@A330

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 25

TITLE: EQUIPMENT/FURNISHINGS - COCKPIT - INSPECTION OF COCKPIT

INSTRUMENT PANEL BRACKET 6.

MODIFICATION No.: None

This page transmits Revision No.02 of Service Bulletin No.A330-25-3538

ADDITIONAL WORK

**CONF ALL

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

REASON

Revision No. 02 issued to extend the effectivity to aircraft MSN 0250.

CHANGES

SUMMARY

EFFECTIVITY OPERATOR LIST UPDATED R

PLANNING INFORMATION

EFFECTIVITY EFFECTIVITY RELATED INFORMATION

UPDATED

R

Configuration definition

CONF 002 CONFIGURATION DEFINITION UPDATED R

MATERIAL INFORMATION

MATERIAL - PRICE AND AVAILABILITY

Procurement Addresses PROCUREMENT ADDRESSES UPDATED R

ACCOMPLISHMENT INSTRUCTIONS

TASK 253538- 832-801-001-Inspection. TASK SOLUTION UPDATED

CAUTION UPDATED

R

Subtask 253538-941-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

R

Subtask 253538-941-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

R

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 1

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@A330

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Subtask 253538-941-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

R

Subtask 253538-941-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

R

Subtask 253538-942-001-001 SUBTASK SOLUTION UPDATED

REFERENCES UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

R

Subtask 253538-942-001-001 SUBTASK SOLUTION UPDATED

REFERENCES UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

R

Subtask 253538-942-001-001 SUBTASK SOLUTION UPDATED

REFERENCES UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

R

Subtask 253538-942-001-001 SUBTASK SOLUTION UPDATED

REFERENCES UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

R

TASK 253538- 833-801-001-Replace

Bracket No. 6.

TASK SOLUTION UPDATED

CAUTION UPDATED

R

Subtask 253538-941-002-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

R

Subtask 253538-941-002-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

R

Subtask 253538-941-002-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

R

Subtask 253538-941-002-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

R

Subtask 253538-942-002-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

R

Subtask 253538-942-002-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

R

Subtask 253538-942-002-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

R

Subtask 253538-942-002-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

R

TASK 253538- 833-802-001-Replace

Bracket No. 7.

TASK SOLUTION UPDATED

CAUTION UPDATED

R

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 2

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@A330

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Subtask 253538-941-003-001 SUBTASK SOLUTION UPDATED

PANEL UPDATED

REFERENCED DOCUMENTATION UPDATED

R

Subtask 253538-941-003-001 SUBTASK SOLUTION UPDATED

PANEL UPDATED

REFERENCED DOCUMENTATION UPDATED

R

Subtask 253538-941-003-001 SUBTASK SOLUTION UPDATED

PANEL UPDATED

REFERENCED DOCUMENTATION UPDATED

R

Subtask 253538-941-003-001 SUBTASK SOLUTION UPDATED

PANEL UPDATED

REFERENCED DOCUMENTATION UPDATED

R

Subtask 253538-942-003-001 SUBTASK SOLUTION UPDATED

PANEL UPDATED

REFERENCED DOCUMENTATION UPDATED

R

Subtask 253538-942-003-001 SUBTASK SOLUTION UPDATED

PANEL UPDATED

REFERENCED DOCUMENTATION UPDATED

R

Subtask 253538-942-003-001 SUBTASK SOLUTION UPDATED

PANEL UPDATED

REFERENCED DOCUMENTATION UPDATED

R

Subtask 253538-942-003-001 SUBTASK SOLUTION UPDATED

PANEL UPDATED

REFERENCED DOCUMENTATION UPDATED

R

FILLING INSTRUCTIONS

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

Replace the complete document.

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

HISTORY OF PREVIOUS REVISIONS

Revision No. 01 issued to:

add Service Bulletin No A330-25-3548 as terminating solution,

update the effectivity,

and minor changes.

REVISION SEQUENCE

ORIGINAL: Sep 10/13

REVISION No. : 01 - Jan 31/14

REVISION No. : 02 - Apr 24/14

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 3

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@A330

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

This Page Intentionally Left Blank

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 4

5

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@A330

SERVICE BULLETIN

SUMMARY

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

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

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 25

TITLE: EQUIPMENT/FURNISHINGS - COCKPIT - INSPECTION OF COCKPIT

INSTRUMENT PANEL BRACKET 6.

**CONF ALL

MODIFICATIONS

None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

During flight tests carried out with A340-600, high stress level were measured on the bracket No. 6 (PN

F2511012820000 Pre Mod No. 55128S18242 or PN F2511373420000 Post Mod No. 55128S18242),

which is one of the 8 parts used to attach the cockpit instrument panel to the aircraft structure.

This is linked to a coupling between the vibration levels due to the bumps of the runways and

introduced through the Nose Landing Gear (NLG), and the cockpit panel. Using accelerations

introduced at pilot seat location, the bracket No. 6 cannot sustain any fatigue loads of the Long Range

Design Service Goal (DSG).

Accomplishment of this Inspection Service Bulletin is no longer necessary in the case of Service

Bulletin A330-25-3548 has been embodied.

This inspection Service Bulletin requires performing a detailed inspection before 17,200 Flight Cycles

(FC) of the bracket No. 6 PN F2511012820000 Pre Mod No. 55128S18242 or PN F2511373420000

Post Mod No. 55128S18242 of the Cockpit Instrument Panel.

Depending on the results of this inspection, this Service Bulletin is issued to give the relevant corrective

action.

Accomplishment of this Service Bulletin will prevent the risk of having the Bracket No. 6 fully broken

and, consequently, further damage on the surrounding structure.

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO

POTENTIAL AD YES A/C OPERATION AFFECTED NO

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 1

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@A330

SERVICE BULLETIN

SUMMARY

EVALUATION TABLE

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 must be accomplished.

MATERIAL PRICE INFORMATION

**CONF 001

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Component COMPA01 2 See SB Bracket

Component COMPA03 1 See SB Fastening

Component COMPA08 1 See SB Fastening

**CONF 002

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Component COMPA01 2 See SB Bracket

Component COMPA04 1 See SB Fastening

Component COMPA09 1 See SB Fastening

**CONF 003

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Component COMPA01 2 See SB Bracket

Component COMPA05 1 See SB Fastening

Component COMPA10 1 See SB Fastening

**CONF 004

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Component COMPA01 2 See SB Bracket

Component COMPA02 1 See SB Bracket

Component COMPA06 1 See SB Fastening

Component COMPA10 1 See SB Fastening

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 2

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@A330

SERVICE BULLETIN

SUMMARY

EFFECTIVITY

**CONF ALL

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

11S 31V 36V 38W 39V 62S 69X 99Y AAR AAW ABD ACA ACI

AEA AFL AFR AIB AIC ALK ARA ARG ASY AVA AWW AZA BEC

BEL BER CAL CCA CEB CES CHH CPA CRK CRL CSA CSC CSN

DAH DAL DGA DLH EDW EIN ETD EVA EVE FIN FJI FWI GAP

GFA GIA GRL HAL HDA HFY HVN I2L IAW IBE ISS IYE JAI

JST KAL KLM LAA MAS MAU MEA MNB MON MSR NMB OHY OMA

PAL QAF QFA QTR RJA RSF RSY SAA SAI SAS SIA SVA SWR

SYA TAE TAM TAP TCX THA THY TNA TOW TPA TSC UAE UAF

USA VIR VKG VOZ WRC XAX XLF YZR

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

**CONF 001

Task 253538-832-801-001: Inspection.

TOTAL MANHOURS 7.50

ELAPSED TIME (HOURS) 7.50

Task 253538-833-801-001: Replace Bracket No. 6.

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 3

5

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@A330

SERVICE BULLETIN

SUMMARY

Task 253538-833-802-001: Replace Bracket No. 7.

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

**CONF 002

Task 253538-832-801-001: Inspection.

TOTAL MANHOURS 7.50

ELAPSED TIME (HOURS) 7.50

Task 253538-833-801-001: Replace Bracket No. 6.

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

Task 253538-833-802-001: Replace Bracket No. 7.

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

**CONF 003

Task 253538-832-801-001: Inspection.

TOTAL MANHOURS 7.50

ELAPSED TIME (HOURS) 7.50

Task 253538-833-801-001: Replace Bracket No. 6.

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

Task 253538-833-802-001: Replace Bracket No. 7.

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

**CONF 004

Task 253538-832-801-001: Inspection.

TOTAL MANHOURS 7.50

ELAPSED TIME (HOURS) 7.50

Task 253538-833-801-001: Replace Bracket No. 6.

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

Task 253538-833-802-001: Replace Bracket No. 7.

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 4

5

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@A330

SERVICE BULLETIN

SUMMARY

APPENDICES

**CONF ALL

None

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 5

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@A330

SERVICE BULLETIN

SUMMARY

**CONF ALL

TO BE INSPECTED

A

A

TO BE INSPECTED

BRACKET No 6

BRACKET No 7

G_SB_253538_5_SAAA_01_01

Figure A-FSAAA - Sheet 01

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 6

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Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A330

SERVICE BULLETIN

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 25

TITLE: EQUIPMENT/FURNISHINGS - COCKPIT - INSPECTION OF COCKPIT

INSTRUMENT PANEL BRACKET 6.

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

NOTE: This Service Bulletin is only applicable to aircraft on which modification No.

203287S32572 (REINFORCE INSTRUMENT PANEL BRACKET NO. 6 IN

COCKPIT AREA) is not embodied.

(1) Models

330-202 330-203 330-223 330-223F 330-243 330-243F 330-301 330-302

330-303 330-321 330-322 330-323 330-341 330-342 330-343

(2) Effectivity by MSN

0012 0017 0030 0037 0045 0050 0054-0055 0060 0062 0064-0067 0070-0072

0082-0083 0086-0087 0095-0096 0098-0099 0102 0106 0109 0111-0113 0116

0118-0122 0127 0132 0138 0140 0143-0144 0148 0153 0155 0162 0165 0171-0172

0177 0181 0183-0184 0188-0189 0191 0195 0198 0200 0203 0205-0206 0209 0211

0219 0222-0224 0226 0229-0232 0234 0238 0240-0241 0244 0247-0251 0253-0256

0258-0259 0261-0262 0265-0267 0269 0271-0272 0275-0277 0279 0281 0283-0288

0290-0291 0293-0296 0299-0301 0303 0305-0306 0308-0309 0311-0317 0320

0322-0324 0326 0328 0330 0333-0334 0337-0340 0342-0346 0348-0351 0353

0356-0358 0361-0362 0364-0366 0368-0370 0372 0375 0380 0382 0384 0386

0388-0389 0392-0393 0396-0398 0400-0401 0403-0405 0407-0409 0412 0418-0423

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 1

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@A330

SERVICE BULLETIN

0425 0427-0428 0432 0437 0439 0441 0443-0444 0448 0451-0452 0454-0456 0458

0461-0463 0465-0466 0469 0472-0473 0476-0477 0479-0481 0484 0486-0487

0489-0491 0493-0494 0496-0498 0500-0513 0515-0516 0518-0519 0521-0522

0524-0527 0529-0530 0532-0533 0535-0536 0539 0542 0548-0553 0555 0558

0564-0565 0567-0568 0570-0571 0573-0574 0576 0578-0579 0581 0584 0587-0588

0591 0593 0595 0597 0600 0602-0603 0605 0607 0609-0610 0612 0614 0616 0618

0620-0621 0623 0625 0627 0629 0631-0638 0640-0642 0644-0645 0647-0650

0652-0659 0661-0667 0669-0671 0673-0676 0678-0680 0682-0684 0686-0688

0690-0693 0695-0697 0699-0701 0703-0705 0707-0709 0711-0714 0716-0718

0720-0722 0724-0726 0728-0730 0732-0735 0737-0739 0741-0743 0745-0747

0749-0752 0754-0756 0758-0760 0769-0770 0772-0774 0776-0778 0780-0782

0784-0786 0788-0789 0791-0792 0795-0797 0799 0801-0803 0805-0807 0809-0811

0813-0815 0817-0828 0830-0834 0836 0838-0843 0845 0847 0849-0855 0857-0863

0865-0869 0871 0873-0877 0879 0881-0885 0887-0893 0895-0896 0898-0901

0903-0909 0911 0913-0916 0918-0920 0922-0923 0925-0928 0930-0932 0934-0937

0939-0952 0954 0956-0959 0961-0971 0973-0980 0982-0986 0988-0992 0994-1004

1006-1016 1018-1023 1025-1026 1028-1029 1031-1039 1041-1049 1051-1055

1057-1063 1065-1067 1069-1078 1080-1082 1084-1090 1092-1101 1103-1108 1110

1112 1114-1116 1118 1120 1123-1124 1126-1127 1129-1133 1135-1138 1141 1143

1145-1151 1153 1155-1157 1159-1161 1163-1165 1167-1175 1177-1178 1180-1181

1183-1184 1186-1193 1195-1196 1198-1206 1208-1241 1243-1252 1254-1256

1258-1272 1274-1473

(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

11S 1053

31V 0205

36V 0437 0451

38W 0401

39V 0939

62S 1321

69X 0494

99Y 1419 1439

AAR 0640 0676 0708 0772 0803 0845 1001 1055 1151 1211 1326 1340

1435 1464

AAW 0999 1043 1472

ABD 0343

ACA 0277 0279 0284 0344 0400 0408 0412 0419

ACI 0507 0510

AEA 0461 0505 0526 0551 0597 0670 0733 0745 0749 0814 0931 0950

0992 1097

AFL 0963 0973 1014 1045 1047 1058 1065 1072 1077 1103 1232 1247

1264 1270 1284 1299 1301 1323 1328 1345 1356 1371

AFR 0422 0443 0448 0458 0465 0481 0498 0500 0502 0503 0516 0519

0567 0584 0657

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 2

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@A330

SERVICE BULLETIN

OPERATOR MSN

AIB 0871

AIC 0353 0362

ALK 0303 0306 0311 0313 0404 0456 0627

ARA 0874 0891 0927

ARG 0290 0300 0358 0364

ASY 0747 0951 0969 1036 1183

AVA 0948 0967 1009 1016 1073 1208 1224 1279 1342 1400

AWW 0255

AZA 0272 0339 1123 1135 1218 1225 1252 1283 1308 1313 1327 1354

BEC 0863

BEL 0030 0037 0045 0082 0095 0229 0249 0324

BER 0288 0322 0403 0432 0444 0454 0469 0476 0493 0665 0739 0822

0828 0911

CAL 0602 0607 0641 0671 0675 0691 0699 0707 0714 0752 0769 0805

0823 0838 0861 0920 1177 1272 1278 1346 1367 1450

CCA 0750 0756 0759 0780 0785 0797 0810 0815 0839 0860 0867 0873

0884 0890 0903 0909 0930 0941 0944 0957 1087 1110 1130 1187

1199 1216 1237 1260 1282 1304 1330 1333 1353 1373 1383 1396

1413 1434 1444 1459 1471

CEB 1420 1445

CES 0713 0720 0728 0732 0735 0773 0777 0781 0782 0791 0821 0830

0836 0851 0862 0866 0916 0928 0936 0942 1262 1267 1280 1291

1303 1324 1331 1372 1375 1402 1421 1429 1440 1461 1468

CHH 0875 0881 0906 0919 0982 1159 1168 1178 1190 1255 1325 1369

1438

CPA 0102 0113 0121 0386 0389 0393 0418 0420 0421 0423 0439 0539

0548 0565 0679 0776 0850 0855 0895 0915 0959 1163 1196 1222

1239 1285 1317 1343 1349 1362 1366 1387 1409 1436 1443

CRK 1031 1034 1039 1042 1051 1054 1059 1062 1115 1277 1286 1320

1322 1358 1384 1398

CRL 0285 0320 1359 1376

CSA 0425

CSC 0462 1082 1138 1241 1397 1432

CSN 0649 0652 0656 0664 0818 0840 0879 0889 0908 0935 0937 0954

0958 0964 1096 1116 1129 1202 1220 1233 1244 1297 1309 1335

1392 1425 1430

DAH 0644 0647 0650 0653 0667

DAL 0524 0533 0542 0549 0552 0578 0588 0591 0609 0614 0618 0620

0621 0631 0633 0663 0674 0690 0718 0722 0778 0784 0796 0799

0806 0817 0827 0843 0857 0858 0859 0865

DGA 0240

DLH 0570 0576 0579 0629 0636 0642 0645 0648 0687 0701 0896 0905

0913 0922 0989 1292 1305 1314

EDW 0291 1193

EIN 0269 0397 0841 0847 0985 1025 1106

ETD 0658 0688 0717 0724 0729 0730 0737 0751 0788 0807 0809 0824

0825 0831 0832 0852 0854 0868 0885 0888 0975 0991 1032 1070

1071 1081 1167 1205 1226 1245 1414

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 3

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@A330

SERVICE BULLETIN

OPERATOR MSN

EVA 0530 0535 0555 0573 0587 0634 0655 0661 0678 0693 0755 1254

1268 1274

EVE 0833

FIN 0994 1007 1013 1023 1067 1078 1088 1173

FJI 1394 1416 1465

FWI 0253 0758 0965 1021 1265

GAP 1456

GFA 0276 0281 0286 0287 0334 0340

GIA 0138 0140 0144 0148 0153 0165 0988 1020 1028 1052 1184 1214

1261 1288 1364 1410 1446

GRL 0230

HAL 1104 1114 1171 1217 1259 1295 1302 1310 1316 1389 1399 1404

1422 1469

HDA 0012 0017 0071 0083 0099 0106 0109 0118 0155 0234 0244 0405

0479 0512 0581 0669 0673 1457

HFY 0096 0127 0211 0262 1008

HVN 0275 0294 0299 0366 0943 0946 0962 1019 1256 1266

I2L 0527 0532 0725

IAW 1339

IBE 1377 1385 1405 1426 1437

ISS 0802

IYE 0625 0632

JAI 0923 0947 0956 1351 1361 1370 1391

JST 0506 0513 0522 0842 0853 0940 0945 1198 1251

KAL 0162 0172 0206 0219 0222 0226 0241 0256 0258 0267 0338 0350

0351 0368 0428 0484 0490 0550 1133 1155 1200 1203 1393

KLM 0682 0686 0703 0738 0770 0801 0811 0819 0834 0900 0925 1161

1287 1294 1300 1381

LAA 1412 1424

MAS 0067 0116 0119 1136 1148 1164 1180 1209 1219 1229 1234 1243

1281 1318 1336 1337 1347 1388 1395 1431 1470

MAU 0883 1057

MEA 0926 0984 0995 0998

MNB 1332

MON 0261 0265

MSR 0600 0610 0666 0683 0696 0709 0726 1143 1230 1238 1246

NMB 1451 1466

OHY 0072 0087 0098 0143

OMA 1038 1044 1049 1063 1093 1120 1227

PAL 0183 0184 0188 0189 0191 0198 0200 0203 1449 1460 1463 1467

QAF 0487 0605

QFA 0508 0553 0558 0564 0574 0593 0595 0603 0695 0705 0712 0887

0892 0898 0976 1061 1094 1169 1174 1258 1365

QTR 0441 0473 0489 0511 0521 0571 0612 0616 0623 0637 0638 0659

0680 0684 0711 0721 0734 0743 0746 0760 0789 0792 0813 0820

0826 0849 0893 0907 0918 1350 1386 1406

RJA 0970 0979 1002

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 4

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@A330

SERVICE BULLETIN

OPERATOR MSN

RSF 0980 0996 1235 1379

RSY 0120 0171

SAA 1191 1210 1223 1236 1249 1271

SAI 0055 0070 0086

SAS 0496 0497 0515 0568

SIA 0978 0983 0986 0997 1006 1010 1012 1015 1085 1098 1099 1105

1107 1124 1132 1146 1149 1156 1157 1382 1401 1427 1447 1453

SVA 1108 1127 1137 1141 1147 1153 1189 1192 1454 1462 1473

SWR 1000 1018 1026 1029 1084 1089 1101 1145 1181 1188 1276 1290

1355 1403

SYA 0345

TAE 0348

TAM 0232 0238 0247 0259 0361 0466 0472 0477 0486 0700 0869 0876

0949 0961 0968 0977 1112 1118 1213 1221

TAP 0181 0195 0223 0305 0308 0312 0317 0877 0899 0904 0914 0934

TCX 0254 0266 0301 0398

THA 0050 0060 0062 0064 0065 0066 0112 0122 0209 0224 0231 0346

0990 1003 1035 1037 1060 1074 1086 1090 1263 1269 1289 1338

1348 1374 1408

THY 0463 0504 0529 0697 0704 0742 0754 0774 0882 0901 0932 1004

1092 1150 1160 1170 1172 1204 1212 1228 1240 1298 1307 1311

1344 1418 1442 1458

TNA 1357 1378

TOW 1033 1046 1248 1275 1312 1334 1363 1390

TPA 1368 1380 1428 1448

TSC 0111 0132 0177 0250 0271 0369 0407 0427 0480 0795 0966 0971

UAE 0248 0251 0283 0293 0295 0314 0316 0326 0328 0382 0384 0392

0396 0409 0452 0455 0491 0509 0518 0525 0536

UAF 1080 1186 1250

USA 0315 0323 0333 0337 0342 0370 0375 0380 0388 1011 1022 1041

1069 1076 1095 1100 1415 1417 1441 1455

VIR 1195 1201 1206 1215 1231 1296 1315 1329 1341 1352

VKG 0309 0349 0356 0357

VOZ 0365 0372 1293 1306 1319 1407 1452

WRC 0296

XAX 0054 0330 0654 0662 0692 0716 0741 0786 0952 0974 1048 1066

1075 1126 1131 1165 1411 1423 1433

XLF 0501 0635 1360

YZR 1175

(4) Configuration by MSN

MSN CONFIGURATION

0012 0017 0030 0037 0045 0050 0054 0055 0060 0062 0064

0065 0066 0067 0070 0071 0072 0082 0083 0086 0087 0095

0096 0098 0099 0102 0106 0109 0111 0112 0113 0116 0118

0119 0120 0121 0122 0127 0132 0138 0140 0143 0144 0148

0153 0155 0162 0165 0171 0172 0177 0181 0183 0184

001

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

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@A330

SERVICE BULLETIN

MSN CONFIGURATION

0188 0189 0191 0195 0198 0200 0203 0205 0206 0209 0211

0219 0222 0223 0224 0226 0229 0230 0231 0232 0234 0238

0240 0241 0244 0247 0248 0249 0250 0251 0253 0254 0255

0256 0258 0259 0261 0262 0265 0266 0267 0269 0271 0272

0275 0276 0277 0279 0281 0283 0284 0285 0286 0287 0288

0290 0291 0293 0294 0295 0296 0299 0300 0301 0303 0305

0306 0308 0309 0311 0312 0313 0314 0315 0316 0317 0320

0322 0323 0324 0326 0328 0330 0333 0334 0337 0338 0339

0340 0342 0343 0344 0345 0346 0348 0349 0350 0351 0353

0356 0357 0358 0361 0362 0364 0365 0366 0368 0369 0370

0372 0375 0380 0382 0384 0386 0388 0389 0392 0393 0396

0397 0398 0400 0401 0403 0404 0405 0407 0408 0409 0412

0418 0419 0420 0421 0422 0423 0425 0427 0428 0432 0437

0439 0441 0443 0444 0448 0451 0452 0454 0455 0456 0458

0461 0462 0463 0465 0466 0469 0472 0473 0476 0477 0479

0480 0481 0484 0486 0487 0489 0490 0491 0493 0494 0496

0497 0498 0500 0501 0502 0503 0504 0505 0506 0507 0508

0509 0510 0511 0512 0513 0515 0516 0518 0519 0521 0522

0524 0525 0526 0527 0529 0530 0532 0533 0535 0536 0539

0542 0548 0549 0550 0551 0552 0553 0555 0558 0564 0565

0567 0568 0570 0571 0573 0574 0576 0578 0579 0581 0584

0587 0588 0591 0593 0595 0597 0600 0602 0603 0605 0607

0609 0610 0612 0614 0616 0618 0620 0621 0623 0625 0627

0629 0631 0632 0633 0634 0635 0636 0637 0638 0640 0641

0642 0644 0645 0647 0648 0649 0650

002

0652 0653 0654 0655 0656 0657 0658 0659 0661 0662 0663

0664 0665 0666 0667 0669 0670 0671 0673 0674 0675 0676

0678 0679 0680 0682 0683 0684 0686 0687 0688 0690 0691

0692 0693 0695 0696 0697 0699 0700 0701 0703 0704 0705

0707 0708 0709 0711 0712 0713 0714 0716 0717 0718 0720

0721 0722 0724 0725 0726 0728 0729 0730 0732 0733 0734

0735 0737 0738 0739 0741 0742 0743 0745 0746 0747 0749

0750 0751 0752 0754 0755 0756 0758 0759 0760 0769 0770

0772 0773 0774 0776 0777 0778 0780 0781 0782 0784 0785

0786 0788 0789 0791 0792 0795 0796 0797 0799 0801 0802

0803 0805 0806 0807 0809 0810 0811 0813 0814 0815 0817

0818 0819 0820 0821 0822 0823 0824 0825 0826 0827 0828

0830 0831 0832 0833 0834 0836 0838 0839 0840 0841 0842

0843 0845 0847 0849 0850 0851 0852 0853 0854 0855 0857

0858 0859 0860 0861 0862 0863 0865 0866 0867

003

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 6

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@A330

SERVICE BULLETIN

MSN CONFIGURATION

0868 0869 0871 0873 0874 0875 0876 0877 0879 0881 0882

0883 0884 0885 0887 0888 0889 0890 0891 0892 0893 0895

0896 0898 0899 0900 0901 0903 0904 0905 0906 0907 0908

0909 0911 0913 0914 0915 0916 0918 0919 0920 0922 0923

0925 0926 0927 0928 0930 0931 0932 0934 0935 0936 0937

0939 0940 0941 0942 0943 0944 0945 0946 0947 0948 0949

0950 0951 0952 0954 0956 0957 0958 0959 0961 0962 0963

0964 0965 0966 0967 0968 0969 0970 0971 0973 0974 0975

0976 0977 0978 0979 0980 0982 0983 0984 0985 0986 0988

0989 0990 0991 0992 0994 0995 0996 0997 0998 0999 1000

1001 1002 1003 1004 1006 1007 1008 1009 1010 1011 1012

1013 1014 1015 1016 1018 1019 1020 1021 1022 1023 1025

1026 1028 1029 1031 1032 1033 1034 1035 1036 1037 1038

1039 1041 1042 1043 1044 1045 1046 1047 1048 1049 1051

1052 1053 1054 1055 1057 1058 1059 1060 1061 1062 1063

1065 1066 1067 1069 1070 1071 1072 1073 1074 1075 1076

1077 1078 1080 1081 1082 1084 1085 1086 1087 1088 1089

1090 1092 1093 1094 1095 1096 1097 1098 1099 1100 1101

1103 1104 1105 1106 1107 1108 1110 1112 1114 1115 1116

1118 1120 1123 1124 1126 1127 1129 1130 1131 1132 1133

1135 1136 1137 1138 1141 1143 1145 1146 1147 1148 1149

1150 1151 1153 1155 1156 1157 1159 1160 1161 1163 1164

1165 1167 1168 1169 1170 1171 1172 1173 1174 1175 1177

1178 1180 1181 1183 1184 1186 1187 1188 1189 1190 1191

1192 1193 1195 1196 1198 1199 1200 1201 1202 1203 1204

1205 1206 1208 1209 1210 1211 1212 1213 1214 1215 1216

1217 1218 1219 1220 1221 1222 1223 1224 1225 1226 1227

1228 1229 1230 1231 1232 1233 1234 1235 1236 1237 1238

1239 1240 1241 1243 1244 1245 1246 1247 1248 1249 1250

1251 1252 1254 1255 1256 1258 1259 1260 1261 1262 1263

1264 1265 1266 1267 1268 1269 1270 1271 1272 1274 1275

1276 1277 1278 1279 1280 1281 1282 1283 1284 1285 1286

1287 1288 1289 1290 1291 1292 1293 1294 1295 1296 1297

1298 1299 1300 1301 1302 1303 1304 1305 1306 1307 1308

1309 1310 1311 1312 1313 1314 1315 1316 1317 1318 1319

1320 1321 1322 1323 1324 1325 1326 1327 1328 1329 1330

1331 1332 1333 1334 1335 1336 1337 1338 1339 1340 1341

1342 1343 1344 1345 1346 1347 1348 1349 1350 1351 1352

1353 1354 1355 1356 1357 1358 1359 1360 1361 1362 1363

1364 1365 1366 1367 1368 1369 1370 1371 1372 1373 1374

1375 1376 1377 1378 1379 1380 1381 1382 1383 1384 1385

1386 1387 1388 1389 1390 1391 1392 1393 1394 1395 1396

1397 1398 1399 1400 1401 1402 1403 1404 1405 1406 1407

1408 1409 1410 1411 1412 1413 1414 1415 1416 1417 1418

1419 1420 1421 1422 1423 1424 1425 1426 1427 1428 1429

1430 1431 1432 1433 1434 1435 1436 1437 1438 1439 1440

1441 1442 1443 1444 1445 1446 1447 1448 1449 1450 1451

1452 1453 1454 1455 1456 1457 1458 1459 1460 1461 1462

1463 1464 1465 1466 1467 1468 1469 1470 1471 1472 1473

004

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 7

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@A330

SERVICE BULLETIN

(5) Configuration definition

**CONF 001

Config. 001 is valid for aircraft on which Mod. No. 45411S13604 , Mod. No.

53446S18217 and Mod. No. 55128S18242 are not embodied.

**CONF 002

Config. 002 is valid for aircraft on which Mod. No. 45411S13604 is embodied and Mod.

No. 53446S18217 and Mod. No. 55128S18242 are not embodied.

**CONF 003

Config. 003 is valid for aircraft on which Mod. No. 45411S13604 and Mod. No.

53446S18217 are embodied and Mod. No. 55128S18242 is not embodied.

**CONF 004

Config. 004 is valid for aircraft on which Mod. No. 45411S13604 , Mod. No.

53446S18217 and Mod. No. 55128S18242 are embodied.

(6) Material Effectivity

**CONF 001

MATERIAL QTY PER A/C SEE NOTES

Component COMPA01 2

Component COMPA03 1

Component COMPA08 1

Consumable CMLA01 1

**CONF 002

MATERIAL QTY PER A/C SEE NOTES

Component COMPA01 2

Component COMPA04 1

Component COMPA09 1

Consumable CMLA01 1

**CONF 003

MATERIAL QTY PER A/C SEE NOTES

Component COMPA01 2

Component COMPA05 1

Component COMPA10 1

Consumable CMLA01 1

**CONF 004

MATERIAL QTY PER A/C SEE NOTES

Component COMPA01 2

Component COMPA02 1

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 8

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@A330

SERVICE BULLETIN

MATERIAL QTY PER A/C SEE NOTES

Component COMPA06 1

Component COMPA10 1

Consumable CMLA01 1

**CONF ALL

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

During flight tests carried out with A340-600, high stress level were measured

on the bracket No. 6 (PN F2511012820000 Pre Mod No. 55128S18242 or PN

F2511373420000 Post Mod No. 55128S18242), which is one of the 8 parts used to

attach the cockpit instrument panel to the aircraft structure.

This is linked to a coupling between the vibration levels due to the bumps of the

runways and introduced through the Nose Landing Gear (NLG), and the cockpit panel.

Using accelerations introduced at pilot seat location, the bracket No. 6 cannot sustain

any fatigue loads of the Long Range Design Service Goal (DSG).

(2) Objective/Action

Accomplishment of this Inspection Service Bulletin is no longer necessary in the case of

Service Bulletin A330-25-3548 has been embodied.

This inspection Service Bulletin requires performing a detailed inspection before 17,200

Flight Cycles (FC) of the bracket No. 6 PN F2511012820000 Pre Mod No. 55128S18242

or PN F2511373420000 Post Mod No. 55128S18242 of the Cockpit Instrument Panel.

Depending on the results of this inspection, this Service Bulletin is issued to give the

relevant corrective action.

(3) Advantages

Accomplishment of this Service Bulletin will prevent the risk of having the Bracket No. 6

fully broken and, consequently, further damage on the surrounding structure.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 9

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@A330

SERVICE BULLETIN

**CONF 001

Task 253538-832-801-001: Inspection.

(1) Do a Detailed Inspection of the Bracket No. 6.

(2) Do a Detailed Inspection of the Bracket No. 7.

(3) Install/Close Items Removed/Opened for access.

Task 253538-833-801-001: Replace Bracket No. 6.

(1) Replace the Bracket No. 6.

(2) Install/Close Items Removed/Opened for access.

Task 253538-833-802-001: Replace Bracket No. 7.

(1) Replace the Bracket No. 7.

(2) Install/Close Items Removed/Opened for access

**CONF 002

Task 253538-832-801-001: Inspection.

(1) Do a Detailed Inspection of the Bracket No. 6.

(2) Do a Detailed Inspection of the Bracket No. 7.

(3) Install/Close Items Removed/Opened for access.

Task 253538-833-801-001: Replace Bracket No. 6.

(1) Replace the Bracket No. 6.

(2) Install/Close Items Removed/Opened for access.

Task 253538-833-802-001: Replace Bracket No. 7.

(1) Replace the Bracket No. 7.

(2) Install/Close Items Removed/Opened for access

**CONF 003

Task 253538-832-801-001: Inspection.

(1) Do a Detailed Inspection of the Bracket No. 6.

(2) Do a Detailed Inspection of the Bracket No. 7.

(3) Install/Close Items Removed/Opened for access.

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 10

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@A330

SERVICE BULLETIN

Task 253538-833-801-001: Replace Bracket No. 6.

(1) Replace the Bracket No. 6.

(2) Install/Close Items Removed/Opened for access.

Task 253538-833-802-001: Replace Bracket No. 7.

(1) Replace the Bracket No. 7.

(2) Install/Close Items Removed/Opened for access

**CONF 004

Task 253538-832-801-001: Inspection.

(1) Do a Detailed Inspection of the Bracket No. 6.

(2) Do a Detailed Inspection of the Bracket No. 7.

(3) Install/Close Items Removed/Opened for access.

Task 253538-833-801-001: Replace Bracket No. 6.

(1) Replace the Bracket No. 6.

(2) Install/Close Items Removed/Opened for access.

Task 253538-833-802-001: Replace Bracket No. 7.

(1) Replace the Bracket No. 7.

(2) Install/Close Items Removed/Opened for access

**CONF ALL

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

(2) Accomplishment Timescale

**CONF 001

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

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

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

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 11

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@A330

SERVICE BULLETIN

Compliance (whichever occurs

later)

Condition Action

Threshold Grace period

from SB first

issuance date

Repetitive

interval

All aircraft Do a detailed inspection of the

bracket No. 6 (Refer to TASK

253538-832-801 001

Inspection. )

17,200 FC from

aircraft first flight

500 FC

See Note*

None

Do a detailed inspection of the

bracket No. 6 again (Refer to

TASK 253538-832-801 001

Inspection. )

None None 2,600 FC

OR

Implement Service Bulletin

No. A330-25-3548 as

terminative solution.

2600 FC None None

OR

Replace the bracket No. 6

(Refer to TASK

253538-833-801 001 Replace

Bracket No. 6. )

Within 2,600 FC

after inspection

None None

AND

No crack found

Do a detailed inspection of the

bracket No. 6 again (Refer to

TASK 253538-832-801 001

Inspection. )

17,200 FC None None

Replace the bracket No. 6

(Refer to TASK

253538-833-801 001 Replace

Bracket No. 6. )

Within 2,600 FC

after inspection

None None

AND

Do a detailed inspection of the

bracket No. 6 again (Refer to

TASK 253538-832-801 001

Inspection. )

17,200 FC None None

OR

Crack found and

both bracket lugs

are not fully broken

Implement Service Bulletin

No. A330-25-3548 as

terminative solution.

2,600 FC None None

Crack found and

both bracket lugs

fully broken

Do a detailed inspection of the

bracket No. 7 (Refer to

SUBTASK 253538-700-004

001 Do a Detailed Inspection

of the Bracket No. 7. )

Before next flight None None

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 12

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@A330

SERVICE BULLETIN

Compliance (whichever occurs

later)

Condition Action

Threshold Grace period

from SB first

issuance date

Repetitive

interval

Replace the bracket No. 6

(Refer to TASK

253538-833-801 001 Replace

Bracket No. 6. ) and replace

the bracket No. 7 (Refer to

TASK 253538-833-802 001

Replace Bracket No. 7. )

Before next flight None None

AND

Do a detailed inspection of the

bracket No. 6 again (Refer to

TASK 253538-832-801 001

Inspection. )

17,200 FC None None

OR

Replace the bracket No. 7

(Refer to TASK

253538-833-802 001 Replace

Bracket No. 7. )

Before next flight None None

AND

No crack found on

bracket No. 7

Implement Service Bulletin

No. A330-25-3548 as

terminative solution.

Before next flight None None

Crack found on

bracket No. 7

Contact AIRBUS Before next flight None None

Note*: For AC having accumulated near or more than 17200 FC, perform the inspection before 500

FC from SB first issuance date

Table 1 - Do a detailed inspection of the Bracket No. 6.

**CONF 002

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

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

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

Compliance (whichever occurs

later)

Condition Action

Threshold Grace period

from SB first

issuance date

Repetitive

interval

All aircraft Do a detailed inspection of the

bracket No. 6 (Refer to TASK

253538-832-801 001

Inspection. )

17,200 FC from

aircraft first flight

500 FC

See Note*

None

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 13

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@A330

SERVICE BULLETIN

Compliance (whichever occurs

later)

Condition Action

Threshold Grace period

from SB first

issuance date

Repetitive

interval

Do a detailed inspection of the

bracket No. 6 again (Refer to

TASK 253538-832-801 001

Inspection. )

None None 2,600 FC

OR

Implement Service Bulletin

No. A330-25-3548 as

terminative solution.

2600 FC None None

OR

Replace the bracket No. 6

(Refer to TASK

253538-833-801 001 Replace

Bracket No. 6. )

Within 2,600 FC

after inspection

None None

AND

No crack found

Do a detailed inspection of the

bracket No. 6 again (Refer to

TASK 253538-832-801 001

Inspection. )

17,200 FC None None

Replace the bracket No. 6

(Refer to TASK

253538-833-801 001 Replace

Bracket No. 6. )

Within 2,600 FC

after inspection

None None

AND

Do a detailed inspection of the

bracket No. 6 again (Refer to

TASK 253538-832-801 001

Inspection. )

17,200 FC None None

OR

Crack found and

both bracket lugs

are not fully broken

Implement Service Bulletin

No. A330-25-3548 as

terminative solution.

2,600 FC None None

Crack found and

both bracket lugs

fully broken

Do a detailed inspection of the

bracket No. 7 (Refer to

SUBTASK 253538-700-004

001 Do a Detailed Inspection

of the Bracket No. 7. )

Before next flight None None

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 14

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@A330

SERVICE BULLETIN

Compliance (whichever occurs

later)

Condition Action

Threshold Grace period

from SB first

issuance date

Repetitive

interval

Replace the bracket No. 6

(Refer to TASK

253538-833-801 001 Replace

Bracket No. 6. ) and replace

the bracket No. 7 (Refer to

TASK 253538-833-802 001

Replace Bracket No. 7. )

Before next flight None None

AND

Do a detailed inspection of the

bracket No. 6 again (Refer to

TASK 253538-832-801 001

Inspection. )

17,200 FC None None

OR

Replace the bracket No. 7

(Refer to TASK

253538-833-802 001 Replace

Bracket No. 7. )

Before next flight None None

AND

No crack found on

bracket No. 7

Implement Service Bulletin

No. A330-25-3548 as

terminative solution.

Before next flight None None

Crack found on

bracket No. 7

Contact AIRBUS Before next flight None None

Note*: For AC having accumulated near or more than 17200 FC, perform the inspection before 500

FC from SB first issuance date

Table 1 - Do a detailed inspection of the Bracket No. 6.

**CONF 003

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

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

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

Compliance (whichever occurs

later)

Condition Action

Threshold Grace period

from SB first

issuance date

Repetitive

interval

All aircraft Do a detailed inspection of the

bracket No. 6 (Refer to TASK

253538-832-801 001

Inspection. )

17,200 FC from

aircraft first flight

500 FC

See Note*

None

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 15

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@A330

SERVICE BULLETIN

Compliance (whichever occurs

later)

Condition Action

Threshold Grace period

from SB first

issuance date

Repetitive

interval

Do a detailed inspection of the

bracket No. 6 again (Refer to

TASK 253538-832-801 001

Inspection. )

None None 2,600 FC

OR

Implement Service Bulletin

No. A330-25-3548 as

terminative solution.

2600 FC None None

OR

Replace the bracket No. 6

(Refer to TASK

253538-833-801 001 Replace

Bracket No. 6. )

Within 2,600 FC

after inspection

None None

AND

No crack found

Do a detailed inspection of the

bracket No. 6 again (Refer to

TASK 253538-832-801 001

Inspection. )

17,200 FC None None

Replace the bracket No. 6

(Refer to TASK

253538-833-801 001 Replace

Bracket No. 6. )

Within 2,600 FC

after inspection

None None

AND

Do a detailed inspection of the

bracket No. 6 again (Refer to

TASK 253538-832-801 001

Inspection. )

17,200 FC None None

OR

Crack found and

both bracket lugs

are not fully broken

Implement Service Bulletin

No. A330-25-3548 as

terminative solution.

2,600 FC None None

Crack found and

both bracket lugs

fully broken

Do a detailed inspection of the

bracket No. 7 (Refer to

SUBTASK 253538-700-004

001 Do a Detailed Inspection

of the Bracket No. 7. )

Before next flight None None

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 16

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SERVICE BULLETIN

Compliance (whichever occurs

later)

Condition Action

Threshold Grace period

from SB first

issuance date

Repetitive

interval

Replace the bracket No. 6

(Refer to TASK

253538-833-801 001 Replace

Bracket No. 6. ) and replace

the bracket No. 7 (Refer to

TASK 253538-833-802 001

Replace Bracket No. 7. )

Before next flight None None

AND

Do a detailed inspection of the

bracket No. 6 again (Refer to

TASK 253538-832-801 001

Inspection. )

17,200 FC None None

OR

Replace the bracket No. 7

(Refer to TASK

253538-833-802 001 Replace

Bracket No. 7. )

Before next flight None None

AND

No crack found on

bracket No. 7

Implement Service Bulletin

No. A330-25-3548 as

terminative solution.

Before next flight None None

Crack found on

bracket No. 7

Contact AIRBUS Before next flight None None

Note*: For AC having accumulated near or more than 17200 FC, perform the inspection before 500

FC from SB first issuance date

Table 1 - Do a detailed inspection of the Bracket No. 6.

**CONF 004

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

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

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

Compliance (whichever occurs

later)

Condition Action

Threshold Grace period

from SB first

issuance date

Repetitive

interval

All aircraft Do a detailed inspection of the

bracket No. 6 (Refer to TASK

253538-832-801 001

Inspection. )

17,200 FC from

aircraft first flight

500 FC

See Note*

None

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 17

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SERVICE BULLETIN

Compliance (whichever occurs

later)

Condition Action

Threshold Grace period

from SB first

issuance date

Repetitive

interval

Do a detailed inspection of the

bracket No. 6 again (Refer to

TASK 253538-832-801 001

Inspection. )

None None 2,600 FC

OR

Implement Service Bulletin

No. A330-25-3548 as

terminative solution.

2600 FC None None

OR

Replace the bracket No. 6

(Refer to TASK

253538-833-801 001 Replace

Bracket No. 6. )

Within 2,600 FC

after inspection

None None

AND

No crack found

Do a detailed inspection of the

bracket No. 6 again (Refer to

TASK 253538-832-801 001

Inspection. )

17,200 FC None None

Replace the bracket No. 6

(Refer to TASK

253538-833-801 001 Replace

Bracket No. 6. )

Within 2,600 FC

after inspection

None None

AND

Do a detailed inspection of the

bracket No. 6 again (Refer to

TASK 253538-832-801 001

Inspection. )

17,200 FC None None

OR

Crack found and

both bracket lugs

are not fully broken

Implement Service Bulletin

No. A330-25-3548 as

terminative solution.

2,600 FC None None

Crack found and

both bracket lugs

fully broken

Do a detailed inspection of the

bracket No. 7 (Refer to

SUBTASK 253538-700-004

001 Do a Detailed Inspection

of the Bracket No. 7. )

Before next flight None None

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 18

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SERVICE BULLETIN

Compliance (whichever occurs

later)

Condition Action

Threshold Grace period

from SB first

issuance date

Repetitive

interval

Replace the bracket No. 6

(Refer to TASK

253538-833-801 001 Replace

Bracket No. 6. ) and replace

the bracket No. 7 (Refer to

TASK 253538-833-802 001

Replace Bracket No. 7. )

Before next flight None None

AND

Do a detailed inspection of the

bracket No. 6 again (Refer to

TASK 253538-832-801 001

Inspection. )

17,200 FC None None

OR

Replace the bracket No. 7

(Refer to TASK

253538-833-802 001 Replace

Bracket No. 7. )

Before next flight None None

AND

No crack found on

bracket No. 7

Implement Service Bulletin

No. A330-25-3548 as

terminative solution.

Before next flight None None

Crack found on

bracket No. 7

Contact AIRBUS Before next flight None None

Note*: For AC having accumulated near or more than 17200 FC, perform the inspection before 500

FC from SB first issuance date

Table 1 - Do a detailed inspection of the Bracket No. 6.

**CONF ALL

F. APPROVAL

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

Organization Approval No. EASA.21J.031.

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

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

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

before incorporation of the Service Bulletin.

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 19

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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 253538-832-801-001: Inspection.

Get Access 2.50

On Aircraft

Do a Detailed Inspection of the Bracket No. 6. 1.00

Do a Detailed Inspection of the Bracket No. 7. 1.00

Install/Close Items Removed/Opened for access. 0.50

Close-Up 2.50

TOTAL MANHOURS 7.50

ELAPSED TIME (HOURS) 7.50

Task 253538-833-801-001: Replace Bracket No. 6.

Get Access 2.50

On Aircraft

Replace the Bracket No. 6. 2.00

Install/Close Items Removed/Opened for access. 0.50

Tests 4.00

Close-Up 2.50

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

Task 253538-833-802-001: Replace Bracket No. 7.

Get Access 2.50

On Aircraft

Replace the Bracket No. 7. 2.00

Install/Close Items Removed/Opened for access 0.50

Tests 4.00

Close-Up 2.50

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

**CONF 002

Task 253538-832-801-001: Inspection.

Get Access 2.50

On Aircraft

Do a Detailed Inspection of the Bracket No. 6. 1.00

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 20

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@A330

SERVICE BULLETIN

Task 253538-832-801-001: Inspection.

Do a Detailed Inspection of the Bracket No. 7. 1.00

Install/Close Items Removed/Opened for access. 0.50

Close-Up 2.50

TOTAL MANHOURS 7.50

ELAPSED TIME (HOURS) 7.50

Task 253538-833-801-001: Replace Bracket No. 6.

Get Access 2.50

On Aircraft

Replace the Bracket No. 6. 2.00

Install/Close Items Removed/Opened for access. 0.50

Tests 4.00

Close-Up 2.50

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

Task 253538-833-802-001: Replace Bracket No. 7.

Get Access 2.50

On Aircraft

Replace the Bracket No. 7. 2.00

Install/Close Items Removed/Opened for access 0.50

Tests 4.00

Close-Up 2.50

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

**CONF 003

Task 253538-832-801-001: Inspection.

Get Access 2.50

On Aircraft

Do a Detailed Inspection of the Bracket No. 6. 1.00

Do a Detailed Inspection of the Bracket No. 7. 1.00

Install/Close Items Removed/Opened for access. 0.50

Close-Up 2.50

TOTAL MANHOURS 7.50

ELAPSED TIME (HOURS) 7.50

Task 253538-833-801-001: Replace Bracket No. 6.

Get Access 2.50

On Aircraft

Replace the Bracket No. 6. 2.00

Install/Close Items Removed/Opened for access. 0.50

Tests 4.00

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 21

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SERVICE BULLETIN

Task 253538-833-801-001: Replace Bracket No. 6.

Close-Up 2.50

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

Task 253538-833-802-001: Replace Bracket No. 7.

Get Access 2.50

On Aircraft

Replace the Bracket No. 7. 2.00

Install/Close Items Removed/Opened for access 0.50

Tests 4.00

Close-Up 2.50

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

**CONF 004

Task 253538-832-801-001: Inspection.

Get Access 2.50

On Aircraft

Do a Detailed Inspection of the Bracket No. 6. 1.00

Do a Detailed Inspection of the Bracket No. 7. 1.00

Install/Close Items Removed/Opened for access. 0.50

Close-Up 2.50

TOTAL MANHOURS 7.50

ELAPSED TIME (HOURS) 7.50

Task 253538-833-801-001: Replace Bracket No. 6.

Get Access 2.50

On Aircraft

Replace the Bracket No. 6. 2.00

Install/Close Items Removed/Opened for access. 0.50

Tests 4.00

Close-Up 2.50

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

Task 253538-833-802-001: Replace Bracket No. 7.

Get Access 2.50

On Aircraft

Replace the Bracket No. 7. 2.00

Install/Close Items Removed/Opened for access 0.50

Tests 4.00

Close-Up 2.50

TOTAL MANHOURS 11.50

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 22

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@A330

SERVICE BULLETIN

Task 253538-833-802-001: Replace Bracket No. 7.

ELAPSED TIME (HOURS) 11.50

**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 06-41-52 12-34-24

21-26-00 22-96-00 22-97-00

24-41-00 25-11-51 31-50-00

31-60-00 31-63-22 33-12-13

33-13-00 33-14-00 52-10-00

Elec. Std. Practices Manual (ESPM) 20-52-20 20-55-00

Service Bulletin (SB) A330-25-3548

Standards Manual (SM)

Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00

51-44-00 51-75-12

**CONF 002

Aircraft Maintenance Manual (AMM) 06-20-00 06-41-52 12-34-24

21-26-00 22-96-00 22-97-00

24-41-00 25-11-51 31-50-00

31-60-00 31-63-22 33-12-13

33-13-00 33-14-00 52-10-00

Elec. Std. Practices Manual (ESPM) 20-52-20 20-55-00

Service Bulletin (SB) A330-25-3548

Standards Manual (SM)

Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00

51-44-00 51-75-12

**CONF 003

Aircraft Maintenance Manual (AMM) 06-20-00 06-41-52 12-34-24

21-26-00 22-96-00 22-97-00

24-41-00 25-11-51 31-50-00

31-60-00 31-63-22 33-12-13

33-13-00 33-14-00 52-10-00

Elec. Std. Practices Manual (ESPM) 20-52-20 20-55-00

Service Bulletin (SB) A330-25-3548

Standards Manual (SM)

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 23

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@A330

SERVICE BULLETIN

Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00

51-44-00 51-75-12

**CONF 004

Aircraft Maintenance Manual (AMM) 06-20-00 06-41-52 12-34-24

21-26-00 22-96-00 22-97-00

24-41-00 25-11-51 31-50-00

31-60-00 31-63-22 33-12-13

33-13-00 33-14-00 52-10-00

Elec. Std. Practices Manual (ESPM) 20-52-20 20-55-00

Service Bulletin (SB) A330-25-3548

Standards Manual (SM)

Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00

51-44-00 51-75-12

**CONF ALL

K. PUBLICATION AFFECTED

Illustrated Parts Catalog (IPC) 25-14-01

Impact on Scheduled maintenance: Refer to MPD

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 24

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@A330

SERVICE BULLETIN

2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

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:

Component COMPA01

Component COMPA02

AIRBUS

Material, Logistics and Suppliers

IFD - In Flight Desk

Weg beim Jaeger 150

D-22335 HAMBURG

GERMANY

For ordering by internet:

http://spares.airbus.com

For ordering by fax: +49 40 50 76 4012

For ordering by E-mail:

ifd.spares@airbus.com

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

multiple suppliers ensure access to minimum prices AIRBUS recommends Customers

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

B/E Aerospace. The address is:

Component COMPA03

Component COMPA04

Component COMPA05

Component COMPA06

Component COMPA08

Component COMPA09

Component COMPA10

B/E AEROSPACE INC.

CONSUMABLES MANAGEMENT

10000 NW 15th Terrace Miami

FL 33172

USA

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

Tel US: +1 305 925 2600

Tel ASIA: +1 310 900 1300

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

Fax US: +1 305 507 7191

Fax ASIA: +1 310 819 1200

SITA: MIAMMCR

E-Mail: AOGdesk_CMG@beaerospace.com

internet: http://www.beconsumables.com

or, alternatively any other source on the open

market

(2) Price and Availability

No AIRBUS kit will be provided.

Operator supplied AIRBUS parts required to accomplish this Service Bulletin are to be

purchased by a spares purchase order.

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 25

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SERVICE BULLETIN

Operator supplied standard hardware parts required to accomplish this Service Bulletin

are to be supplied from the Operator’s stock.

B. INDUSTRY SUPPORT INFORMATION

AIRBUS will not provide industry support for accomplishment of this Service Bulletin.

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

Synthetic Ester Base GreaseGeneral Purpose Low T03HBD9 As required

(2) Components

Component COMPA01

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

NOTES

16 F2511012820095 BRACKET (16) F2511012820000

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Component COMPA02

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

NOTES

6 F2511373420095 1 BRACKET (6) F2511373420000

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Component COMPA03

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

NOTES

7 NAS6604-10 1 BOLT

8 NAS1726-4E 1 NUT

11 ASNA2050DCJ3215 3 RIVET

15 ASNA2050DEJ4020 4 RIVET

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 26

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SERVICE BULLETIN

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 above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Component COMPA04

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

NOTES

11 ASNA2050DCJ3215 3 RIVET

15 ASNA2050DEJ4020 4 RIVET

17 NSA5042-04-160 1 BOLT

18 NSA5060-3 1 NUT

19 NSA5325-3 1 WASHER

20 MS24665-134 1 PIN

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 above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Component COMPA05

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

NOTES

11 ASNA2050DCJ3215 3 RIVET

15 ASNA2050DEJ4020 4 RIVET

17 NSA5042-04-160 1 BOLT

18 NSA5060-3 1 NUT

19 NSA5325-3 1 WASHER

21 MS24665-71 1 PIN

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 above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Component COMPA06

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

NOTES

9 EN6115V3-5 4 BOLT

10 ASNA2531-3 4 NUT

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 27

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SERVICE BULLETIN

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

NOTES

11 ASNA2050DCJ3215 3 RIVET

17 NSA5042-04-160 1 BOLT

18 NSA5060-3 1 NUT

19 NSA5325-3 1 WASHER

21 MS24665-71 1 PIN

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 above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Component COMPA08

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

NOTES

7 NAS6604-10 1 BOLT

8 NAS1726-4E 1 NUT

15 ASNA2050DEJ4020 4 RIVET

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 above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Component COMPA09

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

NOTES

15 ASNA2050DEJ4020 4 RIVET

17 NSA5042-04-160 1 BOLT

18 NSA5060-3 1 NUT

19 NSA5325-3 1 WASHER

20 MS24665-134 1 PIN

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 above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 28

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SERVICE BULLETIN

Component COMPA10

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

NOTES

15 ASNA2050DEJ4020 4 RIVET

17 NSA5042-04-160 1 BOLT

18 NSA5060-3 1 NUT

19 NSA5325-3 1 WASHER

21 MS24665-71 1 PIN

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 above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

None

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 29

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SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 30

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SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

Task 253538-832-801-001 - Inspection.

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

INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

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

THIS:

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

NECESSARY ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00.

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.

NOTE: This Service Bulletin is classified mandatory or expected to be classified mandatory

by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these

accomplishment instructions are Required for Compliance (RC) and must be done

to comply with the AD. Other paragraphs are recommended and may be deviated

from, done as part of other actions or done with accepted methods different from

those given in the Service Bulletin, as long as the RC paragraphs can be done and

the aircraft can be put back into a serviceable condition.

NOTE: The purpose of flow charts is to supplement the information given in the Procedure

and Compliance paragraphs and not to serve as the primary source for tasks or

compliance times given in this Service Bulletin.

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 31

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SERVICE BULLETIN

Task Associated Data

**CONF 001

Zone

212

Manpower

TOTAL MANHOURS 7.50

ELAPSED TIME (HOURS) 7.50

**CONF 002

Zone

212

Manpower

TOTAL MANHOURS 7.50

ELAPSED TIME (HOURS) 7.50

**CONF 003

Zone

212

Manpower

TOTAL MANHOURS 7.50

ELAPSED TIME (HOURS) 7.50

**CONF 004

Zone

212

Manpower

TOTAL MANHOURS 7.50

ELAPSED TIME (HOURS) 7.50

**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 253538-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

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

06-41-52, Page Block 001

(a) For the identification of zones, refer to AMM 06-20-00, Page Block 001.

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 32

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@A330

SERVICE BULLETIN

(b) For the identification of access panels, refer to AMM 06-41-52, Page Block 001.

(2) Subtask 253538-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

**CONF 002

(1) Subtask 253538-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

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

06-41-52, Page Block 001

(a) For the identification of zones, refer to AMM 06-20-00, Page Block 001.

(b) For the identification of access panels, refer to AMM 06-41-52, Page Block 001.

(2) Subtask 253538-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

**CONF 003

(1) Subtask 253538-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

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

06-41-52, Page Block 001

(a) For the identification of zones, refer to AMM 06-20-00, Page Block 001.

(b) For the identification of access panels, refer to AMM 06-41-52, Page Block 001.

(2) Subtask 253538-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 33

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A330

SERVICE BULLETIN

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

Service Bulletin.

**CONF 004

(1) Subtask 253538-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

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

06-41-52, Page Block 001

(a) For the identification of zones, refer to AMM 06-20-00, Page Block 001.

(b) For the identification of access panels, refer to AMM 06-41-52, Page Block 001.

(2) Subtask 253538-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

**CONF ALL

B. PREPARATION

**CONF 001

(1) Subtask 253538-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 34

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@A330

SERVICE BULLETIN

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

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

12-34-24-860-802.

(2) Subtask 253538-010-001-001 - Remove/Open for Access

Manpower Resources

Skills NON SPECIFIC

References

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

(a) Remove the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retain

3 Washer Item (2) Retain

1 Panel Item (3) Retain

(b) Remove the cover assembly panel.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retain

1 Panel Item (4) Retain

**CONF 002

(1) Subtask 253538-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 35

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A330

SERVICE BULLETIN

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

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

12-34-24-860-802.

(2) Subtask 253538-010-001-001 - Remove/Open for Access

Manpower Resources

Skills NON SPECIFIC

References

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

(a) Remove the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retain

3 Washer Item (2) Retain

1 Panel Item (3) Retain

(b) Remove the cover assembly panel.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retain

1 Panel Item (4) Retain

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 36

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@A330

SERVICE BULLETIN

**CONF 003

(1) Subtask 253538-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

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

12-34-24-860-802.

(2) Subtask 253538-010-001-001 - Remove/Open for Access

Manpower Resources

Skills NON SPECIFIC

References

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

(a) Remove the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retain

3 Washer Item (2) Retain

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 37

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@A330

SERVICE BULLETIN

1 Panel Item (3) Retain

(b) Remove the cover assembly panel.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retain

1 Panel Item (4) Retain

**CONF 004

(1) Subtask 253538-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

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

12-34-24-860-802.

(2) Subtask 253538-010-001-001 - Remove/Open for Access

Manpower Resources

Skills NON SPECIFIC

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 38

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@A330

SERVICE BULLETIN

References

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

(a) Remove the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retain

3 Washer Item (2) Retain

1 Panel Item (3) Retain

(b) Remove the cover assembly panel.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retain

1 Panel Item (4) Retain

**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 253538-700-001-001 - Do a Detailed Inspection of the Bracket No. 6.

Work Zones and Access Panels

Zone Access/Work location

212

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Service Bulletin (SB) A330-25-3548

Fig. A-FBAAA

Area to be inspected

Sheet 01

Sheet 02

Fig. A-FFAAA

Flow-chart

Sheet 01

Fig. A-FRAAA

Inspection Report

Sheet 01

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 39

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@A330

SERVICE BULLETIN

At the threshold given in the PLANNING INFORMATION paragraph E.(2):

(a) Do a detailed inspection of the bracket No. 6.

Refer to Fig. A-FBAAA

Refer to Fig. A-FFAAA

1 If no crack is found:

a Do a detailed inspection of the bracket No. 6 at the interval given

in the PLANNING INFORMATION paragraph E.(2), refer to TASK

253538-832-801 001 Inspection.

or

b Implement Service Bulletin No. A330-25-3548 as terminative solution at

the threshold given in the PLANNING INFORMATION paragraph E.(2).

or

c Replace the bracket No. 6 at the threshold given in the PLANNING

INFORMATION paragraph E.(2), refer to TASK 253538-833-801 001

Replace Bracket No. 6.

and

Do a detailed inspection of the bracket No. 6 at the threshold given

in the PLANNING INFORMATION paragraph E.(2), refer to TASK

253538-832-801 001 Inspection.

2 If a crack is found and both bracket lugs are not fully broken:

a Replace the bracket No. 6 at the threshold given in the PLANNING

INFORMATION paragraph E.(2), refer to TASK 253538-833-801 001

Replace Bracket No. 6.

and

Do a detailed inspection of the bracket No. 6 at the threshold given

in the PLANNING INFORMATION paragraph E.(2), refer to TASK

253538-832-801 001 Inspection.

or

b Implement Service Bulletin No. A330-25-3548 as terminative solution at

the threshold given in the PLANNING INFORMATION paragraph E.(2).

3 If a crack is found and both bracket lugs are fully broken:

a Do a detailed inspection of the bracket No. 7.

Refer to SUBTASK 253538-700-004- 001

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 40

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@A330

SERVICE BULLETIN

(b) Send inspection report to Airbus, refer to Fig. A-FRAAA.

(2) Subtask 253538-700-004-001 - Do a Detailed Inspection of the Bracket No. 7.

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills NON SPECIFIC

References

Service Bulletin (SB) A330-25-3548

Fig. A-FBAAA

Area to be inspected

Sheet 01

Sheet 02

Fig. A-FFAAA

Flow-chart

Sheet 01

Fig. A-FRAAA

Inspection Report

Sheet 01

At the threshold given in the PLANNING INFORMATION paragraph E.(2):

(a) Do a detailed inspection of the bracket No. 7.

Refer to Fig. A-FBAAA

Refer to Fig. A-FFAAA

1 If no crack is found on the bracket No. 7.

a Replace the bracket No. 6 at the threshold given in the PLANNING

INFORMATION paragraph E.(2), refer to TASK 253538-833-801 001

Replace Bracket No. 6.

and

Replace the bracket No. 7 at the threshold given in the PLANNING

INFORMATION paragraph E.(2), refer to TASK 253538-833-802 001

Replace Bracket No. 7.

and

Do a detailed inspection of the bracket No. 6 at the threshold given

in the PLANNING INFORMATION paragraph E.(2), refer to TASK

253538-832-801 001 Inspection.

or

b Replace the bracket No. 7 at the threshold given in the PLANNING

INFORMATION paragraph E.(2), refer to TASK 253538-833-802 001

Replace Bracket No. 7.

and

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 41

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A330

SERVICE BULLETIN

Implement Service Bulletin No. A330-25-3548 as terminative solution at

the threshold given in the PLANNING INFORMATION paragraph E.(2).

2 If a crack is found on the bracket No. 7.

a Contact AIRBUS before next flight.

(b) Send inspection report to Airbus, refer to Fig. A-FRAAA.

(3) Subtask 253538-410-003-001 - Install/Close Items Removed/Opened for access.

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

References

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

NOTE: If you intend to accomplish an associated Repair Task during the same

layover period, the subsequent Close-up procedure is not necessary.

(a) Install the cover assembly plate.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retained at

removal

1 Panel Item (4) Retained at

removal

(b) Install the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retained at

removal

3 Washer Item (2) Retained at

removal

1 Panel Item (3) Retained at

removal

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 42

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Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A330

SERVICE BULLETIN

**CONF 002

(1) Subtask 253538-700-001-001 - Do a Detailed Inspection of the Bracket No. 6.

Work Zones and Access Panels

Zone Access/Work location

212

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Service Bulletin (SB) A330-25-3548

Fig. A-FBAAA

Area to be inspected

Sheet 01

Sheet 02

Fig. A-FFAAA

Flow-chart

Sheet 01

Fig. A-FRAAA

Inspection Report

Sheet 01

At the threshold given in the PLANNING INFORMATION paragraph E.(2):

(a) Do a detailed inspection of the bracket No. 6.

Refer to Fig. A-FBAAA

Refer to Fig. A-FFAAA

1 If no crack is found:

a Do a detailed inspection of the bracket No. 6 at the interval given

in the PLANNING INFORMATION paragraph E.(2), refer to TASK

253538-832-801 001 Inspection.

or

b Implement Service Bulletin No. A330-25-3548 as terminative solution at

the threshold given in the PLANNING INFORMATION paragraph E.(2).

or

c Replace the bracket No. 6 at the threshold given in the PLANNING

INFORMATION paragraph E.(2), refer to TASK 253538-833-801 001

Replace Bracket No. 6.

and

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 43

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Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A330

SERVICE BULLETIN

Do a detailed inspection of the bracket No. 6 at the threshold given

in the PLANNING INFORMATION paragraph E.(2), refer to TASK

253538-832-801 001 Inspection.

2 If a crack is found and both bracket lugs are not fully broken:

a Replace the bracket No. 6 at the threshold given in the PLANNING

INFORMATION paragraph E.(2), refer to TASK 253538-833-801 001

Replace Bracket No. 6.

and

Do a detailed inspection of the bracket No. 6 at the threshold given

in the PLANNING INFORMATION paragraph E.(2), refer to TASK

253538-832-801 001 Inspection.

or

b Implement Service Bulletin No. A330-25-3548 as terminative solution at

the threshold given in the PLANNING INFORMATION paragraph E.(2).

3 If a crack is found and both bracket lugs are fully broken:

a Do a detailed inspection of the bracket No. 7.

Refer to SUBTASK 253538-700-004- 001

(b) Send inspection report to Airbus, refer to Fig. A-FRAAA.

(2) Subtask 253538-700-004-001 - Do a Detailed Inspection of the Bracket No. 7.

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills NON SPECIFIC

References

Service Bulletin (SB) A330-25-3548

Fig. A-FBAAA

Area to be inspected

Sheet 01

Sheet 02

Fig. A-FFAAA

Flow-chart

Sheet 01

Fig. A-FRAAA

Inspection Report

Sheet 01

At the threshold given in the PLANNING INFORMATION paragraph E.(2):

(a) Do a detailed inspection of the bracket No. 7.

Refer to Fig. A-FBAAA

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 44

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@A330

SERVICE BULLETIN

Refer to Fig. A-FFAAA

1 If no crack is found on the bracket No. 7.

a Replace the bracket No. 6 at the threshold given in the PLANNING

INFORMATION paragraph E.(2), refer to TASK 253538-833-801 001

Replace Bracket No. 6.

and

Replace the bracket No. 7 at the threshold given in the PLANNING

INFORMATION paragraph E.(2), refer to TASK 253538-833-802 001

Replace Bracket No. 7.

and

Do a detailed inspection of the bracket No. 6 at the threshold given

in the PLANNING INFORMATION paragraph E.(2), refer to TASK

253538-832-801 001 Inspection.

or

b Replace the bracket No. 7 at the threshold given in the PLANNING

INFORMATION paragraph E.(2), refer to TASK 253538-833-802 001

Replace Bracket No. 7.

and

Implement Service Bulletin No. A330-25-3548 as terminative solution at

the threshold given in the PLANNING INFORMATION paragraph E.(2).

2 If a crack is found on the bracket No. 7.

a Contact AIRBUS before next flight.

(b) Send inspection report to Airbus, refer to Fig. A-FRAAA.

(3) Subtask 253538-410-003-001 - Install/Close Items Removed/Opened for access.

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

References

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

NOTE: If you intend to accomplish an associated Repair Task during the same

layover period, the subsequent Close-up procedure is not necessary.

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 45

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A330

SERVICE BULLETIN

(a) Install the cover assembly plate.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retained at

removal

1 Panel Item (4) Retained at

removal

(b) Install the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retained at

removal

3 Washer Item (2) Retained at

removal

1 Panel Item (3) Retained at

removal

**CONF 003

(1) Subtask 253538-700-001-001 - Do a Detailed Inspection of the Bracket No. 6.

Work Zones and Access Panels

Zone Access/Work location

212

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Service Bulletin (SB) A330-25-3548

Fig. A-FBAAA

Area to be inspected

Sheet 01

Sheet 02

Fig. A-FFAAA

Flow-chart

Sheet 01

Fig. A-FRAAA

Inspection Report

Sheet 01

At the threshold given in the PLANNING INFORMATION paragraph E.(2):

(a) Do a detailed inspection of the bracket No. 6.

Refer to Fig. A-FBAAA

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 46

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Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A330

SERVICE BULLETIN

Refer to Fig. A-FFAAA

1 If no crack is found:

a Do a detailed inspection of the bracket No. 6 at the interval given

in the PLANNING INFORMATION paragraph E.(2), refer to TASK

253538-832-801 001 Inspection.

or

b Implement Service Bulletin No. A330-25-3548 as terminative solution at

the threshold given in the PLANNING INFORMATION paragraph E.(2).

or

c Replace the bracket No. 6 at the threshold given in the PLANNING

INFORMATION paragraph E.(2), refer to TASK 253538-833-801 001

Replace Bracket No. 6.

and

Do a detailed inspection of the bracket No. 6 at the threshold given

in the PLANNING INFORMATION paragraph E.(2), refer to TASK

253538-832-801 001 Inspection.

2 If a crack is found and both bracket lugs are not fully broken:

a Replace the bracket No. 6 at the threshold given in the PLANNING

INFORMATION paragraph E.(2), refer to TASK 253538-833-801 001

Replace Bracket No. 6.

and

Do a detailed inspection of the bracket No. 6 at the threshold given

in the PLANNING INFORMATION paragraph E.(2), refer to TASK

253538-832-801 001 Inspection.

or

b Implement Service Bulletin No. A330-25-3548 as terminative solution at

the threshold given in the PLANNING INFORMATION paragraph E.(2).

3 If a crack is found and both bracket lugs are fully broken:

a Do a detailed inspection of the bracket No. 7.

Refer to SUBTASK 253538-700-004- 001

(b) Send inspection report to Airbus, refer to Fig. A-FRAAA.

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 47

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@A330

SERVICE BULLETIN

(2) Subtask 253538-700-004-001 - Do a Detailed Inspection of the Bracket No. 7.

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills NON SPECIFIC

References

Service Bulletin (SB) A330-25-3548

Fig. A-FBAAA

Area to be inspected

Sheet 01

Sheet 02

Fig. A-FFAAA

Flow-chart

Sheet 01

Fig. A-FRAAA

Inspection Report

Sheet 01

At the threshold given in the PLANNING INFORMATION paragraph E.(2):

(a) Do a detailed inspection of the bracket No. 7.

Refer to Fig. A-FBAAA

Refer to Fig. A-FFAAA

1 If no crack is found on the bracket No. 7.

a Replace the bracket No. 6 at the threshold given in the PLANNING

INFORMATION paragraph E.(2), refer to TASK 253538-833-801 001

Replace Bracket No. 6.

and

Replace the bracket No. 7 at the threshold given in the PLANNING

INFORMATION paragraph E.(2), refer to TASK 253538-833-802 001

Replace Bracket No. 7.

and

Do a detailed inspection of the bracket No. 6 at the threshold given

in the PLANNING INFORMATION paragraph E.(2), refer to TASK

253538-832-801 001 Inspection.

or

b Replace the bracket No. 7 at the threshold given in the PLANNING

INFORMATION paragraph E.(2), refer to TASK 253538-833-802 001

Replace Bracket No. 7.

and

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 48

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A330

SERVICE BULLETIN

Implement Service Bulletin No. A330-25-3548 as terminative solution at

the threshold given in the PLANNING INFORMATION paragraph E.(2).

2 If a crack is found on the bracket No. 7.

a Contact AIRBUS before next flight.

(b) Send inspection report to Airbus, refer to Fig. A-FRAAA.

(3) Subtask 253538-410-003-001 - Install/Close Items Removed/Opened for access.

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

References

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

NOTE: If you intend to accomplish an associated Repair Task during the same

layover period, the subsequent Close-up procedure is not necessary.

(a) Install the cover assembly plate.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retained at

removal

1 Panel Item (4) Retained at

removal

(b) Install the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retained at

removal

3 Washer Item (2) Retained at

removal

1 Panel Item (3) Retained at

removal

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 49

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A330

SERVICE BULLETIN

**CONF 004

(1) Subtask 253538-700-001-001 - Do a Detailed Inspection of the Bracket No. 6.

Work Zones and Access Panels

Zone Access/Work location

212

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Service Bulletin (SB) A330-25-3548

Fig. A-FBAAA

Area to be inspected

Sheet 01

Sheet 02

Fig. A-FFAAA

Flow-chart

Sheet 01

Fig. A-FRAAA

Inspection Report

Sheet 01

At the threshold given in the PLANNING INFORMATION paragraph E.(2):

(a) Do a detailed inspection of the bracket No. 6.

Refer to Fig. A-FBAAA

Refer to Fig. A-FFAAA

1 If no crack is found:

a Do a detailed inspection of the bracket No. 6 at the interval given

in the PLANNING INFORMATION paragraph E.(2), refer to TASK

253538-832-801 001 Inspection.

or

b Implement Service Bulletin No. A330-25-3548 as terminative solution at

the threshold given in the PLANNING INFORMATION paragraph E.(2).

or

c Replace the bracket No. 6 at the threshold given in the PLANNING

INFORMATION paragraph E.(2), refer to TASK 253538-833-801 001

Replace Bracket No. 6.

and

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

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Do a detailed inspection of the bracket No. 6 at the threshold given

in the PLANNING INFORMATION paragraph E.(2), refer to TASK

253538-832-801 001 Inspection.

2 If a crack is found and both bracket lugs are not fully broken:

a Replace the bracket No. 6 at the threshold given in the PLANNING

INFORMATION paragraph E.(2), refer to TASK 253538-833-801 001

Replace Bracket No. 6.

and

Do a detailed inspection of the bracket No. 6 at the threshold given

in the PLANNING INFORMATION paragraph E.(2), refer to TASK

253538-832-801 001 Inspection.

or

b Implement Service Bulletin No. A330-25-3548 as terminative solution at

the threshold given in the PLANNING INFORMATION paragraph E.(2).

3 If a crack is found and both bracket lugs are fully broken:

a Do a detailed inspection of the bracket No. 7.

Refer to SUBTASK 253538-700-004- 001

(b) Send inspection report to Airbus, refer to Fig. A-FRAAA.

(2) Subtask 253538-700-004-001 - Do a Detailed Inspection of the Bracket No. 7.

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills NON SPECIFIC

References

Service Bulletin (SB) A330-25-3548

Fig. A-FBAAA

Area to be inspected

Sheet 01

Sheet 02

Fig. A-FFAAA

Flow-chart

Sheet 01

Fig. A-FRAAA

Inspection Report

Sheet 01

At the threshold given in the PLANNING INFORMATION paragraph E.(2):

(a) Do a detailed inspection of the bracket No. 7.

Refer to Fig. A-FBAAA

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Refer to Fig. A-FFAAA

1 If no crack is found on the bracket No. 7.

a Replace the bracket No. 6 at the threshold given in the PLANNING

INFORMATION paragraph E.(2), refer to TASK 253538-833-801 001

Replace Bracket No. 6.

and

Replace the bracket No. 7 at the threshold given in the PLANNING

INFORMATION paragraph E.(2), refer to TASK 253538-833-802 001

Replace Bracket No. 7.

and

Do a detailed inspection of the bracket No. 6 at the threshold given

in the PLANNING INFORMATION paragraph E.(2), refer to TASK

253538-832-801 001 Inspection.

or

b Replace the bracket No. 7 at the threshold given in the PLANNING

INFORMATION paragraph E.(2), refer to TASK 253538-833-802 001

Replace Bracket No. 7.

and

Implement Service Bulletin No. A330-25-3548 as terminative solution at

the threshold given in the PLANNING INFORMATION paragraph E.(2).

2 If a crack is found on the bracket No. 7.

a Contact AIRBUS before next flight.

(b) Send inspection report to Airbus, refer to Fig. A-FRAAA.

(3) Subtask 253538-410-003-001 - Install/Close Items Removed/Opened for access.

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

References

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

NOTE: If you intend to accomplish an associated Repair Task during the same

layover period, the subsequent Close-up procedure is not necessary.

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

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(a) Install the cover assembly plate.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retained at

removal

1 Panel Item (4) Retained at

removal

(b) Install the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retained at

removal

3 Washer Item (2) Retained at

removal

1 Panel Item (3) Retained at

removal

**CONF ALL

D. TEST

**CONF 001

None

**CONF 002

None

**CONF 003

None

**CONF 004

None

**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 253538-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

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NOTE: If you intend to accomplish an associated Repair Task during the same

layover period, the subsequent Close-up procedure is not necessary.

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

(b) Restore the systems and the aircraft to normal operation conditions.

**CONF 002

(1) Subtask 253538-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

NOTE: If you intend to accomplish an associated Repair Task during the same

layover period, the subsequent Close-up procedure is not necessary.

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

(b) Restore the systems and the aircraft to normal operation conditions.

**CONF 003

(1) Subtask 253538-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

NOTE: If you intend to accomplish an associated Repair Task during the same

layover period, the subsequent Close-up procedure is not necessary.

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

(b) Restore the systems and the aircraft to normal operation conditions.

**CONF 004

(1) Subtask 253538-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

NOTE: If you intend to accomplish an associated Repair Task during the same

layover period, the subsequent Close-up procedure is not necessary.

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

(b) Restore the systems and the aircraft to normal operation conditions.

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

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Task 253538-833-801-001 - Replace Bracket No. 6.

**CONF ALL

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

INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

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

THIS:

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

NECESSARY ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00.

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.

NOTE: This Service Bulletin is classified mandatory or expected to be classified mandatory

by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these

accomplishment instructions are Required for Compliance (RC) and must be done

to comply with the AD. Other paragraphs are recommended and may be deviated

from, done as part of other actions or done with accepted methods different from

those given in the Service Bulletin, as long as the RC paragraphs can be done and

the aircraft can be put back into a serviceable condition.

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

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Task Associated Data

**CONF 001

Zone

212

Manpower

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

**CONF 002

Zone

212

Manpower

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

**CONF 003

Zone

212

Manpower

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

**CONF 004

Zone

212

Manpower

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 253538-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

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

06-41-52, Page Block 001

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References

Structural Repair Manual (SRM) 51-24-00

51-42-00

51-43-00

51-44-00

51-75-12

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

Consumable Materials (CML).

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

(c) For the identification of access panels, refer to AMM 06-41-52, Page Block 001.

(d) Remove and install fasteners in accordance with SRM 51-42-00.

(e) Obtain alternative and substitute fastener data, in accordance with SRM 51-43-00.

(f) Obtain fasteners hole diameters and drill and "deburr" data in accordance with

SRM 51-44-00.

(g) Cut the rivets to the necessary length.

(h) Renew the protective finish in accordance with SRM 51-75-12.

(i) Apply sealant in accordance with SRM 51-24-00.

(2) Subtask 253538-839-002-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

**CONF 002

(1) Subtask 253538-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

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

06-41-52, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-42-00

51-43-00

51-44-00

51-75-12

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

Consumable Materials (CML).

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

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

(c) For the identification of access panels, refer to AMM 06-41-52, Page Block 001.

(d) Remove and install fasteners in accordance with SRM 51-42-00.

(e) Obtain alternative and substitute fastener data, in accordance with SRM 51-43-00.

(f) Obtain fasteners hole diameters and drill and "deburr" data in accordance with

SRM 51-44-00.

(g) Cut the rivets to the necessary length.

(h) Renew the protective finish in accordance with SRM 51-75-12.

(i) Apply sealant in accordance with SRM 51-24-00.

(2) Subtask 253538-839-002-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

**CONF 003

(1) Subtask 253538-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

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

06-41-52, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-42-00

51-43-00

51-44-00

51-75-12

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

Consumable Materials (CML).

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

(c) For the identification of access panels, refer to AMM 06-41-52, Page Block 001.

(d) Remove and install fasteners in accordance with SRM 51-42-00.

(e) Obtain alternative and substitute fastener data, in accordance with SRM 51-43-00.

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

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(f) Obtain fasteners hole diameters and drill and "deburr" data in accordance with

SRM 51-44-00.

(g) Cut the rivets to the necessary length.

(h) Renew the protective finish in accordance with SRM 51-75-12.

(i) Apply sealant in accordance with SRM 51-24-00.

(2) Subtask 253538-839-002-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

**CONF 004

(1) Subtask 253538-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

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

06-41-52, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-42-00

51-43-00

51-44-00

51-75-12

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

Consumable Materials (CML).

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

(c) For the identification of access panels, refer to AMM 06-41-52, Page Block 001.

(d) Remove and install fasteners in accordance with SRM 51-42-00.

(e) Obtain alternative and substitute fastener data, in accordance with SRM 51-43-00.

(f) Obtain fasteners hole diameters and drill and "deburr" data in accordance with

SRM 51-44-00.

(g) Cut the rivets to the necessary length.

(h) Renew the protective finish in accordance with SRM 51-75-12.

(i) Apply sealant in accordance with SRM 51-24-00.

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

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SERVICE BULLETIN

(2) Subtask 253538-839-002-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

**CONF ALL

B. PREPARATION

**CONF 001

(1) Subtask 253538-941-002-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

Task 25-11-51-000-801

Task 31-63-22-000-801

Task 33-12-13-000-801

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

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

12-34-24-860-802.

(c) If necessary, remove the First Officer Seat (FIN 4MS), refer to AMM Task

25-11-51-000-801.

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(d) Do the Job Set-up procedure as specified in the removal of the Display Unit (DU)

(FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.

(e) In the cockpit, on the panel 235VU, make sure that these pushbutton switches are

released:

- BAT 1, BAT 2, APU BAT,

- GEN 1, (2), APU GEN,

- EXT A (B).

(f) If necessary, remove the Light Unit (LU) (FIN 14LE), refer to AMM Task

33-12-13-000-801.

(g) Open, safety/lock and tag these circuit breakers:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742 701PP 10PB1 72 S

742 702PP 10PB2 71 S

(h) Make sure that there are warning notices in the cockpit to tell persons not to

operate the pushbutton switches on the overhead panels:

- 211VU (EMER ELEC PWR)

- 235VU (ELEC)

(i) Make sure that there are warning notices in the cockpit to tell persons not to start

the APU.

(j) Make sure that the external connectors are not connected to the aircraft

receptacles EXT PWR A (B).

(k) Make sure that there is a warning notice at the access door 121EL to tell persons

not to connect the external power connectors.

(2) Subtask 253538-010-002-001 - Remove/Open for Access

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 31-63-22-000-801

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

NOTE: If you intend to accomplish this Repair Task during the same layover

period as the associated Inspection, the subsequent Preparation

procedure is not necessary.

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(a) Remove the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retain

3 Washer Item (2) Retain

1 Panel Item (3) Retain

(b) Remove the cover assembly panel.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retain

1 Panel Item (4) Retain

(c) Remove the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.

**CONF 002

(1) Subtask 253538-941-002-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

Task 25-11-51-000-801

Task 31-63-22-000-801

Task 33-12-13-000-801

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

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- All controls in NORM, AUTO or OFF position.

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

12-34-24-860-802.

(c) If necessary, remove the First Officer Seat (FIN 4MS), refer to AMM Task

25-11-51-000-801.

(d) Do the Job Set-up procedure as specified in the removal of the Display Unit (DU)

(FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.

(e) In the cockpit, on the panel 235VU, make sure that these pushbutton switches are

released:

- BAT 1, BAT 2, APU BAT,

- GEN 1, (2), APU GEN,

- EXT A (B).

(f) If necessary, remove the Light Unit (LU) (FIN 14LE), refer to AMM Task

33-12-13-000-801.

(g) Open, safety/lock and tag these circuit breakers:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742 701PP 10PB1 72 S

742 702PP 10PB2 71 S

(h) Make sure that there are warning notices in the cockpit to tell persons not to

operate the pushbutton switches on the overhead panels:

- 211VU (EMER ELEC PWR)

- 235VU (ELEC)

(i) Make sure that there are warning notices in the cockpit to tell persons not to start

the APU.

(j) Make sure that the external connectors are not connected to the aircraft

receptacles EXT PWR A (B).

(k) Make sure that there is a warning notice at the access door 121EL to tell persons

not to connect the external power connectors.

(2) Subtask 253538-010-002-001 - Remove/Open for Access

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 31-63-22-000-801

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References

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

NOTE: If you intend to accomplish this Repair Task during the same layover

period as the associated Inspection, the subsequent Preparation

procedure is not necessary.

(a) Remove the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retain

3 Washer Item (2) Retain

1 Panel Item (3) Retain

(b) Remove the cover assembly panel.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retain

1 Panel Item (4) Retain

(c) Remove the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.

**CONF 003

(1) Subtask 253538-941-002-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

Task 25-11-51-000-801

Task 31-63-22-000-801

Task 33-12-13-000-801

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

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- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

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

12-34-24-860-802.

(c) If necessary, remove the First Officer Seat (FIN 4MS), refer to AMM Task

25-11-51-000-801.

(d) Do the Job Set-up procedure as specified in the removal of the Display Unit (DU)

(FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.

(e) In the cockpit, on the panel 235VU, make sure that these pushbutton switches are

released:

- BAT 1, BAT 2, APU BAT,

- GEN 1, (2), APU GEN,

- EXT A (B).

(f) If necessary, remove the Light Unit (LU) (FIN 14LE), refer to AMM Task

33-12-13-000-801.

(g) Open, safety/lock and tag these circuit breakers:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742 701PP 10PB1 72 S

742 702PP 10PB2 71 S

(h) Make sure that there are warning notices in the cockpit to tell persons not to

operate the pushbutton switches on the overhead panels:

- 211VU (EMER ELEC PWR)

- 235VU (ELEC)

(i) Make sure that there are warning notices in the cockpit to tell persons not to start

the APU.

(j) Make sure that the external connectors are not connected to the aircraft

receptacles EXT PWR A (B).

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 65

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(k) Make sure that there is a warning notice at the access door 121EL to tell persons

not to connect the external power connectors.

(2) Subtask 253538-010-002-001 - Remove/Open for Access

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 31-63-22-000-801

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

NOTE: If you intend to accomplish this Repair Task during the same layover

period as the associated Inspection, the subsequent Preparation

procedure is not necessary.

(a) Remove the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retain

3 Washer Item (2) Retain

1 Panel Item (3) Retain

(b) Remove the cover assembly panel.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retain

1 Panel Item (4) Retain

(c) Remove the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.

**CONF 004

(1) Subtask 253538-941-002-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

Task 25-11-51-000-801

Task 31-63-22-000-801

Task 33-12-13-000-801

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 66

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SERVICE BULLETIN

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

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

12-34-24-860-802.

(c) If necessary, remove the First Officer Seat (FIN 4MS), refer to AMM Task

25-11-51-000-801.

(d) Do the Job Set-up procedure as specified in the removal of the Display Unit (DU)

(FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.

(e) In the cockpit, on the panel 235VU, make sure that these pushbutton switches are

released:

- BAT 1, BAT 2, APU BAT,

- GEN 1, (2), APU GEN,

- EXT A (B).

(f) If necessary, remove the Light Unit (LU) (FIN 14LE), refer to AMM Task

33-12-13-000-801.

(g) Open, safety/lock and tag these circuit breakers:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742 701PP 10PB1 72 S

742 702PP 10PB2 71 S

(h) Make sure that there are warning notices in the cockpit to tell persons not to

operate the pushbutton switches on the overhead panels:

- 211VU (EMER ELEC PWR)

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 67

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SERVICE BULLETIN

- 235VU (ELEC)

(i) Make sure that there are warning notices in the cockpit to tell persons not to start

the APU.

(j) Make sure that the external connectors are not connected to the aircraft

receptacles EXT PWR A (B).

(k) Make sure that there is a warning notice at the access door 121EL to tell persons

not to connect the external power connectors.

(2) Subtask 253538-010-002-001 - Remove/Open for Access

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 31-63-22-000-801

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

NOTE: If you intend to accomplish this Repair Task during the same layover

period as the associated Inspection, the subsequent Preparation

procedure is not necessary.

(a) Remove the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retain

3 Washer Item (2) Retain

1 Panel Item (3) Retain

(b) Remove the cover assembly panel.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retain

1 Panel Item (4) Retain

(c) Remove the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 68

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SERVICE BULLETIN

**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 253538-833-001-001 - Replace the Bracket No. 6.

Work Zones and Access Panels

Zone Access/Work location

212

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

16 F2511012820095 1 BRACKET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Component COMPA03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

7 NAS6604-10 1 BOLT

8 NAS1726-4E 1 NUT

11 ASNA2050DCJ3215 3 RIVET

15 ASNA2050DEJ4020 4 RIVET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Synthetic Ester Base

Grease-General Purpose

Low T

03HBD9 As required

References

Structural Repair Manual (SRM) 51-42-00

51-44-00

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 69

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References

Fig. A-FBBAA

Replacement of the bracket No. 6

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Remove the bracket No. 6.

Refer to Fig. A-FBBAA

In accordance with SRM 51-42-00.

1 Remove:

1 Screw Item (7) Discard

1 Nut Item (8) Discard

2 Remove the rivets:

- Remove the head of the four rivets.

- Drill four holes through the cockpit main panel to remove the four rivets

and obtain a diameter comprised between 4.07 and 4.16 mm (0.160 and

0.164 in).

2 Rivet Item (15) Discard

2 Rivet Item (14) Discard

3 Remove the bracket:

1 Bracket F2511012820000 Item (16) Discard

(b) Install the new bracket.

Refer to Fig. A-FBBAA

In accordance with SRM 51-42-00 and SRM 51-44-00.

1 Temporarily put the bracket item 16 on the RH side of the upper bracket.

a If necessary, remove:

3 Rivets Item (11) Discard

b Mark the position of the hole of the upper bracket on the new bracket.

c If removed, install:

3 Rivet ASNA2050DCJ3215 Item 11

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 70

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SERVICE BULLETIN

2 On bench, drill the marked hole to a diameter comprised between 6.5 and 6.7

mm (0.256 and 0.264 in).

3 Put in position the new bracket item 16 with the bolt item 7.

Install:

1 Bracket F2511012820095 Item 16

1 Bolt NAS6604-10 Item 7

NOTE: Install the bolt item 7 with:

Synthetic Ester

Base GreaseGeneral Purpose

Low T

03HBD9 As required

4 Measure the clearance between the new bracket item 16 and the upper

bracket as show in Fig. A-FBBAA Sheet 04

a Check that the minimum clearances are 0.35 mm (0.014 in) at LHS and

0.65 (0.026 in) mm at RHS.

5 Drill the four holes in the bracket item 16 to align with the holes of the

structure.

6 Install:

4 Rivet ASNA2050DEJ4020 Item 15

7 Install the nut item 8:

1 Nut NAS1726-4E Item 8

NOTE: Torque the nut item 8 to a torque value between 0.28 and 0.37

mdaN (24.782 and 32.748lbf.in).

(2) Subtask 253538-410-002-001 - Install/Close Items Removed/Opened for access.

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 31-63-22-400-801

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

NOTE: If you intend to accomplish an associated Repair Task during the same

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 71

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SERVICE BULLETIN

layover period, the subsequent Close-up procedure is not necessary.

(a) Install the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-400-801.

(b) Install the cover assembly plate.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retained at

removal

1 Panel Item (4) Retained at

removal

(c) Install the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retained at

removal

3 Washer Item (2) Retained at

removal

1 Panel Item (3) Retained at

removal

**CONF 002

(1) Subtask 253538-833-001-002 - Replace the Bracket No. 6.

Work Zones and Access Panels

Zone Access/Work location

212

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

16 F2511012820095 1 BRACKET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 72

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SERVICE BULLETIN

Component COMPA04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

11 ASNA2050DCJ3215 3 RIVET

15 ASNA2050DEJ4020 4 RIVET

17 NSA5042-04-160 1 BOLT

18 NSA5060-3 1 NUT

19 NSA5325-3 1 WASHER

20 MS24665-134 1 PIN

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Synthetic Ester Base

Grease-General Purpose

Low T

03HBD9 As required

References

Structural Repair Manual (SRM) 51-42-00

51-44-00

Fig. A-FBBAC

Replacement of the bracket No. 6

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Remove the bracket No. 6.

Refer to Fig. A-FBBAC

In accordance with SRM 51-42-00.

1 Remove:

1 Axis Item (17) Discard

1 Nut Item (18) Discard

1 Washer Item (19) Discard

1 Pin Item (20) Discard

2 Remove the rivets:

- Remove the head of the four rivets.

- Drill four holes through the cockpit main panel to remove the four rivets

and obtain a diameter comprised between 4.07 and 4.16 mm (0.160 and

0.164 in).

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 73

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SERVICE BULLETIN

2 Rivet Item (15) Discard

2 Rivet Item (14) Discard

3 Remove the bracket:

1 Bracket F2511012820000 Item (16) Discard

(b) Install the new bracket.

Refer to Fig. A-FBBAC

In accordance with SRM 51-42-00 and SRM 51-44-00.

1 Temporarily put the bracket item 16 on the RH side of the upper bracket.

a If necessary, remove:

3 Rivets Item (11) Discard

b Mark the position of the hole of the upper bracket on the new bracket.

c If removed, install:

3 Rivet ASNA2050DCJ3215 Item 11

2 On bench, drill the marked hole to a diameter comprised between 6.5 and 6.7

mm (0.256 and 0.264 in).

3 Put in position the new bracket item 16 with the bolt item 17.

1 Bracket F2511012820095 Item 16

1 Bolt NSA5042-04-160 Item 17

NOTE: Install the bolt item 17 with:

Synthetic Ester

Base GreaseGeneral Purpose

Low T

03HBD9 As required

4 Measure the clearance between the new bracket item 16 and the upper

bracket as show in Fig. A-FBBAC Sheet 04

a Check that the minimum clearances are 0.35 (0.014 in) mm at LHS and

0.65 mm (0.026 in) at RHS.

5 Drill the four holes in the bracket item 16 to align with the holes of the

structure.

6 Install:

4 Rivet ASNA2050DEJ4020 Item 15

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 74

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7 Install the nut item 18:

1 Nut NSA5060-3 Item 18

1 Washer NSA5325-3 Item 19

1 Pin-Cotter MS24665-134 Item 20

NOTE: Torque the nut item 18 to a torque value between 0.28 and

0.37 mdaN (24.782 and 32.748 lbf.in).

(2) Subtask 253538-410-002-001 - Install/Close Items Removed/Opened for access.

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 31-63-22-400-801

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

NOTE: If you intend to accomplish an associated Repair Task during the same

layover period, the subsequent Close-up procedure is not necessary.

(a) Install the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-400-801.

(b) Install the cover assembly plate.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retained at

removal

1 Panel Item (4) Retained at

removal

(c) Install the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retained at

removal

3 Washer Item (2) Retained at

removal

1 Panel Item (3) Retained at

removal

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 75

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SERVICE BULLETIN

**CONF 003

(1) Subtask 253538-833-001-003 - Replace the Bracket No. 6.

Work Zones and Access Panels

Zone Access/Work location

212

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

16 F2511012820095 1 BRACKET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Component COMPA05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

11 ASNA2050DCJ3215 3 RIVET

15 ASNA2050DEJ4020 4 RIVET

17 NSA5042-04-160 1 BOLT

18 NSA5060-3 1 NUT

19 NSA5325-3 1 WASHER

21 MS24665-71 1 PIN

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Synthetic Ester Base

Grease-General Purpose

Low T

03HBD9 As required

References

Structural Repair Manual (SRM) 51-42-00

51-44-00

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 76

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SERVICE BULLETIN

References

Fig. A-FBBAD

Replacement of the bracket No. 6

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Remove the bracket No. 6.

Refer to Fig. A-FBBAD

In accordance with SRM 51-42-00.

1 Remove:

1 Axis Item (17) Discard

1 Nut Item (18) Discard

1 Washer Item (19) Discard

1 Pin Item (21) Discard

2 Remove the rivets:

- Remove the head of the four rivets.

- Drill four holes through the cockpit main panel to remove the four rivets

and obtain a diameter comprised between 4.07 and 4.16 mm (0.160 and

0.164 in).

2 Rivet Item (15) Discard

2 Rivet Item (14) Discard

3 Remove the bracket:

1 Bracket F2511012820000 Item (16) Discard

(b) Install the new bracket.

Refer to Fig. A-FBBAD

In accordance with SRM 51-42-00 and SRM 51-44-00.

1 Temporarily put the bracket item 16 on the RH side of the upper bracket.

a If necessary, remove:

3 Rivets Item (11) Discard

b Mark the position of the hole of the upper bracket on the new bracket.

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 77

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SERVICE BULLETIN

c If removed, install:

3 Rivet ASNA2050DCJ3215 Item 11

2 On bench, drill the marked hole to a diameter comprised between 6.5 and 6.7

mm (0.256 and 0.264 in).

3 Put in position the new bracket item 16 with the bolt item 17.

Install:

1 Bracket F2511012820095 Item 16

1 Bolt NSA5042-04-160 Item 17

NOTE: Install the bolt item 17 with:

Synthetic Ester

Base GreaseGeneral Purpose

Low T

03HBD9 As required

4 Measure the clearance between the new bracket item 16 and the upper

bracket as show in Fig. A-FBBAD Sheet 04

a Check that the minimum clearances are 0.35 mm (0.014 in) at LHS and

0.65 mm (0.026 in) at RHS.

5 Drill the four holes in the bracket item 16 to align with the holes of the

structure.

6 Install:

4 Rivet ASNA2050DEJ4020 Item 15

7 Install the nut item 18:

1 Nut NSA5060-3 Item 18

1 Washer NSA5325-3 Item 19

1 Pin-Cotter MS24665-71 Item 21

NOTE: Torque the nut item 18 to a torque value between 0.28 and

0.37 mdaN (24.782 and 32.748 lbf.in).

(2) Subtask 253538-410-002-001 - Install/Close Items Removed/Opened for access.

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 78

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SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 31-63-22-400-801

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

NOTE: If you intend to accomplish an associated Repair Task during the same

layover period, the subsequent Close-up procedure is not necessary.

(a) Install the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-400-801.

(b) Install the cover assembly plate.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retained at

removal

1 Panel Item (4) Retained at

removal

(c) Install the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retained at

removal

3 Washer Item (2) Retained at

removal

1 Panel Item (3) Retained at

removal

**CONF 004

(1) Subtask 253538-833-001-004 - Replace the Bracket No. 6.

Work Zones and Access Panels

Zone Access/Work location

212

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 79

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SERVICE BULLETIN

Material necessary to do the job

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

6 F2511373420095 1 BRACKET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Component COMPA06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 EN6115V3-5 4 BOLT

10 ASNA2531-3 4 NUT

11 ASNA2050DCJ3215 3 RIVET

17 NSA5042-04-160 1 BOLT

18 NSA5060-3 1 NUT

19 NSA5325-3 1 WASHER

21 MS24665-71 1 PIN

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Synthetic Ester Base

Grease-General Purpose

Low T

03HBD9 As required

References

Structural Repair Manual (SRM) 51-42-00

51-44-00

Fig. A-FBBAB

Replacement of the bracket No. 6

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Remove the bracket No. 6.

Refer to Fig. A-FBBAB

In accordance with SRM 51-42-00.

1 Remove:

1 Axis Item (17) Discard

1 Nut Item (18) Discard

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 80

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SERVICE BULLETIN

1 Washer Item (19) Discard

1 Pin Item (21) Discard

2 Remove the fasteners:

4 Bolt Item (9) Discard

4 Nut Item (10) Discard

3 Remove the bracket:

1 Bracket F2511373420000 Item (6) Discard

(b) Install the new bracket.

Refer to Fig. A-FBBAB

In accordance with SRM 51-42-00 and SRM 51-44-00.

1 Temporarily put the bracket item 6 on the RH side of the upper bracket.

a If necessary, remove:

3 Rivets Item (11) Discard

b Mark the position of the hole of the upper bracket on the new bracket.

c If removed, install:

3 Rivet ASNA2050DCJ3215 Item 11

2 On bench, drill the marked hole to a diameter comprised between 6.5 and 6.7

mm (0.256 and 0.264 in).

3 Put in position the new bracket item 6 with the bolt item 17.

1 Bracket F2511373420095 Item 6

1 Bolt NSA5042-04-160 Item 17

NOTE: Install the bolt item 17 with:

Synthetic Ester

Base GreaseGeneral Purpose

Low T

03HBD9 As required

4 Measure the clearance between the new bracket item 6 and the upper bracket

as show in Fig. A-FBBAB Sheet 04

a Check that the minimum clearances are 0.35 mm (0.014 in) at LHS and

0.65 mm (0.026 in) at RHS.

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 81

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SERVICE BULLETIN

5 Drill the four holes in the bracket item 6 to align with the holes of the structure.

6 Install:

4 Nut ASNA2531-3 Item 10

4 Bolt EN6115V3-5 Item 9

7 Install the nut item 18:

1 Nut NSA5060-3 Item 18

1 Washer NSA5325-3 Item 19

1 Pin-Cotter MS24665-71 Item 21

NOTE: Torque the nut item 18 to a torque value between 0.28 and

0.37 mdaN (24.782 and 32.748 lbf.in).

(2) Subtask 253538-410-002-001 - Install/Close Items Removed/Opened for access.

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 31-63-22-400-801

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

NOTE: If you intend to accomplish an associated Repair Task during the same

layover period, the subsequent Close-up procedure is not necessary.

(a) Install the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-400-801.

(b) Install the cover assembly plate.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retained at

removal

1 Panel Item (4) Retained at

removal

(c) Install the protection plate.

Refer to Fig. A-FBCAA Sheet 01

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 82

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SERVICE BULLETIN

3 Stud Item (1) Retained at

removal

3 Washer Item (2) Retained at

removal

1 Panel Item (3) Retained at

removal

**CONF ALL

D. TEST

**CONF 001

(1) Subtask 253538-700-003-001 - Test

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-26-00-710-803

Task 22-96-00-740-801

Task 22-97-00-740-801

Task 24-41-00-861-801

Task 25-11-51-400-801

Task 31-50-00-710-803

Task 31-50-00-740-801

Task 31-60-00-710-802

Task 31-63-22-200-802

Task 33-12-13-400-801

Task 33-13-00-710-801

Task 33-14-00-710-801

Elec. Std. Practices Manual (ESPM) 20-52-20

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

equipment removed for access, refer to SUBTASK 253538-410-002 001

Install/Close Items Removed/Opened for access.

(a) In the cockpit, on the panel 235VU, push these pushbutton switches:

- BAT 1, BAT 2, APU BAT,

- GEN 1, (2), APU GEN,

- EXT A (B).

(b) Remove the warning notices.

(c) Energize the aircraft electrical circuits, refer to AMM Task 24-41-00-861-801.

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 83

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(d) Remove the safety clips and/or tags and close/unlock these circuit breakers:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742 701PP 10PB1 72 S

742 702PP 10PB2 71 S

(e) Preliminary test:

NOTE: If the aircraft is operated in actual CAT III conditions, you must

also do the LAND CAT III capability test, refer to AMM Task

22-97-00-740-801.

1 On each connector which was disconnected:

- Do the checks as defined by ESPM 20-52-20.

NOTE: The functional test and/or operational test (OT) requested by

this ESPM procedure is given hereafter.

2 Do the OT of the instrument and Panel Integral Lighting, refer to AMM Task

33-13-00-710-801.

3 Do the OT of Lights, refer to AMM Task 33-14-00-710-801.

4 Do the OT of the Avionics-Equipment Ventilation System, refer to AMM Task

21-26-00-710-803.

5 Do the OT of the Auto Flight System (SYSTEM TEST), refer to AMM Task

22-96-00-740-801.

6 Do the OT of the ECAM Control Panel, refer to AMM Task 31-50-00-710-803.

7 Do the test of the FWS, AMM Task 31-50-00-740-801.

8 Do the OT of the EIS, refer to AMM Task 31-60-00-710-802.

(f) Do the test procedure as specified after the installation of the DU (FINs 1WK2 and

3WK2), refer to AMM Task 31-63-22-200-802.

(g) If removed, do the test procedure as specified after the installation of the First

Officer Seat (FIN 4MS), refer to AMM Task 25-11-51-400-801.

(h) If removed, do the test procedure as specified after the installation of the LU (FIN

14LE), refer to AMM Task 33-12-13-400-801.

**CONF 002

(1) Subtask 253538-700-003-001 - Test

Manpower Resources

Skills NON SPECIFIC

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References

Aircraft Maintenance Manual (AMM) Task 21-26-00-710-803

Task 22-96-00-740-801

Task 22-97-00-740-801

Task 24-41-00-861-801

Task 25-11-51-400-801

Task 31-50-00-710-803

Task 31-50-00-740-801

Task 31-60-00-710-802

Task 31-63-22-200-802

Task 33-12-13-400-801

Task 33-13-00-710-801

Task 33-14-00-710-801

Elec. Std. Practices Manual (ESPM) 20-52-20

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

equipment removed for access, refer to SUBTASK 253538-410-002 001

Install/Close Items Removed/Opened for access.

(a) In the cockpit, on the panel 235VU, push these pushbutton switches:

- BAT 1, BAT 2, APU BAT,

- GEN 1, (2), APU GEN,

- EXT A (B).

(b) Remove the warning notices.

(c) Energize the aircraft electrical circuits, refer to AMM Task 24-41-00-861-801.

(d) Remove the safety clips and/or tags and close/unlock these circuit breakers:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742 701PP 10PB1 72 S

742 702PP 10PB2 71 S

(e) Preliminary test:

NOTE: If the aircraft is operated in actual CAT III conditions, you must

also do the LAND CAT III capability test, refer to AMM Task

22-97-00-740-801.

1 On each connector which was disconnected:

- Do the checks as defined by ESPM 20-52-20.

NOTE: The functional test and/or operational test (OT) requested by

this ESPM procedure is given hereafter.

2 Do the OT of the instrument and Panel Integral Lighting, refer to AMM Task

33-13-00-710-801.

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3 Do the OT of Lights, refer to AMM Task 33-14-00-710-801.

4 Do the OT of the Avionics-Equipment Ventilation System, refer to AMM Task

21-26-00-710-803.

5 Do the OT of the Auto Flight System (SYSTEM TEST), refer to AMM Task

22-96-00-740-801.

6 Do the OT of the ECAM Control Panel, refer to AMM Task 31-50-00-710-803.

7 Do the test of the FWS, AMM Task 31-50-00-740-801.

8 Do the OT of the EIS, refer to AMM Task 31-60-00-710-802.

(f) Do the test procedure as specified after the installation of the DU (FINs 1WK2 and

3WK2), refer to AMM Task 31-63-22-200-802.

(g) If removed, do the test procedure as specified after the installation of the First

Officer Seat (FIN 4MS), refer to AMM Task 25-11-51-400-801.

(h) If removed, do the test procedure as specified after the installation of the LU (FIN

14LE), refer to AMM Task 33-12-13-400-801.

**CONF 003

(1) Subtask 253538-700-003-001 - Test

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-26-00-710-803

Task 22-96-00-740-801

Task 22-97-00-740-801

Task 24-41-00-861-801

Task 25-11-51-400-801

Task 31-50-00-710-803

Task 31-50-00-740-801

Task 31-60-00-710-802

Task 31-63-22-200-802

Task 33-12-13-400-801

Task 33-13-00-710-801

Task 33-14-00-710-801

Elec. Std. Practices Manual (ESPM) 20-52-20

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

equipment removed for access, refer to SUBTASK 253538-410-002 001

Install/Close Items Removed/Opened for access.

(a) In the cockpit, on the panel 235VU, push these pushbutton switches:

- BAT 1, BAT 2, APU BAT,

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- GEN 1, (2), APU GEN,

- EXT A (B).

(b) Remove the warning notices.

(c) Energize the aircraft electrical circuits, refer to AMM Task 24-41-00-861-801.

(d) Remove the safety clips and/or tags and close/unlock these circuit breakers:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742 701PP 10PB1 72 S

742 702PP 10PB2 71 S

(e) Preliminary test:

NOTE: If the aircraft is operated in actual CAT III conditions, you must

also do the LAND CAT III capability test, refer to AMM Task

22-97-00-740-801.

1 On each connector which was disconnected:

- Do the checks as defined by ESPM 20-52-20.

NOTE: The functional test and/or operational test (OT) requested by

this ESPM procedure is given hereafter.

2 Do the OT of the instrument and Panel Integral Lighting, refer to AMM Task

33-13-00-710-801.

3 Do the OT of Lights, refer to AMM Task 33-14-00-710-801.

4 Do the OT of the Avionics-Equipment Ventilation System, refer to AMM Task

21-26-00-710-803.

5 Do the OT of the Auto Flight System (SYSTEM TEST), refer to AMM Task

22-96-00-740-801.

6 Do the OT of the ECAM Control Panel, refer to AMM Task 31-50-00-710-803.

7 Do the test of the FWS, AMM Task 31-50-00-740-801.

8 Do the OT of the EIS, refer to AMM Task 31-60-00-710-802.

(f) Do the test procedure as specified after the installation of the DU (FINs 1WK2 and

3WK2), refer to AMM Task 31-63-22-200-802.

(g) If removed, do the test procedure as specified after the installation of the First

Officer Seat (FIN 4MS), refer to AMM Task 25-11-51-400-801.

(h) If removed, do the test procedure as specified after the installation of the LU (FIN

14LE), refer to AMM Task 33-12-13-400-801.

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

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**CONF 004

(1) Subtask 253538-700-003-001 - Test

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-26-00-710-803

Task 22-96-00-740-801

Task 22-97-00-740-801

Task 24-41-00-861-801

Task 25-11-51-400-801

Task 31-50-00-710-803

Task 31-50-00-740-801

Task 31-60-00-710-802

Task 31-63-22-200-802

Task 33-12-13-400-801

Task 33-13-00-710-801

Task 33-14-00-710-801

Elec. Std. Practices Manual (ESPM) 20-52-20

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

equipment removed for access, refer to SUBTASK 253538-410-002 001

Install/Close Items Removed/Opened for access.

(a) In the cockpit, on the panel 235VU, push these pushbutton switches:

- BAT 1, BAT 2, APU BAT,

- GEN 1, (2), APU GEN,

- EXT A (B).

(b) Remove the warning notices.

(c) Energize the aircraft electrical circuits, refer to AMM Task 24-41-00-861-801.

(d) Remove the safety clips and/or tags and close/unlock these circuit breakers:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742 701PP 10PB1 72 S

742 702PP 10PB2 71 S

(e) Preliminary test:

NOTE: If the aircraft is operated in actual CAT III conditions, you must

also do the LAND CAT III capability test, refer to AMM Task

22-97-00-740-801.

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1 On each connector which was disconnected:

- Do the checks as defined by ESPM 20-52-20.

NOTE: The functional test and/or operational test (OT) requested by

this ESPM procedure is given hereafter.

2 Do the OT of the instrument and Panel Integral Lighting, refer to AMM Task

33-13-00-710-801.

3 Do the OT of Lights, refer to AMM Task 33-14-00-710-801.

4 Do the OT of the Avionics-Equipment Ventilation System, refer to AMM Task

21-26-00-710-803.

5 Do the OT of the Auto Flight System (SYSTEM TEST), refer to AMM Task

22-96-00-740-801.

6 Do the OT of the ECAM Control Panel, refer to AMM Task 31-50-00-710-803.

7 Do the test of the FWS, AMM Task 31-50-00-740-801.

8 Do the OT of the EIS, refer to AMM Task 31-60-00-710-802.

(f) Do the test procedure as specified after the installation of the DU (FINs 1WK2 and

3WK2), refer to AMM Task 31-63-22-200-802.

(g) If removed, do the test procedure as specified after the installation of the First

Officer Seat (FIN 4MS), refer to AMM Task 25-11-51-400-801.

(h) If removed, do the test procedure as specified after the installation of the LU (FIN

14LE), refer to AMM Task 33-12-13-400-801.

**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 253538-942-002-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 25-11-51-400-801

Task 31-63-22-400-801

Task 33-12-13-400-801

NOTE: If you intend to accomplish an associated Repair Task during the same

layover period, the subsequent Close-up procedure is not necessary.

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

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(b) Parts and/or equipment removed for access, to be installed before the SUBTASK

253538-700-003 001 Test

1 Install the LU (FIN 14LE), refer to AMM Task 33-12-13-400-801.

2 If removed, install the First Officer Seat (FIN 4MS), refer to AMM Task

25-11-51-400-801.

(c) Do the close-up procedure as specified in the installation of DU (FINs 1WK2 and

3WK2), refer to AMM Task 31-63-22-400-801

(d) Restore the systems and the aircraft to normal operation conditions.

**CONF 002

(1) Subtask 253538-942-002-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 25-11-51-400-801

Task 31-63-22-400-801

Task 33-12-13-400-801

NOTE: If you intend to accomplish an associated Repair Task during the same

layover period, the subsequent Close-up procedure is not necessary.

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

(b) Parts and/or equipment removed for access, to be installed before the SUBTASK

253538-700-003 001 Test

1 Install the LU (FIN 14LE), refer to AMM Task 33-12-13-400-801.

2 If removed, install the First Officer Seat (FIN 4MS), refer to AMM Task

25-11-51-400-801.

(c) Do the close-up procedure as specified in the installation of DU (FINs 1WK2 and

3WK2), refer to AMM Task 31-63-22-400-801

(d) Restore the systems and the aircraft to normal operation conditions.

**CONF 003

(1) Subtask 253538-942-002-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

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References

Aircraft Maintenance Manual (AMM) Task 25-11-51-400-801

Task 31-63-22-400-801

Task 33-12-13-400-801

NOTE: If you intend to accomplish an associated Repair Task during the same

layover period, the subsequent Close-up procedure is not necessary.

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

(b) Parts and/or equipment removed for access, to be installed before the SUBTASK

253538-700-003 001 Test

1 Install the LU (FIN 14LE), refer to AMM Task 33-12-13-400-801.

2 If removed, install the First Officer Seat (FIN 4MS), refer to AMM Task

25-11-51-400-801.

(c) Do the close-up procedure as specified in the installation of DU (FINs 1WK2 and

3WK2), refer to AMM Task 31-63-22-400-801

(d) Restore the systems and the aircraft to normal operation conditions.

**CONF 004

(1) Subtask 253538-942-002-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 25-11-51-400-801

Task 31-63-22-400-801

Task 33-12-13-400-801

NOTE: If you intend to accomplish an associated Repair Task during the same

layover period, the subsequent Close-up procedure is not necessary.

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

(b) Parts and/or equipment removed for access, to be installed before the SUBTASK

253538-700-003 001 Test

1 Install the LU (FIN 14LE), refer to AMM Task 33-12-13-400-801.

2 If removed, install the First Officer Seat (FIN 4MS), refer to AMM Task

25-11-51-400-801.

(c) Do the close-up procedure as specified in the installation of DU (FINs 1WK2 and

3WK2), refer to AMM Task 31-63-22-400-801

(d) Restore the systems and the aircraft to normal operation conditions.

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

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This Page Intentionally Left Blank

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Task 253538-833-802-001 - Replace Bracket No. 7.

**CONF ALL

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

INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

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

THIS:

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

NECESSARY ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00.

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.

NOTE: This Service Bulletin is classified mandatory or expected to be classified mandatory

by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these

accomplishment instructions are Required for Compliance (RC) and must be done

to comply with the AD. Other paragraphs are recommended and may be deviated

from, done as part of other actions or done with accepted methods different from

those given in the Service Bulletin, as long as the RC paragraphs can be done and

the aircraft can be put back into a serviceable condition.

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

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Task Associated Data

**CONF 001

Zone

212

Manpower

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

**CONF 002

Zone

212

Manpower

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

**CONF 003

Zone

212

Manpower

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

**CONF 004

Zone

212

Manpower

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 253538-910-003-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

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

06-41-52, Page Block 001

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References

Structural Repair Manual (SRM) 51-24-00

51-42-00

51-43-00

51-44-00

51-75-12

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

Consumable Materials (CML).

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

(c) For the identification of access panels, refer to AMM 06-41-52, Page Block 001.

(d) Remove and install fasteners in accordance with SRM 51-42-00.

(e) Obtain alternative and substitute fastener data, in accordance with SRM 51-43-00.

(f) Obtain fasteners hole diameters and drill and "deburr" data in accordance with

SRM 51-44-00.

(g) Cut the rivets to the necessary length.

(h) Renew the protective finish in accordance with SRM 51-75-12.

(i) Apply sealant in accordance with SRM 51-24-00.

(2) Subtask 253538-839-003-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

**CONF 002

(1) Subtask 253538-910-003-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

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

06-41-52, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-42-00

51-43-00

51-44-00

51-75-12

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

Consumable Materials (CML).

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

(c) For the identification of access panels, refer to AMM 06-41-52, Page Block 001.

(d) Remove and install fasteners in accordance with SRM 51-42-00.

(e) Obtain alternative and substitute fastener data, in accordance with SRM 51-43-00.

(f) Obtain fasteners hole diameters and drill and "deburr" data in accordance with

SRM 51-44-00.

(g) Cut the rivets to the necessary length.

(h) Renew the protective finish in accordance with SRM 51-75-12.

(i) Apply sealant in accordance with SRM 51-24-00.

(2) Subtask 253538-839-003-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

**CONF 003

(1) Subtask 253538-910-003-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

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

06-41-52, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-42-00

51-43-00

51-44-00

51-75-12

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

Consumable Materials (CML).

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

(c) For the identification of access panels, refer to AMM 06-41-52, Page Block 001.

(d) Remove and install fasteners in accordance with SRM 51-42-00.

(e) Obtain alternative and substitute fastener data, in accordance with SRM 51-43-00.

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

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(f) Obtain fasteners hole diameters and drill and "deburr" data in accordance with

SRM 51-44-00.

(g) Cut the rivets to the necessary length.

(h) Renew the protective finish in accordance with SRM 51-75-12.

(i) Apply sealant in accordance with SRM 51-24-00.

(2) Subtask 253538-839-003-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

**CONF 004

(1) Subtask 253538-910-003-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

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

06-41-52, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-42-00

51-43-00

51-44-00

51-75-12

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

Consumable Materials (CML).

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

(c) For the identification of access panels, refer to AMM 06-41-52, Page Block 001.

(d) Remove and install fasteners in accordance with SRM 51-42-00.

(e) Obtain alternative and substitute fastener data, in accordance with SRM 51-43-00.

(f) Obtain fasteners hole diameters and drill and "deburr" data in accordance with

SRM 51-44-00.

(g) Cut the rivets to the necessary length.

(h) Renew the protective finish in accordance with SRM 51-75-12.

(i) Apply sealant in accordance with SRM 51-24-00.

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 97

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(2) Subtask 253538-839-003-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

**CONF ALL

B. PREPARATION

**CONF 001

(1) Subtask 253538-941-003-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

Task 25-11-51-000-801

Task 31-63-22-000-801

Task 33-12-13-000-801

Task 52-10-00-010-801

NOTE: If you intend to accomplish this Repair Task during the same layover

period as the associated Inspection, the subsequent Preparation

procedure is not necessary.

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

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

12-34-24-860-802.

(c) If necessary, remove the First Officer Seat (FIN 4MS), refer to AMM Task

25-11-51-000-801.

(d) Do the Job Set-up procedure as specified in the removal of the Display Unit

(DU)(FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.

(e) In the cockpit, on the panel 235VU, make sure that these pushbutton switches are

released:

- BAT 1, BAT 2, APU BAT,

- GEN 1, (2), APU GEN,

- EXT A (B).

(f) If necessary, remove the Light Unit (LU) (FIN 14LE), refer to AMM Task

33-12-13-000-801.

(g) Open, safety/lock and tag these circuit breakers:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742 701PP 10PB1 72 S

742 702PP 10PB2 71 S

(h) Make sure that there are warning notices in the cockpit to tell persons not to

operate the pushbutton switches on the overhead panels:

- 211VU (EMER ELEC PWR)

- 235VU (ELEC)

(i) Make sure that there are warning notices in the cockpit to tell persons not to start

the APU.

(j) Make sure that the external connectors are not connected to the aircraft

receptacles EXT PWR A (B).

(k) Make sure that there is a warning notice at the access door 121EL to tell persons

not to connect the external power connectors.

(2) Subtask 253538-010-003-001 - Remove/Open for Access

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 31-63-22-000-801

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 99

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SERVICE BULLETIN

References

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

NOTE: If you intend to accomplish this Repair Task during the same layover

period as the associated Inspection, the subsequent Preparation

procedure is not necessary.

(a) Remove the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retain

3 Washer Item (2) Retain

1 Panel Item (3) Retain

(b) Remove the cover assembly panel.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retain

1 Panel Item (4) Retain

(c) Remove the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.

**CONF 002

(1) Subtask 253538-941-003-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

Task 25-11-51-000-801

Task 31-63-22-000-801

Task 33-12-13-000-801

Task 52-10-00-010-801

NOTE: If you intend to accomplish this Repair Task during the same layover

period as the associated Inspection, the subsequent Preparation

procedure is not necessary.

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 100

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SERVICE BULLETIN

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

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

12-34-24-860-802.

(c) If necessary, remove the First Officer Seat (FIN 4MS), refer to AMM Task

25-11-51-000-801.

(d) Do the Job Set-up procedure as specified in the removal of the Display Unit

(DU)(FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.

(e) In the cockpit, on the panel 235VU, make sure that these pushbutton switches are

released:

- BAT 1, BAT 2, APU BAT,

- GEN 1, (2), APU GEN,

- EXT A (B).

(f) If necessary, remove the Light Unit (LU) (FIN 14LE), refer to AMM Task

33-12-13-000-801.

(g) Open, safety/lock and tag these circuit breakers:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742 701PP 10PB1 72 S

742 702PP 10PB2 71 S

(h) Make sure that there are warning notices in the cockpit to tell persons not to

operate the pushbutton switches on the overhead panels:

- 211VU (EMER ELEC PWR)

- 235VU (ELEC)

(i) Make sure that there are warning notices in the cockpit to tell persons not to start

the APU.

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 101

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SERVICE BULLETIN

(j) Make sure that the external connectors are not connected to the aircraft

receptacles EXT PWR A (B).

(k) Make sure that there is a warning notice at the access door 121EL to tell persons

not to connect the external power connectors.

(2) Subtask 253538-010-003-001 - Remove/Open for Access

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 31-63-22-000-801

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

NOTE: If you intend to accomplish this Repair Task during the same layover

period as the associated Inspection, the subsequent Preparation

procedure is not necessary.

(a) Remove the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retain

3 Washer Item (2) Retain

1 Panel Item (3) Retain

(b) Remove the cover assembly panel.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retain

1 Panel Item (4) Retain

(c) Remove the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.

**CONF 003

(1) Subtask 253538-941-003-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 102

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@A330

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

Task 25-11-51-000-801

Task 31-63-22-000-801

Task 33-12-13-000-801

Task 52-10-00-010-801

NOTE: If you intend to accomplish this Repair Task during the same layover

period as the associated Inspection, the subsequent Preparation

procedure is not necessary.

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

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

12-34-24-860-802.

(c) If necessary, remove the First Officer Seat (FIN 4MS), refer to AMM Task

25-11-51-000-801.

(d) Do the Job Set-up procedure as specified in the removal of the Display Unit

(DU)(FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.

(e) In the cockpit, on the panel 235VU, make sure that these pushbutton switches are

released:

- BAT 1, BAT 2, APU BAT,

- GEN 1, (2), APU GEN,

- EXT A (B).

(f) If necessary, remove the Light Unit (LU) (FIN 14LE), refer to AMM Task

33-12-13-000-801.

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 103

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SERVICE BULLETIN

(g) Open, safety/lock and tag these circuit breakers:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742 701PP 10PB1 72 S

742 702PP 10PB2 71 S

(h) Make sure that there are warning notices in the cockpit to tell persons not to

operate the pushbutton switches on the overhead panels:

- 211VU (EMER ELEC PWR)

- 235VU (ELEC)

(i) Make sure that there are warning notices in the cockpit to tell persons not to start

the APU.

(j) Make sure that the external connectors are not connected to the aircraft

receptacles EXT PWR A (B).

(k) Make sure that there is a warning notice at the access door 121EL to tell persons

not to connect the external power connectors.

(2) Subtask 253538-010-003-001 - Remove/Open for Access

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 31-63-22-000-801

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

NOTE: If you intend to accomplish this Repair Task during the same layover

period as the associated Inspection, the subsequent Preparation

procedure is not necessary.

(a) Remove the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retain

3 Washer Item (2) Retain

1 Panel Item (3) Retain

(b) Remove the cover assembly panel.

Refer to Fig. A-FBCAA Sheet 02

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 104

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SERVICE BULLETIN

3 Stud Item (5) Retain

1 Panel Item (4) Retain

(c) Remove the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.

**CONF 004

(1) Subtask 253538-941-003-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

Task 25-11-51-000-801

Task 31-63-22-000-801

Task 33-12-13-000-801

Task 52-10-00-010-801

NOTE: If you intend to accomplish this Repair Task during the same layover

period as the associated Inspection, the subsequent Preparation

procedure is not necessary.

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

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

12-34-24-860-802.

(c) If necessary, remove the First Officer Seat (FIN 4MS), refer to AMM Task

25-11-51-000-801.

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 105

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SERVICE BULLETIN

(d) Do the Job Set-up procedure as specified in the removal of the Display Unit

(DU)(FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.

(e) In the cockpit, on the panel 235VU, make sure that these pushbutton switches are

released:

- BAT 1, BAT 2, APU BAT,

- GEN 1, (2), APU GEN,

- EXT A (B).

(f) If necessary, remove the Light Unit (LU) (FIN 14LE), refer to AMM Task

33-12-13-000-801.

(g) Open, safety/lock and tag these circuit breakers:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742 701PP 10PB1 72 S

742 702PP 10PB2 71 S

(h) Make sure that there are warning notices in the cockpit to tell persons not to

operate the pushbutton switches on the overhead panels:

- 211VU (EMER ELEC PWR)

- 235VU (ELEC)

(i) Make sure that there are warning notices in the cockpit to tell persons not to start

the APU.

(j) Make sure that the external connectors are not connected to the aircraft

receptacles EXT PWR A (B).

(k) Make sure that there is a warning notice at the access door 121EL to tell persons

not to connect the external power connectors.

(2) Subtask 253538-010-003-001 - Remove/Open for Access

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 31-63-22-000-801

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

NOTE: If you intend to accomplish this Repair Task during the same layover

period as the associated Inspection, the subsequent Preparation

procedure is not necessary.

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 106

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@A330

SERVICE BULLETIN

(a) Remove the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retain

3 Washer Item (2) Retain

1 Panel Item (3) Retain

(b) Remove the cover assembly panel.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retain

1 Panel Item (4) Retain

(c) Remove the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.

**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 253538-833-002-001 - Replace the Bracket No. 7.

Work Zones and Access Panels

Zone Access/Work location

212

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills NON SPECIFIC

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

16 F2511012820095 1 BRACKET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 107

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@A330

SERVICE BULLETIN

Component COMPA08

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

7 NAS6604-10 1 BOLT

8 NAS1726-4E 1 NUT

15 ASNA2050DEJ4020 4 RIVET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Synthetic Ester Base

Grease-General Purpose

Low T

03HBD9 As required

References

Structural Repair Manual (SRM) 51-42-00

51-44-00

Fig. A-FBDAA

Replacement of the bracket No. 7

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Remove the bracket No. 7.

Refer to Fig. A-FBDAA

In accordance with SRM 51-42-00.

1 Remove:

1 Screw Item (7) Discard

1 Nut Item (8) Discard

2 Remove the rivets:

- Remove the head of the four rivets.

- Drill four holes through the cockpit main panel to remove the four rivets

and obtain a diameter comprised between 4.07 and 4.16 mm (0.160 and

0.164 in).

4 Rivet Item (15) Discard

3 Remove the bracket:

1 Bracket F2511012820000 Item (16) Discard

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 108

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SERVICE BULLETIN

(b) Install the new bracket.

Refer to Fig. A-FBDAA

In accordance with SRM 51-42-00 and SRM 51-44-00.

1 Temporarily put the bracket item 16 on the RH side of the upper bracket.

a Mark the position of the hole of the upper bracket on the new bracket.

2 On bench, drill the marked hole to a diameter comprised between 6.5 and 6.7

mm (0.256 and 0.264 in).

3 Put in position the new bracket item 16 with the bolt item 7.

Install:

1 Bracket F2511012820095 Item 16

1 Bolt NAS6604-10 Item 7

NOTE: Install the bolt item 7 with:

Synthetic Ester

Base GreaseGeneral Purpose

Low T

03HBD9 As required

4 Measure the clearance between the new bracket item 16 and the upper

bracket as show in Fig. A-FBDAA Sheet 04

a Check that the minimum clearances are 0.35 mm (0.014 in) at LHS and

0.65 (0.026 in) mm at RHS.

5 Drill the four holes in the bracket item 16 to align with the holes of the

structure.

6 Install:

4 Rivet ASNA2050DEJ4020 Item 15

7 Install the nut item 8:

1 Nut NAS1726-4E Item 8

NOTE: Torque the nut item 8 to a torque value between 0.28 and 0.37

mdaN (24.782 and 32.748lbf.in).

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 109

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SERVICE BULLETIN

(2) Subtask 253538-410-004-001 - Install/Close Items Removed/Opened for access

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 31-63-22-400-801

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

(a) Install the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-400-801.

(b) Install the cover assembly plate.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retained at

removal

1 Panel Item (4) Retained at

removal

(c) Install the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retained at

removal

3 Washer Item (2) Retained at

removal

1 Panel Item (3) Retained at

removal

**CONF 002

(1) Subtask 253538-833-002-002 - Replace the Bracket No. 7.

Work Zones and Access Panels

Zone Access/Work location

212

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 110

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SERVICE BULLETIN

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills NON SPECIFIC

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

16 F2511012820095 1 BRACKET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Component COMPA09

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

15 ASNA2050DEJ4020 4 RIVET

17 NSA5042-04-160 1 BOLT

18 NSA5060-3 1 NUT

19 NSA5325-3 1 WASHER

20 MS24665-134 1 PIN

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Synthetic Ester Base

Grease-General Purpose

Low T

03HBD9 As required

References

Structural Repair Manual (SRM) 51-42-00

51-44-00

Fig. A-FBDAB

Replacement of the bracket No. 7

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Remove the bracket No. 7.

Refer to Fig. A-FBDAB

In accordance with SRM 51-42-00.

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 111

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SERVICE BULLETIN

1 Remove:

1 Axis Item (17) Discard

1 Nut Item (18) Discard

1 Washer Item (19) Discard

1 Pin Item (20) Discard

2 Remove the rivets:

- Remove the head of the four rivets.

- Drill four holes through the cockpit main panel to remove the four rivets

and obtain a diameter comprised between 4.07 and 4.16 mm (0.160 and

0.164 in).

4 Rivet Item (15) Discard

3 Remove the bracket:

1 Bracket F2511012820000 Item (16) Discard

(b) Install the new bracket.

Refer to Fig. A-FBDAB

In accordance with SRM 51-42-00 and SRM 51-44-00.

1 Temporarily put the bracket item 16 on the RH side of the upper bracket.

a Mark the position of the hole of the upper bracket on the new bracket.

2 On bench, drill the marked hole to a diameter comprised between 6.5 and 6.7

mm (0.256 and 0.264 in).

3 Put in position the new bracket item 16 with the bolt item 17.

1 Bracket F2511012820095 Item 16

1 Bolt NSA5042-04-160 Item 17

NOTE: Install the bolt item 17 with:

Synthetic Ester

Base GreaseGeneral Purpose

Low T

03HBD9 As required

4 Measure the clearance between the new bracket item 16 and the upper

bracket as show in Fig. A-FBDAB Sheet 04

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 112

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@A330

SERVICE BULLETIN

a Check that the minimum clearances are 0.35 (0.014 in) mm at LHS and

0.65 mm (0.026 in) at RHS.

5 Drill the four holes in the bracket item 16 to align with the holes of the

structure.

6 Install:

4 Rivet ASNA2050DEJ4020 Item 15

7 Install the nut item 18:

1 Nut NSA5060-3 Item 18

1 Washer NSA5325-3 Item 19

1 Pin-Cotter MS24665-134 Item 20

NOTE: Torque the nut item 18 to a torque value between 0.28 and

0.37 mdaN (24.782 and 32.748 lbf.in).

(2) Subtask 253538-410-004-001 - Install/Close Items Removed/Opened for access

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 31-63-22-400-801

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

(a) Install the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-400-801.

(b) Install the cover assembly plate.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retained at

removal

1 Panel Item (4) Retained at

removal

(c) Install the protection plate.

Refer to Fig. A-FBCAA Sheet 01

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 113

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@A330

SERVICE BULLETIN

3 Stud Item (1) Retained at

removal

3 Washer Item (2) Retained at

removal

1 Panel Item (3) Retained at

removal

**CONF 003

(1) Subtask 253538-833-002-003 - Replace the Bracket No. 7.

Work Zones and Access Panels

Zone Access/Work location

212

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills NON SPECIFIC

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

16 F2511012820095 1 BRACKET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Component COMPA10

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

15 ASNA2050DEJ4020 4 RIVET

17 NSA5042-04-160 1 BOLT

18 NSA5060-3 1 NUT

19 NSA5325-3 1 WASHER

21 MS24665-71 1 PIN

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 114

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@A330

SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Synthetic Ester Base

Grease-General Purpose

Low T

03HBD9 As required

References

Structural Repair Manual (SRM) 51-42-00

51-44-00

Fig. A-FBDAC

Replacement of the bracket No. 7

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Remove the bracket No. 7.

Refer to Fig. A-FBDAC

In accordance with SRM 51-42-00.

1 Remove:

1 Axis Item (17) Discard

1 Nut Item (18) Discard

1 Washer Item (19) Discard

1 Pin Item (21) Discard

2 Remove the rivets:

- Remove the head of the four rivets.

- Drill four holes through the cockpit main panel to remove the four rivets

and obtain a diameter comprised between 4.07 and 4.16 mm (0.160 and

0.164 in).

4 Rivet Item (15) Discard

3 Remove the bracket:

1 Bracket F2511012820000 Item (16) Discard

(b) Install the new bracket.

Refer to Fig. A-FBDAC

In accordance with SRM 51-42-00 and SRM 51-44-00.

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 115

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@A330

SERVICE BULLETIN

1 Temporarily put the bracket item 16 on the RH side of the upper bracket.

a Mark the position of the hole of the upper bracket on the new bracket.

2 On bench, drill the marked hole to a diameter comprised between 6.5 and 6.7

mm (0.256 and 0.264 in).

3 Put in position the new bracket item 16 with the bolt item 17.

Install:

1 Bracket F2511012820095 Item 16

1 Bolt NSA5042-04-160 Item 17

NOTE: Install the bolt item 17 with:

Synthetic Ester

Base GreaseGeneral Purpose

Low T

03HBD9 As required

4 Measure the clearance between the new bracket item 16 and the upper

bracket as show in Fig. A-FBDAC Sheet 04

a Check that the minimum clearances are 0.35 mm (0.014 in) at LHS and

0.65 mm (0.026 in) at RHS.

5 Drill the four holes in the bracket item 16 to align with the holes of the

structure.

6 Install:

4 Rivet ASNA2050DEJ4020 Item 15

7 Install the nut item 18:

1 Nut NSA5060-3 Item 18

1 Washer NSA5325-3 Item 19

1 Pin-Cotter MS24665-71 Item 21

NOTE: Torque the nut item 18 to a torque value between 0.28 and

0.37 mdaN (24.782 and 32.748 lbf.in).

(2) Subtask 253538-410-004-001 - Install/Close Items Removed/Opened for access

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 116

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SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 31-63-22-400-801

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

(a) Install the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-400-801.

(b) Install the cover assembly plate.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retained at

removal

1 Panel Item (4) Retained at

removal

(c) Install the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retained at

removal

3 Washer Item (2) Retained at

removal

1 Panel Item (3) Retained at

removal

**CONF 004

(1) Subtask 253538-833-002-004 - Replace the Bracket No. 7.

Work Zones and Access Panels

Zone Access/Work location

212

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills NON SPECIFIC

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

16 F2511012820095 1 BRACKET

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 117

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SERVICE BULLETIN

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Component COMPA10

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

15 ASNA2050DEJ4020 4 RIVET

17 NSA5042-04-160 1 BOLT

18 NSA5060-3 1 NUT

19 NSA5325-3 1 WASHER

21 MS24665-71 1 PIN

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Synthetic Ester Base

Grease-General Purpose

Low T

03HBD9 As required

References

Structural Repair Manual (SRM) 51-42-00

51-44-00

Fig. A-FBDAC

Replacement of the bracket No. 7

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Remove the bracket No. 7.

Refer to Fig. A-FBDAC

In accordance with SRM 51-42-00.

1 Remove:

1 Axis Item (17) Discard

1 Nut Item (18) Discard

1 Washer Item (19) Discard

1 Pin Item (21) Discard

2 Remove the rivets:

- Remove the head of the four rivets.

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 118

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- Drill four holes through the cockpit main panel to remove the four rivets

and obtain a diameter comprised between 4.07 and 4.16 mm (0.160 and

0.164 in).

4 Rivet Item (15) Discard

3 Remove the bracket:

1 Bracket F2511012820000 Item (16) Discard

(b) Install the new bracket.

Refer to Fig. A-FBDAC

In accordance with SRM 51-42-00 and SRM 51-44-00.

1 Temporarily put the bracket item 16 on the RH side of the upper bracket.

a Mark the position of the hole of the upper bracket on the new bracket.

2 On bench, drill the marked hole to a diameter comprised between 6.5 and 6.7

mm (0.256 and 0.264 in).

3 Put in position the new bracket item 16 with the bolt item 17.

Install:

1 Bracket F2511012820095 Item 16

1 Bolt NSA5042-04-160 Item 17

NOTE: Install the bolt item 17 with:

Synthetic Ester

Base GreaseGeneral Purpose

Low T

03HBD9 As required

4 Measure the clearance between the new bracket item 16 and the upper

bracket as show in Fig. A-FBDAC Sheet 04

a Check that the minimum clearances are 0.35 mm (0.014 in) at LHS and

0.65 mm (0.026 in) at RHS.

5 Drill the four holes in the bracket item 16 to align with the holes of the

structure.

6 Install:

4 Rivet ASNA2050DEJ4020 Item 15

7 Install the nut item 18:

1 Nut NSA5060-3 Item 18

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 119

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SERVICE BULLETIN

1 Washer NSA5325-3 Item 19

1 Pin-Cotter MS24665-71 Item 21

NOTE: Torque the nut item 18 to a torque value between 0.28 and

0.37 mdaN (24.782 and 32.748 lbf.in).

(2) Subtask 253538-410-004-001 - Install/Close Items Removed/Opened for access

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 31-63-22-400-801

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

(a) Install the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-400-801.

(b) Install the cover assembly plate.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retained at

removal

1 Panel Item (4) Retained at

removal

(c) Install the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retained at

removal

3 Washer Item (2) Retained at

removal

1 Panel Item (3) Retained at

removal

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 120

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SERVICE BULLETIN

**CONF ALL

D. TEST

**CONF 001

(1) Subtask 253538-700-005-001 - Test

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-26-00-710-803

Task 22-96-00-740-801

Task 22-97-00-740-801

Task 24-41-00-861-801

Task 25-11-51-400-801

Task 31-50-00-710-803

Task 31-50-00-740-801

Task 31-60-00-710-802

Task 31-63-22-200-802

Task 33-12-13-400-801

Task 33-13-00-710-801

Task 33-14-00-710-801

Elec. Std. Practices Manual (ESPM) 20-52-20

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

equipment removed for access, refer to SUBTASK 253538-410-004 001

Install/Close Items Removed/Opened for access

(a) In the cockpit, on the panel 235VU, push these pushbutton switches:

- BAT 1, BAT 2, APU BAT,

- GEN 1, (2), APU GEN,

- EXT A (B).

(b) Remove the warning notices.

(c) Energize the aircraft electrical circuits, refer to AMM Task 24-41-00-861-801.

(d) Remove the safety clips and/or tags and close/unlock these circuit breakers:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742 701PP 10PB1 72 S

742 702PP 10PB2 71 S

(e) Preliminary test:

NOTE: If the aircraft is operated in actual CAT III conditions, you must

also do the LAND CAT III capability test, refer to AMM Task

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 121

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22-97-00-740-801.

1 On each connector which was disconnected:

- Do the checks as defined by ESPM 20-52-20.

NOTE: The functional test and/or operational test (OT) requested by

this ESPM procedure is given hereafter.

2 Do the OT of the instrument and Panel Integral Lighting, refer to AMM Task

33-13-00-710-801.

3 Do the OT of Lights, refer to AMM Task 33-14-00-710-801.

4 Do the OT of the Avionics-Equipment Ventilation System, refer to AMM Task

21-26-00-710-803.

5 Do the OT of the Auto Flight System (SYSTEM TEST), refer to AMM Task

22-96-00-740-801.

6 Do the OT of the ECAM Control Panel, refer to AMM Task 31-50-00-710-803.

7 Do the test of the FWS, AMM Task 31-50-00-740-801.

8 Do the OT of the EIS, refer to AMM Task 31-60-00-710-802.

(f) Do the test procedure as specified after the installation of the DU (FINs 1WK2 and

3WK2), refer to AMM Task 31-63-22-200-802.

(g) If removed, do the test procedure as specified after the installation of the First

Officer Seat (FIN 4MS), refer to AMM Task 25-11-51-400-801.

(h) If removed, do the test procedure as specified after the installation of the LU (FIN

14LE), refer to AMM Task 33-12-13-400-801.

**CONF 002

(1) Subtask 253538-700-005-001 - Test

Manpower Resources

Skills NON SPECIFIC

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 122

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SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 21-26-00-710-803

Task 22-96-00-740-801

Task 22-97-00-740-801

Task 24-41-00-861-801

Task 25-11-51-400-801

Task 31-50-00-710-803

Task 31-50-00-740-801

Task 31-60-00-710-802

Task 31-63-22-200-802

Task 33-12-13-400-801

Task 33-13-00-710-801

Task 33-14-00-710-801

Elec. Std. Practices Manual (ESPM) 20-52-20

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

equipment removed for access, refer to SUBTASK 253538-410-004 001

Install/Close Items Removed/Opened for access

(a) In the cockpit, on the panel 235VU, push these pushbutton switches:

- BAT 1, BAT 2, APU BAT,

- GEN 1, (2), APU GEN,

- EXT A (B).

(b) Remove the warning notices.

(c) Energize the aircraft electrical circuits, refer to AMM Task 24-41-00-861-801.

(d) Remove the safety clips and/or tags and close/unlock these circuit breakers:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742 701PP 10PB1 72 S

742 702PP 10PB2 71 S

(e) Preliminary test:

NOTE: If the aircraft is operated in actual CAT III conditions, you must

also do the LAND CAT III capability test, refer to AMM Task

22-97-00-740-801.

1 On each connector which was disconnected:

- Do the checks as defined by ESPM 20-52-20.

NOTE: The functional test and/or operational test (OT) requested by

this ESPM procedure is given hereafter.

2 Do the OT of the instrument and Panel Integral Lighting, refer to AMM Task

33-13-00-710-801.

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 123

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3 Do the OT of Lights, refer to AMM Task 33-14-00-710-801.

4 Do the OT of the Avionics-Equipment Ventilation System, refer to AMM Task

21-26-00-710-803.

5 Do the OT of the Auto Flight System (SYSTEM TEST), refer to AMM Task

22-96-00-740-801.

6 Do the OT of the ECAM Control Panel, refer to AMM Task 31-50-00-710-803.

7 Do the test of the FWS, AMM Task 31-50-00-740-801.

8 Do the OT of the EIS, refer to AMM Task 31-60-00-710-802.

(f) Do the test procedure as specified after the installation of the DU (FINs 1WK2 and

3WK2), refer to AMM Task 31-63-22-200-802.

(g) If removed, do the test procedure as specified after the installation of the First

Officer Seat (FIN 4MS), refer to AMM Task 25-11-51-400-801.

(h) If removed, do the test procedure as specified after the installation of the LU (FIN

14LE), refer to AMM Task 33-12-13-400-801.

**CONF 003

(1) Subtask 253538-700-005-001 - Test

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-26-00-710-803

Task 22-96-00-740-801

Task 22-97-00-740-801

Task 24-41-00-861-801

Task 25-11-51-400-801

Task 31-50-00-710-803

Task 31-50-00-740-801

Task 31-60-00-710-802

Task 31-63-22-200-802

Task 33-12-13-400-801

Task 33-13-00-710-801

Task 33-14-00-710-801

Elec. Std. Practices Manual (ESPM) 20-52-20

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

equipment removed for access, refer to SUBTASK 253538-410-004 001

Install/Close Items Removed/Opened for access

(a) In the cockpit, on the panel 235VU, push these pushbutton switches:

- BAT 1, BAT 2, APU BAT,

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 124

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SERVICE BULLETIN

- GEN 1, (2), APU GEN,

- EXT A (B).

(b) Remove the warning notices.

(c) Energize the aircraft electrical circuits, refer to AMM Task 24-41-00-861-801.

(d) Remove the safety clips and/or tags and close/unlock these circuit breakers:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742 701PP 10PB1 72 S

742 702PP 10PB2 71 S

(e) Preliminary test:

NOTE: If the aircraft is operated in actual CAT III conditions, you must

also do the LAND CAT III capability test, refer to AMM Task

22-97-00-740-801.

1 On each connector which was disconnected:

- Do the checks as defined by ESPM 20-52-20.

NOTE: The functional test and/or operational test (OT) requested by

this ESPM procedure is given hereafter.

2 Do the OT of the instrument and Panel Integral Lighting, refer to AMM Task

33-13-00-710-801.

3 Do the OT of Lights, refer to AMM Task 33-14-00-710-801.

4 Do the OT of the Avionics-Equipment Ventilation System, refer to AMM Task

21-26-00-710-803.

5 Do the OT of the Auto Flight System (SYSTEM TEST), refer to AMM Task

22-96-00-740-801.

6 Do the OT of the ECAM Control Panel, refer to AMM Task 31-50-00-710-803.

7 Do the test of the FWS, AMM Task 31-50-00-740-801.

8 Do the OT of the EIS, refer to AMM Task 31-60-00-710-802.

(f) Do the test procedure as specified after the installation of the DU (FINs 1WK2 and

3WK2), refer to AMM Task 31-63-22-200-802.

(g) If removed, do the test procedure as specified after the installation of the First

Officer Seat (FIN 4MS), refer to AMM Task 25-11-51-400-801.

(h) If removed, do the test procedure as specified after the installation of the LU (FIN

14LE), refer to AMM Task 33-12-13-400-801.

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 125

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SERVICE BULLETIN

**CONF 004

(1) Subtask 253538-700-005-001 - Test

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-26-00-710-803

Task 22-96-00-740-801

Task 22-97-00-740-801

Task 24-41-00-861-801

Task 25-11-51-400-801

Task 31-50-00-710-803

Task 31-50-00-740-801

Task 31-60-00-710-802

Task 31-63-22-200-802

Task 33-12-13-400-801

Task 33-13-00-710-801

Task 33-14-00-710-801

Elec. Std. Practices Manual (ESPM) 20-52-20

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

equipment removed for access, refer to SUBTASK 253538-410-004 001

Install/Close Items Removed/Opened for access

(a) In the cockpit, on the panel 235VU, push these pushbutton switches:

- BAT 1, BAT 2, APU BAT,

- GEN 1, (2), APU GEN,

- EXT A (B).

(b) Remove the warning notices.

(c) Energize the aircraft electrical circuits, refer to AMM Task 24-41-00-861-801.

(d) Remove the safety clips and/or tags and close/unlock these circuit breakers:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742 701PP 10PB1 72 S

742 702PP 10PB2 71 S

(e) Preliminary test:

NOTE: If the aircraft is operated in actual CAT III conditions, you must

also do the LAND CAT III capability test, refer to AMM Task

22-97-00-740-801.

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 126

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SERVICE BULLETIN

1 On each connector which was disconnected:

- Do the checks as defined by ESPM 20-52-20.

NOTE: The functional test and/or operational test (OT) requested by

this ESPM procedure is given hereafter.

2 Do the OT of the instrument and Panel Integral Lighting, refer to AMM Task

33-13-00-710-801.

3 Do the OT of Lights, refer to AMM Task 33-14-00-710-801.

4 Do the OT of the Avionics-Equipment Ventilation System, refer to AMM Task

21-26-00-710-803.

5 Do the OT of the Auto Flight System (SYSTEM TEST), refer to AMM Task

22-96-00-740-801.

6 Do the OT of the ECAM Control Panel, refer to AMM Task 31-50-00-710-803.

7 Do the test of the FWS, AMM Task 31-50-00-740-801.

8 Do the OT of the EIS, refer to AMM Task 31-60-00-710-802.

(f) Do the test procedure as specified after the installation of the DU (FINs 1WK2 and

3WK2), refer to AMM Task 31-63-22-200-802.

(g) If removed, do the test procedure as specified after the installation of the First

Officer Seat (FIN 4MS), refer to AMM Task 25-11-51-400-801.

(h) If removed, do the test procedure as specified after the installation of the LU (FIN

14LE), refer to AMM Task 33-12-13-400-801.

**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 253538-942-003-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 25-11-51-400-801

Task 31-63-22-400-801

Task 33-12-13-400-801

Task 52-10-00-010-801

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

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 127

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SERVICE BULLETIN

(b) Parts and/or equipment removed for access, to be installed before the SUBTASK

253538-700-003 001 Test

1 Install the LU (FIN 14LE), refer to AMM Task 33-12-13-400-801.

2 If removed, install the First Officer Seat (FIN 4MS), refer to AMM Task

25-11-51-400-801.

(c) Do the close-up procedure as specified in the installation of DU (FINs 1WK2 and

3WK2), refer to AMM Task 31-63-22-400-801

(d) Restore the systems and the aircraft to normal operation conditions.

**CONF 002

(1) Subtask 253538-942-003-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 25-11-51-400-801

Task 31-63-22-400-801

Task 33-12-13-400-801

Task 52-10-00-010-801

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

(b) Parts and/or equipment removed for access, to be installed before the SUBTASK

253538-700-003 001 Test

1 Install the LU (FIN 14LE), refer to AMM Task 33-12-13-400-801.

2 If removed, install the First Officer Seat (FIN 4MS), refer to AMM Task

25-11-51-400-801.

(c) Do the close-up procedure as specified in the installation of DU (FINs 1WK2 and

3WK2), refer to AMM Task 31-63-22-400-801

(d) Restore the systems and the aircraft to normal operation conditions.

**CONF 003

(1) Subtask 253538-942-003-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 25-11-51-400-801

Task 31-63-22-400-801

Task 33-12-13-400-801

Task 52-10-00-010-801

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 128

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SERVICE BULLETIN

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

(b) Parts and/or equipment removed for access, to be installed before the SUBTASK

253538-700-003 001 Test

1 Install the LU (FIN 14LE), refer to AMM Task 33-12-13-400-801.

2 If removed, install the First Officer Seat (FIN 4MS), refer to AMM Task

25-11-51-400-801.

(c) Do the close-up procedure as specified in the installation of DU (FINs 1WK2 and

3WK2), refer to AMM Task 31-63-22-400-801

(d) Restore the systems and the aircraft to normal operation conditions.

**CONF 004

(1) Subtask 253538-942-003-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 25-11-51-400-801

Task 31-63-22-400-801

Task 33-12-13-400-801

Task 52-10-00-010-801

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

(b) Parts and/or equipment removed for access, to be installed before the SUBTASK

253538-700-003 001 Test

1 Install the LU (FIN 14LE), refer to AMM Task 33-12-13-400-801.

2 If removed, install the First Officer Seat (FIN 4MS), refer to AMM Task

25-11-51-400-801.

(c) Do the close-up procedure as specified in the installation of DU (FINs 1WK2 and

3WK2), refer to AMM Task 31-63-22-400-801

(d) Restore the systems and the aircraft to normal operation conditions.

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 129

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SERVICE BULLETIN

**CONF ALL

BRACKET No 6

A

A

BRACKET No 7

C

B

G_SB_253538_5_BAAA_01_01

Figure A-FBAAA - Sheet 01

Area to be inspected

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 130

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SERVICE BULLETIN

**CONF ALL

TYPICAL CRACKS LOCATIONS

AREAS TO BE INSPECTED 

(BOTH SIDES OF THE TWO LUGS)

B C

TYPICAL CRACKS LOCATIONS

D

D

G_SB_253538_5_BAAA_02_02

Figure A-FBAAA - Sheet 02

Area to be inspected

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 131

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SERVICE BULLETIN

**CONF 001

BRACKET No 6

A

A

B C

G_SB_253538_5_BBAA_01_01

Figure A-FBBAA - Sheet 01

Replacement of the bracket No. 6

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 132

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SERVICE BULLETIN

**CONF 001

(16)

FWD

BEFORE

(7)

(8)

B

HOLE

SYMBOL ITEM OLD PN DESCRIPTION

RIVET

RIVET

ASNA2050DCJ3215 RIVET

(15)

(14)

(11)

ASNA2051DEJ4020

ASNA2050DEJ4020

G_SB_253538_5_BBAA_02_03

Figure A-FBBAA - Sheet 02

Replacement of the bracket No. 6

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 133

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SERVICE BULLETIN

**CONF 001

16

FWD

AFTER

C

01

HOLE

SYMBOL ITEM PN DESCRIPTION

HOLE DIAMETER

MIN MAX

RIVET

ASNA2050DCJ3215 RIVET

15

11

4.07 mm

(0.160 in)

4.16 mm

(0.164 in) ASNA2050DEJ4020

3.25 mm

(0.128 in)

3.35 mm

(0.132 in)

NOTE:

01 DRILL THE MARKED HOLE TO DIAMETER COMPRISED BETWEEN 6.5 mm (0.256 in)

AND 6.7 mm (0.264 in) 

A

A

G_SB_253538_5_BBAA_03_05

Figure A-FBBAA - Sheet 03

Replacement of the bracket No. 6

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 134

5

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@A330

SERVICE BULLETIN

**CONF 001

NOTE:

CHECK THAT THE MINIMUM CLEARANCES ARE 0.35 mm (0.014 in) AT LHS

7

16

8

A A

AND 0.65 mm (0.026 in) AT RHS

01

01 01

TORQUE THE NUT ITEM 8 TO A TORQUE VALUE BETWEEN 0.28 m.daN (24.782 lbf.in)

AND 0.37 m.daN (32.748 lbf.in)

02

02

MEASURE THE

CLEARANCE

MEASURE THE

CLEARANCE

G_SB_253538_5_BBAA_04_02

Figure A-FBBAA - Sheet 04

Replacement of the bracket No. 6

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 135

5

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@A330

SERVICE BULLETIN

**CONF 002

BRACKET No 6

A

B C

A

G_SB_253538_5_BBAC_01_00

Figure A-FBBAC - Sheet 01

Replacement of the bracket No. 6

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 136

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A330

SERVICE BULLETIN

**CONF 002

(16)

FWD

BEFORE

(17)

(18)

B

(19)

(20)

HOLE

SYMBOL ITEM OLD PN DESCRIPTION

RIVET

RIVET

ASNA2050DCJ3215 RIVET

(15)

(14)

(11)

ASNA2051DEJ4020

ASNA2050DEJ4020

G_SB_253538_5_BBAC_02_02

Figure A-FBBAC - Sheet 02

Replacement of the bracket No. 6

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 137

5

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@A330

SERVICE BULLETIN

**CONF 002

16

FWD

AFTER

C

01

HOLE

SYMBOL ITEM PN DESCRIPTION

HOLE DIAMETER

MIN MAX

RIVET

ASNA2050DCJ3215 RIVET

15

11

4.07 mm

(0.160 in)

4.16 mm

(0.164 in) ASNA2050DEJ4020

3.25 mm

(0.128 in)

3.35 mm

(0.132 in)

NOTE:

01 DRILL THE MARKED HOLE TO DIAMETER COMPRISED BETWEEN 6.5 mm (0.256 in)

AND 6.7 mm (0.264 in) 

A

A

G_SB_253538_5_BBAC_03_03

Figure A-FBBAC - Sheet 03

Replacement of the bracket No. 6

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 138

5

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@A330

SERVICE BULLETIN

**CONF 002

A A

01 01

16

17

19

18

20

NOTE:

CHECK THAT THE MINIMUM CLEARANCES ARE 0.35 mm (0.014 in) AT LHS

AND 0.65 mm (0.026 in) AT RHS

01

TORQUE THE NUT ITEM 18 TO A TORQUE VALUE BETWEEN 0.28 m.daN (24.782 lbf.in)

AND 0.37 m.daN (32.748 lbf.in)

02

02

MEASURE THE

CLEARANCE

MEASURE THE

CLEARANCE

G_SB_253538_5_BBAC_04_01

Figure A-FBBAC - Sheet 04

Replacement of the bracket No. 6

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 139

5

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@A330

SERVICE BULLETIN

**CONF 003

BRACKET No 6

A

B C

A

G_SB_253538_5_BBAD_01_00

Figure A-FBBAD - Sheet 01

Replacement of the bracket No. 6

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 140

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A330

SERVICE BULLETIN

**CONF 003

(16)

FWD

BEFORE

(17)

(18)

B

(19)

(21)

HOLE

SYMBOL ITEM OLD PN DESCRIPTION

RIVET

RIVET

ASNA2050DCJ3215 RIVET

(15)

(14)

(11)

ASNA2051DEJ4020

ASNA2050DEJ4020

G_SB_253538_5_BBAD_02_02

Figure A-FBBAD - Sheet 02

Replacement of the bracket No. 6

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 141

5

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@A330

SERVICE BULLETIN

**CONF 003

16

FWD

AFTER

C

01

HOLE

SYMBOL ITEM PN DESCRIPTION

HOLE DIAMETER

MIN MAX

RIVET

ASNA2050DCJ3215 RIVET

15

11

4.07 mm

(0.160 in)

4.16 mm

(0.164 in) ASNA2050DEJ4020

3.25 mm

(0.128 in)

3.35 mm

(0.132 in)

NOTE:

01 DRILL THE MARKED HOLE TO DIAMETER COMPRISED BETWEEN 6.5 mm (0.256 in)

AND 6.7 mm (0.264 in) 

A

A

G_SB_253538_5_BBAD_03_03

Figure A-FBBAD - Sheet 03

Replacement of the bracket No. 6

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 142

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A330

SERVICE BULLETIN

**CONF 003

A A

01 01

16

17

19

18

21

NOTE:

CHECK THAT THE MINIMUM CLEARANCES ARE 0.35 mm (0.014 in) AT LHS

AND 0.65 mm (0.026 in) AT RHS

01

TORQUE THE NUT ITEM 18 TO A TORQUE VALUE BETWEEN 0.28 m.daN (24.782 lbf.in)

AND 0.37 m.daN (32.748 lbf.in)

02

02

MEASURE THE

CLEARANCE

MEASURE THE

CLEARANCE

G_SB_253538_5_BBAD_04_01

Figure A-FBBAD - Sheet 04

Replacement of the bracket No. 6

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 143

5

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@A330

SERVICE BULLETIN

**CONF 004

BRACKET No 6

A

B C

A

G_SB_253538_5_BBAB_01_00

Figure A-FBBAB - Sheet 01

Replacement of the bracket No. 6

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 144

5

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@A330

SERVICE BULLETIN

**CONF 004

(6)

FWD

BEFORE

(17)

(18)

B

HOLE

SYMBOL ITEM OLD PN DESCRIPTION

BOLT

ASNA2050DCJ3215 RIVET

(9)

(11)

EN6115V3−5

(10) ASNA2531−3 NUT

(19)

(21)

G_SB_253538_5_BBAB_02_04

Figure A-FBBAB - Sheet 02

Replacement of the bracket No. 6

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 145

5

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@A330

SERVICE BULLETIN

**CONF 004

6

FWD

AFTER

C

HOLE

SYMBOL ITEM PN DESCRIPTION

HOLE DIAMETER

MIN MAX

BOLT

ASNA2050DCJ3215 RIVET

9

11

4.780 mm

(0.189 in)

4.821 mm

(0.190 in)

EN6115V3−5

3.25 mm

(0.128 in)

3.35 mm

(0.132 in)

10 ASNA2531−3 NUT

NOTE:

01 DRILL THE MARKED HOLE TO DIAMETER COMPRISED BETWEEN 6.5 mm (0.256 in)

AND 6.7 mm (0.264 in) 

A

A

01

G_SB_253538_5_BBAB_03_03

Figure A-FBBAB - Sheet 03

Replacement of the bracket No. 6

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 146

5

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@A330

SERVICE BULLETIN

**CONF 004

A A

NOTE:

CHECK THAT THE MINIMUM CLEARANCES ARE 0.35 mm (0.014 in) AT LHS

AND 0.65 mm (0.026 in) AT RHS

01

TORQUE THE NUT ITEM 18 TO A TORQUE VALUE BETWEEN 0.28 m.daN (24.782 lbf.in)

AND 0.37 m.daN (32.748 lbf.in)

02

01 01

6

17

19

18

21

02

MEASURE THE

CLEARANCE

MEASURE THE

CLEARANCE

G_SB_253538_5_BBAB_04_02

Figure A-FBBAB - Sheet 04

Replacement of the bracket No. 6

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 147

5

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@A330

SERVICE BULLETIN

**CONF 001

A

A

BRACKET No 7

B C

G_SB_253538_5_BDAA_01_00

Figure A-FBDAA - Sheet 01

Replacement of the bracket No. 7

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 148

5

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@A330

SERVICE BULLETIN

**CONF 001

(16)

FWD

BEFORE

(7)

(8)

B

HOLE

SYMBOL ITEM OLD PN DESCRIPTION

(15) ASNA2050DEJ4020 RIVET

G_SB_253538_5_BDAA_02_01

Figure A-FBDAA - Sheet 02

Replacement of the bracket No. 7

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 149

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A330

SERVICE BULLETIN

**CONF 001

16

FWD

AFTER

C

01

HOLE

SYMBOL ITEM PN DESCRIPTION

HOLE DIAMETER

MIN MAX

15 RIVET 4.07 mm

(0.160 in)

4.16 mm

(0.164 in) ASNA2050DEJ4020

NOTE:

01 DRILL THE MARKED HOLE TO DIAMETER COMPRISED BETWEEN 6.5 mm (0.256 in)

AND 6.7 mm (0.264 in) 

A

A

G_SB_253538_5_BDAA_03_01

Figure A-FBDAA - Sheet 03

Replacement of the bracket No. 7

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 150

5

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@A330

SERVICE BULLETIN

**CONF 001

NOTE:

CHECK THAT THE MINIMUM CLEARANCES ARE 0.35 mm (0.014 in) AT LHS

7

16

8

A A

AND 0.65 mm (0.026 in) AT RHS

01

01 01

TORQUE THE NUT ITEM 8 TO A TORQUE VALUE BETWEEN 0.28 m.daN (24.782 lbf.in)

AND 0.37 m.daN (32.748 lbf.in)

02

02

MEASURE THE

CLEARANCE

MEASURE THE

CLEARANCE

G_SB_253538_5_BDAA_04_00

Figure A-FBDAA - Sheet 04

Replacement of the bracket No. 7

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 151

5

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@A330

SERVICE BULLETIN

**CONF 002

A

A

BRACKET No 7

B C

G_SB_253538_5_BDAB_01_00

Figure A-FBDAB - Sheet 01

Replacement of the bracket No. 7

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 152

5

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@A330

SERVICE BULLETIN

**CONF 002

(16)

FWD

BEFORE

(17)

(18)

B

(19)

(20)

HOLE

SYMBOL ITEM OLD PN DESCRIPTION

(15) ASNA2050DEJ4020 RIVET

G_SB_253538_5_BDAB_02_01

Figure A-FBDAB - Sheet 02

Replacement of the bracket No. 7

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 153

5

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@A330

SERVICE BULLETIN

**CONF 002

16

FWD

AFTER

C

01

HOLE

SYMBOL ITEM PN DESCRIPTION

HOLE DIAMETER

MIN MAX

15 RIVET 4.07 mm

(0.160 in)

4.16 mm

(0.164 in) ASNA2050DEJ4020

NOTE:

01 DRILL THE MARKED HOLE TO DIAMETER COMPRISED BETWEEN 6.5 mm (0.256 in)

AND 6.7 mm (0.264 in) 

A

A

G_SB_253538_5_BDAB_03_01

Figure A-FBDAB - Sheet 03

Replacement of the bracket No. 7

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 154

5

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@A330

SERVICE BULLETIN

**CONF 002

A A

01 01

16

17

19

18

20

NOTE:

CHECK THAT THE MINIMUM CLEARANCES ARE 0.35 mm (0.014 in) AT LHS

AND 0.65 mm (0.026 in) AT RHS

01

TORQUE THE NUT ITEM 18 TO A TORQUE VALUE BETWEEN 0.28 m.daN (24.782 lbf.in)

AND 0.37 m.daN (32.748 lbf.in)

02

02

MEASURE THE

CLEARANCE

MEASURE THE

CLEARANCE

G_SB_253538_5_BDAB_04_00

Figure A-FBDAB - Sheet 04

Replacement of the bracket No. 7

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 155

5

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@A330

SERVICE BULLETIN

**CONF 003 thru 004

A

A

BRACKET No 7

B C

G_SB_253538_5_BDAC_01_00

Figure A-FBDAC - Sheet 01

Replacement of the bracket No. 7

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 156

5

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@A330

SERVICE BULLETIN

**CONF 003 thru 004

(16)

FWD

BEFORE

(17)

(18)

B

HOLE

SYMBOL ITEM OLD PN DESCRIPTION

(12) ASNA2050DEJ4020 RIVET

(19)

(21)

G_SB_253538_5_BDAC_02_00

Figure A-FBDAC - Sheet 02

Replacement of the bracket No. 7

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 157

5

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@A330

SERVICE BULLETIN

**CONF 003 thru 004

16

FWD

AFTER

C

HOLE

SYMBOL ITEM PN DESCRIPTION

HOLE DIAMETER

MIN MAX

15 ASNA2050DEJ4020 RIVET 4.07 mm

(0.160 in)

4.16 mm

(0.164 in)

NOTE:

01 DRILL THE MARKED HOLE TO DIAMETER COMPRISED BETWEEN 6.5 mm (0.256 in)

AND 6.7 mm (0.264 in) 

A

A

01

G_SB_253538_5_BDAC_03_01

Figure A-FBDAC - Sheet 03

Replacement of the bracket No. 7

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 158

5

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@A330

SERVICE BULLETIN

**CONF 003 thru 004

A A

NOTE:

CHECK THAT THE MINIMUM CLEARANCES ARE 0.35 mm (0.014 in) AT LHS

AND 0.65 mm (0.026 in) AT RHS

01

TORQUE THE NUT ITEM 18 TO A TORQUE VALUE BETWEEN 0.28 m.daN (24.782 lbf.in)

AND 0.37 m.daN (32.748 lbf.in)

02

01 01

16

17

19

18

21

02

MEASURE THE

CLEARANCE

MEASURE THE

CLEARANCE

G_SB_253538_5_BDAC_04_00

Figure A-FBDAC - Sheet 04

Replacement of the bracket No. 7

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 159

5

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@A330

SERVICE BULLETIN

**CONF ALL

(3)

(1)

(2)

A

A B

G_SB_253538_5_BCAA_01_00

Figure A-FBCAA - Sheet 01

Removal/Installation of the protection plate and cover assembly panels

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 160

5

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@A330

SERVICE BULLETIN

**CONF ALL

(4)

(5)

TYPICAL INSTALATION

C C

C

C

B

G_SB_253538_5_BCAA_02_00

Figure A-FBCAA - Sheet 02

Removal/Installation of the protection plate and cover assembly panels

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 161

5

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@A330

SERVICE BULLETIN

**CONF ALL

QUESTION

ACTION

FINDING

YES CRACKS FOUND

AT THE THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2)

REFER TO TASK 253538−832−801−001

BRACKET LUGS ARE

FULLY BROKEN?

YES

DO A DETAILED INSPECTION OF THE COCKPIT

INSTRUMENT PANEL BRACKET No 7

OR

YES CRACKS FOUND

CONTACT AIRBUS

BEFORE NEXT

FLIGHT

REPLACE BRACKET No 6 AND BRACKET No 7

REFER TO TASK 253538−833−801−001

REFER TO SUBTASK 253538−700−004−001

TWO

BEFORE NEXT FLIGHT

NO

REPLACE BRACKET No 6

REFER TO TASK 253538−833−801−001

AT THE THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2)

DO A DETAILED INSPECTION OF THE COCKPIT

INSTRUMENT PANEL BRACKET No 6

REFER TO TASK 253538−832−801−001

AT THE INTERVAL GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2)

NO

NO

INSTRUMENT PANEL BRACKET No 6

DO A DETAILED INSPECTION OF THE COCKPIT

AT THE THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2)

REFER TO TASK 253538−832−801−001

INSTRUMENT PANEL BRACKET No 6

DO A DETAILED INSPECTION OF THE COCKPIT

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN.

AT THE THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2)

AND TASK 253538−833−802−001

IMPLEMENT SB No 25−3548 AS

TERMINATIVE SOLUTION AT THE

REPLACE BRACKET No 7

REFER TO TASK 253538−833−802−001

BEFORE NEXT FLIGHT

OR

OR

IMPLEMENT SB No 25−3548

AS TERMINATIVE SOLUTION

THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2)

G_SB_253538_5_FAAA_01_08

Figure A-FFAAA - Sheet 01

Flow-chart

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 162

5

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@A330

SERVICE BULLETIN

**CONF ALL

INSPECTION REPORT

RETURN TO: 

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES1

FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − CENTER

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

E−mail: Structure.sbinspectionresult@airbus.com

FAX +33 (0)5 61 93 36 14

WING BOX (WB/LR)

SERVICE BULLETIN NO.:

A/C MSN:

OPERATOR:

FLIGHT HOURS (FH):

FLIGHT CYCLES (FC):

INSPECTION METHOD:

DATE OF INSPECTION:

A330−25−3538

DETAILED

INSPECTION

CRACKS FOUND YES NO

TWO LUGS FULLY BROKEN YES NO

BRACKET REPLACED YES NO

CRACKS FOUND YES NO

BRACKET NUMBER 6

BRACKET NUMBER 7

BRACKET REPLACED YES NO

G_SB_253538_5_RAAA_01_01

Figure A-FRAAA - Sheet 01

Inspection Report

DATE: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 163

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@A330

SERVICE BULLETIN

REPORTING SHEET

TITLE: EQUIPMENT/FURNISHINGS - COCKPIT - INSPECTION OF COCKPIT

INSTRUMENT PANEL BRACKET 6.

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: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 1

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@A330

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: Sep 10/13 SERVICE BULLETIN No.: A330-25-3538

REVISION No.: 02 - Apr 24/14 Page: 1

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