@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

ATA SYSTEM: 53

TITLE: FUSELAGE - GENERAL - SUSPECTED NON-CONFORMING NUTS

INSPECTION.

MODIFICATION No.: None

This page transmits Revision No.01 of Service Bulletin No.A320-53-1218

ADDITIONAL WORK

**CONF ALL

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

issue.

REASON

Revision No 01 issued to :

- update the Threshold

- modify the address in the Material Information Paragraph.

CHANGES

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

APPROVAL APPROVAL UPDATED R

MATERIAL INFORMATION

MATERIAL - PRICE AND AVAILABILITY

Procurement Addresses PROCUREMENT ADDRESSES UPDATED

MATERIAL SET UPDATED

R

INDUSTRY SUPPORT INFORMATION INDUSTRY SUPPORT INFORMATION UPDATED R

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 1

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

FILLING INSTRUCTIONS

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

Replace the complete document.

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

HISTORY OF PREVIOUS REVISIONS

No previous revision

REVISION SEQUENCE

ORIGINAL: Feb 08/10

REVISION No. : 01 - Jun 17/10

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 2

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SERVICE BULLETIN

SUMMARY

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

This summary is for information only and is not approved for modification of the aircraft.

ATA SYSTEM: 53

TITLE: FUSELAGE - GENERAL - SUSPECTED NON-CONFORMING NUTS

INSPECTION.

**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 RECOMMENDED (1) CANCELS INSPECTION SB NO

POTENTIAL AD YES A/C OPERATION AFFECTED NO

RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO

COST SAVING NO ETOPS AFFECTED NO

STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO

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

disruptions.

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 1

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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

Kit 531218A01R00 1 38.00 Nut

Component COMPA01 1 See SB Bolt

**CONF 002

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 531218A02R00 1 286.00 Nut

Component COMPA02 1 See SB Bolt

**CONF 003

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 531218A03R00 1 38.00 Nut

Component COMPA03 1 See SB Bolt

**CONF 004

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 531218A02R00 1 286.00 Nut

Kit 531218A03R00 1 38.00 Nut

TOTAL 324.00

Component COMPA02 1 See SB Bolt

Component COMPA03 1 See SB Bolt

**CONF 005

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 531218A01R00 1 38.00 Nut

Kit 531218A02R00 1 286.00 Nut

TOTAL 324.00

Component COMPA01 1 See SB Bolt

Component COMPA02 1 See SB Bolt

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 2

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SERVICE BULLETIN

SUMMARY

**CONF 006

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 531218A01R00 1 38.00 Nut

Kit 531218A02R00 1 286.00 Nut

Kit 531218A03R00 1 38.00 Nut

TOTAL 362.00

Component COMPA01 1 See SB Bolt

Component COMPA02 1 See SB Bolt

Component COMPA03 1 See SB Bolt

**CONF 007

No Material

EFFECTIVITY

**CONF ALL

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

42W 52U 62X AAR ABQ ABY ADH AEE AFL AFR AIJ AVA AXM

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

CSZ DKH DLH EIN EZY FFT GWI HHI HVN IAC IBE IGO JBU

JST KNE KZR LAN LBT MON NKS NLY PAL QTR RJA RNV SBI

TAI 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

SOFT NO

OBRM NO

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 3

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SERVICE BULLETIN

SUMMARY

MANPOWER

**CONF 001

Task 531218-832-801-001: Inspection

TOTAL MANHOURS 5.25

ELAPSED TIME (HOURS) 5.25

Task 531218-833-801-001: Repair

TOTAL MANHOURS 2.00

ELAPSED TIME (HOURS) 1.50

**CONF 002

Task 531218-832-801-001: Inspection

TOTAL MANHOURS 8.50

ELAPSED TIME (HOURS) 8.50

Task 531218-833-801-001: Repair

TOTAL MANHOURS 1.75

ELAPSED TIME (HOURS) 1.00

**CONF 003

Task 531218-832-801-001: Inspection

TOTAL MANHOURS 4.50

ELAPSED TIME (HOURS) 4.50

Task 531218-833-801-001: Repair

TOTAL MANHOURS 6.00

ELAPSED TIME (HOURS) 4.50

**CONF 004

Task 531218-832-801-001: Inspection

TOTAL MANHOURS 11.00

ELAPSED TIME (HOURS) 6.50

Task 531218-833-801-001: Repair

TOTAL MANHOURS 7.75

ELAPSED TIME (HOURS) 4.50

**CONF 005

Task 531218-832-801-001: Inspection

TOTAL MANHOURS 11.75

ELAPSED TIME (HOURS) 6.50

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 4

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SERVICE BULLETIN

SUMMARY

Task 531218-833-801-001: Repair

TOTAL MANHOURS 3.75

ELAPSED TIME (HOURS) 1.50

**CONF 006

Task 531218-832-801-001: Inspection

TOTAL MANHOURS 14.25

ELAPSED TIME (HOURS) 7.50

Task 531218-833-801-001: Repair

TOTAL MANHOURS 9.75

ELAPSED TIME (HOURS) 4.50

**CONF 007

APPENDICES

**CONF ALL

Appendix 01

Appendix 02

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 5

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SERVICE BULLETIN

SUMMARY

**CONF 001, 005 thru 006

N_SB_531218_5_SCAA_01_00

NOTE:

DETAILED VISUAL INSPECTION AREA

Z232

A

STGR10

STGR11

FR35 FR35.1 FR35.4

FWD

B

B

FR35

FR35.4

A

Figure A-FSCAA - Sheet 01

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 6

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SERVICE BULLETIN

SUMMARY

**CONF 002, 004 thru 006

NOTE:

DETAILED VISUAL INSPECTION AREAS

Z130

FR35.5

FR24

FR24A

FR28

B

A

FR24A

B

A

Y 1300

Y 765

Y 254

Y−254

Y−765

N_SB_531218_5_SAAA_01_00

VIEW LOOKING FWD

Figure A-FSAAA - Sheet 01

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 7

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SERVICE BULLETIN

SUMMARY

**CONF 003 thru 004, 006

FR9

FR14

FR19

FR20

Z123 Z124 − 

A

A

NOTE:

DETAILED VISUAL INSPECTION AREAS

N_SB_531218_5_SBAA_01_00

Figure A-FSBAA - Sheet 01

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 8

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SERVICE BULLETIN

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

ATA SYSTEM: 53

TITLE: FUSELAGE - GENERAL - SUSPECTED NON-CONFORMING NUTS

INSPECTION.

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

3339-3340 3350 3355 3360 3367 3369 3372 3380 3382 3385 3387-3388 3390 3393

3395 3397-3508 3510-3519 3522-3523 3525 3527 3529-3530 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

42W 3513

52U 3542

62X 3402

AAR 3437 3483 3496

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 1

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SERVICE BULLETIN

OPERATOR MSN

ABQ 3385 3388

ABY 3444 3476

ADH 3502 3515

AEE 3423 3439 3462 3478 3527

AFL 3410 3511

AFR 3372 3399 3401 3419 3420 3441 3470

AIJ 3508 3514

AVA 3408 3467 3518

AXM 3404 3427 3448 3477 3486 3489 3505

AZA 3412 3464 3482

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 3449

CSN 3459 3493 3507 3552

CSZ 3435 3440 3456

DKH 3485

DLH 3339 3360 3387 3434

EIN 3501

EZY 3411 3413 3426 3432 3442 3466 3537 3544 3555

FFT 3431

GWI 3500

HHI 3403

HVN 3355

IAC 3340 3367 3498

IBE 3380 3443

IGO 3414 3453 3457 3497

JBU 3416 3451 3479 3488 3517

JST 3474 3495

KNE 3425 3475 3530

KZR 3484 3519

LAN 3390 3438 3469

LBT 3480

MON 3546

NKS 3393 3395

NLY 3407 3504

PAL 3455

QTR 3369 3397

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 2

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SERVICE BULLETIN

OPERATOR MSN

RJA 3428 3458 3522

RNV 3492

SBI 3446 3473 3490 3494

TAI 3418 3510

THY 3350 3382 3405 3429 3525 3539

VLG 3400 3529

VOI 3450 3463 3491

VRD 3398 3417 3445 3460 3465 3503

WZZ 3409 3430

(4) Configuration by MSN

MSN CONFIGURATION

3339 3340 3350 3355 3360 3367 3369 3372 001

3380 3529 3530 3537 3555 002

3382 3522 3523 3525 3527 3539 3552 005

3385 3388 3390 3393 3395 3403 3406 3407 3408 3409 3410

3411 3412 3413 3414 3415 3416 3417 3418 3420 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

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 3513 3516 3518 3542 3544

3548

004

3387 3397 3399 3401 3405 3419 3429 3434 3441 3458 3459

3462 3471 3493 3498 3504 3507 3512 3546

006

3398 3400 3402 3404 3508 3510 3511 3514 3515 3517 3519 003

3461 3506 007

(5) Configuration definition

**CONF 001

Config. 001 is valid for aircraft on which suspected non-conforming nuts are installed in

Zone 232.

**CONF 002

Config. 002 is valid for aircraft on which suspected non-conforming nuts are installed in

Zone 130.

**CONF 003

Config. 003 is valid for aircraft on which suspected non-conforming nuts are installed in

Zone 123-124.

**CONF 004

Config. 004 is valid for aircraft on which suspected non-conforming nuts are installed in

Zone 123-124 and 130.

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 3

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**CONF 005

Config. 005 is valid for aircraft on which suspected non-conforming nuts are installed in

Zone 130 and 232.

**CONF 006

Config. 006 is valid for aircraft on which suspected non-conforming nuts are installed in

Zone 123-124, 130 and 232.

**CONF 007

Config. 007 is valid for aircraft on which the replacement of the non-conforming nuts has

been already performed with the RAS ref 70512739/015/2009 and RAS ref

705112751/013/2009.

This Service Bulletin is not to be accomplished.

(6) Material Effectivity

**CONF 001

MATERIAL QTY PER A/C SEE NOTES

Consumable CMLA01 1

Consumable CMLA02 1

Kit 531218A01R00 1

Component COMPA01 1

**CONF 002

MATERIAL QTY PER A/C SEE NOTES

Consumable CMLA01 1

Consumable CMLA04 1

Kit 531218A02R00 1

Component COMPA02 1

**CONF 003

MATERIAL QTY PER A/C SEE NOTES

Consumable CMLA01 1

Consumable CMLA02 1

Consumable CMLA03 1

Kit 531218A03R00 1

Component COMPA03 1

**CONF 004

MATERIAL QTY PER A/C SEE NOTES

Consumable CMLA01 1

Consumable CMLA02 1

Consumable CMLA03 1

Consumable CMLA04 1

Kit 531218A02R00 1

Kit 531218A03R00 1

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 4

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MATERIAL QTY PER A/C SEE NOTES

Component COMPA02 1

Component COMPA03 1

**CONF 005

MATERIAL QTY PER A/C SEE NOTES

Consumable CMLA01 1

Consumable CMLA02 1

Consumable CMLA04 1

Kit 531218A01R00 1

Kit 531218A02R00 1

Component COMPA01 1

Component COMPA02 1

**CONF 006

MATERIAL QTY PER A/C SEE NOTES

Consumable CMLA01 1

Consumable CMLA02 1

Consumable CMLA03 1

Consumable CMLA04 1

Kit 531218A01R00 1

Kit 531218A02R00 1

Kit 531218A03R00 1

Component COMPA01 1

Component COMPA02 1

Component COMPA03 1

**CONF 007

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.

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 5

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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.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

**CONF 001

Task 531218-832-801-001: Inspection

(1) Do a Detailed Visual Inspection of the Nuts (Z232)

Task 531218-833-801-001: Repair

(1) Replace the Nuts with the Same PN (Z232)

(2) Do a Visual Inspection of the Holes (Z232)

(3) Install the Fasteners at Nominal Diameter (Z232)

(4) Install the Fasteners at First Oversize Diameter (Z232)

**CONF 002

Task 531218-832-801-001: Inspection

(1) Do a Detailed Visual Inspection of the Nuts (Z130)

Task 531218-833-801-001: Repair

(1) Replace the Nuts with the Same PN (Z130)

(2) Replace the Fasteners at Nominal Diameter (Z130)

**CONF 003

Task 531218-832-801-001: Inspection

(1) Do a Detailed Visual Inspection of the Nuts (Z123-124)

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

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Task 531218-833-801-001: Repair

(1) Replace the Nuts with the Same PN (Z123-124)

(2) Do a Visual Inspection of the Holes (Z123-124)

(3) Install the Fasteners at Nominal Diameter (Z123-124)

(4) Install the Fasteners at First Oversize Diameter (Z123-124)

**CONF 004

Task 531218-832-801-001: Inspection

(1) Do a Detailed Visual Inspection of the Nuts (Z130)

(2) Do a Detailed Visual Inspection of the Nuts (Z123-124)

Task 531218-833-801-001: Repair

(1) Replace the Nuts with the Same PN (Z130)

(2) Replace the Fasteners at Nominal Diameter (Z130)

(3) Replace the Nuts with the Same PN (Z123-124)

(4) Do a Visual Inspection of the Holes (Z123-124)

(5) Install the Fasteners at Nominal Diameter (Z123-124)

(6) Install the Fasteners at First Oversize Diameter (Z123-124)

**CONF 005

Task 531218-832-801-001: Inspection

(1) Do a Detailed Visual Inspection of the Nuts (Z232)

(2) Do a Detailed Visual Inspection of the Nuts (Z130)

Task 531218-833-801-001: Repair

(1) Replace the Nuts with the Same PN (Z232)

(2) Do a Visual Inspection of the Holes (Z232)

(3) Install the Fasteners at Nominal Diameter (Z232)

(4) Install the Fasteners at First Oversize Diameter (Z232)

(5) Replace the Nuts with the Same PN (Z130)

(6) Replace the Fasteners at Nominal Diameter (Z130)

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 7

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**CONF 006

Task 531218-832-801-001: Inspection

(1) Do a Detailed Visual Inspection of the Nuts (Z232)

(2) Do a Detailed Visual Inspection of the Nuts (Z130)

(3) Do a Detailed Visual Inspection of the Nuts (Z123-124)

Task 531218-833-801-001: Repair

(1) Replace the Nuts with the Same PN (Z232)

(2) Do a Visual Inspection of the Holes (Z232)

(3) Install the Fasteners at Nominal Diameter (Z232)

(4) Install the Fasteners at First Oversize Diameter (Z232)

(5) Replace the Nuts with the Same PN (Z130)

(6) Replace the Fasteners at Nominal Diameter (Z130)

(7) Replace the Nuts with the Same PN (Z123-124)

(8) Do a Visual Inspection of the Holes (Z123-124)

(9) Install the Fasteners at Nominal Diameter (Z123-124)

(10) Install the Fasteners at First Oversize Diameter (Z123-124)

**CONF ALL

E. COMPLIANCE

(1) Classification

RECOMMENDED: Service Bulletin recommended to be accomplished to prevent

significant operational disruptions.

(2) Accomplishment Timescale

**CONF 001 thru 006

It is recommended to accomplish this Service Bulletin within 6 Years from Entry In

Service (EIS).

**CONF 007

None

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 8

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**CONF ALL

F. APPROVAL

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

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

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

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

before incorporation of the Service Bulletin.

G. MANPOWER

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

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

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

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

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

included.

**CONF 001

Task 531218-832-801-001: Inspection

Get Access 2.50

On Aircraft

Do a Detailed Visual Inspection of the Nuts (Z232) 0.25

Close-Up 2.50

TOTAL MANHOURS 5.25

ELAPSED TIME (HOURS) 5.25

Task 531218-833-801-001: Repair

On Aircraft

Replace the Nuts with the Same PN (Z232) 0.25

Do a Visual Inspection of the Holes (Z232) 0.50

Install the Fasteners at Nominal Diameter (Z232) 0.50

Install the Fasteners at First Oversize Diameter (Z232) 0.75

TOTAL MANHOURS 2.00

ELAPSED TIME (HOURS) 1.50

NOTE: For detail concerning the elapsed time assumptions, refer to Appendix 02

**CONF 002

Task 531218-832-801-001: Inspection

Get Access 4.00

On Aircraft

Do a Detailed Visual Inspection of the Nuts (Z130) 0.50

Close-Up 4.00

TOTAL MANHOURS 8.50

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 9

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Task 531218-832-801-001: Inspection

ELAPSED TIME (HOURS) 8.50

NOTE: For detail concerning the elapsed time assumptions, refer to Appendix 02

Task 531218-833-801-001: Repair

On Aircraft

Replace the Nuts with the Same PN (Z130) 0.75

Replace the Fasteners at Nominal Diameter (Z130) 1.00

TOTAL MANHOURS 1.75

ELAPSED TIME (HOURS) 1.00

NOTE: For detail concerning the elapsed time assumptions, refer to Appendix 02

**CONF 003

Task 531218-832-801-001: Inspection

Get Access 2.00

On Aircraft

Do a Detailed Visual Inspection of the Nuts (Z123-124) 0.50

Close-Up 2.00

TOTAL MANHOURS 4.50

ELAPSED TIME (HOURS) 4.50

Task 531218-833-801-001: Repair

On Aircraft

Replace the Nuts with the Same PN (Z123-124) 1.00

Do a Visual Inspection of the Holes (Z123-124) 1.50

Install the Fasteners at Nominal Diameter (Z123-124) 1.50

Install the Fasteners at First Oversize Diameter

(Z123-124)

2.00

TOTAL MANHOURS 6.00

ELAPSED TIME (HOURS) 4.50

NOTE: For detail concerning the elapsed time assumptions, refer to Appendix 02

**CONF 004

Task 531218-832-801-001: Inspection

Get Access 5.00

On Aircraft

Do a Detailed Visual Inspection of the Nuts (Z130) 0.50

Do a Detailed Visual Inspection of the Nuts (Z123-124) 0.50

Close-Up 5.00

TOTAL MANHOURS 11.00

ELAPSED TIME (HOURS) 6.50

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 10

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NOTE: For detail concerning the elapsed time assumptions, refer to Appendix 02

Task 531218-833-801-001: Repair

On Aircraft

Replace the Nuts with the Same PN (Z130) 0.75

Replace the Fasteners at Nominal Diameter (Z130) 1.00

Replace the Nuts with the Same PN (Z123-124) 1.00

Do a Visual Inspection of the Holes (Z123-124) 1.50

Install the Fasteners at Nominal Diameter (Z123-124) 1.50

Install the Fasteners at First Oversize Diameter

(Z123-124)

2.00

TOTAL MANHOURS 7.75

ELAPSED TIME (HOURS) 4.50

NOTE: For detail concerning the elapsed time assumptions, refer to Appendix 02

**CONF 005

Task 531218-832-801-001: Inspection

Get Access 5.50

On Aircraft

Do a Detailed Visual Inspection of the Nuts (Z232) 0.25

Do a Detailed Visual Inspection of the Nuts (Z130) 0.50

Close-Up 5.50

TOTAL MANHOURS 11.75

ELAPSED TIME (HOURS) 6.50

NOTE: For detail concerning the elapsed time assumptions, refer to Appendix 02

Task 531218-833-801-001: Repair

On Aircraft

Replace the Nuts with the Same PN (Z232) 0.25

Do a Visual Inspection of the Holes (Z232) 0.50

Install the Fasteners at Nominal Diameter (Z232) 0.50

Install the Fasteners at First Oversize Diameter (Z232) 0.75

Replace the Nuts with the Same PN (Z130) 0.75

Replace the Fasteners at Nominal Diameter (Z130) 1.00

TOTAL MANHOURS 3.75

ELAPSED TIME (HOURS) 1.50

NOTE: For detail concerning the elapsed time assumptions, refer to Appendix 02

**CONF 006

Task 531218-832-801-001: Inspection

Get Access 6.50

On Aircraft

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 11

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Task 531218-832-801-001: Inspection

Do a Detailed Visual Inspection of the Nuts (Z232) 0.25

Do a Detailed Visual Inspection of the Nuts (Z130) 0.50

Do a Detailed Visual Inspection of the Nuts (Z123-124) 0.50

Close-Up 6.50

TOTAL MANHOURS 14.25

ELAPSED TIME (HOURS) 7.50

NOTE: For detail concerning the elapsed time assumptions, refer to Appendix 02

Task 531218-833-801-001: Repair

On Aircraft

Replace the Nuts with the Same PN (Z232) 0.25

Do a Visual Inspection of the Holes (Z232) 0.50

Install the Fasteners at Nominal Diameter (Z232) 0.50

Install the Fasteners at First Oversize Diameter (Z232) 0.75

Replace the Nuts with the Same PN (Z130) 0.75

Replace the Fasteners at Nominal Diameter (Z130) 1.00

Replace the Nuts with the Same PN (Z123-124) 1.00

Do a Visual Inspection of the Holes (Z123-124) 1.50

Install the Fasteners at Nominal Diameter (Z123-124) 1.50

Install the Fasteners at First Oversize Diameter

(Z123-124)

2.00

TOTAL MANHOURS 9.75

ELAPSED TIME (HOURS) 4.50

NOTE: For detail concerning the elapsed time assumptions, refer to Appendix 02

**CONF 007

**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 12-34-24

20-21-11 25-23-47 25-23-48

32-22-00 52-10-00

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 12

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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) 51-42-00 51-43-00 51-75-12

**CONF 002

Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 06-41-53

12-34-24 20-21-11 25-54-11

32-22-00 52-10-00 52-30-00

Consumable Material List (CML)

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

Standards Manual (SM)

Structural Repair Manual (SRM) 51-42-00 51-43-00 51-75-12

**CONF 003

Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 12-34-24

20-21-11 32-22-00 52-10-00

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) 51-42-00 51-43-00 51-75-12

**CONF 004

Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 06-41-53

12-34-24 20-21-11 25-54-11

32-22-00 52-10-00 52-30-00

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) 51-42-00 51-43-00 51-75-12

**CONF 005

Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 06-41-53

12-34-24 20-21-11 25-23-47

25-23-48 25-54-11 32-22-00

52-10-00 52-30-00

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) 51-42-00 51-43-00 51-75-12

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 13

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**CONF 006

Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 06-41-53

12-34-24 20-21-11 25-23-47

25-23-48 25-54-11 32-22-00

52-10-00 52-30-00

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) 51-42-00 51-43-00 51-75-12

**CONF 007

Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 20-21-11

32-22-00

Consumable Material List (CML)

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

Standards Manual (SM)

Structural Repair Manual (SRM) 51-42-00 51-43-00 51-75-12

Repair Approval Sheet (RAS) : 70512751/013/2009

Repair Approval Sheet (RAS) : 70512739/015/2009

**CONF ALL

K. PUBLICATION AFFECTED

None

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 14

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SERVICE BULLETIN

2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

Kit 531218A01R00

Kit 531218A02R00

Kit 531218A03R00

Customers with aircraft shown in the

effectivity of this Service Bulletin should send

a purchase order to AIRBUS. Quote the

number of this Service Bulletin. The address

is :

AIRBUS Material logistics and Suppliers

Weg beim Jaeger 150

D-22335 HAMBURG

GERMANY

For ordering by internet:

http://spares.airbus.com

For ordering by fax: +49 40 50 76 25 90

For ordering by E-mail :airbus.kit@airbus.com

Component COMPA01

Component COMPA02

Component COMPA03

Customers with aircraft shown in the

effectivity of this Service Bulletin can send a

purchase order to B/E Aerospace. Quote the

number of this Service Bulletin. The address

is :

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

web address : www.beconsumables.com

<http://www.beconsumables.com>

(2) Price and Availability

Kit 531218A01R00

Cost 38.00 USD

Availability 90 calendar days from receipt of order

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

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

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

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 15

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

at the issue date of the Service Bulletin.

Kit 531218A02R00

Cost 286.00 USD

Availability 90 calendar days from receipt of order

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

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

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

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

at the issue date of the Service Bulletin.

Kit 531218A03R00

Cost 38.00 USD

Availability 90 calendar days from receipt of order

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

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

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

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

at the issue date of the Service Bulletin.

B. INDUSTRY SUPPORT INFORMATION

For the accomplishment of this Service Bulletin at or before 6 years check from Entry

In Service (EIS), AIRBUS will provide the kits at no charge. AIRBUS will also credit the

manhours indicated in this Service Bulletin at the operator’s agreed in-house warranty labor

rate as well as the material for the correction for claims received not later than 90 days after

completion of the last affected aircraft of your fleet.

C. LIST OF COMPONENTS

Kit 531218A01R00

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

NOTES

1 ASNA2531-4 3 NUT

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Kit 531218A02R00

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

NOTES

1 ASNA2531-4 8 NUT

10 NAS1149F0432P 16 WASHER

12 D2551006220000 4 GUIDE

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 16

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NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Kit 531218A03R00

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

NOTES

1 ASNA2531-4 10 NUT

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.

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

Consumable CMLA02

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Anti-Corrosion Primer (epoxyImproved Adhesion)16-006B As required

Consumable CMLA03

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Polyurethane Primer 16-001C As required

Polyurethane Topcoat, Grey (for

Internal Applic.)

16-002A As required

Polyurethane Finish Paint (for

External Applic.)

16-018A As required

Wash Primer 16-020 As required

Consumable CMLA04

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Synth.ester Based Grease High

Pressure

04-004 As required

Identification Paint 07-020 As required

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 17

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(2) Components

Component COMPA01

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

NOTES

2 EN6115V4-5 3 BOLT

3 EN6115V4X-5 3 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.

NOTE: The quantities given in this Kit are valid for a maximum repair

configuration.

Component COMPA02

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

NOTES

11 NAS6604-6 8 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.

NOTE: The quantities given in this Kit are valid for a maximum repair

configuration.

Component COMPA03

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

NOTES

4 EN6114V4-11 4 BOLT

5 EN6114V4X-11 4 BOLT

6 EN6114V4-12 4 BOLT

7 EN6114V4X-12 6 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.

NOTE: The quantities given in this Kit are valid for a maximum repair

configuration.

(3) Equipment

None

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 18

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E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

(1) Tooling - Price and Availability

To accomplish this Service Bulletin it is necessary to use the tools listed in AMM Task

32-22-00-010-001.

(2) Tools

None

(3) Special Tools

None

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 19

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This Page Intentionally Left Blank

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 20

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3. ACCOMPLISHMENT INSTRUCTIONS

Task 531218-832-801-001 - 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, ESPM 20-55-00.

Task Associated Data

**CONF 001

Zone

232

Manpower

TOTAL MANHOURS 5.25

ELAPSED TIME (HOURS) 5.25

**CONF 002

Zone

130

Manpower

TOTAL MANHOURS 8.50

ELAPSED TIME (HOURS) 8.50

**CONF 003

Zone

123

From 123 to 124

Manpower

TOTAL MANHOURS 4.50

ELAPSED TIME (HOURS) 4.50

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 21

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**CONF 004

Zone

123 130

From 123 to 124

Manpower

TOTAL MANHOURS 11.00

ELAPSED TIME (HOURS) 6.50

**CONF 005

Zone

130 232

Manpower

TOTAL MANHOURS 11.75

ELAPSED TIME (HOURS) 6.50

**CONF 006

Zone

123 130 232

From 123 to 124

Manpower

TOTAL MANHOURS 14.25

ELAPSED TIME (HOURS) 7.50

**CONF 007

None

**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 531218-910-002-001 - 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

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 22

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References

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

06-31-53, Page Block 001

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

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

(c) Clean the surface with :

Solvent General

Purpose

11-026 As required

(2) Subtask 531218-839-001-001 - Documentation

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 531218-910-002-001 - 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

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

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

(c) Clean the surface with :

Solvent General

Purpose

11-026 As required

(2) Subtask 531218-839-001-001 - Documentation

Manpower Resources

Skills NON SPECIFIC

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 23

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

Service Bulletin.

**CONF 003

(1) Subtask 531218-910-002-001 - 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

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

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

(c) Clean the surface with :

Solvent General

Purpose

11-026 As required

(2) Subtask 531218-839-001-001 - Documentation

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

**CONF 004

(1) Subtask 531218-910-002-001 - 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

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 24

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References

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

06-31-53, Page Block 001

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

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

(c) Clean the surface with :

Solvent General

Purpose

11-026 As required

(2) Subtask 531218-839-001-001 - Documentation

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

**CONF 005

(1) Subtask 531218-910-002-001 - 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

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

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

(c) Clean the surface with :

Solvent General

Purpose

11-026 As required

(2) Subtask 531218-839-001-001 - Documentation

Manpower Resources

Skills NON SPECIFIC

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 25

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

Service Bulletin.

**CONF 006

(1) Subtask 531218-910-002-001 - 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

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

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

(c) Clean the surface with :

Solvent General

Purpose

11-026 As required

(2) Subtask 531218-839-001-001 - Documentation

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

**CONF 007

None

**CONF ALL

B. PREPARATION

**CONF 001

(1) Subtask 531218-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 26

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SERVICE BULLETIN

References

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

Task 52-10-00-010-001

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

12-34-24-869-002).

(b) Put access platform(s) in position.

(c) Open the passenger/crew door 831 or 841 (Refer to AMM Task 52-10-00-010-001).

(2) Subtask 531218-010-001-001 - Remove for Access (Z232)

Work Zones and Access Panels

Zone Access/Work location

232

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 25-23-47-000-012

Task 25-23-48-000-001

(a) Remove the cove light panel 232CX (Refer to AMM Task 25-23-48-000-001).

(b) Remove the ceiling panel of the emergency exit door 232EX (Refer to AMM Task

25-23-47-000-012).

(c) If necessary, for a better access push the wire without disconnection.

**CONF 002

(1) Subtask 531218-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

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

Task 52-10-00-010-001

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

12-34-24-869-002).

(b) Put access platform(s) in position.

(c) Open the passenger/crew door 831 or 841 (Refer to AMM Task 52-10-00-010-001).

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 27

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SERVICE BULLETIN

(2) Subtask 531218-010-002-001 - Remove/Open for Access (Z130)

Manpower Resources

Skills NON SPECIFIC

References

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

Task 25-54-11-000-001

Task 52-30-00-860-001

Task 52-30-00-860-003

Task 52-30-00-860-005

(a) Open the cargo-compartment door 825 (Refer to AMM Task 52-30-00-860-001 or

AMM Task 52-30-00-860-003 or AMM Task 52-30-00-860-005).

(b) Remove the FWD cargo compartment panels FINs131DW, 131CW, 131EW,

131BW, 131AW and 132BW (Refer to AMM 06-41-53, Page Block 001 and AMM

Task 25-54-11-000-001).

**CONF 003

(1) Subtask 531218-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

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

Task 52-10-00-010-001

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

12-34-24-869-002).

(b) Put access platform(s) in position.

(c) Open the passenger/crew door 831 or 841 (Refer to AMM Task 52-10-00-010-001).

(2) Subtask 531218-010-003-001 - Open for Access (Z123-124)

Work Zones and Access Panels

Zone Access/Work location

123

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 32-22-00-010-001

(a) Open the nose landing gear doors (Refer to AMM Task 32-22-00-010-001).

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 28

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SERVICE BULLETIN

**CONF 004

(1) Subtask 531218-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

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

Task 52-10-00-010-001

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

12-34-24-869-002).

(b) Put access platform(s) in position.

(c) Open the passenger/crew door 831 or 841 (Refer to AMM Task 52-10-00-010-001).

(2) Subtask 531218-010-002-001 - Remove/Open for Access (Z130)

Manpower Resources

Skills NON SPECIFIC

References

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

Task 25-54-11-000-001

Task 52-30-00-860-001

Task 52-30-00-860-003

Task 52-30-00-860-005

(a) Open the cargo-compartment door 825 (Refer to AMM Task 52-30-00-860-001 or

AMM Task 52-30-00-860-003 or AMM Task 52-30-00-860-005).

(b) Remove the FWD cargo compartment panels FINs131DW, 131CW, 131EW,

131BW, 131AW and 132BW (Refer to AMM 06-41-53, Page Block 001 and AMM

Task 25-54-11-000-001).

(3) Subtask 531218-010-003-001 - Open for Access (Z123-124)

Work Zones and Access Panels

Zone Access/Work location

123

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 32-22-00-010-001

(a) Open the nose landing gear doors (Refer to AMM Task 32-22-00-010-001).

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 29

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SERVICE BULLETIN

**CONF 005

(1) Subtask 531218-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

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

Task 52-10-00-010-001

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

12-34-24-869-002).

(b) Put access platform(s) in position.

(c) Open the passenger/crew door 831 or 841 (Refer to AMM Task 52-10-00-010-001).

(2) Subtask 531218-010-001-001 - Remove for Access (Z232)

Work Zones and Access Panels

Zone Access/Work location

232

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 25-23-47-000-012

Task 25-23-48-000-001

(a) Remove the cove light panel 232CX (Refer to AMM Task 25-23-48-000-001).

(b) Remove the ceiling panel of the emergency exit door 232EX (Refer to AMM Task

25-23-47-000-012).

(c) If necessary, for a better access push the wire without disconnection.

(3) Subtask 531218-010-002-001 - Remove/Open for Access (Z130)

Manpower Resources

Skills NON SPECIFIC

References

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

Task 25-54-11-000-001

Task 52-30-00-860-001

Task 52-30-00-860-003

Task 52-30-00-860-005

(a) Open the cargo-compartment door 825 (Refer to AMM Task 52-30-00-860-001 or

AMM Task 52-30-00-860-003 or AMM Task 52-30-00-860-005).

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 30

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SERVICE BULLETIN

(b) Remove the FWD cargo compartment panels FINs131DW, 131CW, 131EW,

131BW, 131AW and 132BW (Refer to AMM 06-41-53, Page Block 001 and AMM

Task 25-54-11-000-001).

**CONF 006

(1) Subtask 531218-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

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

Task 52-10-00-010-001

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

12-34-24-869-002).

(b) Put access platform(s) in position.

(c) Open the passenger/crew door 831 or 841 (Refer to AMM Task 52-10-00-010-001).

(2) Subtask 531218-010-001-001 - Remove for Access (Z232)

Work Zones and Access Panels

Zone Access/Work location

232

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 25-23-47-000-012

Task 25-23-48-000-001

(a) Remove the cove light panel 232CX (Refer to AMM Task 25-23-48-000-001).

(b) Remove the ceiling panel of the emergency exit door 232EX (Refer to AMM Task

25-23-47-000-012).

(c) If necessary, for a better access push the wire without disconnection.

(3) Subtask 531218-010-002-001 - Remove/Open for Access (Z130)

Manpower Resources

Skills NON SPECIFIC

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 31

5

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SERVICE BULLETIN

References

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

Task 25-54-11-000-001

Task 52-30-00-860-001

Task 52-30-00-860-003

Task 52-30-00-860-005

(a) Open the cargo-compartment door 825 (Refer to AMM Task 52-30-00-860-001 or

AMM Task 52-30-00-860-003 or AMM Task 52-30-00-860-005).

(b) Remove the FWD cargo compartment panels FINs131DW, 131CW, 131EW,

131BW, 131AW and 132BW (Refer to AMM 06-41-53, Page Block 001 and AMM

Task 25-54-11-000-001).

(4) Subtask 531218-010-003-001 - Open for Access (Z123-124)

Work Zones and Access Panels

Zone Access/Work location

123

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 32-22-00-010-001

(a) Open the nose landing gear doors (Refer to AMM Task 32-22-00-010-001).

**CONF 007

None

**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 531218-210-001-001 - Do a Detailed Visual Inspection of the Nuts (Z232)

Work Zones and Access Panels

Zone Access/Work location

232 Work location Frame 35

Stringer 11

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 32

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SERVICE BULLETIN

References

Fig. A-FBCAA

Inspection Area (Z232)

Sheet 01

Sheet 02

Fig. A-FFCAA

Flow Chart (Z232)

Sheet 01

(a) For the inspection area in Zone 232, refer to Fig. A-FBCAA Sheet 01 and Fig. AFBCAA Sheet 02.

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

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

**CONF 002

(1) Subtask 531218-210-002-001 - Do a Detailed Visual Inspection of the Nuts (Z130)

Work Zones and Access Panels

Zone Access/Work location

130 Work location Frame 24A

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

Fig. A-FBAAA

Inspection Area (Z130)

Sheet 01

Sheet 02

(a) For the inspection area in Zone 130, refer to Fig. A-FBAAA Sheet 01 and Fig. AFBAAA Sheet 02.

(b) Do a detailed visual inspection, refer to Fig. FFAAA.

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

**CONF 003

(1) Subtask 531218-210-003-001 - Do a Detailed Visual Inspection of the Nuts

(Z123-124)

Work Zones and Access Panels

Zone Access/Work location

From 123 Work location from Frame 9 to Frame 14

To 124 Work location from Frame 9 to Frame 14

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 33

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Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

Fig. A-FBBAA

Inspection Area (Z123-124)

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Fig. A-FFBAA

Flow Chart (Z123-124)

Sheet 01

(a) For the inspection area in Zone 123, 124, refer to Fig. A-FBBAA Sheet 01 thru Fig.

A-FBBAA Sheet 05.

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

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

**CONF 004

(1) Subtask 531218-210-002-001 - Do a Detailed Visual Inspection of the Nuts (Z130)

Work Zones and Access Panels

Zone Access/Work location

130 Work location Frame 24A

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

Fig. A-FBAAA

Inspection Area (Z130)

Sheet 01

Sheet 02

(a) For the inspection area in Zone 130, refer to Fig. A-FBAAA Sheet 01 and Fig. AFBAAA Sheet 02.

(b) Do a detailed visual inspection, refer to Fig. FFAAA.

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

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 34

5

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SERVICE BULLETIN

(2) Subtask 531218-210-003-001 - Do a Detailed Visual Inspection of the Nuts

(Z123-124)

Work Zones and Access Panels

Zone Access/Work location

From 123 Work location from Frame 9 to Frame 14

To 124 Work location from Frame 9 to Frame 14

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

Fig. A-FBBAA

Inspection Area (Z123-124)

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Fig. A-FFBAA

Flow Chart (Z123-124)

Sheet 01

(a) For the inspection area in Zone 123, 124, refer to Fig. A-FBBAA Sheet 01 thru Fig.

A-FBBAA Sheet 05.

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

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

**CONF 005

(1) Subtask 531218-210-001-001 - Do a Detailed Visual Inspection of the Nuts (Z232)

Work Zones and Access Panels

Zone Access/Work location

232 Work location Frame 35

Stringer 11

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Fig. A-FBCAA

Inspection Area (Z232)

Sheet 01

Sheet 02

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 35

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References

Fig. A-FFCAA

Flow Chart (Z232)

Sheet 01

(a) For the inspection area in Zone 232, refer to Fig. A-FBCAA Sheet 01 and Fig. AFBCAA Sheet 02.

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

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

(2) Subtask 531218-210-002-001 - Do a Detailed Visual Inspection of the Nuts (Z130)

Work Zones and Access Panels

Zone Access/Work location

130 Work location Frame 24A

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

Fig. A-FBAAA

Inspection Area (Z130)

Sheet 01

Sheet 02

(a) For the inspection area in Zone 130, refer to Fig. A-FBAAA Sheet 01 and Fig. AFBAAA Sheet 02.

(b) Do a detailed visual inspection, refer to Fig. FFAAA.

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

**CONF 006

(1) Subtask 531218-210-001-001 - Do a Detailed Visual Inspection of the Nuts (Z232)

Work Zones and Access Panels

Zone Access/Work location

232 Work location Frame 35

Stringer 11

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 36

5

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SERVICE BULLETIN

References

Fig. A-FBCAA

Inspection Area (Z232)

Sheet 01

Sheet 02

Fig. A-FFCAA

Flow Chart (Z232)

Sheet 01

(a) For the inspection area in Zone 232, refer to Fig. A-FBCAA Sheet 01 and Fig. AFBCAA Sheet 02.

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

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

(2) Subtask 531218-210-002-001 - Do a Detailed Visual Inspection of the Nuts (Z130)

Work Zones and Access Panels

Zone Access/Work location

130 Work location Frame 24A

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

Fig. A-FBAAA

Inspection Area (Z130)

Sheet 01

Sheet 02

(a) For the inspection area in Zone 130, refer to Fig. A-FBAAA Sheet 01 and Fig. AFBAAA Sheet 02.

(b) Do a detailed visual inspection, refer to Fig. FFAAA.

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

(3) Subtask 531218-210-003-001 - Do a Detailed Visual Inspection of the Nuts

(Z123-124)

Work Zones and Access Panels

Zone Access/Work location

From 123 Work location from Frame 9 to Frame 14

To 124 Work location from Frame 9 to Frame 14

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 37

5

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SERVICE BULLETIN

References

Fig. A-FBBAA

Inspection Area (Z123-124)

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Fig. A-FFBAA

Flow Chart (Z123-124)

Sheet 01

(a) For the inspection area in Zone 123, 124, refer to Fig. A-FBBAA Sheet 01 thru Fig.

A-FBBAA Sheet 05.

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

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

**CONF 007

None

**CONF ALL

D. TEST

**CONF 001

None

**CONF 002

None

**CONF 003

None

**CONF 004

None

**CONF 005

None

**CONF 006

None

**CONF 007

None

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 38

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**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 531218-410-001-001 - Install Items Removed (Z232)

Work Zones and Access Panels

Zone Access/Work location

232

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 25-23-47-400-012

Task 25-23-48-400-001

(a) Install the ceiling panel of the emergency exit door 232EX (Refer to AMM Task

25-23-47-400-012).

(b) Install the cove light panel 232CX (Refer to AMM Task 25-23-48-400-001).

(2) Subtask 531218-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 52-10-00-410-001

(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) Close the passenger/crew door 831 or 841 (Refer to AMM Task 52-10-00-410-001).

(d) Remove the access platform(s).

**CONF 002

(1) Subtask 531218-410-002-001 - Install/Close Items Removed/Opened for access

(Z130)

Work Zones and Access Panels

Zone Access/Work location

130

Manpower Resources

Skills NON SPECIFIC

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 39

5

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SERVICE BULLETIN

References

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

Task 25-54-11-400-001

Task 52-30-00-860-002

Task 52-30-00-860-004

Task 52-30-00-860-006

(a) Install the FWD cargo compartment panels FINs131DW, 131CW, 131EW, 131BW,

131AW and 132BW (Refer to AMM 06-41-53, Page Block 001 and AMM Task

25-54-11-400-001).

(b) close the cargo-compartment door 825 (Refer to AMM Task 52-30-00-860-002 or

AMM Task 52-30-00-860-004 or AMM Task 52-30-00-860-006).

(2) Subtask 531218-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 52-10-00-410-001

(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) Close the passenger/crew door 831 or 841 (Refer to AMM Task 52-10-00-410-001).

(d) Remove the access platform(s).

**CONF 003

(1) Subtask 531218-410-003-001 - Close Items Opened for Access (Z123-124)

Work Zones and Access Panels

Zone Access/Work location

123

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 32-22-00-410-001

(a) Close the nose landing gear doors (Refer to AMM Task 32-22-00-410-001).

(2) Subtask 531218-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 40

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SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 52-10-00-410-001

(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) Close the passenger/crew door 831 or 841 (Refer to AMM Task 52-10-00-410-001).

(d) Remove the access platform(s).

**CONF 004

(1) Subtask 531218-410-002-001 - Install/Close Items Removed/Opened for access

(Z130)

Work Zones and Access Panels

Zone Access/Work location

130

Manpower Resources

Skills NON SPECIFIC

References

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

Task 25-54-11-400-001

Task 52-30-00-860-002

Task 52-30-00-860-004

Task 52-30-00-860-006

(a) Install the FWD cargo compartment panels FINs131DW, 131CW, 131EW, 131BW,

131AW and 132BW (Refer to AMM 06-41-53, Page Block 001 and AMM Task

25-54-11-400-001).

(b) close the cargo-compartment door 825 (Refer to AMM Task 52-30-00-860-002 or

AMM Task 52-30-00-860-004 or AMM Task 52-30-00-860-006).

(2) Subtask 531218-410-003-001 - Close Items Opened for Access (Z123-124)

Work Zones and Access Panels

Zone Access/Work location

123

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 32-22-00-410-001

(a) Close the nose landing gear doors (Refer to AMM Task 32-22-00-410-001).

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 41

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(3) Subtask 531218-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 52-10-00-410-001

(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) Close the passenger/crew door 831 or 841 (Refer to AMM Task 52-10-00-410-001).

(d) Remove the access platform(s).

**CONF 005

(1) Subtask 531218-410-001-001 - Install Items Removed (Z232)

Work Zones and Access Panels

Zone Access/Work location

232

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 25-23-47-400-012

Task 25-23-48-400-001

(a) Install the ceiling panel of the emergency exit door 232EX (Refer to AMM Task

25-23-47-400-012).

(b) Install the cove light panel 232CX (Refer to AMM Task 25-23-48-400-001).

(2) Subtask 531218-410-002-001 - Install/Close Items Removed/Opened for access

(Z130)

Work Zones and Access Panels

Zone Access/Work location

130

Manpower Resources

Skills NON SPECIFIC

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 42

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References

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

Task 25-54-11-400-001

Task 52-30-00-860-002

Task 52-30-00-860-004

Task 52-30-00-860-006

(a) Install the FWD cargo compartment panels FINs131DW, 131CW, 131EW, 131BW,

131AW and 132BW (Refer to AMM 06-41-53, Page Block 001 and AMM Task

25-54-11-400-001).

(b) close the cargo-compartment door 825 (Refer to AMM Task 52-30-00-860-002 or

AMM Task 52-30-00-860-004 or AMM Task 52-30-00-860-006).

(3) Subtask 531218-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 52-10-00-410-001

(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) Close the passenger/crew door 831 or 841 (Refer to AMM Task 52-10-00-410-001).

(d) Remove the access platform(s).

**CONF 006

(1) Subtask 531218-410-001-001 - Install Items Removed (Z232)

Work Zones and Access Panels

Zone Access/Work location

232

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 25-23-47-400-012

Task 25-23-48-400-001

(a) Install the ceiling panel of the emergency exit door 232EX (Refer to AMM Task

25-23-47-400-012).

(b) Install the cove light panel 232CX (Refer to AMM Task 25-23-48-400-001).

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 43

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(2) Subtask 531218-410-002-001 - Install/Close Items Removed/Opened for access

(Z130)

Work Zones and Access Panels

Zone Access/Work location

130

Manpower Resources

Skills NON SPECIFIC

References

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

Task 25-54-11-400-001

Task 52-30-00-860-002

Task 52-30-00-860-004

Task 52-30-00-860-006

(a) Install the FWD cargo compartment panels FINs131DW, 131CW, 131EW, 131BW,

131AW and 132BW (Refer to AMM 06-41-53, Page Block 001 and AMM Task

25-54-11-400-001).

(b) close the cargo-compartment door 825 (Refer to AMM Task 52-30-00-860-002 or

AMM Task 52-30-00-860-004 or AMM Task 52-30-00-860-006).

(3) Subtask 531218-410-003-001 - Close Items Opened for Access (Z123-124)

Work Zones and Access Panels

Zone Access/Work location

123

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 32-22-00-410-001

(a) Close the nose landing gear doors (Refer to AMM Task 32-22-00-410-001).

(4) Subtask 531218-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 52-10-00-410-001

(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.

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 44

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(c) Close the passenger/crew door 831 or 841 (Refer to AMM Task 52-10-00-410-001).

(d) Remove the access platform(s).

**CONF 007

None

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 45

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This Page Intentionally Left Blank

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 46

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Task 531218-833-801-001 - 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, ESPM 20-55-00.

Task Associated Data

**CONF 001

Zone

232

Manpower

TOTAL MANHOURS 2.00

ELAPSED TIME (HOURS) 1.50

**CONF 002

Zone

130

Manpower

TOTAL MANHOURS 1.75

ELAPSED TIME (HOURS) 1.00

**CONF 003

Zone

From 123 to 124

Manpower

TOTAL MANHOURS 6.00

ELAPSED TIME (HOURS) 4.50

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 47

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**CONF 004

Zone

130

From 123 to 124

Manpower

TOTAL MANHOURS 7.75

ELAPSED TIME (HOURS) 4.50

**CONF 005

Zone

130 232

Manpower

TOTAL MANHOURS 3.75

ELAPSED TIME (HOURS) 1.50

**CONF 006

Zone

130 232

From 123 to 124

Manpower

TOTAL MANHOURS 9.75

ELAPSED TIME (HOURS) 4.50

**CONF 007

None

**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 531218-910-001-002 - 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

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 48

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Consumable CMLA02

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Anti-Corrosion Primer

(epoxy-Improved Adhesion)

16-006B As required

References

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

06-31-53, Page Block 001

Task 20-21-11-911-001

Consumable Material List (CML)

Standards Manual (SM)

Structural Repair Manual (SRM) 51-42-00

51-43-00

51-75-12

(a) For the specification of materials (Mat. No.) that you must use in this Service

Bulletin refer to Consumable Materials 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) 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) To torque tighten the standard threaded fasteners (Refer to AMM Task

20-21-11-911-001).

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

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

(h) Clean the surface with :

Solvent General

Purpose

11-026 As required

(i) Renew the protective finish (Refer to SRM 51-75-12) :

1 Zone 232 internal area, apply :

Anti-Corrosion

Primer (epoxyImproved Adhesion)

16-006B As required

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 49

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**CONF 002

(1) Subtask 531218-910-001-003 - 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

Task 20-21-11-911-001

Consumable Material List (CML)

Standards Manual (SM)

Structural Repair Manual (SRM) 51-42-00

51-43-00

51-75-12

(a) For the specification of materials (Mat. No.) that you must use in this Service

Bulletin refer to Consumable Materials 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) 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) To torque tighten the standard threaded fasteners (Refer to AMM Task

20-21-11-911-001).

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

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

(h) Clean the surface with :

Solvent General

Purpose

11-026 As required

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 50

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**CONF 003

(1) Subtask 531218-910-001-001 - 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

Solvent General Purpose 11-026 As required

Consumable CMLA02

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Anti-Corrosion Primer

(epoxy-Improved Adhesion)

16-006B As required

Consumable CMLA03

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polyurethane Primer 16-001C As required

Polyurethane Topcoat, Grey

(for Internal Applic.)

16-002A As required

Polyurethane Finish Paint

(for External Applic.)

16-018A As required

Wash Primer 16-020 As required

References

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

06-31-53, Page Block 001

Task 20-21-11-911-001

Consumable Material List (CML)

Standards Manual (SM)

Structural Repair Manual (SRM) 51-42-00

51-43-00

51-75-12

(a) For the specification of materials (Mat. No.) that you must use in this Service

Bulletin refer to Consumable Materials 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) For the Frame (FR) identification (Refer to AMM 06-31-53, Page Block 001).

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 51

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

(e) To torque tighten the standard threaded fasteners (Refer to AMM Task

20-21-11-911-001).

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

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

(h) Clean the surface with :

Solvent General

Purpose

11-026 As required

(i) Renew the protective finish (Refer to SRM 51-75-12) :

1 Zone 232 internal area, apply :

Anti-Corrosion

Primer (epoxyImproved Adhesion)

16-006B As required

2 Zone 123-124 internal area, apply :

Anti-Corrosion

Primer (epoxyImproved Adhesion)

16-006B As required

Polyurethane

Topcoat, Grey (for

Internal Applic.)

16-002A As required

3 Zone 123-124 external area, apply :

Wash Primer 16-020 As required

Polyurethane

Primer

16-001C As required

Polyurethane Finish

Paint (for External

Applic.)

16-018A As required

**CONF 004

(1) Subtask 531218-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 52

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Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

Consumable CMLA02

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Anti-Corrosion Primer

(epoxy-Improved Adhesion)

16-006B As required

Consumable CMLA03

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polyurethane Primer 16-001C As required

Polyurethane Topcoat, Grey

(for Internal Applic.)

16-002A As required

Polyurethane Finish Paint

(for External Applic.)

16-018A As required

Wash Primer 16-020 As required

References

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

06-31-53, Page Block 001

Task 20-21-11-911-001

Consumable Material List (CML)

Standards Manual (SM)

Structural Repair Manual (SRM) 51-42-00

51-43-00

51-75-12

(a) For the specification of materials (Mat. No.) that you must use in this Service

Bulletin refer to Consumable Materials 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) 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) To torque tighten the standard threaded fasteners (Refer to AMM Task

20-21-11-911-001).

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

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 53

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

(h) Clean the surface with :

Solvent General

Purpose

11-026 As required

(i) Renew the protective finish (Refer to SRM 51-75-12) :

1 Zone 232 internal area, apply :

Anti-Corrosion

Primer (epoxyImproved Adhesion)

16-006B As required

2 Zone 123-124 internal area, apply :

Anti-Corrosion

Primer (epoxyImproved Adhesion)

16-006B As required

Polyurethane

Topcoat, Grey (for

Internal Applic.)

16-002A As required

3 Zone 123-124 external area, apply :

Wash Primer 16-020 As required

Polyurethane

Primer

16-001C As required

Polyurethane Finish

Paint (for External

Applic.)

16-018A As required

**CONF 005

(1) Subtask 531218-910-001-002 - 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

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 54

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Consumable CMLA02

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Anti-Corrosion Primer

(epoxy-Improved Adhesion)

16-006B As required

References

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

06-31-53, Page Block 001

Task 20-21-11-911-001

Consumable Material List (CML)

Standards Manual (SM)

Structural Repair Manual (SRM) 51-42-00

51-43-00

51-75-12

(a) For the specification of materials (Mat. No.) that you must use in this Service

Bulletin refer to Consumable Materials 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) 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) To torque tighten the standard threaded fasteners (Refer to AMM Task

20-21-11-911-001).

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

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

(h) Clean the surface with :

Solvent General

Purpose

11-026 As required

(i) Renew the protective finish (Refer to SRM 51-75-12) :

1 Zone 232 internal area, apply :

Anti-Corrosion

Primer (epoxyImproved Adhesion)

16-006B As required

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 55

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**CONF 006

(1) Subtask 531218-910-001-001 - 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

Solvent General Purpose 11-026 As required

Consumable CMLA02

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Anti-Corrosion Primer

(epoxy-Improved Adhesion)

16-006B As required

Consumable CMLA03

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polyurethane Primer 16-001C As required

Polyurethane Topcoat, Grey

(for Internal Applic.)

16-002A As required

Polyurethane Finish Paint

(for External Applic.)

16-018A As required

Wash Primer 16-020 As required

References

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

06-31-53, Page Block 001

Task 20-21-11-911-001

Consumable Material List (CML)

Standards Manual (SM)

Structural Repair Manual (SRM) 51-42-00

51-43-00

51-75-12

(a) For the specification of materials (Mat. No.) that you must use in this Service

Bulletin refer to Consumable Materials 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) For the Frame (FR) identification (Refer to AMM 06-31-53, Page Block 001).

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 56

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

(e) To torque tighten the standard threaded fasteners (Refer to AMM Task

20-21-11-911-001).

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

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

(h) Clean the surface with :

Solvent General

Purpose

11-026 As required

(i) Renew the protective finish (Refer to SRM 51-75-12) :

1 Zone 232 internal area, apply :

Anti-Corrosion

Primer (epoxyImproved Adhesion)

16-006B As required

2 Zone 123-124 internal area, apply :

Anti-Corrosion

Primer (epoxyImproved Adhesion)

16-006B As required

Polyurethane

Topcoat, Grey (for

Internal Applic.)

16-002A As required

3 Zone 123-124 external area, apply :

Wash Primer 16-020 As required

Polyurethane

Primer

16-001C As required

Polyurethane Finish

Paint (for External

Applic.)

16-018A As required

**CONF 007

None

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 57

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**CONF ALL

B. PREPARATION

**CONF 001

None

**CONF 002

None

**CONF 003

None

**CONF 004

None

**CONF 005

None

**CONF 006

None

**CONF 007

None

**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 531218-960-001-001 - Replace the Nuts with the Same PN (Z232)

Work Zones and Access Panels

Zone Access/Work location

232 Work location Frame 35

Stringer 11

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 58

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Material necessary to do the job

Kit 531218A01R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 ASNA2531-4 3 NUT

References

Fig. A-FCCAA

Replacement of the Fasteners (Z232)

Sheet 01

Sheet 02

Sheet 03

(a) Remove the nuts :

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

3 Nut Item (1) Discard

NOTE: Use the ALEN key to maintain the bolts.

NOTE: If the bolt rotates during the removal of the nuts, refer to SUBTASK

531218-210-004 001 Do a Visual Inspection of the Holes (Z232) .

(b) Install the nuts :

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

3 Nut ASNA2531-4 Item 1

NOTE: Use the ALEN key to maintain the bolts.

NOTE: If the bolt rotates during the installation of the nuts, refer to

SUBTASK 531218-210-004 001 Do a Visual Inspection of the Holes

(Z232) .

(2) Subtask 531218-210-004-001 - Do a Visual Inspection of the Holes (Z232)

Work Zones and Access Panels

Zone Access/Work location

232 Work location Frame 35

Stringer 11

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

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

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 59

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References

Fig. A-FCCAA

Replacement of the Fasteners (Z232)

Sheet 01

Sheet 02

Sheet 03

(a) Remove the concerned bolt.

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

3 Bolt Item (2) Discard

NOTE: The quantity given in this Subtask is valid for a maximum inspection

configuration.

(b) Clean the hole.

(c) Do a visual inspection of the hole (Refer to NTM 51-90-00).

1 If the hole is not scratched, replace the fastener at the nominal diameter

(Refer to SUBTASK 531218-831-001 001 Install the Fasteners at Nominal

Diameter (Z232) ).

2 If the hole is scratched, replace the fastener at first oversize (Refer to

SUBTASK 531218-831-002 001 Install the Fasteners at First Oversize

Diameter (Z232) ).

(3) Subtask 531218-831-001-001 - Install the Fasteners at Nominal Diameter (Z232)

Work Zones and Access Panels

Zone Access/Work location

232 Work location Frame 35

Stringer 11

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Kit 531218A01R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 ASNA2531-4 3 NUT

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 EN6115V4-5 3 BOLT

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 60

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NOTE: The quantities given in this Kit are valid for a maximum repair

configuration.

References

Fig. A-FCCAA

Replacement of the Fasteners (Z232)

Sheet 01

Sheet 02

Sheet 03

(a) Install :

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

3 Bolt EN6115V4-5 Item 2

3 Nut ASNA2531-4 Item 1

NOTE: The quantities given in this Subtask are valid for a maximum repair

configuration.

(4) Subtask 531218-831-002-001 - Install the Fasteners at First Oversize Diameter

(Z232)

Work Zones and Access Panels

Zone Access/Work location

232 Work location Frame 35

Stringer 11

Manpower Resources

Manhours 0.75

Minimum number of person 1

Subtask elapsed time 0.75

Skills AIRFRAME

Material necessary to do the job

Kit 531218A01R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 ASNA2531-4 3 NUT

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

3 EN6115V4X-5 3 BOLT

NOTE: The quantities given in this Kit are valid for a maximum repair

configuration.

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 61

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References

Fig. A-FCCAA

Replacement of the Fasteners (Z232)

Sheet 01

Sheet 02

Sheet 03

(a) If not yet, remove :

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

3 Bolt Item (2) Discard

(b) Oversize the hole to the dimension given in Fig. A-FCCAA Sheet 03.

(c) Clean the drilled areas.

(d) Install :

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

3 Bolt EN6115V4X-5 Item 3

3 Nut ASNA2531-4 Item 1

NOTE: The quantities given in this Subtask are valid for a maximum repair

configuration.

**CONF 002

(1) Subtask 531218-960-002-001 - Replace the Nuts with the Same PN (Z130)

Work Zones and Access Panels

Zone Access/Work location

130 Work location Frame 24A

Manpower Resources

Manhours 0.75

Minimum number of person 1

Subtask elapsed time 0.75

Skills AIRFRAME

Material necessary to do the job

Kit 531218A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 ASNA2531-4 8 NUT

10 NAS1149F0432P 16 WASHER

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 62

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Consumable CMLA04

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Identification Paint 07-020 As required

References

Fig. A-FCAAA

Replacement of the Nuts (Z130)

Sheet 01

Sheet 02

(a) Remove the upper nuts.

Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02

4 Nut Item (1) Discard

4 Bolt Item (11) Retain

8 Washer Item (10) Discard

(b) Install the upper nuts.

Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02

4 Bolt Item (11) Retained at

removal

4 Nut ASNA2531-4 Item 1

8 Washer-Flat NAS1149F0432P Item 10

NOTE: Tightening torque the nut Item 1 between 0.70m.daN (62lbf.in.) and

0.80mdaN (71lbf.in.).

After tightened the nut Item 1 apply :

Identification Paint 07-020 As required

(c) Remove the lower nuts.

Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02

4 Nut Item (1) Discard

4 Bolt Item (11) Retain

8 Washer Item (10) Discard

(d) Install the lower nuts.

Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 63

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4 Bolt Item (11) Retained at

removal

4 Nut ASNA2531-4 Item 1

8 Washer-Flat NAS1149F0432P Item 10

After tightened the nut Item 1 apply :

Identification Paint 07-020 As required

(2) Subtask 531218-831-003-001 - Replace the Fasteners at Nominal Diameter (Z130)

Work Zones and Access Panels

Zone Access/Work location

130 Work location Frame 24A

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

Material necessary to do the job

Kit 531218A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 ASNA2531-4 8 NUT

10 NAS1149F0432P 16 WASHER

12 D2551006220000 4 GUIDE

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

11 NAS6604-6 8 BOLT

NOTE: The quantities given in this Kit are valid for a maximum repair

configuration.

Consumable CMLA04

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Synth.ester Based Grease

High Pressure

04-004 As required

Identification Paint 07-020 As required

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 64

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References

Fig. A-FCDAA

Replacement of the Fasteners (Z130)

Sheet 01

Sheet 02

(a) Remove the upper nuts.

Refer to Fig. A-FCDAA Sheet 01 and Fig. A-FCDAA Sheet 02

4 Nut Item (1) Discard

4 Bolt Item (11) Discard

8 Washer Item (10) Discard

4 Guide Item (12) Discard

(b) Install the upper nuts.

Refer to Fig. A-FCDAA Sheet 01 and Fig. A-FCDAA Sheet 02

4 Guide D2551006220000 Item 12

4 Bolt NAS6604-6 Item 11

4 Nut ASNA2531-4 Item 1

8 Washer-Flat NAS1149F0432P Item 10

Apply on the guide Item 12 :

Synth.ester Based

Grease High

Pressure

04-004 As required

NOTE: Tightening torque the nut Item 1 between 0.70m.daN (62lbf.in.) and

0.80mdaN (71lbf.in.).

After tightened the nut Item 1 apply :

Identification Paint 07-020 As required

(c) Remove the lower nuts.

Refer to Fig. A-FCDAA Sheet 01 and Fig. A-FCDAA Sheet 02

4 Nut Item (1) Discard

4 Bolt Item (11) Discard

8 Washer Item (10) Discard

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 65

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(d) Install the lower nuts.

Refer to Fig. A-FCDAA Sheet 01 and Fig. A-FCDAA Sheet 02

4 Bolt NAS6604-6 Item 11

4 Nut ASNA2531-4 Item 1

8 Washer-Flat NAS1149F0432P Item 10

After tightened the nut Item 1 apply :

Identification Paint 07-020 As required

**CONF 003

(1) Subtask 531218-960-003-001 - Replace the Nuts with the Same PN (Z123-124)

Work Zones and Access Panels

Zone Access/Work location

From 123 Work location from Frame 9 to Frame 14

To 124 Work location from Frame 9 to Frame 14

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

Material necessary to do the job

Kit 531218A03R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 ASNA2531-4 10 NUT

References

Fig. A-FCBAA

Replacement of the Fasteners

(Z123-124)

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Replace the nuts of the Holes H10 thru H13 :

Refer to Fig. A-FCBAA Sheet 01, Fig. A-FCBAA Sheet 02 and Fig. A-FCBAA Sheet

06

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 66

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1 Remove :

4 Nut Item (1) Discard

NOTE: Use the ALEN key to maintain the bolts.

NOTE: If the bolt rotates during the removal of the nuts, refer to

SUBTASK 531218-210-006 001 Do a Visual Inspection of the

Holes (Z123-124) .

2 Install :

4 Nut ASNA2531-4 Item 1

NOTE: Use the ALEN key to maintain the bolts.

NOTE: If the bolt rotates during the removal of the nuts, refer to

SUBTASK 531218-210-006 001 Do a Visual Inspection of the

Holes (Z123-124) .

(b) Replace the nuts of the Holes H14 and H15 :

Refer to Fig. A-FCBAA Sheet 01, Fig. A-FCBAA Sheet 03 and Fig. A-FCBAA Sheet

06

1 Remove :

2 Nut Item (1) Discard

NOTE: Use the ALEN key to maintain the bolts.

NOTE: If the bolt rotates during the removal of the nuts, refer to

SUBTASK 531218-210-006 001 Do a Visual Inspection of the

Holes (Z123-124) .

2 Install :

2 Nut ASNA2531-4 Item 1

NOTE: Use the ALEN key to maintain the bolts.

NOTE: If the bolt rotates during the removal of the nuts, refer to

SUBTASK 531218-210-006 001 Do a Visual Inspection of the

Holes (Z123-124) .

(c) Replace the nuts of the Holes H16 thru H19 :

Refer to Fig. A-FCBAA Sheet 01, Fig. A-FCBAA Sheet 04 thru Fig. A-FCBAA Sheet

06

1 Remove :

4 Nut Item (1) Discard

NOTE: Use the ALEN key to maintain the bolts.

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 67

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NOTE: If the bolt rotates during the removal of the nuts, refer to

SUBTASK 531218-210-006 001 Do a Visual Inspection of the

Holes (Z123-124) .

2 Install :

4 Nut ASNA2531-4 Item 1

NOTE: Use the ALEN key to maintain the bolts.

NOTE: If the bolt rotates during the removal of the nuts, refer to

SUBTASK 531218-210-006 001 Do a Visual Inspection of the

Holes (Z123-124) .

(2) Subtask 531218-210-006-001 - Do a Visual Inspection of the Holes (Z123-124)

Work Zones and Access Panels

Zone Access/Work location

From 123 Work location from Frame 9 to Frame 14

To 124 Work location from Frame 9 to Frame 14

Manpower Resources

Manhours 1.50

Minimum number of person 1

Subtask elapsed time 1.50

Skills AIRFRAME

References

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

Fig. A-FCBAA

Replacement of the Fasteners

(Z123-124)

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

NOTE: The quantity given in this Subtask is valid for a maximum inspection

configuration.

(a) Holes H10 thru H13 :

Refer to Fig. A-FCBAA Sheet 01, Fig. A-FCBAA Sheet 02 and Fig. A-FCBAA Sheet

06

1 Remove the concerned bolt.

4 Bolt Item (4) Discard

2 Clean the hole.

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 68

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3 Do a visual inspection of the hole (Refer to NTM 51-90-00).

a If the hole is not scratched, replace the fastener at the nominal diameter

(Refer to SUBTASK 531218-831-005 001 Install the Fasteners at

Nominal Diameter (Z123-124) ).

b If the hole is scratched, replace the fastener at first oversize (Refer to

SUBTASK 531218-831-006 001 Install the Fasteners at First Oversize

Diameter (Z123-124) ).

(b) Holes H14 and H15 :

Refer to Fig. A-FCBAA Sheet 01, Fig. A-FCBAA Sheet 03 and Fig. A-FCBAA Sheet

06

1 Remove the concerned bolt.

2 Bolt Item (6) Discard

2 Clean the hole.

3 Replace the fastener at first oversize (Refer to SUBTASK 531218-831-006

001 Install the Fasteners at First Oversize Diameter (Z123-124) ).

(c) Holes H16 thru H19 :

Refer to Fig. A-FCBAA Sheet 01, Fig. A-FCBAA Sheet 04 thru Fig. A-FCBAA Sheet

06

1 Remove the concerned bolt.

4 Bolt Item (6) Discard

2 Clean the hole.

3 Do a visual inspection of the hole (Refer to NTM 51-90-00).

a If the hole is not scratched, replace the fastener at the nominal diameter

(Refer to SUBTASK 531218-831-005 001 Install the Fasteners at

Nominal Diameter (Z123-124) ).

b If the hole is scratched, replace the fastener at first oversize (Refer to

SUBTASK 531218-831-006 001 Install the Fasteners at First Oversize

Diameter (Z123-124) ).

(3) Subtask 531218-831-005-001 - Install the Fasteners at Nominal Diameter (Z123-124)

Work Zones and Access Panels

Zone Access/Work location

From 123 Work location from Frame 9 to Frame 14

To 124 Work location from Frame 9 to Frame 14

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 69

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Manpower Resources

Manhours 1.50

Minimum number of person 1

Subtask elapsed time 1.50

Skills AIRFRAME

Material necessary to do the job

Kit 531218A03R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 ASNA2531-4 8 NUT

Component COMPA03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

4 EN6114V4-11 4 BOLT

6 EN6114V4-12 4 BOLT

NOTE: The quantities given in this Kit are valid for a maximum repair

configuration.

References

Fig. A-FCBAA

Replacement of the Fasteners

(Z123-124)

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

NOTE: The quantities given in this Subtask are valid for a maximum repair

configuration.

(a) Holes H10 thru H13 :

Refer to Fig. A-FCBAA Sheet 01 thru Fig. A-FCBAA Sheet 06

1 Install :

4 Bolt EN6114V4-11 Item 4

4 Nut ASNA2531-4 Item 1

(b) Holes H16 thru H19 :

Refer to Fig. A-FCBAA Sheet 01, Fig. A-FCBAA Sheet 04 thru Fig. A-FCBAA Sheet

06

1 Install :

4 Bolt EN6114V4-12 Item 6

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 70

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4 Nut ASNA2531-4 Item 1

(4) Subtask 531218-831-006-001 - Install the Fasteners at First Oversize Diameter

(Z123-124)

Work Zones and Access Panels

Zone Access/Work location

From 123 Work location from Frame 9 to Frame 14

To 124 Work location from Frame 9 to Frame 14

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

Material necessary to do the job

Kit 531218A03R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 ASNA2531-4 10 NUT

Component COMPA03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

5 EN6114V4X-11 4 BOLT

7 EN6114V4X-12 6 BOLT

NOTE: The quantities given in this Kit are valid for a maximum repair

configuration.

References

Fig. A-FCBAA

Replacement of the Fasteners

(Z123-124)

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

NOTE: The quantities given in this Subtask are valid for a maximum repair

configuration.

(a) Holes H10 thru H13 :

Refer to Fig. A-FCBAA Sheet 01, Fig. A-FCBAA Sheet 02 and Fig. A-FCBAA Sheet

06

1 If not yet, remove :

4 Bolt Item (5) Discard

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 71

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2 Oversize the hole to the dimension given in Fig. A-FCBAA Sheet 06.

3 Clean the drilled areas.

4 Install :

4 Bolt EN6114V4X-11 Item 5

4 Nut ASNA2531-4 Item 1

(b) Holes H14 thru H15 :

Refer to Fig. A-FCBAA Sheet 01, Fig. A-FCBAA Sheet 03 and Fig. A-FCBAA Sheet

06

1 If not yet, remove :

2 Bolt Item (6) Discard

2 Oversize the hole to the dimension given in Fig. A-FCBAA Sheet 06.

3 Clean the drilled areas.

4 Install :

2 Bolt EN6114V4X-12 Item 7

2 Nut ASNA2531-4 Item 1

(c) Holes H16 thru H19 :

Refer to Fig. A-FCBAA Sheet 01, Fig. A-FCBAA Sheet 04 thru Fig. A-FCBAA Sheet

06

1 If not yet, remove :

4 Bolt Item (6) Discard

2 Oversize the hole to the dimension given in Fig. A-FCBAA Sheet 06.

3 Clean the drilled areas.

4 Install :

4 Bolt EN6114V4X-12 Item 7

4 Nut ASNA2531-4 Item 1

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 72

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**CONF 004

(1) Subtask 531218-960-002-001 - Replace the Nuts with the Same PN (Z130)

Work Zones and Access Panels

Zone Access/Work location

130 Work location Frame 24A

Manpower Resources

Manhours 0.75

Minimum number of person 1

Subtask elapsed time 0.75

Skills AIRFRAME

Material necessary to do the job

Kit 531218A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 ASNA2531-4 8 NUT

10 NAS1149F0432P 16 WASHER

Consumable CMLA04

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Identification Paint 07-020 As required

References

Fig. A-FCAAA

Replacement of the Nuts (Z130)

Sheet 01

Sheet 02

(a) Remove the upper nuts.

Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02

4 Nut Item (1) Discard

4 Bolt Item (11) Retain

8 Washer Item (10) Discard

(b) Install the upper nuts.

Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02

4 Bolt Item (11) Retained at

removal

4 Nut ASNA2531-4 Item 1

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 73

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8 Washer-Flat NAS1149F0432P Item 10

NOTE: Tightening torque the nut Item 1 between 0.70m.daN (62lbf.in.) and

0.80mdaN (71lbf.in.).

After tightened the nut Item 1 apply :

Identification Paint 07-020 As required

(c) Remove the lower nuts.

Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02

4 Nut Item (1) Discard

4 Bolt Item (11) Retain

8 Washer Item (10) Discard

(d) Install the lower nuts.

Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02

4 Bolt Item (11) Retained at

removal

4 Nut ASNA2531-4 Item 1

8 Washer-Flat NAS1149F0432P Item 10

After tightened the nut Item 1 apply :

Identification Paint 07-020 As required

(2) Subtask 531218-831-003-001 - Replace the Fasteners at Nominal Diameter (Z130)

Work Zones and Access Panels

Zone Access/Work location

130 Work location Frame 24A

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 74

5

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Material necessary to do the job

Kit 531218A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 ASNA2531-4 8 NUT

10 NAS1149F0432P 16 WASHER

12 D2551006220000 4 GUIDE

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

11 NAS6604-6 8 BOLT

NOTE: The quantities given in this Kit are valid for a maximum repair

configuration.

Consumable CMLA04

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Synth.ester Based Grease

High Pressure

04-004 As required

Identification Paint 07-020 As required

References

Fig. A-FCDAA

Replacement of the Fasteners (Z130)

Sheet 01

Sheet 02

(a) Remove the upper nuts.

Refer to Fig. A-FCDAA Sheet 01 and Fig. A-FCDAA Sheet 02

4 Nut Item (1) Discard

4 Bolt Item (11) Discard

8 Washer Item (10) Discard

4 Guide Item (12) Discard

(b) Install the upper nuts.

Refer to Fig. A-FCDAA Sheet 01 and Fig. A-FCDAA Sheet 02

4 Guide D2551006220000 Item 12

4 Bolt NAS6604-6 Item 11

4 Nut ASNA2531-4 Item 1

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 75

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8 Washer-Flat NAS1149F0432P Item 10

Apply on the guide Item 12 :

Synth.ester Based

Grease High

Pressure

04-004 As required

NOTE: Tightening torque the nut Item 1 between 0.70m.daN (62lbf.in.) and

0.80mdaN (71lbf.in.).

After tightened the nut Item 1 apply :

Identification Paint 07-020 As required

(c) Remove the lower nuts.

Refer to Fig. A-FCDAA Sheet 01 and Fig. A-FCDAA Sheet 02

4 Nut Item (1) Discard

4 Bolt Item (11) Discard

8 Washer Item (10) Discard

(d) Install the lower nuts.

Refer to Fig. A-FCDAA Sheet 01 and Fig. A-FCDAA Sheet 02

4 Bolt NAS6604-6 Item 11

4 Nut ASNA2531-4 Item 1

8 Washer-Flat NAS1149F0432P Item 10

After tightened the nut Item 1 apply :

Identification Paint 07-020 As required

(3) Subtask 531218-960-003-001 - Replace the Nuts with the Same PN (Z123-124)

Work Zones and Access Panels

Zone Access/Work location

From 123 Work location from Frame 9 to Frame 14

To 124 Work location from Frame 9 to Frame 14

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 76

5

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SERVICE BULLETIN

Material necessary to do the job

Kit 531218A03R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 ASNA2531-4 10 NUT

References

Fig. A-FCBAA

Replacement of the Fasteners

(Z123-124)

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Replace the nuts of the Holes H10 thru H13 :

Refer to Fig. A-FCBAA Sheet 01, Fig. A-FCBAA Sheet 02 and Fig. A-FCBAA Sheet

06

1 Remove :

4 Nut Item (1) Discard

NOTE: Use the ALEN key to maintain the bolts.

NOTE: If the bolt rotates during the removal of the nuts, refer to

SUBTASK 531218-210-006 001 Do a Visual Inspection of the

Holes (Z123-124) .

2 Install :

4 Nut ASNA2531-4 Item 1

NOTE: Use the ALEN key to maintain the bolts.

NOTE: If the bolt rotates during the removal of the nuts, refer to

SUBTASK 531218-210-006 001 Do a Visual Inspection of the

Holes (Z123-124) .

(b) Replace the nuts of the Holes H14 and H15 :

Refer to Fig. A-FCBAA Sheet 01, Fig. A-FCBAA Sheet 03 and Fig. A-FCBAA Sheet

06

1 Remove :

2 Nut Item (1) Discard

NOTE: Use the ALEN key to maintain the bolts.

NOTE: If the bolt rotates during the removal of the nuts, refer to

SUBTASK 531218-210-006 001 Do a Visual Inspection of the

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 77

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Holes (Z123-124) .

2 Install :

2 Nut ASNA2531-4 Item 1

NOTE: Use the ALEN key to maintain the bolts.

NOTE: If the bolt rotates during the removal of the nuts, refer to

SUBTASK 531218-210-006 001 Do a Visual Inspection of the

Holes (Z123-124) .

(c) Replace the nuts of the Holes H16 thru H19 :

Refer to Fig. A-FCBAA Sheet 01, Fig. A-FCBAA Sheet 04 thru Fig. A-FCBAA Sheet

06

1 Remove :

4 Nut Item (1) Discard

NOTE: Use the ALEN key to maintain the bolts.

NOTE: If the bolt rotates during the removal of the nuts, refer to

SUBTASK 531218-210-006 001 Do a Visual Inspection of the

Holes (Z123-124) .

2 Install :

4 Nut ASNA2531-4 Item 1

NOTE: Use the ALEN key to maintain the bolts.

NOTE: If the bolt rotates during the removal of the nuts, refer to

SUBTASK 531218-210-006 001 Do a Visual Inspection of the

Holes (Z123-124) .

(4) Subtask 531218-210-006-001 - Do a Visual Inspection of the Holes (Z123-124)

Work Zones and Access Panels

Zone Access/Work location

From 123 Work location from Frame 9 to Frame 14

To 124 Work location from Frame 9 to Frame 14

Manpower Resources

Manhours 1.50

Minimum number of person 1

Subtask elapsed time 1.50

Skills AIRFRAME

References

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

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 78

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References

Fig. A-FCBAA

Replacement of the Fasteners

(Z123-124)

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

NOTE: The quantity given in this Subtask is valid for a maximum inspection

configuration.

(a) Holes H10 thru H13 :

Refer to Fig. A-FCBAA Sheet 01, Fig. A-FCBAA Sheet 02 and Fig. A-FCBAA Sheet

06

1 Remove the concerned bolt.

4 Bolt Item (4) Discard

2 Clean the hole.

3 Do a visual inspection of the hole (Refer to NTM 51-90-00).

a If the hole is not scratched, replace the fastener at the nominal diameter

(Refer to SUBTASK 531218-831-005 001 Install the Fasteners at

Nominal Diameter (Z123-124) ).

b If the hole is scratched, replace the fastener at first oversize (Refer to

SUBTASK 531218-831-006 001 Install the Fasteners at First Oversize

Diameter (Z123-124) ).

(b) Holes H14 and H15 :

Refer to Fig. A-FCBAA Sheet 01, Fig. A-FCBAA Sheet 03 and Fig. A-FCBAA Sheet

06

1 Remove the concerned bolt.

2 Bolt Item (6) Discard

2 Clean the hole.

3 Replace the fastener at first oversize (Refer to SUBTASK 531218-831-006

001 Install the Fasteners at First Oversize Diameter (Z123-124) ).

(c) Holes H16 thru H19 :

Refer to Fig. A-FCBAA Sheet 01, Fig. A-FCBAA Sheet 04 thru Fig. A-FCBAA Sheet

06

1 Remove the concerned bolt.

4 Bolt Item (6) Discard

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 79

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2 Clean the hole.

3 Do a visual inspection of the hole (Refer to NTM 51-90-00).

a If the hole is not scratched, replace the fastener at the nominal diameter

(Refer to SUBTASK 531218-831-005 001 Install the Fasteners at

Nominal Diameter (Z123-124) ).

b If the hole is scratched, replace the fastener at first oversize (Refer to

SUBTASK 531218-831-006 001 Install the Fasteners at First Oversize

Diameter (Z123-124) ).

(5) Subtask 531218-831-005-001 - Install the Fasteners at Nominal Diameter (Z123-124)

Work Zones and Access Panels

Zone Access/Work location

From 123 Work location from Frame 9 to Frame 14

To 124 Work location from Frame 9 to Frame 14

Manpower Resources

Manhours 1.50

Minimum number of person 1

Subtask elapsed time 1.50

Skills AIRFRAME

Material necessary to do the job

Kit 531218A03R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 ASNA2531-4 8 NUT

Component COMPA03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

4 EN6114V4-11 4 BOLT

6 EN6114V4-12 4 BOLT

NOTE: The quantities given in this Kit are valid for a maximum repair

configuration.

References

Fig. A-FCBAA

Replacement of the Fasteners

(Z123-124)

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

NOTE: The quantities given in this Subtask are valid for a maximum repair

configuration.

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 80

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(a) Holes H10 thru H13 :

Refer to Fig. A-FCBAA Sheet 01 thru Fig. A-FCBAA Sheet 06

1 Install :

4 Bolt EN6114V4-11 Item 4

4 Nut ASNA2531-4 Item 1

(b) Holes H16 thru H19 :

Refer to Fig. A-FCBAA Sheet 01, Fig. A-FCBAA Sheet 04 thru Fig. A-FCBAA Sheet

06

1 Install :

4 Bolt EN6114V4-12 Item 6

4 Nut ASNA2531-4 Item 1

(6) Subtask 531218-831-006-001 - Install the Fasteners at First Oversize Diameter

(Z123-124)

Work Zones and Access Panels

Zone Access/Work location

From 123 Work location from Frame 9 to Frame 14

To 124 Work location from Frame 9 to Frame 14

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

Material necessary to do the job

Kit 531218A03R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 ASNA2531-4 10 NUT

Component COMPA03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

5 EN6114V4X-11 4 BOLT

7 EN6114V4X-12 6 BOLT

NOTE: The quantities given in this Kit are valid for a maximum repair

configuration.

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 81

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References

Fig. A-FCBAA

Replacement of the Fasteners

(Z123-124)

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

NOTE: The quantities given in this Subtask are valid for a maximum repair

configuration.

(a) Holes H10 thru H13 :

Refer to Fig. A-FCBAA Sheet 01, Fig. A-FCBAA Sheet 02 and Fig. A-FCBAA Sheet

06

1 If not yet, remove :

4 Bolt Item (5) Discard

2 Oversize the hole to the dimension given in Fig. A-FCBAA Sheet 06.

3 Clean the drilled areas.

4 Install :

4 Bolt EN6114V4X-11 Item 5

4 Nut ASNA2531-4 Item 1

(b) Holes H14 thru H15 :

Refer to Fig. A-FCBAA Sheet 01, Fig. A-FCBAA Sheet 03 and Fig. A-FCBAA Sheet

06

1 If not yet, remove :

2 Bolt Item (6) Discard

2 Oversize the hole to the dimension given in Fig. A-FCBAA Sheet 06.

3 Clean the drilled areas.

4 Install :

2 Bolt EN6114V4X-12 Item 7

2 Nut ASNA2531-4 Item 1

(c) Holes H16 thru H19 :

Refer to Fig. A-FCBAA Sheet 01, Fig. A-FCBAA Sheet 04 thru Fig. A-FCBAA Sheet

06

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 82

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1 If not yet, remove :

4 Bolt Item (6) Discard

2 Oversize the hole to the dimension given in Fig. A-FCBAA Sheet 06.

3 Clean the drilled areas.

4 Install :

4 Bolt EN6114V4X-12 Item 7

4 Nut ASNA2531-4 Item 1

**CONF 005

(1) Subtask 531218-960-001-001 - Replace the Nuts with the Same PN (Z232)

Work Zones and Access Panels

Zone Access/Work location

232 Work location Frame 35

Stringer 11

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 531218A01R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 ASNA2531-4 3 NUT

References

Fig. A-FCCAA

Replacement of the Fasteners (Z232)

Sheet 01

Sheet 02

Sheet 03

(a) Remove the nuts :

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

3 Nut Item (1) Discard

NOTE: Use the ALEN key to maintain the bolts.

NOTE: If the bolt rotates during the removal of the nuts, refer to SUBTASK

531218-210-004 001 Do a Visual Inspection of the Holes (Z232) .

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 83

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(b) Install the nuts :

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

3 Nut ASNA2531-4 Item 1

NOTE: Use the ALEN key to maintain the bolts.

NOTE: If the bolt rotates during the installation of the nuts, refer to

SUBTASK 531218-210-004 001 Do a Visual Inspection of the Holes

(Z232) .

(2) Subtask 531218-210-004-001 - Do a Visual Inspection of the Holes (Z232)

Work Zones and Access Panels

Zone Access/Work location

232 Work location Frame 35

Stringer 11

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

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

Fig. A-FCCAA

Replacement of the Fasteners (Z232)

Sheet 01

Sheet 02

Sheet 03

(a) Remove the concerned bolt.

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

3 Bolt Item (2) Discard

NOTE: The quantity given in this Subtask is valid for a maximum inspection

configuration.

(b) Clean the hole.

(c) Do a visual inspection of the hole (Refer to NTM 51-90-00).

1 If the hole is not scratched, replace the fastener at the nominal diameter

(Refer to SUBTASK 531218-831-001 001 Install the Fasteners at Nominal

Diameter (Z232) ).

2 If the hole is scratched, replace the fastener at first oversize (Refer to

SUBTASK 531218-831-002 001 Install the Fasteners at First Oversize

Diameter (Z232) ).

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 84

5

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(3) Subtask 531218-831-001-001 - Install the Fasteners at Nominal Diameter (Z232)

Work Zones and Access Panels

Zone Access/Work location

232 Work location Frame 35

Stringer 11

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Kit 531218A01R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 ASNA2531-4 3 NUT

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 EN6115V4-5 3 BOLT

NOTE: The quantities given in this Kit are valid for a maximum repair

configuration.

References

Fig. A-FCCAA

Replacement of the Fasteners (Z232)

Sheet 01

Sheet 02

Sheet 03

(a) Install :

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

3 Bolt EN6115V4-5 Item 2

3 Nut ASNA2531-4 Item 1

NOTE: The quantities given in this Subtask are valid for a maximum repair

configuration.

(4) Subtask 531218-831-002-001 - Install the Fasteners at First Oversize Diameter

(Z232)

Work Zones and Access Panels

Zone Access/Work location

232 Work location Frame 35

Stringer 11

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 85

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Manpower Resources

Manhours 0.75

Minimum number of person 1

Subtask elapsed time 0.75

Skills AIRFRAME

Material necessary to do the job

Kit 531218A01R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 ASNA2531-4 3 NUT

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

3 EN6115V4X-5 3 BOLT

NOTE: The quantities given in this Kit are valid for a maximum repair

configuration.

References

Fig. A-FCCAA

Replacement of the Fasteners (Z232)

Sheet 01

Sheet 02

Sheet 03

(a) If not yet, remove :

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

3 Bolt Item (2) Discard

(b) Oversize the hole to the dimension given in Fig. A-FCCAA Sheet 03.

(c) Clean the drilled areas.

(d) Install :

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

3 Bolt EN6115V4X-5 Item 3

3 Nut ASNA2531-4 Item 1

NOTE: The quantities given in this Subtask are valid for a maximum repair

configuration.

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 86

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SERVICE BULLETIN

(5) Subtask 531218-960-002-001 - Replace the Nuts with the Same PN (Z130)

Work Zones and Access Panels

Zone Access/Work location

130 Work location Frame 24A

Manpower Resources

Manhours 0.75

Minimum number of person 1

Subtask elapsed time 0.75

Skills AIRFRAME

Material necessary to do the job

Kit 531218A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 ASNA2531-4 8 NUT

10 NAS1149F0432P 16 WASHER

Consumable CMLA04

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Identification Paint 07-020 As required

References

Fig. A-FCAAA

Replacement of the Nuts (Z130)

Sheet 01

Sheet 02

(a) Remove the upper nuts.

Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02

4 Nut Item (1) Discard

4 Bolt Item (11) Retain

8 Washer Item (10) Discard

(b) Install the upper nuts.

Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02

4 Bolt Item (11) Retained at

removal

4 Nut ASNA2531-4 Item 1

8 Washer-Flat NAS1149F0432P Item 10

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 87

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NOTE: Tightening torque the nut Item 1 between 0.70m.daN (62lbf.in.) and

0.80mdaN (71lbf.in.).

After tightened the nut Item 1 apply :

Identification Paint 07-020 As required

(c) Remove the lower nuts.

Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02

4 Nut Item (1) Discard

4 Bolt Item (11) Retain

8 Washer Item (10) Discard

(d) Install the lower nuts.

Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02

4 Bolt Item (11) Retained at

removal

4 Nut ASNA2531-4 Item 1

8 Washer-Flat NAS1149F0432P Item 10

After tightened the nut Item 1 apply :

Identification Paint 07-020 As required

(6) Subtask 531218-831-003-001 - Replace the Fasteners at Nominal Diameter (Z130)

Work Zones and Access Panels

Zone Access/Work location

130 Work location Frame 24A

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

Material necessary to do the job

Kit 531218A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 ASNA2531-4 8 NUT

10 NAS1149F0432P 16 WASHER

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 88

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ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

12 D2551006220000 4 GUIDE

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

11 NAS6604-6 8 BOLT

NOTE: The quantities given in this Kit are valid for a maximum repair

configuration.

Consumable CMLA04

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Synth.ester Based Grease

High Pressure

04-004 As required

Identification Paint 07-020 As required

References

Fig. A-FCDAA

Replacement of the Fasteners (Z130)

Sheet 01

Sheet 02

(a) Remove the upper nuts.

Refer to Fig. A-FCDAA Sheet 01 and Fig. A-FCDAA Sheet 02

4 Nut Item (1) Discard

4 Bolt Item (11) Discard

8 Washer Item (10) Discard

4 Guide Item (12) Discard

(b) Install the upper nuts.

Refer to Fig. A-FCDAA Sheet 01 and Fig. A-FCDAA Sheet 02

4 Guide D2551006220000 Item 12

4 Bolt NAS6604-6 Item 11

4 Nut ASNA2531-4 Item 1

8 Washer-Flat NAS1149F0432P Item 10

Apply on the guide Item 12 :

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 89

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Synth.ester Based

Grease High

Pressure

04-004 As required

NOTE: Tightening torque the nut Item 1 between 0.70m.daN (62lbf.in.) and

0.80mdaN (71lbf.in.).

After tightened the nut Item 1 apply :

Identification Paint 07-020 As required

(c) Remove the lower nuts.

Refer to Fig. A-FCDAA Sheet 01 and Fig. A-FCDAA Sheet 02

4 Nut Item (1) Discard

4 Bolt Item (11) Discard

8 Washer Item (10) Discard

(d) Install the lower nuts.

Refer to Fig. A-FCDAA Sheet 01 and Fig. A-FCDAA Sheet 02

4 Bolt NAS6604-6 Item 11

4 Nut ASNA2531-4 Item 1

8 Washer-Flat NAS1149F0432P Item 10

After tightened the nut Item 1 apply :

Identification Paint 07-020 As required

**CONF 006

(1) Subtask 531218-960-001-001 - Replace the Nuts with the Same PN (Z232)

Work Zones and Access Panels

Zone Access/Work location

232 Work location Frame 35

Stringer 11

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 90

5

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Material necessary to do the job

Kit 531218A01R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 ASNA2531-4 3 NUT

References

Fig. A-FCCAA

Replacement of the Fasteners (Z232)

Sheet 01

Sheet 02

Sheet 03

(a) Remove the nuts :

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

3 Nut Item (1) Discard

NOTE: Use the ALEN key to maintain the bolts.

NOTE: If the bolt rotates during the removal of the nuts, refer to SUBTASK

531218-210-004 001 Do a Visual Inspection of the Holes (Z232) .

(b) Install the nuts :

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

3 Nut ASNA2531-4 Item 1

NOTE: Use the ALEN key to maintain the bolts.

NOTE: If the bolt rotates during the installation of the nuts, refer to

SUBTASK 531218-210-004 001 Do a Visual Inspection of the Holes

(Z232) .

(2) Subtask 531218-210-004-001 - Do a Visual Inspection of the Holes (Z232)

Work Zones and Access Panels

Zone Access/Work location

232 Work location Frame 35

Stringer 11

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

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

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 91

5

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References

Fig. A-FCCAA

Replacement of the Fasteners (Z232)

Sheet 01

Sheet 02

Sheet 03

(a) Remove the concerned bolt.

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

3 Bolt Item (2) Discard

NOTE: The quantity given in this Subtask is valid for a maximum inspection

configuration.

(b) Clean the hole.

(c) Do a visual inspection of the hole (Refer to NTM 51-90-00).

1 If the hole is not scratched, replace the fastener at the nominal diameter

(Refer to SUBTASK 531218-831-001 001 Install the Fasteners at Nominal

Diameter (Z232) ).

2 If the hole is scratched, replace the fastener at first oversize (Refer to

SUBTASK 531218-831-002 001 Install the Fasteners at First Oversize

Diameter (Z232) ).

(3) Subtask 531218-831-001-001 - Install the Fasteners at Nominal Diameter (Z232)

Work Zones and Access Panels

Zone Access/Work location

232 Work location Frame 35

Stringer 11

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Kit 531218A01R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 ASNA2531-4 3 NUT

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 EN6115V4-5 3 BOLT

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 92

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NOTE: The quantities given in this Kit are valid for a maximum repair

configuration.

References

Fig. A-FCCAA

Replacement of the Fasteners (Z232)

Sheet 01

Sheet 02

Sheet 03

(a) Install :

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

3 Bolt EN6115V4-5 Item 2

3 Nut ASNA2531-4 Item 1

NOTE: The quantities given in this Subtask are valid for a maximum repair

configuration.

(4) Subtask 531218-831-002-001 - Install the Fasteners at First Oversize Diameter

(Z232)

Work Zones and Access Panels

Zone Access/Work location

232 Work location Frame 35

Stringer 11

Manpower Resources

Manhours 0.75

Minimum number of person 1

Subtask elapsed time 0.75

Skills AIRFRAME

Material necessary to do the job

Kit 531218A01R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 ASNA2531-4 3 NUT

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

3 EN6115V4X-5 3 BOLT

NOTE: The quantities given in this Kit are valid for a maximum repair

configuration.

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 93

5

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References

Fig. A-FCCAA

Replacement of the Fasteners (Z232)

Sheet 01

Sheet 02

Sheet 03

(a) If not yet, remove :

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

3 Bolt Item (2) Discard

(b) Oversize the hole to the dimension given in Fig. A-FCCAA Sheet 03.

(c) Clean the drilled areas.

(d) Install :

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

3 Bolt EN6115V4X-5 Item 3

3 Nut ASNA2531-4 Item 1

NOTE: The quantities given in this Subtask are valid for a maximum repair

configuration.

(5) Subtask 531218-960-002-001 - Replace the Nuts with the Same PN (Z130)

Work Zones and Access Panels

Zone Access/Work location

130 Work location Frame 24A

Manpower Resources

Manhours 0.75

Minimum number of person 1

Subtask elapsed time 0.75

Skills AIRFRAME

Material necessary to do the job

Kit 531218A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 ASNA2531-4 8 NUT

10 NAS1149F0432P 16 WASHER

Consumable CMLA04

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Identification Paint 07-020 As required

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 94

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References

Fig. A-FCAAA

Replacement of the Nuts (Z130)

Sheet 01

Sheet 02

(a) Remove the upper nuts.

Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02

4 Nut Item (1) Discard

4 Bolt Item (11) Retain

8 Washer Item (10) Discard

(b) Install the upper nuts.

Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02

4 Bolt Item (11) Retained at

removal

4 Nut ASNA2531-4 Item 1

8 Washer-Flat NAS1149F0432P Item 10

NOTE: Tightening torque the nut Item 1 between 0.70m.daN (62lbf.in.) and

0.80mdaN (71lbf.in.).

After tightened the nut Item 1 apply :

Identification Paint 07-020 As required

(c) Remove the lower nuts.

Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02

4 Nut Item (1) Discard

4 Bolt Item (11) Retain

8 Washer Item (10) Discard

(d) Install the lower nuts.

Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02

4 Bolt Item (11) Retained at

removal

4 Nut ASNA2531-4 Item 1

8 Washer-Flat NAS1149F0432P Item 10

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 95

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After tightened the nut Item 1 apply :

Identification Paint 07-020 As required

(6) Subtask 531218-831-003-001 - Replace the Fasteners at Nominal Diameter (Z130)

Work Zones and Access Panels

Zone Access/Work location

130 Work location Frame 24A

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

Material necessary to do the job

Kit 531218A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 ASNA2531-4 8 NUT

10 NAS1149F0432P 16 WASHER

12 D2551006220000 4 GUIDE

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

11 NAS6604-6 8 BOLT

NOTE: The quantities given in this Kit are valid for a maximum repair

configuration.

Consumable CMLA04

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Synth.ester Based Grease

High Pressure

04-004 As required

Identification Paint 07-020 As required

References

Fig. A-FCDAA

Replacement of the Fasteners (Z130)

Sheet 01

Sheet 02

(a) Remove the upper nuts.

Refer to Fig. A-FCDAA Sheet 01 and Fig. A-FCDAA Sheet 02

4 Nut Item (1) Discard

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 96

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4 Bolt Item (11) Discard

8 Washer Item (10) Discard

4 Guide Item (12) Discard

(b) Install the upper nuts.

Refer to Fig. A-FCDAA Sheet 01 and Fig. A-FCDAA Sheet 02

4 Guide D2551006220000 Item 12

4 Bolt NAS6604-6 Item 11

4 Nut ASNA2531-4 Item 1

8 Washer-Flat NAS1149F0432P Item 10

Apply on the guide Item 12 :

Synth.ester Based

Grease High

Pressure

04-004 As required

NOTE: Tightening torque the nut Item 1 between 0.70m.daN (62lbf.in.) and

0.80mdaN (71lbf.in.).

After tightened the nut Item 1 apply :

Identification Paint 07-020 As required

(c) Remove the lower nuts.

Refer to Fig. A-FCDAA Sheet 01 and Fig. A-FCDAA Sheet 02

4 Nut Item (1) Discard

4 Bolt Item (11) Discard

8 Washer Item (10) Discard

(d) Install the lower nuts.

Refer to Fig. A-FCDAA Sheet 01 and Fig. A-FCDAA Sheet 02

4 Bolt NAS6604-6 Item 11

4 Nut ASNA2531-4 Item 1

8 Washer-Flat NAS1149F0432P Item 10

After tightened the nut Item 1 apply :

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 97

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Identification Paint 07-020 As required

(7) Subtask 531218-960-003-001 - Replace the Nuts with the Same PN (Z123-124)

Work Zones and Access Panels

Zone Access/Work location

From 123 Work location from Frame 9 to Frame 14

To 124 Work location from Frame 9 to Frame 14

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

Material necessary to do the job

Kit 531218A03R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 ASNA2531-4 10 NUT

References

Fig. A-FCBAA

Replacement of the Fasteners

(Z123-124)

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Replace the nuts of the Holes H10 thru H13 :

Refer to Fig. A-FCBAA Sheet 01, Fig. A-FCBAA Sheet 02 and Fig. A-FCBAA Sheet

06

1 Remove :

4 Nut Item (1) Discard

NOTE: Use the ALEN key to maintain the bolts.

NOTE: If the bolt rotates during the removal of the nuts, refer to

SUBTASK 531218-210-006 001 Do a Visual Inspection of the

Holes (Z123-124) .

2 Install :

4 Nut ASNA2531-4 Item 1

NOTE: Use the ALEN key to maintain the bolts.

NOTE: If the bolt rotates during the removal of the nuts, refer to

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 98

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SUBTASK 531218-210-006 001 Do a Visual Inspection of the

Holes (Z123-124) .

(b) Replace the nuts of the Holes H14 and H15 :

Refer to Fig. A-FCBAA Sheet 01, Fig. A-FCBAA Sheet 03 and Fig. A-FCBAA Sheet

06

1 Remove :

2 Nut Item (1) Discard

NOTE: Use the ALEN key to maintain the bolts.

NOTE: If the bolt rotates during the removal of the nuts, refer to

SUBTASK 531218-210-006 001 Do a Visual Inspection of the

Holes (Z123-124) .

2 Install :

2 Nut ASNA2531-4 Item 1

NOTE: Use the ALEN key to maintain the bolts.

NOTE: If the bolt rotates during the removal of the nuts, refer to

SUBTASK 531218-210-006 001 Do a Visual Inspection of the

Holes (Z123-124) .

(c) Replace the nuts of the Holes H16 thru H19 :

Refer to Fig. A-FCBAA Sheet 01, Fig. A-FCBAA Sheet 04 thru Fig. A-FCBAA Sheet

06

1 Remove :

4 Nut Item (1) Discard

NOTE: Use the ALEN key to maintain the bolts.

NOTE: If the bolt rotates during the removal of the nuts, refer to

SUBTASK 531218-210-006 001 Do a Visual Inspection of the

Holes (Z123-124) .

2 Install :

4 Nut ASNA2531-4 Item 1

NOTE: Use the ALEN key to maintain the bolts.

NOTE: If the bolt rotates during the removal of the nuts, refer to

SUBTASK 531218-210-006 001 Do a Visual Inspection of the

Holes (Z123-124) .

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 99

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(8) Subtask 531218-210-006-001 - Do a Visual Inspection of the Holes (Z123-124)

Work Zones and Access Panels

Zone Access/Work location

From 123 Work location from Frame 9 to Frame 14

To 124 Work location from Frame 9 to Frame 14

Manpower Resources

Manhours 1.50

Minimum number of person 1

Subtask elapsed time 1.50

Skills AIRFRAME

References

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

Fig. A-FCBAA

Replacement of the Fasteners

(Z123-124)

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

NOTE: The quantity given in this Subtask is valid for a maximum inspection

configuration.

(a) Holes H10 thru H13 :

Refer to Fig. A-FCBAA Sheet 01, Fig. A-FCBAA Sheet 02 and Fig. A-FCBAA Sheet

06

1 Remove the concerned bolt.

4 Bolt Item (4) Discard

2 Clean the hole.

3 Do a visual inspection of the hole (Refer to NTM 51-90-00).

a If the hole is not scratched, replace the fastener at the nominal diameter

(Refer to SUBTASK 531218-831-005 001 Install the Fasteners at

Nominal Diameter (Z123-124) ).

b If the hole is scratched, replace the fastener at first oversize (Refer to

SUBTASK 531218-831-006 001 Install the Fasteners at First Oversize

Diameter (Z123-124) ).

(b) Holes H14 and H15 :

Refer to Fig. A-FCBAA Sheet 01, Fig. A-FCBAA Sheet 03 and Fig. A-FCBAA Sheet

06

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 100

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1 Remove the concerned bolt.

2 Bolt Item (6) Discard

2 Clean the hole.

3 Replace the fastener at first oversize (Refer to SUBTASK 531218-831-006

001 Install the Fasteners at First Oversize Diameter (Z123-124) ).

(c) Holes H16 thru H19 :

Refer to Fig. A-FCBAA Sheet 01, Fig. A-FCBAA Sheet 04 thru Fig. A-FCBAA Sheet

06

1 Remove the concerned bolt.

4 Bolt Item (6) Discard

2 Clean the hole.

3 Do a visual inspection of the hole (Refer to NTM 51-90-00).

a If the hole is not scratched, replace the fastener at the nominal diameter

(Refer to SUBTASK 531218-831-005 001 Install the Fasteners at

Nominal Diameter (Z123-124) ).

b If the hole is scratched, replace the fastener at first oversize (Refer to

SUBTASK 531218-831-006 001 Install the Fasteners at First Oversize

Diameter (Z123-124) ).

(9) Subtask 531218-831-005-001 - Install the Fasteners at Nominal Diameter (Z123-124)

Work Zones and Access Panels

Zone Access/Work location

From 123 Work location from Frame 9 to Frame 14

To 124 Work location from Frame 9 to Frame 14

Manpower Resources

Manhours 1.50

Minimum number of person 1

Subtask elapsed time 1.50

Skills AIRFRAME

Material necessary to do the job

Kit 531218A03R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 ASNA2531-4 8 NUT

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 101

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Component COMPA03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

4 EN6114V4-11 4 BOLT

6 EN6114V4-12 4 BOLT

NOTE: The quantities given in this Kit are valid for a maximum repair

configuration.

References

Fig. A-FCBAA

Replacement of the Fasteners

(Z123-124)

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

NOTE: The quantities given in this Subtask are valid for a maximum repair

configuration.

(a) Holes H10 thru H13 :

Refer to Fig. A-FCBAA Sheet 01 thru Fig. A-FCBAA Sheet 06

1 Install :

4 Bolt EN6114V4-11 Item 4

4 Nut ASNA2531-4 Item 1

(b) Holes H16 thru H19 :

Refer to Fig. A-FCBAA Sheet 01, Fig. A-FCBAA Sheet 04 thru Fig. A-FCBAA Sheet

06

1 Install :

4 Bolt EN6114V4-12 Item 6

4 Nut ASNA2531-4 Item 1

(10) Subtask 531218-831-006-001 - Install the Fasteners at First Oversize Diameter

(Z123-124)

Work Zones and Access Panels

Zone Access/Work location

From 123 Work location from Frame 9 to Frame 14

To 124 Work location from Frame 9 to Frame 14

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 102

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Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

Material necessary to do the job

Kit 531218A03R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 ASNA2531-4 10 NUT

Component COMPA03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

5 EN6114V4X-11 4 BOLT

7 EN6114V4X-12 6 BOLT

NOTE: The quantities given in this Kit are valid for a maximum repair

configuration.

References

Fig. A-FCBAA

Replacement of the Fasteners

(Z123-124)

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

NOTE: The quantities given in this Subtask are valid for a maximum repair

configuration.

(a) Holes H10 thru H13 :

Refer to Fig. A-FCBAA Sheet 01, Fig. A-FCBAA Sheet 02 and Fig. A-FCBAA Sheet

06

1 If not yet, remove :

4 Bolt Item (5) Discard

2 Oversize the hole to the dimension given in Fig. A-FCBAA Sheet 06.

3 Clean the drilled areas.

4 Install :

4 Bolt EN6114V4X-11 Item 5

4 Nut ASNA2531-4 Item 1

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 103

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(b) Holes H14 thru H15 :

Refer to Fig. A-FCBAA Sheet 01, Fig. A-FCBAA Sheet 03 and Fig. A-FCBAA Sheet

06

1 If not yet, remove :

2 Bolt Item (6) Discard

2 Oversize the hole to the dimension given in Fig. A-FCBAA Sheet 06.

3 Clean the drilled areas.

4 Install :

2 Bolt EN6114V4X-12 Item 7

2 Nut ASNA2531-4 Item 1

(c) Holes H16 thru H19 :

Refer to Fig. A-FCBAA Sheet 01, Fig. A-FCBAA Sheet 04 thru Fig. A-FCBAA Sheet

06

1 If not yet, remove :

4 Bolt Item (6) Discard

2 Oversize the hole to the dimension given in Fig. A-FCBAA Sheet 06.

3 Clean the drilled areas.

4 Install :

4 Bolt EN6114V4X-12 Item 7

4 Nut ASNA2531-4 Item 1

**CONF 007

None

**CONF ALL

D. TEST

**CONF 001

None

**CONF 002

None

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 104

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**CONF 003

None

**CONF 004

None

**CONF 005

None

**CONF 006

None

**CONF 007

None

**CONF ALL

E. CLOSE-UP

**CONF 001

None

**CONF 002

None

**CONF 003

None

**CONF 004

None

**CONF 005

None

**CONF 006

None

**CONF 007

None

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 105

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**CONF 001, 005 thru 006

N_SB_531218_5_BCAA_01_00

Z232

A

STGR10

STGR11

FR35 FR35.1 FR35.4

FWD

B

FR35

FR35.4

A

C

B

Figure A-FBCAA - Sheet 01

Inspection Area (Z232)

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 106

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**CONF 001, 005 thru 006

FWD

N_SB_531218_5_BCAA_02_00

BOTTOM VIEW

C

NOTE:

01 FASTENERS TO BE INSPECTED

FASTENERS NOT AFFECTED

01

Figure A-FBCAA - Sheet 02

Inspection Area (Z232)

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 107

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**CONF 001, 005 thru 006

IN Z232 AT THE THRESHOLD GIVEN IN THE

PLANNING INFORMATION PARAGRAPH E.(2).

NO MISSING

DO A DETAILED VISUAL INSPECTION OF THE NUTS

REPLACE THE NUT WITH

THE SAME PN

REFER TO REPAIR

SUBTASK 531218−210−004−001

NUT YES

CRACKED NO NUT YES

REFER TO REPAIR

ROTATE NO BOLT YES

SEND INSPECTION

REPORT TO AIRBUS

NO FURTHER ACTION

NO FURTHER ACTION

REPLACE THE FASTENERS

AT THE FIRST OVERSIZE

REFER TO REPAIR

SUBTASK 531218−831−002−001

SEND INSPECTION

REPORT TO AIRBUS

SUBTASK 531218−960−001−001

QUESTION

ACTION

FINDING

NOTE:

01 THIS INFORMATION IS TO BE RECORDED IN THE INSPECTION REPORT

01

N_SB_531218_5_FCAA_01_01

FIND THE MISSING

PARTS

Figure A-FFCAA - Sheet 01

Flow Chart (Z232)

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 108

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**CONF 002, 004 thru 006

Z130

FR35.5

FR24

FR24A

FR28

B

A

FR24A

A

Y 1300

Y 765

Y 254

Y−254

Y−765

VIEW LOOKING FWD

N_SB_531218_5_BAAA_01_00

C C C C

D D D D

B

Figure A-FBAAA - Sheet 01

Inspection Area (Z130)

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 109

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**CONF 002, 004 thru 006

VIEW LOOKING FWD

N_SB_531218_5_BAAA_02_00

TYPICAL VIEW

VIEW LOOKING FWD

TYPICAL VIEW

C

D

NOTE:

01 FASTENERS TO BE INSPECTED

01

01

Figure A-FBAAA - Sheet 02

Inspection Area (Z130)

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 110

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**CONF 002, 004 thru 006

IN Z130 AT THE THRESHOLD GIVEN IN THE

PLANNING INFORMATION PARAGRAPH E.(2).

NO MISSING

DO A DETAILED VISUAL INSPECTION OF THE NUTS

REPLACE THE NUT WITH

THE SAME PN

NUT YES

CRACKED NO NUT YES

REFER TO REPAIR

SEND INSPECTION

REPORT TO AIRBUS

NO FURTHER ACTION

NO FURTHER ACTION

REPLACE THE FASTENERS

AT NOMINAL DIAMETER

REFER TO REPAIR

SUBTASK 531218−831−003−001

SEND INSPECTION

REPORT TO AIRBUS

SUBTASK 531218−960−002−001

QUESTION

ACTION

FINDING

NOTE:

01 THIS INFORMATION IS TO BE RECORDED IN THE INSPECTION REPORT

01

FIND THE MISSING

PARTS

N_SB_531218_5_FAAA_01_00

Figure A-FFAAA - Sheet 01

Flow Chart (Z130)

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 111

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SERVICE BULLETIN

**CONF 003 thru 004, 006

FR9

FR14

FR19

FR20

Z123 Z124 − 

A

A

D

D

C

C

B

N_SB_531218_5_BBAA_01_00

Figure A-FBBAA - Sheet 01

Inspection Area (Z123-124)

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 112

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**CONF 003 thru 004, 006

NOTE:

01 FASTENERS TO BE INSPECTED

N_SB_531218_5_BBAA_02_00

VIEW LOOKING FWD

01 01

B

Figure A-FBBAA - Sheet 02

Inspection Area (Z123-124)

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 113

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**CONF 003 thru 004, 006

NOTE:

01 FASTENERS TO BE INSPECTED

01

C FWD

LH SIDE SHOWN

RH SIDE SYMMETRICAL

N_SB_531218_5_BBAA_03_00

Figure A-FBBAA - Sheet 03

Inspection Area (Z123-124)

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 114

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**CONF 003 thru 004, 006

LH SIDE SHOWN

RH SIDE SYMMETRICAL

D

E

F

N_SB_531218_5_BBAA_04_00

Figure A-FBBAA - Sheet 04

Inspection Area (Z123-124)

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 115

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**CONF 003 thru 004, 006

NOTE:

01 FASTENERS TO BE INSPECTED

FWD

E

F

01

01

N_SB_531218_5_BBAA_05_00

Figure A-FBBAA - Sheet 05

Inspection Area (Z123-124)

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 116

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**CONF 003 thru 004, 006

QUESTION

ACTION

FINDING

IN Z123−Z124 AT THE THRESHOLD GIVEN IN THE

PLANNING INFORMATION PARAGRAPH E.(2).

NO MISSING

DO A DETAILED VISUAL INSPECTION OF THE NUTS

REPLACE THE NUT WITH

THE SAME PN

REFER TO REPAIR

SUBTASK 531218−210−006−001

NUT YES

CRACKED NO NUT YES

REFER TO REPAIR

ROTATE NO BOLT YES

SEND INSPECTION

REPORT TO AIRBUS

NO FURTHER ACTION

REPLACE THE FASTENERS

AT THE FIRST OVERSIZE

REFER TO REPAIR

SUBTASK 531218−831−006−001

SEND INSPECTION

REPORT TO AIRBUS

SUBTASK 531218−960−003−001

NOTE:

01 THIS INFORMATION IS TO BE RECORDED IN THE INSPECTION REPORT

01

N_SB_531218_5_FBAA_01_01

FIND THE MISSING

PARTS

Figure A-FFBAA - Sheet 01

Flow Chart (Z123-124)

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 117

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**CONF 001, 005 thru 006

Z232

A

STGR10

STGR11

FR35 FR35.1 FR35.4

FWD

B

FR35

FR35.4

A

C

B

N_SB_531218_5_CCAA_01_00

Figure A-FCCAA - Sheet 01

Replacement of the Fasteners (Z232)

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 118

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SERVICE BULLETIN

**CONF 001, 005 thru 006

FWD

BOTTOM VIEW

C

NOTE:

FASTENERS NOT AFFECTED

N_SB_531218_5_CCAA_02_00

Figure A-FCCAA - Sheet 02

Replacement of the Fasteners (Z232)

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 119

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SERVICE BULLETIN

**CONF 001, 005 thru 006

NOTE:

HEAD ON HIDDEN FACE

N_SB_531218_5_CCAA_03_00

HOLE

SYMBOL ITEM PN AFTER DESCRIPTION REMARKS

HOLE DIAMETER

MIN MAX

6.706 mm

(0.264 in)

6.747 mm

(0.267 in) FIRST OVERSIZE

ASNA2531−4 NUT

EN6115V4X−5 BOLT

(1) 1

HOLE

SYMBOL ITEM PN AFTER DESCRIPTION REMARKS

NOMINAL DIA.

ASNA2531−4 NUT

EN6115V4−5 BOLT

HOLE

SYMBOL ITEM PN AFTER DESCRIPTION REMARKS

(1) 1 ASNA2531−4 NUT NOT APPLICABLE

(1) 1

REPLACEMENT OF THE NUTS

REPLACEMENT OF THE FASTENERS AT NOMINAL DIAMETER

REPLACEMENT OF THE FASTENERS AT FIRST OVERSIZE DIAMETER

F

F

F

F

(2) 2

(2) 3

Figure A-FCCAA - Sheet 03

Replacement of the Fasteners (Z232)

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 120

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SERVICE BULLETIN

**CONF 002, 004 thru 006

Z130

FR35.5

FR24

FR24A

FR28

B

A

FR24A

A

Y 1300

Y 765

Y 254

Y−254

Y−765

VIEW LOOKING FWD

C C C C

D D D D

B

N_SB_531218_5_CAAA_01_00

Figure A-FCAAA - Sheet 01

Replacement of the Nuts (Z130)

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 121

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**CONF 002, 004 thru 006

VIEW LOOKING FWD

TYPICAL VIEW

VIEW LOOKING FWD

TYPICAL VIEW

C

D

NOTE:

01 TIGHTENING TORQUE ITEM 1 BETWEEN 0.70 m.daN (62 lbf. in) AND 0.80 m.daN (71 lbf. in) 

01

10

(10)

10

(10)

1

(1)

10

(10)

10

(10) 1

(1) (11)

(11)

02

02

02 AFTER TIGHTENED APPLY MAT. No. 07−020 ON ITEM 1.

N_SB_531218_5_CAAA_02_01

Figure A-FCAAA - Sheet 02

Replacement of the Nuts (Z130)

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 122

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SERVICE BULLETIN

**CONF 002, 004 thru 006

Z130

FR35.5

FR24

FR24A

FR28

B

A

FR24A

A

Y 1300

Y 765

Y 254

Y−254

Y−765

VIEW LOOKING FWD

C C C C

D D D D

B

N_SB_531218_5_CDAA_01_00

Figure A-FCDAA - Sheet 01

Replacement of the Fasteners (Z130)

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 123

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**CONF 002, 004 thru 006

VIEW LOOKING FWD

TYPICAL VIEW

VIEW LOOKING FWD

TYPICAL VIEW

C

D

NOTE:

01 TIGHTENING TORQUE ITEM 1 BETWEEN 0.70 m.daN (62 lbf. in) AND 0.80 m.daN (71 lbf. in) 

01

10

(10)

10

(10)

1

(1)

10

(10)

10

(10) 1

(1) (11)

(11)

A A

12

(12)

11

A

A

11

02

03

02

02 AFTER TIGHTENED APPLY MAT. No. 07−020 ON ITEM 1.

APPLY MAT. No. 04−004. N_SB_531218_5_CDAA_02_01 03

Figure A-FCDAA - Sheet 02

Replacement of the Fasteners (Z130)

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 124

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SERVICE BULLETIN

**CONF 003 thru 004, 006

FR9

FR14

FR19

FR20

Z123 Z124 − 

A

A

D

D

C

C

B

N_SB_531218_5_CBAA_01_00

Figure A-FCBAA - Sheet 01

Replacement of the Fasteners (Z123-124)

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 125

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SERVICE BULLETIN

**CONF 003 thru 004, 006

VIEW LOOKING FWD

B

H13 H12

H11

H10

N_SB_531218_5_CBAA_02_00

Figure A-FCBAA - Sheet 02

Replacement of the Fasteners (Z123-124)

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 126

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SERVICE BULLETIN

**CONF 003 thru 004, 006

C FWD

LH SIDE SHOWN

RH SIDE SYMMETRICAL

H15 RH SIDE

H14 LH SIDE

N_SB_531218_5_CBAA_03_00

Figure A-FCBAA - Sheet 03

Replacement of the Fasteners (Z123-124)

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 127

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SERVICE BULLETIN

**CONF 003 thru 004, 006

LH SIDE SHOWN

RH SIDE SYMMETRICAL

D

E

F

N_SB_531218_5_CBAA_04_00

Figure A-FCBAA - Sheet 04

Replacement of the Fasteners (Z123-124)

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 128

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SERVICE BULLETIN

**CONF 003 thru 004, 006

FWD

E

F

H16 LH SIDE

H17 RH SIDE H19 RH SIDE

H18 LH SIDE

N_SB_531218_5_CBAA_05_00

Figure A-FCBAA - Sheet 05

Replacement of the Fasteners (Z123-124)

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 129

5

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SERVICE BULLETIN

**CONF 003 thru 004, 006

N_SB_531218_5_CBAA_06_00

HOLE

SYMBOL ITEM PN AFTER DESCRIPTION REMARKS

HOLE DIAMETER

MIN MAX

6.706 mm

(0.264 in)

6.747 mm

(0.267 in)

6.622 mm

(0.261 in)

6.658 mm

(0.262 in)

FIRST OVERSIZE

FIRST OVERSIZE

ASNA2531−4 NUT

EN6114V4X−11 BOLT

ASNA2531−4 NUT

EN6114V4X−12 BOLT

6.706 mm

(0.264 in)

6.747 mm

(0.267 in) FIRST OVERSIZE

ASNA2531−4 NUT

EN6114V4X−12 BOLT

H10

THRU

H13

H14

AND

H15

H16

THRU

H19

1

5

1

7

1

7

(1)

(4)

(1)

(6)

(1)

(6)

HOLE

SYMBOL ITEM PN AFTER DESCRIPTION REMARKS

NOMINAL DIA.

NOT APPLICABLE

ASNA2531−4 NUT

EN6114V4−11 BOLT

N/A N/A

N/A N/A

NOMINAL DIA.

ASNA2531−4 NUT

EN6114V4−12 BOLT

H10

THRU

H13

H14

AND

H15

H16

THRU

H19

N/A

N/A

HOLE

SYMBOL ITEM PN AFTER DESCRIPTION REMARKS

ASNA2531−4 NUT NOT APPLICABLE

H10

THRU

H19

(1) 1

4

(6) 6

(1) 1

(4)

(1) 1

REPLACEMENT OF THE NUTS

REPLACEMENT OF THE FASTENERS AT NOMINAL DIAMETER

REPLACEMENT OF THE FASTENERS AT FIRST OVERSIZE DIAMETER

Figure A-FCBAA - Sheet 06

Replacement of the Fasteners (Z123-124)

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 130

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Appendix 01

**CONF 001 thru 006

(1) The results 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 007

None

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 1

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SERVICE BULLETIN

Appendix 01

**CONF 001, 005 thru 006

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A320−53−1218

DATE OF INSPECTION :

INSPECTION METHOD : DETAILED VISUAL

INSPECTION

INSPECTION REPORT

NUT MISSING

YES

LENGHT

NO

NUT CRACKED

YES

NO

YES

NO

YES

NO

AT THE NOMINAL

YES

NO

YES

NO

HOLE SCRATCHED

(BOLT ROTATED)

NUT REPLACED WITH

THE SAME PN

FASTENERS REPLACED

DIAMETER

AT THE FIRST OVERSIZE

FASTENERS REPLACED

DIAMETER

HOLES H20 H21 H22

N_SB_531218_5_ACAA_01_01

Figure A-FACAA - Sheet 01

Inspection Report (Z232)

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 2

5

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SERVICE BULLETIN

Appendix 01

**CONF 001, 005 thru 006

Z232

A

STGR10

STGR11

FR35 FR35.1 FR35.4

FWD

B

FR35

FR35.4

A

C

B

N_SB_531218_5_ACAA_02_00

Figure A-FACAA - Sheet 02

Inspection Report (Z232)

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 3

5

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SERVICE BULLETIN

Appendix 01

**CONF 001, 005 thru 006

FWD

BOTTOM VIEW

C

NOTE:

FASTENERS NOT AFFECTED

N_SB_531218_5_ACAA_03_00

H20

H21

H22

Figure A-FACAA - Sheet 03

Inspection Report (Z232)

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 4

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SERVICE BULLETIN

Appendix 01

**CONF 002, 004 thru 006

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A320−53−1218

DATE OF INSPECTION :

INSPECTION METHOD : DETAILED VISUAL

INSPECTION

INSPECTION REPORT

NUT MISSING

YES

NO

NUT CRACKED

YES

NO

YES

NO

AT THE NOMINAL

YES

NO

NUT REPLACED WITH

THE SAME PN

FASTENERS REPLACED

DIAMETER

HOLES H1 H2 H3 H4 H5 H6 H7 H8

N_SB_531218_5_AAAA_01_02

Figure A-FAAAA - Sheet 01

Inspection Report (Z130)

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 5

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SERVICE BULLETIN

Appendix 01

**CONF 002, 004 thru 006

Z130

FR35.5

FR24

FR24A

FR28

B

A

FR24A

B

A

Y 1300

Y 765

Y 254

Y−254

Y−765

VIEW LOOKING FWD

N_SB_531218_5_AAAA_02_00

H1 H2 H3

H5 H6 H7 H8

H4

Figure A-FAAAA - Sheet 02

Inspection Report (Z130)

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 6

5

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SERVICE BULLETIN

Appendix 01

**CONF 003 thru 004, 006

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A320−53−1218

DATE OF INSPECTION :

INSPECTION METHOD : DETAILED VISUAL

INSPECTION

INSPECTION REPORT

NUT MISSING

YES

LENGHT

NO

NUT CRACKED

YES

NO

YES

NO

YES

NO

AT THE NOMINAL

YES

NO

YES

NO

HOLE SCRATCHED

(SCREW ROTATED)

NUT REPLACED WITH

THE SAME PN

FASTENERS REPLACED

DIAMETER

AT THE FIRST OVERSIZE

FASTENERS REPLACED

DIAMETER

HOLES H10 H11 H12 H13 H14 H15 H16 H17 H18 H19

N_SB_531218_5_ABAA_01_03

Figure A-FABAA - Sheet 01

Inspection Report (Z123-124)

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 7

5

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SERVICE BULLETIN

Appendix 01

**CONF 003 thru 004, 006

FR9

FR14

FR19

FR20

Z123 Z124 − 

A

A

D

D

C

C

B

N_SB_531218_5_ABAA_02_00

Figure A-FABAA - Sheet 02

Inspection Report (Z123-124)

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 8

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SERVICE BULLETIN

Appendix 01

**CONF 003 thru 004, 006

VIEW LOOKING FWD

B

N_SB_531218_5_ABAA_03_00

H13 H12

H11

H10

Figure A-FABAA - Sheet 03

Inspection Report (Z123-124)

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 9

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SERVICE BULLETIN

Appendix 01

**CONF 003 thru 004, 006

C FWD

LH SIDE SHOWN

RH SIDE SYMMETRICAL

N_SB_531218_5_ABAA_04_00

H15 RH SIDE

H14 LH SIDE

Figure A-FABAA - Sheet 04

Inspection Report (Z123-124)

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 10

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SERVICE BULLETIN

Appendix 01

**CONF 003 thru 004, 006

LH SIDE SHOWN

RH SIDE SYMMETRICAL

D

E

F

N_SB_531218_5_ABAA_05_00

Figure A-FABAA - Sheet 05

Inspection Report (Z123-124)

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 11

5

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SERVICE BULLETIN

Appendix 01

**CONF 003 thru 004, 006

FWD

E

F

N_SB_531218_5_ABAA_06_00

H16 LH SIDE

H17 RH SIDE H19 RH SIDE

H18 LH SIDE

Figure A-FABAA - Sheet 06

Inspection Report (Z123-124)

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 12

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SERVICE BULLETIN

Appendix 02

**CONF 001 thru 006

(1) For detail concerning the elapsed time assumption of the modification, refer to the Gantt chart

shown below :

**CONF 007

None

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 1

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SERVICE BULLETIN

Appendix 02

**CONF 001

ELAPSED TIME ASSUMPTIONS SB No. A320−53−1218

ELAPSED TIME

(HOURS)

NOTE: THIS CHART

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)

2.00

1.50

STEPS

0 0.5 1 2.0

0.25 0.25 1

FASTENERS 0.75 0.75 1

FIRST OVER.

REPLACEMENT

OF THE NUTS

1.5

INSTALL

0.50 0.50 1

VISUAL

INSPECTION

0.50 0.50 1

HOLES

INSTALL 

FASTENERS

NOM. DIA.

N_SB_531218_5_ADAA_01_00

Figure A-FADAA - Sheet 01

Elapsed Time Assumptions Repair

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 2

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Appendix 02

**CONF 002

ELAPSED TIME ASSUMPTIONS SB No. A320−53−1218

ELAPSED TIME

(HOURS)

NOTE: THIS CHART

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)

1.75

1.00

STEPS

0 0.5 1 2

0.75 0.75 1 REPLACEMENT

OF THE NUTS

1.5

1.00 1.00 1

REPLACEMENT

FASTENERS

NOM. DIA.

N_SB_531218_5_AEAA_01_00

Figure A-FAEAA - Sheet 01

Elapsed Time Assumptions Repair

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 3

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Appendix 02

**CONF 003

ELAPSED TIME ASSUMPTIONS SB No. A320−53−1218

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)

6.00

4.50

STEPS

1.50 1.50 1

0

REPLACEMENT 1.00 1.00 1

1 2

VISUAL INSPECTION 1.50 1.50 1 HOLES

INSTALL FASTENERS

2.00 2.00 1

0.5 1.5 2 2.5 3 3.5 4 4.5 5.5 5 6 7 6.5

NORM. DIA.

OF THE NUTS

INSTALL FASTENERS

FIRST OVER.

N_SB_531218_5_AFAA_01_00

Figure A-FAFAA - Sheet 01

Elapsed Time Assumptions Repair

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 4

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Appendix 02

**CONF 004

ELAPSED TIME ASSUMPTIONS SB No. A320−53−1218

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)

11.00

6.50

STEPS

0.50 0.50 1

0

GET ACCESS 5.50 3.00 2

1 2

INSPECTION NUTS 0.50 0.50 1 (Z130)

INSPECTION NUTS

CLOSE−UP 5.00 3.00 2

0.5 1.5 2 2.5 3 3.5 4 4.5 5.5 5 6 7 6.5

(Z123−124)

N_SB_531218_5_AGAA_01_00

Figure A-FAGAA - Sheet 01

Elapsed Time Assumptions Inspection

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 5

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Appendix 02

**CONF 004

ELAPSED TIME ASSUMPTIONS SB No. A320−53−1218

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)

7.75

4.50

STEPS

1.00 1.00 1

0

REPLACEMENT

0.75 0.75 1

1 2

1.00 1.00 1

1.50 1.50 1

2.00 2.00 1

0.5 1.5 2 2.5 3 3.5 4 4.5 5.5 5

INSPECTION HOLES

(Z123−124)

OF THE NUTS

(Z130)

REPLACE

FASTENERS

NOM. DIA.

(Z130)

REPLACEMENT

OF THE NUTS

(Z123−124)

VISUAL 

1.50 1.50 1

INSTALL FASTENERS

NOM. DIA.

(Z123−124)

INSTALL FASTENERS

FIRST OVER.

(Z123−124)

N_SB_531218_5_AHAA_01_00

Figure A-FAHAA - Sheet 01

Elapsed Time Assumptions Repair

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 6

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Appendix 02

**CONF 005

ELAPSED TIME ASSUMPTIONS SB No. A320−53−1218

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)

11.75

6.50

STEPS

0.50 0.50 1

0

GET ACCESS 5.50 3.00 2

1 2

INSPECTION NUTS 0.25 0.25 1 (Z232)

INSPECTION NUTS

CLOSE−UP 5.50 3.00 2

0.5 1.5 2 2.5 3 3.5 4 4.5 5.5 5 6 7 6.5

(Z130)

N_SB_531218_5_AJAA_01_00

Figure A-FAJAA - Sheet 01

Elapsed Time Assumptions Inspection

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 7

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

Appendix 02

**CONF 005

ELAPSED TIME ASSUMPTIONS SB No. A320−53−1218

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)

3.75

1.50

STEPS

0 0.5 1 2.0

0.25 0.25 1

0.75 0.75 1 FASTENERS

FIRST OVER.

REPLACEMENT

OF THE NUTS

1.5

INSTALL

0.50 0.50 1

VISUAL

INSPECTION

0.50 0.50 1

HOLES

INSTALL 

FASTENERS

NOM. DIA.

N_SB_531218_5_AKAA_01_00

(Z232)

(Z232)

(Z232)

(Z232)

0.75 0.75 1

REPLACEMENT

OF THE NUTS

(Z130)

1.00 1.00 1

REPLACE

FASTENERS

NOM. DIA.

(Z130)

Figure A-FAKAA - Sheet 01

Elapsed Time Assumptions Repair

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 8

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

Appendix 02

**CONF 006

ELAPSED TIME ASSUMPTIONS SB No. A320−53−1218

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)

14.25

7.50

STEPS

0.50 0.50 1

0

GET ACCESS 6.50 3.50 2

1 2

INSPECTION NUTS 0.25 0.25 1 (Z232)

INSPECTION NUTS

0.50 0.50 1

CLOSE−UP 6.50 3.50 2

0.5 1.5 2 2.5 3 3.5 4 4.5 5.5 5 6 7 6.5 7.5

(Z130)

INSPECTION NUTS

(Z123−124)

N_SB_531218_5_ALAA_01_00

Figure A-FALAA - Sheet 01

Elapsed Time Assumptions Inspection

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 9

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

Appendix 02

**CONF 006

ELAPSED TIME ASSUMPTIONS SB No. A320−53−1218

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)

9.75

4.50

STEPS

1.00 1.00 1

0

REPLACEMENT

0.25 0.25 1

1 2

0.50 0.50 1

0.75 0.75 1

0.5 1.5 2 2.5 3 3.5 4 4.5 5.5 5

INSPECTION HOLES

(Z232)

OF THE NUTS

(Z232)

REPLACEMENT

OF THE NUTS

(Z123−124)

VISUAL 

0.50 0.50 1

INSTALL FASTENERS

NOM. DIA.

(Z232)

INSTALL FASTENERS

FIRST OVER.

(Z232)

REPLACEMENT

OF THE NUTS 0.75 0.75 1

(Z130)

INSPECTION HOLES 1.50 1.50 1

(Z123−124)

VISUAL 

1.50 1.50 1

INSTALL FASTENERS

NOM. DIA.

(Z123−124)

2.00 2.00 1

INSTALL FASTENERS

FIRST OVER.

(Z123−124)

1.00 1.00 1

REPLACE FASTENERS

NOM. DIA.

(Z130)

N_SB_531218_5_ANAA_01_00

Figure A-FANAA - Sheet 01

Elapsed Time Assumptions Repair

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 10

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

REPORTING SHEET

TITLE: FUSELAGE - GENERAL - SUSPECTED NON-CONFORMING NUTS

INSPECTION.

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 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 1

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SERVICE BULLETIN

QUALITY PERCEPTION FORM

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

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

improve the quality of our Service Bulletins.

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

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

- Quality rating of this SB 4 3 2 1

- Quality rating of the Accomplishment Instructions 4 3 2 1

- Quality rating of the Illustrations 4 3 2 1

- Is this SB easy to understand ? Y / N

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

short description of the issue.

Planning Material Instructions

X Effectivity X Kit content X Preparation

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

X Manpower X Industry support X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustrations

Comments:

Operator: Date:

Name/Title:

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE: Feb 08/10 SERVICE BULLETIN No.: A320-53-1218

REVISION No.: 01 - Jun 17/10 Page: 1

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