# @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



# MANDATORYMANDATORYMANDATORY 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 5

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# @A318/A319/A320/A321 SERVICE BULLETIN 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 5

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# @A318/A319/A320/A321 SERVICE BULLETIN 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 5

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# @A318/A319/A320/A321 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 5

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# @A318/A319/A320/A321 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. 

# MANDATORYMANDATORYMANDATORY 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 5

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# @A318/A319/A320/A321 SERVICE BULLETIN 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 5

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# @A318/A319/A320/A321 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 5

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# @A318/A319/A320/A321 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 5

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# @A318/A319/A320/A321 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



# MANDATORYMANDATORYMANDATORY 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 5

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# @A318/A319/A320/A321 SERVICE BULLETIN
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 REVISION No.: 02 - Apr 06/12 Page: 2 5

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# @A318/A319/A320/A321 SERVICE BULLETIN
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 REVISION No.: 02 - Apr 06/12 Page: 3 5

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# @A318/A319/A320/A321 SERVICE BULLETIN (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 5

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# @A318/A319/A320/A321 SERVICE BULLETIN (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 5

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# @A318/A319/A320/A321 SERVICE BULLETIN **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. EASA21J.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 REVISION No.: 02 - Apr 06/12 Page: 6 5

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# @A318/A319/A320/A321 SERVICE BULLETIN 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
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# @A318/A319/A320/A321 SERVICE BULLETIN 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 5

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# @A318/A319/A320/A321 SERVICE BULLETIN 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

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

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# @A318/A319/A320/A321 SERVICE BULLETIN 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

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 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 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
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

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

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# @A318/A319/A320/A321 SERVICE BULLETIN 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

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 **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 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 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

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
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). 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 (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 .

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 (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
DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153 REVISION No.: 02 - Apr 06/12 Page: 20 5

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# @A318/A319/A320/A321 SERVICE BULLETIN (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). DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153 REVISION No.: 02 - Apr 06/12 Page: 21 5

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# @A318/A319/A320/A321 SERVICE BULLETIN (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).

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153 REVISION No.: 02 - Apr 06/12 Page: 22 5

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# @A318/A319/A320/A321 SERVICE BULLETIN **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

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153 REVISION No.: 02 - Apr 06/12 Page: 23 5

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# @A318/A319/A320/A321 SERVICE BULLETIN 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

DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153 REVISION No.: 02 - Apr 06/12 Page: 25 5

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# @A318/A319/A320/A321 SERVICE BULLETIN **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).
DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153 REVISION No.: 02 - Apr 06/12 Page: 26 5

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# @A318/A319/A320/A321 SERVICE BULLETIN (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)
DATE: Feb 09/10 SERVICE BULLETIN No.: A320-57-1153 REVISION No.: 02 - Apr 06/12 Page: 27 5

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# @A318/A319/A320/A321 SERVICE BULLETIN
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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# @A318/A319/A320/A321 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

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# @A318/A319/A320/A321 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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# @A318/A319/A320/A321 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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# @A318/A319/A320/A321 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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# @A318/A319/A320/A321 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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# @A318/A319/A320/A321 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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# @A318/A319/A320/A321 SERVICE BULLETIN

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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# @A318/A319/A320/A321 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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# @A318/A319/A320/A321 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 5

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# @A318/A319/A320/A321 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 5

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# @A318/A319/A320/A321 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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# @A318/A319/A320/A321 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 5

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# @A318/A319/A320/A321 SERVICE BULLETIN
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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# @A318/A319/A320/A321 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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# @A318/A319/A320/A321 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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# @A318/A319/A320/A321 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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# @A318/A319/A320/A321 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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# @A318/A319/A320/A321 SERVICE BULLETIN 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 5

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# @A318/A319/A320/A321 SERVICE BULLETIN
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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# @A318/A319/A320/A321 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 5

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# @A318/A319/A320/A321 SERVICE BULLETIN 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 5

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# @A318/A319/A320/A321 SERVICE BULLETIN
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 5

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# @A318/A319/A320/A321 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 571153-833-012 001 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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# @A318/A319/A320/A321 SERVICE BULLETIN (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 5

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# @A318/A319/A320/A321 SERVICE BULLETIN 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 5

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# @A318/A319/A320/A321 SERVICE BULLETIN **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

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

# @A318/A319/A320/A321 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 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**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 FR36



## 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 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_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 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**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 RIB1 FR36

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 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

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 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**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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# @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_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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# @A318/A319/A320/A321 SERVICE BULLETIN

**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 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 001

AT THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2).

MISSING NO 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:** THIS INFORMATION IS TO BE RECORDED IN THE INSPECTION REPORT 01 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 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 002

AT THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2).

MISSING NO 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:** THIS INFORMATION IS TO BE RECORDED IN THE INSPECTION REPORT 01 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 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



### 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 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 001

VIEW LOOKING FWD LH SIDE SHOWN RH SIDE SYMMETRICAL RIB1 FR36



## 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 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**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 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**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) WET ASNA2531−4 NUT 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 APPLY MAT. No. 09−002 ON ALL FASTENERS (WET ASSEMBLY) 01 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

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 002

VIEW LOOKING FWD LH SIDE SHOWN RH SIDE SYMMETRICAL RIB1 FR36



## 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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# @A318/A319/A320/A321 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) WET ASNA2531−4 NUT 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

APPLY MAT. No. 09−002 ON ALL FASTENERS (WET ASSEMBLY) 01 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) WET ASNA2531−4 NUT EN6115V4X12 BOLT ITEM NEW ITEM ASSEMBLY

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

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

# @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

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

# @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

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

# @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) WET ASNA2531−4 NUT EN6115V4X12 BOLT ITEM NEW ITEM ASSEMBLY

APPLY MAT. No. 09−002 ON ALL FASTENERS (WET ASSEMBLY) 01 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) WET ASNA2531−4 NUT 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

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

# @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 H11H12 H13

H14 H15 H16 H17 H18 H19

H20 H21 H22 H23 H24 H25 H26 H53 H52 H27 H49 H50 H51 H28 H48 H29 H30 H31 H32

H47 H46 H45 H33 H44 H43 H34 H42 H41H40 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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# @A318/A319/A320/A321 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 RIB1 FR36

H1 H2 H3 H4 H5 H6 H7

H10
H12 H8 H9
H11

H13 H14 H15 H16 H43 H42 H17 H39 H40
H41 H18 H38 H19 H20 H21 H22

H37 H36 H35 H23 H34 H33 H24 H32 H30H31 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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# @A318/A319/A320/A321 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

40 5 10 REMOVAL ON THE 11.00 5.50 2 SEALANT

INSPECTION ON THE NUTS

0.50 0.50 1 TEST

30.00 15.00 2 CLOSE−UP

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

40 5 10 REMOVAL ON THE 8.00 4.00 2 SEALANT

INSPECTION ON THE NUTS

0.50 0.50 1 TEST

30.00 15.00 2 CLOSE−UP

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 20 10 5 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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# @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 20 10 5 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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# @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) 38.00 19.00 STEPS

0 20 10 5 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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# @A318/A319/A320/A321 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 20 10 5 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 5

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# @A318/A319/A320/A321 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 20 10 5 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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# @A318/A319/A320/A321 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 20 10 5 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 5

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# @A318/A319/A320/A321 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 5

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# @A318/A319/A320/A321 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 5

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