD01 AIRBUS Material, Logistics and Suppliers

IFD - In Flight Desk

Weg beim Jaeger 150

D-22335 HAMBURG

GERMANY

For ordering by internet:

http://spares.airbus.com

For ordering by fax: +49 40 50 76 4012

For ordering by E-mail:

ifd.spares@airbus.com

AIRBUS Material, Logistics and Suppliers do not stock standard hardware as competitive

multiple suppliers ensure access to minimum prices. AIRBUS recommends Customers

with aircraft shown in the effectivity of this Service Bulletin to send a purchase order to

B/E Aerospace. The address is:

Component COMPD02 B/E AEROSPACE INC.

CONSUMABLES MANAGEMENT

10000 NW 15th Terrace Miami

FL 33172

USA

Tel EMEA: +49 (0) 40 822 285 31500

Tel US: +1 305 925 2600

Tel ASIA: +1 310 900 1300

Fax EMEA: +49 (0) 40 822 285 31010

Fax US: +1 305 507 7191

Fax ASIA: +1 310 819 1200

SITA: MIAMMCR

E-Mail: AOGdesk_CMG@beaerospace.com

internet: http://www.beconsumables.com

or, alternatively any other source on the open

market.

(2) Price and Availability

No AIRBUS kit will be provided.

Operator supplied AIRBUS parts required to accomplish this Service Bulletin are to be

purchased by a spares purchase order.

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SERVICE BULLETIN

Operator supplied standard hardware parts required to accomplish this Service Bulletin

are to be supplied from the Operator’s stock.

B. INDUSTRY SUPPORT INFORMATION

AIRBUS will not provide industry support for accomplishment of this Service Bulletin.

For the organisation of this retrofit, you are kindly requested to contact AIRBUS retrofit

management department.

AIRBUS CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

France

E-mail : monitored.retrofit@airbus.com

Tel : (33) 5 67 19 06 22

Fax : (33) 5 61 93 27 45

C. LIST OF COMPONENTS

No Kit

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

NOTE: To accomplish this Service Bulletin, and in case of strut replacement, it is

necessary to use the expendable parts listed in AMM 53-10-47, Page

Block 401.

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Coating - Flexible Structure 04QAB2 As required

Polysulfide Sealant-Low Adhesion

Fillet Structure

06AEB2 As required

Non Hardening Jointing Putty-High

Temp. Area Str

06LDG2 As required

Non Aqueous Cleaner-General 08BAA9 As required

Corrosion Preventive CompoundWater Displacing12ADB1 As required

Textile-Lint Free Cotton 14SBA1 As required

(2) Components

Component COMPD01

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

NOTES

R21449H 1 ROD

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SERVICE BULLETIN

NOTE: Alternatively, it is possible to install PN R21449, PN R21449D, PN

R21449G or PN R21449H, refer to IPC 53-19-89.

NOTE: The components listed above are only required if the replacement of a

support strut is necessary. The quantity of these items are to be ordered

as required.

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Component COMPD02

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

NOTES

MS24665-374 2 PIN

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 components listed above are only required if the replacement of a

support strut is necessary. The quantity of these items are to be ordered

as required.

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

(1) Tooling - Price and Availability

None

(2) Tools

If it is required to replace a support strut to accomplish this Service Bulletin it is

necessary to use the tools listed in AMM 53-10-47, Page Block 401.

(3) Special Tools

None

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This Page Intentionally Left Blank

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SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

Task 532137-832-848-001 - Inspection

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: This Service Bulletin is classified mandatory or expected to be classified mandatory

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.

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.

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Task Associated Data

**CONF 001

Zone

310

Access

Door 313AL

Manpower

TOTAL MANHOURS 7.50

ELAPSED TIME (HOURS) 5.00

**CONF 002

Zone

310

Access

Door 313AL

Manpower

TOTAL MANHOURS 7.00

ELAPSED TIME (HOURS) 4.50

**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 532137-910-201-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

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

06-31-00, Page Block 001

06-41-00, Page Block 001

20-21-12, Page Block 001

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-24-00

51-40-20

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

the Consumable Materials List (CML).

(b) For the Frame (FR) identification , refer to AMM 06-31-00, Page Block 001.

(c) For the identification of zones, refer to AMM 06-21-00, Page Block 001.

(d) For the identification of access panels, refer to AMM 06-41-00, Page Block 001.

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(e) Torque tighten the standard threaded fasteners, refer to AMM 20-21-12, Page

Block 001.

(f) Remove and install the fasteners in accordance with SRM 51-40-20.

(g) Apply sealant in accordance with SRM 51-24-00.

(2) Subtask 532137-839-201-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

**CONF 002

(1) Subtask 532137-910-201-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

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

06-31-00, Page Block 001

06-41-00, Page Block 001

20-21-12, Page Block 001

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-24-00

51-40-20

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

the Consumable Materials List (CML).

(b) For the Frame (FR) identification , refer to AMM 06-31-00, Page Block 001.

(c) For the identification of zones, refer to AMM 06-21-00, Page Block 001.

(d) For the identification of access panels, refer to AMM 06-41-00, Page Block 001.

(e) Torque tighten the standard threaded fasteners, refer to AMM 20-21-12, Page

Block 001.

(f) Remove and install the fasteners in accordance with SRM 51-40-20.

(g) Apply sealant in accordance with SRM 51-24-00.

(2) Subtask 532137-839-201-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137

REVISION No.: 00 - Feb 14/14 Page: 15

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SERVICE BULLETIN

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

Service Bulletin.

**CONF ALL

B. PREPARATION

**CONF 001

(1) Subtask 532137-941-201-001 - Job Set-up

Work Zones and Access Panels

Zone Access/Work location

310 Access Door 313AL

Manpower Resources

Skills NON SPECIFIC

References

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

(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 the access platform(s) in position below the access door 313AL.

(d) Open the access door 313AL.

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137

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SERVICE BULLETIN

**CONF 002

(1) Subtask 532137-941-201-001 - Job Set-up

Work Zones and Access Panels

Zone Access/Work location

310 Access Door 313AL

Manpower Resources

Skills NON SPECIFIC

References

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

(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 the access platform(s) in position below the access door 313AL.

(d) Open the access door 313AL.

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SERVICE BULLETIN

**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 532137-832-201-001 - Identify the support struts installed

Work Zones and Access Panels

Zone Access/Work location

310

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

References

Fig. A-GBAAA

Inspection Area

Sheet 01

Fig. A-GFAAA

Inspection Flow Chart

Sheet 01

Sheet 02

Sheet 03

(a) Check the records of the THS support struts located at FR91 in tail cone, if struts

replacement is recorded since aircraft Entry Into Service (EIS), within 12 months

from Service Bulletin issuance date.

Refer to Fig. A-GFAAA Sheet 01.

1 If the complete records are not available since aircraft EIS:

a Do a General Visual Inspection (GVI) of the struts on aircraft within 12

months from Service Bulletin issuance date.

<1> If the installed struts are not in accordance with the one given in Fig.

A-GBAAA Sheet 01, View B.

<a> Report the inspection results to Airbus within 1 month.

<b> No further action.

<2> If the installed struts are in accordance with the one given in Fig. AGBAAA Sheet 01, View B.

<a> If clamps are installed, continue with SUBTASK

532137-280-202 001 Do a HFEC inspection of the strut ends

after removal of the clamps

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SERVICE BULLETIN

<b> If clamps are not installed, continue with SUBTASK

532137-280-201 001 Do a High Frequency Eddy Current

(HFEC) inspection of the THS support strut ends

2 If the complete records are available since aircraft EIS:

a If the struts were replaced since aircraft EIS.

<1> Do a GVI of the struts on aircraft within 12 months from Service

Bulletin issuance date.

<a> If the installed struts are not in accordance with the one given

in Fig. A-GBAAA Sheet 01, View B.

[1] Report the inspection results to Airbus within 1 month.

[2] No further action.

<b> If the installed struts are in accordance with the one given in

Fig. A-GBAAA Sheet 01, View B.

[1] If clamps are installed, continue with SUBTASK

532137-280-202 001 Do a HFEC inspection of the strut

ends after removal of the clamps .

[2] If clamps are not installed, continue with SUBTASK

532137-280-201 001 Do a High Frequency Eddy Current

(HFEC) inspection of the THS support strut ends .

b If the struts were not replaced since aircraft EIS.

<a> Report the inspection results to Airbus within 1 month.

<b> No further action.

(2) Subtask 532137-280-201-001 - Do a High Frequency Eddy Current (HFEC)

inspection of the THS support strut ends

Work Zones and Access Panels

Zone Access/Work location

310

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills NON SPECIFIC

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137

REVISION No.: 00 - Feb 14/14 Page: 19

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SERVICE BULLETIN

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9 As required

Textile-Lint Free Cotton 14SBA1 As required

References

Non Destructive Test Manual (NTM) 53-19-47 -Part 6

Service Bulletin (SB) A310-53-2136

Fig. A-GBAAA

Inspection Area

Sheet 01

Fig. A-GFAAA

Inspection Flow Chart

Sheet 01

Sheet 02

Sheet 03

(a) Clean the THS support struts with:

Non Aqueous

Cleaner-General

08BAA9 As required

and

Textile-Lint Free

Cotton

14SBA1 As required

(b) Do an HFEC inspection of each strut end located at FR91 in tail cone as given in

NTM 53-19-47 -Part 6 at Threshold given in para 1.E.(2), refer to Fig. A-GBAAA

Sheet 01, View B.

Refer to Fig. A-GFAAA Sheet 02.

1 If there is/are no crack(s) found on strut end, refer to Fig. A-GBAAA Sheet 01,

View C.

a Accomplish Service Bulletin No. A310-53-2136 before next flight.

b Report the inspection results to Airbus within 1 month.

c Do SUBTASK 532137-280-202 001 Do a HFEC inspection of the strut

ends after removal of the clamps every 24 months.

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SERVICE BULLETIN

2 If there is/are crack(s) found on at least one strut end, refer to Fig. A-GBAAA

Sheet 01, View C.

a If the individual maximum crack length is more than 15.0 mm (0.591 in),

or more than 4 cracks per strut end are equal or less than 15.0 mm

(0.591 in).

<1> Replace the damaged strut by a new one before next flight, refer to

SUBTASK 532137-831-201 001 Replace the THS support struts .

<2> Accomplish Service Bulletin No. A310-53-2136 before next flight.

<3> Report the inspection results to Airbus within 10 days.

<4> Do SUBTASK 532137-280-202 001 Do a HFEC inspection of the

strut ends after removal of the clamps every 24 months.

b If the individual maximum crack length is equal or less than 15.0 mm

(0.591 in), or not more than 4 cracks per strut end are equal or less than

15.0 mm (0.591 in).

<1> Accomplish Service Bulletin No. A310-53-2136 before next flight.

<2> Report the inspection results to Airbus within 10 days.

<3> Do SUBTASK 532137-280-202 001 Do a HFEC inspection of the

strut ends after removal of the clamps every 24 months.

(3) Subtask 532137-280-202-001 - Do a HFEC inspection of the strut ends after

removal of the clamps

Work Zones and Access Panels

Zone Access/Work location

310

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills NON SPECIFIC

References

Non Destructive Test Manual (NTM) 53-19-47 , Part 6

Fig. A-GBAAA

Inspection Area

Sheet 01

Fig. A-GFAAA

Inspection Flow Chart

Sheet 01

Sheet 02

Sheet 03

(a) Remove clamp from each support strut end at interval given in para 1.E.(2) and

refer to SUBTASK 532137-020-201 001 Remove the clamps from the THS support

struts .

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137

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SERVICE BULLETIN

(b) Do an HFEC inspection of each strut end where clamps were installed before next

flight as per NTM 53-19-47 , Part 6, refer to Fig. A-GBAAA Sheet 01, View B and

Fig. A-GFAAA Sheet 03.

1 If no crack(s) found on strut ends, refer to Fig. A-GBAAA Sheet 01, View C.

a Install clamp on each strut end before next flight, refer to SUBTASK

532137-420-201 001 Install the clamps on the THS support struts .

b Report the inspection results to Airbus within 1 month.

c Do the work steps C.(3)(a) to C.(3)(b) again every 24 months.

2 If crack(s) found on at least one strut end, refer to Fig. A-GBAAA Sheet 01,

View C.

a If the individual maximum crack length is more than 15.0 mm (0.591 in),

or more than 4 cracks per strut end are equal or less than 15.0 mm

(0.591 in).

<1> Replace the damaged strut by a new one before next flight, refer to

SUBTASK 532137-831-201 001 Replace the THS support struts .

<2> Install clamp on each strut end before next flight, refer to SUBTASK

532137-420-201 001 Install the clamps on the THS support struts .

<3> Report the inspection results to Airbus within 10 days.

<4> Do the work steps C.(3)(a) to C.(3)(b) again every 24 months.

b If the individual maximum crack length is equal or less than 15.0 mm

(0.591 in), or not more than 4 cracks per strut end are equal or less than

15.0 mm (0.591 in).

<1> Install clamp on each strut end before next flight, refer to SUBTASK

532137-420-201 001 Install the clamps on the THS support struts .

<2> Report the inspection results to Airbus within 10 days.

<3> Do the work steps C.(3)(a) to C.(3)(b) again every 24 months.

(4) Subtask 532137-020-201-001 - Remove the clamps from the THS support struts

Work Zones and Access Panels

Zone Access/Work location

310

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137

REVISION No.: 00 - Feb 14/14 Page: 22

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SERVICE BULLETIN

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9 As required

Textile-Lint Free Cotton 14SBA1 As required

References

Fig. A-GBBAA

Removal/Installation of the Clamps

Sheet 01

(a) From each support strut, remove:

Refer to Fig. A-GBBAA Sheet 01, Views A to D.

2 Nut NAS1726-5E Item (4) Retain

2 Washer NAS1149D0563K Item (3) Retain

2 Bolt NSA5031-5-38 Item (2) Retain

2 Clamp A5347310320000 Item (1) Retain

(b) Remove the remaining sealant from the support struts and clean them with:

Refer to Fig. A-GBBAA Sheet 01, Views A to D.

Non Aqueous

Cleaner-General

08BAA9 As required

Textile-Lint Free

Cotton

14SBA1 As required

(5) Subtask 532137-420-201-001 - Install the clamps on the THS support struts

Work Zones and Access Panels

Zone Access/Work location

310

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137

REVISION No.: 00 - Feb 14/14 Page: 23

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@A310

SERVICE BULLETIN

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Coating - Flexible Structure 04QAB2

Polysulfide Sealant-Low

Adhesion Fillet Structure

06AEB2 As required

Non Hardening Jointing

Putty-High Temp. Area Str

06LDG2 As required

Corrosion Preventive

Compound-Water

Displacing

12ADB1 As required

References

Fig. A-GBBAA

Removal/Installation of the Clamps

Sheet 01

(a) To the interface surfaces of the clamps, Item (1), apply:

Refer to Fig. A-GBBAA Sheet 01, Views A to D.

Polysulfide SealantLow Adhesion Fillet

Structure

06AEB2 As required

NOTE: Application of the sealant is required at the interfaces between the

two clamp halves and at the interfaces between the clamps and the

support struts.

(b) To the bolts, item (2), apply:

Refer to Fig. A-GBBAA Sheet 01, Views A to D.

Non Hardening

Jointing Putty-High

Temp. Area Str

06LDG2 As required

(c) On each support strut, install:

Refer to Fig. A-GBBAA Sheet 01, Views B to D.

NOTE: Consider that the clamps must be installed within the cylindrical

area only.

NOTE: Make sure that the dimension of the gap is between 3.0 mm and

3.5 mm (0.118 in and 0.138 in).

NOTE: Before installation of the clamp, mark the correct position with a

pen.

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@A310

SERVICE BULLETIN

2 Nut NAS1726-5E Item (4) Retained at

removal

2 Washer NAS1149D0563K Item (3) Retained at

removal

2 Bolt NSA5031-5-38 Item (2) Retained at

removal

2 Clamp A5347310320000 Item (1) Retained at

removal

(d) Protect the visible edges of the sealant with:

Refer to Fig. A-GBBAA Sheet 01, Views C and D.

Coating - Flexible

Structure

04QAB2 As required

(e) On the clamps and fasteners which you have installed, apply:

Refer to Fig. A-GBBAA Sheet 01, Views C and D.

Corrosion

Preventive

Compound-Water

Displacing

12ADB1 As required

(6) Subtask 532137-831-201-001 - Replace the THS support struts

Work Zones and Access Panels

Zone Access/Work location

310

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills NON SPECIFIC

Material necessary to do the job

Component COMPD01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

R21449H 1 ROD

NOTE: Alternatively, it is possible to install PN R21449, PN R21449D, PN

R21449G or PN R21449H, refer to IPC 53-19-89.

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137

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SERVICE BULLETIN

NOTE: The components listed above are only required if the replacement of a

support strut is necessary. The quantity of these items are to be ordered

as required.

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Component COMPD02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

MS24665-374 2 PIN

NOTE: The components listed above are only required if the replacement of a

support strut is necessary. The quantity of these items are to be ordered

as required.

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

References

Aircraft Maintenance Manual (AMM) 53-10-47, Page Block 401

55-10-11, Page Block 401

Illustrated Parts Catalog (IPC) 53-19-89

(a) Remove the affected THS support strut

CAUTION: ONLY ONE SUPPORT STRUT MAY BE REMOVED AT ONE

TIME.

CAUTION: IF ALL SUPPORT STRUTS ARE TO BE REMOVED, TWO

STRUTS P/N 98A27407568000 MUST BE INSTALLED, REFER

TO AMM 53-10-47, Page Block 401.

NOTE: If necessary, you can lift the THS by using slings to ease the strut

removal, refer to AMM 55-10-11, Page Block 401.

(b) Remove the affected THS support strut, refer to AMM 53-10-47, Page Block 401.

(c) Install the affected THS support strut, refer to AMM 53-10-47, Page Block 401 and

use these parts:

1 Rod Assy R21449H

NOTE: Alternatively, it is possible to install PN R21449, PN R21449D, PN

R21449G or PN R21449H, refer to IPC 53-19-89.

and

2 Pin-Cotter MS24665-374

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137

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SERVICE BULLETIN

**CONF 002

(1) Subtask 532137-280-201-002 - Do a HFEC inspection of the Trimmable Horizontal

Stabilizer (THS) support strut ends

Work Zones and Access Panels

Zone Access/Work location

310

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9 As required

Textile-Lint Free Cotton 14SBA1 As required

References

Non Destructive Test Manual (NTM) 53-19-47 -Part 6

Service Bulletin (SB) A310-53-2136

Fig. A-GBAAA

Inspection Area

Sheet 01

Fig. A-GFAAB

Inspection Flow Chart

Sheet 01

Sheet 02

(a) Clean the THS support struts with:

Non Aqueous

Cleaner-General

08BAA9 As required

and

Textile-Lint Free

Cotton

14SBA1 As required

(b) Do a Special Detailed Inspection of the Trimmable Horizontal Stabilizer (THS)

support struts located at FR91 in tail cone at Threshold given in para 1.E.(2), refer

to Fig. A-GBAAA Sheet 01, View B.

Refer to Fig. A-GFAAB Sheet 01.

(c) If clamps are installed, continue with SUBTASK 532137-280-202 002 Do a HFEC

inspection of the strut ends after removal of the clamps

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SERVICE BULLETIN

(d) If clamps are not installed:

1 Do an HFEC inspection of all 8 strut ends as per NTM 53-19-47 -Part 6,

before next flight, refer to Fig. A-GBAAA Sheet 01, View B.

a If there is/are crack(s) found on at least one strut end, refer to Fig. AGBAAA Sheet 01, View C.

<1> If the individual maximum crack length is more than 15.0 mm (0.591

in), or more than 4 cracks per strut end are equal or less than 15.0

mm (0.591 in).

<a> Replace the damaged strut by a new one before next flight,

refer to SUBTASK 532137-831-201 001 Replace the THS

support struts .

<b> Accomplish Service Bulletin No. A310-53-2136 before next

flight.

<c> Report the inspection results to Airbus within 10 days.

<d> Do SUBTASK 532137-280-202 002 Do a HFEC inspection of

the strut ends after removal of the clamps every 24 months.

<2> If the individual maximum crack length is equal or less than 15.0

mm (0.591 in), or not more than 4 cracks per strut end are equal or

less than 15.0 mm (0.591 in).

<a> Accomplish Service Bulletin No. A310-53-2136 before next

flight.

<b> Report the inspection results to Airbus within 10 days.

<c> Do SUBTASK 532137-280-202 002 Do a HFEC inspection of

the strut ends after removal of the clamps every 24 months.

b If there is/are no crack(s) found on strut ends, refer to Fig. A-GBAAA

Sheet 01, View C.

<1> Accomplish Service Bulletin No. A310-53-2136 before next flight.

<2> Report the inspection results to Airbus within 1 month.

<3> Do SUBTASK 532137-280-202 002 Do a HFEC inspection of the

strut ends after removal of the clamps every 24 months.

(2) Subtask 532137-280-202-002 - Do a HFEC inspection of the strut ends after

removal of the clamps

Work Zones and Access Panels

Zone Access/Work location

310

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137

REVISION No.: 00 - Feb 14/14 Page: 28

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@A310

SERVICE BULLETIN

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills NON SPECIFIC

References

Non Destructive Test Manual (NTM) 53-19-47 , Part 6

Fig. A-GBAAA

Inspection Area

Sheet 01

Fig. A-GFAAB

Inspection Flow Chart

Sheet 01

Sheet 02

(a) Remove clamp from each support strut end, refer to SUBTASK 532137-020-201

001 Remove the clamps from the THS support struts .

(b) Do a HFEC inspection of each strut end where clamps were installed as per NTM

53-19-47 , Part 6 before next flight, refer to Fig. A-GBAAA Sheet 01, View B and

Fig. A-GFAAB Sheet 02.

1 If no cracks found on strut ends, refer to Fig. A-GBAAA Sheet 01, View C.

a Install clamp on each strut end before next flight, refer to SUBTASK

532137-420-201 001 Install the clamps on the THS support struts .

b Report the inspection results to Airbus within 1 month.

c Do the work steps C.(2)(a) to C.(2)(b) again every 24 months.

2 If crack(s) found on at least one strut end, refer to Fig. A-GBAAA Sheet 01,

View C.

a If the individual maximum crack length is more than 15.0 mm (0.591 in),

or more than 4 cracks per strut end are equal or less than 15.0 mm

(0.591 in).

<1> Replace the damaged strut by a new one before next flight, refer to

SUBTASK 532137-831-201 001 Replace the THS support struts .

<2> Install clamp on each strut end before next flight, refer to SUBTASK

532137-420-201 001 Install the clamps on the THS support struts .

<3> Report the inspection results to Airbus within 10 days.

<4> Do the work steps C.(2)(a) to C.(2)(b) again every 24 months.

b If the individual maximum crack length is equal or less than 15.0 mm

(0.591 in), or not more than 4 cracks per strut end are equal or less than

15.0 mm (0.591 in).

<1> Install clamp on each strut end before next flight, refer to SUBTASK

532137-420-201 001 Install the clamps on the THS support struts .

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137

REVISION No.: 00 - Feb 14/14 Page: 29

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SERVICE BULLETIN

<2> Report the inspection results to Airbus within 10 days.

<3> Do the work steps C.(2)(a) to C.(2)(b) again every 24 months.

(3) Subtask 532137-020-201-001 - Remove the clamps from the THS support struts

Work Zones and Access Panels

Zone Access/Work location

310

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9 As required

Textile-Lint Free Cotton 14SBA1 As required

References

Fig. A-GBBAA

Removal/Installation of the Clamps

Sheet 01

(a) From each support strut, remove:

Refer to Fig. A-GBBAA Sheet 01, Views A to D.

2 Nut NAS1726-5E Item (4) Retain

2 Washer NAS1149D0563K Item (3) Retain

2 Bolt NSA5031-5-38 Item (2) Retain

2 Clamp A5347310320000 Item (1) Retain

(b) Remove the remaining sealant from the support struts and clean them with:

Refer to Fig. A-GBBAA Sheet 01, Views A to D.

Non Aqueous

Cleaner-General

08BAA9 As required

Textile-Lint Free

Cotton

14SBA1 As required

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137

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SERVICE BULLETIN

(4) Subtask 532137-420-201-001 - Install the clamps on the THS support struts

Work Zones and Access Panels

Zone Access/Work location

310

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Coating - Flexible Structure 04QAB2

Polysulfide Sealant-Low

Adhesion Fillet Structure

06AEB2 As required

Non Hardening Jointing

Putty-High Temp. Area Str

06LDG2 As required

Corrosion Preventive

Compound-Water

Displacing

12ADB1 As required

References

Fig. A-GBBAA

Removal/Installation of the Clamps

Sheet 01

(a) To the interface surfaces of the clamps, Item (1), apply:

Refer to Fig. A-GBBAA Sheet 01, Views A to D.

Polysulfide SealantLow Adhesion Fillet

Structure

06AEB2 As required

NOTE: Application of the sealant is required at the interfaces between the

two clamp halves and at the interfaces between the clamps and the

support struts.

(b) To the bolts, item (2), apply:

Refer to Fig. A-GBBAA Sheet 01, Views A to D.

Non Hardening

Jointing Putty-High

Temp. Area Str

06LDG2 As required

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137

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(c) On each support strut, install:

Refer to Fig. A-GBBAA Sheet 01, Views B to D.

NOTE: Consider that the clamps must be installed within the cylindrical

area only.

NOTE: Make sure that the dimension of the gap is between 3.0 mm and

3.5 mm (0.118 in and 0.138 in).

NOTE: Before installation of the clamp, mark the correct position with a

pen.

2 Nut NAS1726-5E Item (4) Retained at

removal

2 Washer NAS1149D0563K Item (3) Retained at

removal

2 Bolt NSA5031-5-38 Item (2) Retained at

removal

2 Clamp A5347310320000 Item (1) Retained at

removal

(d) Protect the visible edges of the sealant with:

Refer to Fig. A-GBBAA Sheet 01, Views C and D.

Coating - Flexible

Structure

04QAB2 As required

(e) On the clamps and fasteners which you have installed, apply:

Refer to Fig. A-GBBAA Sheet 01, Views C and D.

Corrosion

Preventive

Compound-Water

Displacing

12ADB1 As required

(5) Subtask 532137-831-201-001 - Replace the THS support struts

Work Zones and Access Panels

Zone Access/Work location

310

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills NON SPECIFIC

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137

REVISION No.: 00 - Feb 14/14 Page: 32

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SERVICE BULLETIN

Material necessary to do the job

Component COMPD01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

R21449H 1 ROD

NOTE: Alternatively, it is possible to install PN R21449, PN R21449D, PN

R21449G or PN R21449H, refer to IPC 53-19-89.

NOTE: The components listed above are only required if the replacement of a

support strut is necessary. The quantity of these items are to be ordered

as required.

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Component COMPD02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

MS24665-374 2 PIN

NOTE: The components listed above are only required if the replacement of a

support strut is necessary. The quantity of these items are to be ordered

as required.

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

References

Aircraft Maintenance Manual (AMM) 53-10-47, Page Block 401

55-10-11, Page Block 401

Illustrated Parts Catalog (IPC) 53-19-89

(a) Remove the affected THS support strut

CAUTION: ONLY ONE SUPPORT STRUT MAY BE REMOVED AT ONE

TIME.

CAUTION: IF ALL SUPPORT STRUTS ARE TO BE REMOVED, TWO

STRUTS P/N 98A27407568000 MUST BE INSTALLED, REFER

TO AMM 53-10-47, Page Block 401.

NOTE: If necessary, you can lift the THS by using slings to ease the strut

removal, refer to AMM 55-10-11, Page Block 401.

(b) Remove the affected THS support strut, refer to AMM 53-10-47, Page Block 401.

(c) Install the affected THS support strut, refer to AMM 53-10-47, Page Block 401 and

use these parts:

1 Rod Assy R21449H

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137

REVISION No.: 00 - Feb 14/14 Page: 33

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SERVICE BULLETIN

NOTE: Alternatively, it is possible to install PN R21449, PN R21449D, PN

R21449G or PN R21449H, refer to IPC 53-19-89.

and

2 Pin-Cotter MS24665-374

**CONF ALL

D. TEST

**CONF 001

None

**CONF 002

None

**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 532137-942-201-001 - Close-up

Work Zones and Access Panels

Zone Access/Work location

310 Access Door 313AL

Manpower Resources

Skills NON SPECIFIC

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Close the access door 313AL.

(c) Remove the access platform(s).

**CONF 002

(1) Subtask 532137-942-201-001 - Close-up

Work Zones and Access Panels

Zone Access/Work location

310 Access Door 313AL

Manpower Resources

Skills NON SPECIFIC

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137

REVISION No.: 00 - Feb 14/14 Page: 34

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(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Close the access door 313AL.

(c) Remove the access platform(s).

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137

REVISION No.: 00 - Feb 14/14 Page: 35

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@A310

SERVICE BULLETIN

**CONF 001

COMPLETE

RECORDS

AVAILABLE SINCE

AIRCRAFT EIS

DO A GENERAL VISUAL INSPECTION

OF STRUTS ON AIRCRAFT

STRUT(S)

REPLACED SINCE

AIRCRAFT

REPORT THE

INSPECTION

RESULTS TO AIRBUS

WITHIN 1 MONTH

NO FURTHER ACTION

CLAMPS INSTALLED

CONTINUE ON

SHEET 02

CONTINUE ON

SHEET 03

NO YES

YES NO

NO YES

REPORT THE

INSPECTION

RESULTS TO AIRBUS

WITHIN 1 MONTH

NO FURTHER ACTION

NO YES

EIS

STRUT(S) AFFECTED

INSTALLED

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:

CHECK, IF STRUTS REPLACEMENT IS RECORDED

SINCE AIRCRAFT ENTRY INTO SERVICE (EIS)

B_SB_532137_6_FAAA_01_02

Figure A-GFAAA - Sheet 01

Inspection Flow Chart

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137

REVISION No.: 00 - Feb 14/14 Page: 36

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SERVICE BULLETIN

**CONF 001

CONTINUED FROM

SHEET 01

CRACK(S) FOUND

ON AT LEAST ONE

STRUT END

NO YES

ACCOMPLISH SERVICE

BULLETIN NO. A310−53−2136

YES

NO

REPLACE THE DAMAGED

STRUT BY A NEW ONE

CRACKS WITHIN

THE GIVEN LIMITS

REPORT THE INSPECTION

RESULTS TO AIRBUS:

−WITHIN 10 DAYS WHEN FINDING

−WITHIN 1 MONTH WHEN NIL FINDING

DO A HIGH FREQUENCY EDDY CURRENT

(HFEC) INSPECTION OF EACH STRUT END

AT THRESHOLD GIVEN IN PARA 1.E.(2)

OF THIS SERVICE BULLETIN

REPEAT THE INSPECTION

AT INTERVALS GIVEN IN

PARA 1.E.(2)

BEFORE NEXT FLIGHT

BEFORE NEXT FLIGHT

B_SB_532137_6_FAAA_02_03

Figure A-GFAAA - Sheet 02

Inspection Flow Chart

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137

REVISION No.: 00 - Feb 14/14 Page: 37

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SERVICE BULLETIN

**CONF 001

CONTINUED FROM

SHEET 01

REMOVE CLAMP FROM EACH SUPPORT

STRUT END AT INTERVAL GIVEN IN

PARA 1.E.(2) OF THIS SERVICE BULLETIN

DO A HFEC INSPECTION OF EACH STRUT

END WHERE CLAMPS WERE INSTALLED

CRACK(S) FOUND

ON AT LEAST ONE

STRUT END

NO YES

NO

REPLACE THE DAMAGED

STRUT BY A NEW ONE

RE−INSTALL

CLAMP ON EACH

STRUT END

YES CRACKS WITHIN

THE GIVEN LIMITS

REPORT THE INSPECTION

RESULTS TO AIRBUS:

−WITHIN 10 DAYS WHEN FINDING

−WITHIN 1 MONTH WHEN NIL FINDING

REPEAT THE INSPECTION

AT INTERVALS GIVEN IN

PARA 1.E.(2)

BEFORE NEXT FLIGHT

BEFORE NEXT FLIGHT

BEFORE NEXT FLIGHT

B_SB_532137_6_FAAA_03_02

Figure A-GFAAA - Sheet 03

Inspection Flow Chart

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137

REVISION No.: 00 - Feb 14/14 Page: 38

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@A310

SERVICE BULLETIN

**CONF 002

CLAMPS INSTALLED CONTINUE ON

SHEET 02 NO YES

DO A SPECIAL DETAILED INSPECTION OF THE TRIMMABLE

HORIZONTAL STABILIZER (THS) SUPPORT STRUTS LOCATED

AT FR91 IN TAIL CONE AT THRESHOLD GIVEN IN PARA 1.E.(2)

OF THIS SERVICE BULLETIN

CRACK(S)

FOUND ON AT LEAST

ONE STRUT

NO YES

END

YES NO

REPLACE THE DAMAGED

STRUT BY A NEW ONE

ACCOMPLISH SERVICE

BULLETIN NO. A310−53−2136

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:

CRACKS WITHIN

THE GIVEN LIMITS

REPORT THE INSPECTION

RESULTS TO AIRBUS:

−WITHIN 10 DAYS WHEN FINDING

−WITHIN 1 MONTH WHEN NIL FINDING

REPEAT THE INSPECTION

AT INTERVALS GIVEN IN

PARA 1.E.(2)

BEFORE NEXT FLIGHT

DO A HFEC INSPECTION OF ALL 8 STRUT ENDS

B_SB_532137_6_FAAB_01_04

Figure A-GFAAB - Sheet 01

Inspection Flow Chart

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137

REVISION No.: 00 - Feb 14/14 Page: 39

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@A310

SERVICE BULLETIN

**CONF 002

CONTINUED FROM

SHEET 01

REMOVE CLAMP FROM EACH 

SUPPORT STRUT END

DO A HFEC INSPECTION OF

ALL 8 STRUT ENDS

CRACK(S)

FOUND ON AT LEAST

ONE STRUT

YES NO

END

NO YES

RE−INSTALL CLAMP AT

EACH SUPPORT STRUT

END REPLACE THE DAMAGED STRUT

CRACKS WITHIN

THE GIVEN LIMITS

REPORT THE INSPECTION

RESULTS TO AIRBUS:

−WITHIN 10 DAYS WHEN FINDING

−WITHIN 1 MONTH WHEN NIL FINDING

REPEAT THE INSPECTION

AT INTERVALS GIVEN IN

PARA 1.E.(2)

BEFORE NEXT FLIGHT

B_SB_532137_6_FAAB_02_03

Figure A-GFAAB - Sheet 02

Inspection Flow Chart

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137

REVISION No.: 00 - Feb 14/14 Page: 40

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@A310

SERVICE BULLETIN

**CONF ALL

FR91

B

B

B

AREA TO BE INSPECTED

C C

B

TYPICAL

STRUT TO BE

INSPECTED

PN R21449

PN R21449D

PN R21449G

OR

PN R21449H

C

TYPICAL

TYPICAL

CRACKS

B

Z310

A

A

B_SB_532137_6_BAAA_01_01

Figure A-GBAAA - Sheet 01

Inspection Area

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137

REVISION No.: 00 - Feb 14/14 Page: 41

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@A310

SERVICE BULLETIN

**CONF ALL

C

C

FR91

TYPICAL

D

(1)

(2)

(3)

(4) C

D

B

A

D

(2)

(3)

(4)

(1)

B

B

B

B

Z310

A

01 PROTECT WITH COMPOUND (MAT. NO. 12ADB1)

02

NOTE:

01

02

3.0 mm TO 3.5 mm

(0.118 in TO 0.138 in)

CONSIDER THAT THE CLAMPS MUST BE INSTALLED

WITHIN THE CYLINDRICAL AREA ONLY B_SB_532137_6_BBAA_01_02

Figure A-GBBAA - Sheet 01

Removal/Installation of the Clamps

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137

REVISION No.: 00 - Feb 14/14 Page: 42

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@A310

SERVICE BULLETIN

**CONF 001

FR91

Z310

A

A

INSPECTION REPORT

SERVICE BULLETIN NO:

DATE OF INSPECTION:

AIRCRAFT MSN:

FLIGHT CYCLES:

FLIGHT HOURS:

PLEASE SEND REPORTING SHEET TO:

 AIRBUS CUSTOMER SERVICES ENGINEERING

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

E−MAIL: structure.sbinspectionresult@airbus.com

A310−53−2137

SEES1

FINDINGS: YES NO

INSPECTION METHOD: SPECIAL DETAILED INSPECTION

FAX: +33(0)561 93 36 14

TYPICAL

AREA TO BE

INSPECTED

AREA TO BE

INSPECTED

A

B

B

A

A

B

B

A

B

B

B

B

B

4

3

1

2

B_SB_532137_6_AAAA_01_01

Figure A-GAAAA - Sheet 01

Inspection Report

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137

REVISION No.: 00 - Feb 14/14 Page: 43

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@A310

SERVICE BULLETIN

**CONF 001

INSPECTION REPORT

STRUT

NUMBER

RECORDS

COMPLETE

SINCE

AIRCRAFT

EIS

STRUT

REPLACED

SINCE

AIRCRAFT

EIS

STRUT

AFFECTED

CLAMPS

INSTALLED

YES

NO

YES

NO

YES

NO

YES

NO

1

YES

NO

YES

NO

YES

NO

YES

NO

2

YES

NO

YES

NO

YES

NO

YES

NO

3

YES

NO

YES

NO

YES

NO

YES

NO

4

STRUT

NUMBER

1

2

3

4

CRACK

QUANTITY

LENGTH

CRACK 1

LENGTH

CRACK 2

LENGTH

CRACK 3

LENGTH

CRACK 4

STRUT

REPLACED

INSTALLED 

PARTNUMBER

YES

NO

YES

NO

YES

NO

YES

NO

A

B

END

POS

A

B

A

B

A

B

LENGTH

CRACK 5

B_SB_532137_6_AAAA_02_02

Figure A-GAAAA - Sheet 02

Inspection Report

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137

REVISION No.: 00 - Feb 14/14 Page: 44

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@A310

SERVICE BULLETIN

**CONF 002

FR91

Z310

A

A

INSPECTION REPORT

SERVICE BULLETIN NO:

DATE OF INSPECTION:

AIRCRAFT MSN:

FLIGHT CYCLES:

FLIGHT HOURS:

PLEASE SEND REPORTING SHEET TO:

 AIRBUS CUSTOMER SERVICES ENGINEERING

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

E−MAIL: structure.sbinspectionresult@airbus.com

A310−53−2137

SEES1

FINDINGS: YES NO

INSPECTION METHOD: SPECIAL DETAILED INSPECTION

FAX: +33(0)561 93 36 14

TYPICAL

AREA TO BE

INSPECTED

AREA TO BE

INSPECTED

A

B

B

A

A

B

B

A

B

B

B

B

B

4

3

1

2

B_SB_532137_6_AAAB_01_01

Figure A-GAAAB - Sheet 01

Inspection Report

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137

REVISION No.: 00 - Feb 14/14 Page: 45

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@A310

SERVICE BULLETIN

**CONF 002 INSPECTION REPORT CRACK QUANTITY LENGTH CRACK 1 LENGTH CRACK 2 LENGTH CRACK 3 LENGTH CRACK 4 STRUT REPLACED INSTALLED PARTNUMBER

YES

NO

YES

NO

YES

NO

YES

NO

A

B

END

POS

A

B

A

B

A

B

CLAMPS

INSTALLED

YES

NO

YES

NO

YES

NO

YES

NO

STRUT

NUMBER

1

2

3

4

LENGTH

CRACK 5

B_SB_532137_6_AAAB_02_01

Figure A-GAAAB - Sheet 02

Inspection Report

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137

REVISION No.: 00 - Feb 14/14 Page: 46

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@A310

SERVICE BULLETIN

Appendix 01 - Elapsed Time Assumptions

**CONF 001

ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A310−53−2137

GET ACCESS

MH ET/S

TOTAL MANHOURS

SB ELAPSED TIME

STEPS

0.50 0.50

0 5

0.50 0.50

2.00 2.00

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.

ARE NOT REFLECTED IN THIS GANTT CHART.

01

02

NOTES:

PER

1

1

1

:

:

SB ELAPSED TIME

(HOURS)

123 4 6

IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS

IDENTIFY THE SUPPORT

STRUTS INSTALLED

7 8

DO A HFEC INSPECTION OF 2.00 2.00 1

THE STRUT ENDS AFTER

REMOVAL OF THE CLAMPS

REMOVE THE CLAMPS FROM 1

THE THS SUPPORT STRUTS

INSTALL THE CLAMPS ON 0.50 0.50 1

THE THS SUPPORT STRUTS

REPLACE THE THS SUPPORT 1.00 1.00 1

STRUTS

CLOSE−UP 0.50 0.50 1

7.50

5.00

DO A HFEC INSPECTION OF

ENDS

0.50 0.50

THE THS SUPPORT STRUT

B_SB_532137_6_ABAA_01_01

Figure A-GABAA - Sheet 01

Gantt Chart

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137

REVISION No.: 00 - Feb 14/14 Page: 1

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@A310

SERVICE BULLETIN

Appendix 01 - Elapsed Time Assumptions

**CONF 002

ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A310−53−2137

GET ACCESS

MH ET/S

TOTAL MANHOURS

SB ELAPSED TIME

7.00

4.50

STEPS

0.50 0.50

0 5

2.00 2.00

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.

ARE NOT REFLECTED IN THIS GANTT CHART.

01

02

NOTES:

PER

1

1

:

:

SB ELAPSED TIME

(HOURS)

123 4 6

IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS

7 8

DO A HFEC INSPECTION OF 2.00 2.00 1

THE STRUT ENDS AFTER

REMOVAL OF THE CLAMPS

REMOVE THE CLAMPS FROM 0.50 0.50 1

THE THS SUPPORT STRUTS

INSTALL THE CLAMPS ON 0.50 0.50 1

THE THS SUPPORT STRUTS

REPLACE THE THS SUPPORT 1.00 1.00 1

STRUTS

CLOSE−UP 0.50 0.50 1

DO A HFEC INSPECTION OF

THE THS SUPPORT STRUT

ENDS

B_SB_532137_6_ABAB_01_02

Figure A-GABAB - Sheet 01

Gantt Chart

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137

REVISION No.: 00 - Feb 14/14 Page: 2

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@A310

SERVICE BULLETIN

REPORTING SHEET

TITLE: FUSELAGE - TAIL CONE - THS SUPPORT STRUTS AT FR91 -

INSPECTION FOR CRACKS

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: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137

REVISION No.: 00 - Feb 14/14 Page: 1

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

QUALITY PERCEPTION FORM

Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data

that you provide us will be used to analyse areas of difficulties and to take corrective action to further

improve the quality of our Service Bulletins.

We thank you for the time you have taken in completing this form.

(Please rate on a scale of 1 to 4, with 4 being the highest score)

- Quality rating of this SB 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: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137

REVISION No.: 00 - Feb 14/14 Page: 1

6

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