@A310

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

ATA SYSTEM: 53

TITLE: FUSELAGE - GENERAL - REINFORCE THE FLOOR CROSSBEAMS AT

FR22/FR23 AND FR61/FR62

MODIFICATION No.: 13434D23217

This page transmits Revision No.02 of Service Bulletin No.A310-53-2133

ADDITIONAL WORK

**CONF ALL

No additional work is required by this revision for aircraft modified by any previous issue.

REASON

Revision No.02 issued to :

- correct AMM references,

- add the rework areas on figures,

- incorporate minor changes.

CHANGES

SUMMARY

EFFECTIVITY OPERATOR LIST UPDATED R

CONCURRENT REQUIREMENTS CONCURRENT REQUIREMENTS UPDATED R

PLANNING INFORMATION

EFFECTIVITY EFFECTIVITY RELATED INFORMATION

UPDATED

R

Configuration definition CONFIGURATION LIST UPDATED R

CONCURRENT REQUIREMENTS CONCURRENT SB LIST UPDATED R

APPROVAL APPROVAL UPDATED R

WEIGHT AND BALANCE WEIGHT UPDATED

BALANCE UPDATED

R

WEIGHT UPDATED

BALANCE UPDATED

R

REFERENCES REFERENCED DOCUMENTATION UPDATED R

REFERENCED DOCUMENTATION UPDATED R

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 1

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

MATERIAL INFORMATION

MATERIAL - PRICE AND AVAILABILITY

Price and Availability PRICE AND AVAILABILITY UPDATED

MATERIAL SET UPDATED

R

ACCOMPLISHMENT INSTRUCTIONS

TASK 532133- 831-848-001-

MODIFICATION

Subtask 532133-910-201-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

R

Subtask 532133-839-201-001 SUBTASK SOLUTION UPDATED R

Subtask 532133-910-201-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

R

Subtask 532133-839-201-001 SUBTASK SOLUTION UPDATED R

Subtask 532133-941-201-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Subtask 532133-941-201-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Subtask 532133-831-204-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

REFERENCED DOCUMENTATION UPDATED

R

Subtask 532133-831-208-001 SUBTASK SOLUTION UPDATED R

Subtask 532133-831-204-002 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

REFERENCED DOCUMENTATION UPDATED

R

Subtask 532133-831-208-001 SUBTASK SOLUTION UPDATED R

Subtask 532133-942-201-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Subtask 532133-942-201-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Fig. A-GBCAA FIGURE SOLUTION UPDATED R

Fig. A-GBCAA Sheet 02 SHEET UPDATED R

Fig. A-GBCAA Sheet 03 SHEET UPDATED R

Fig. A-GBCAA Sheet 05 SHEET UPDATED R

Fig. A-GBCAA Sheet 08 SHEET ADDED N

Fig. A-GBGAA FIGURE SOLUTION UPDATED R

Fig. A-GBGAA Sheet 02 SHEET UPDATED R

Fig. A-GBGAA Sheet 03 SHEET UPDATED R

Fig. A-GBGAA Sheet 05 SHEET UPDATED R

Fig. A-GBGAA Sheet 08 SHEET ADDED N

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 2

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@A310

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

FILLING INSTRUCTIONS

This Service Bulletin has been generated electronically and is reissued as a complete document.

Replace the complete document.

Put this Revision Transmittal Sheet in front of the Service Bulletin.

HISTORY OF PREVIOUS REVISIONS

This Revision is issued to :

incorporate the result of the validation report from A300-600 aircraft MSN 0605.

REVISION SEQUENCE

ORIGINAL: Jan 15/10

REVISION No. : 01 - May 21/10

REVISION No. : 02 - Apr 27/11

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 3

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

This Page Intentionally Left Blank

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 4

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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.

ATA SYSTEM: 53

TITLE: FUSELAGE - GENERAL - REINFORCE THE FLOOR CROSSBEAMS AT

FR22/FR23 AND FR61/FR62

**CONF ALL

MODIFICATIONS

MODIFICATION CLASSIFICATION

MAJOR None

MINOR 13434D23217

NOTE: As per EASA IR 21, a minor change is one that has no appreciable effect on the

mass, balance, structural strength, reliability, operational characteristics affecting the

airworthiness of the product. All other changes are major changes.

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

Some operators have reported cracks in the crossbeam at the junction with the cargo door actuator

support beam. The damage was located on the outboard row of rivets on the crossbeam at FR23. The

laboratory analysis has revealed that the cracks initiated in the fastener hole are propagated vertically.

That the design of the forward and aft cargo door attachment is similar, the crossbeams at FR22, FR23,

FR61 and FR62 should be reinforced to avoid crack initiation.

This Service Bulletin details the procedure to install the reinforce fittings and relocate the brackets at

the floor crossbeams at FR22, FR23, FR61 and FR62.

NOTE: It is not necessary to accomplish the Inspection Service Bulletin No. A310-53-2134

before doing this Service Bulletin. This Service Bulletin can be accomplished directly as

given in the accomplishment instruction.

NOTE: To reach the mod advantages, this Service Bulletin is to be accomplished, if:

- Service Bulletin No. A310-53-2094 has been previously accomplished,

- none repair has been performed in the affected areas in accordance with SRM, All

Operators Telex 53-07, Inspection Service Bulletin No. A310-53-2095 or Repair

Approval Sheet (RAS).

In case of existing repairs, the operators are requested to contact Airbus Repair Support

before accomplishment of this Service Bulletin, for further instructions.

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 1

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@A310

SERVICE BULLETIN

SUMMARY

The accomplishment of this Service Bulletin will :

- contribute to avoid the development of cracks,

- cancel the inspection requirements in accordance with the Inspection Service Bulletin No.

A310-53-2134.

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE RECOMMENDED (1) CANCELS INSPECTION SB YES

POTENTIAL AD NO A/C OPERATION AFFECTED NO

RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO

COST SAVING NO ETOPS AFFECTED NO

STRUCTURAL LIFE EXTN YES VENDOR SB INVOLVED NO

NOTE (1): Service Bulletin recommended to be accomplished to prevent significant operational

disruptions.

MATERIAL PRICE INFORMATION

**CONF 001

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 532133D01R02 1 1,140.00 Reinforcement and attachment parts

Kit 532133D02R01 1 1,030.00 Reinforcement and attachment parts

TOTAL 2,170.00

Component COMPD01 1 See SB Clamp and attachment parts

Standard tool TOOLD01 2 See SB Support Struts - FWD and AFT Cargo

Compartment Doors

**CONF 002

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 532133D01R02 1 1,140.00 Reinforcement and attachment parts

Kit 532133D03R01 1 1,090.00 Reinforcement and attachment parts

TOTAL 2,230.00

Component COMPD01 1 See SB Clamp and attachment parts

Standard tool TOOLD01 2 See SB Support Struts - FWD and AFT Cargo

Compartment Doors

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 2

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@A310

SERVICE BULLETIN

SUMMARY

EFFECTIVITY

**CONF ALL

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

18T 19U 52X 58X 82Z 83V 85Z 98W 99Y AFG AIB AIC BAF

BBC CFC DAH DEC DGA F2I FDX G8E GAF HFY I2L IRA IRM

IYE JAB JAV K1P KAC KYV KZU MGL MWA PIA QAF R1T RJA

ROT RZO SBI SGX SUD THY TSC UBD UZB WHT WTJ

The equivalent of this Service Bulletin has been validated on A300-600 aircraft MSN 0605.

CONCURRENT REQUIREMENTS

NOTE: Accomplishment of this Service Bulletin requires the prior or simultaneous

accomplishment of the following Service Bulletin(s) or the equivalent production

modification(s):

Service Bulletin No. A310-53-2095

REFERENCES / REPERCUSSIONS

TFU None

OEB None

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER None

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

MANPOWER

**CONF 001

Task 532133-831-848-001: MODIFICATION

TOTAL MANHOURS 34.00

ELAPSED TIME (HOURS) 22.00

**CONF 002

Task 532133-831-848-001: MODIFICATION

TOTAL MANHOURS 34.00

ELAPSED TIME (HOURS) 22.00

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

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@A310

SERVICE BULLETIN

SUMMARY

APPENDICES

**CONF ALL

None

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 4

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@A310

SERVICE BULLETIN

SUMMARY

**CONF ALL

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2

SEAT TRACK 4

FR21 FR22 FR23 FR24

SEAT TRACK 6

Z130

A

B_SB_532133_6_SAAA_01_00

AREAS TO BE MODIFIED

FWD

A

Figure A-GSAAA - Sheet 01

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

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@A310

SERVICE BULLETIN

SUMMARY

**CONF ALL

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2

SEAT TRACK 4

A

SEAT TRACK 6

FR60 FR61 FR62 FR63

Z150

AREAS TO BE MODIFIED

FWD

A

B_SB_532133_6_SAAA_02_00

Figure A-GSAAA - Sheet 02

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 6

6

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

SERVICE BULLETIN

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

ATA SYSTEM: 53

TITLE: FUSELAGE - GENERAL - REINFORCE THE FLOOR CROSSBEAMS AT

FR22/FR23 AND FR61/FR62

MODIFICATION No.: 13434D23217

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

The equivalent of this Service Bulletin has been validated on A300-600 aircraft MSN 0605.

(1) Models

310-203 310-204 310-221 310-222 310-304 310-308 310-322 310-324

310-325

(2) Effectivity by MSN

0162 0191 0201 0217 0224 0230 0233 0237 0241 0245 0248 0251 0254 0257 0260

0264 0267 0273 0278 0281 0283 0288 0291 0293 0297 0303 0309 0313 0316 0318

0320 0326 0331 0333 0335 0338-0339 0342-0343 0345-0346 0353 0355-0357

0359-0360 0362 0364 0367 0369-0370 0372 0375 0378-0379 0386 0389-0390 0392

0394 0397 0399-0400 0406-0407 0410 0413 0416 0418-0419 0421-0422 0425

0427-0429 0431 0434 0436-0437 0439 0441 0444-0449 0452 0454 0456-0458 0467

0472-0473 0475-0476 0478 0480-0492 0494-0500 0502-0503 0519-0520 0522-0524

0526-0527 0531 0534 0537-0539 0541-0542 0544-0545 0547 0549-0552 0562

0564-0565 0567-0568 0571 0573-0574 0576 0585-0588 0590-0595 0597 0599-0600

0620 0622 0624 0636 0638 0640 0642 0644 0646-0654 0656 0658 0660-0661 0663

0665 0667 0669 0671-0672 0674 0676 0678 0680 0682 0684 0686-0687 0689 0691

0693 0697 0700 0702 0704 0706

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

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SERVICE BULLETIN

(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

18T 0473

19U 0399

52X 0410

58X 0431

82Z 0550 0551

83V 0427

85Z 0547

98W 0416

99Y 0489

AFG 0496 0497

AIB 0650 0674 0686

AIC 0392 0406 0407 0413 0428 0429 0538 0544 0654 0665 0669 0680

BAF 0367 0372

BBC 0594 0642 0700

CFC 0425 0441 0444 0446 0482

DAH 0291 0293

DEC 0684 0693 0697

DGA 0418 0421 0422

F2I 0309 0419 0487

FDX 0162 0191 0201 0217 0224 0230 0233 0237 0241 0245 0248 0251

0254 0257 0260 0264 0267 0273 0278 0281 0283 0288 0297 0303

0313 0316 0318 0326 0331 0333 0335 0339 0342 0343 0345 0346

0353 0355 0356 0359 0360 0362 0364 0369 0378 0394 0397 0400

0439 0449 0452 0454 0456 0457 0458 0467 0492 0500 0534 0539

0542 0549 0552 0593 0638

G8E 0475

GAF 0434 0484 0498 0499 0503 0522 0523

HFY 0495 0565

I2L 0486 0640

IRA 0338 0370 0375 0379 0389 0390 0436 0671

IRM 0488 0524 0537 0564 0567 0586 0595 0620

IYE 0568 0702 0704

JAB 0320

JAV 0357 0481

K1P 0648

KAC 0647 0649 0663

KYV 0386

KZU 0592 0622 0646

MGL 0526

MWA 0652

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

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@A310

SERVICE BULLETIN

OPERATOR MSN

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

QAF 0667

R1T 0591

RJA 0445 0490 0491 0531

ROT 0636 0644

RZO 0571 0624 0651 0661

SBI 0520

SGX 0519 0562

SUD 0437

THY 0476 0478 0480 0502

TSC 0447 0472 0483 0485 0527 0541 0545 0588 0597 0599 0600 0658

UBD 0672

UZB 0574 0576 0706

WHT 0448 0573

WTJ 0494

(4) Configuration by MSN

MSN CONFIGURATION

0162 0191 0201 0217 0224 0230 0233 0237 0241 0245 0248

0251 0254 0257 0260 0264 0267 0273 0278 0281 0283 0288

0291 0293 0297 0303 0309 0313 0316 0318 0320 0326 0331

0333 0335 0338 0339 0342 0343 0345 0346 0353 0355 0356

0357 0359 0360 0362 0364 0367 0369 0370 0372 0375 0378

0379 0386 0389 0390 0392 0394 0397 0399 0400 0406 0407

0410 0413 0416 0418 0419 0421 0422 0425 0427 0428 0429

0431 0434 0436 0437 0441 0444 0445

001

0439 0446 0447 0448 0449 0452 0454 0456 0457 0458 0467

0472 0473 0475 0476 0478 0480 0481 0482 0483 0484 0485

0486 0487 0488 0489 0490 0491 0492 0494 0495 0496 0497

0498 0499 0500 0502 0503 0519 0520 0522 0523 0524 0526

0527 0531 0534 0537 0538 0539 0541 0542 0544 0545 0547

0549 0550 0551 0552 0562 0564 0565 0567 0568 0571 0573

0574 0576 0585 0586 0587 0588 0590 0591 0592 0593 0594

0595 0597 0599 0600 0620 0622 0624 0636 0638 0640 0642

0644 0646 0647 0648 0649 0650 0651 0652 0653 0654 0656

0658 0660 0661 0663 0665 0667 0669 0671 0672 0674 0676

0678 0680 0682 0684 0686 0687 0689 0691 0693 0697 0700

0702 0704 0706

002

(5) Configuration definition

**CONF 001

Config. 001 is valid for aircraft on which Modification No. 05596D04241 (FUSELAGE -

FLOOR STRUCTURE - MODIFY CROSSBEAM AND SEAT TRACK JUNCTION POINT)

is not embodied.

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

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SERVICE BULLETIN

**CONF 002

Config. 002 is valid for aircraft on which Modification No. 05596D04241 (FUSELAGE -

FLOOR STRUCTURE - MODIFY CROSSBREED AND SEAT TRACK JUNCTION

POINT) is embodied.

(6) Material Effectivity

**CONF 001

MATERIAL QTY PER A/C SEE NOTES

Kit 532133D01R02 1

Kit 532133D02R01 1

Component COMPD01 1

Consumable CMLD01 1

Standard tool TOOLD01 2

**CONF 002

MATERIAL QTY PER A/C SEE NOTES

Kit 532133D01R02 1

Kit 532133D03R01 1

Component COMPD01 1

Consumable CMLD01 1

Standard tool TOOLD01 2

**CONF ALL

B. CONCURRENT REQUIREMENTS

NOTE: Accomplishment of this Service Bulletin requires the prior or simultaneous

accomplishment of the following Service Bulletin(s) or the equivalent

production modification(s):

Service Bulletin No. A310-53-2095

C. REASON

(1) History

Some operators have reported cracks in the crossbeam at the junction with the cargo

door actuator support beam. The damage was located on the outboard row of rivets on

the crossbeam at FR23. The laboratory analysis has revealed that the cracks initiated in

the fastener hole are propagated vertically. That the design of the forward and aft cargo

door attachment is similar, the crossbeams at FR22, FR23, FR61 and FR62 should be

reinforced to avoid crack initiation.

(2) Objective/Action

This Service Bulletin details the procedure to install the reinforce fittings and relocate the

brackets at the floor crossbeams at FR22, FR23, FR61 and FR62.

NOTE: It is not necessary to accomplish the Inspection Service Bulletin No.

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 4

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@A310

SERVICE BULLETIN

A310-53-2134 before doing this Service Bulletin. This Service Bulletin

can be accomplished directly as given in the accomplishment instruction.

NOTE: To reach the mod advantages, this Service Bulletin is to be

accomplished, if:

- Service Bulletin No. A310-53-2094 has been previously

accomplished,

- none repair has been performed in the affected areas in accordance

with SRM, All Operators Telex 53-07, Inspection Service Bulletin No.

A310-53-2095 or Repair Approval Sheet (RAS).

In case of existing repairs, the operators are requested to contact Airbus

Repair Support before accomplishment of this Service Bulletin, for further

instructions.

(3) Advantages

The accomplishment of this Service Bulletin will :

- contribute to avoid the development of cracks,

- cancel the inspection requirements in accordance with the Inspection Service

Bulletin No. A310-53-2134.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

**CONF 001

Task 532133-831-848-001: MODIFICATION

(1) Remove the existing fasteners from the crossbeam at FR22 and FR23.

(2) Rotating Probe Inspection at the crossbeam FR22 and FR23.

(3) Install the reinforcement and brackets at the crossbeam at FR22 and FR23.

(4) Remove the brackets and fasteners from the crossbeam FR61 and FR62.

(5) Rotating Probe Inspection at the crossbeam FR61 and FR62.

(6) Install the reinforcement and bracket at the crossbeam at FR61 and FR62.

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

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@A310

SERVICE BULLETIN

**CONF 002

Task 532133-831-848-001: MODIFICATION

(1) Remove the existing fasteners from the crossbeam at FR22 and FR23.

(2) Rotating Probe Inspection at the crossbeam at FR22 and FR23.

(3) Install the reinforcement and brackets at the crossbeam at FR22 and FR23.

(4) Remove the brackets and fasteners from the crossbeam FR61 and FR62.

(5) Rotating Probe Inspection at the crossbeam FR61 and FR62.

(6) Install the reinforcement and bracket at the crossbeam at FR61 and FR62.

**CONF ALL

E. COMPLIANCE

(1) Classification

RECOMMENDED: Service Bulletin recommended to be accomplished to prevent

significant operational disruptions.

(2) Accomplishment Timescale

Accomplishment of this Service Bulletin is recommended at the earliest opportunity

where manpower and facilities are available.

F. APPROVAL

The technical content of this document is approved under authority of Design Organization

Approval No. EASA.21J.031.

If an aircraft listed in the effectivity has a modification or repair embodied that is not of

AIRBUS origin, and which affects the content of this Service Bulletin, the operator is

responsible for obtaining approval by its airworthiness authority for any adaptation necessary

before incorporation of the Service Bulletin.

Aircraft that listed in this Service Bulletin and have been converted to freighter aircraft may

have a difference in the affected area. In this event, the operator should contact the relevant

Customer Service to obtain the necessary information about the future/planned Service

Bulletins for the converted aircraft.

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.

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

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@A310

SERVICE BULLETIN

**CONF 001

Task 532133-831-848-001: MODIFICATION

Get Access 4.00

On Aircraft

Remove the existing fasteners from the crossbeam at

FR22 and FR23.

4.00

Rotating Probe Inspection at the crossbeam FR22 and

FR23.

4.00

Install the reinforcement and brackets at the

crossbeam at FR22 and FR23.

6.00

Remove the brackets and fasteners from the

crossbeam FR61 and FR62.

4.00

Rotating Probe Inspection at the crossbeam FR61 and

FR62.

4.00

Install the reinforcement and bracket at the crossbeam

at FR61 and FR62.

4.00

Tests 1.00

Close-Up 3.00

TOTAL MANHOURS 34.00

ELAPSED TIME (HOURS) 22.00

**CONF 002

Task 532133-831-848-001: MODIFICATION

Get Access 4.00

On Aircraft

Remove the existing fasteners from the crossbeam at

FR22 and FR23.

4.00

Rotating Probe Inspection at the crossbeam at FR22

and FR23.

4.00

Install the reinforcement and brackets at the

crossbeam at FR22 and FR23.

6.00

Remove the brackets and fasteners from the

crossbeam FR61 and FR62.

4.00

Rotating Probe Inspection at the crossbeam FR61 and

FR62.

4.00

Install the reinforcement and bracket at the crossbeam

at FR61 and FR62.

4.00

Tests 1.00

Close-Up 3.00

TOTAL MANHOURS 34.00

ELAPSED TIME (HOURS) 22.00

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

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@A310

SERVICE BULLETIN

**CONF ALL

H. WEIGHT AND BALANCE

**CONF 001

The weight and balance estimates given in this Service Bulletin are based on the

Manufacturer’s Empty Weight (MEW) and do not include operator item’s. For the definition of

MEW and operator’s items refer to Weight and Balance Manual (WBM) Chapter 1-00-07.

Manufacturers Empty Weight +0.533 KG (+1.1750 LB)

Effect on Balance +13.696 KGM (+99.063 LB.FT )

**CONF 002

The weight and balance estimates given in this Service Bulletin are based on the

Manufacturer’s Empty Weight (MEW) and do not include operator item’s. For the definition of

MEW and operator’s items refer to Weight and Balance Manual (WBM) Chapter 1-00-07.

Manufacturers Empty Weight +0.585 KG (+1.2896 LB)

Effect on Balance +14.198 KGM (+102.694 LB.FT )

**CONF ALL

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

**CONF 001

Aircraft Maintenance Manual (AMM) 06-41-53 24-00-00 24-41-00

25-54-10 25-55-10 52-30-00

52-33-18

All Operators Telex (AOT) 53-07

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-33-11 20-33-33 20-55-00

Non Destructive Test Manual (NTM) 51-10-01

Service Bulletin (SB) A310-53-2094

A310-53-2095

A310-53-2134

Standards Manual (SM)

Structural Repair Manual (SRM) 51-27-11 51-40-12 51-40-30

51-40-32 51-40-40 51-40-41

51-76-00

Weight and Balance Manual (WBM) Weight and Balance Manual

(WBM) Chapter 1-00-07

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**CONF 002

Aircraft Maintenance Manual (AMM) 06-41-53 24-00-00 24-41-00

25-54-10 25-55-10 52-30-00

52-33-18

All Operators Telex (AOT) 53-07

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-33-11 20-33-33 20-55-00

Non Destructive Test Manual (NTM) 51-10-01

Service Bulletin (SB) A310-53-2094

A310-53-2095

A310-53-2134

Standards Manual (SM)

Structural Repair Manual (SRM) 51-27-11 51-40-12 51-40-30

51-40-32 51-40-40 51-40-41

51-76-00

Weight and Balance Manual (WBM) Weight and Balance Manual

(WBM) Chapter 1-00-07

**CONF ALL

K. PUBLICATION AFFECTED

**CONF 001

Structural Repair Manual (SRM) 53-13-15 53-17-15

**CONF 002

Structural Repair Manual (SRM) 53-13-15 53-17-15

**CONF ALL

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

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2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

Kit 532133D01R02

Kit 532133D02R01

Kit 532133D03R01

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:

AIRBUS Material, Logistics and Suppliers

Weg beim Jaeger 150

D-22335 Hamburg

Germany

For ordering by internet:

http://spares.airbus.com

For SB Kits by fax: +49 40 50 76 25 90

For Spares by fax : +49 40 50 76 40 12

Component COMPD01 Parts to be procured from:

B/E Aerospace Consumables Management

GmbH

Nordportbogen 6

D-22848 Norderstedt

Germany

Tel: +49 40 82 22 85 0

Fax: +49 40 82 22 85 31 00 5

(2) Price and Availability

Kit 532133D01R02

Cost 1,140.00 USD

Availability 120 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require Kits before this time, please include a retrofit planning schedule with

your order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin.

Kit 532133D02R01

Cost 1,030.00 USD

Availability 120 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require Kits before this time, please include a retrofit planning schedule with

your order so that we can try to comply with your requirements.

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The sales terms (costs and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin.

Kit 532133D03R01

Cost 1,090.00 USD

Availability 120 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require Kits before this time, please include a retrofit planning schedule with

your order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin.

B. INDUSTRY SUPPORT INFORMATION

AIRBUS will provide a 15% reduction to the applicable sales prices given in the paragraph

’Price and Availability’ for orders placed before 31st of December 2015.

C. LIST OF COMPONENTS

Kit 532133D01R02

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

NOTES

4 ASNA2528-3 32 NUT

5 ASNA2528-3A 14 NUT

6 EN6115K3-3 16 BOLT

10 EN6115K3X5 16 BOLT

11 EN6115K3A5 10 BOLT

12 EN6115K3AX5 4 BOLT

17 ABS0337-01A 1 RECEPTCL

22 A5327429220200 1 PLATE

23 A5327429220800 1 PLATE

24 F5347726220000 1 ANGLE

25 EN6069D4-05 2 RIVET

26 EN6081D6-09 4 RIVET

27 EN6069AD3-06 2 RIVET

34 DAN5-6-6X 7 PIN

35 DAN11-6X 7 COLLAR

36 DAN5-6-6Y 7 PIN

37 DAN11-6Y 7 COLLAR

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.

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Kit 532133D02R01

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

NOTES

1 A5378103420600 1 RNFRCMNT

2 A5378103421400 1 RNFRCMNT

4 ASNA2528-3 32 NUT

5 ASNA2528-3A 14 NUT

6 EN6115K3-3 16 BOLT

9 EN6115K3X4 2 BOLT

10 EN6115K3X5 14 BOLT

12 EN6115K3AX5 2 BOLT

13 EN6115K3AX6 2 BOLT

14 EN6115K3A6 10 BOLT

15 LN9198-3215CF 4 RIVET

16 DIN65399-3215CF 3 RIVET

34 DAN5-6-6X 7 PIN

35 DAN11-6X 7 COLLAR

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.

Kit 532133D03R01

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

NOTES

4 ASNA2528-3 36 NUT

5 ASNA2528-3A 14 NUT

6 EN6115K3-3 4 BOLT

7 EN6115K3-4 16 BOLT

9 EN6115K3X4 2 BOLT

10 EN6115K3X5 2 BOLT

13 EN6115K3AX6 4 BOLT

14 EN6115K3A6 10 BOLT

15 LN9198-3215CF 4 RIVET

16 DIN65399-3215CF 3 RIVET

20 A5378103420800 1 RNFRCMNT

21 A5378103421600 1 RNFRCMNT

30 EN6115K3X6 12 BOLT

34 DAN5-6-6X 7 PIN

35 DAN11-6X 7 COLLAR

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.

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D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibiting Brush

Consistency

09-013 As required

Cleaning Solvent 11-016 As required

Solvent General Purpose 11-026 As required

Anti-Corrosion Primer

(polyurethane)

16-001 As required

Polyurethane Topcoat Grey (for

Internal Applic.)

16-002 As required

Wash Primer 16-020 As required

(2) Components

Component COMPD01

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

NOTES

50 NAS1801-3-26 1 SCREW

51 NAS1149D0332K 2 WASHER

52 NSA5527-03-01D 1 SPACER

53 NSA5527-03-08D 1 SPACER

54 MS21042-3 1 NUT

55 MS21919WCH3 1 CLAMP

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.

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

(1) Tooling - Price and Availability

None

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(2) Tools

Standard tool TOOLD01

ITEM TOOL N ̊ TOOL NAME QTY SEE

NOTES

98A52307523000 Support Struts - FWD and AFT

Cargo Compartment Doors

2 (1)

NOTE (1): The safety equipments are operator supplied.

(3) Special Tools

Fatigue Technology Incorporated (FTI) has allocated the following tool kit number for

cold working, refer FTI Tooling List No. FTI-A310-53-2133-1.

NOTE: For the definition of capital, durable and expandable tools, refer to SIL

51-012.

- Capital Tool Kit No : FTI-FT20-LB20-CAP

. The capital tools provided in this kit are not specific to this Service Bulletin and

are normally already available in operator’s stock as a long term investment or

can be loaned from FTI.

- Durable Tool Kit No : DK-A310532133-1

. The capital tools provided in this kit are not specific to this Service Bulletin and

are normally already available in operator’s stock as a long term investment or

can be loaned from FTI.

- Expendable Tool Kit No : EK-A310532133-1

. The capital tools provided in this kit are not specific to this Service Bulletin and

are normally already available in operator’s stock as a long term investment or

can be loaned from FTI.

Operators interested in obtaining the FTI tool kit should contact:

Fatigue Technology Inc.

401 ANDOVER PARK EAST

SEATTLE, WA 98188-2868

USA

E-mail: sales@fatiguetech.com

E-mail: aog@fatiguetech.com

Phone: (1) 206 246 2010

Fax: (1) 206 244 9886

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3. ACCOMPLISHMENT INSTRUCTIONS

Task 532133-831-848-001 - MODIFICATION

WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS

INCLUDED IN THE REFERENCED PROCEDURES

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL

WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND

MECHANICALLY SERVICEABLE).

WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS,

ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA

AS CLEAN AS POSSIBLE. TO DO THIS :

- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS

NECESSARY ON ELECTRICAL 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.

Task Associated Data

**CONF 001

Zone

130 150

Manpower

TOTAL MANHOURS 34.00

ELAPSED TIME (HOURS) 22.00

**CONF 002

Zone

130 150

Manpower

TOTAL MANHOURS 34.00

ELAPSED TIME (HOURS) 22.00

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**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 532133-910-201-001 - Standard Practices

Work Zones and Access Panels

Zone Access/Work location

130

150

Manpower Resources

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibiting Brush

Consistency

09-013 As required

Cleaning Solvent 11-016 As required

Anti-Corrosion Primer

(polyurethane)

16-001 As required

Polyurethane Topcoat Grey

(for Internal Applic.)

16-002 As required

Wash Primer 16-020 As required

References

Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-40-12

51-40-30

51-40-32

51-40-40

51-76-00

(a) If the length of any fastener specified in this Service Bulletin does not meet

installation standards given in SRM Chapter 51, then a fastener of the same

specification, or an approved substitute, with a length which meets the installation

standards given in SRM Chapter 51 may be used. In addition, washers may be

installed for fastener grip length in accordance with SRM Chapter 51.

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

the Consumable Materials List (CML)).

(c) For the location of access panels (Refer to AMM 06-41-53, Page Block 001).

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(d) Remove the old sealant with non-metallic scrapers and a stiff brush.

(e) Drill and deburr the rivet holes (Refer to SRM 51-40-40).

(f) After drilling and cutting, apply

Anti-Corrosion

Primer

(polyurethane)

16-001 As required

and

Polyurethane

Topcoat Grey (for

Internal Applic.)

16-002 As required

and

Wash Primer 16-020 As required

and (Refer to SRM 51-40-12) on the affected areas.

(g) Clean the reworked surfaces and the surfaces to be sealed with

Cleaning Solvent 11-016 As required

(h) Apply

Corrosion Inhibiting

Brush Consistency

09-013 As required

on all mating surfaces.

(i) Install rivets and pins on all mating surfaces with

Corrosion Inhibiting

Brush Consistency

09-013 As required

(j) For alternative and substitute fasteners (Refer to SRM 51-40-30).

(k) For the procedure to use sealant (Refer to SRM 51-76-00).

(l) Apply a sealant bead with :

Corrosion Inhibiting

Brush Consistency

09-013 As required

(m) Install only Hi-Lok fasteners with interference fit in cold expanded holes.

(2) Subtask 532133-839-201-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

**CONF 002

(1) Subtask 532133-910-201-001 - Standard Practices

Work Zones and Access Panels

Zone Access/Work location

130

150

Manpower Resources

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibiting Brush

Consistency

09-013 As required

Cleaning Solvent 11-016 As required

Anti-Corrosion Primer

(polyurethane)

16-001 As required

Polyurethane Topcoat Grey

(for Internal Applic.)

16-002 As required

Wash Primer 16-020 As required

References

Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-40-12

51-40-30

51-40-32

51-40-40

51-76-00

(a) If the length of any fastener specified in this Service Bulletin does not meet

installation standards given in SRM Chapter 51, then a fastener of the same

specification, or an approved substitute, with a length which meets the installation

standards given in SRM Chapter 51 may be used. In addition, washers may be

installed for fastener grip length in accordance with SRM Chapter 51.

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

the Consumable Materials List (CML)).

(c) For the location of access panels (Refer to AMM 06-41-53, Page Block 001).

(d) Remove the old sealant with non-metallic scrapers and a stiff brush.

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(e) Drill and deburr the rivet holes (Refer to SRM 51-40-40).

(f) After drilling and cutting, apply

Anti-Corrosion

Primer

(polyurethane)

16-001 As required

and

Polyurethane

Topcoat Grey (for

Internal Applic.)

16-002 As required

and

Wash Primer 16-020 As required

and (Refer to SRM 51-40-12) on the affected areas.

(g) Clean the reworked surfaces and the surfaces to be sealed with

Cleaning Solvent 11-016 As required

(h) Apply

Corrosion Inhibiting

Brush Consistency

09-013 As required

on all mating surfaces.

(i) Install rivets and pins on all mating surfaces with

Corrosion Inhibiting

Brush Consistency

09-013 As required

(j) For alternative and substitute fasteners (Refer to SRM 51-40-30).

(k) For the procedure to use sealant (Refer to SRM 51-76-00).

(l) Apply a sealant bead with :

Corrosion Inhibiting

Brush Consistency

09-013 As required

(m) Install only Hi-Lok fasteners with interference fit in cold expanded holes.

(2) Subtask 532133-839-201-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

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**CONF ALL

B. PREPARATION

**CONF 001

(1) Subtask 532133-941-201-001 - Preparation

Work Zones and Access Panels

Zone Access/Work location

130

150

Manpower Resources

Skills NON SPECIFIC

Material necessary to do the job

Standard tool TOOLD01

ITEM TOOL N ̊ TOOL NAME QTY SEE

NOTES

98A52307523000 Support Struts - FWD and

AFT Cargo Compartment

Doors

2 (1)

NOTE (1): The safety equipments are operator supplied.

References

Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001

24-00-00, Page Block 301

24-41-00, Page Block 301

25-54-10, Page Block 201

25-54-10, Page Block 201

25-55-10, Page Block 201

52-30-00, Page Block 301

52-33-18, 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.

(c) De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page Block

301).

(d) Open the FWD cargo-compartment door 811 (Refer to AMM 52-30-00, Page Block

301).

(e) Open the AFT cargo-compartment door 812 (Refer to AMM 52-30-00, Page Block

301).

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(f) Disconnect the door actuator from the FWD and AFT cargo-compartment doors and

install :

98A52307523000 Support Struts -

FWD and AFT

Cargo

Compartment Doors

2

Refer to AMM 52-30-00, Page Block 301.

NOTE: Do not use the actuator safety lock(s).

(g) Open, safety and tag these circuit breaker(s) :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

128VU HYDRAULIC/ACCU PRESS

CTL AND CARGO PUMP

7GX 803/C11

101VU ELEC HYD PUMP 23GX ALT2

NOTE: The location of the circuit breaker(s) can be different from the

location given in the table.

(h) Remove and retain the FWD cargo-compartment ceiling panels as necessary

(Refer to AMM 25-54-10, Page Block 201 and AMM 06-41-53, Page Block 001).

(i) Remove the door actuator lining between FR22 and FR23.

(j) Remove the FWD cargo-compartment actuator from the actuator support beam

(Refer to AMM 52-33-18, Page Block 401).

(k) Remove and retain the AFT cargo-compartment ceiling panels as necessary (Refer

to AMM 25-55-10, Page Block 201 and AMM 06-41-53, Page Block 001).

(l) Remove the door actuator lining between FR61 and FR62 for access.

(m) Remove the AFT cargo-compartment actuator from the actuator support beam

(Refer to AMM 52-33-18, Page Block 401).

**CONF 002

(1) Subtask 532133-941-201-001 - Preparation

Work Zones and Access Panels

Zone Access/Work location

130

150

Manpower Resources

Skills NON SPECIFIC

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Material necessary to do the job

Standard tool TOOLD01

ITEM TOOL N ̊ TOOL NAME QTY SEE

NOTES

98A52307523000 Support Struts - FWD and

AFT Cargo Compartment

Doors

2 (1)

NOTE (1): The safety equipments are operator supplied.

References

Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001

24-00-00, Page Block 301

24-41-00, Page Block 301

25-54-10, Page Block 201

25-54-10, Page Block 201

25-55-10, Page Block 201

52-30-00, Page Block 301

52-33-18, 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.

(c) De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page Block

301).

(d) Open the FWD cargo-compartment door 811 (Refer to AMM 52-30-00, Page Block

301).

(e) Open the AFT cargo-compartment door 812 (Refer to AMM 52-30-00, Page Block

301).

(f) Disconnect the door actuator from the FWD and AFT cargo-compartment doors and

install :

98A52307523000 Support Struts -

FWD and AFT

Cargo

Compartment Doors

2

Refer to AMM 52-30-00, Page Block 301.

NOTE: Do not use the actuator safety lock(s).

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(g) Open, safety and tag these circuit breaker(s) :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

128VU HYDRAULIC/ACCU PRESS

CTL AND CARGO PUMP

7GX 803/C11

101VU ELEC HYD PUMP 23GX ALT2

NOTE: The location of the circuit breaker(s) can be different from the

location given in the table.

(h) Remove and retain the FWD cargo-compartment ceiling panels as necessary

(Refer to AMM 25-54-10, Page Block 201 and AMM 06-41-53, Page Block 001).

(i) Remove the door actuator lining between FR22 and FR23.

(j) Remove the FWD cargo-compartment actuator from the actuator support beam

(Refer to AMM 52-33-18, Page Block 401).

(k) Remove and retain the AFT cargo-compartment ceiling panels as necessary (Refer

to AMM 25-55-10, Page Block 201 and AMM 06-41-53, Page Block 001).

(l) Remove the door actuator lining between FR61 and FR62 for access.

(m) Remove the AFT cargo-compartment actuator from the actuator support beam

(Refer to AMM 52-33-18, Page Block 401).

**CONF ALL

C. PROCEDURE

NOTE: It is not necessary to accomplish the Inspection Service Bulletin No.

A310-53-2134 before doing this Service Bulletin. This Service Bulletin can be

accomplished directly as given in the accomplishment instruction.

NOTE: To reach the mod advantages, this Service Bulletin is to be accomplished, if:

- Service Bulletin No. A310-53-2094 has been previously accomplished,

- none repair has been performed in the affected areas in accordance

with SRM, All Operators Telex 53-07, Inspection Service Bulletin No.

A310-53-2095 or Repair Approval Sheet (RAS).

In case of existing repairs, the operators are requested to contact Airbus

Repair Support before accomplishment of this Service Bulletin, for further

instructions.

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 25

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SERVICE BULLETIN

**CONF 001

(1) Subtask 532133-831-201-001 - Remove the existing fasteners from the crossbeam

at FR22 and FR23.

Work Zones and Access Panels

Zone Access/Work location

130

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

Material necessary to do the job

Kit 532133D02R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

16 DIN65399-3215CF 3 RIVET

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Cleaning Solvent 11-016 As required

Solvent General Purpose 11-026 As required

References

Consumable Material List (CML)

Fig. A-GBAAA

Removal of the Existing Fasteners from

the Crossbeam FR22 and FR23

Sheet 01

Sheet 02

Sheet 03

Sheet 04

WARNING: BEFORE YOU REMOVE ANY RIVETS FROM THE CROSSBEAM FR22

OR FR23, ENSURE THAT THE FORWARD DOOR ACTUATOR IS

DISCONNECTED FROM THE ACTUATOR BEAM.

(a) Remove fasteners from the crossbeam at FR22.

1 Remove the existing fasteners :

Fig. A-GBAAA Sheet 02, Detail B, and Fig. A-GBAAA Sheet 03, Detail D

2 Clean the fastener holes and the adjacent area with :

Cleaning Solvent 11-016 As required

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

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SERVICE BULLETIN

(b) If pins are installed in the actuator beam at FR22, remove them.

1 Remove the existing pins :

Refer to Fig. A-GBAAA Sheet 02, Detail B, and Fig. A-GBAAA Sheet 04,

Detail F

2 Clean the pin holes and the adjacent area with :

Solvent General

Purpose

11-026 As required

(c) Remove the brackets and fasteners from the crossbeam at FR23.

1 Remove the existing fasteners and the brackets :

Fig. A-GBAAA Sheet 02, Detail C, and Fig. A-GBAAA Sheet 03, Detail E

2 Bracket A9249161420100 Item (3) Retain

a Close the three holes with :

3 Rivet DIN65399-3215CF Item 16

NOTE: An inspection of these holes is not necessary.

2 Clean the fastener holes and the adjacent area with :

Cleaning Solvent 11-016 As required

(2) Subtask 532133-831-202-001 - Rotating Probe Inspection at the crossbeam FR22

and FR23.

Work Zones and Access Panels

Zone Access/Work location

130

Manpower Resources

Manhours 4.00

Minimum number of person 1

Subtask elapsed time 4.00

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01 PART 6, Procedure A

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 27

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@A310

SERVICE BULLETIN

References

Fig. A-GBCAA

Installation of the Reinforcement at the

Crossbeam FR22 and FR23

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

(a) Rotating Probe Inspection at the crossbeam at FR22.

1 Do a rotating probe inspection of the fastener holes at FR22 (Refer to NTM

51-10-01 PART 6, Procedure A).

Refer to Fig. A-GBCAA Sheet 03, Detail D

a If no crack(s) are found :

<1> - Refer to para. (3)(a).

b If crack(s) are found :

<1> Contact AIRBUS for further instructions.

(b) Rotating Probe Inspection at the crossbeam at FR23

1 Do a rotating probe inspection of the fastener holes at FR23 (Refer to NTM

51-10-01 PART 6, Procedure A).

Refer to Fig. A-GBCAA Sheet 04, Detail F

a If no crack(s) are found :

<1> - Refer to para. (3)(c).

b If crack(s) are found :

<1> Contact AIRBUS for further instructions.

(3) Subtask 532133-831-204-001 - Install the reinforcement and brackets at the

crossbeam at FR22 and FR23.

Work Zones and Access Panels

Zone Access/Work location

130

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 28

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@A310

SERVICE BULLETIN

Material necessary to do the job

Kit 532133D02R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 A5378103420600 1 RNFRCMNT

2 A5378103421400 1 RNFRCMNT

4 ASNA2528-3 32 NUT

5 ASNA2528-3A 14 NUT

6 EN6115K3-3 16 BOLT

9 EN6115K3X4 2 BOLT

10 EN6115K3X5 14 BOLT

12 EN6115K3AX5 2 BOLT

13 EN6115K3AX6 2 BOLT

14 EN6115K3A6 10 BOLT

15 LN9198-3215CF 4 RIVET

34 DAN5-6-6X 7 PIN

35 DAN11-6X 7 COLLAR

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

References

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-33-11

20-33-33

Structural Repair Manual (SRM) 51-27-11

51-40-41

51-76-00

Fig. A-GBCAA

Installation of the Reinforcement at the

Crossbeam FR22 and FR23

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

(a) Install the reinforcement at the crossbeam at FR22.

Refer to Fig. A-GBCAA Sheet 02, Detail B, Fig. A-GBCAA Sheet 03, Detail E, Fig.

A-GBCAA Sheet 05, Fig. A-GBCAA Sheet 07, Detail J and K and Fig. A-GBCAA

Sheet 08, Detail L and M

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 29

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@A310

SERVICE BULLETIN

1 If the reinforcement, Item 1, has been delivered with the old contour, rework

the reinforcement to the new contour to avoid any interference with a plastic

cable support.

Refer to SRM 51-27-11

Refer to Fig. A-GBCAA Sheet 07, Details J and K

2 If the reinforcement, Item 1, has been delivered with the old contour and if it

has any interference with a plastic cable support on the inboard side, rework

the reinforcement to the new contour.

Refer to SRM 51-27-11

Refer to Fig. A-GBCAA Sheet 08, Details L and M

3 At FR22 install temporarily :

1 Reinforcement A5378103420600 Item 1

4 If no ’cold expansion’ drill the fastener holes and open to final dimension.

5 If ’cold expansion’ transfer drill the fastener holes and open to the specific

starting hole diameter.

6 Cold expand the specified fastener holes where no cracks were found.

Refer to SRM 51-40-41

Refer to FTI Tooling List No. FTI-A310-53-2133-1

Refer to Fig. A-GBCAA Sheet 03, Detail E, and Fig. A-GBCAA Sheet 05

7 Ream the specified holes on the reinforcement and structure with the correct

gage finish reamer.

Refer to Fig. A-GBCAA Sheet 03, Detail E, and Fig. A-GBCAA Sheet 05

8 Remove the temporarily installed item 1.

9 Clean the reamed fastener holes with :

Solvent General

Purpose

11-026 As required

10 Install the reinforcement, Item 1, with :

Refer to SRM 51-76-00

22 Nut ASNA2528-3 Item 4

2 Nut ASNA2528-3A Item 5

6 Bolt EN6115K3-3 Item 6

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 30

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SERVICE BULLETIN

2 Bolt EN6115K3X4 Item 9

14 Bolt EN6115K3X5 Item 10

2 Bolt EN6115K3AX5 Item 12

(b) If nominal size pins have been removed from the actuator beam at FR22, install

new 1st oversize pins.

Refer to Fig. A-GBCAA Sheet 02, Detail B, Fig. A-GBCAA Sheet 05 and Fig. AGBCAA Sheet 06, Detail H

1 Install :

7 Pin DAN5-6-6X Item 34

7 Collar DAN11-6X Item 35

(c) Install the reinforcement and brackets at the crossbeam at FR23.

Refer to Fig. A-GBCAA Sheet 02, Detail C, Fig. A-GBCAA Sheet 04, Detail G, and

Fig. A-GBCAA Sheet 05

1 At FR23 install temporarily :

1 Reinforcement A5378103421400 Item 2

2 If no ’cold expansion’ drill the fastener holes and open to final dimension.

3 If ’cold expansion’ transfer drill the fastener holes and open to the specific

starting hole diameter.

4 Cold expand the specified fastener holes where no cracks were found.

Refer to SRM 51-40-41

Refer to FTI Tooling List No. FTI-A310-53-2133-1

Refer to Fig. A-GBCAA Sheet 04, Detail G, and Fig. A-GBCAA Sheet 05

5 Ream the specified holes on the reinforcement and structure with the correct

gage finish reamer.

Refer to Fig. A-GBCAA Sheet 04, Detail G, and Fig. A-GBCAA Sheet 05

6 Remove the temporarily installed item 2.

7 Clean the reamed fastener holes with :

Solvent General

Purpose

11-026 As required

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 31

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@A310

SERVICE BULLETIN

8 Install the reinforcement, Item 2, with :

10 Nut ASNA2528-3 Item 4

12 Nut ASNA2528-3A Item 5

10 Bolt EN6115K3-3 Item 6

2 Bolt EN6115K3AX6 Item 13

10 Bolt EN6115K3A6 Item 14

9 At FR23 put in position and install :

2 Bracket A9249161420100 Item (3) Retained at

removal

with :

4 Rivet LN9198-3215CF Item 15

(d) Perform minor amendment of screws, spacers and split conduits (Refer to ESPM

20-33-11 and ESPM 20-33-33).

(4) Subtask 532133-831-206-001 - Remove the brackets and fasteners from the

crossbeam FR61 and FR62.

Work Zones and Access Panels

Zone Access/Work location

150

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

Material necessary to do the job

Kit 532133D01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

25 EN6069D4-05 2 RIVET

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

References

Consumable Material List (CML)

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 32

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@A310

SERVICE BULLETIN

References

Fig. A-GBJAA

Removal of the Existing Fasteners from

the Crossbeam FR61 and FR62

Sheet 01

Sheet 02

Sheet 03

Sheet 04

WARNING: BEFORE YOU REMOVE ANY RIVETS FROM THE CROSSBEAM

FR61 OR FR62, ENSURE THAT THE AFTER DOOR ACTUATOR IS

DISCONNECTED FROM THE ACTUATOR BEAM.

(a) Remove the existing fasteners from the crossbeam FR61.

1 Remove the existing fasteners :

Refer to Fig. A-GBJAA Sheet 02, Detail B, and Fig. A-GBJAA Sheet 03, Detail

D

2 Clean the fastener holes and the adjacent area with :

Solvent General

Purpose

11-026 As required

(b) If pins are installed in the actuator beam at FR61, remove them.

1 Remove the existing pins :

Refer to Fig. A-GBJAA Sheet 02, Detail B, and Fig. A-GBJAA Sheet 04, Detail

F

2 Clean the pin holes and the adjacent area with :

Solvent General

Purpose

11-026 As required

(c) Remove the brackets and the fasteners from the crossbeam FR62.

1 Remove the brackets and the fasteners :

Refer to Fig. A-GBJAA Sheet 02, Detail C, and Fig. A-GBJAA Sheet 03, Detail

E

1 Receptacle DAN367-01 Item (17) Discard

1 Bracket A9249193420000 Item (18) Discard

and close the two holes with :

2 Rivet EN6069D4-05 Item 25

2 Clean the fastener holes and the adjacent area with :

Solvent General

Purpose

11-026 As required

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 33

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@A310

SERVICE BULLETIN

(5) Subtask 532133-832-202-001 - Rotating Probe Inspection at the crossbeam FR61

and FR62.

Work Zones and Access Panels

Zone Access/Work location

150

Manpower Resources

Manhours 4.00

Minimum number of person 1

Subtask elapsed time 4.00

Skills AIRFRAME

References

Consumable Material List (CML)

Non Destructive Test Manual (NTM) 51-10-01 PART 6, Procedure A

Fig. A-GBLAA

Installation of the Reinforcement at the

Crossbeam FR61 and FR62

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Rotating Probe Inspection at the crossbeam at FR61.

1 Do a rotating probe inspection of the fastener holes at FR61 (Refer to NTM

51-10-01 PART 6, Procedure A).

Refer to Fig. A-GBLAA Sheet 03, Detail D

a If no crack(s) are found :

<1> - Refer to para. (6)(a).

b If crack(s) are found :

<1> Contact AIRBUS for further instructions.

(b) Rotating Probe Inspection at the crossbeam at FR62.

1 Do a rotating probe inspection of the fastener holes at FR62 (Refer to NTM

51-10-01 PART 6, Procedure A).

Refer to Fig. A-GBLAA Sheet 04, Detail F

a If no crack(s) are found :

<1> - Refer to para. (6)(c).

b If crack(s) are found :

<1> Contact AIRBUS for further instructions.

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 34

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@A310

SERVICE BULLETIN

(6) Subtask 532133-831-208-001 - Install the reinforcement and bracket at the

crossbeam at FR61 and FR62.

Work Zones and Access Panels

Zone Access/Work location

150

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

Material necessary to do the job

Kit 532133D01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

4 ASNA2528-3 32 NUT

5 ASNA2528-3A 14 NUT

6 EN6115K3-3 16 BOLT

10 EN6115K3X5 16 BOLT

11 EN6115K3A5 10 BOLT

12 EN6115K3AX5 4 BOLT

17 ABS0337-01A 1 RECEPTCL

22 A5327429220200 1 PLATE

23 A5327429220800 1 PLATE

24 F5347726220000 1 ANGLE

26 EN6081D6-09 4 RIVET

27 EN6069AD3-06 2 RIVET

34 DAN5-6-6X 7 PIN

35 DAN11-6X 7 COLLAR

36 DAN5-6-6Y 7 PIN

37 DAN11-6Y 7 COLLAR

Component COMPD01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

50 NAS1801-3-26 1 SCREW

51 NAS1149D0332K 2 WASHER

52 NSA5527-03-01D 1 SPACER

53 NSA5527-03-08D 1 SPACER

54 MS21042-3 1 NUT

55 MS21919WCH3 1 CLAMP

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 35

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@A310

SERVICE BULLETIN

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

References

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-33-11

20-33-33

Structural Repair Manual (SRM) 51-40-41

51-76-00

Fig. A-GBLAA

Installation of the Reinforcement at the

Crossbeam FR61 and FR62

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Install the reinforcement at the crossbeam at FR61.

Refer to Fig. A-GBLAA Sheet 02, Detail B, Fig. A-GBLAA Sheet 03, Detail E, and

Fig. A-GBLAA Sheet 05

1 At FR61 install temporarily :

1 Reinforcement A5327429220200 Item 22

2 If no ’cold expansion’ drill the fastener holes and open to final dimension.

3 If ’cold expansion’ transfer drill the fastener holes and open to the specific

starting hole diameter.

4 Cold expand the specified fastener holes where no cracks were found.

Refer to SRM 51-40-41

Refer to FTI Tooling List No. FTI-A310-53-2133-1

Refer to Fig. A-GBLAA Sheet 03, Detail E, and Fig. A-GBLAA Sheet 05

5 Ream the specified holes on the reinforcement and structure with the correct

gage finish reamer.

Refer to Fig. A-GBLAA Sheet 03, Detail E, and Fig. A-GBLAA Sheet 05

6 Remove the temporarily installed Item 22.

7 Clean the reamed fastener holes with :

Solvent General

Purpose

11-026 As required

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 36

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@A310

SERVICE BULLETIN

8 Install the reinforcement, Item 22, with :

Refer to SRM 51-76-00

24 Nut ASNA2528-3 Item 4

2 Nut ASNA2528-3A Item 5

8 Bolt EN6115K3-3 Item 6

16 Bolt EN6115K3X5 Item 10

2 Bolt EN6115K3AX5 Item 12

(b) If pins have been removed from the actuator beam at FR61, install new pins.

Refer to Fig. A-GBLAA Sheet 02, Detail B, Fig. A-GBLAA Sheet 05 and Fig. AGBLAA Sheet 06, Detail H

1 If nominal size pins have been removed from the actuator beam at FR61,

install new 1st oversize pins.

a Install :

7 Pin DAN5-6-6X Item 34

7 Collar DAN11-6X Item 35

2 If 1st oversize pins have been removed from the actuator beam at FR61,

install new 2nd oversize pins.

a Install :

7 Pin DAN5-6-6Y Item 36

7 Collar DAN11-6Y Item 37

(c) Install the reinforcement and bracket at the crossbeam at FR62.

Refer to Fig. A-GBLAA Sheet 02, Detail C, Fig. A-GBLAA Sheet 04, Detail G, and

Fig. A-GBLAA Sheet 05

1 At FR62 hold in position temporarily :

1 Bracket F5347726220000 Item 24

2 If a plastic cable support interferes with bracket, Item 24, replace the plastic

cable support with the following :

Refer to ESPM 20-33-11

1 Screw NAS1801-3-26 Item 50

2 Washer NAS1149D0332K Item 51

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 37

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@A310

SERVICE BULLETIN

1 Spacer NSA5527-03-01D Item 52

1 Spacer NSA5527-03-08D Item 53

1 Nut MS21042-3 Item 54

1 Clamp MS21919WCH3 Item 55

NOTE: The screw, Item 50, has to be installed from the AFT of the

FR62 and the clamp, Item 55, has to be orientated at 12

o’clock position (Up).

3 At FR62 install temporarily :

1 Reinforcement A5327429220800 Item 23

4 If no ’cold expansion’ drill the fastener holes and open to final dimension.

5 If ’cold expansion’ transfer drill the fastener holes and open to the specific

starting hole diameter.

6 Cold expand the specified fastener holes where no cracks were found.

Refer to SRM 51-40-41

Refer to FTI Tooling List No. FTI-A310-53-2133-1

Refer to Fig. A-GBLAA Sheet 04, Detail G, and Fig. A-GBLAA Sheet 05

7 Ream the specified holes on the reinforcement and structure with the correct

gage finish reamer.

Refer to Fig. A-GBLAA Sheet 04, Detail G, and Fig. A-GBLAA Sheet 05

8 Remove the temporarily installed Item 23.

9 Clean the reamed fastener holes with :

Solvent General

Purpose

11-026 As required

10 Install the reinforcement, Item 23 with :

Refer to SRM 51-76-00

Refer to Fig. A-GBLAA Sheet 04, Detail G

8 Nut ASNA2528-3 Item 4

12 Nut ASNA2528-3A Item 5

8 Bolt EN6115K3-3 Item 6

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 38

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@A310

SERVICE BULLETIN

10 Bolt EN6115K3A5 Item 11

2 Bolt EN6115K3AX5 Item 12

11 At FR62 install :

Refer to Fig. A-GBLAA Sheet 04, Detail G and Section A-A

1 Bracket F5347726220000 Item 24

1 Receptacle ABS0337-01A Item 17

with :

4 Rivet EN6081D6-09 Item 26

2 Rivet EN6069AD3-06 Item 27

(d) Perform minor amendment of screws, spacers and split conduits (Refer to ESPM

20-33-11 and ESPM 20-33-33).

**CONF 002

(1) Subtask 532133-831-201-002 - Remove the existing fasteners from the crossbeam

at FR22 and FR23.

Work Zones and Access Panels

Zone Access/Work location

130

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

Material necessary to do the job

Kit 532133D03R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

16 DIN65399-3215CF 3 RIVET

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Cleaning Solvent 11-016 As required

Solvent General Purpose 11-026 As required

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 39

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@A310

SERVICE BULLETIN

References

Consumable Material List (CML)

Fig. A-GBEAA

Removal of the Existing Fasteners from

the Crossbeam FR22 and FR23

Sheet 01

Sheet 02

Sheet 03

Sheet 04

WARNING: BEFORE YOU REMOVE ANY RIVETS FROM THE CROSSBEAM FR22

OR FR23, ENSURE THAT THE FORWARD DOOR ACTUATOR IS

DISCONNECTED FROM THE ACTUATOR BEAM.

(a) Remove the existing fasteners from the crossbeam at FR22.

1 Remove the existing fasteners :

Refer to Fig. A-GBEAA Sheet 02, Detail B, and Fig. A-GBEAA Sheet 03,

Detail D

2 Clean the fastener holes and the adjacent area with :

Cleaning Solvent 11-016 As required

(b) If pins are installed in the actuator beam at FR22, remove them.

1 Remove the existing pins :

Refer to Fig. A-GBEAA Sheet 02, Detail B, and Fig. A-GBEAA Sheet 04,

Detail F

2 Clean the pin holes and the adjacent area with :

Solvent General

Purpose

11-026 As required

(c) Remove fasteners from the crossbeam at FR23.

1 Remove the existing fasteners and the brackets :

Refer to Fig. A-GBEAA Sheet 02, Detail C, and Fig. A-GBEAA Sheet 03,

Detail E

2 Bracket A9249161420100 Item (3) Retain

a Close the three holes with :

3 Rivet DIN65399-3215CF Item 16

NOTE: An inspection of these holes is not necessary.

2 Clean the fastener holes and the adjacent area with :

Cleaning Solvent 11-016 As required

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 40

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@A310

SERVICE BULLETIN

(2) Subtask 532133-831-202-002 - Rotating Probe Inspection at the crossbeam at FR22

and FR23.

Work Zones and Access Panels

Zone Access/Work location

130

Manpower Resources

Manhours 4.00

Minimum number of person 1

Subtask elapsed time 4.00

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01 PART 6, Procedure A

Fig. A-GBGAA

Installation of the Reinforcement at the

Crossbeam FR22 and FR23

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

(a) Rotating Probe Inspection at the crossbeam at FR22.

1 Do a rotating probe inspection of the fastener holes at FR22 (Refer to NTM

51-10-01 PART 6, Procedure A).

Refer to Fig. A-GBGAA Sheet 03, Detail D

a If no crack(s) are found :

<1> - Refer to para. (3)(a).

b If crack(s) are found :

<1> Contact AIRBUS for further instructions.

(b) Rotating Probe Inspection at the crossbeam at FR23

1 Do a rotating probe inspection of the fastener holes at FR23 (Refer to NTM

51-10-01 PART 6, Procedure A).

Refer to Fig. A-GBGAA Sheet 04, Detail F

a If no crack(s) are found :

<1> - Refer to para. (3)(c).

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b If crack(s) are found :

<1> Contact AIRBUS for further instructions.

(3) Subtask 532133-831-204-002 - Install the reinforcement and brackets at the

crossbeam at FR22 and FR23.

Work Zones and Access Panels

Zone Access/Work location

130

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Kit 532133D03R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

4 ASNA2528-3 36 NUT

5 ASNA2528-3A 14 NUT

6 EN6115K3-3 4 BOLT

7 EN6115K3-4 16 BOLT

9 EN6115K3X4 2 BOLT

10 EN6115K3X5 2 BOLT

13 EN6115K3AX6 4 BOLT

14 EN6115K3A6 10 BOLT

15 LN9198-3215CF 4 RIVET

20 A5378103420800 1 RNFRCMNT

21 A5378103421600 1 RNFRCMNT

30 EN6115K3X6 12 BOLT

34 DAN5-6-6X 7 PIN

35 DAN11-6X 7 COLLAR

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

References

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-33-11

20-33-33

Structural Repair Manual (SRM) 51-27-11

51-40-41

51-76-00

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References

Fig. A-GBGAA

Installation of the Reinforcement at the

Crossbeam FR22 and FR23

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

(a) Install the reinforcement at the crossbeam at FR22.

Refer to Fig. A-GBGAA Sheet 02, Detail B, Fig. A-GBGAA Sheet 03, Detail E, Fig.

A-GBGAA Sheet 05, Fig. A-GBGAA Sheet 07, Detail J and K and Fig. A-GBGAA

Sheet 08, Detail L and M

1 If the reinforcement, Item 20, has been delivered with the old contour, rework

the reinforcement to the new contour to avoid any interference with a plastic

cable support.

Refer to SRM 51-27-11

Refer to Fig. A-GBGAA Sheet 07, Details J and K

2 If the reinforcement, Item 20, has been delivered with the old contour and if it

has any interference with a plastic cable support on the inboard side, rework

the reinforcement to the new contour.

Refer to SRM 51-27-11

Refer to Fig. A-GBGAA Sheet 08, Details L and M

3 At FR22 install temporarily :

1 Reinforcement A5378103420800 Item 20

4 If no ’cold expansion’ drill the fastener holes and open to final dimension.

5 If ’cold expansion’ transfer drill the fastener holes and open to the specific

starting hole diameter.

6 Cold expand the specified fastener holes where no cracks were found.

Refer to SRM 51-40-41

Refer to FTI Tooling List No. FTI-A310-53-2133-1

Refer to Fig. A-GBGAA Sheet 03, Detail E, and Fig. A-GBGAA Sheet 05

7 Ream the specified holes on the reinforcement and structure with the correct

gage finish reamer.

Refer to Fig. A-GBGAA Sheet 03, Detail E, and Fig. A-GBGAA Sheet 05

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8 Remove the temporarily installed Item 20.

9 Clean the reamed fastener holes with :

Solvent General

Purpose

11-026 As required

10 Install the reinforcement, Item 20, with :

Refer to SRM 51-76-00

24 Nut ASNA2528-3 Item 4

2 Nut ASNA2528-3A Item 5

8 Bolt EN6115K3-4 Item 7

2 Bolt EN6115K3X4 Item 9

2 Bolt EN6115K3X5 Item 10

2 Bolt EN6115K3AX6 Item 13

12 Bolt EN6115K3X6 Item 30

(b) If nominal size pins have been removed from the actuator beam at FR22, install

new 1st oversize pins.

Refer to Fig. A-GBGAA Sheet 02, Detail B, Fig. A-GBGAA Sheet 05 and Fig. AGBGAA Sheet 06, Detail H

1 Install :

7 Pin DAN5-6-6X Item 34

7 Collar DAN11-6X Item 35

(c) Install the reinforcement and brackets at the crossbeam at FR23.

Refer to Fig. A-GBGAA Sheet 02, Detail C, Fig. A-GBGAA Sheet 04, Detail G, and

Fig. A-GBGAA Sheet 05

1 At FR23 install temporarily :

1 Reinforcement A5378103421600 Item 21

2 If no ’cold expansion’ drill the fastener holes and open to final dimension.

3 If ’cold expansion’ transfer drill the fastener holes and open to the specific

starting hole diameter.

4 Cold expand the specified fastener holes where no cracks were found.

Refer to SRM 51-40-41

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

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Refer to FTI Tooling List No. FTI-A310-53-2133-1

Refer to Fig. A-GBGAA Sheet 04, Detail G, and Fig. A-GBGAA Sheet 05

5 Ream the specified holes on the reinforcement and structure with the correct

gage finish reamer.

Refer to Fig. A-GBGAA Sheet 04, Detail G, and Fig. A-GBGAA Sheet 05

6 Remove the temporarily installed Item 21.

7 Clean the reamed fastener holes with :

Solvent General

Purpose

11-026 As required

8 Install the reinforcement, Item 21, with :

(Refer to SRM 51-76-00

12 Nut ASNA2528-3 Item 4

12 Nut ASNA2528-3A Item 5

4 Bolt EN6115K3-3 Item 6

8 Bolt EN6115K3-4 Item 7

2 Bolt EN6115K3AX6 Item 13

10 Bolt EN6115K3A6 Item 14

9 At FR23 put in position and install :

2 Bracket A9249161420100 Item (3) Retained at

removal

with :

4 Rivet LN9198-3215CF Item 15

(d) Perform minor amendment of screws, spacers and split conduits (Refer to ESPM

20-33-11 and ESPM 20-33-33).

(4) Subtask 532133-831-206-001 - Remove the brackets and fasteners from the

crossbeam FR61 and FR62.

Work Zones and Access Panels

Zone Access/Work location

150

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

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Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

Material necessary to do the job

Kit 532133D01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

25 EN6069D4-05 2 RIVET

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

References

Consumable Material List (CML)

Fig. A-GBJAA

Removal of the Existing Fasteners from

the Crossbeam FR61 and FR62

Sheet 01

Sheet 02

Sheet 03

Sheet 04

WARNING: BEFORE YOU REMOVE ANY RIVETS FROM THE CROSSBEAM

FR61 OR FR62, ENSURE THAT THE AFTER DOOR ACTUATOR IS

DISCONNECTED FROM THE ACTUATOR BEAM.

(a) Remove the existing fasteners from the crossbeam FR61.

1 Remove the existing fasteners :

Refer to Fig. A-GBJAA Sheet 02, Detail B, and Fig. A-GBJAA Sheet 03, Detail

D

2 Clean the fastener holes and the adjacent area with :

Solvent General

Purpose

11-026 As required

(b) If pins are installed in the actuator beam at FR61, remove them.

1 Remove the existing pins :

Refer to Fig. A-GBJAA Sheet 02, Detail B, and Fig. A-GBJAA Sheet 04, Detail

F

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2 Clean the pin holes and the adjacent area with :

Solvent General

Purpose

11-026 As required

(c) Remove the brackets and the fasteners from the crossbeam FR62.

1 Remove the brackets and the fasteners :

Refer to Fig. A-GBJAA Sheet 02, Detail C, and Fig. A-GBJAA Sheet 03, Detail

E

1 Receptacle DAN367-01 Item (17) Discard

1 Bracket A9249193420000 Item (18) Discard

and close the two holes with :

2 Rivet EN6069D4-05 Item 25

2 Clean the fastener holes and the adjacent area with :

Solvent General

Purpose

11-026 As required

(5) Subtask 532133-832-202-001 - Rotating Probe Inspection at the crossbeam FR61

and FR62.

Work Zones and Access Panels

Zone Access/Work location

150

Manpower Resources

Manhours 4.00

Minimum number of person 1

Subtask elapsed time 4.00

Skills AIRFRAME

References

Consumable Material List (CML)

Non Destructive Test Manual (NTM) 51-10-01 PART 6, Procedure A

Fig. A-GBLAA

Installation of the Reinforcement at the

Crossbeam FR61 and FR62

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

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(a) Rotating Probe Inspection at the crossbeam at FR61.

1 Do a rotating probe inspection of the fastener holes at FR61 (Refer to NTM

51-10-01 PART 6, Procedure A).

Refer to Fig. A-GBLAA Sheet 03, Detail D

a If no crack(s) are found :

<1> - Refer to para. (6)(a).

b If crack(s) are found :

<1> Contact AIRBUS for further instructions.

(b) Rotating Probe Inspection at the crossbeam at FR62.

1 Do a rotating probe inspection of the fastener holes at FR62 (Refer to NTM

51-10-01 PART 6, Procedure A).

Refer to Fig. A-GBLAA Sheet 04, Detail F

a If no crack(s) are found :

<1> - Refer to para. (6)(c).

b If crack(s) are found :

<1> Contact AIRBUS for further instructions.

(6) Subtask 532133-831-208-001 - Install the reinforcement and bracket at the

crossbeam at FR61 and FR62.

Work Zones and Access Panels

Zone Access/Work location

150

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

Material necessary to do the job

Kit 532133D01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

4 ASNA2528-3 32 NUT

5 ASNA2528-3A 14 NUT

6 EN6115K3-3 16 BOLT

10 EN6115K3X5 16 BOLT

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ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

11 EN6115K3A5 10 BOLT

12 EN6115K3AX5 4 BOLT

17 ABS0337-01A 1 RECEPTCL

22 A5327429220200 1 PLATE

23 A5327429220800 1 PLATE

24 F5347726220000 1 ANGLE

26 EN6081D6-09 4 RIVET

27 EN6069AD3-06 2 RIVET

34 DAN5-6-6X 7 PIN

35 DAN11-6X 7 COLLAR

36 DAN5-6-6Y 7 PIN

37 DAN11-6Y 7 COLLAR

Component COMPD01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

50 NAS1801-3-26 1 SCREW

51 NAS1149D0332K 2 WASHER

52 NSA5527-03-01D 1 SPACER

53 NSA5527-03-08D 1 SPACER

54 MS21042-3 1 NUT

55 MS21919WCH3 1 CLAMP

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

References

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-33-11

20-33-33

Structural Repair Manual (SRM) 51-40-41

51-76-00

Fig. A-GBLAA

Installation of the Reinforcement at the

Crossbeam FR61 and FR62

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Install the reinforcement at the crossbeam at FR61.

Refer to Fig. A-GBLAA Sheet 02, Detail B, Fig. A-GBLAA Sheet 03, Detail E, and

Fig. A-GBLAA Sheet 05

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1 At FR61 install temporarily :

1 Reinforcement A5327429220200 Item 22

2 If no ’cold expansion’ drill the fastener holes and open to final dimension.

3 If ’cold expansion’ transfer drill the fastener holes and open to the specific

starting hole diameter.

4 Cold expand the specified fastener holes where no cracks were found.

Refer to SRM 51-40-41

Refer to FTI Tooling List No. FTI-A310-53-2133-1

Refer to Fig. A-GBLAA Sheet 03, Detail E, and Fig. A-GBLAA Sheet 05

5 Ream the specified holes on the reinforcement and structure with the correct

gage finish reamer.

Refer to Fig. A-GBLAA Sheet 03, Detail E, and Fig. A-GBLAA Sheet 05

6 Remove the temporarily installed Item 22.

7 Clean the reamed fastener holes with :

Solvent General

Purpose

11-026 As required

8 Install the reinforcement, Item 22, with :

Refer to SRM 51-76-00

24 Nut ASNA2528-3 Item 4

2 Nut ASNA2528-3A Item 5

8 Bolt EN6115K3-3 Item 6

16 Bolt EN6115K3X5 Item 10

2 Bolt EN6115K3AX5 Item 12

(b) If pins have been removed from the actuator beam at FR61, install new pins.

Refer to Fig. A-GBLAA Sheet 02, Detail B, Fig. A-GBLAA Sheet 05 and Fig. AGBLAA Sheet 06, Detail H

1 If nominal size pins have been removed from the actuator beam at FR61,

install new 1st oversize pins.

a Install :

7 Pin DAN5-6-6X Item 34

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7 Collar DAN11-6X Item 35

2 If 1st oversize pins have been removed from the actuator beam at FR61,

install new 2nd oversize pins.

a Install :

7 Pin DAN5-6-6Y Item 36

7 Collar DAN11-6Y Item 37

(c) Install the reinforcement and bracket at the crossbeam at FR62.

Refer to Fig. A-GBLAA Sheet 02, Detail C, Fig. A-GBLAA Sheet 04, Detail G, and

Fig. A-GBLAA Sheet 05

1 At FR62 hold in position temporarily :

1 Bracket F5347726220000 Item 24

2 If a plastic cable support interferes with bracket, Item 24, replace the plastic

cable support with the following :

Refer to ESPM 20-33-11

1 Screw NAS1801-3-26 Item 50

2 Washer NAS1149D0332K Item 51

1 Spacer NSA5527-03-01D Item 52

1 Spacer NSA5527-03-08D Item 53

1 Nut MS21042-3 Item 54

1 Clamp MS21919WCH3 Item 55

NOTE: The screw, Item 50, has to be installed from the AFT of the

FR62 and the clamp, Item 55, has to be orientated at 12

o’clock position (Up).

3 At FR62 install temporarily :

1 Reinforcement A5327429220800 Item 23

4 If no ’cold expansion’ drill the fastener holes and open to final dimension.

5 If ’cold expansion’ transfer drill the fastener holes and open to the specific

starting hole diameter.

6 Cold expand the specified fastener holes where no cracks were found.

Refer to SRM 51-40-41

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

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Refer to FTI Tooling List No. FTI-A310-53-2133-1

Refer to Fig. A-GBLAA Sheet 04, Detail G, and Fig. A-GBLAA Sheet 05

7 Ream the specified holes on the reinforcement and structure with the correct

gage finish reamer.

Refer to Fig. A-GBLAA Sheet 04, Detail G, and Fig. A-GBLAA Sheet 05

8 Remove the temporarily installed Item 23.

9 Clean the reamed fastener holes with :

Solvent General

Purpose

11-026 As required

10 Install the reinforcement, Item 23 with :

Refer to SRM 51-76-00

Refer to Fig. A-GBLAA Sheet 04, Detail G

8 Nut ASNA2528-3 Item 4

12 Nut ASNA2528-3A Item 5

8 Bolt EN6115K3-3 Item 6

10 Bolt EN6115K3A5 Item 11

2 Bolt EN6115K3AX5 Item 12

11 At FR62 install :

Refer to Fig. A-GBLAA Sheet 04, Detail G and Section A-A

1 Bracket F5347726220000 Item 24

1 Receptacle ABS0337-01A Item 17

with :

4 Rivet EN6081D6-09 Item 26

2 Rivet EN6069AD3-06 Item 27

(d) Perform minor amendment of screws, spacers and split conduits (Refer to ESPM

20-33-11 and ESPM 20-33-33).

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

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**CONF ALL

D. TEST

**CONF 001

(1) Subtask 532133-700-201-001 - Testing

Work Zones and Access Panels

Zone Access/Work location

130

150

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 52-30-00, Page Block 301

52-33-18, Page Block 401

52-33-18, Page Block 501

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

equipment.

(b) Install the FWD cargo-compartment actuator to the actuator support beam (Refer to

AMM 52-33-18, Page Block 401).

(c) Install the AFT cargo-compartment actuator to the actuator support beam (Refer to

AMM 52-33-18, Page Block 401).

(d) Make sure that the applicable cargo-door safety-equipment is removed from the

FWD and AFT cargo-compartment doors (Refer to AMM 52-30-00, Page Block

301).

(e) Remove the safety clip(s) and tag(s) and close this (these) circuit breaker(s)

PANEL DESIGNATION FIN LOCATION SEE

NOTES

128VU HYDRAULIC/ACCU PRESS

CTL AND CARGO PUMP

7GX 803/C11

101VU ELEC HYD PUMP 23GX ALT2

NOTE: The location of the circuit breaker(s) can be different from the

location given in the table.

(f) Adjust the FWD and AFT door actuator and do a functional test (Refer to AMM

52-33-18, Page Block 401).

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

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SERVICE BULLETIN

**CONF 002

(1) Subtask 532133-700-201-001 - Testing

Work Zones and Access Panels

Zone Access/Work location

130

150

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 52-30-00, Page Block 301

52-33-18, Page Block 401

52-33-18, Page Block 501

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

equipment.

(b) Install the FWD cargo-compartment actuator to the actuator support beam (Refer to

AMM 52-33-18, Page Block 401).

(c) Install the AFT cargo-compartment actuator to the actuator support beam (Refer to

AMM 52-33-18, Page Block 401).

(d) Make sure that the applicable cargo-door safety-equipment is removed from the

FWD and AFT cargo-compartment doors (Refer to AMM 52-30-00, Page Block

301).

(e) Remove the safety clip(s) and tag(s) and close this (these) circuit breaker(s)

PANEL DESIGNATION FIN LOCATION SEE

NOTES

128VU HYDRAULIC/ACCU PRESS

CTL AND CARGO PUMP

7GX 803/C11

101VU ELEC HYD PUMP 23GX ALT2

NOTE: The location of the circuit breaker(s) can be different from the

location given in the table.

(f) Adjust the FWD and AFT door actuator and do a functional test (Refer to AMM

52-33-18, Page Block 401).

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

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**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 532133-942-201-001 - Close-up

Work Zones and Access Panels

Zone Access/Work location

130

150

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001

25-54-10, Page Block 201

25-55-10, Page Block 201

52-30-00, Page Block 301

(a) Install the retained FWD cargo-compartment ceiling panels (Refer to AMM

25-54-10, Page Block 201 and AMM 06-41-53, Page Block 001).

(b) Install the door actuator lining between FR22 and FR23.

(c) Install the retained AFT cargo-compartment ceiling panels (Refer to AMM 25-55-10,

Page Block 201 and AMM 06-41-53, Page Block 001).

(d) Install the door actuator lining between FR61 and FR62.

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

equipment.

(f) Close the FWD cargo-compartment door 811 (Refer to AMM 52-30-00, Page Block

301).

(g) Close the AFT cargo-compartment door 812 (Refer to AMM 52-30-00, Page Block

301).

(h) Remove the access platform(s).

**CONF 002

(1) Subtask 532133-942-201-001 - Close-up

Work Zones and Access Panels

Zone Access/Work location

130

150

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

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SERVICE BULLETIN

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001

25-54-10, Page Block 201

25-55-10, Page Block 201

52-30-00, Page Block 301

(a) Install the retained FWD cargo-compartment ceiling panels (Refer to AMM

25-54-10, Page Block 201 and AMM 06-41-53, Page Block 001).

(b) Install the door actuator lining between FR22 and FR23.

(c) Install the retained AFT cargo-compartment ceiling panels (Refer to AMM 25-55-10,

Page Block 201 and AMM 06-41-53, Page Block 001).

(d) Install the door actuator lining between FR61 and FR62.

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

equipment.

(f) Close the FWD cargo-compartment door 811 (Refer to AMM 52-30-00, Page Block

301).

(g) Close the AFT cargo-compartment door 812 (Refer to AMM 52-30-00, Page Block

301).

(h) Remove the access platform(s).

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

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SERVICE BULLETIN

**CONF 001

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2

SEAT TRACK 4

FR21 FR22 FR23 FR24

B

C

SEAT TRACK 6

B_SB_532133_6_BAAA_01_00

Z130

A

FWD

A

Figure A-GBAAA - Sheet 01

Removal of the Existing Fasteners from the Crossbeam FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

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SERVICE BULLETIN

**CONF 001

D

FR22

E

B

FR23

(3)

(3)

C

B_SB_532133_6_BAAA_02_01

F

Figure A-GBAAA - Sheet 02

Removal of the Existing Fasteners from the Crossbeam FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

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**CONF 001

NOTE:

01 (7 POS)

01 (7 POS)

01

01 01

VIEW LOOKING FWD

VIEW LOOKING AFT

FR22

FR23

01 (6 POS)

01 (6 POS)

02 01

02

HOLE

SYMBOL ITEM

DIN65399−3215CF RIVET

P/N DESCRIPTION KIT REMARKS

16

D

E

EXISTING FASTENER TO BE REMOVED

02 CLOSED EXISTING HOLES. AN INSPECTION OF THESE HOLES

01

IS NOT NECESSARY B_SB_532133_6_BAAA_03_01

D02

Figure A-GBAAA - Sheet 03

Removal of the Existing Fasteners from the Crossbeam FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 59

6

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

SERVICE BULLETIN

**CONF 001

03 IF PINS ARE INSTALLED, REMOVE THEM

(7 POS) 03

NOTE:

FR22

FWD

B_SB_532133_6_BAAA_04_00

F

Figure A-GBAAA - Sheet 04

Removal of the Existing Fasteners from the Crossbeam FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 60

6

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

SERVICE BULLETIN

**CONF 001

B_SB_532133_6_BCAA_01_00

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2

SEAT TRACK 4

FR21 FR22 FR23 FR24

B

C

SEAT TRACK 6

Z130

A

FWD

A

Figure A-GBCAA - Sheet 01

Installation of the Reinforcement at the Crossbeam FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 61

6

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

SERVICE BULLETIN

**CONF 001

FR22

FR23

2

(3)

(3)

H

J K

D E

F G

C

B

1

L M

B_SB_532133_6_BCAA_02_04

Figure A-GBCAA - Sheet 02

Installation of the Reinforcement at the Crossbeam FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 62

6

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

SERVICE BULLETIN

**CONF 001

01 HOLES TO BE INSPECTED IN ACCORDANCE WITH NTM 51−10−01

02 HOLES TO BE COLD EXPANDED IN ACCORDANCE WITH SRM 51−30−47

NOTE:

01

01

01

01

(7 POS)

(7 POS)

VIEW LOOKING FWD

FR22

VIEW LOOKING FWD

FR22

FOR RIVETS SYMBOLS, REFER TO SHEET 5

1

A

FOR DIMENSIONS, REFER TO SHEET 5

01

POSITION OF SPLIT IN EXPANSION 

SLEEVE DURING COLD EXPANSION

02

02 02

02

D

E

B_SB_532133_6_BCAA_03_02

Figure A-GBCAA - Sheet 03

Installation of the Reinforcement at the Crossbeam FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 63

6

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

SERVICE BULLETIN

**CONF 001

VIEW LOOKING AFT

FR23

VIEW LOOKING AFT

FR23

FOR RIVETS SYMBOLS, REFER TO SHEET 5

01

01 (6 POS)

(6 POS)

01 HOLES TO BE INSPECTED IN ACCORDANCE WITH NTM 51−10−01

02 HOLES TO BE COLD EXPANDED IN ACCORDANCE WITH SRM 51−30−47

NOTE:

2

D F

H

J

FOR DIMENSIONS, REFER TO SHEET 5

POSITION OF SPLIT IN EXPANSION 

SLEEVE DURING COLD EXPANSION

02 02 02

(3)

(3)

B_SB_532133_6_BCAA_04_02

F

G

Figure A-GBCAA - Sheet 04

Installation of the Reinforcement at the Crossbeam FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 64

6

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

SERVICE BULLETIN

**CONF 001

HOLE

SYMBOL ITEM

EN6115K3−3 PIN

P/N DESCRIPTION KIT

6

4 ASNA2528−3 COLLAR

EN6115K3X4 PIN

ASNA2528−3 COLLAR

EN6115K3X5 PIN

ASNA2528−3 COLLAR

9

4

10

4

EN6115K3AX6 PIN

ASNA2528−3A COLLAR

13

5

D02

D02

D02

D02

mm

DIMENSIONS

(in)

C

B

A 1.6 0.06

0.16

0.31

4.0

R 8.0

15 LN9198−3215CF RIVET

EN6115K3A6 PIN

ASNA2528−3A COLLAR

14

5

D02

EN6115K3AX5 PIN

ASNA2528−3A COLLAR

12

5

D02

STDN REMARKS

STARTING HOLE DIAMETER

MIN. MAX.

FINAL HOLE DIAMETER

MIN. MAX.

4.72 mm

(0.185 in)

4.76 mm

(0.187 in)

5.06 mm

(0.199 in)

5.09 mm

(0.20 in)

5.06 mm

(0.199 in)

5.09 mm

(0.20 in)

5.45 mm

(0.215 in)

5.49 mm

(0.216 in)

6−2−N

6−2−N

5.31 mm

(0.209 in)

5.38 mm

(0.212 in)

5.31 mm

(0.209 in)

5.38 mm

(0.212 in)

5.85 mm

(0.230 in)

5.89 mm

(0.231 in)

5.85 mm

(0.230 in)

5.89 mm

(0.231 in)

02 HOLES TO BE COLD EXPANDED IN ACCORDANCE WITH SRM 51−30−47

NOTE:

EN6115K3−3 PIN

ASNA2528−3 COLLAR

D02 4−4−N 4.29 mm

(0.169 in)

4.34 mm

(0.171 in)

4.72 mm

(0.185 in)

4.76 mm

(0.187 in)

STDN = STANDARD TOOL DIAMETER NUMBER

DAN5−6−6X PIN

DAN11−6X COLLAR

5.11mm

(0.201 in)

5.15mm

(0.203 in) D02

02

02

02

6

4

34

35

D02

E

D 1.10

1.50

28.0

38.1

F

G 1.77

40.0 1.57

45.0

H 49.0 1.93

J 73.5 2.89

K 33.0 1.30

L 41.0 1.61

B_SB_532133_6_BCAA_05_03

Figure A-GBCAA - Sheet 05

Installation of the Reinforcement at the Crossbeam FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 65

6

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

SERVICE BULLETIN

**CONF 001

FOR RIVET SYMBOLS, REFER TO SHEET 5

(7 POS) 03

03 IF PINS HAVE BEEN REMOVED, INSTALL NEW PINS

NOTE:

FR22

FWD

B_SB_532133_6_BCAA_06_00

H

Figure A-GBCAA - Sheet 06

Installation of the Reinforcement at the Crossbeam FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 66

6

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

SERVICE BULLETIN

**CONF 001

05 REWORK THE REINFORCEMENT, ITEM 1, TO THE NEW CONTOUR

IN ACCORDANCE WITH SRM 51−27−11

C

B

E

G

C

C

FOR DIMENSIONS, REFER TO SHEET 5

05

04

04 REINFORCEMENT, ITEM 1, WITH OLD CONTOUR

NOTE:

J

K

1

1

B_SB_532133_6_BCAA_07_00

Figure A-GBCAA - Sheet 07

Installation of the Reinforcement at the Crossbeam FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 67

6

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

SERVICE BULLETIN

**CONF 001

05 REWORK THE REINFORCEMENT, ITEM 1, TO THE NEW CONTOUR

IN ACCORDANCE WITH SRM 51−27−11

C

B

E

G

C

C

FOR DIMENSIONS, REFER TO SHEET 5

04

04 REINFORCEMENT, ITEM 1, WITH OLD CONTOUR

NOTE:

1

B

K

L

C

C

05 1

L

M

C

B_SB_532133_6_BCAA_08_00

Figure A-GBCAA - Sheet 08

Installation of the Reinforcement at the Crossbeam FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 68

6

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

SERVICE BULLETIN

**CONF 002

B_SB_532133_6_BEAA_01_00

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2

SEAT TRACK 4

FR21 FR22 FR23 FR24

B

C

SEAT TRACK 6

Z130

A

FWD

A

Figure A-GBEAA - Sheet 01

Removal of the Existing Fasteners from the Crossbeam FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 69

6

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

SERVICE BULLETIN

**CONF 002

D

FR22

E

B

FR23

(3)

(3)

C

B_SB_532133_6_BEAA_02_01

F

Figure A-GBEAA - Sheet 02

Removal of the Existing Fasteners from the Crossbeam FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 70

6

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

SERVICE BULLETIN

**CONF 002

NOTE:

01 (7 POS)

01 (7 POS)

01

01 01

VIEW LOOKING FWD

VIEW LOOKING AFT

FR22

FR23

01 (6 POS)

01 (6 POS)

02 01

02

HOLE

SYMBOL ITEM

DIN65399−3215CF RIVET

P/N DESCRIPTION KIT REMARKS

16

D

E

B_SB_532133_6_BEAA_03_01

EXISTING FASTENER TO BE REMOVED

02 CLOSED EXISTING HOLES. AN INSPECTION OF THESE HOLES

01

IS NOT NECESSARY

D03

Figure A-GBEAA - Sheet 03

Removal of the Existing Fasteners from the Crossbeam FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 71

6

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

SERVICE BULLETIN

**CONF 002

03 IF PINS ARE INSTALLED, REMOVE THEM

(7 POS) 03

NOTE:

FR22

FWD

B_SB_532133_6_BEAA_04_00

F

Figure A-GBEAA - Sheet 04

Removal of the Existing Fasteners from the Crossbeam FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 72

6

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

SERVICE BULLETIN

**CONF 002

B_SB_532133_6_BGAA_01_00

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2

SEAT TRACK 4

FR21 FR22 FR23 FR24

B

C

SEAT TRACK 6

Z130

A

FWD

A

Figure A-GBGAA - Sheet 01

Installation of the Reinforcement at the Crossbeam FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 73

6

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

SERVICE BULLETIN

**CONF 002

FR22

FR23

(3)

(3)

21

J K

D E

F G

B

C

H

20

L M

B_SB_532133_6_BGAA_02_03

Figure A-GBGAA - Sheet 02

Installation of the Reinforcement at the Crossbeam FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 74

6

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

SERVICE BULLETIN

**CONF 002

01 HOLES TO BE INSPECTED IN ACCORDANCE WITH NTM 51−10−01

02 HOLES TO BE COLD EXPANDED IN ACCORDANCE WITH SRM 51−30−47

NOTE:

01

01

01

01

01

(7 POS)

(7 POS)

VIEW LOOKING FWD

FR22

VIEW LOOKING FWD

FR22

FOR RIVET SYMBOLS, REFER TO SHEET 5

FOR DIMENSIONS, REFER TO SHEET 5

A

POSITION OF SPLIT IN EXPANSION 

SLEEVE DURING COLD EXPANSION

02

02

02

02

20

D

E

B_SB_532133_6_BGAA_03_05

Figure A-GBGAA - Sheet 03

Installation of the Reinforcement at the Crossbeam FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 75

6

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

SERVICE BULLETIN

**CONF 002

VIEW LOOKING AFT

FR23

VIEW LOOKING AFT

FR23

FOR RIVETS SYMBOLS, REFER TO SHEET 5

01

01 (6 POS)

(6 POS)

01 HOLES TO BE INSPECTED IN ACCORDANCE WITH NTM 51−10−01

02 HOLES TO BE COLD EXPANDED IN ACCORDANCE WITH SRM 51−30−47

NOTE:

E

F

G

K

FOR DIMENSIONS, REFER TO SHEET 5

POSITION OF SPLIT IN EXPANSION 

SLEEVE DURING COLD EXPANSION

02

02

21

02 02

(3)

(3)

B_SB_532133_6_BGAA_04_02

F

G

Figure A-GBGAA - Sheet 04

Installation of the Reinforcement at the Crossbeam FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 76

6

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

SERVICE BULLETIN

**CONF 002

HOLE

SYMBOL ITEM

EN6115K3−3 PIN

P/N DESCRIPTION KIT

6

4 ASNA2528−3 COLLAR

EN6115K3X4 PIN

ASNA2528−3 COLLAR

EN6115K3X5 PIN

ASNA2528−3 COLLAR

9

4

10

4

EN6115K3AX6 PIN

ASNA2528−3A COLLAR

13

5

D03

D03

D03

D03

15 LN9198−3215CF RIVET

EN6115K3A6 PIN

ASNA2528−3A COLLAR

14

5

D03

EN6115K3−4 PIN

ASNA2528−3 COLLAR

7

4

D03

EN6115K3X6 PIN

4 ASNA2528−3 COLLAR

D03

30

STDN REMARKS

STARTING HOLE DIAMETER

MIN. MAX.

FINAL HOLE DIAMETER

MIN. MAX.

4.72 mm

(0.185 in)

4.76 mm

(0.187 in)

5.06 mm

(0.199 in)

5.09 mm

(0.20 in)

5.06 mm

(0.199 in)

5.09 mm

(0.20 in)

5.45 mm

(0.215 in)

5.49 mm

(0.216 in)

6−2−N 5.31 mm

(0.209 in)

5.38 mm

(0.212 in)

5.85 mm

(0.230 in)

5.89 mm

(0.231 in)

4.72 mm

(0.185 in)

4.76 mm

(0.187 in)

D03

5.06 mm

(0.199 in)

5.09 mm

(0.20 in)

mm

DIMENSIONS

(in)

C

D

B

A 1.6 0.06

0.16

0.39

0.31

4.0

R 8.0

R 10.0

02 HOLES TO BE COLD EXPANDED IN ACCORDANCE WITH SRM 51−30−47

NOTE:

STDN = STANDARD TOOL DIAMETER NUMBER

DAN5−6−6X PIN

DAN11−6X COLLAR

5.11 mm

(0.201 in)

5.15 mm

(0.203 in) D03

EN6115K3−3 PIN

ASNA2528−3 COLLAR

D03 4−4−N 4.29 mm

(0.169 in)

4.34 mm

(0.171 in)

4.72 mm

(0.185 in)

4.76 mm

(0.187 in)

EN6115K3−4 PIN

ASNA2528−3 COLLAR

D03 4.72 mm

(0.185 in)

4.76 mm

(0.187 in) 4−4−N 4.29 mm

(0.169 in)

4.34 mm

(0.171 in)

02

02

02

34

35

6

4

7

4

F

G

E 1.10

1.93

1.57

28.0

40.0

49.0

H 52.5 2.01

J

K 2.89

59.4 2.34

73.5

L

M 1.61

33.0 1.30

41.0

B_SB_532133_6_BGAA_05_04

Figure A-GBGAA - Sheet 05

Installation of the Reinforcement at the Crossbeam FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 77

6

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

SERVICE BULLETIN

**CONF 002

FOR RIVET SYMBOLS, REFER TO SHEET 5

(7 POS) 03

03 IF PINS HAVE BEEN REMOVED, INSTALL NEW PINS

NOTE:

FR22

FWD

B_SB_532133_6_BGAA_06_00

H

Figure A-GBGAA - Sheet 06

Installation of the Reinforcement at the Crossbeam FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 78

6

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

SERVICE BULLETIN

**CONF 002

05 REWORK THE REINFORCEMENT, ITEM 20, TO THE NEW CONTOUR

IN ACCORDANCE WITH SRM 51−27−11

C

B

H

J

D

D

FOR DIMENSIONS, REFER TO SHEET 5

05 20

04

04 REINFORCEMENT, ITEM 20, WITH OLD CONTOUR

NOTE:

J

K

20

B_SB_532133_6_BGAA_07_01

Figure A-GBGAA - Sheet 07

Installation of the Reinforcement at the Crossbeam FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 79

6

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

SERVICE BULLETIN

**CONF 002

05 REWORK THE REINFORCEMENT, ITEM 20, TO THE NEW CONTOUR

IN ACCORDANCE WITH SRM 51−27−11

C

B

H

J

D

D

FOR DIMENSIONS, REFER TO SHEET 5

05 20

04

04 REINFORCEMENT, ITEM 20, WITH OLD CONTOUR

NOTE:

20

B

L

M

D

D

C

L

M

B_SB_532133_6_BGAA_08_00

Figure A-GBGAA - Sheet 08

Installation of the Reinforcement at the Crossbeam FR22 and FR23

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 80

6

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

SERVICE BULLETIN

**CONF ALL

B_SB_532133_6_BJAA_01_00

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2

SEAT TRACK 4

A

B

C

SEAT TRACK 6

FR60 FR61 FR62 FR63

Z150

FWD

A

Figure A-GBJAA - Sheet 01

Removal of the Existing Fasteners from the Crossbeam FR61 and FR62

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 81

6

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

SERVICE BULLETIN

**CONF ALL

D

FR61

FR62

E C

(17)

B

(18)

B_SB_532133_6_BJAA_02_02

F

Figure A-GBJAA - Sheet 02

Removal of the Existing Fasteners from the Crossbeam FR61 and FR62

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 82

6

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

SERVICE BULLETIN

**CONF ALL

NOTE:

01 (7 POS)

01 01

VIEW LOOKING FWD

VIEW LOOKING AFT

FR61

FR62

01 (7 POS)

01 (6 POS)

01 (6 POS)

HOLE

SYMBOL ITEM

EN6069D4−05 RIVET

P/N DESCRIPTION KIT REMARKS

02

25

D

E

D01

B_SB_532133_6_BJAA_03_01

EXISTING FASTENER TO BE REMOVED

02 CLOSED EXISTING HOLES. AN INSPECTION OF THESE HOLES

01

IS NOT NECESSARY

Figure A-GBJAA - Sheet 03

Removal of the Existing Fasteners from the Crossbeam FR61 and FR62

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 83

6

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

SERVICE BULLETIN

**CONF ALL

03 IF PINS ARE INSTALLED, REMOVE THEM

(7 POS) 03

NOTE:

FR61

F

FWD

B_SB_532133_6_BJAA_04_00

Figure A-GBJAA - Sheet 04

Removal of the Existing Fasteners from the Crossbeam FR61 and FR62

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 84

6

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

SERVICE BULLETIN

**CONF ALL

B_SB_532133_6_BLAA_01_00

SEAT TRACK 5

SEAT TRACK 3

SEAT TRACK 2

SEAT TRACK 4

B

C

SEAT TRACK 6

FR60 FR61 FR62 FR63

A

Z150

FWD

A

Figure A-GBLAA - Sheet 01

Installation of the Reinforcement at the Crossbeam FR61 and FR62

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 85

6

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

SERVICE BULLETIN

**CONF ALL

D

FR61

FR62 E

F

G

B

17 23

22

24

C

B_SB_532133_6_BLAA_02_01

H

Figure A-GBLAA - Sheet 02

Installation of the Reinforcement at the Crossbeam FR61 and FR62

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 86

6

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

SERVICE BULLETIN

**CONF ALL

VIEW LOOKING FWD

FR61

VIEW LOOKING FWD

FR61

FOR RIVETS SYMBOLS, REFER TO SHEET 5

01

(7 POS)

01 (7 POS) 01

01

D

01 HOLES TO BE INSPECTED IN ACCORDANCE WITH NTM 51−10−01

02 HOLES TO BE COLD EXPANDED IN ACCORDANCE WITH SRM 51−30−47

NOTE:

B_SB_532133_6_BLAA_03_00

22

01

01

POSITION OF SPLIT IN EXPANSION 

SLEEVE DURING COLD EXPANSION

02

02

02

02 E

Figure A-GBLAA - Sheet 03

Installation of the Reinforcement at the Crossbeam FR61 and FR62

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 87

6

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

SERVICE BULLETIN

**CONF ALL

VIEW LOOKING AFT

FR62

01

(6 POS)

(6 POS)

01

VIEW LOOKING AFT

FR62

F

23

01 HOLES TO BE INSPECTED IN ACCORDANCE WITH NTM 51−10−01

02 HOLES TO BE COLD EXPANDED IN ACCORDANCE WITH SRM 51−30−47

NOTE:

A

A

A

27

17

24

POSITION OF SPLIT IN EXPANSION 

SLEEVE DURING COLD EXPANSION

02

G

02

02

(2 POS)

FOR RIVETS SYMBOLS, REFER TO SHEET 5 B_SB_532133_6_BLAA_04_02

FOR DIMENSION, REFER TO SHEET 5

A A

Figure A-GBLAA - Sheet 04

Installation of the Reinforcement at the Crossbeam FR61 and FR62

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 88

6

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

SERVICE BULLETIN

**CONF ALL

HOLE

SYMBOL ITEM

EN6115K3−3 PIN

P/N DESCRIPTION KIT

6

4 ASNA2528−3 COLLAR

DIMENSIONS

mm (in.)

A 8.1 0.32 D01

STDN REMARKS

STARTING HOLE DIAMETER

MIN. MAX.

FINAL HOLE DIAMETER

MIN. MAX.

4.72 mm

(0.185 in)

4.76 mm

(0.187 in)

B_SB_532133_6_BLAA_05_02 HOLES TO BE COLD EXPANDED IN ACCORDANCE WITH SRM 51−30−47

NOTE:

EN6115K3X5 PIN

ASNA2528−3 COLLAR

10

4

EN6081D6−09 RIVET

D01

D01

EN6115K3A5 PIN

ASNA2528−3A COLLAR

11

5

26

D01

ASNA2528−3A COLLAR

12

5

6−2−N 5.31mm

(0.209 in)

5.38 mm

(0.212 in)

5.85 mm

(0.230 in)

5.89 mm

(0.231 in) D01

5.06 mm

(0.199 in)

5.09 mm

(0.20 in)

5.45 mm

(0.215 in)

5.49 mm

(0.216 in)

EN6115K3AX5

27 EN6096AD3−06 RIVET D01

PIN

EN6115K3−3 PIN

ASNA2528−3 COLLAR

D01 4−4−N 4.29 mm

(0.169 in)

4.34 mm

(0.171 in)

STDN = STANDARD TOOL DIAMETER NUMBER

DAN5−6−6X

COLLAR

PIN

DAN11−6X

D01 5.11 mm

(0.201 in)

5.15 mm

(0.203 in)

DAN5−6−6Y

COLLAR

PIN

DAN11−6Y

D01 5.51 mm

(0.217 in)

5.55 mm

(0.218 in)

34

35

36

37

02

02

02

6

4

4.72 mm

(0.185 in)

4.76 mm

(0.187 in)

Figure A-GBLAA - Sheet 05

Installation of the Reinforcement at the Crossbeam FR61 and FR62

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 89

6

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

SERVICE BULLETIN

**CONF ALL

(7 POS)

FR61

FWD

FOR RIVET SYMBOLS, REFER TO SHEET 5

IF REQUIRED, INSTALL 2ND OVERSIZE PINS

IF PINS HAVE BEEN REMOVED, INSTALL NEW PINS

NOTE:

B_SB_532133_6_BLAA_06_00

03

04

03

04

H

Figure A-GBLAA - Sheet 06

Installation of the Reinforcement at the Crossbeam FR61 and FR62

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 90

6

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

SERVICE BULLETIN

REPORTING SHEET

TITLE: FUSELAGE - GENERAL - REINFORCE THE FLOOR CROSSBEAMS AT

FR22/FR23 AND FR61/FR62

MODIFICATION No.: 13434D23217

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: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 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 4 3 2 1

- Quality rating of the Accomplishment Instructions 4 3 2 1

- Quality rating of the Illustrations 4 3 2 1

- Is this SB easy to understand ? Y / N

If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a

short description of the issue.

Planning Material Instructions

X Effectivity X Kit content X Preparation

X Reason X List of Materials Operator Supplied X Mod/Inspection

X Manpower X Industry support X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustrations

Comments:

Operator: Date:

Name/Title:

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE: Jan 15/10 SERVICE BULLETIN No.: A310-53-2133

REVISION No.: 02 - Apr 27/11 Page: 1

6

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