@A318/A319/A320/A321

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

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 57

TITLE: WINGS - GENERAL - INSPECTION OF SUSPECTED NON

CONFORMING NUTS.

MODIFICATION No.: None

This page transmits Revision No.02 of Service Bulletin No.A320-57-1153

ADDITIONAL WORK

**CONF ALL

NOTE: No additional work is required by this revision for aircraft modified by any previous

issue.

REASON

Revision No. 02 issued to inform the operators that this Service Bulletin is rendered mandatory, write

the bolt PN EN6115V4X* instead of EN6115V4X-*, modify the SB title, modify the illustrations and

modify the test job set-up.

CHANGES

FRONT MATTER

WINGS - GENERAL - INSPECTION OF

SUSPECTED NON CONFORMING

NUTS.

SB TITLE UPDATED R

SUMMARY

GENERAL EVALUATION GENERAL EVALUATION TABLE UPDATED R

EFFECTIVITY OPERATOR LIST UPDATED R

PLANNING INFORMATION

EFFECTIVITY EFFECTIVITY RELATED INFORMATION

UPDATED

R

COMPLIANCE

Classification CLASSIFICATION UPDATED R

Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED R

REFERENCES REFERENCED DOCUMENTATION UPDATED R

MATERIAL INFORMATION

MATERIAL - PRICE AND AVAILABILITY

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 1

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REVISION TRANSMITTAL SHEET

Procurement Addresses PROCUREMENT ADDRESSES UPDATED

MATERIAL SET UPDATED

R

Price and Availability PRICE AND AVAILABILITY UPDATED R

LIST OF MATERIALS - OPERATOR

SUPPLIED

Components

Component COMPA01 PART MATERIAL SET UPDATED

PART NUMBER UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

KEYWORD UPDATED

R

Component COMPA02 PART MATERIAL SET UPDATED

PART NUMBER UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

KEYWORD UPDATED

R

ACCOMPLISHMENT INSTRUCTIONS

TASK 571153- 832-801-001-Inspection

Subtask 571153-941-003-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

REFERENCES UPDATED

R

Subtask 571153-941-003-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

REFERENCES UPDATED

R

Subtask 571153-942-001-001 SUBTASK SOLUTION UPDATED

REFERENCES UPDATED

PANEL UPDATED

REFERENCED DOCUMENTATION UPDATED

R

Subtask 571153-942-001-001 SUBTASK SOLUTION UPDATED

REFERENCES UPDATED

PANEL UPDATED

REFERENCED DOCUMENTATION UPDATED

R

TASK 571153- 833-801-001-Repair

Subtask 571153-833-004-001 SUBTASK SOLUTION UPDATED

PART NUMBER UPDATED

MATERIAL LIST UPDATED

R

Subtask 571153-833-007-001 SUBTASK SOLUTION UPDATED

PART NUMBER UPDATED

MATERIAL LIST UPDATED

R

Subtask 571153-833-009-001 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

MATERIAL LIST UPDATED

R

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 2

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REVISION TRANSMITTAL SHEET

Subtask 571153-833-012-001 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

MATERIAL LIST UPDATED

R

Fig. A-FBAAA

Fig. A-FBAAA Sheet 02 SHEET UPDATED R

Fig. A-FBAAB

Fig. A-FBAAB Sheet 02 SHEET UPDATED R

Fig. A-FBBAA

Fig. A-FBBAA Sheet 02 SHEET UPDATED R

Fig. A-FBBAB

Fig. A-FBBAB Sheet 02 SHEET UPDATED R

Fig. A-FBDAA

Fig. A-FBDAA Sheet 02 SHEET UPDATED R

Fig. A-FBDAA Sheet 03 SHEET UPDATED R

Fig. A-FBDAA Sheet 04 SHEET UPDATED R

Fig. A-FBDAB

Fig. A-FBDAB Sheet 02 SHEET UPDATED R

Fig. A-FBDAB Sheet 03 SHEET UPDATED R

Fig. A-FBEAA

Fig. A-FBEAA Sheet 02 SHEET UPDATED R

Fig. A-FBEAA Sheet 03 SHEET UPDATED R

Fig. A-FBEAB

Fig. A-FBEAB Sheet 02 SHEET UPDATED R

Fig. A-FBEAB Sheet 03 SHEET UPDATED R

Appendix 01 : Inspection Report

Fig. A-FAAAA

Fig. A-FAAAA Sheet 02 SHEET UPDATED R

Fig. A-FAAAA Sheet 03 SHEET UPDATED R

Fig. A-FAAAB

Fig. A-FAAAB Sheet 02 SHEET UPDATED R

Fig. A-FAAAB Sheet 03 SHEET UPDATED R

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

Revision No 01 issued to :

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 3

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

update the Threshold,

modify the address in the Material Information Paragraph,

update the Consumable Material List (CML).

REVISION SEQUENCE

ORIGINAL: Feb 09/10

REVISION No. : 01 - Jun 28/10

REVISION No. : 02 - Apr 06/12

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 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.

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 57

TITLE: WINGS - GENERAL - INSPECTION OF SUSPECTED NON

CONFORMING NUTS.

**CONF ALL

MODIFICATIONS

None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

During structural parts assembly on the production line, some nuts were detected cracked. An

investigation was immediately launched to determine the affected nut types and the associated batches.

AIRBUS and the nut manufacturer, LISI Monadnock, have identified that the affected nut type is

ASNA2531-4.

These suspected non conforming nuts have been installed in production on aircraft listed in effectivity

paragraph.

This Service Bulletin consists in replacing all the suspect nuts with new ones of same type.

Accomplishment of this Service Bulletin will restore the aircraft structure to its original design

configuration.

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO

POTENTIAL AD YES A/C OPERATION AFFECTED NO

RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO

COST SAVING NO ETOPS AFFECTED NO

STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO

DE-FUELLING/VENTILATING YES

NOTE (1): Service Bulletin must be accomplished.

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 1

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SUMMARY

MATERIAL PRICE INFORMATION

**CONF 001

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Component COMPA01 1 See SB Bolts, nuts

**CONF 002

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Component COMPA02 1 See SB Bolts, nuts

**CONF 003

No Material

EFFECTIVITY

**CONF ALL

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

62X 95V AAR ABQ ABY ADH AEE AFL AFR AIJ AVA AXM AZA

BAL BAW BER BHP BKP BMA CCA CEB CES CHH CSA CSC CSN

CSZ DCS DKH DLH EIN EZY FFT GMI GWI HAY IAC IBE IGO

JBU JST KNE KZR LAN LBT MON NKS NLY PAL PVJ QTR RJA

SBI TAI TAM THY VLG VOI VRD WZZ

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU None

OEB None

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER OIT SE 999.0059/08

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 2

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SERVICE BULLETIN

SUMMARY

SOFT NO

OBRM NO

MANPOWER

**CONF 001

Task 571153-832-801-001: Inspection

TOTAL MANHOURS 72.50

ELAPSED TIME (HOURS) 36.50

Task 571153-833-801-001: Repair

TOTAL MANHOURS 86.00

ELAPSED TIME (HOURS) 43.00

**CONF 002

Task 571153-832-801-001: Inspection

TOTAL MANHOURS 68.50

ELAPSED TIME (HOURS) 34.00

Task 571153-833-801-001: Repair

TOTAL MANHOURS 62.00

ELAPSED TIME (HOURS) 31.00

**CONF 003

APPENDICES

**CONF ALL

Appendix 01 : Inspection Report

Appendix 02 : Elapsed Time Assumption of the Inspection

Appendix 03 : Elapsed Time Assumption of the Repair

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 3

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SERVICE BULLETIN

SUMMARY

**CONF 001 thru 002

RIB1

NOTE:

DETAILED VISUAL INSPECTION AREAS

FRONT SPAR

REAR SPAR

STRINGER 8

JOINT FITTING

STRINGER 11

JOINT FITTING

LH SIDE SHOWN

RH SIDE SYMMETRICAL

A

A

N_SB_571153_5_SAAA_01_00

FR36

Figure A-FSAAA - Sheet 01

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 4

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SERVICE BULLETIN

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 57

TITLE: WINGS - GENERAL - INSPECTION OF SUSPECTED NON

CONFORMING NUTS.

MODIFICATION No.: None

This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the

property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with

any information contained in it. It is delivered on the express condition that said document and the

information contained in it shall be treated as confidential, shall not be used for any purpose other than

that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall

not be duplicated in any manner (except for the purposes of performing the tasks described hereunder

and provided that any recipient of such document shall comply with the conditions herein), without

AIRBUS prior written consent.

1. PLANNING INFORMATION

**CONF ALL

A. EFFECTIVITY

(1) Models

318-112 318-121 319-111 319-112 319-115 319-132 319-133 320-214

320-216 320-232 320-233 321-211 321-212 321-213 321-231

(2) Effectivity by MSN

3359 3361-3362 3365-3366 3368 3370-3508 3510-3519 3522-3523 3525 3527

3529-3530 3533-3534 3537 3539 3542 3544 3546 3548 3552 3555

(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

62X 3402

95V 3379

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 1

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OPERATOR MSN

AAR 3437 3483 3496

ABQ 3385 3388 3403

ABY 3444 3476

ADH 3502 3515

AEE 3365 3392 3423 3439 3462 3478 3527

AFL 3373 3410 3511

AFR 3372 3399 3401 3419 3420 3441 3470

AIJ 3374 3508 3514

AVA 3408 3467 3518

AXM 3370 3394 3404 3427 3448 3477 3486 3489 3505

AZA 3362 3412 3464 3482

BAL 3492

BAW 3468 3499

BER 3415 3447 3516

BHP 3422

BKP 3421 3424 3454

BMA 3512

CCA 3461 3506 3523

CEB 3433 3472 3487

CES 3471 3481

CHH 3548

CSA 3406 3436 3452

CSC 3386 3449

CSN 3459 3493 3507 3552

CSZ 3366 3383 3435 3440 3456

DCS 3513

DKH 3368 3485

DLH 3387 3434

EIN 3377 3501

EZY 3411 3413 3426 3432 3442 3466 3537 3544 3555

FFT 3389 3431

GMI 3407

GWI 3375 3500 3534

HAY 3533

IAC 3498

IBE 3380 3443

IGO 3414 3453 3457 3497

JBU 3381 3416 3451 3479 3488 3517

JST 3474 3495

KNE 3361 3396 3425 3475 3530

KZR 3484 3519

LAN 3371 3390 3438 3469

LBT 3480

MON 3546

NKS 3393 3395

NLY 3504

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

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OPERATOR MSN

PAL 3455

PVJ 3542

QTR 3397

RJA 3428 3458 3522

SBI 3446 3473 3490 3494

TAI 3378 3418 3510

TAM 3391

THY 3382 3405 3429 3525 3539

VLG 3376 3400 3529

VOI 3450 3463 3491

VRD 3359 3398 3417 3445 3460 3465 3503

WZZ 3384 3409 3430

(4) Configuration by MSN

MSN CONFIGURATION

3359 3361 3362 3365 3366 3368 3370 3371 3373 3374 3375

3376 3377 3378 3379 3380 3381 3383 3384 3385 3386 3388

3389 3390 3391 3392 3393 3394 3395 3396 3398 3400 3402

3403 3404 3406 3407 3408 3409 3410 3411 3412 3413 3414

3415 3416 3417 3418 3421 3422 3423 3424 3425 3426 3427

3428 3430 3431 3432 3433 3435 3436 3437 3438 3439 3440

3442 3443 3444 3445 3446 3447 3448 3449 3450 3451 3452

3453 3454 3455 3456 3457 3460 3461 3463 3464 3465 3466

3467 3468 3469 3470 3472 3473 3474 3475 3476 3477 3478

3479 3480 3481 3482 3483 3484 3485 3486 3487 3488 3489

3490 3491 3492 3494 3495 3496 3497 3499 3500 3501 3502

3503 3505 3506 3508 3510 3511 3513 3514 3515 3516 3517

3518 3519 3529 3530 3533 3534 3537 3542 3544 3548 3555

001

3372 3382 3387 3397 3399 3401 3405 3419 3429 3434 3441

3458 3459 3462 3471 3493 3498 3504 3507 3512 3522 3523

3525 3527 3539 3546 3552

002

3420 003

(5) Configuration definition

**CONF 001

Config. 001 is valid for A320, A319 and A318 aircraft.

**CONF 002

Config. 002 is valid for A321 aircraft.

**CONF 003

Config. 003 is valid for aircraft on which the replacement of the non-conforming nuts has

been already performed with the RAS ref 70511319/017/2008. This Service Bulletin is

not to be accomplished.

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

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(6) Material Effectivity

**CONF 001

MATERIAL QTY PER A/C SEE NOTES

Consumable CMLA01 As required

Component COMPA01 1 (1)

NOTE (1): The quantities given are valid for a maximum repair configuration.

**CONF 002

MATERIAL QTY PER A/C SEE NOTES

Consumable CMLA01 As required

Component COMPA02 1 (1)

NOTE (1): The quantities given are valid for a maximum repair configuration.

**CONF 003

None

**CONF ALL

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

During structural parts assembly on the production line, some nuts were detected

cracked. An investigation was immediately launched to determine the affected nut types

and the associated batches.

AIRBUS and the nut manufacturer, LISI Monadnock, have identified that the affected nut

type is ASNA2531-4.

These suspected non conforming nuts have been installed in production on aircraft listed

in effectivity paragraph.

(2) Objective/Action

This Service Bulletin consists in replacing all the suspect nuts with new ones of same

type.

(3) Advantages

Accomplishment of this Service Bulletin will restore the aircraft structure to its original

design configuration.

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 4

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(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

**CONF 001

Task 571153-832-801-001: Inspection

(1) Detailed Visual Inspection on the Nuts in the LH Wing Tank.

(2) Detailed Visual Inspection on the Nuts in the RH Wing Tank.

Task 571153-833-801-001: Repair

(1) Replacement of the Nuts in the LH Wing Tank.

(2) Replacement of the Fasteners at Nominal Diameter in the LH Wing Tank.

(3) Replacement of the Fasteners at First Oversize Diameter in the LH Wing Tank.

(4) Replacement of the Nuts in the RH Wing Tank.

(5) Replacement of the Fasteners at Nominal Diameter in the RH Wing Tank.

(6) Replacement of the Fasteners at First Oversize Diameter in the RH Wing Tank.

**CONF 002

Task 571153-832-801-001: Inspection

(1) Detailed Visual Inspection on the Nuts in the LH Wing Tank.

(2) Detailed Visual Inspection on the Nuts in the RH Wing Tank.

Task 571153-833-801-001: Repair

(1) Replacement of the Nuts in the LH Wing Tank.

(2) Replacement of the Fasteners at Nominal Diameter in the LH Wing Tank.

(3) Replacement of the Fasteners at First Oversize Diameter in the LH Wing Tank.

(4) Replacement of the Nuts in the RH Wing Tank.

(5) Replacement of the Fasteners at Nominal Diameter in the RH Wing Tank.

(6) Replacement of the Fasteners at First Oversize Diameter in the RH Wing Tank.

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 5

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**CONF ALL

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

(2) Accomplishment Timescale

**CONF 001 thru 002

Accomplishment of this Service Bulletin is requested before 12 Years from Entry In

Service (EIS).

This Service Bulletin has been classified Mandatory by the issue of an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must

be used as the reference document for the mandated accomplishment timescale.

**CONF 003

None

**CONF ALL

F. APPROVAL

Approved under EASA Design Organization Approval No. EASA 21J.031.

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

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

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

before incorporation of the Service Bulletin.

G. MANPOWER

The manpower estimates given in this Service Bulletin are based on the direct labor cost to

do the work. These estimates assume that the work will be done by experienced personnel,

and may need to be revised upwards to suit operator’s circumstances. The estimates do not

include the time to prepare, plan or inspect the work. Manufacture and procurement of parts

and tools, drying times for paints, sealants, etc., and general administration work are also not

included.

**CONF 001

Task 571153-832-801-001: Inspection

Get Access 27.00

On Aircraft

Detailed Visual Inspection on the Nuts in the LH Wing

Tank.

7.50

Detailed Visual Inspection on the Nuts in the RH Wing

Tank.

7.50

Tests 0.50

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

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Task 571153-832-801-001: Inspection

Close-Up 30.00

TOTAL MANHOURS 72.50

ELAPSED TIME (HOURS) 36.50

NOTE: For detail concerning the elapsed time assumptions of the inspection, refer to

Appendix 02 : Elapsed Time Assumption of the Inspection

Task 571153-833-801-001: Repair

On Aircraft

Replacement of the Nuts in the LH Wing Tank. 12.00

Replacement of the Fasteners at Nominal Diameter in

the LH Wing Tank.

12.00

Replacement of the Fasteners at First Oversize

Diameter in the LH Wing Tank.

19.00

Replacement of the Nuts in the RH Wing Tank. 12.00

Replacement of the Fasteners at Nominal Diameter in

the RH Wing Tank.

12.00

Replacement of the Fasteners at First Oversize

Diameter in the RH Wing Tank.

19.00

TOTAL MANHOURS 86.00

ELAPSED TIME (HOURS) 43.00

NOTE: For detail concerning the elapsed time assumptions of the repair, refer to

Appendix 03 : Elapsed Time Assumption of the Repair

**CONF 002

Task 571153-832-801-001: Inspection

Get Access 27.00

On Aircraft

Detailed Visual Inspection on the Nuts in the LH Wing

Tank.

5.50

Detailed Visual Inspection on the Nuts in the RH Wing

Tank.

5.50

Tests 0.50

Close-Up 30.00

TOTAL MANHOURS 68.50

ELAPSED TIME (HOURS) 34.00

NOTE: For detail concerning the elapsed time assumptions of the inspection, refer to

Appendix 02 : Elapsed Time Assumption of the Inspection

Task 571153-833-801-001: Repair

On Aircraft

Replacement of the Nuts in the LH Wing Tank. 8.50

Replacement of the Fasteners at Nominal Diameter in

the LH Wing Tank.

8.50

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 7

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Task 571153-833-801-001: Repair

Replacement of the Fasteners at First Oversize

Diameter in the LH Wing Tank.

14.00

Replacement of the Nuts in the RH Wing Tank. 8.50

Replacement of the Fasteners at Nominal Diameter in

the RH Wing Tank.

8.50

Replacement of the Fasteners at First Oversize

Diameter in the RH Wing Tank.

14.00

TOTAL MANHOURS 62.00

ELAPSED TIME (HOURS) 31.00

NOTE: For detail concerning the elapsed time assumptions of the repair, refer to

Appendix 03 : Elapsed Time Assumption of the Repair

**CONF 003

**CONF ALL

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

**CONF 001

Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 06-40-00

12-34-24 28-00-00 28-10-00

28-25-00 57-27-11 57-27-12

57-41-37

Consumable Material List (CML)

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

Non Destructive Test Manual (NTM) 51-90-00

Standards Manual (SM)

Structural Repair Manual (SRM) 51-23-11 51-24-00 51-42-00

51-43-00 51-44-00 51-75-12

51-76-12

**CONF 002

Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 06-40-00

12-34-24 28-00-00 28-10-00

28-25-00 57-27-11 57-27-12

57-41-37

Consumable Material List (CML)

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

Non Destructive Test Manual (NTM) 51-90-00

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 8

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Standards Manual (SM)

Structural Repair Manual (SRM) 51-23-11 51-24-00 51-42-00

51-43-00 51-44-00 51-75-12

51-76-12

**CONF 003

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

Repair Approval Sheet (RAS) : 70511319/017/2008

**CONF ALL

K. PUBLICATION AFFECTED

None

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

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

multiple suppliers ensure access to minimum prices AIRBUS recommends Customers

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

B/E Aerospace. The address is:

Component COMPA01

Component COMPA02

B/E AEROSPACE INC

CONSUMABLES MANAGEMENT

10000 NW 15TH Terrace Miami

FL 33172

USA

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

Tel US : +1 305 925 2600

Tel ASIA : +1 310 900 1300

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

Fax US : +1 305 507 7191

Fax ASIA : +1 310 819 1200

SITA : MIAMMCR

E-Mail : AOGdesk_CMG@beaerospace.com

Internet : http://www.beconsumables.com

or, alternatively any other source on the open

market.

(2) Price and Availability

No AIRBUS kit will be provided.

Operator supplied standard hardware parts required to accomplish this Service Bulletin

are to be supplied from the Operator’s stock.

B. INDUSTRY SUPPORT INFORMATION

For the accomplishment of this Service Bulletin at or before 12 years from Entry In Service

(EIS), AIRBUS will credit the materials at no charge, and will credit the manhours for the

correction at the operator’s agreed in-house warranty labor rate for claims received not later

than 90 days after completion of the last affected aircraft of your fleet.

C. LIST OF COMPONENTS

No Kit

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D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Fuel Tank Sealant Polysulfide 09-002 As required

Solvent General Purpose 11-026 As required

(2) Components

Component COMPA01

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

NOTES

1 EN6115V4-5 24 Bolt

2 ASNA2531-4 126 Nut

3 EN6115V4-6 62 Bolt

4 EN6115V4-8 8 Bolt

5 EN6115V4-9 8 Bolt

6 EN6115V4-10 4 Bolt

7 EN6115V4X5 24 Bolt

8 EN6115V4X6 62 Bolt

9 EN6115V4X8 8 Bolt

10 EN6115V4X9 8 Bolt

11 EN6115V4X10 4 Bolt

12 EN6115V4-12 20 Bolt

16 EN6115V4X12 20 Bolt

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.

Component COMPA02

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

NOTES

2 ASNA2531-4 98 Nut

4 EN6115V4-8 12 Bolt

5 EN6115V4-9 12 Bolt

9 EN6115V4X8 12 Bolt

10 EN6115V4X9 12 Bolt

12 EN6115V4-12 6 Bolt

13 EN6115V4-7 62 Bolt

14 EN6115V4-11 6 Bolt

15 EN6115V4X11 6 Bolt

16 EN6115V4X12 6 Bolt

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

NOTES

17 EN6115V4X7 62 Bolt

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

None

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3. ACCOMPLISHMENT INSTRUCTIONS

Task 571153-832-801-001 - Inspection

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

INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO

THIS :

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

NECESSARY ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IF THERE IS CONTAMINATION, (Refer to ESPM 20-55-00).

Task Associated Data

**CONF 001

Manpower

TOTAL MANHOURS 72.50

ELAPSED TIME (HOURS) 36.50

**CONF 002

Manpower

TOTAL MANHOURS 68.50

ELAPSED TIME (HOURS) 34.00

**CONF 003

None

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**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 571153-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

References

Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001

06-31-53, Page Block 001

06-40-00, Page Block 001

Consumable Material List (CML)

(a) For the specification of the material numbers (Mat. No.) That you must use in this

Service Bulletin refer to Consumable Material List (CML).

(b) Use a non-metallic spatula to remove the sealant and clean the areas with :

Solvent General

Purpose

11-026 As required

(c) For the Frame (FR) identification (Refer to AMM 06-31-53, Page Block 001).

(d) For the identification of Zones (Refer to AMM 06-20-00, Page Block 001).

(e) For the identification of access panels (Refer to AMM 06-40-00, Page Block 001).

(2) Subtask 571153-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

**CONF 002

(1) Subtask 571153-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

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Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

References

Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001

06-31-53, Page Block 001

06-40-00, Page Block 001

Consumable Material List (CML)

(a) For the specification of the material numbers (Mat. No.) That you must use in this

Service Bulletin refer to Consumable Material List (CML).

(b) Use a non-metallic spatula to remove the sealant and clean the areas with :

Solvent General

Purpose

11-026 As required

(c) For the Frame (FR) identification (Refer to AMM 06-31-53, Page Block 001).

(d) For the identification of Zones (Refer to AMM 06-20-00, Page Block 001).

(e) For the identification of access panels (Refer to AMM 06-40-00, Page Block 001).

(2) Subtask 571153-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

**CONF 003

None

**CONF ALL

B. PREPARATION

**CONF 001

(1) Subtask 571153-941-001-001 - Job Set-up on the LH and RH Wing Tank.

Manpower Resources

Skills NON SPECIFIC

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References

Aircraft Maintenance Manual (AMM) Task 12-34-24-869-002

Task 28-00-00-910-001

Task 28-10-00-910-001

Task 28-25-00-650-001

Task 57-27-11-000-001

Task 57-27-12-000-001

Task 57-41-37-000-004

(a) Make sure that the aircraft is electrically grounded (Refer to AMM Task

12-34-24-869-002).

(b) Put the access platforms in position.

(c) Defuel the LH and RH wing tanks (Refer to AMM Task 28-25-00-650-001).

(d) Degas and ventilated the LH and RH wing tanks (Refer to AMM Task

28-00-00-910-001 and AMM Task 28-10-00-910-001).

(e) Remove the wing access panels (540AB and 640AB) (Refer to AMM Task

57-27-11-000-001).

(f) Remove the fuel surge access doors (540BZ and 640BZ) (Refer to AMM Task

57-27-12-000-001).

(g) Remove the pressure relief panels (521AB and 621AB) (Refer to AMM Task

57-41-37-000-004).

**CONF 002

(1) Subtask 571153-941-001-001 - Job Set-up on the LH and RH Wing Tank.

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-869-002

Task 28-00-00-910-001

Task 28-10-00-910-001

Task 28-25-00-650-001

Task 57-27-11-000-001

Task 57-27-12-000-001

Task 57-41-37-000-004

(a) Make sure that the aircraft is electrically grounded (Refer to AMM Task

12-34-24-869-002).

(b) Put the access platforms in position.

(c) Defuel the LH and RH wing tanks (Refer to AMM Task 28-25-00-650-001).

(d) Degas and ventilated the LH and RH wing tanks (Refer to AMM Task

28-00-00-910-001 and AMM Task 28-10-00-910-001).

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(e) Remove the wing access panels (540AB and 640AB) (Refer to AMM Task

57-27-11-000-001).

(f) Remove the fuel surge access doors (540BZ and 640BZ) (Refer to AMM Task

57-27-12-000-001).

(g) Remove the pressure relief panels (521AB and 621AB) (Refer to AMM Task

57-41-37-000-004).

**CONF 003

None

**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 571153-210-001-001 - Detailed Visual Inspection on the Nuts in the LH

Wing Tank.

Manpower Resources

Manhours 7.50

Minimum number of person 1

Subtask elapsed time 7.50

Skills NON SPECIFIC

References

Fig. A-FBAAA

Area to be Inspected on the Front Spar

Sheet 01

Sheet 02

Fig. A-FBBAA

Area to be Inspected on the STGR 8

and STGR 11

Sheet 01

Sheet 02

Fig. A-FBCAA

Flow Chart

Sheet 01

(a) For the inspection areas, refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 02,

Fig. A-FBBAA Sheet 01 and Fig. A-FBBAA Sheet 02

(b) Do the detailed visual inspection, refer to Fig. A-FBCAA Sheet 01

(c) For the inspection report, refer to Appendix 01 : Inspection Report .

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(2) Subtask 571153-210-003-001 - Detailed Visual Inspection on the Nuts in the RH

Wing Tank.

Manpower Resources

Manhours 7.50

Minimum number of person 1

Subtask elapsed time 7.50

Skills NON SPECIFIC

References

Fig. A-FBAAA

Area to be Inspected on the Front Spar

Sheet 01

Sheet 02

Fig. A-FBBAA

Area to be Inspected on the STGR 8

and STGR 11

Sheet 01

Sheet 02

Fig. A-FBCAA

Flow Chart

Sheet 01

(a) For the inspection areas, refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 02,

Fig. A-FBBAA Sheet 01 and Fig. A-FBBAA Sheet 02

(b) Do the detailed visual inspection, refer to Fig. A-FBCAA Sheet 01

(c) For the inspection report, refer to Appendix 01 : Inspection Report .

**CONF 002

(1) Subtask 571153-210-004-001 - Detailed Visual Inspection on the Nuts in the LH

Wing Tank.

Manpower Resources

Manhours 5.50

Minimum number of person 1

Subtask elapsed time 5.50

Skills NON SPECIFIC

References

Fig. A-FBAAB

Area to be Inspected on the Front Spar

Sheet 01

Sheet 02

Fig. A-FBBAB

Area to be Inspected on the STGR 8

and STGR 11

Sheet 01

Sheet 02

Fig. A-FBCAB

Flow Chart

Sheet 01

(a) For the inspection areas, refer to Fig. A-FBAAB Sheet 01 ,Fig. A-FBAAB Sheet 02,

Fig. A-FBBAB Sheet 01 and Fig. A-FBBAB Sheet 02

(b) Do the detailed visual inspection, refer to Fig. A-FBCAB Sheet 01

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(c) For the inspection report, refer to Appendix 01 : Inspection Report .

(2) Subtask 571153-210-005-001 - Detailed Visual Inspection on the Nuts in the RH

Wing Tank.

Manpower Resources

Manhours 5.50

Minimum number of person 1

Subtask elapsed time 5.50

Skills NON SPECIFIC

References

Fig. A-FBAAB

Area to be Inspected on the Front Spar

Sheet 01

Sheet 02

Fig. A-FBBAB

Area to be Inspected on the STGR 8

and STGR 11

Sheet 01

Sheet 02

Fig. A-FBCAB

Flow Chart

Sheet 01

(a) For the inspection areas, refer to Fig. A-FBAAB Sheet 01 ,Fig. A-FBAAB Sheet 02,

Fig. A-FBBAB Sheet 01 and Fig. A-FBBAB Sheet 02

(b) Do the detailed visual inspection, refer to Fig. A-FBCAB Sheet 01

(c) For the inspection report, refer to Appendix 01 : Inspection Report .

**CONF 003

None

**CONF ALL

D. TEST

**CONF 001

(1) Subtask 571153-941-003-001 - Job Set-up

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 57-27-11-400-001

Task 57-27-12-400-001

Task 57-41-37-400-002

(a) Install the pressure relief panels (521AB and 621AB) (Refer to AMM Task

57-41-37-400-002).

(b) Install the fuel surge access doors (540BZ and 640BZ) (Refer to AMM Task

57-27-12-400-001).

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(c) Install the wing access panels (540AB and 640AB) (Refer to AMM Task

57-27-11-400-001).

(2) Subtask 571153-730-001-001 - Test

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 28-25-00-869-001

Task 57-27-11-400-001

(a) Refuel the LH and RH wing tanks (Refer to AMM Task 28-25-00-869-001).

(b) Do the test after the installation of the panel (540AB and 640AB) (Refer to AMM

Task 57-27-11-400-001).

**CONF 002

(1) Subtask 571153-941-003-001 - Job Set-up

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 57-27-11-400-001

Task 57-27-12-400-001

Task 57-41-37-400-002

(a) Install the pressure relief panels (521AB and 621AB) (Refer to AMM Task

57-41-37-400-002).

(b) Install the fuel surge access doors (540BZ and 640BZ) (Refer to AMM Task

57-27-12-400-001).

(c) Install the wing access panels (540AB and 640AB) (Refer to AMM Task

57-27-11-400-001).

(2) Subtask 571153-730-001-001 - Test

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 28-25-00-869-001

Task 57-27-11-400-001

(a) Refuel the LH and RH wing tanks (Refer to AMM Task 28-25-00-869-001).

(b) Do the test after the installation of the panel (540AB and 640AB) (Refer to AMM

Task 57-27-11-400-001).

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**CONF 003

None

**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 571153-942-001-001 - Close-up on the LH and RH Wing Tank.

Manpower Resources

Skills NON SPECIFIC

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

equipment.

(b) Restore the systems and the aircraft to normal operating condition.

(c) Remove the access platforms.

**CONF 002

(1) Subtask 571153-942-001-001 - Close-up on the LH and RH Wing Tank.

Manpower Resources

Skills NON SPECIFIC

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

equipment.

(b) Restore the systems and the aircraft to normal operating condition.

(c) Remove the access platforms.

**CONF 003

None

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Task 571153-833-801-001 - Repair

**CONF ALL

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

INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO

THIS :

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

NECESSARY ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IF THERE IS CONTAMINATION, (Refer to ESPM 20-55-00).

Task Associated Data

**CONF 001

Manpower

TOTAL MANHOURS 86.00

ELAPSED TIME (HOURS) 43.00

**CONF 002

Manpower

TOTAL MANHOURS 62.00

ELAPSED TIME (HOURS) 31.00

**CONF 003

None

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**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 571153-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Fuel Tank Sealant

Polysulfide

09-002 As required

Solvent General Purpose 11-026 As required

References

Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001

06-31-53, Page Block 001

06-40-00, Page Block 001

Consumable Material List (CML)

Standards Manual (SM)

Structural Repair Manual (SRM) 51-23-11

51-24-00

51-42-00

51-43-00

51-44-00

51-75-12

51-76-12

(a) For the specification of the material numbers (Mat. No.) That you must use in this

Service Bulletin refer to Consumable Material List (CML).

(b) 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.

(c) Use a non-metallic spatula to remove the sealant and clean the areas with :

Solvent General

Purpose

11-026 As required

(d) For the Frame (FR) identification (Refer to AMM 06-31-53, Page Block 001).

(e) For the identification of Zones (Refer to AMM 06-20-00, Page Block 001).

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(f) For the identification of access panels (Refer to AMM 06-40-00, Page Block 001).

(g) For the specification of the material numbers (Mat. No.) (Refer to CML).

(h) Apply the sealant (Refer to SRM 51-24-00).

(i) For the removal and installation of the fasteners (Refer to SRM 51-42-00).

(j) For alternative and substitute fasteners (Refer to SRM 51-43-00).

(k) Drill the holes (Refer to SRM 51-44-00).

(l) Renew the protective finish (Refer to SRM 51-75-12 and SRM 51-23-11).

(m) Repair of fuel tank sealing (Refer to SRM 51-76-12).

(n) Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

on the fasteners.

(o) Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

on all fasteners (wet assembly).

**CONF 002

(1) Subtask 571153-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Fuel Tank Sealant

Polysulfide

09-002 As required

Solvent General Purpose 11-026 As required

References

Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001

06-31-53, Page Block 001

06-40-00, Page Block 001

Consumable Material List (CML)

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References

Standards Manual (SM)

Structural Repair Manual (SRM) 51-23-11

51-24-00

51-42-00

51-43-00

51-44-00

51-75-12

51-76-12

(a) For the specification of the material numbers (Mat. No.) That you must use in this

Service Bulletin refer to Consumable Material List (CML).

(b) 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.

(c) Use a non-metallic spatula to remove the sealant and clean the areas with :

Solvent General

Purpose

11-026 As required

(d) For the Frame (FR) identification (Refer to AMM 06-31-53, Page Block 001).

(e) For the identification of Zones (Refer to AMM 06-20-00, Page Block 001).

(f) For the identification of access panels (Refer to AMM 06-40-00, Page Block 001).

(g) For the specification of the material numbers (Mat. No.) (Refer to CML).

(h) Apply the sealant (Refer to SRM 51-24-00).

(i) For the removal and installation of the fasteners (Refer to SRM 51-42-00).

(j) For alternative and substitute fasteners (Refer to SRM 51-43-00).

(k) Drill the holes (Refer to SRM 51-44-00).

(l) Renew the protective finish (Refer to SRM 51-75-12 and SRM 51-23-11).

(m) Repair of fuel tank sealing (Refer to SRM 51-76-12).

(n) Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

on the fasteners.

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 28

5

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SERVICE BULLETIN

(o) Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

on all fasteners (wet assembly).

**CONF 003

None

**CONF ALL

B. PREPARATION

**CONF 001

None

**CONF 002

None

**CONF 003

None

**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 571153-833-001-001 - Replacement of the Nuts in the LH Wing Tank.

Manpower Resources

Manhours 12.00

Minimum number of person 1

Subtask elapsed time 12.00

Skills NON SPECIFIC

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-4 63 Nut

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 29

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SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Fuel Tank Sealant

Polysulfide

09-002 As required

References

Fig. A-FBDAA

Replacement of the Fasteners on the

Front Spar

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FBEAA

Replacement of the Fasteners on the

STGR 8 and STGR 11

Sheet 01

Sheet 02

Sheet 03

WARNING: REMOVE 50 PERCENT OF NUTS (EQUALLY SPREAD), INSTALL

NEW NUTS AND THEN 50 PERCENT REMAINING NUTS

REPLACEMENT.

(a) Replacement of the nuts on the front spar :

Refer to Fig. A-FBDAA Sheet 01 thru Fig. A-FBDAA Sheet 04

1 Use the alen key to maintain the bolt and remove :

53 Nut ASNA2531-4 Item (2) Discard

NOTE: If the bolt rotates during the removal of the nuts (Refer to

SUBTASK 571153-833-003 001 Replacement of the Fasteners

at Nominal Diameter in the LH Wing Tank.

2 Use the alen key to maintain the bolt and install :

53 Nut ASNA2531-4 Item 2

NOTE: If the bolt rotates during the installation of the nuts (Refer to

SUBTASK 571153-833-003 001 Replacement of the Fasteners

at Nominal Diameter in the LH Wing Tank.

a Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

on the nuts.

(b) Replacement of the nuts on the STGR 8 and STGR 11.

Refer to Fig. A-FBEAA Sheet 01 thru Fig. A-FBEAA Sheet 03

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 30

5

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SERVICE BULLETIN

1 Use the alen key to maintain the bolt and remove :

10 Nut ASNA2531-4 Item (2) Discard

NOTE: If the bolt rotates during the removal of the nuts (Refer to

SUBTASK 571153-833-003 001 Replacement of the Fasteners

at Nominal Diameter in the LH Wing Tank.

2 Use the alen key to maintain the bolt and install :

10 Nut ASNA2531-4 Item 2

NOTE: If the bolt rotates during the installation of the nuts (Refer to

SUBTASK 571153-833-003 001 Replacement of the Fasteners

at Nominal Diameter in the LH Wing Tank.

a Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

on the nuts.

(2) Subtask 571153-833-003-001 - Replacement of the Fasteners at Nominal Diameter

in the LH Wing Tank.

Manpower Resources

Manhours 12.00

Minimum number of person 1

Subtask elapsed time 12.00

Skills NON SPECIFIC

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V4-5 12 Bolt

2 ASNA2531-4 63 Nut

3 EN6115V4-6 31 Bolt

4 EN6115V4-8 4 Bolt

5 EN6115V4-9 4 Bolt

6 EN6115V4-10 2 Bolt

12 EN6115V4-12 10 Bolt

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Fuel Tank Sealant

Polysulfide

09-002 As required

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 31

5

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SERVICE BULLETIN

References

Non Destructive Test Manual (NTM) 51-90-00, Page Block 001

Fig. A-FBDAA

Replacement of the Fasteners on the

Front Spar

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FBEAA

Replacement of the Fasteners on the

STGR 8 and STGR 11

Sheet 01

Sheet 02

Sheet 03

NOTE: Instruction in case of bolt rotates during the nuts replacement.

(a) Remove the nut and bolt on the front spar.

Refer to Fig. A-FBDAA Sheet 01 thru Fig. A-FBDAA Sheet 04

1 Clean the hole and perform a visual inspection, looking for scratches (Refer to

NTM 51-90-00, Page Block 001).

a If no scratches :

<1> Install the new fasteners.

12 Bolt EN6115V4-5 Item 1

31 Bolt EN6115V4-6 Item 3

4 Bolt EN6115V4-8 Item 4

4 Bolt EN6115V4-9 Item 5

2 Bolt EN6115V4-10 Item 6

53 Nut ASNA2531-4 Item 2

NOTE: The quantities given are valid for a maximum repair

configuration.

<2> Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

On the fasteners (wet assembly).

<3> Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

on the fasteners.

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 32

5

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SERVICE BULLETIN

b If the hole is scratched :

<1> Replace the fastener at first oversize diameter (Refer to SUBTASK

571153-833-004 001 Replacement of the Fasteners at First

Oversize Diameter in the LH Wing Tank. .

(b) Remove the nut and bolt on the STGR 8 and STGR 11.

Refer to Fig. A-FBEAA Sheet 01 thru Fig. A-FBEAA Sheet 03

1 Clean the hole and perform a visual inspection, looking for scratches (Refer to

NTM 51-90-00, Page Block 001).

a If no scratches :

<1> Install the new fasteners.

10 Bolt EN6115V4-12 Item 12

10 Nut ASNA2531-4 Item 2

NOTE: The quantities given are valid for a maximum repair

configuration.

<2> Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

On the fasteners (wet assembly).

<3> Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

on the fasteners.

b If the hole is scratched :

<1> Replace the fastener at first oversize diameter (Refer to SUBTASK

571153-833-004 001 Replacement of the Fasteners at First

Oversize Diameter in the LH Wing Tank. .

(3) Subtask 571153-833-004-001 - Replacement of the Fasteners at First Oversize

Diameter in the LH Wing Tank.

Manpower Resources

Manhours 19.00

Minimum number of person 1

Subtask elapsed time 19.00

Skills NON SPECIFIC

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 33

5

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SERVICE BULLETIN

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-4 63 Nut

7 EN6115V4X5 12 Bolt

8 EN6115V4X6 31 Bolt

9 EN6115V4X8 4 Bolt

10 EN6115V4X9 4 Bolt

11 EN6115V4X10 2 Bolt

16 EN6115V4X12 10 Bolt

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Fuel Tank Sealant

Polysulfide

09-002 As required

References

Fig. A-FBDAA

Replacement of the Fasteners on the

Front Spar

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FBEAA

Replacement of the Fasteners on the

STGR 8 and STGR 11

Sheet 01

Sheet 02

Sheet 03

(a) On the front spar :

Refer to Fig. A-FBDAA Sheet 01 thru Fig. A-FBDAA Sheet 04

1 Oversize the hole to the dimension given in the Fig. A-FBDAA Sheet 04.

2 Install :

12 Bolt EN6115V4X5 Item 7

31 Bolt EN6115V4X6 Item 8

4 Bolt EN6115V4X8 Item 9

4 Bolt EN6115V4X9 Item 10

2 Bolt EN6115V4X10 Item 11

53 Nut ASNA2531-4 Item 2

NOTE: The quantities given are valid for a maximum repair

configuration.

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 34

5

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a Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

On the fasteners (wet assembly).

b Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

on the fasteners.

(b) On the STGR 8 and STGR 11.

Refer to Fig. A-FBEAA Sheet 01 thru Fig. A-FBEAA Sheet 03

1 Oversize the hole to the dimension given in the Fig. A-FBEAA Sheet 03.

2 Install :

10 Bolt EN6115V4X12 Item 16

10 Nut ASNA2531-4 Item 2

NOTE: The quantities given are valid for a maximum repair

configuration.

a Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

On the fasteners (wet assembly).

b Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

on the fasteners.

(4) Subtask 571153-833-005-001 - Replacement of the Nuts in the RH Wing Tank.

Manpower Resources

Manhours 12.00

Minimum number of person 1

Subtask elapsed time 12.00

Skills NON SPECIFIC

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 35

5

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SERVICE BULLETIN

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-4 63 Nut

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Fuel Tank Sealant

Polysulfide

09-002 As required

References

Fig. A-FBDAA

Replacement of the Fasteners on the

Front Spar

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FBEAA

Replacement of the Fasteners on the

STGR 8 and STGR 11

Sheet 01

Sheet 02

Sheet 03

WARNING: REMOVE 50 PERCENT OF NUTS (EQUALLY SPREAD), INSTALL

NEW NUTS AND THEN 50 PERCENT REMAINING NUTS

REPLACEMENT.

(a) Replacement of the nuts on the front spar :

Refer to Fig. A-FBDAA Sheet 01 thru Fig. A-FBDAA Sheet 04

1 Use the alen key to maintain the bolt and remove :

53 Nut ASNA2531-4 Item (2) Discard

NOTE: If the bolt rotates during the removal of the nuts (Refer to

SUBTASK 571153-833-006 001 Replacement of the Fasteners

at Nominal Diameter in the RH Wing Tank.

2 Use the alen key to maintain the bolt and install :

53 Nut ASNA2531-4 Item 2

NOTE: If the bolt rotates during the installation of the nuts (Refer to

SUBTASK 571153-833-006 001 Replacement of the Fasteners

at Nominal Diameter in the RH Wing Tank.

a Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

on the nuts.

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 36

5

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SERVICE BULLETIN

(b) Replacement of the nuts on the STGR 8 and STGR 11.

Refer to Fig. A-FBEAA Sheet 01 thru Fig. A-FBEAA Sheet 03

1 Use the alen key to maintain the bolt and remove :

10 Nut ASNA2531-4 Item (2) Discard

NOTE: If the bolt rotates during the removal of the nuts (Refer to

SUBTASK 571153-833-006 001 Replacement of the Fasteners

at Nominal Diameter in the RH Wing Tank.

2 Use the alen key to maintain the bolt and install :

10 Nut ASNA2531-4 Item 2

NOTE: If the bolt rotates during the installation of the nuts (Refer to

SUBTASK 571153-833-006 001 Replacement of the Fasteners

at Nominal Diameter in the RH Wing Tank.

a Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

on the nuts.

(5) Subtask 571153-833-006-001 - Replacement of the Fasteners at Nominal Diameter

in the RH Wing Tank.

Manpower Resources

Manhours 12.00

Minimum number of person 1

Subtask elapsed time 12.00

Skills NON SPECIFIC

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V4-5 12 Bolt

2 ASNA2531-4 63 Nut

3 EN6115V4-6 31 Bolt

4 EN6115V4-8 4 Bolt

5 EN6115V4-9 4 Bolt

6 EN6115V4-10 2 Bolt

12 EN6115V4-12 10 Bolt

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 37

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SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Fuel Tank Sealant

Polysulfide

09-002 As required

References

Non Destructive Test Manual (NTM) 51-90-00, Page Block 001

Fig. A-FBDAA

Replacement of the Fasteners on the

Front Spar

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FBEAA

Replacement of the Fasteners on the

STGR 8 and STGR 11

Sheet 01

Sheet 02

Sheet 03

NOTE: Instruction in case of bolt rotates during the nut replacement.

(a) Remove the nut and bolt on the front spar.

Refer to Fig. A-FBDAA Sheet 01 thru Fig. A-FBDAA Sheet 04

1 Clean the hole and perform a visual inspection, looking for scratches (Refer to

NTM 51-90-00, Page Block 001).

a If no scratches :

<1> Install the new fasteners.

12 Bolt EN6115V4-5 Item 1

31 Bolt EN6115V4-6 Item 3

4 Bolt EN6115V4-8 Item 4

4 Bolt EN6115V4-9 Item 5

2 Bolt EN6115V4-10 Item 6

53 Nut ASNA2531-4 Item 2

NOTE: The quantities given are valid for a maximum repair

configuration.

<2> Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

On the fasteners (wet assembly).

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 38

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SERVICE BULLETIN

<3> Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

on the fasteners.

b If the hole is scratched :

<1> Replace the fastener at first oversize diameter (Refer to SUBTASK

571153-833-007 001 Replacement of the Fasteners at First

Oversize Diameter in the RH Wing Tank. .

(b) Remove the nut and bolt on the STGR 8 and STGR 11.

Refer to Fig. A-FBEAA Sheet 01 thru Fig. A-FBEAA Sheet 03

1 Clean the hole and perform a visual inspection, looking for scratches (Refer to

NTM 51-90-00, Page Block 001).

a If no scratches :

<1> Install the new fasteners.

10 Bolt EN6115V4-12 Item 12

10 Nut ASNA2531-4 Item 2

NOTE: The quantities given are valid for a maximum repair

configuration.

<2> Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

On the fasteners (wet assembly).

<3> Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

on the fasteners.

b If the hole is scratched :

<1> Replace the fastener at first oversize diameter (Refer to SUBTASK

571153-833-007 001 Replacement of the Fasteners at First

Oversize Diameter in the RH Wing Tank. .

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 39

5

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SERVICE BULLETIN

(6) Subtask 571153-833-007-001 - Replacement of the Fasteners at First Oversize

Diameter in the RH Wing Tank.

Manpower Resources

Manhours 19.00

Minimum number of person 1

Subtask elapsed time 19.00

Skills NON SPECIFIC

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-4 63 Nut

7 EN6115V4X5 12 Bolt

8 EN6115V4X6 31 Bolt

9 EN6115V4X8 4 Bolt

10 EN6115V4X9 4 Bolt

11 EN6115V4X10 2 Bolt

16 EN6115V4X12 10 Bolt

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Fuel Tank Sealant

Polysulfide

09-002 As required

References

Fig. A-FBDAA

Replacement of the Fasteners on the

Front Spar

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FBEAA

Replacement of the Fasteners on the

STGR 8 and STGR 11

Sheet 01

Sheet 02

Sheet 03

(a) On the front spar :

Refer to Fig. A-FBDAA Sheet 01 thru Fig. A-FBDAA Sheet 04

1 Oversize the hole to the dimension given in the Fig. A-FBDAA Sheet 04.

2 Install :

12 Bolt EN6115V4X5 Item 7

31 Bolt EN6115V4X6 Item 8

4 Bolt EN6115V4X8 Item 9

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 40

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4 Bolt EN6115V4X9 Item 10

2 Bolt EN6115V4X10 Item 11

53 Nut ASNA2531-4 Item 2

NOTE: The quantities given are valid for a maximum repair

configuration.

a Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

On the fasteners (wet assembly).

b Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

on the fasteners.

(b) On the STGR 8 and STGR 11.

Refer to Fig. A-FBEAA Sheet 01 thru Fig. A-FBEAA Sheet 03

1 Oversize the hole to the dimension given in the Fig. A-FBEAA Sheet 03.

2 Install :

10 Bolt EN6115V4X12 Item 16

10 Nut ASNA2531-4 Item 2

NOTE: The quantities given are valid for a maximum repair

configuration.

a Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

On the fasteners (wet assembly).

b Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

on the fasteners.

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 41

5

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SERVICE BULLETIN

**CONF 002

(1) Subtask 571153-833-002-001 - Replacement of the Nuts in the LH Wing Tank.

Manpower Resources

Manhours 8.50

Minimum number of person 1

Subtask elapsed time 8.50

Skills NON SPECIFIC

Material necessary to do the job

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-4 49 Nut

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Fuel Tank Sealant

Polysulfide

09-002 As required

References

Fig. A-FBDAB

Replacement of the Fasteners on the

Front Spar

Sheet 01

Sheet 02

Sheet 03

Fig. A-FBEAB

Replacement of the Fasteners on the

STGR 8 and STGR 11

Sheet 01

Sheet 02

Sheet 03

WARNING: REMOVE 50 PERCENT OF NUTS (EQUALLY SPREAD), INSTALL

NEW NUTS AND THEN 50 PERCENT REMAINING NUTS

REPLACEMENT.

(a) Replacement of the nuts on the front spar :

1 Use the alen key to maintain the bolt and remove :

Refer to Fig. A-FBDAB Sheet 01 thru Fig. A-FBDAB Sheet 03

43 Nut ASNA2531-4 Item (2) Discard

NOTE: If the bolt rotates during the removal of the nuts (Refer to

SUBTASK 571153-833-008 001 Replacement of the Fasteners

at Nominal Diameter in the LH Wing Tank.

2 Use the alen key to maintain the bolt and install :

43 Nut ASNA2531-4 Item 2

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 42

5

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SERVICE BULLETIN

NOTE: If the bolt rotates during the installation of the nuts (Refer to

SUBTASK 571153-833-008 001 Replacement of the Fasteners

at Nominal Diameter in the LH Wing Tank.

a Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

on the nuts.

(b) Replacement of the nuts on the STGR 8 and STGR 11.

Refer to FIG Fig. A-FBEAB Sheet 01 thru Fig. A-FBEAB Sheet 03

1 Use the alen key to maintain the bolt and remove :

6 Nut ASNA2531-4 Item (2) Discard

NOTE: If the bolt rotates during the removal of the nuts (Refer to

SUBTASK 571153-833-008 001 Replacement of the Fasteners

at Nominal Diameter in the LH Wing Tank.

2 Use the alen key to maintain the bolt and install :

6 Nut ASNA2531-4 Item 2

NOTE: If the bolt rotates during the installation of the nuts (Refer to

SUBTASK 571153-833-008 001 Replacement of the Fasteners

at Nominal Diameter in the LH Wing Tank.

a Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

on the nuts.

(2) Subtask 571153-833-008-001 - Replacement of the Fasteners at Nominal Diameter

in the LH Wing Tank.

Manpower Resources

Manhours 8.50

Minimum number of person 1

Subtask elapsed time 8.50

Skills NON SPECIFIC

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 43

5

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SERVICE BULLETIN

Material necessary to do the job

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-4 49 Nut

4 EN6115V4-8 6 Bolt

5 EN6115V4-9 6 Bolt

12 EN6115V4-12 3 Bolt

13 EN6115V4-7 31 Bolt

14 EN6115V4-11 3 Bolt

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Fuel Tank Sealant

Polysulfide

09-002 As required

References

Non Destructive Test Manual (NTM) 51-90-00, Page Block 001

Fig. A-FBDAB

Replacement of the Fasteners on the

Front Spar

Sheet 01

Sheet 02

Sheet 03

Fig. A-FBEAB

Replacement of the Fasteners on the

STGR 8 and STGR 11

Sheet 01

Sheet 02

Sheet 03

NOTE: Instruction in case of bolt rotates during the nut replacement.

(a) Remove the nut and bolt on the front spar.

Refer to Fig. A-FBDAB Sheet 01 thru Fig. A-FBDAB Sheet 03

1 Clean the hole and perform a visual inspection, looking for scratches (Refer to

NTM 51-90-00, Page Block 001).

a If no scratches :

<1> Install the new fasteners.

6 Bolt EN6115V4-9 Item 5

6 Bolt EN6115V4-8 Item 4

31 Bolt EN6115V4-7 Item 13

43 Nut ASNA2531-4 Item 2

NOTE: The quantities given are valid for a maximum repair

configuration.

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 44

5

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SERVICE BULLETIN

<2> Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

On the fasteners (wet assembly).

<3> Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

on the fasteners.

b If the hole is scratched :

<1> Replace the fastener at first oversize diameter (Refer to SUBTASK

571153-833-009 001 Replacement of the Fasteners at First

Oversize Diameter in the LH Wing Tank. .

(b) Remove the nut and bolt on the STGR 8 and STGR 11.

Refer to Fig. A-FBEAB Sheet 01 thru Fig. A-FBEAB Sheet 03

1 Clean the hole and perform a visual inspection, looking for scratches (Refer to

NTM 51-90-00, Page Block 001).

a If no scratches :

<1> Install the new fasteners.

3 Bolt EN6115V4-12 Item 12

3 Bolt EN6115V4-11 Item 14

6 Nut ASNA2531-4 Item 2

NOTE: The quantities given are valid for a maximum repair

configuration.

<2> Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

On the fasteners (wet assembly).

<3> Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

on the fasteners.

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 45

5

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b If the hole is scratched :

<1> Replace the fastener at first oversize diameter (Refer to SUBTASK

571153-833-009 001 Replacement of the Fasteners at First

Oversize Diameter in the LH Wing Tank. .

(3) Subtask 571153-833-009-001 - Replacement of the Fasteners at First Oversize

Diameter in the LH Wing Tank.

Manpower Resources

Manhours 14.00

Minimum number of person 1

Subtask elapsed time 14.00

Skills NON SPECIFIC

Material necessary to do the job

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-4 49 Nut

9 EN6115V4X8 6 Bolt

10 EN6115V4X9 6 Bolt

15 EN6115V4X11 3 Bolt

16 EN6115V4X12 3 Bolt

17 EN6115V4X7 31 Bolt

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Fuel Tank Sealant

Polysulfide

09-002 As required

References

Fig. A-FBDAB

Replacement of the Fasteners on the

Front Spar

Sheet 01

Sheet 02

Sheet 03

Fig. A-FBEAB

Replacement of the Fasteners on the

STGR 8 and STGR 11

Sheet 01

Sheet 02

Sheet 03

(a) On the front spar :

Refer to Fig. A-FBDAB Sheet 01 thru Fig. A-FBDAB Sheet 03

1 Oversize the hole to the dimension given in the Fig. A-FBDAB Sheet 03.

2 Install :

31 Bolt EN6115V4X7 Item 17

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 46

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6 Bolt EN6115V4X9 Item 10

6 Bolt EN6115V4X8 Item 9

43 Nut ASNA2531-4 Item 2

NOTE: The quantities given are valid for a maximum repair

configuration.

a Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

on the fasteners.

b Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

on the fasteners.

(b) On the STGR 8 and STGR 11.

Fig. A-FBEAB Sheet 01 thru Fig. A-FBEAB Sheet 03

1 Oversize the hole to the dimension given in the Fig. A-FBEAB Sheet 03.

2 Install :

3 Bolt EN6115V4X12 Item 16

3 Bolt EN6115V4X11 Item 15

6 Nut ASNA2531-4 Item 2

NOTE: The quantities given are valid for a maximum repair

configuration.

a Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

on the fasteners.

b Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

on the fasteners.

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 47

5

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SERVICE BULLETIN

(4) Subtask 571153-833-010-001 - Replacement of the Nuts in the RH Wing Tank.

Manpower Resources

Manhours 8.50

Minimum number of person 1

Subtask elapsed time 8.50

Skills NON SPECIFIC

Material necessary to do the job

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-4 49 Nut

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Fuel Tank Sealant

Polysulfide

09-002 As required

References

Fig. A-FBDAB

Replacement of the Fasteners on the

Front Spar

Sheet 01

Sheet 02

Sheet 03

Fig. A-FBEAB

Replacement of the Fasteners on the

STGR 8 and STGR 11

Sheet 01

Sheet 02

Sheet 03

WARNING: REMOVE 50 PERCENT OF NUTS (EQUALLY SPREAD), INSTALL

NEW NUTS AND THEN 50 PERCENT REMAINING NUTS

REPLACEMENT.

(a) Replacement of the nuts on the front spar :

Fig. A-FBDAB Sheet 01 thruFig. A-FBDAB Sheet 03

1 Use the alen key to maintain the bolt and remove :

43 Nut ASNA2531-4 Item (2) Discard

NOTE: If the bolt rotates during the removal of the nuts (Refer to

SUBTASK 571153-833-011 001 Replacement of the Fasteners

at Nominal Diameter in the RH Wing Tank.

2 Use the alen key to maintain the bolt and install :

43 Nut ASNA2531-4 Item 2

NOTE: If the bolt rotates during the installation of the nuts (Refer to

SUBTASK 571153-833-011 001 Replacement of the Fasteners

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 48

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at Nominal Diameter in the RH Wing Tank.

a Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

on the nuts.

(b) Replacement of the nuts on the STGR 8 and STGR 11.

Refer to Fig. A-FBEAB Sheet 01 thruFig. A-FBEAB Sheet 03

1 Use the alen key to maintain the bolt and remove :

6 Nut ASNA2531-4 Item (2) Discard

NOTE: If the bolt rotates during the removal of the nuts (Refer to

SUBTASK 571153-833-011 001 Replacement of the Fasteners

at Nominal Diameter in the RH Wing Tank.

2 Use the alen key to maintain the bolt and install :

6 Nut ASNA2531-4 Item 2

NOTE: If the bolt rotates during the installation of the nuts (Refer to

SUBTASK 571153-833-011 001 Replacement of the Fasteners

at Nominal Diameter in the RH Wing Tank.

a Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

on the nuts.

(5) Subtask 571153-833-011-001 - Replacement of the Fasteners at Nominal Diameter

in the RH Wing Tank.

Manpower Resources

Manhours 8.50

Minimum number of person 1

Subtask elapsed time 8.50

Skills NON SPECIFIC

Material necessary to do the job

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-4 49 Nut

4 EN6115V4-8 6 Bolt

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 49

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ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

5 EN6115V4-9 6 Bolt

12 EN6115V4-12 3 Bolt

13 EN6115V4-7 31 Bolt

14 EN6115V4-11 3 Bolt

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Fuel Tank Sealant

Polysulfide

09-002 As required

References

Non Destructive Test Manual (NTM) 51-90-00, Page Block 001

Fig. A-FBDAB

Replacement of the Fasteners on the

Front Spar

Sheet 01

Sheet 02

Sheet 03

Fig. A-FBEAB

Replacement of the Fasteners on the

STGR 8 and STGR 11

Sheet 01

Sheet 02

Sheet 03

NOTE: Instruction in case of bolt rotates during the nut replacement.

(a) Remove the nut and bolt on the front spar.

Refer to Fig. A-FBDAB Sheet 01 thru Fig. A-FBDAB Sheet 03

1 Clean the hole and perform a visual inspection, looking for scratches (Refer to

NTM 51-90-00, Page Block 001).

a If no scratches :

<1> Install the new fasteners.

6 Bolt EN6115V4-9 Item 5

6 Bolt EN6115V4-8 Item 4

31 Bolt EN6115V4-7 Item 13

43 Nut ASNA2531-4 Item 2

NOTE: The quantities given are valid for a maximum repair

configuration.

<2> Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

On the fasteners (wet assembly).

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 50

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<3> Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

on the fasteners.

b If the hole is scratched :

<1> Replace the fastener at first oversize diameter (Refer to SUBTASK

571153-833-012 001 Replacement of the Fasteners at First

Oversize Diameter in the RH Wing Tank. .

(b) Remove the nut and bolt on the STGR 8 and STGR 11.

Refer to Fig. A-FBEAB Sheet 01 thru Fig. A-FBEAB Sheet 03

1 Clean the hole and perform a visual inspection, looking for scratches (Refer to

NTM 51-90-00, Page Block 001).

a If no scratches :

<1> Install the new fasteners.

3 Bolt EN6115V4-12 Item 12

3 Bolt EN6115V4-11 Item 14

6 Nut ASNA2531-4 Item 2

NOTE: The quantities given are valid for a maximum repair

configuration.

<2> Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

On the fasteners (wet assembly).

<3> Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

on the fasteners.

b If the hole is scratched :

<1> Replace the fastener at first oversize diameter (Refer to SUBTASK

571153-833-012 001 Replacement of the Fasteners at First

Oversize Diameter in the RH Wing Tank. .

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 51

5

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(6) Subtask 571153-833-012-001 - Replacement of the Fasteners at First Oversize

Diameter in the RH Wing Tank.

Manpower Resources

Manhours 14.00

Minimum number of person 1

Subtask elapsed time 14.00

Skills NON SPECIFIC

Material necessary to do the job

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-4 49 Nut

9 EN6115V4X8 6 Bolt

10 EN6115V4X9 6 Bolt

15 EN6115V4X11 3 Bolt

16 EN6115V4X12 3 Bolt

17 EN6115V4X7 31 Bolt

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Fuel Tank Sealant

Polysulfide

09-002 As required

References

Fig. A-FBDAB

Replacement of the Fasteners on the

Front Spar

Sheet 01

Sheet 02

Sheet 03

Fig. A-FBEAB

Replacement of the Fasteners on the

STGR 8 and STGR 11

Sheet 01

Sheet 02

Sheet 03

(a) On the front spar :

Refer to Fig. A-FBDAB Sheet 01 thru Fig. A-FBDAB Sheet 03

1 Oversize the hole to the dimension given in the Fig. A-FBDAB Sheet 03.

2 Install :

31 Bolt EN6115V4X7 Item 17

6 Bolt EN6115V4X9 Item 10

6 Bolt EN6115V4X8 Item 9

43 Nut ASNA2531-4 Item 2

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 52

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NOTE: The quantities given are valid for a maximum repair

configuration.

a Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

on the fasteners.

b Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

on the fasteners.

(b) On the STGR 8 and STGR 11.

Refer to Fig. A-FBEAB Sheet 01 thru Fig. A-FBEAB Sheet 03

1 Oversize the hole to the dimension given in the Fig. A-FBEAB Sheet 03.

2 Install :

3 Bolt EN6115V4X12 Item 16

3 Bolt EN6115V4X11 Item 15

6 Nut ASNA2531-4 Item 2

NOTE: The quantities given are valid for a maximum repair

configuration.

a Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

on the fasteners.

b Apply :

Fuel Tank Sealant

Polysulfide

09-002 As required

on the fasteners.

**CONF 003

None

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 53

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**CONF ALL

D. TEST

**CONF 001

None

**CONF 002

None

**CONF 003

None

**CONF ALL

E. CLOSE-UP

**CONF 001

None

**CONF 002

None

**CONF 003

None

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 54

5

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SERVICE BULLETIN

**CONF 001

RIB1

FRONT SPAR

REAR SPAR

LH SIDE SHOWN

RH SIDE SYMMETRICAL

A

A

FR36

N_SB_571153_5_BAAA_01_00

B

Figure A-FBAAA - Sheet 01

Area to be Inspected on the Front Spar

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 55

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**CONF 001

VIEW LOOKING FWD

LH SIDE SHOWN

RH SIDE SYMMETRICAL

HEAD ON VISIBLE FACE

NOTES:

N

HEAD ON HIDDEN SIDE F

FASTENERS TO BE INSPECTED

FASTENERS TO BE INSPECTED

N

F

FR36 RIB1

B

N_SB_571153_5_BAAA_02_02

Figure A-FBAAA - Sheet 02

Area to be Inspected on the Front Spar

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 56

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**CONF 002

RIB1

FRONT SPAR

REAR SPAR

LH SIDE SHOWN

RH SIDE SYMMETRICAL

A

A

FR36

B

N_SB_571153_5_BAAB_01_00

Figure A-FBAAB - Sheet 01

Area to be Inspected on the Front Spar

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 57

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**CONF 002

VIEW LOOKING FWD

LH SIDE SHOWN

RH SIDE SYMMETRICAL

HEAD ON VISIBLE FACE

NOTES:

N

HEAD ON HIDDEN SIDE F

FASTENERS TO BE INSPECTED

FASTENERS TO BE INSPECTED

N

F

B

FR36 RIB1

N_SB_571153_5_BAAB_02_02

Figure A-FBAAB - Sheet 02

Area to be Inspected on the Front Spar

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 58

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**CONF 001

RIB1

FRONT SPAR

REAR SPAR

LH SIDE SHOWN

RH SIDE SYMMETRICAL

A

A

FR36

N_SB_571153_5_BBAA_01_00

C

B

STRINGER 8

JOINT FITTING

STRINGER 11

JOINT FITTING

Figure A-FBBAA - Sheet 01

Area to be Inspected on the STGR 8 and STGR 11

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 59

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**CONF 001

NOTE:

FASTENERS TO BE INSPECTED

RIB1

RIB1

STGR11

STGR8

B

C

N_SB_571153_5_BBAA_02_01

Figure A-FBBAA - Sheet 02

Area to be Inspected on the STGR 8 and STGR 11

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 60

5

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SERVICE BULLETIN

**CONF 002

RIB1

FRONT SPAR

REAR SPAR

LH SIDE SHOWN

RH SIDE SYMMETRICAL

A

A

FR36

C

B

STRINGER 8

JOINT FITTING

STRINGER 11

JOINT FITTING

N_SB_571153_5_BBAB_01_00

Figure A-FBBAB - Sheet 01

Area to be Inspected on the STGR 8 and STGR 11

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 61

5

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**CONF 002

NOTE:

FASTENERS TO BE INSPECTED

RIB1

RIB1

STGR11

STGR8

B

C

N_SB_571153_5_BBAB_02_01

Figure A-FBBAB - Sheet 02

Area to be Inspected on the STGR 8 and STGR 11

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 62

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**CONF 001

AT THRESHOLD GIVEN IN THE

PLANNING INFORMATION PARAGRAPH E.(2).

NO MISSING

DO A DETAILED VISUAL INSPECTION OF THE NUTS

REPLACE THE NUT AT

NOMINAL DIAMETER

REFER TO REPAIR SUBTACK

NUT YES

CRACKED NO NUT YES

ROTATE NO BOLT YES

SEND INSPECTION

REPORT TO AIRBUS

NO FURTHER ACTION

NO FURTHER ACTION

REPLACE THE NUT AND BOLT

FASTENER AT FIRST OVERSIZE

REFER TO REPAIR SUBTASK

571153−833−004−001

SEND INSPECTION

REPORT TO AIRBUS

571153−833−007−001

571153−833−003−001

571153−833−006−001

QUESTION

ACTION

FINDING

NOTE:

01 THIS INFORMATION IS TO BE RECORDED IN THE INSPECTION REPORT

01

REFER TO REPAIR SUBTASK

571153−833−001−001

571153−833−005−001

N_SB_571153_5_BCAA_01_02

FIND THE MISSING

PARTS

Figure A-FBCAA - Sheet 01

Flow Chart

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 63

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**CONF 002

AT THRESHOLD GIVEN IN THE

PLANNING INFORMATION PARAGRAPH E.(2).

NO MISSING

DO A DETAILED VISUAL INSPECTION OF THE NUTS

REPLACE THE NUT AT

NOMINAL DIAMETER

REFER TO REPAIR SUBTACK

NUT YES

CRACKED NO NUT YES

ROTATE NO BOLT YES

SEND INSPECTION

REPORT TO AIRBUS

NO FURTHER ACTION

NO FURTHER ACTION

REPLACE THE NUT AND BOLT

FASTENER AT FIRST OVERSIZE

REFER TO REPAIR SUBTASK

571153−833−009−001

SEND INSPECTION

REPORT TO AIRBUS

571153−833−012−001

571153−833−008−001

571153−833−011−001

QUESTION

ACTION

FINDING

NOTE:

01 THIS INFORMATION IS TO BE RECORDED IN THE INSPECTION REPORT

01

REFER TO REPAIR SUBTASK

571153−833−002−001

571153−833−010−001

N_SB_571153_5_BCAB_01_02

FIND THE MISSING

PARTS

Figure A-FBCAB - Sheet 01

Flow Chart

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 64

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**CONF 001

RIB1

FRONT SPAR

REAR SPAR

LH SIDE SHOWN

RH SIDE SYMMETRICAL

A

A

FR36

B

N_SB_571153_5_BDAA_01_00

Figure A-FBDAA - Sheet 01

Replacement of the Fasteners on the Front Spar

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 65

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**CONF 001

VIEW LOOKING FWD

LH SIDE SHOWN

RH SIDE SYMMETRICAL

FR36 RIB1

B

N_SB_571153_5_BDAA_02_03

Figure A-FBDAA - Sheet 02

Replacement of the Fasteners on the Front Spar

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 66

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**CONF 001

HOLE

SYMBOL

OLD PN AFTER DESCRIPTION

ASNA2531−4 NUT

ASNA2531−4 NUT

ASNA2531−4 NUT

ASNA2531−4 NUT

ASNA2531−4 NUT

ITEM

NEW

ITEM

(2) 2

(2) 2

(2) 2

(2) 2

(2) 2

N

N

N

F

N

HOLE

SYMBOL

OLD

OR

PN AFTER DESCRIPTION

ASNA2531−4 NUT

EN6115V4−5 BOLT

ASNA2531−4 NUT

EN6115V4−6 BOLT

ASNA2531−4 NUT

EN6115V4−8 BOLT

ASNA2531−4 NUT

EN6115V4−9 BOLT

ASNA2531−4 NUT

EN6115V4−10 BOLT

ITEM

NEW

ITEM

N

N

N

F

N

REMARKS

REMARKS

WET

ASSEMBLY

WET

ASSEMBLY

WET

ASSEMBLY

WET

ASSEMBLY

WET

ASSEMBLY

01

02

02

02

02

02

02

01

02

01

02

01

02

01

02

(2) 2

(1) 1

(2) 2

(3) 3

(2) 2

(4) 4

(2) 2

(5) 5

(2) 2

(6) 6

REPLACEMENT OF THE NUT

REPLACEMENT OF THE FASTENERS AT NOMINAL DIAMETER

N_SB_571153_5_BDAA_03_02

Figure A-FBDAA - Sheet 03

Replacement of the Fasteners on the Front Spar

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 67

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**CONF 001

HOLE

SYMBOL

OLD

OR

PN AFTER DESCRIPTION REMARKS

HOLE DIAMETER

MIN MAX

6.706 mm

(0.264 in)

6.747 mm

(0.2656 in)

ASNA2531−4 NUT WET

EN6115V4X5 BOLT

ASNA2531−4 NUT

EN6115V4X6 BOLT

6.706 mm

(0.264 in)

6.747 mm

(0.2656 in)

ASNA2531−4 NUT

EN6115V4X8 BOLT

ASNA2531−4 NUT

EN6115V4X9 BOLT

6.706 mm

(0.264 in)

6.747 mm

(0.2656 in)

ASNA2531−4 NUT

EN6115V4X10 BOLT

ITEM

NEW

ITEM

ASSEMBLY

WET

ASSEMBLY

WET

ASSEMBLY

WET

ASSEMBLY

WET

ASSEMBLY

(2) 2

(1)

(2)

7

2

(3) 8

(2) 2

(4) 9

(2) 2

(5) 10

(2) 2

(6) 11

6.706 mm

(0.264 in)

6.747 mm

(0.2656 in)

6.706 mm

(0.264 in)

6.747 mm

(0.2656 in)

HEAD ON VISIBLE FACE

NOTES:

N

HEAD ON HIDDEN SIDE F

01 APPLY MAT. No. 09−002 ON ALL FASTENERS (WET ASSEMBLY)

02 APPLY MAT. No. 09−002 ON ALL FASTENERS

N

N

N

F

N

01

02

01

02

01

02

01

02

01

02

REPLACEMENT OF THE FASTENERS AT FIRST OVERSIZE DIAMETER

N_SB_571153_5_BDAA_04_05

Figure A-FBDAA - Sheet 04

Replacement of the Fasteners on the Front Spar

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 68

5

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@A318/A319/A320/A321

SERVICE BULLETIN

**CONF 002

RIB1

FRONT SPAR

REAR SPAR

LH SIDE SHOWN

RH SIDE SYMMETRICAL

A

A

FR36

B

N_SB_571153_5_BDAB_01_00

Figure A-FBDAB - Sheet 01

Replacement of the Fasteners on the Front Spar

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 69

5

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@A318/A319/A320/A321

SERVICE BULLETIN

**CONF 002

VIEW LOOKING FWD

LH SIDE SHOWN

RH SIDE SYMMETRICAL

FR36 RIB1

B

N_SB_571153_5_BDAB_02_03

Figure A-FBDAB - Sheet 02

Replacement of the Fasteners on the Front Spar

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 70

5

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SERVICE BULLETIN

**CONF 002

HOLE

SYMBOL

OLD PN AFTER DESCRIPTION

ASNA2531−4 NUT

ASNA2531−4 NUT

ASNA2531−4 NUT

ITEM

NEW

ITEM

(2) 2

(2) 2

(2) 2

N

F

HOLE

SYMBOL

OLD

OR

PN AFTER DESCRIPTION

ASNA2531−4 NUT

EN6115V4−7 BOLT

ASNA2531−4 NUT

EN6115V4−9 BOLT

ASNA2531−4 NUT

EN6115V4−9 BOLT

ITEM

NEW

ITEM

REMARKS

REMARKS

WET

ASSEMBLY

WET

ASSEMBLY

WET

ASSEMBLY

01

02

02

02

02

01

02

02

REPLACEMENT OF THE NUT

REPLACEMENT OF THE FASTENERS AT NOMINAL DIAMETER

HOLE

SYMBOL

OLD PN AFTER DESCRIPTION REMARKS

HOLE DIAMETER

MIN MAX

6.706 mm

(0.264 in)

6.747 mm

(0.2656 in)

ASNA2531−4 NUT WET

EN6115V4X7 BOLT

ASNA2531−4 NUT

EN6115V4X9 BOLT

6.706 mm

(0.264 in)

6.747 mm

(0.2656 in)

ASNA2531−4 NUT

EN6115V4X9 BOLT

ITEM

NEW

ITEM

ASSEMBLY

WET

ASSEMBLY

WET

ASSEMBLY

6.706 mm

(0.264 in)

6.747 mm

(0.2656 in)

HEAD ON VISIBLE FACE

NOTES:

N

HEAD ON HIDDEN SIDE F

01 APPLY MAT. No. 09−002 ON ALL FASTENERS (WET ASSEMBLY)

02 APPLY MAT. No. 09−002 ON ALL FASTENERS

01

02

01

02

01

02

REPLACEMENT OF THE FASTENERS AT FIRST OVERSIZE DIAMETER

N

N

F

N

N

F

N

01

(2) 2

(2) 2

(5) 5

(2) 2

(5) 5

(5)

(5)

(2) 2

(2) 2

(2)

ASNA2531−4 NUT

EN6115V4−8 BOLT

WET

ASSEMBLY

01

02

01

OR

6.706 mm

(0.264 in)

6.747 mm

(0.2656 in)

ASNA2531−4 NUT

EN6115V4X8 BOLT

WET

ASSEMBLY 01

02

N

2

(8) 13

(8) 17

10

10

2

4

2

9

(2)

(4)

(2)

(4)

N

ASNA2531−4 NUT 02

N

2 2

N_SB_571153_5_BDAB_03_05

Figure A-FBDAB - Sheet 03

Replacement of the Fasteners on the Front Spar

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 71

5

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@A318/A319/A320/A321

SERVICE BULLETIN

**CONF 001

RIB1

FRONT SPAR

REAR SPAR

LH SIDE SHOWN

RH SIDE SYMMETRICAL

A

A

FR36

C

B

STRINGER 8

JOINT FITTING

STRINGER 11

JOINT FITTING

N_SB_571153_5_BEAA_01_00

Figure A-FBEAA - Sheet 01

Replacement of the Fasteners on the STGR 8 and STGR 11

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 72

5

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@A318/A319/A320/A321

SERVICE BULLETIN

**CONF 001

B

C

RIB1

RIB1

STGR11

STGR8

N_SB_571153_5_BEAA_02_01

Figure A-FBEAA - Sheet 02

Replacement of the Fasteners on the STGR 8 and STGR 11

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 73

5

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@A318/A319/A320/A321

SERVICE BULLETIN

**CONF 001

HOLE

SYMBOL

OLD PN AFTER DESCRIPTION

ASNA2531−4 NUT

ITEM

NEW

ITEM

HOLE

SYMBOL

OLD

OR

PN AFTER DESCRIPTION

ASNA2531−4 NUT

EN6115V4−12 BOLT

ITEM

NEW

ITEM

REMARKS

REMARKS

WET

ASSEMBLY 01

02

02

HOLE

SYMBOL

OLD PN AFTER DESCRIPTION REMARKS

HOLE DIAMETER

MIN MAX

6.706 mm

(0.264 in)

6.747 mm

(0.2656 in)

ASNA2531−4 NUT WET

EN6115V4X12 BOLT

ITEM

NEW

ITEM

ASSEMBLY

01 APPLY MAT. No. 09−002 ON ALL FASTENERS (WET ASSEMBLY)

02 APPLY MAT. No. 09−002 ON ALL FASTENERS

01

02

NOTE:

OR

12

(2) 2

(2) 2

(2) 2

(7)

(7) 16

N_SB_571153_5_BEAA_03_04

Figure A-FBEAA - Sheet 03

Replacement of the Fasteners on the STGR 8 and STGR 11

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 74

5

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@A318/A319/A320/A321

SERVICE BULLETIN

**CONF 002

RIB1

FRONT SPAR

REAR SPAR

LH SIDE SHOWN

RH SIDE SYMMETRICAL

A

A

FR36

C

B

STRINGER 8

JOINT FITTING

STRINGER 11

JOINT FITTING

N_SB_571153_5_BEAB_01_00

Figure A-FBEAB - Sheet 01

Replacement of the Fasteners on the STGR 8 and STGR 11

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 75

5

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@A318/A319/A320/A321

SERVICE BULLETIN

**CONF 002

B

C

RIB1

RIB1

STGR11

STGR8

N_SB_571153_5_BEAB_02_01

Figure A-FBEAB - Sheet 02

Replacement of the Fasteners on the STGR 8 and STGR 11

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 76

5

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@A318/A319/A320/A321

SERVICE BULLETIN

**CONF 002

HOLE

SYMBOL

OLD PN AFTER DESCRIPTION

ASNA2531−4 NUT

ITEM

NEW

ITEM

HOLE

SYMBOL

OLD PN AFTER DESCRIPTION

ASNA2531−4 NUT

EN6115V4−12 BOLT

ITEM

NEW

ITEM

REMARKS

REMARKS

WET

ASSEMBLY 01

02

02

HOLE

SYMBOL

OLD PN AFTER DESCRIPTION REMARKS

HOLE DIAMETER

MIN MAX

6.706 mm

(0.264 in)

6.747 mm

(0.2656 in)

ASNA2531−4 NUT WET

EN6115V4X12 BOLT

ITEM

NEW

ITEM

ASSEMBLY

01 APPLY MAT. No. 09−002 ON ALL FASTENERS (WET ASSEMBLY)

02 APPLY MAT. No. 09−002 ON ALL FASTENERS

01

02

NOTE:

12

(2) 2

(2) 2

(2) 2

(7)

(7) 16

ASNA2531−4 NUT

ASNA2531−4 NUT

EN6115V4−11 BOLT

WET

ASSEMBLY 01

02

02

6.706 mm

(0.264 in)

6.747 mm

(0.2656 in)

ASNA2531−4 NUT WET

EN6115V4X11 BOLT ASSEMBLY 01

02

(2) (2)

(2) 2

(2) 22

(14) 15

(14) 14

OR REPLACEMENT OF THE FASTENERS AT NOMINAL DIAMETER

REPLACEMENT OF THE NUT

OR REPLACEMENT OF THE FASTENERS AT FIRST OVERSIZE DIAMETER

N_SB_571153_5_BEAB_03_05

Figure A-FBEAB - Sheet 03

Replacement of the Fasteners on the STGR 8 and STGR 11

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 77

5

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@A318/A319/A320/A321

SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 78

5

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@A318/A319/A320/A321

SERVICE BULLETIN

Appendix 01 : Inspection Report

**CONF 001 thru 002

(1) INSPECTION REPORT

(a) The result of the inspection, including no findings, replacement or actions to be done, must

be forwarded to AIRBUS Department SEES4 on the attached inspection report sheet.

**CONF 003

None

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 1

5

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@A318/A319/A320/A321

SERVICE BULLETIN

Appendix 01 : Inspection Report

**CONF 001

RIB1

FRONT SPAR

REAR SPAR

LH SIDE SHOWN

RH SIDE SYMMETRICAL

A

A

FR36

STRINGER 8

JOINT FITTING

STRINGER 11

JOINT FITTING

N_SB_571153_5_AAAA_01_00

B D

C

Figure A-FAAAA - Sheet 01

Inspection Report

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 2

5

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@A318/A319/A320/A321

SERVICE BULLETIN

Appendix 01 : Inspection Report

**CONF 001

VIEW LOOKING FWD

LH SIDE SHOWN

RH SIDE SYMMETRICAL

HEAD ON VISIBLE FACE

NOTES:

N

HEAD ON HIDDEN SIDE F

FASTENERS TO BE INSPECTED

FASTENERS TO BE INSPECTED

N

F

RIB1

H1

H2

H3

H4

H5

H6

H7

H8

H9

H10

H11

H12

H13

H14

H15

H16

H17

H18

H19

H20

H21

H25 H24 H23 H22

H26 H53

H52

H27 H49

H50

H51

H48 H28

H29

H30

H31

H32

H47

H46

H45

H33

H44

H43 H34

H42

H41

H40

H39

H35

H36

H37

H38

FR36

B

N_SB_571153_5_AAAA_02_02

Figure A-FAAAA - Sheet 02

Inspection Report

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 3

5

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@A318/A319/A320/A321

SERVICE BULLETIN

Appendix 01 : Inspection Report

**CONF 001

NOTE:

FASTENERS TO BE INSPECTED

H54 H55 H56 H57 H58

H59

H60

H61

H62

H63

RIB1

RIB1

STGR11

STGR8

C

D

N_SB_571153_5_AAAA_03_01

Figure A-FAAAA - Sheet 03

Inspection Report

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 4

5

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@A318/A319/A320/A321

SERVICE BULLETIN

Appendix 01 : Inspection Report

**CONF 001

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A320−57−1153

DATE OF INSPECTION :

INSPECTION METHOD : DETAILED VISUAL

INSPECTION

INSPECTION REPORT

PLEASE RECORD OTHER FINDINGS :

WING TO FUSELAGE JONCTION (LH SIDE)

FASTENERS

H1

REPLACED

AT

FIRST

OVERSIZE

DIAMETER

FASTENERS

REPLACED

AT

NOMINAL

DIAMETER

NUT

REPLACED HOLE

SCRATCHED

(BOLT

ROTATED)

NUT

CRACKED

NUT

MISSING

YES NO YES NO YES NO YES NO YES NO YES NO

H2

H3

H4

H5

H6

H7

H8

H9

H10

H11

H12

H13

H14

H15

H16

H17

H18

H19

H20

H21

AT

NOMINAL

DIAMETER

N_SB_571153_5_AAAA_04_02

Figure A-FAAAA - Sheet 04

Inspection Report

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 5

5

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@A318/A319/A320/A321

SERVICE BULLETIN

Appendix 01 : Inspection Report

**CONF 001

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A320−57−1153

DATE OF INSPECTION :

INSPECTION METHOD : DETAILED VISUAL

INSPECTION

INSPECTION REPORT

PLEASE RECORD OTHER FINDINGS :

WING TO FUSELAGE JONCTION (LH SIDE)

FASTENERS

H22

REPLACED

AT

FIRST

OVERSIZE

DIAMETER

FASTENERS

REPLACED

AT

NOMINAL

DIAMETER

NUT

CRACKED

NUT

MISSING

YES NO YES NO YES NO YES NO YES NO YES NO

H23

H24

H25

H26

H27

H28

H29

H30

H31

H32

H33

H34

H35

H36

H37

H38

H39

H40

H41

H42

NUT

REPLACED HOLE

SCRATCHED

(BOLT

ROTATED)

AT

NOMINAL

DIAMETER

N_SB_571153_5_AAAA_05_02

Figure A-FAAAA - Sheet 05

Inspection Report

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 6

5

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@A318/A319/A320/A321

SERVICE BULLETIN

Appendix 01 : Inspection Report

**CONF 001

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A320−57−1153

DATE OF INSPECTION :

INSPECTION METHOD : DETAILED VISUAL

INSPECTION

INSPECTION REPORT

PLEASE RECORD OTHER FINDINGS :

WING TO FUSELAGE JONCTION (LH SIDE)

FASTENERS

H43

REPLACED

AT

FIRST

OVERSIZE

DIAMETER

FASTENERS

REPLACED

AT

NOMINAL

DIAMETER

NUT

CRACKED

NUT

MISSING

YES NO YES NO YES NO YES NO YES NO YES NO

H44

H45

H46

H47

H48

H49

H50

H51

H52

H53

H54

H55

H56

H57

H58

H59

H60

H61

H62

H63

NUT

REPLACED HOLE

SCRATCHED

(BOLT

ROTATED)

AT

NOMINAL

DIAMETER

N_SB_571153_5_AAAA_06_02

Figure A-FAAAA - Sheet 06

Inspection Report

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 7

5

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@A318/A319/A320/A321

SERVICE BULLETIN

Appendix 01 : Inspection Report

**CONF 001

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A320−57−1153

DATE OF INSPECTION :

INSPECTION METHOD : DETAILED VISUAL

INSPECTION

INSPECTION REPORT

PLEASE RECORD OTHER FINDINGS :

WING TO FUSELAGE JONCTION (RH SIDE)

FASTENERS

H1

REPLACED

AT

FIRST

OVERSIZE

DIAMETER

FASTENERS

REPLACED

AT

NOMINAL

DIAMETER

NUT

CRACKED

NUT

MISSING

YES NO YES NO YES NO YES NO YES NO YES NO

H2

H3

H4

H5

H6

H7

H8

H9

H10

H11

H12

H13

H14

H15

H16

H17

H18

H19

H20

H21

NUT

REPLACED HOLE

SCRATCHED

(BOLT

ROTATED)

AT

NOMINAL

DIAMETER

N_SB_571153_5_AAAA_07_02

Figure A-FAAAA - Sheet 07

Inspection Report

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 8

5

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@A318/A319/A320/A321

SERVICE BULLETIN

Appendix 01 : Inspection Report

**CONF 001

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A320−57−1153

DATE OF INSPECTION :

INSPECTION METHOD : DETAILED VISUAL

INSPECTION

INSPECTION REPORT

PLEASE RECORD OTHER FINDINGS :

WING TO FUSELAGE JONCTION (RH SIDE)

FASTENERS

H22

REPLACED

AT

FIRST

OVERSIZE

DIAMETER

FASTENERS

REPLACED

AT

NOMINAL

DIAMETER

NUT

CRACKED

NUT

MISSING

YES NO YES NO YES NO YES NO YES NO YES NO

H23

H24

H25

H26

H27

H28

H29

H30

H31

H32

H33

H34

H35

H36

H37

H38

H39

H40

H41

H42

NUT

REPLACED HOLE

SCRATCHED

(BOLT

ROTATED)

AT

NOMINAL

DIAMETER

N_SB_571153_5_AAAA_08_02

Figure A-FAAAA - Sheet 08

Inspection Report

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 9

5

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@A318/A319/A320/A321

SERVICE BULLETIN

Appendix 01 : Inspection Report

**CONF 001

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A320−57−1153

DATE OF INSPECTION :

INSPECTION METHOD : DETAILED VISUAL

INSPECTION

INSPECTION REPORT

PLEASE RECORD OTHER FINDINGS :

WING TO FUSELAGE JONCTION (RH SIDE)

FASTENERS

H43

REPLACED

AT

FIRST

OVERSIZE

DIAMETER

FASTENERS

REPLACED

AT

NOMINAL

DIAMETER

NUT

CRACKED

NUT

MISSING

YES NO YES NO YES NO YES NO YES NO YES NO

H44

H45

H46

H47

H48

H49

H50

H51

H52

H53

H54

H55

H56

H57

H58

H59

H60

H61

H62

H63

NUT

REPLACED HOLE

SCRATCHED

(BOLT

ROTATED)

AT

NOMINAL

DIAMETER

N_SB_571153_5_AAAA_09_02

Figure A-FAAAA - Sheet 09

Inspection Report

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 10

5

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SERVICE BULLETIN

Appendix 01 : Inspection Report

**CONF 002

RIB1

FRONT SPAR

REAR SPAR

LH SIDE SHOWN

RH SIDE SYMMETRICAL

A

A

FR36

STRINGER 8

JOINT FITTING

STRINGER 11

JOINT FITTING

B D

C

N_SB_571153_5_AAAB_01_00

Figure A-FAAAB - Sheet 01

Inspection Report

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 11

5

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@A318/A319/A320/A321

SERVICE BULLETIN

Appendix 01 : Inspection Report

**CONF 002

VIEW LOOKING FWD

LH SIDE SHOWN

RH SIDE SYMMETRICAL

HEAD ON VISIBLE FACE

NOTES:

N

HEAD ON HIDDEN SIDE F

FASTENERS TO BE INSPECTED

FASTENERS TO BE INSPECTED

N

F

B

FR36 RIB1

H1

H2

H3

H4

H5

H6

H7

H10

H12

H8

H9

H11

H14 H13 H15

H16

H43

H42

H17 H39

H40

H41

H18 H38

H19

H20

H21

H22

H37

H36

H35

H23

H34

H33

H24

H32

H30

H31

H29

H25

H28

H27

H26

N_SB_571153_5_AAAB_02_02

Figure A-FAAAB - Sheet 02

Inspection Report

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 12

5

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@A318/A319/A320/A321

SERVICE BULLETIN

Appendix 01 : Inspection Report

**CONF 002

NOTE:

FASTENERS TO BE INSPECTED

H44 H45 H46

H47

H48

H49

RIB1

RIB1

STGR11

STGR8

C

D

N_SB_571153_5_AAAB_03_01

Figure A-FAAAB - Sheet 03

Inspection Report

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 13

5

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@A318/A319/A320/A321

SERVICE BULLETIN

Appendix 01 : Inspection Report

**CONF 002

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A320−57−1153

DATE OF INSPECTION :

INSPECTION METHOD : DETAILED VISUAL

INSPECTION

INSPECTION REPORT

PLEASE RECORD OTHER FINDINGS :

WING TO FUSELAGE JONCTION (LH SIDE)

FASTENERS

H1

REPLACED

AT

FIRST

OVERSIZE

DIAMETER

FASTENERS

REPLACED

AT

NOMINAL

DIAMETER

NUT

REPLACED HOLE

SCRATCHED

(BOLT

ROTATED)

NUT

CRACKED

NUT

MISSING

YES NO YES NO YES NO YES NO YES NO YES NO

H2

H3

H4

H5

H6

H7

H8

H9

H10

H11

H12

H13

H14

H15

H16

H17

H18

H19

H20

AT

NOMINAL

DIAMETER

N_SB_571153_5_AAAB_04_02

Figure A-FAAAB - Sheet 04

Inspection Report

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 14

5

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@A318/A319/A320/A321

SERVICE BULLETIN

Appendix 01 : Inspection Report

**CONF 002

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A320−57−1153

DATE OF INSPECTION :

INSPECTION METHOD : DETAILED VISUAL

INSPECTION

INSPECTION REPORT

PLEASE RECORD OTHER FINDINGS :

WING TO FUSELAGE JONCTION (LH SIDE)

FASTENERS

H21

REPLACED

AT

FIRST

OVERSIZE

DIAMETER

FASTENERS

REPLACED

AT

NOMINAL

DIAMETER

NUT

CRACKED

NUT

MISSING

YES NO YES NO YES NO YES NO YES NO YES NO

H22

H23

H24

H25

H26

H27

H28

H29

H30

H31

H32

H33

H34

H35

H36

H37

H38

H39

H40

NUT

REPLACED HOLE

SCRATCHED

(BOLT

ROTATED)

AT

NOMINAL

DIAMETER

N_SB_571153_5_AAAB_05_02

Figure A-FAAAB - Sheet 05

Inspection Report

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 15

5

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@A318/A319/A320/A321

SERVICE BULLETIN

Appendix 01 : Inspection Report

**CONF 002

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A320−57−1153

DATE OF INSPECTION :

INSPECTION METHOD : DETAILED VISUAL

INSPECTION

INSPECTION REPORT

PLEASE RECORD OTHER FINDINGS :

WING TO FUSELAGE JONCTION (LH SIDE)

FASTENERS

H41

REPLACED

AT

FIRST

OVERSIZE

DIAMETER

FASTENERS

REPLACED

AT

NOMINAL

DIAMETER

NUT

CRACKED

NUT

MISSING

YES NO YES NO YES NO YES NO YES NO YES NO

H42

H43

H44

H45

H46

H47

H48

H49

NUT

REPLACED HOLE

SCRATCHED

(BOLT

ROTATED)

AT

NOMINAL

DIAMETER

N_SB_571153_5_AAAB_06_02

Figure A-FAAAB - Sheet 06

Inspection Report

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 16

5

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@A318/A319/A320/A321

SERVICE BULLETIN

Appendix 01 : Inspection Report

**CONF 002

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A320−57−1153

DATE OF INSPECTION :

INSPECTION METHOD : DETAILED VISUAL

INSPECTION

INSPECTION REPORT

PLEASE RECORD OTHER FINDINGS :

WING TO FUSELAGE JONCTION (RH SIDE)

FASTENERS

H1

REPLACED

AT

FIRST

OVERSIZE

DIAMETER

FASTENERS

REPLACED

AT

NOMINAL

DIAMETER

NUT

REPLACED HOLE

SCRATCHED

(BOLT

ROTATED)

NUT

CRACKED

NUT

MISSING

YES NO YES NO YES NO YES NO YES NO YES NO

H2

H3

H4

H5

H6

H7

H8

H9

H10

H11

H12

H13

H14

H15

H16

H17

H18

H19

H20

AT

NOMINAL

DIAMETER

N_SB_571153_5_AAAB_07_02

Figure A-FAAAB - Sheet 07

Inspection Report

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 17

5

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@A318/A319/A320/A321

SERVICE BULLETIN

Appendix 01 : Inspection Report

**CONF 002

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A320−57−1153

DATE OF INSPECTION :

INSPECTION METHOD : DETAILED VISUAL

INSPECTION

INSPECTION REPORT

PLEASE RECORD OTHER FINDINGS :

WING TO FUSELAGE JONCTION (RH SIDE)

FASTENERS

H21

REPLACED

AT

FIRST

OVERSIZE

DIAMETER

FASTENERS

REPLACED

AT

NOMINAL

DIAMETER

NUT

CRACKED

NUT

MISSING

YES NO YES NO YES NO YES NO YES NO YES NO

H22

H23

H24

H25

H26

H27

H28

H29

H30

H31

H32

H33

H34

H35

H36

H37

H38

H39

H40

NUT

REPLACED HOLE

SCRATCHED

(BOLT

ROTATED)

AT

NOMINAL

DIAMETER

N_SB_571153_5_AAAB_08_02

Figure A-FAAAB - Sheet 08

Inspection Report

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 18

5

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@A318/A319/A320/A321

SERVICE BULLETIN

Appendix 01 : Inspection Report

**CONF 002

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A320−57−1153

DATE OF INSPECTION :

INSPECTION METHOD : DETAILED VISUAL

INSPECTION

INSPECTION REPORT

PLEASE RECORD OTHER FINDINGS :

WING TO FUSELAGE JONCTION (RH SIDE)

FASTENERS

H41

REPLACED

AT

FIRST

OVERSIZE

DIAMETER

FASTENERS

REPLACED

AT

NOMINAL

DIAMETER

NUT

CRACKED

NUT

MISSING

YES NO YES NO YES NO YES NO YES NO YES NO

H42

H43

H44

H45

H46

H47

H48

H49

NUT

REPLACED HOLE

SCRATCHED

(BOLT

ROTATED)

AT

NOMINAL

DIAMETER

N_SB_571153_5_AAAB_09_02

Figure A-FAAAB - Sheet 09

Inspection Report

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 19

5

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@A318/A319/A320/A321

SERVICE BULLETIN

Appendix 01 : Inspection Report

This Page Intentionally Left Blank

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 20

5

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SERVICE BULLETIN

Appendix 02 : Elapsed Time Assumption of the Inspection

**CONF 001

(1) For detail concerning the elapsed time assumptions, refer to the Gantt chart shown below.

**CONF 002

(1) For detail concerning the elapsed time assumptions, refer to the Gantt chart shown below.

**CONF 003

None

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 1

5

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@A318/A319/A320/A321

SERVICE BULLETIN

Appendix 02 : Elapsed Time Assumption of the Inspection

**CONF 001

N_SB_571153_5_ABAA_01_00

ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A320−57−1153

ELAPSED TIME

(HOURS)

NOTE: THIS CHART IS ONLY A PROPOSAL.

OPERATORS MAY DETERMINE THAT ANOTHER WAY

TO DO THE WORK IS MORE SUITABLE FOR THEM.

MH ET PER

MH:

ET:

PER:

MANHOURS

ELAPSED TIME

NUMBER OF PERSONS

TOTAL MANHOURS (MH)

ELAPSED TIME (ET)

72.50

36.50

STEPS

4.00 2.00 2

0

GET ACCESS 27.00 13.50 2

5 10 40

REMOVAL ON THE 11.00 5.50 2 SEALANT

INSPECTION ON THE

NUTS

TEST 0.50 0.50 1

CLOSE−UP 30.00 15.00 2

15 20 25 30 35

Figure A-FABAA - Sheet 01

Elapsed Time Assumption of the Inspection

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 2

5

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@A318/A319/A320/A321

SERVICE BULLETIN

Appendix 02 : Elapsed Time Assumption of the Inspection

**CONF 002

ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A320−57−1153

ELAPSED TIME

(HOURS)

NOTE: THIS CHART IS ONLY A PROPOSAL.

OPERATORS MAY DETERMINE THAT ANOTHER WAY

TO DO THE WORK IS MORE SUITABLE FOR THEM.

MH ET PER

MH:

ET:

PER:

MANHOURS

ELAPSED TIME

NUMBER OF PERSONS

TOTAL MANHOURS (MH)

ELAPSED TIME (ET)

68.50

34.50

STEPS

3.00 1.50 2

0

GET ACCESS 27.00 13.50 2

5 10 40

REMOVAL ON THE 8.00 4.00 2 SEALANT

INSPECTION ON THE

NUTS

TEST 0.50 0.50 1

CLOSE−UP 30.00 15.00 2

15 20 25 30 35

N_SB_571153_5_ABAB_01_02

Figure A-FABAB - Sheet 01

Elapsed Time Assumption of the Inspection

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 3

5

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@A318/A319/A320/A321

SERVICE BULLETIN

Appendix 02 : Elapsed Time Assumption of the Inspection

This Page Intentionally Left Blank

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 4

5

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@A318/A319/A320/A321

SERVICE BULLETIN

Appendix 03 : Elapsed Time Assumption of the Repair

**CONF 001

(1) For detail concerning the elapsed time assumptions, refer to the Gantt chart shown below.

**CONF 002

(1) For detail concerning the elapsed time assumptions, refer to the Gantt chart shown below.

**CONF 003

None

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 1

5

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@A318/A319/A320/A321

SERVICE BULLETIN

Appendix 03 : Elapsed Time Assumption of the Repair

**CONF 001

ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A320−57−1153

ELAPSED TIME

(HOURS)

NOTE: THIS CHART IS ONLY A PROPOSAL.

OPERATORS MAY DETERMINE THAT ANOTHER WAY

TO DO THE WORK IS MORE SUITABLE FOR THEM.

MH ET PER

MH:

ET:

PER:

MANHOURS

ELAPSED TIME

NUMBER OF PERSONS

TOTAL MANHOURS (MH)

ELAPSED TIME (ET)

24.00

12.00

STEPS

0 5 10 20

11.00 5.50 2

2.00 1.00 2 APPLICATION OF

THE SEALANT

REPLACE THE

NUTS

15

N_SB_571153_5_ACAA_01_00

VALID ONLY IF BOLT ROTATE DURING THE REMOVAL OF THE NUT

11.00 5.50 2 INSPECTION ON

THE HOLE

Figure A-FACAA - Sheet 01

Elapsed Time Assumption of the Repair

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 2

5

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SERVICE BULLETIN

Appendix 03 : Elapsed Time Assumption of the Repair

**CONF 001

ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A320−57−1153

ELAPSED TIME

(HOURS)

NOTE: THIS CHART IS ONLY A PROPOSAL.

OPERATORS MAY DETERMINE THAT ANOTHER WAY

TO DO THE WORK IS MORE SUITABLE FOR THEM.

MH ET PER

MH:

ET:

PER:

MANHOURS

ELAPSED TIME

NUMBER OF PERSONS

TOTAL MANHOURS (MH)

ELAPSED TIME (ET)

24.00

12.00

STEPS

0 5 10 20

22.00 11.00 2

2.00 1.00 2 APPLICATION OF

THE SEALANT

REPLACE THE

FASTENERS AT

NOMINAL

15

FOR ONE FASTENER, TAKES APPROXIMATELY 10 MINUTES.

DIAMETER

N_SB_571153_5_ACAA_02_01

Figure A-FACAA - Sheet 02

Elapsed Time Assumption of the Repair

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 3

5

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SERVICE BULLETIN

Appendix 03 : Elapsed Time Assumption of the Repair

**CONF 001

ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A320−57−1153

ELAPSED TIME

(HOURS)

NOTE: THIS CHART IS ONLY A PROPOSAL.

OPERATORS MAY DETERMINE THAT ANOTHER WAY

TO DO THE WORK IS MORE SUITABLE FOR THEM.

MH ET PER

MH:

ET:

PER:

MANHOURS

ELAPSED TIME

NUMBER OF PERSONS

TOTAL MANHOURS (MH)

ELAPSED TIME (ET)

38.00

19.00

STEPS

0 5 10 20

36.00 18.00 2

2.00 1.00 2 APPLICATION OF

THE SEALANT

REPLACE THE

FASTENERS AT

FIRST OVERSIZE

15

N_SB_571153_5_ACAA_03_00

FOR ONE FIRST OVERSIZE AND INSTALLATION OF THE FASTENER,

TAKES APPROXIMATELY 10 MINUTES.

Figure A-FACAA - Sheet 03

Elapsed Time Assumption of the Repair

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 4

5

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SERVICE BULLETIN

Appendix 03 : Elapsed Time Assumption of the Repair

**CONF 002

ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A320−57−1153

ELAPSED TIME

(HOURS)

NOTE: THIS CHART IS ONLY A PROPOSAL.

OPERATORS MAY DETERMINE THAT ANOTHER WAY

TO DO THE WORK IS MORE SUITABLE FOR THEM.

MH ET PER

MH:

ET:

PER:

MANHOURS

ELAPSED TIME

NUMBER OF PERSONS

TOTAL MANHOURS (MH)

ELAPSED TIME (ET)

17.00

8.50

STEPS

0 5 10 20

8.00 4.00 2

1.00 0.5 2 APPLICATION OF

THE SEALANT

REPLACE THE

NUTS

15

N_SB_571153_5_ACAB_01_00

VALID ONLY IF SCREW ROTATE DURING THE REMOVAL OF THE NUT

8.00 4.00 2 INSPECTION ON

THE HOLE

Figure A-FACAB - Sheet 01

Elapsed Time Assumption of the Repair

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 5

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SERVICE BULLETIN

Appendix 03 : Elapsed Time Assumption of the Repair

**CONF 002

ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A320−57−1153

ELAPSED TIME

(HOURS)

NOTE: THIS CHART IS ONLY A PROPOSAL.

OPERATORS MAY DETERMINE THAT ANOTHER WAY

TO DO THE WORK IS MORE SUITABLE FOR THEM.

MH ET PER

MH:

ET:

PER:

MANHOURS

ELAPSED TIME

NUMBER OF PERSONS

TOTAL MANHOURS (MH)

ELAPSED TIME (ET)

17.00

8.50

STEPS

0 5 10 20

16.00 8.00 2

1.00 0.50 2 APPLICATION OF

THE SEALANT

REPLACE THE

FASTENERS AT

NOMINAL

15

FOR ONE FASTENER, TAKES APPROXIMATELY 10 MINUTES.

DIAMETER

N_SB_571153_5_ACAB_02_01

Figure A-FACAB - Sheet 02

Elapsed Time Assumption of the Repair

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 6

5

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SERVICE BULLETIN

Appendix 03 : Elapsed Time Assumption of the Repair

**CONF 002

ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A320−57−1153

ELAPSED TIME

(HOURS)

NOTE: THIS CHART IS ONLY A PROPOSAL.

OPERATORS MAY DETERMINE THAT ANOTHER WAY

TO DO THE WORK IS MORE SUITABLE FOR THEM.

MH ET PER

MH:

ET:

PER:

MANHOURS

ELAPSED TIME

NUMBER OF PERSONS

TOTAL MANHOURS (MH)

ELAPSED TIME (ET)

28.00

14.00

STEPS

0 5 10 20

27.00 13.50 2

1.00 0.50 2 APPLICATION OF

THE SEALANT

REPLACE THE

FASTENERS AT

FIRST OVERSIZE

15

FOR ONE FIRST OVERSIZE AND INSTALLATION OF THE FASTENER,

TAKES APPROXIMATELY 10 MINUTES.

N_SB_571153_5_ACAB_03_00

Figure A-FACAB - Sheet 03

Elapsed Time Assumption of the Repair

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 7

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SERVICE BULLETIN

REPORTING SHEET

TITLE: WINGS - GENERAL - INSPECTION OF SUSPECTED NON

CONFORMING NUTS.

MODIFICATION No.: None

Please complete the appropriate item (A or B):

A - SB WILL BE embodied YES/NO (if NO please comment)

If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of

embodiment:

B - SB HAS BEEN embodied on aircraft:

Operator comments:

From Airline:

Name/Title:

Signature: Date:

If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to

next normal revision or prior to SB embodiment, please indicate required service(s):

Either: Modification Operational Impact (MOI), if available YES/NO

Or : Intermediate revision YES/NO

Important Information: This SB will only be incorporated in your maintenance and operational

documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With

the next feasible revision, this will result in

- Updating of maintenance documentation to show pre and post SB data.

- Updating of maintenance and operational documentation to show post SB data after embodiment.

If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically

include them in the manual revisions. Refer to SIL 00-037 for detailed information.

Please return this completed sheet to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn: SDC32 Technical Data and Documentation Services

FAX: (+33) 5 61 93 28 06

e-mail: sb.reporting@airbus.com

or via your Resident Customer Support Office.

Alternatively, SB lists via letters or fax are also accepted.

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 1

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SERVICE BULLETIN

QUALITY PERCEPTION FORM

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

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

improve the quality of our Service Bulletins.

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

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

- Quality rating of this SB 4321

- Quality rating of the Accomplishment Instructions 4321

- Quality rating of the Illustrations 4321

- Is this SB easy to understand ? Y/N

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

short description of the issue.

Planning Material Instructions

X Effectivity X Kit content X Preparation

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

X Manpower X Industry support X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustrations

Comments:

Operator: Date:

Name/Title:

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153

REVISION No.: 02 - Apr 06/12 Page: 1

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