@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: 57

TITLE: WINGS - SECTION 21 - INTRODUCE SHOT PEENING ON LOWER

SURFACE PANEL

MODIFICATION No.: 22418P2408

This page transmits Revision No.06 of Service Bulletin No.A320-57-1043

ADDITIONAL WORK

**CONF ALL

Additional work is required by this revision for aircraft modified by any previous issue.

Shot peening procedure has to be performed with the new procedure to remove Chromic Acid Anodized

(CAA) layer as described in Rev. 06 of this Service Bulletin.

REASON

Revision No. 06 issued to change the supplier address, modify the procedure of shot peening, add a

procedure to remove Chromic Acid Anodized (CAA) layer and to add ADDITIONAL WORK for aircraft

modified by any previous issue.

CHANGES

SUMMARY

MODIFICATIONS Minor editorial or document structure change N

REASON/DESCRIPTION/OPERATIONAL

CONSEQUENCES

Minor editorial or document structure change N

GENERAL EVALUATION Minor editorial or document structure change N

MATERIAL PRICE INFORMATION Minor editorial or document structure change N

EFFECTIVITY Minor editorial or document structure change N

CONCURRENT REQUIREMENTS Minor editorial or document structure change N

REFERENCES / REPERCUSSIONS Minor editorial or document structure change N

NATURE OF THE WORK Minor editorial or document structure change N

MANPOWER Minor editorial or document structure change N

APPENDICES Minor editorial or document structure change N

Fig. A-FSAAA Minor editorial or document structure change N

Fig. A-FSAAA Sheet 01 Minor editorial or document structure change N

DATE: Feb 16/93 SERVICE BULLETIN No.: A320-57-1043

REVISION No.: 06 - Dec 05/13 Page: 1

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REVISION TRANSMITTAL SHEET

PLANNING INFORMATION

EFFECTIVITY Minor editorial or document structure change N

Configuration definition Minor editorial or document structure change N

CONF 001 Minor editorial or document structure change N

Material Effectivity Minor editorial or document structure change N

Minor editorial or document structure change N

CONCURRENT REQUIREMENTS Minor editorial or document structure change N

REASON Minor editorial or document structure change N

History Minor editorial or document structure change N

Objective/Action Minor editorial or document structure change N

Advantages Minor editorial or document structure change N

Operational/Maintenance

Consequences

Minor editorial or document structure change N

DESCRIPTION Minor editorial or document structure change N

COMPLIANCE Minor editorial or document structure change N

Classification Minor editorial or document structure change N

Accomplishment Timescale Minor editorial or document structure change N

APPROVAL Minor editorial or document structure change N

Minor editorial or document structure change N

MANPOWER Minor editorial or document structure change N

Minor editorial or document structure change N

WEIGHT AND BALANCE Minor editorial or document structure change N

ELECTRICAL LOAD DATA Minor editorial or document structure change N

REFERENCES Minor editorial or document structure change N

Minor editorial or document structure change N

PUBLICATION AFFECTED Minor editorial or document structure change N

Minor editorial or document structure change N

INTERCHANGEABILITY/MIXABILITY Minor editorial or document structure change N

SPARES Minor editorial or document structure change N

MATERIAL INFORMATION

MATERIAL - PRICE AND AVAILABILITY Minor editorial or document structure change N

Procurement Addresses Minor editorial or document structure change N

Price and Availability Minor editorial or document structure change N

INDUSTRY SUPPORT INFORMATION Minor editorial or document structure change N

LIST OF COMPONENTS Minor editorial or document structure change N

LIST OF MATERIALS - OPERATOR

SUPPLIED

Minor editorial or document structure change N

Consumable Materials Minor editorial or document structure change N

Consumable CMLA01 Minor editorial or document structure change N

Components Minor editorial or document structure change N

Equipment Minor editorial or document structure change N

DATE: Feb 16/93 SERVICE BULLETIN No.: A320-57-1043

REVISION No.: 06 - Dec 05/13 Page: 2

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REVISION TRANSMITTAL SHEET

PARTS TO BE RE-IDENTIFIED BY

OPERATOR

Minor editorial or document structure change N

TOOLING Minor editorial or document structure change N

Tooling - Price and Availability Minor editorial or document structure change N

Tools Minor editorial or document structure change N

Special Tools Minor editorial or document structure change N

ACCOMPLISHMENT INSTRUCTIONS

TASK 571043- 831-801-001-Modification Minor editorial or document structure change N

Task associated data - 001 Minor editorial or document structure change N

Subtask 571043-839-001-001 Minor editorial or document structure change N

Subtask 571043-910-001-001 Minor editorial or document structure change N

Subtask 571043-941-001-001 Minor editorial or document structure change N

Subtask 571043-020-001-001 Minor editorial or document structure change N

Subtask 571043-832-001-001 Minor editorial or document structure change N

Subtask 571043-831-001-001 Minor editorial or document structure change N

Subtask 571043-700-001-001 Minor editorial or document structure change N

Subtask 571043-420-001-001 Minor editorial or document structure change N

Subtask 571043-942-001-001 Minor editorial or document structure change N

TASK 571043- 831-802-001-Modification -

ADDITIONAL WORK for Aircraft modified

by Revision No. 05 or any Previous Issue

ADDITIONAL WORK for aircraft modified by

Revision No. 05 or any previous issue added.

N

Task associated data - 001 Minor editorial or document structure change N

Subtask 571043-910-002-001 Minor editorial or document structure change N

Subtask 571043-839-002-001 Minor editorial or document structure change N

Subtask 571043-941-002-001 Minor editorial or document structure change N

Subtask 571043-020-002-001 Minor editorial or document structure change N

Subtask 571043-832-003-001 Minor editorial or document structure change N

Subtask 571043-831-002-001 Minor editorial or document structure change N

Subtask 571043-700-002-001 Minor editorial or document structure change N

Subtask 571043-420-002-001 Minor editorial or document structure change N

Subtask 571043-942-002-001 Minor editorial or document structure change N

Fig. A-FBAAA Minor editorial or document structure change N

Fig. A-FBAAA Sheet 01 Minor editorial or document structure change N

Fig. A-FBBAA Minor editorial or document structure change N

Fig. A-FBBAA Sheet 01 Minor editorial or document structure change N

Fig. A-FBBAA Sheet 02 Minor editorial or document structure change N

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.

DATE: Feb 16/93 SERVICE BULLETIN No.: A320-57-1043

REVISION No.: 06 - Dec 05/13 Page: 3

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REVISION TRANSMITTAL SHEET

HISTORY OF PREVIOUS REVISIONS

Revision No. 01 issued to include changes in effectivity, address of supplier FISHER and incorporate

Change Notice No. 0.A.

Revision No. 02 issued to modify Figure 2, incorporate Change Notice No.1.A. and update the

effectivity.

Revision No. 03 issued to delete notes about MRB and include a HFEC inspection procedure before

shot peening.

Revision No. 04 issued to add preparation operations before modification and test operations after

modification. Moreover, the shot peening areas have been reduced to avoid removal of fasteners and

hydraulic pump support.

Revision No. 05 issued to modify the threshold related to the embodiment of this Service Bulletin. The

threshold figure indicated in the previous issues of this Service Bulletin has been defined on the

basis of full scale fatigue tests. Since then, a survey, carried out on the A320 family fleet, has

highlighted some differences between the mission parameters of in-service aircraft andthose initially

considered.The differences are mainly on the weight of fuel at landing and on the average flight time

which are higher than those defined for the analysis of the fatigue related tasks.This has led to an

adjustment of the A320 family reference fatigue mission. Consequently, the threshold related to the

embodiment of this Service Bulletin has been revised and a new limit, expressed in flight hours, has

been introduced.

REVISION SEQUENCE

ORIGINAL: Feb 16/93

REVISION No.: 01 - Jun 14/96

REVISION No.: 02 - May 14/97

REVISION No.: 03 - Oct 24/97

REVISION No.: 04 - May 15/99

REVISION No.: 05 - Apr 30/02

REVISION No. : 06 - Dec 05/13

DATE: Feb 16/93 SERVICE BULLETIN No.: A320-57-1043

REVISION No.: 06 - Dec 05/13 Page: 4

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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: 57

TITLE: WINGS - SECTION 21 - INTRODUCE SHOT PEENING ON LOWER

SURFACE PANEL

**CONF ALL

MODIFICATIONS

MODIFICATION CLASSIFICATION

MAJOR None

MINOR 22418P2408

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

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

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

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

During full scale fatigue tests, cracks were detected on the center wing box lower panel, in the radius of

the milling step between stiffener 13 and 14 near the fuel pump aperture.

Embodiment of Modification Service Bulletin No. A320-57-1043 up to revision 05 could lead to shot

peening on Chromic Acid Anodized layer (CAA) protection with no fatigue benefit effect.

Therefore, in case of Modification Service Bulletin No. A320-57-1043 was accomplished before revision

06, an inspection is still required as per Inspection Service Bulletin No. A320-57-1082.

In order to cancel Inspection Service Bulletin No. A320-57-1082 requirements, the Modification Service

Bulletin No. A320-57-1043 at revision 06 has to be accomplished. This will ensure required removal of

the CAA protection prior application of the shot peening procedure.

To avoid possible crack initiation and subsequent extensive repair on the lower panel, this Modification

Service Bulletin recommends introduction of shot peening in the radius of the milling step between

stiffener 13 and 14 near the fuel pump aperture.

Accomplishment of this Service Bulletin at revision No. 06 cancels the inspection requirements of

Service Bulletin No. A320-57-1082.

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE RECOMMENDED (1) CANCELS INSPECTION SB YES

DATE: Feb 16/93 SERVICE BULLETIN No.: A320-57-1043

REVISION No.: 06 - Dec 05/13 Page: 1

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SUMMARY

EVALUATION TABLE

POTENTIAL AD NO A/C OPERATION AFFECTED NO

RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO

COST SAVING NO ETOPS AFFECTED NO

STRUCTURAL LIFE EXTN YES VENDOR SB INVOLVED NO

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

disruptions.

MATERIAL PRICE INFORMATION

No Material

EFFECTIVITY

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

14S 26S 29S 31V 35U 56W 66X 69X 73W 85T 86Z 98W ACA

AFR AGC AHY AIB ANA ART B2V BGH C9G CTN CYP D2F DAL

DLH ETD ETJ F2I FPY G2X HRM IAC IBE IBS IRA JAV KAC

KHO MMA MSR MXA NVD RNV SGL SKU SNX SOL SVR TAM TAR

TBZ ULG USA VLG WRC XLF

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU None

OEB None

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER None

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

MANPOWER

Task 571043-831-801-001: Modification

TOTAL MANHOURS 11.00

ELAPSED TIME (HOURS) 7.00

DATE: Feb 16/93 SERVICE BULLETIN No.: A320-57-1043

REVISION No.: 06 - Dec 05/13 Page: 2

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SUMMARY

Task 571043-831-802-001: Modification - ADDITIONAL WORK for Aircraft modified by Revision

No. 05 or any Previous Issue

TOTAL MANHOURS 11.00

ELAPSED TIME (HOURS) 7.00

APPENDICES

None

DATE: Feb 16/93 SERVICE BULLETIN No.: A320-57-1043

REVISION No.: 06 - Dec 05/13 Page: 3

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SUMMARY

**CONF ALL

AREA TO BE SHOT PEENED

A

FR42

A

FR41

N_SB_571043_5_SAAA_01_02

Figure A-FSAAA - Sheet 01

DATE: Feb 16/93 SERVICE BULLETIN No.: A320-57-1043

REVISION No.: 06 - Dec 05/13 Page: 4

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SERVICE BULLETIN

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

ATA SYSTEM: 57

TITLE: WINGS - SECTION 21 - INTRODUCE SHOT PEENING ON LOWER

SURFACE PANEL

MODIFICATION No.: 22418P2408

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

NOTE: This modification is embodied before delivery on A319 aircraft with

Manufacturer Serial Number (MSN) 0546 and subsequent and A320 aircraft

MSN 0359, 0371, 0374, 0378 and subsequent

(1) Models

320-211 320-212 320-231

(2) Effectivity by MSN

0029 0045-0059 0061 0063-0078 0080-0090 0093-0097 0099 0104 0109-0127 0135

0137-0138 0140-0142 0145 0147-0150 0152-0155 0157-0162 0164-0168 0170-0176

0178-0179 0181-0183 0185 0189-0190 0192 0194-0195 0197-0221 0223-0224

0229-0237 0239-0246 0248-0256 0258-0270 0272-0279 0281-0285 0287 0289-0303

0306-0309 0311-0312 0314 0316-0325 0328-0335 0339-0343 0345-0347 0349-0351

0353-0358 0360-0362 0366-0368 0370 0372-0373 0375-0376

(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.

DATE: Feb 16/93 SERVICE BULLETIN No.: A320-57-1043

REVISION No.: 06 - Dec 05/13 Page: 1

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OPERATOR MSN

14S 0283

26S 0368

29S 0291 0292

31V 0164 0332

35U 0088

56W 0250 0335

66X 0230

69X 0219

73W 0087

85T 0234

86Z 0168

98W 0109 0120

ACA 0059 0068 0073 0084 0122 0126 0127 0141 0149 0150 0154 0159

0174 0175 0183 0210 0231 0232 0233 0242 0248 0253 0254 0255

0265 0277 0284 0290 0309 0324 0330 0341

AFR 0061 0063 0115 0145 0155 0214 0236 0237 0239 0270 0278 0285

0287

AGC 0190

AHY 0331

AIB 0138

ANA 0167 0170 0212 0245 0300 0328

ART 0142 0244 0279 0311 0333

B2V 0185

BGH 0349

C9G 0246

CTN 0258

CYP 0256

D2F 0243 0251

DAL 0118 0121 0125 0152 0153 0160 0171 0192 0197 0206 0208 0213

0262 0263 0272 0273 0281 0282 0297 0298 0306 0307 0318 0319

0329 0339 0340 0355 0358 0360 0367 0372

DLH 0069 0070 0071 0072 0078 0083 0086 0093 0094 0104 0110 0111

0116 0117 0135 0137 0147 0161 0162 0172 0200 0201 0202 0209

0216 0217 0218 0267 0268 0269 0346

ETD 0350

ETJ 0325

F2I 0085 0148 0204 0215 0221 0249 0294 0301 0373

FPY 0112 0189 0342

G2X 0347

HRM 0293

IAC 0045 0046 0047 0048 0049 0050 0051 0056 0057 0058 0074 0075

0080 0089 0090 0095 0096 0097

IBE 0158 0173 0223 0274 0356

IBS 0176 0207 0224 0266 0323

IRA 0303 0312 0345

JAV 0029

DATE: Feb 16/93 SERVICE BULLETIN No.: A320-57-1043

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OPERATOR MSN

KAC 0181 0182 0195

KHO 0354 0361 0376

MMA 0113 0114 0295 0316

MSR 0165 0166 0178 0194 0198 0322 0351 0366

MXA 0252 0259 0260 0261 0275 0276 0296 0320 0321 0353

NVD 0211 0299 0375

RNV 0229

SGL 0357

SKU 0179

SNX 0289

SOL 0302

SVR 0140 0157 0203 0220

TAM 0334

TAR 0119 0123 0124 0205 0370

TBZ 0362

ULG 0308 0314

USA 0052 0053 0054 0055 0064 0065 0066 0067 0076 0077 0081 0082

0099 0317

VLG 0199 0240 0241 0264

WRC 0235

XLF 0343

(4) Configuration by MSN

MSN CONFIGURATION

0029 0045 0046 0047 0048 0049 0050 0051 0052 0053 0054

0055 0056 0057 0058 0059 0061 0063 0064 0065 0066 0067

0068 0069 0070 0071 0072 0073 0074 0075 0076 0077 0078

0080 0081 0082 0083 0084 0085 0086 0087 0088 0089 0090

0093 0094 0095 0096 0097 0099 0104 0109 0110 0111 0112

0113 0114 0115 0116 0117 0118 0119 0120 0121 0122 0123

0124 0125 0126 0127 0135 0137 0138 0140 0141 0142 0145

0147 0148 0149 0150 0152 0153 0154 0155 0157 0158 0159

0160 0161 0162 0164 0165 0166 0167 0168 0170 0171 0172

0173 0174 0175 0176 0178 0179 0181 0182 0183 0185 0189

0190 0192 0194 0195 0197 0198 0199 0200 0201 0202 0203

0204 0205 0206 0207 0208 0209 0210 0211 0212 0213 0214

0215 0216 0217 0218 0219 0220 0221 0223 0224 0229 0230

0231 0232 0233 0234 0235 0236 0237 0239 0240 0241 0242

0243 0244 0245 0246 0248 0249 0250 0251 0252 0253 0254

0255 0256 0258 0259 0260 0261 0262 0263 0264 0265 0266

0267 0268 0269 0270 0272 0273 0274 0275 0276 0277 0278

0279 0281 0282 0283 0284 0285 0287 0289 0290 0291 0292

0293 0294 0295 0296 0297 0298 0299 0300 0301 0302 0303

0306 0307 0308 0309 0311 0312 0314 0316 0317 0318 0319

0320 0321 0322 0323 0324 0325 0328 0329 0330 0331 0332

0333 0334 0335 0339 0340 0341 0342 0343 0345 0346 0347

0349 0350 0351 0353 0354 0355 0356 0357 0358 0360 0361

0362 0366 0367 0368 0370 0372 0373 0375 0376

001

DATE: Feb 16/93 SERVICE BULLETIN No.: A320-57-1043

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(5) Configuration definition

**CONF 001

Config. 001 is valid for all the aircraft given in the effectivity of this Service Bulletin as a

standard configuration.

(6) Material Effectivity

MATERIAL QTY PER A/C SEE NOTES

Consumable CMLA01 1

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

During full scale fatigue tests, cracks were detected on the center wing box lower panel,

in the radius of the milling step between stiffener 13 and 14 near the fuel pump aperture.

Embodiment of Modification Service Bulletin No. A320-57-1043 up to revision 05 could

lead to shot peening on Chromic Acid Anodized layer (CAA) protection with no fatigue

benefit effect.

Therefore, in case of Modification Service Bulletin No. A320-57-1043 was accomplished

before revision 06, an inspection is still required as per Inspection Service Bulletin No.

A320-57-1082.

In order to cancel Inspection Service Bulletin No. A320-57-1082 requirements, the

Modification Service Bulletin No. A320-57-1043 at revision 06 has to be accomplished.

This will ensure required removal of the CAA protection prior application of the shot

peening procedure.

(2) Objective/Action

To avoid possible crack initiation and subsequent extensive repair on the lower panel,

this Modification Service Bulletin recommends introduction of shot peening in the radius

of the milling step between stiffener 13 and 14 near the fuel pump aperture.

(3) Advantages

Accomplishment of this Service Bulletin at revision No. 06 cancels the inspection

requirements of Service Bulletin No. A320-57-1082.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

DATE: Feb 16/93 SERVICE BULLETIN No.: A320-57-1043

REVISION No.: 06 - Dec 05/13 Page: 4

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Task 571043-831-801-001: Modification

(1) Do a HFEC inspection

(2) Do a shot peening

Task 571043-831-802-001: Modification - ADDITIONAL WORK for Aircraft modified by

Revision No. 05 or any Previous Issue

(1) Do a HFEC inspection

(2) Do a shot peening

E. COMPLIANCE

(1) Classification

RECOMMENDED: Service Bulletin recommended to be accomplished to prevent

significant operational disruptions.

(2) Accomplishment Timescale

Accomplishment of this Service Bulletin is recommended at the earliest opportunity

where manpower and facilities are available.

F. APPROVAL

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

Organisation Approval No. EASA.21J.031.

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

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

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

before incorporation of the Service Bulletin.

G. MANPOWER

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

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

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

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

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

included.

Task 571043-831-801-001: Modification

Get Access 3.00

On Aircraft

Do a HFEC inspection 2.00

Do a shot peening 2.00

Tests 1.00

Close-Up 3.00

TOTAL MANHOURS 11.00

DATE: Feb 16/93 SERVICE BULLETIN No.: A320-57-1043

REVISION No.: 06 - Dec 05/13 Page: 5

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Task 571043-831-801-001: Modification

ELAPSED TIME (HOURS) 7.00

Task 571043-831-802-001: Modification - ADDITIONAL WORK for Aircraft modified by Revision

No. 05 or any Previous Issue

Get Access 3.00

On Aircraft

Do a HFEC inspection 2.00

Do a shot peening 2.00

Tests 1.00

Close-Up 3.00

TOTAL MANHOURS 11.00

ELAPSED TIME (HOURS) 7.00

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

Aircraft Maintenance Manual (AMM) 06-41-53 12-34-24 29-00-00

29-12-00 29-14-00 29-23-00

29-24-00 29-24-51

Consumable Material List (CML)

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

Non Destructive Test Manual (NTM) 57-11-95

Process and Material Specification (PMS) Process and Material Specification

(PMS) 01-01-13

Service Bulletin (SB) A320-57-1082

Structural Repair Manual (SRM) 51-75-11

K. PUBLICATION AFFECTED

Structural Repair Manual (SRM) 57-11-11

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

DATE: Feb 16/93 SERVICE BULLETIN No.: A320-57-1043

REVISION No.: 06 - Dec 05/13 Page: 6

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2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

None

(2) Price and Availability

None

B. INDUSTRY SUPPORT INFORMATION

None

C. LIST OF COMPONENTS

No Kit

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Polish Metal Aluminum 05-025 As required

Sealing Tape 08-005 As required

Fabric Tape Pressure Sensitive 08-038 As required

Methyl Alcohol 11-006 As required

Solvent General Purpose 11-026 As required

Chemical Conversion Coating

Yellow Aluminum

13-002 As required

Polyurethane Primer 16-001 As required

Anti-Corrosion Primer (epoxyImprvdadhesion)16-006 As required

(2) Components

None

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

DATE: Feb 16/93 SERVICE BULLETIN No.: A320-57-1043

REVISION No.: 06 - Dec 05/13 Page: 7

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SERVICE BULLETIN

F. TOOLING

(1) Tooling - Price and Availability

Accomplishment of this Service Bulletin entails :

FOR SHOT PEENING :

- The use of standard tool listed in ACCOMPLISHMENT INSTRUCTIONS paragraph

3.C(2) (SUBTASK 571043-831-001 001 Do a shot peening ).

FOR HFEC INSPECTIONS :

- Equipment and material for the inspection of the lower surface panel of the center

wing box by HFEC inspection, refer to NTM 57-11-95 Part 6.

(2) Tools

None

(3) Special Tools

None

DATE: Feb 16/93 SERVICE BULLETIN No.: A320-57-1043

REVISION No.: 06 - Dec 05/13 Page: 8

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3. ACCOMPLISHMENT INSTRUCTIONS

Task 571043-831-801-001 - Modification

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

INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

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

THIS:

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

NECESSARY ON 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.

IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00.

NOTE: The accomplishment instructions of this Service Bulletin refer to procedures

included in other AIRBUS documents. When the words "refer to" are used and the

operator has an accepted alternative procedure, the accepted alternative procedure

can be used. When the words "in accordance with" are included in the instruction,

the procedure in the AIRBUS document must be used.

NOTE: The access and close-up instructions, not comprising return to service tests, in this

Service Bulletin do not constitute or affect the technical intent of the Service

Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or

close-up steps to add flexibility to their maintenance operations as long as the

technical intent of the Service Bulletin is met within the set parameters.

NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms.

Refer to paragraph 1.J., References, for the definition of acronyms.

Task Associated Data

Manpower

TOTAL MANHOURS 11.00

ELAPSED TIME (HOURS) 7.00

A. GENERAL

(1) Subtask 571043-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

DATE: Feb 16/93 SERVICE BULLETIN No.: A320-57-1043

REVISION No.: 06 - Dec 05/13 Page: 9

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

Service Bulletin.

(2) Subtask 571043-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Consumable Material List (CML)

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

Consumable Materials List (CML).

B. PREPARATION

(1) Subtask 571043-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

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

Task 12-34-24-869-002

Task 29-00-00-864-001

Task 29-00-00-910-002

Task 29-14-00-614-001

Task 29-23-00-860-001

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

12-34-24-869-002.

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

(c) Obey the hydraulic safety procedures, refer to AMM Task 29-00-00-910-002.

(d) Put the warning notices in position to tell persons not to pressurize the Yellow

hydraulic system :

- In the cockpit, on the Hydraulic/Fuel Panel 40VU of the overhead panel.

- On the ground service panels of the Green and Yellow hydraulic systems.

(e) Put the warning notices in position to tell persons not to pressurize the Blue

hydraulic system :

- In the cockpit, on the Hydraulic/Fuel Panel 40VU of the overhead panel.

- On the ground service panels of the Blue hydraulic systems.

(f) Make sure that Blue and Yellow hydraulic systems are depressurized and put it in

the maintenance configuration, refer to AMM Task 29-00-00-864-001.

DATE: Feb 16/93 SERVICE BULLETIN No.: A320-57-1043

REVISION No.: 06 - Dec 05/13 Page: 10

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(g) Depressurize the reservoirs of the Blue and Yellow hydraulic systems, refer to AMM

Task 29-14-00-614-001.

(h) Disconnect the isolation coupling from the Power Transfer Unit (PTU), refer to AMM

Task 29-23-00-860-001.

(i) Open the access doors 195BB and 196BB, refer to AMM 06-41-53, Page Block

001.

(j) Open, safety and tag these circuit breakers :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

49VU HYD/HYD PWR/B

WARN/AND CTL

2702GJ 14 D

49VU HYD/HYD PWR/B WARN/&

CTL

2702GJ 12 C

121VU HYDRAULIC/SOL

VALVES/G/Y/B/LEAK/TST

1881GP 35 N

123VU B HYD/ELEC PUMP 2701GJ 09AB

121VU HYDRAULIC/HYD POWER/Y 3803GX 30 N

123VU Y HYD/ELEC/PUMP 3802GX 06AB

123VU Y HYD/ELEC PUMP/NORM 3801GX 03AB

(2) Subtask 571043-020-001-001 - Remove the pipes for access

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 29-24-51-000-001

Fig. A-FBAAA

Removal for Access to the Working Area

Sheet 01

Get access to the working area.

(a) Remove the suction pipe, refer to item 1 of AMM Task 29-24-51-000-001.

(b) Remove :

Refer to Fig. A-FBAAA Sheet 01

2 Bolts Item (1) Retain

4 Washers Item (2) Retain

2 Clamp Blocks Item (3) Retain

2 Clamp Blocks Item (4) Retain

2 Bolts Item (5) Retain

DATE: Feb 16/93 SERVICE BULLETIN No.: A320-57-1043

REVISION No.: 06 - Dec 05/13 Page: 11

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2 Nuts Item (6) Retain

1 Bracket Item (7) Retain

2 Bolts Item (8) Retain

1 Pipe Item (9) Retain

1 Pipe Item (10) Retain

C. PROCEDURE

(1) Subtask 571043-832-001-001 - Do a HFEC inspection

Manpower Resources

Manhours 2.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 57-11-95 Part 6

Fig. A-FBBAA

Shot Peening on the Outer Side of the

Lower Panel in the Thickness Changes

near the Fuel Pump Aperture

Sheet 01

Sheet 02

Do a High Frequency Eddy Current (HFEC) Inspection on the lower panel, the lower

surface of the center wing box, refer to NTM 57-11-95, Part 6

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

(a) The accomplishment instructions of this Service Bulletin refer to procedures

included in other AIRBUS documents. When the words

(b) If you find no crack :

- Do a shot peening as written in SUBTASK 571043-831-001.

(c) If you find a crack :

- Contact Airbus and apply corrective actions defined by Airbus, before next

flight.

DATE: Feb 16/93 SERVICE BULLETIN No.: A320-57-1043

REVISION No.: 06 - Dec 05/13 Page: 12

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(2) Subtask 571043-831-001-001 - Do a shot peening

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polish Metal Aluminum 05-025 As required

Sealing Tape 08-005 As required

Fabric Tape Pressure

Sensitive

08-038 As required

Methyl Alcohol 11-006 As required

Solvent General Purpose 11-026 As required

Chemical Conversion

Coating Yellow Aluminum

13-002 As required

Polyurethane Primer 16-001 As required

Anti-Corrosion Primer

(Epoxy-Imprvd Adhesion)

16-006 As required

References

Process and Material Specification

(PMS)

Process and Material Specification (PMS)

01-01-13

Structural Repair Manual (SRM) 51-75-11

Fig. A-FBBAA

Shot Peening on the Outer Side of the

Lower Panel in the Thickness Changes

near the Fuel Pump Aperture

Sheet 01

Sheet 02

Do a shot peening on the outer side of the lower panel, where thickness changes, near

the fuel pump aperture.

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

(a) SHOT PEENING PROCEDURE

1 Equipment and materials

a Vacu blast : JUNIOR MATRASUR or equivalent

USF

28-30, rue de Tournefils

BP 45

91542 MENNECY

Tel : +33 (0)1-64-57-07-91

DATE: Feb 16/93 SERVICE BULLETIN No.: A320-57-1043

REVISION No.: 06 - Dec 05/13 Page: 13

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Fax : + 33 (0)1-64-57-12-60

b Gun type : MATRASUR 617161

c Almen test specimen : A2 + GF 9801-4141

d Holding fixture : 9801-4130

e Dial indicator : 9999-0787

Supplier :

FISHER

105, rue Charles Michels

BP 174

93208 St Denis cedex

Tel : +33 (0)1-49-22-13-13

f Bead : Glass beads BV300, dia. 0.3 mm (0.012 in.)

Supplier :

VAPOR BLAST

Avenue Le Verrier

Z.A.I. des bruyeres

78190 TRAPPES

Tel : 16-1-30-69-09-09

Fax : 16-1-30-69-09-27

2 Vacu blast unit set-up

- Switch on the VACU BLAST unit (refer to the manufacturer’s instructions)

- Load the glass beads BV300

- Adjust the intensity to agree with the ALMEN test specimen : F13A2 to

F16A2.

You must adjust the intensity of the shot peening to make a deflection of 0.13

mm (0.0052 in.) to 0.16 mm (0.0064 in.) of the Almen specimen "’A".

3 Job set-up

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

a Mask area surrounding the area to be stripped with

Sealing Tape 08-005 As required

, enlarge area by 5mm.

b Strip paint in accordance with SRM 51-75-11.

c Clean the area with solvent.

DATE: Feb 16/93 SERVICE BULLETIN No.: A320-57-1043

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d Remove the surface protection Chromic Acid Anodized (CAA) layer by

polishing using :

Polish Metal

Aluminum

05-025 As required

until a bright finish is obtained.

e Mechanical rework to remove paint, primer and CAA, ensure depth

comprised between 0.3 mm (0.012 in.) and 0.4 mm (0.016 in.).

f Finishing the part until obtaining aluminium shinning on all areas as per

instructions given in Fig. A-FBBAA Sheet 02.

g Ensure that the surface is smooth and without defects.

h clean area with :

Solvent General

Purpose

11-026 As required

or alcohol.

i Remove masking tape.

j Carefully apply a protection to the areas around the areas to shot peen

with :

Fabric Tape

Pressure Sensitive

08-038 As required

k Apply a protection to the adjacent area and equipment (with manila paper

or equivalent).

l Shot peen the surface with a number of passes that you specified before,

refer to Process and Material Specification (PMS) 01-01-13 for the

general data related to the shot peening procedure.

m Clean the area that you shot peened with :

Methyl Alcohol 11-006 As required

and renew the protective finish with :

Chemical

Conversion Coating

Yellow Aluminum

13-002 As required

Polyurethane

Primer

16-001 As required

and

DATE: Feb 16/93 SERVICE BULLETIN No.: A320-57-1043

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Anti-Corrosion

Primer (EpoxyImprvd Adhesion)

16-006 As required

D. TEST

(1) Subtask 571043-700-001-001 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 29-12-00-700-001

Task 29-14-00-720-001

Task 29-23-00-710-004

Task 29-24-00-710-001

NOTE: This test procedure is to be accomplished after the installation of the

equipment removed for access, SUBTASK 571043-420-001 001 Install

the pipes

(a) Job Set-up

1 Remove the safety clips and tags and close these circuit breakers :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

49VU HYD/HYD PWR/B

WARN/AND CTL

2702GJ 14 D

49VU HYD/HYD PWR/B WARN/&

CTL

2702GJ 12 C

121VU HYDRAULIC/SOL

VALVES/G/Y/B/LEAK/TST

1881GP 35 N

123VU B HYD/ELEC PUMP 2701GJ 09AB

121VU HYDRAULIC/HYD POWER/Y 3803GX 30 N

123VU Y HYD/ELEC/PUMP 3802GX 06AB

123VU Y HYD/ELEC PUMP/NORM 3801GX 03AB

(b) Tests

1 Do an operational test of the Yellow auxilliary power, refer to AMM Task

29-24-00-710-001 and make sure that is no leak on the pipes that you

installed again.

2 Do an operational test of the electric pump of the Blue hydraulic system, refer

to AMM Task 29-12-00-700-001 and make sure that there is no leak on the

pipes that you installed again.

3 Do a functional test of the pressure system of the hydraulic reservoirs, refer to

AMM Task 29-14-00-720-001.

4 Do an operational test of the power transfer unit, refer to AMM Task

29-23-00-710-004.

DATE: Feb 16/93 SERVICE BULLETIN No.: A320-57-1043

REVISION No.: 06 - Dec 05/13 Page: 16

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E. CLOSE-UP

(1) Subtask 571043-420-001-001 - Install the pipes

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 29-24-51-400-001

Fig. A-FBAAA

Removal for Access to the Working Area

Sheet 01

(a) Install the suction pipe, refer to Item 1 of AMM Task 29-24-51-400-001.

(b) Install :

Refer to Fig. A-FBAAA Sheet 01

1 Bracket Item (7) Retained at

removal

2 Nuts Item (6) Retained at

removal

2 Bolts Item (5) Retained at

removal

2 Clamp Blocks Item (4) Retained at

removal

1 Pipe Item (9) Retained at

removal

1 Pipe Item (10) Retained at

removal

2 Clamp Blocks Item (3) Retained at

removal

4 Washers Item (2) Retained at

removal

2 Bolts Item (1) Retained at

removal

2 Bolts Item (8) Retained at

removal

DATE: Feb 16/93 SERVICE BULLETIN No.: A320-57-1043

REVISION No.: 06 - Dec 05/13 Page: 17

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(2) Subtask 571043-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

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

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

equipment.

(b) Close the access doors 195BB and 196BB, refer to AMM 06-41-53, Page Block

001.

(c) Remove the warning notices.

(d) Remove the access platform(s).

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

DATE: Feb 16/93 SERVICE BULLETIN No.: A320-57-1043

REVISION No.: 06 - Dec 05/13 Page: 18

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Task 571043-831-802-001 - Modification - ADDITIONAL WORK for Aircraft modified by

Revision No. 05 or any Previous Issue

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.

IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00.

NOTE: The accomplishment instructions of this Service Bulletin refer to procedures

included in other AIRBUS documents. When the words "refer to" are used and the

operator has an accepted alternative procedure, the accepted alternative procedure

can be used. When the words "in accordance with" are included in the instruction,

the procedure in the AIRBUS document must be used.

NOTE: The access and close-up instructions, not comprising return to service tests, in this

Service Bulletin do not constitute or affect the technical intent of the Service

Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or

close-up steps to add flexibility to their maintenance operations as long as the

technical intent of the Service Bulletin is met within the set parameters.

NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms.

Refer to paragraph 1.J., References, for the definition of acronyms.

Task Associated Data

Manpower

TOTAL MANHOURS 11.00

ELAPSED TIME (HOURS) 7.00

A. GENERAL

(1) Subtask 571043-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

DATE: Feb 16/93 SERVICE BULLETIN No.: A320-57-1043

REVISION No.: 06 - Dec 05/13 Page: 19

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References

Consumable Material List (CML)

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

Consumable Materials List (CML).

(2) Subtask 571043-839-002-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

B. PREPARATION

(1) Subtask 571043-941-002-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

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

Task 12-34-24-869-002

Task 29-00-00-864-001

Task 29-00-00-910-002

Task 29-14-00-614-001

Task 29-23-00-860-001

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

12-34-24-869-002.

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

(c) Obey the hydraulic safety procedures, refer to AMM Task 29-00-00-910-002.

(d) Put the warning notices in position to tell persons not to pressurize the Yellow

hydraulic system :

- In the cockpit, on the Hydraulic/Fuel Panel 40VU of the overhead panel.

- On the ground service panels of the Green and Yellow hydraulic systems.

(e) Put the warning notices in position to tell persons not to pressurize the Blue

hydraulic system :

- In the cockpit, on the Hydraulic/Fuel Panel 40VU of the overhead panel.

- On the ground service panels of the Blue hydraulic systems.

(f) Make sure that Blue and Yellow hydraulic systems are depressurized and put it in

the maintenance configuration, refer to AMM Task 29-00-00-864-001.

DATE: Feb 16/93 SERVICE BULLETIN No.: A320-57-1043

REVISION No.: 06 - Dec 05/13 Page: 20

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(g) Depressurize the reservoirs of the Blue and Yellow hydraulic systems, refer to AMM

Task 29-14-00-614-001.

(h) Disconnect the isolation coupling from the Power Transfer Unit (PTU), refer to AMM

Task 29-23-00-860-001.

(i) Open the access doors 195BB and 196BB, refer to AMM 06-41-53, Page Block

001.

(j) Open, safety and tag these circuit breakers :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

49VU HYD/HYD PWR/B

WARN/AND CTL

2702GJ 14 D

49VU HYD/HYD PWR/B WARN/&

CTL

2702GJ 12 C

121VU HYDRAULIC/SOL

VALVES/G/Y/B/LEAK/TST

1881GP 35 N

123VU B HYD/ELEC PUMP 2701GJ 09AB

121VU HYDRAULIC/HYD POWER/Y 3803GX 30 N

123VU Y HYD/ELEC/PUMP 3802GX 06AB

123VU Y HYD/ELEC PUMP/NORM 3801GX 03AB

(2) Subtask 571043-020-002-001 - Remove the pipes for access

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 29-24-51-000-001

Fig. A-FBAAA

Removal for Access to the Working Area

Sheet 01

Get access to the working area.

(a) Remove the suction pipe, refer to item 1 of AMM Task 29-24-51-000-001.

(b) Remove :

Refer to Fig. A-FBAAA Sheet 01

2 Bolts Item (1) Retain

4 Washers Item (2) Retain

2 Clamp Blocks Item (3) Retain

2 Clamp Blocks Item (4) Retain

2 Bolts Item (5) Retain

DATE: Feb 16/93 SERVICE BULLETIN No.: A320-57-1043

REVISION No.: 06 - Dec 05/13 Page: 21

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2 Nuts Item (6) Retain

1 Bracket Item (7) Retain

2 Bolts Item (8) Retain

1 Pipe Item (9) Retain

1 Pipe Item (10) Retain

C. PROCEDURE

(1) Subtask 571043-832-003-001 - Do a HFEC inspection

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 57-11-95 Part 6

Fig. A-FBBAA

Shot Peening on the Outer Side of the

Lower Panel in the Thickness Changes

near the Fuel Pump Aperture

Sheet 01

Sheet 02

Do a High Frequency Eddy Current (HFEC) Inspection on the lower panel, the lower

surface of the center wing box, refer to NTM 57-11-95, Part 6

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

(a) If you find no crack :

- Do a shot peening as written in SUBTASK 571043-831-002.

(b) If you find a crack :

- Contact Airbus and apply corrective actions defined by Airbus, before next

flight.

(2) Subtask 571043-831-002-001 - Do a shot peening

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

DATE: Feb 16/93 SERVICE BULLETIN No.: A320-57-1043

REVISION No.: 06 - Dec 05/13 Page: 22

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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

Polish Metal Aluminum 05-025 As required

Sealing Tape 08-005 As required

Fabric Tape Pressure

Sensitive

08-038 As required

Methyl Alcohol 11-006 As required

Solvent General Purpose 11-026 As required

Chemical Conversion

Coating Yellow Aluminum

13-002 As required

Polyurethane Primer 16-001 As required

Anti-Corrosion Primer

(Epoxy-Imprvd Adhesion)

16-006 As required

References

Process and Material Specification

(PMS)

Process and Material Specification (PMS)

01-01-13

Structural Repair Manual (SRM) 51-75-11

Fig. A-FBBAA

Shot Peening on the Outer Side of the

Lower Panel in the Thickness Changes

near the Fuel Pump Aperture

Sheet 01

Sheet 02

Do a shot peening on the outer side of the lower panel, where thickness changes, near

the fuel pump aperture.

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

(a) SHOT PEENING PROCEDURE

1 Equipment and materials

a Vacu blast : JUNIOR MATRASUR or equivalent

USF

28-30, rue de Tournefils

BP 45

91542 MENNECY

Tel : +33 (0)1-64-57-07-91

Fax : + 33 (0)1-64-57-12-60

b Gun type : MATRASUR 617161

c Almen test specimen : A2 + GF 9801-4141

d Holding fixture : 9801-4130

DATE: Feb 16/93 SERVICE BULLETIN No.: A320-57-1043

REVISION No.: 06 - Dec 05/13 Page: 23

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e Dial indicator : 9999-0787

Supplier :

FISHER

105, rue Charles Michels

BP 174

93208 St Denis cedex

Tel : +33 (0)1-49-22-13-13

f Bead : Glass beads BV300, dia. 0.3 mm (0.012 in.)

Supplier :

VAPOR BLAST

Avenue Le Verrier

Z.A.I. des bruyeres

78190 TRAPPES

Tel : 16-1-30-69-09-09

Fax : 16-1-30-69-09-27

2 Vacu blast unit set-up

- Switch on the VACU BLAST unit (refer to the manufacturer’s instructions)

- Load the glass beads BV300

- Adjust the intensity to agree with the ALMEN test specimen : F13A2 to

F16A2.

You must adjust the intensity of the shot peening to make a deflection of 0.13

mm (0.0052 in.) to 0.16 mm (0.0064 in.) of the Almen specimen "’A".

3 Job set-up

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

a Mask area surrounding the area to be stripped with

Sealing Tape 08-005 As required

, enlarge area by 5mm.

b Strip paint in accordance with SRM 51-75-11.

c Clean the area with solvent.

d Remove the surface protection Chromic Acid Anodized (CAA) layer by

polishing using :

Polish Metal

Aluminum

05-025 As required

until a bright finish is obtained.

DATE: Feb 16/93 SERVICE BULLETIN No.: A320-57-1043

REVISION No.: 06 - Dec 05/13 Page: 24

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e Mechanical rework to remove paint, primer and CAA, ensure depth

comprised between 0.3 mm (0.012 in.) and 0.4 mm (0.016 in.).

f Finishing the part until obtaining aluminium shinning on all areas as per

instructions given in Fig. A-FBBAA Sheet 02.

g Ensure that the surface is smooth and without defects.

h clean area with :

Solvent General

Purpose

11-026 As required

or alcohol.

i Remove masking tape.

j Carefully apply a protection to the areas around the areas to shot peen

with :

Fabric Tape

Pressure Sensitive

08-038 As required

k Apply a protection to the adjacent area and equipment (with manila paper

or equivalent).

l Shot peen the surface with a number of passes that you specified before,

refer to Process and Material Specification (PMS) 01-01-13 for the

general data related to the shot peening procedure.

m Clean the area that you shot peened with :

Methyl Alcohol 11-006 As required

and renew the protective finish with :

Chemical

Conversion Coating

Yellow Aluminum

13-002 As required

Polyurethane

Primer

16-001 As required

and

Anti-Corrosion

Primer (EpoxyImprvd Adhesion)

16-006 As required

DATE: Feb 16/93 SERVICE BULLETIN No.: A320-57-1043

REVISION No.: 06 - Dec 05/13 Page: 25

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D. TEST

(1) Subtask 571043-700-002-001 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 29-12-00-700-001

Task 29-14-00-720-001

Task 29-23-00-710-004

Task 29-24-00-710-001

NOTE: This test procedure is to be accomplished after the installation of the

equipment removed for access, SUBTASK 571043-420-002 001 Install

the pipes

(a) Job Set-up

1 Remove the safety clips and tags and close these circuit breakers :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

49VU HYD/HYD PWR/B

WARN/AND CTL

2702GJ 14 D

49VU HYD/HYD PWR/B WARN/&

CTL

2702GJ 12 C

121VU HYDRAULIC/SOL

VALVES/G/Y/B/LEAK/TST

1881GP 35 N

123VU B HYD/ELEC PUMP 2701GJ 09AB

121VU HYDRAULIC/HYD POWER/Y 3803GX 30 N

123VU Y HYD/ELEC/PUMP 3802GX 06AB

123VU Y HYD/ELEC PUMP/NORM 3801GX 03AB

(b) Tests

1 Do an operational test of the Yellow auxilliary power, refer to AMM Task

29-24-00-710-001 and make sure that is no leak on the pipes that you

installed again.

2 Do an operational test of the electric pump of the Blue hydraulic system, refer

to AMM Task 29-12-00-700-001 and make sure that there is no leak on the

pipes that you installed again.

3 Do a functional test of the pressure system of the hydraulic reservoirs, refer to

AMM Task 29-14-00-720-001.

4 Do an operational test of the power transfer unit, refer to AMM Task

29-23-00-710-004.

DATE: Feb 16/93 SERVICE BULLETIN No.: A320-57-1043

REVISION No.: 06 - Dec 05/13 Page: 26

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E. CLOSE-UP

(1) Subtask 571043-420-002-001 - Install the pipes

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 29-24-51-400-001

Fig. A-FBAAA

Removal for Access to the Working Area

Sheet 01

(a) Install the suction pipe, refer to Item 1 of AMM Task 29-24-51-400-001.

(b) Install :

Refer to Fig. A-FBAAA Sheet 01

1 Bracket Item (7) Retained at

removal

2 Nuts Item (6) Retained at

removal

2 Bolts Item (5) Retained at

removal

2 Clamp Blocks Item (4) Retained at

removal

1 Pipe Item (9) Retained at

removal

1 Pipe Item (10) Retained at

removal

2 Clamp Blocks Item (3) Retained at

removal

4 Washers Item (2) Retained at

removal

2 Bolts Item (1) Retained at

removal

2 Bolts Item (8) Retained at

removal

DATE: Feb 16/93 SERVICE BULLETIN No.: A320-57-1043

REVISION No.: 06 - Dec 05/13 Page: 27

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(2) Subtask 571043-942-002-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

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

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

equipment.

(b) Close the access doors 195BB and 196BB, refer to AMM 06-41-53, Page Block

001.

(c) Remove the warning notices.

(d) Remove the access platform(s).

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

DATE: Feb 16/93 SERVICE BULLETIN No.: A320-57-1043

REVISION No.: 06 - Dec 05/13 Page: 28

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**CONF ALL

B

1

2

3

4

7

5

5

6

8

2

3

4

2

8

1

2

A

B

C

C

A Z195

FR42

FR41

10

9

N_SB_571043_5_BAAA_01_01

Figure A-FBAAA - Sheet 01

Removal for Access to the Working Area

DATE: Feb 16/93 SERVICE BULLETIN No.: A320-57-1043

REVISION No.: 06 - Dec 05/13 Page: 29

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**CONF ALL

9mm 20mm

(0.354in.) (0.787in.)

A/C

FUEL PUMP APERTURE

EXTERNAL SIDE OF THE

LOWER PANEL

EXTERNAL VIEW OF LOWER PANEL

AREA TO BE INSPECTED AREA TO BE INSPECTED

329 mm

(12.952 in.)

329 mm

(12.952 in.)

AREAS TO BE SHOT PEENED

A

B

F

W

D B

FR41

FR42

FUEL PUMP APERTURE

A A

A

FR42

FR41

CL

A A

C C

AREAS TO BE SHOT PEENED

N_SB_571043_5_BBAA_01_03

Figure A-FBBAA - Sheet 01

Shot Peening on the Outer Side of the Lower Panel in the Thickness Changes near the Fuel

Pump Aperture

DATE: Feb 16/93 SERVICE BULLETIN No.: A320-57-1043

REVISION No.: 06 - Dec 05/13 Page: 30

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**CONF ALL

20 mm

(0.787 in.)

9 mm

(0.354 in.)

EXTERNAL VIEW OF LOWER PANEL

LH SIDE SHOWN (RH SIDE SYMMETRICAL)

30 mm

(1.181 in.)

20 mm

(0.787 in.)

9 mm

(0.354 in.)

20 mm

(0.787 in.)

9 mm

(0.354 in.)

AREA TO BE

SHOT PEENED

F

W

D C

MECHANICAL REWORK TO REMOVE PAINT, PRIMER AND CAA:

− ENSURE DEPTH 0.3mm (+0.1 / −0) WITH REGARD TO THE PAINTED SURFACE

(0.012 in) (+0.004 / −0)

NOTE:

− MECHANICAL REWORK COTATION: MINIMUM SURFACE

TO MECHANICAL REWORK N_SB_571043_5_BBAA_02_02

Figure A-FBBAA - Sheet 02

Shot Peening on the Outer Side of the Lower Panel in the Thickness Changes near the Fuel Pump

Aperture

DATE: Feb 16/93 SERVICE BULLETIN No.: A320-57-1043

REVISION No.: 06 - Dec 05/13 Page: 31

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REPORTING SHEET

TITLE: WINGS - SECTION 21 - INTRODUCE SHOT PEENING ON LOWER

SURFACE PANEL

MODIFICATION No.: 22418P2408

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 16/93 SERVICE BULLETIN No.: A320-57-1043

REVISION No.: 06 - Dec 05/13 Page: 1

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SERVICE BULLETIN

QUALITY PERCEPTION FORM

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

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

improve the quality of our Service Bulletins.

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

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

- Quality rating of this SB 4321

- Quality rating of the Accomplishment Instructions 4321

- Quality rating of the Illustrations 4321

- Is this SB easy to understand ? Y/N

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

short description of the issue.

Planning Material Instructions

X Effectivity X Kit content X Preparation

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

X Manpower X Industry support X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustrations

Comments:

Operator: Date:

Name/Title:

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE: Feb 16/93 SERVICE BULLETIN No.: A320-57-1043

REVISION No.: 06 - Dec 05/13 Page: 1

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