@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 - CURTAINS AND PARTITIONS -

INTRODUCE MODIFIED ELECTRICAL BONDING OF COCKPIT DOOR.

MODIFICATION No.: 203228D50684 203229D61659 203371D48094

This page transmits Revision No.02 of Service Bulletin No.A330-25-3534

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:

- update length of bonding lead in Config. 003

- update Accomplishment Instructions to remove and install coat stowage to the extent necessary

- update location of bonding hole on door post

- update Concurrent Requirements

CHANGES

SUMMARY

MATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE

UPDATED

R

MATERIAL PRICE INFORMATION TABLE

UPDATED

R

MATERIAL PRICE INFORMATION TABLE

UPDATED

R

EFFECTIVITY OPERATOR LIST UPDATED R

CONCURRENT REQUIREMENTS CONCURRENT REQUIREMENTS UPDATED

CONFIGURATION UPDATED

R

CONCURRENT REQUIREMENTS ADDED N

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 1

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@A330

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

CONCURRENT REQUIREMENTS DELETED FOR

APPLICABLE MSN

D

PLANNING INFORMATION

EFFECTIVITY EFFECTIVITY RELATED INFORMATION

UPDATED

R

Configuration definition

CONF 001 CONFIGURATION DEFINITION UPDATED R

Material Effectivity MATERIAL EFFECTIVITY UPDATED

MATERIAL SET UPDATED

MATERIAL SET QUANTITY UPDATED

R

CONCURRENT REQUIREMENTS CONCURRENT SB LIST UPDATED

CONFIGURATION UPDATED

R

CONCURRENT SB LIST ADDED N

CONCURRENT SB LIST DELETED FOR

APPLICABLE MSN

D

COMPLIANCE

Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED R

REFERENCES REFERENCED DOCUMENTATION UPDATED R

MATERIAL INFORMATION

MATERIAL - PRICE AND AVAILABILITY

Procurement Addresses PROCUREMENT ADDRESSES UPDATED

MATERIAL SET UPDATED

R

Price and Availability PRICE AND AVAILABILITY UPDATED

MATERIAL PRICE UPDATED

MATERIAL SET UPDATED

R

INDUSTRY SUPPORT INFORMATION INDUSTRY SUPPORT INFORMATION UPDATED R

LIST OF COMPONENTS

Kit 253534D03R06 PART MATERIAL SET UPDATED

MATERIAL SET LABEL UPDATED

QUANTITY UPDATED

R

LIST OF MATERIALS - OPERATOR

SUPPLIED

Components COMPONENTS UPDATED R

Component COMPD02 PART MATERIAL SET ADDED N

ACCOMPLISHMENT INSTRUCTIONS

TASK 253534- 831-848-001-Modification

Subtask 253534-941-201-001 SUBTASK SOLUTION UPDATED

NOTE UPDATED

R

Subtask 253534-941-201-001 SUBTASK SOLUTION UPDATED

NOTE UPDATED

R

Subtask 253534-941-201-002 SUBTASK SOLUTION UPDATED

NOTE UPDATED

R

Subtask 253534-831-201-001 SUBTASK SOLUTION UPDATED

NOTE UPDATED

R

Subtask 253534-831-203-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

NOTE UPDATED

REFERENCES UPDATED

R

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 2

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Subtask 253534-831-201-002 SUBTASK SOLUTION UPDATED

NOTE UPDATED

R

Subtask 253534-831-203-002 SUBTASK SOLUTION UPDATED

NOTE UPDATED

R

Subtask 253534-831-201-004 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 253534-831-203-003 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

PART NUMBER DESCRIPTION UPDATED

NOTE UPDATED

MATERIAL LIST UPDATED

R

Subtask 253534-760-201-001 SUBTASK SOLUTION UPDATED R

Subtask 253534-942-201-001 SUBTASK SOLUTION UPDATED R

Subtask 253534-942-201-001 SUBTASK SOLUTION UPDATED R

Subtask 253534-942-201-002 SUBTASK SOLUTION UPDATED R

Fig. A-GBCAA

Fig. A-GBCAA Sheet 03 SHEET UPDATED R

Fig. A-GBCAB

Fig. A-GBCAB Sheet 03 SHEET UPDATED R

Fig. A-GBDAC

Fig. A-GBDAC Sheet 03 SHEET UPDATED R

FILING 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:

update the reason paragraph to remove reference to the In-Flight Entertainment (IFE) wiring

delete MSN 0205 from the effectivity

update of Concurrent Requirement to add Service Bulletin No. A330-25-3213.

REVISION SEQUENCE

ORIGINAL: May 27/14

REVISION No. : 01 - Oct 23/14

REVISION No. : 02 - May 18/15

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 3

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@A330

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

This Page Intentionally Left Blank

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 4

6

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SERVICE BULLETIN

SUMMARY

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

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

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 25

TITLE: EQUIPMENT/FURNISHINGS - CURTAINS AND PARTITIONS -

INTRODUCE MODIFIED ELECTRICAL BONDING OF COCKPIT DOOR.

**CONF ALL

MODIFICATIONS

MODIFICATION CLASSIFICATION

MAJOR None

MINOR 203228D50684 203229D61659 203371D48094

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

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

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

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

Airbus has identified a potential risk of electrical shocks in case of chafing at the cockpit door. The

electrical bonding of the cockpit door has to be improved in order to mitigate this potential risk.

This Service Bulletin details the work necessary to improve the electrical bonding.

Accomplishment of this Service Bulletin improves the effectiveness of the electrical bonding thus will

contribute to prevent the risk of an electrical shock.

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO

POTENTIAL AD YES A/C OPERATION AFFECTED NO

RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO

COST SAVING NO ETOPS AFFECTED NO

STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO

NOTE (1): Service Bulletin must be accomplished.

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 1

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@A330

SERVICE BULLETIN

SUMMARY

MATERIAL PRICE INFORMATION

**CONF 001

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 253534D01R08 1 765.00 Screw, Washer, Nut, Rivet, Bracket,

Bonding-Lead, Tube, Placard

Component COMPD01 1 See SB Bonding Lead, Screw, Washer

**CONF 002

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 253534D01R08 1 765.00 Screw, Washer, Nut, Rivet, Bracket,

Bonding-Lead, Tube, Placard

Component COMPD01 1 See SB Bonding Lead, Screw, Washer

**CONF 003

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 253534D03R06 1 2,700.00 Screw, Washer, Bracket, Bonding-Lead,

Tube, Placard

Component COMPD02 1 See SB Bonding Lead

EFFECTIVITY

**CONF ALL

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

18P 38W 39V 43P 44W 83V AAR AAW ABD ACA ACI AEA AFL

AFR AIB ALK ARA ARG ASY AVA AZA AZU BEC BEL BER BGH

CAL CCA CES CHH CPA CRK CRL CSA CSC CSN DAH DAL DGA

DLH EDW EIN ETD EVA EVE FIN FJI FWI G8E GFA GIA GRL

HAL HDA HFY HVN IAW IBE IYE JAI JST KAL KLM MAS MAU

MEA MNB MON MSR OBS OHY OMA PAL QAF QFA QTR RJA RSF

RSY SAA SAI SAS SIA SVA SWR TAE TAM TAP TAX TCX THA

THY TNA TOW TPA TSC UAE UAF USA VIR VKG VOZ WRC XAX

XLF

CONCURRENT REQUIREMENTS

**CONF 001

Accomplishment of this Service Bulletin requires the prior or simultaneous accomplishment of the

following Service Bulletins:

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 2

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@A330

SERVICE BULLETIN

SUMMARY

Service Bulletin No. A330-25-3213

A330-25-3254

NOTE: Service Bulletin No. A330-25-3213 (EQUIPMENT/FURNISHINGS - PAX

COMPARTMENT - MODIFY CDLS WIRING LOOM IN UPPER COCKPIT DOOR

PLATE COVER) which applies Modification No. 51911D44499.

NOTE: Service Bulletin No. A330-25-3213 is valid for all aircraft in the effectivity of this Service

Bulletin which have not embodied Modification No. 52869D44765 or Modification No.

53292D44777.

NOTE: Service Bulletin No. A330-25-3254 (EQUIPMENT/FURNISHINGS - PASSENGER

COMPARTMENT - INTRODUCE NOISE REDUCED COMPONENTS FOR CDLS) which

applies Modification No. 51721D44341, 52230D44532, and 52652D44690.

NOTE: The operator must check the aircraft records to determine which of the above

information is applicable.

**CONF 002 thru 003

None

REFERENCES / REPERCUSSIONS

**CONF ALL

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 253534-831-848-001: Modification

TOTAL MANHOURS 7.00

ELAPSED TIME (HOURS) 7.00

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 3

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@A330

SERVICE BULLETIN

SUMMARY

**CONF 002

Task 253534-831-848-001: Modification

TOTAL MANHOURS 8.75

ELAPSED TIME (HOURS) 8.75

**CONF 003

Task 253534-831-848-001: Modification

TOTAL MANHOURS 6.00

ELAPSED TIME (HOURS) 6.00

APPENDICES

**CONF ALL

None

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 4

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@A330

SERVICE BULLETIN

SUMMARY

**CONF 001

A

FR11

FR16A

B

A

Z220

B

FR11

FR11A

G_SB_253534_6_SAAA_01_03

Figure A-GSAAA - Sheet 01

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 5

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@A330

SERVICE BULLETIN

SUMMARY

**CONF 002

A

FR11

FR16A

B

A

Z220

B

FR11

FR11A

G_SB_253534_6_SAAB_01_03

Figure A-GSAAB - Sheet 01

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 6

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@A330

SERVICE BULLETIN

SUMMARY

**CONF 003

A

FR11

FR16A

B

A

Z220

B

FR11

FR11A

G_SB_253534_6_SAAC_01_03

Figure A-GSAAC - Sheet 01

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 7

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SERVICE BULLETIN

SUMMARY

This Page Intentionally Left Blank

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 8

6

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@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 - CURTAINS AND PARTITIONS -

INTRODUCE MODIFIED ELECTRICAL BONDING OF COCKPIT DOOR.

MODIFICATION No.: 203228D50684 203229D61659 203371D48094

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

This modification is applicable by Service Bulletin only.

(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 0064-0066 0070-0072

0082-0083 0086-0087 0095-0096 0098-0099 0102 0106 0109 0111-0113 0116 0118

0120-0122 0127 0132 0138 0140 0143-0144 0148 0153 0155 0162 0165 0171-0172

0177 0181 0183-0184 0188-0189 0191 0195 0198 0200 0203 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

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

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

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SERVICE BULLETIN

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 1274-1399 1406

(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

18P 1321

38W 0401

39V 0874 0939

43P 1053

44W 0970

83V 0353 0362

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

AAW 0999 1043

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

AIB 0345 0437 0451 0871

ALK 0303 0306 0311 0313 0404 0456 0627

ARA 0891 0927

ARG 0290 0300 0358 0364

ASY 0747 0951 0969 1036 1183

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

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SERVICE BULLETIN

OPERATOR MSN

AVA 0948 0967 1009 1016 1073 1208 1224 1279 1342

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

AZU 0365 0372 0462 0494 0527 0532

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

BGH 0255

CAL 0602 0607 0641 0671 0675 0691 0699 0707 0714 0725 0752 0769

0805 0823 0838 0861 0920 1177 1272 1278 1346 1367

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

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

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

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

CRK 1031 1034 1039 1042 1051 1054 1059 1062 1115 1175 1277 1286

1320 1322 1358 1384 1398

CRL 0285 0320 1359 1376

CSA 0425

CSC 1082 1138 1241 1397

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

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 0330 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

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

FWI 0253 0758 0965 1021 1265

G8E 0184 0189 0191

GFA 0276 0281 0286 0287 0334 0340

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 3

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@A330

SERVICE BULLETIN

OPERATOR MSN

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

1261 1288 1364

GRL 0230

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

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

0479 0512 0581 0669 0673

HFY 0096 0127 0211 0262 1008

HVN 0275 0294 0299 0366 0943 0946 0962 1019 1256 1266

IAW 1339

IBE 1377 1385

IYE 0625 0632

JAI 0923 0947 0956 1351 1361 1370 1391

JST 0842 0853 0945

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

MAS 0116 1136 1148 1164 1180 1209 1219 1229 1234 1243 1281 1318

1336 1337 1347 1388 1395

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

OBS 0802

OHY 0072 0087 0098 0143

OMA 1038 1044 1049 1063 1093 1120 1227

PAL 0183 0188 0198 0200 0203

QAF 0487 0605

QFA 0506 0508 0513 0522 0553 0558 0564 0574 0593 0595 0603 0695

0705 0712 0887 0892 0898 0940 0976 1061 1094 1169 1174 1198

1251 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 0979 1002

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

SVA 1108 1127 1137 1141 1147 1153 1189 1192

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

1355

TAE 0348

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 4

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@A330

SERVICE BULLETIN

OPERATOR MSN

TAM 0232 0238 0247 0259 0361 0466 0472 0700 0968 1112 1118 1213

1221

TAP 0181 0195 0223 0305 0308 0312 0317 0477 0486 0877 0899 0904

0914 0934

TAX 0692

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

THY 0463 0504 0529 0697 0704 0742 0754 0774 0869 0876 0882 0901

0932 0949 0961 0977 1004 1092 1150 1160 1170 1172 1204 1212

1228 1240 1298 1307 1311 1344

TNA 1357 1378

TOW 1033 1046 1248 1275 1312 1334 1363 1390

TPA 1368 1380

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

VIR 1195 1201 1206 1215 1231 1296 1315 1329 1341 1352

VKG 0309 0349 0356 0357

VOZ 1293 1306 1319

WRC 0296

XAX 0054 0654 0662 0716 0741 0786 0952 0974 1048 1066 1075 1126

1131 1165

XLF 0501 0635 1360

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SERVICE BULLETIN

(4) Configuration by MSN

MSN CONFIGURATION

0012 0017 0030 0037 0045 0050 0054 0055 0060 0062 0064

0065 0066 0070 0071 0072 0082 0083 0086 0087 0095 0096

0098 0099 0102 0106 0109 0111 0112 0113 0116 0118 0120

0121 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 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 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 0729 0730 0733

0734 0737 0738 0739 0741 0742 0743 0745 0746 0747 0749

0750 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 0809 0810 0811 0813 0814 0815 0817 0818 0819

0820 0822 0823 0824 0826 0827 0828 0830 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 0868 0869 0871 0873 0874 0875 0876

0879 0881 0884 0889 0890 0891 0893 0895 0896 0900 0903

0905 0906 0907 0908 0909 0911 0913 0915 0918 0919 0920

0922 0925 0926 0927 0928 0930 0931 0935 0936 0937 0939

0940 0941 0942 0943 0944 0945 0946 0948 0949 0950 0951

0952 0954 0957 0958 0959 0961 0962 0963 0964 0965 0966

001

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

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SERVICE BULLETIN

MSN CONFIGURATION

0967 0968 0969 0970 0971 0973 0974 0975 0977 0978 0979

0980 0982 0983 0984 0985 0986 0988 0989 0990 0991 0992

0995 0996 0997 0998 0999 1000 1001 1002 1003 1004 1006

1008 1009 1010 1011 1012 1014 1015 1016 1018 1019 1020

1021 1022 1025 1026 1028 1029 1031 1032 1033 1034 1035

1036 1037 1038 1039 1041 1042 1043 1044 1045 1046 1047

1048 1049 1052 1053 1054 1055 1058 1059 1060 1061 1063

1065 1066 1069 1070 1071 1072 1073 1074 1075 1076 1077

1080 1081 1084 1085 1086 1087 1089 1090 1092 1093 1094

1095 1096 1097 1098 1099 1100 1101 1103 1104 1105 1106

1107 1108 1110 1112 1114 1116 1118 1120 1123 1124 1126

1127 1129 1130 1131 1132 1133 1135 1137 1141 1143 1145

1146 1147 1149 1150 1151 1153 1155 1156 1157 1159 1160

1161 1163 1165 1167 1168 1169 1170 1171 1172 1174 1177

1178 1181 1183 1184 1186 1187 1188 1189 1190 1192 1193

1195 1196 1198 1199 1200 1201 1202 1203 1204 1205 1206

1208 1211 1212 1213 1214 1215 1216 1217 1218 1220 1221

1222 1224 1225 1226 1227 1228 1230 1231 1232 1233 1235

1237 1238 1239 1240 1244 1245 1246 1247 1248 1250 1251

1252 1255 1256 1258 1259 1260 1261 1263 1264 1265 1266

1269 1270 1272 1275 1276 1277 1278 1279 1282 1283 1284

1285 1286 1287 1288 1289 1290 1292 1293 1294 1295 1296

1297 1298 1299 1300 1301 1302 1304 1305 1306 1307 1308

1309 1310 1311 1312 1313 1314 1315 1316 1317 1319 1321

1322 1323 1325 1326 1327 1328 1329 1330 1332 1333 1334

1335 1338 1339 1340 1341 1342 1343 1344 1345 1346 1348

1349 1352 1353 1354 1355 1356 1357 1358 1359 1360 1362

1363 1364 1365 1366 1367 1369 1371 1373 1374 1376 1378

1379 1381 1382 1383 1384 1387 1389 1390 1392 1393 1394

1396 1398 1399

001

0728 0732 0735 0751 0807 0821 0825 0831 0877 0882 0883

0885 0887 0888 0892 0898 0899 0901 0904 0914 0916 0923

0932 0934 0947 0956 0976 0994 1007 1013 1023 1057 1067

1078 1082 1088 1138 1173 1191 1209 1210 1219 1223 1229

1234 1236 1241 1243 1249 1254 1262 1267 1268 1271 1274

1280 1281 1291 1303 1318 1324 1331 1336 1337 1347 1351

1361 1370 1372 1375 1377 1385 1388 1391 1395 1397

002

1051 1062 1115 1136 1148 1164 1175 1180 1320 1350 1368

1380 1386 1406

003

(5) Configuration definition

**CONF 001

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

have installed the cockpit door via mod 50014D44099 or 58673D57209 and have

installed a reinforced partition structure via mod 50561S16638 or SB A330-25-3170 or

SB A330-25-3194.

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

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SERVICE BULLETIN

**CONF 002

Config. 002 is valid for all the aircraft given in the effectivity of this Service Bulletin which

have installed a damping device to the cockpit door via mod 51720D44340 and have

installed a reinforced partition structure via mod 50561S16638.

**CONF 003

Config. 003 is valid for all the aircraft given in the effectivity of this Service Bulletin which

have installed the cockpit curtain via mod 57042D48173 and have installed a reinforced

partition structure via mod 50561S16638.

(6) Material Effectivity

**CONF 001

MATERIAL QTY PER A/C SEE NOTES

Kit 253534D01R08 1

Component COMPD01 1 (1)

Consumable CMLD01 1

NOTE (1): Operators having Kit 253534D01R07 will require COMPD01.

**CONF 002

MATERIAL QTY PER A/C SEE NOTES

Kit 253534D01R08 1

Component COMPD01 1 (1)

Consumable CMLD01 1

NOTE (1): Operators having Kit 253534D01R07 will require COMPD01.

**CONF 003

MATERIAL QTY PER A/C SEE NOTES

Kit 253534D03R06 1

Component COMPD02 1 (1)

Consumable CMLD01 1

NOTE (1): Operators having Kit 253534D03R05 will require COMPD02.

**CONF ALL

B. CONCURRENT REQUIREMENTS

**CONF 001

Accomplishment of this Service Bulletin requires the prior or simultaneous accomplishment of

the following Service Bulletins:

Service Bulletin No. A330-25-3213

A330-25-3254

NOTE: Service Bulletin No. A330-25-3213 (EQUIPMENT/FURNISHINGS - PAX

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

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SERVICE BULLETIN

COMPARTMENT - MODIFY CDLS WIRING LOOM IN UPPER COCKPIT

DOOR PLATE COVER) which applies Modification No. 51911D44499.

NOTE: Service Bulletin No. A330-25-3213 is valid for all aircraft in the effectivity of

this Service Bulletin which have not embodied Modification No. 52869D44765

or Modification No. 53292D44777.

NOTE: Service Bulletin No. A330-25-3254 (EQUIPMENT/FURNISHINGS -

PASSENGER COMPARTMENT - INTRODUCE NOISE REDUCED

COMPONENTS FOR CDLS) which applies Modification No. 51721D44341,

52230D44532, and 52652D44690.

NOTE: The operator must check the aircraft records to determine which of the above

information is applicable.

**CONF 002 thru 003

None

**CONF ALL

C. REASON

(1) History

Airbus has identified a potential risk of electrical shocks in case of chafing at the cockpit

door. The electrical bonding of the cockpit door has to be improved in order to mitigate

this potential risk.

(2) Objective/Action

This Service Bulletin details the work necessary to improve the electrical bonding.

(3) Advantages

Accomplishment of this Service Bulletin improves the effectiveness of the electrical

bonding thus will contribute to prevent the risk of an electrical shock.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

**CONF 001

Task 253534-831-848-001: Modification

(1) Modify the Cockpit Door Frame Structure

(2) Install Bonding-Leads to the Upper Cockpit Door Frame

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SERVICE BULLETIN

**CONF 002

Task 253534-831-848-001: Modification

(1) Modify the Cockpit Door Frame Structure

(2) Install Bonding-Leads to the Upper Cockpit Door Frame

**CONF 003

Task 253534-831-848-001: Modification

(1) Modify the Cockpit Door Frame Structure

(2) Install Bonding-Leads to the Upper Cockpit Door Frame

**CONF ALL

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

(2) Accomplishment Timescale

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.

The corresponding EASA AD 2015-0037 was released on Mar 02/15. The compliance

time is 24 months, starting from AD Effective Date of Mar 16/15.

F. APPROVAL

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

Organisation Approval No. EASA.21J.031.

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

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

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

before incorporation of the Service Bulletin.

G. MANPOWER

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

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

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

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

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

included.

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

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SERVICE BULLETIN

**CONF 001

Task 253534-831-848-001: Modification

Get Access 1.00

On Aircraft

Modify the Cockpit Door Frame Structure 3.50

Install Bonding-Leads to the Upper Cockpit Door

Frame

1.00

Tests 0.50

Close-Up 1.00

TOTAL MANHOURS 7.00

ELAPSED TIME (HOURS) 7.00

**CONF 002

Task 253534-831-848-001: Modification

Get Access 1.00

On Aircraft

Modify the Cockpit Door Frame Structure 3.75

Install Bonding-Leads to the Upper Cockpit Door

Frame

2.50

Tests 0.50

Close-Up 1.00

TOTAL MANHOURS 8.75

ELAPSED TIME (HOURS) 8.75

**CONF 003

Task 253534-831-848-001: Modification

Get Access 1.00

On Aircraft

Modify the Cockpit Door Frame Structure 2.00

Install Bonding-Leads to the Upper Cockpit Door

Frame

1.50

Tests 0.50

Close-Up 1.00

TOTAL MANHOURS 6.00

ELAPSED TIME (HOURS) 6.00

**CONF ALL

H. WEIGHT AND BALANCE

The weight and balance estimates given in this Service Bulletin are based on the

Manufacturer’s Empty Weight (MEW) and do not include operator’s items. For the definition of

MEW and operator’s items, refer to the Weight and Balance Manual (WBM) Chapter 1-00-07.

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

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SERVICE BULLETIN

Manufacturers Empty Weight +0.246 KG (+0.5423 LB)

Effect on Balance +2.52 KGM (+18.227 LB.FT )

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

**CONF 001

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

11-00-00 12-34-24 20-21-11

20-21-15 20-28-00 25-13-44

25-13-46 25-23-42 52-51-00

52-51-11 52-51-15

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-32-20 20-33-00 20-33-30

20-51-20 20-55-00

Illustrated Parts Catalog (IPC) 52-51-01

Standards Manual (SM)

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

51-44-00 51-75-12

Weight and Balance Manual (WBM) Chapter 1-00-07

**CONF 002

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

11-00-00 12-34-24 20-21-11

20-21-15 20-28-00 25-13-44

25-13-46 25-23-42 52-51-00

52-51-11 52-51-15

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-32-20 20-33-00 20-33-30

20-51-20 20-55-00

Illustrated Parts Catalog (IPC) 52-51-01

Standards Manual (SM)

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

51-44-00 51-75-12

Weight and Balance Manual (WBM) Chapter 1-00-07

**CONF 003

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

11-00-00 12-34-24 20-21-11

20-21-15 20-28-00 25-13-44

25-13-46 25-23-42 25-26-41

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-32-20 20-33-00 20-33-30

20-51-20 20-55-00

Standards Manual (SM)

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SERVICE BULLETIN

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

51-44-00 51-75-12

Weight and Balance Manual (WBM) Chapter 1-00-07

**CONF ALL

K. PUBLICATION AFFECTED

Aircraft Maintenance Manual (AMM) 52-51-00 52-51-11

Illustrated Parts Catalog (IPC) 25-81-01 52-51-01

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

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SERVICE BULLETIN

This Page Intentionally Left Blank

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SERVICE BULLETIN

2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

This Service Bulletin is the subject of an AIRBUS monitored retrofit campaign.

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:

Kit 253534D01R08

Kit 253534D03R06

AIRBUS Material, Logistics and Suppliers

Weg beim Jaeger 150

D-22335 Hamburg

Germany

For ordering by internet:

http://spares.airbus.com

For ordering by fax: +49 40 50 76 2590

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

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 COMPD01

Component COMPD02

AIRBUS Material, Logistics and Suppliers

Standard Parts Business

Weg beim Jaeger 150

D-22335 HAMBURG

GERMANY

For ordering by internet:

http://spares.airbus.com

For ordering by E-mail:

standard.parts@airbus.com

(2) Price and Availability

This table shows the component kits COMP needed to update the kits already held in

your stock to the latest status.

KIT HELD BY OPERATOR COMP KIT REQUIRED LATEST STATUS OF KIT

253534D01R07 COMPD01 253534D01R08

253534D03R05 COMPD02 253534D03R06

Operator supplied standard hardware parts required to accomplish this Service Bulletin

are to be supplied from Operator‘s stock.

Kit 253534D01R08

Cost 765.00 USD

Availability 90 calendar days from receipt of order

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

order. If items are required before this time, please include a retrofit planning schedule

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

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SERVICE BULLETIN

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

The latest valid price and lead time for ordering purposes shall be obtained through the

AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com.

Kit 253534D03R06

Cost 2,700.00 USD

Availability 90 calendar days from receipt of order

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

order. If items are required before this time, please include a retrofit planning schedule

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

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

The latest valid price and lead time for ordering purposes shall be obtained through the

AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com.

B. INDUSTRY SUPPORT INFORMATION

For aircraft under warranty at Jan 01/12, AIRBUS will credit the manhours indicated in this

Service Bulletin at the agreed in-house warranty labor rate for claims received not later than

90 days after completion of the last affected aircraft of your fleet and AIRBUS will provide the

kits (253534D01R08 and 253534D03R06) listed in paragraph 2.D at no charge for orders

placed before Mar 16/17.

For kits received per SB Revision No. 00 and 01:

- For those Operators having received kit 253534D01R07, parts listed in paragraph 2.D

(COMPD01) will be at no charge for orders placed before Mar 16/17.

- For those Operators having received kit 253534D03R05, parts listed in paragraph 2.D

(COMPD02) will be at no charge for orders placed before Mar 16/17.

This Service Bulletin is the subject of an AIRBUS monitored retrofit campaign.

For the organisation of this retrofit, you are kindly requested to contact AIRBUS retrofit

management department.

AIRBUS CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

France

Tel : (33) 5 67 19 06 22

E-mail : monitored.retrofit@airbus.com

Fax : (33) 5 61 93 27 45

C. LIST OF COMPONENTS

Kit 253534D01R08

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

NOTES

1 NAS1102-3-8 2 SCREW

2 NAS1102-08-10 6 SCREW

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

NOTES

5 NAS1096-3-12 1 SCREW

6 NSA5320-10 1 WASHER

7 ABS1577D54 1 BRACKET

8 ABS0547D503 2 RIVET

9 NAS1802-3-9 2 SCREW

10 ABS0916B05 0.6 (ME) TUBING

11 E0090-10-125NN 2 LEAD

12 NAS1802-3-7 4 SCREW

13 NAS1149C0332R 6 WASHER

14 F2529200920000 2 WASHER

15 NAS1726C3P 4 NUT

16 E0090-10-100NN 1 LEAD

18 F2529200700000 6 PLACARD

19 NAS1802-08-7 1 SCREW

20 NAS1149CN832R 1 WASHER

21 E0090-18-100NN 1 LEAD

22 E0090-18-200NN 1 LEAD

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

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

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

to part number relationship.

Kit 253534D03R06

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

NOTES

1 NAS1102-3-8 2 SCREW

9 NAS1802-3-9 2 SCREW

10 ABS0916B05 0.6 (ME) TUBING

11 E0090-10-125NN 1 LEAD

12 NAS1802-3-7 4 SCREW

13 NAS1149C0332R 6 WASHER

14 F2529200920000 2 WASHER

15 NAS1726C3P 2 NUT

17 E0090-10-200NN 2 LEAD

18 F2529200700000 5 PLACARD

19 NAS1102-08-6 4 SCREW

20 F2528707102800 1 BRACKET

21 F2528707102600 1 BRACKET

22 E0090-10-160NN 1 LEAD

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.

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D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Mineral Oil Base Grease 03FAB1 As required

Varnish - Electrical Bonding 04TMB2 As required

Polysulfide Sealant 06AAB1 As required

Non Aqueous Cleaner-General 08BAA9 As required

Textile-Lint Free Cotton 14SBA1 As required

(2) Components

Component COMPD01

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

NOTES

19 NAS1802-08-7 1 SCREW

20 NAS1149CN832R 1 WASHER

21 E0090-18-100NN 1 LEAD

22 E0090-18-200NN 1 LEAD

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: Operators having Kit 253534D01R07 will require COMPD01.

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

shall be ordered as necessary through the given channel.

Component COMPD02

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

NOTES

17 E0090-10-200NN LEAD

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: Operators having Kit 253534D03R05 will require COMPD02.

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

shall be ordered as necessary through the given channel.

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 18

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SERVICE BULLETIN

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

None

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

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This Page Intentionally Left Blank

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

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SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

Task 253534-831-848-001 - Modification

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

INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

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

THIS:

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

NECESSARY ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

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

NOTE: The accomplishment instructions of this Service Bulletin include procedures given

in other documents or in other sections of the Service Bulletin. When the words

"refer to" are used and the operator has a procedure accepted by the local

authority he belongs to, the accepted alternative procedure can be used. When the

words "in accordance with" are used then the given procedure must be followed.

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: May 27/14 SERVICE BULLETIN No.: A330-25-3534

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Task Associated Data

**CONF 001

Zone

220

Manpower

TOTAL MANHOURS 7.00

ELAPSED TIME (HOURS) 7.00

**CONF 002

Zone

220

Manpower

TOTAL MANHOURS 8.75

ELAPSED TIME (HOURS) 8.75

**CONF 003

Zone

220

Manpower

TOTAL MANHOURS 6.00

ELAPSED TIME (HOURS) 6.00

**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 253534-910-201-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

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

06-31-53, Page Block 001

06-41-53, Page Block 001

11-00-00, Page Block 201

Task 20-21-11-911-801

Task 20-21-15-912-801

20-28-00, Page Block 201

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-32-20

20-33-00

20-33-30

20-51-20

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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 Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

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

(c) For the identification of access panels, refer to AMM 06-41-53, Page Block 001.

(d) Tag all the parts you must remove and retain to make the subsequent installation

easier.

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

Consumable Materials List (CML).

(f) To torque tighten the standard threaded fasteners, refer to AMM Task

20-21-11-911-801.

(g) To torque tighten the electrical component fasteners, refer to AMM Task

20-21-15-912-801.

(h) For the electrical bonding, refer to ESPM 20-51-20 and AMM 20-28-00, Page Block

201.

(i) For the drilling of rivet holes:

- Use a soft lead pencil and make marks to show the position of the rivet holes.

- Make sure that you have the correct edge clearance before you drill the

fastener holes.

- If not shown otherwise the tolerance for rivet holes is + 0.1 mm (+ 0.004 in.).

- Transfer-drill the existing holes with a pilot drill and a drill bush.

- Drill new fastener holes with a pilot drill of 2.5 mm (0.098 in.) diameter.

Increase the hole diameter to the correct size for the fastener which you must

install.

- Deburr the holes after you have drilled them.

(j) Obtain fastener hole diameters and drill data in accordance with SRM 51-44-00.

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

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

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

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

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

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(o) For the identification of wire and wire harnesses, refer to ESPM 20-32-20.

(p) For the general installation of electrical wire harnesses, refer to ESPM 20-33-00.

(q) For the installation of the protective electrical conduits, refer to ESPM 20-33-30.

(r) For the installation of placards, refer to AMM 11-00-00, Page Block 201.

(2) Subtask 253534-839-201-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

**CONF 002

(1) Subtask 253534-910-201-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

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

06-31-53, Page Block 001

06-41-53, Page Block 001

11-00-00, Page Block 201

Task 20-21-11-911-801

Task 20-21-15-912-801

20-28-00, Page Block 201

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-32-20

20-33-00

20-33-30

20-51-20

Structural Repair Manual (SRM) 51-24-00

51-42-00

51-43-00

51-44-00

51-75-12

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

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

(c) For the identification of access panels, refer to AMM 06-41-53, Page Block 001.

(d) Tag all the parts you must remove and retain to make the subsequent installation

easier.

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

Consumable Materials List (CML).

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

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(f) To torque tighten the standard threaded fasteners, refer to AMM Task

20-21-11-911-801.

(g) To torque tighten the electrical component fasteners, refer to AMM Task

20-21-15-912-801.

(h) For the electrical bonding, refer to ESPM 20-51-20 and AMM 20-28-00, Page Block

201.

(i) For the drilling of rivet holes:

- Use a soft lead pencil and make marks to show the position of the rivet holes.

- Make sure that you have the correct edge clearance before you drill the

fastener holes.

- If not shown otherwise the tolerance for rivet holes is + 0.1 mm (+ 0.004 in.).

- Transfer-drill the existing holes with a pilot drill and a drill bush.

- Drill new fastener holes with a pilot drill of 2.5 mm (0.098 in.) diameter.

Increase the hole diameter to the correct size for the fastener which you must

install.

- Deburr the holes after you have drilled them.

(j) Obtain fastener hole diameters and drill data in accordance with SRM 51-44-00.

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

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

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

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

(o) For the identification of wire and wire harnesses, refer to ESPM 20-32-20.

(p) For the general installation of electrical wire harnesses, refer to ESPM 20-33-00.

(q) For the installation of the protective electrical conduits, refer to ESPM 20-33-30.

(r) For the installation of placards, refer to AMM 11-00-00, Page Block 201.

(2) Subtask 253534-839-201-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 25

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SERVICE BULLETIN

**CONF 003

(1) Subtask 253534-910-201-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

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

06-31-53, Page Block 001

06-41-53, Page Block 001

11-00-00, Page Block 201

Task 20-21-11-911-801

Task 20-21-15-912-801

20-28-00, Page Block 201

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-32-20

20-33-00

20-33-30

20-51-20

Structural Repair Manual (SRM) 51-24-00

51-42-00

51-43-00

51-44-00

51-75-12

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

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

(c) For the identification of access panels, refer to AMM 06-41-53, Page Block 001.

(d) Tag all the parts you must remove and retain to make the subsequent installation

easier.

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

Consumable Materials List (CML).

(f) To torque tighten the standard threaded fasteners, refer to AMM Task

20-21-11-911-801.

(g) To torque tighten the electrical component fasteners, refer to AMM Task

20-21-15-912-801.

(h) For the electrical bonding, refer to ESPM 20-51-20 and AMM 20-28-00, Page Block

201.

(i) For the drilling of rivet holes:

- Use a soft lead pencil and make marks to show the position of the rivet holes.

- Make sure that you have the correct edge clearance before you drill the

fastener holes.

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

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SERVICE BULLETIN

- If not shown otherwise the tolerance for rivet holes is + 0.1 mm (+ 0.004 in.).

- Transfer-drill the existing holes with a pilot drill and a drill bush.

- Drill new fastener holes with a pilot drill of 2.5 mm (0.098 in.) diameter.

Increase the hole diameter to the correct size for the fastener which you must

install.

- Deburr the holes after you have drilled them.

(j) Obtain fastener hole diameters and drill data in accordance with SRM 51-44-00.

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

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

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

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

(o) For the identification of wire and wire harnesses, refer to ESPM 20-32-20.

(p) For the general installation of electrical wire harnesses, refer to ESPM 20-33-00.

(q) For the installation of the protective electrical conduits, refer to ESPM 20-33-30.

(r) For the installation of placards, refer to AMM 11-00-00, Page Block 201.

(2) Subtask 253534-839-201-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

**CONF ALL

B. PREPARATION

**CONF 001

(1) Subtask 253534-941-201-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

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

Task 25-13-44-000-801

Task 25-13-46-000-801

Task 25-23-42-000-801

Task 25-23-42-000-808

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

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SERVICE BULLETIN

NOTE: The items given in this note 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.

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

12-34-24-860-802.

(b) Remove the ceiling panel 221AC, refer to AMM Task 25-23-42-000-801 or AMM

Task 25-23-42-000-808.

(c) Remove the ceiling panel 211LC and 211MC, refer to AMM Task

25-13-44-000-801.

(d) Based on aircraft configuration, if installed, remove coat stowage, refer to AMM

Task 25-13-46-000-801.

NOTE: Please be informed that complete removal of the coat stowage is

not necessary, only moving the parts enough to access the zone to

be worked in.

**CONF 002

(1) Subtask 253534-941-201-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

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

Task 25-13-44-000-801

Task 25-13-46-000-801

Task 25-23-42-000-801

Task 25-23-42-000-808

NOTE: The items given in this note shall be considered as the basic Aircraft

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

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SERVICE BULLETIN

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.

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

12-34-24-860-802.

(b) Remove the ceiling panel 221AC, refer to AMM Task 25-23-42-000-801 or AMM

Task 25-23-42-000-808.

(c) Remove the ceiling panel 211LC and 211MC, refer to AMM Task

25-13-44-000-801.

(d) Based on aircraft configuration, if installed, remove coat stowage, refer to AMM

Task 25-13-46-000-801.

NOTE: Please be informed that complete removal of the coat stowage is

not necessary, only moving the parts enough to access the zone to

be worked in.

**CONF 003

(1) Subtask 253534-941-201-002 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

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

Task 25-13-44-000-801

Task 25-13-46-000-801

Task 25-23-42-000-808

NOTE: The items given in this note shall be considered as the basic Aircraft

configuration before you start a maintenance task:

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- 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.

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

12-34-24-860-802.

(b) Remove the ceiling panel 221AC, refer to AMM Task 25-23-42-000-808.

(c) Remove the ceiling panel 211LC and 211MC, refer to AMM Task

25-13-44-000-801.

(d) Based on aircraft configuration, if installed, remove coat stowage, refer to AMM

Task 25-13-46-000-801.

NOTE: Please be informed that complete removal of the coat stowage is

not necessary, only moving the parts enough to access the zone to

be worked in.

**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 253534-831-201-001 - Modify the Cockpit Door Frame Structure

Work Zones and Access Panels

Zone Access/Work location

220

Manpower Resources

Manhours 3.50

Minimum number of person 1

Subtask elapsed time 3.50

Skills AIRFRAME

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Material necessary to do the job

Kit 253534D01R08

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 NAS1102-3-8 2 SCREW

2 NAS1102-08-10 6 SCREW

5 NAS1096-3-12 1 SCREW

6 NSA5320-10 1 WASHER

7 ABS1577D54 1 BRACKET

8 ABS0547D503 2 RIVET

18 F2529200700000 6 PLACARD

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Mineral Oil Base Grease 03FAB1 As required

Varnish - Electrical Bonding 04TMB2 As required

Polysulfide Sealant 06AAB1 As required

Non Aqueous CleanerGeneral08BAA9 As required

Textile-Lint Free Cotton 14SBA1 As required

References

Aircraft Maintenance Manual (AMM) Task 52-51-00-710-803

Task 52-51-15-000-801

Task 52-51-15-400-801

Illustrated Parts Catalog (IPC) 52-51-01

Fig. A-GBAAA

Prepare the bonding points at the wire

protection

Sheet 01

Sheet 02

Sheet 03

Fig. A-GBBAA

Install the bracket at the pelmet

Sheet 01

Sheet 02

Sheet 03

Fig. A-GBCAA

Prepare the bonding points at the door

posts

Sheet 01

Sheet 02

Sheet 03

Fig. A-GBEAA

Prepare the bonding points at the webs

Sheet 01

Sheet 02

Sheet 03

(a) Remove the keypad from the gap cover, refer to AMM Task 52-51-15-000-801.

(b) Loosen the nuts and carefully remove the wire harness from the wire protection as

shown on Fig. A-GBAAA Sheet 02, View C.

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(c) Modify the wire protection as follows:

1 Prepare the bonding point at the front side of the wire protection:

a Mark the position of the bonding point as shown on Fig. A-GBAAA Sheet

03, View D.

b Drill a pilot hole to a diameter of 2.5 mm (0.1 in.).

c Remove the metal surface protection to a diameter of 12.5 mm (0.49 in.)

as shown on Fig. A-GBAAA Sheet 03, View D.

d Drill the hole to a final diameter of 5.1 mm (0.2 in.) as shown on Fig. AGBAAA Sheet 03, View D.

2 Prepare the bonding point at the upper side of the wire protection:

a Mark the position of the bonding point as shown on Fig. A-GBAAA Sheet

03, View E.

b Drill a pilot hole to a diameter of 2.5 mm (0.1 in.).

c Remove the metal surface protection to a diameter of 12.5 mm (0.49 in.)

as shown on Fig. A-GBAAA Sheet 03, View E.

d Drill the hole to a final diameter of 5.1 mm (0.2 in.) as shown on Fig. AGBAAA Sheet 03, View E.

3 Clean the bonding points with:

Non Aqueous

Cleaner-General

08BAA9 As required

Textile-Lint Free

Cotton

14SBA1 As required

4 Apply to the bonding points a thin coat of:

Mineral Oil Base

Grease

03FAB1 As required

NOTE: The application of the grease is only necessary if you can

not install the bonding leads (SUBTASK 253534-831-203 001

Install Bonding-Leads to the Upper Cockpit Door Frame ) in

the next 4 hours.

5 Install as shown on Fig. A-GBAAA Sheet 02, View C:

1 Placard F2529200700000 Item 18

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(d) Modify the door posts as follows:

1 Prepare the bonding point at the LH door post:

a Remove as shown on Fig. A-GBCAA Sheet 02, View E:

1 Screw Item (1) Discard

b Remove the surface protection around the screw hole to a diameter

approximately 3 mm (0.12 in.) larger than the countersink diameter as

shown on Fig. A-GBCAA Sheet 02, View F.

c Install as shown on Fig. A-GBCAA Sheet 02, View F:

1 Screw NAS1102-3-8 Item 1

d Apply to the screw, item 1 as shown on Fig. A-GBCAA Sheet 02, View F:

Varnish - Electrical

Bonding

04TMB2 As required

2 Prepare the bonding points at the RH door post:

a Remove as shown on Fig. A-GBCAA Sheet 02, View E:

1 Screw Item (1) Discard

b Remove the surface protection around the screw hole to a diameter

approximately 3 mm (0.12 in.) larger than the countersink diameter as

shown on Fig. A-GBCAA Sheet 02, View F.

c Install as shown on Fig. A-GBCAA Sheet 02, View F:

1 Screw NAS1102-3-8 Item 1

d Remove as shown on Fig. A-GBCAA Sheet 03, View G:

6 Screw Item (2) Discard

1 Gap Cover Item (3) Retain

1 Door Frame Panel Item (4) Retain

NOTE: This SB illustration is a principal sketch and should be

used as reference only.

NOTE: For the PN of the gap cover, item (3) and the door frame

panel, item (4), refer to IPC 52-51-01.

e Remove as shown on Fig. A-GBCAA Sheet 03, View H:

1 Screw Item (5) Discard

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1 Washer Item (6) Discard

f Remove the surface protection around the screw hole to a diameter

approximately 3 mm (0.12 in.) larger than the screw head diameter as

shown on Fig. A-GBCAA Sheet 03, View J.

g Install as shown on Fig. A-GBCAA Sheet 03, View J:

1 Screw NAS1096-3-12 Item 5

1 Washer NSA5320-10 Item 6

h Apply to the screws, item 1 and 5 as shown on Fig. A-GBCAA Sheet 02,

View F and Fig. A-GBCAA Sheet 03, View J:

Varnish - Electrical

Bonding

04TMB2 As required

i Install as shown on Fig. A-GBCAA Sheet 03, View G:

1 Gap Cover Item (3) Retained at

removal

1 Door Frame Panel Item (4) Retained at

removal

6 Screw NAS1102-08-10 Item 2

3 Install as shown on Fig. A-GBCAA Sheet 02, View C and D:

2 Placard F2529200700000 Item 18

(e) Install the bracket as follows:

1 Remove the surface protection from the contact area of the bracket, item 7 to

the pelmet as shown on Fig. A-GBBAA Sheet 02, View D.

2 Use the bracket, item 7 as template and mark the position of the holes as

shown on Fig. A-GBBAA Sheet 03, View E.

3

CAUTION: MAKE SURE THAT YOU DO NOT DRILL TO MORE THAN

A DEPTH OF 21 MM (0.83 IN.) TO AVOID DAMAGE TO

THE S_GLASS ON THE CABIN SIDE.

Drill pilot holes to a diameter of 2.5 mm (0.098 in.) and a depth of 21 mm-1

mm (0.83 in.-0.039 in.).

4 Drill the pilot holes to the final diameter of 4.1 mm (0.16 in.) and a depth of 21

mm-1 mm (0.83 in.-0.039 in.) as shown on Fig. A-GBBAA Sheet 03, Section

A-A.

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 34

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@A330

SERVICE BULLETIN

5 Deburr the holes.

6 Remove the surface protection around the rivet holes to a diameter

approximately 3 mm (0.12 in.) larger than the rivet head diameter as shown on

Fig. A-GBBAA Sheet 02, View D.

7 Clean the modification area with:

Non Aqueous

Cleaner-General

08BAA9 As required

Textile-Lint Free

Cotton

14SBA1 As required

8 Install as shown on Fig. A-GBBAA Sheet 02, View D:

1 Bracket ABS1577D54 Item 7

2 Rivet ABS0547D503 Item 8

9 Apply to the rivets, item 8 and to the edges of the bracket, item 7 as shown on

Fig. A-GBBAA Sheet 03, Section A-A:

Polysulfide Sealant 06AAB1 As required

Varnish - Electrical

Bonding

04TMB2 As required

10 Install as shown on Fig. A-GBBAA Sheet 02, View C:

1 Placard F2529200700000 Item 18

(f) Modify the webs as follows:

1 Prepare the bonding points at the RH web:

a Mark the position of the bonding point as shown on Fig. A-GBEAA Sheet

02, View D.

b Drill a pilot hole to a diameter of 2.5 mm (0.1 in.).

c Remove the metal surface protection to a diameter of 17 mm (0.7 in.) as

shown on Fig. A-GBEAA Sheet 02, View D.

d Drill the hole to a final diameter of 5.1 mm (0.2 in.) as shown on Fig. AGBEAA Sheet 02, View D.

e Install as shown on Fig. A-GBEAA Sheet 02, View D:

1 Placard F2529200700000 Item 18

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 35

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@A330

SERVICE BULLETIN

2 Prepare the bonding points at the LH web:

a Mark the position of the bonding point as shown on Fig. A-GBEAA Sheet

03, View F.

b Drill a pilot hole to a diameter of 2.5 mm (0.1 in.).

c Remove the metal surface protection to a diameter of 17 mm (0.7 in.) as

shown on Fig. A-GBEAA Sheet 03, View F.

d Drill the hole to a final diameter of 5.1 mm (0.2 in.) as shown on Fig. AGBEAA Sheet 03, View F.

e Install as shown on Fig. A-GBEAA Sheet 03, View F:

1 Placard F2529200700000 Item 18

3 Clean the bonding points with:

Non Aqueous

Cleaner-General

08BAA9 As required

Textile-Lint Free

Cotton

14SBA1 As required

4 Apply to the bonding points a thin coat of:

Mineral Oil Base

Grease

03FAB1 As required

NOTE: The application of the grease is only necessary if you can

not install the bonding leads (SUBTASK 253534-831-203 001

Install Bonding-Leads to the Upper Cockpit Door Frame ) in

the next 4 hours.

(g) Install the keypad to the gap cover, refer to AMM Task 52-51-15-400-801.

(h) Do the operational test of the cockpit door emergency access, refer to AMM Task

52-51-00-710-803.

(2) Subtask 253534-831-203-001 - Install Bonding-Leads to the Upper Cockpit Door

Frame

Work Zones and Access Panels

Zone Access/Work location

220

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 36

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@A330

SERVICE BULLETIN

Material necessary to do the job

Kit 253534D01R08

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 NAS1802-3-9 2 SCREW

10 ABS0916B05 0.6 TUBING

11 E0090-10-125NN 2 LEAD

12 NAS1802-3-7 4 SCREW

13 NAS1149C0332R 6 WASHER

14 F2529200920000 2 WASHER

15 NAS1726C3P 4 NUT

16 E0090-10-100NN 1 LEAD

19 NAS1802-08-7 1 SCREW

20 NAS1149CN832R 1 WASHER

21 E0090-18-100NN 1 LEAD

22 E0090-18-200NN 1 LEAD

Component COMPD01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

19 NAS1802-08-7 1 SCREW

20 NAS1149CN832R 1 WASHER

21 E0090-18-100NN 1 LEAD

22 E0090-18-200NN 1 LEAD

NOTE: Operators having Kit 253534D01R07 will require COMPD01.

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

shall be ordered as necessary through the given channel.

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Varnish - Electrical Bonding 04TMB2 As required

Non Aqueous CleanerGeneral08BAA9 As required

Textile-Lint Free Cotton 14SBA1 As required

References

Aircraft Maintenance Manual (AMM) Task 52-51-11-820-801

Fig. A-GBDAA

Install the bonding-leads at the upper

door frame

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 37

6

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@A330

SERVICE BULLETIN

(a) Install the bonding-leads at the RH door post as follows:

1 Remove as shown on Fig. A-GBDAA Sheet 03, View E:

1 Screw Item (1) Discard

2 Remove the surface protection around the screw hole to a diameter

approximately 3 mm (0.12 in.) larger than the diameter of the washer, item 14

as shown on Fig. A-GBDAA Sheet 03, View F.

3 Clean the bonding points at the wire protection and the door post with:

Non Aqueous

Cleaner-General

08BAA9 As required

Textile-Lint Free

Cotton

14SBA1 As required

4 Cut two pieces of tubing to a length of 0.11 m (4.33 in.) from:

0.6 Tubing ABS0916B05 Item 10

5 Push the tubings, item 10 over the bonding-leads, item 11 and shrink them.

6 Install at the door post as shown on Fig. A-GBDAA Sheet 03, View F:

2 Bonding-Lead E0090-10-125NN Item 11

1 Screw NAS1802-3-9 Item 9

1 Washer NAS1149C0332R Item 13

1 Washer F2529200920000 Item 14

NOTE: The bonding lead length may be adapted if necessary.

7 Attach the bonding-lead, item 11 to the wire protection as shown on Fig. AGBDAA Sheet 03, View F with:

1 Screw NAS1802-3-7 Item 12

1 Washer NAS1149C0332R Item 13

1 Nut NAS1726C3P Item 15

8 Clean the bonding point at the web with:

Non Aqueous

Cleaner-General

08BAA9 As required

Textile-Lint Free

Cotton

14SBA1 As required

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 38

6

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@A330

SERVICE BULLETIN

9 Attach the bonding-lead, item 11 to the web as shown on Fig. A-GBDAA

Sheet 05, View J with:

1 Screw NAS1802-3-7 Item 12

1 Washer NAS1149C0332R Item 13

1 Nut NAS1726C3P Item 15

10 Apply to the Screw, item 12 and the nut, item 15 as shown on Fig. A-GBDAA

Sheet 05, View J:

Varnish - Electrical

Bonding

04TMB2 As required

11 Apply to the Screws, item 9 and 12 and the nut, item 15 as shown on Fig. AGBDAA Sheet 03, View F:

Varnish - Electrical

Bonding

04TMB2 As required

(b) Install the bonding-leads at the LH door post as follows:

1 Remove as shown on Fig. A-GBDAA Sheet 04, View G:

1 Screw Item (1) Discard

2 Remove the surface protection around the screw hole to a diameter

approximately 3 mm (0.12 in.) larger than the diameter of the washer, item 14

as shown on Fig. A-GBDAA Sheet 04, View H.

3 Make sure that there is no surface protection at the bonding point from the

bracket.

4 Clean the bonding points at the wire protection, the bracket and the door post

with:

Non Aqueous

Cleaner-General

08BAA9 As required

Textile-Lint Free

Cotton

14SBA1 As required

5 Cut two pieces of tubing to a length of 0.085 m (3.35 in.) and one piece to a

length of 0.185 m (7.28 in.) from:

0.6 Tubing ABS0916B05 Item 10

6 Push the tubings, item 10 over the bonding-leads, item 16, 21 and 22 and

shrink them.

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 39

6

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@A330

SERVICE BULLETIN

7 Install at the door post as shown on Fig. A-GBDAA Sheet 04, View H:

1 Bonding-Lead E0090-10-100NN Item 16

1 Bonding Lead E0090-18-200NN Item 22

1 Screw NAS1802-3-9 Item 9

1 Washer NAS1149C0332R Item 13

1 Washer F2529200920000 Item 14

For operators with Kit 253534D01R07, get this item from COMPD01:

1 Bonding Lead E0090-18-200NN Item 22

NOTE: The bonding lead length may be adapted if necessary.

8 Attach the bonding-lead, item 22, to the bracket as shown on Fig. A-GBDAA

Sheet 04, View H with:

1 Bonding Lead E0090-18-100NN Item 21

1 Screw NAS1802-08-7 Item 19

1 Washer NAS1149CN832R Item 20

For operators with Kit 253534D01R07, get these items from COMPD01:

1 Bonding Lead E0090-18-100NN Item 21

1 Screw NAS1802-08-7 Item 19

1 Washer NAS1149CN832R Item 20

9 Attach the bonding-lead, item 21, to the wire protection as shown on Fig. AGBDAA Sheet 04, View H with:

1 Screw NAS1802-3-7 Item 12

1 Washer NAS1149C0332R Item 13

1 Nut NAS1726C3P Item 15

10 Clean the bonding point at the web with:

Non Aqueous

Cleaner-General

08BAA9 As required

Textile-Lint Free

Cotton

14SBA1 As required

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 40

6

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@A330

SERVICE BULLETIN

11 Attach the bonding-lead, item 16 to the web as shown on Fig. A-GBDAA

Sheet 05, View K with:

1 Screw NAS1802-3-7 Item 12

1 Washer NAS1149C0332R Item 13

1 Nut NAS1726C3P Item 15

12 Apply to the Screw, item 12 and the nut, item 15 as shown on Fig. A-GBDAA

Sheet 05, View K:

Varnish - Electrical

Bonding

04TMB2 As required

13 Apply to the Screws, item 9 and 12 and the nut, item 15 as shown on Fig. AGBDAA Sheet 04, View H:

Varnish - Electrical

Bonding

04TMB2 As required

(c) Install the wire harness to the wire protection as shown on Fig. A-GBDAA Sheet

06, View L.

(d) Make sure that cockpit door operates easily and closes correctly, refer to AMM

Task 52-51-11-820-801.

**CONF 002

(1) Subtask 253534-831-201-002 - Modify the Cockpit Door Frame Structure

Work Zones and Access Panels

Zone Access/Work location

220

Manpower Resources

Manhours 3.75

Minimum number of person 1

Subtask elapsed time 3.75

Skills AIRFRAME

Material necessary to do the job

Kit 253534D01R08

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 NAS1102-3-8 2 SCREW

2 NAS1102-08-10 6 SCREW

5 NAS1096-3-12 1 SCREW

6 NSA5320-10 1 WASHER

7 ABS1577D54 1 BRACKET

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 41

6

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

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 ABS0547D503 2 RIVET

18 F2529200700000 6 PLACARD

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Mineral Oil Base Grease 03FAB1 As required

Varnish - Electrical Bonding 04TMB2 As required

Polysulfide Sealant 06AAB1 As required

Non Aqueous CleanerGeneral08BAA9 As required

Textile-Lint Free Cotton 14SBA1 As required

References

Aircraft Maintenance Manual (AMM) Task 52-51-00-710-803

Task 52-51-11-000-802

Task 52-51-15-000-801

Task 52-51-15-400-801

Illustrated Parts Catalog (IPC) 52-51-01

Fig. A-GBAAB

Prepare the bonding points at the wire

protection

Sheet 01

Sheet 02

Sheet 03

Fig. A-GBBAB

Install the bracket at the pelmet

Sheet 01

Sheet 02

Sheet 03

Fig. A-GBCAB

Prepare the bonding points at the door

posts

Sheet 01

Sheet 02

Sheet 03

Fig. A-GBEAA

Prepare the bonding points at the webs

Sheet 01

Sheet 02

Sheet 03

(a) Remove the damper unit from the pelmet, refer to AMM Task 52-51-11-000-802.

(b) Remove the keypad from the gap cover, refer to AMM Task 52-51-15-000-801.

(c) Loosen the nuts and carefully remove the wire harness from the wire protection as

shown on Fig. A-GBAAB Sheet 02, View C.

(d) Modify the wire protection as follows:

1 Prepare the bonding point at the front side of the wire protection:

a Mark the position of the bonding point as shown on Fig. A-GBAAB Sheet

03, View D.

b Drill a pilot hole to a diameter of 2.5 mm (0.1 in.).

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 42

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@A330

SERVICE BULLETIN

c Remove the metal surface protection to a diameter of 12.5 mm (0.49 in.)

as shown on Fig. A-GBAAB Sheet 03, View D.

d Drill the hole to a final diameter of 5.1 mm (0.2 in.) as shown on Fig. AGBAAB Sheet 03, View D.

2 Prepare the bonding point at the upper side of the wire protection:

a Mark the position of the bonding point as shown on Fig. A-GBAAB Sheet

03, View E.

b Drill a pilot hole to a diameter of 2.5 mm (0.1 in.).

c Remove the metal surface protection to a diameter of 12.5 mm (0.49 in.)

as shown on Fig. A-GBAAB Sheet 03, View E.

d Drill the hole to a final diameter of 5.1 mm (0.2 in.) as shown on Fig. AGBAAB Sheet 03, View E.

3 Clean the bonding points with:

Non Aqueous

Cleaner-General

08BAA9 As required

Textile-Lint Free

Cotton

14SBA1 As required

4 Apply to the bonding points a thin coat of:

Mineral Oil Base

Grease

03FAB1 As required

NOTE: The application of the grease is only necessary if you can

not install the bonding leads (SUBTASK 253534-831-203 002

Install Bonding-Leads to the Upper Cockpit Door Frame ) in

the next 4 hours.

5 Install as shown on Fig. A-GBAAB Sheet 02, View C:

1 Placard F2529200700000 Item 18

(e) Modify the door posts as follows:

1 Prepare the bonding point at the LH door post:

a Remove as shown on Fig. A-GBCAB Sheet 02, View E:

1 Screw Item (1) Discard

b Remove the surface protection around the screw hole to a diameter

approximately 3 mm (0.12 in.) larger than the countersink diameter as

shown on Fig. A-GBCAB Sheet 02, View F.

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 43

6

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@A330

SERVICE BULLETIN

c Install as shown on Fig. A-GBCAB Sheet 02, View F:

1 Screw NAS1102-3-8 Item 1

d Apply to the screw, item 1 as shown on Fig. A-GBCAB Sheet 02, View F:

Varnish - Electrical

Bonding

04TMB2 As required

2 Prepare the bonding points at the RH door post:

a Remove as shown on Fig. A-GBCAB Sheet 02, View E:

1 Screw Item (1) Discard

b Remove the surface protection around the screw hole to a diameter

approximately 3 mm (0.12 in.) larger than the countersink diameter as

shown on Fig. A-GBCAB Sheet 02, View F.

c Install as shown on Fig. A-GBCAB Sheet 02, View F:

1 Screw NAS1102-3-8 Item 1

d Remove as shown on Fig. A-GBCAB Sheet 03, View G:

6 Screw Item (2) Discard

1 Gap Cover Item (3) Retain

1 Door Frame Panel Item (4) Retain

NOTE: This SB illustration is a principal sketch and should be

used as reference only.

NOTE: For the PN of the gap cover, item (3) and the door frame

panel, item (4), refer to IPC 52-51-01.

e Remove as shown on Fig. A-GBCAB Sheet 03, View H:

1 Screw Item (5) Discard

1 Washer Item (6) Discard

f Remove the surface protection around the screw hole to a diameter

approximately 3 mm (0.12 in.) larger than the screw head diameter as

shown on Fig. A-GBCAB Sheet 03, View J.

g Install as shown on Fig. A-GBCAB Sheet 03, View J:

1 Screw NAS1096-3-12 Item 5

1 Washer NSA5320-10 Item 6

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 44

6

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@A330

SERVICE BULLETIN

h Apply to the screws, item 1 and 5 as shown on Fig. A-GBCAB Sheet 02,

View F and Fig. A-GBCAB Sheet 03, View J:

Varnish - Electrical

Bonding

04TMB2 As required

i Install as shown on Fig. A-GBCAB Sheet 03, View G:

1 Gap Cover Item (3) Retained at

removal

1 Door Frame Panel Item (4) Retained at

removal

6 Screw NAS1102-08-10 Item 2

3 Install as shown on Fig. A-GBCAB Sheet 02, View C and D:

2 Placard F2529200700000 Item 18

(f) Install the bracket as follows:

1 Remove the surface protection from the contact area of the bracket, item 7 to

the pelmet as shown on Fig. A-GBBAB Sheet 02, View D.

2 Use the bracket, item 7 as template and mark the position of the holes as

shown on Fig. A-GBBAB Sheet 03, View E.

3

CAUTION: MAKE SURE THAT YOU DO NOT DRILL TO MORE THAN

A DEPTH OF 21 MM (0.83 IN.) TO AVOID DAMAGE TO

THE S_GLASS ON THE CABIN SIDE.

Drill pilot holes to a diameter of 2.5 mm (0.098 in.) and a depth of 21 mm-1

mm (0.83 in.-0.039 in.).

4 Drill the pilot holes to the final diameter of 4.1 mm (0.16 in.) and a depth of 21

mm-1 mm (0.83 in.-0.039 in.) as shown on Fig. A-GBBAB Sheet 03, Section

A-A.

5 Deburr the holes.

6 Remove the surface protection around the rivet holes to a diameter

approximately 3 mm (0.12 in.) larger than the rivet head diameter as shown on

Fig. A-GBBAB Sheet 02, View D.

7 Clean the modification areas with:

Non Aqueous

Cleaner-General

08BAA9 As required

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 45

6

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

SERVICE BULLETIN

Textile-Lint Free

Cotton

14SBA1 As required

8 Install as shown on Fig. A-GBBAB Sheet 02, View D:

1 Bracket ABS1577D54 Item 7

2 Rivet ABS0547D503 Item 8

9 Apply to the rivets, item 8 and to the edges of the bracket, item 7 as shown on

Fig. A-GBBAB Sheet 03, Section A-A:

Polysulfide Sealant 06AAB1 As required

Varnish - Electrical

Bonding

04TMB2 As required

10 Install as shown on Fig. A-GBBAB Sheet 02, View C:

1 Placard F2529200700000 Item 18

(g) Modify the webs as follows:

1 Prepare the bonding points at the RH web:

a Mark the position of the bonding point as shown on Fig. A-GBEAA Sheet

02, View D.

b Drill a pilot hole to a diameter of 2.5 mm (0.1 in.).

c Remove the metal surface protection to a diameter of 17 mm (0.7 in.) as

shown on Fig. A-GBEAA Sheet 02, View D.

d Drill the hole to a final diameter of 5.1 mm (0.2 in.) as shown on Fig. AGBEAA Sheet 02, View D.

e Install as shown on Fig. A-GBEAA Sheet 02, View D:

1 Placard F2529200700000 Item 18

2 Prepare the bonding points at the LH web:

a Mark the position of the bonding point as shown on Fig. A-GBEAA Sheet

03, View F.

b Drill a pilot hole to a diameter of 2.5 mm (0.1 in.).

c Remove the metal surface protection to a diameter of 17 mm (0.7 in.) as

shown on Fig. A-GBEAA Sheet 03, View F.

d Drill the hole to a final diameter of 5.1 mm (0.2 in.) as shown on Fig. AGBEAA Sheet 03, View F.

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 46

6

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

SERVICE BULLETIN

e Install as shown on Fig. A-GBEAA Sheet 03, View F:

1 Placard F2529200700000 Item 18

3 Clean the bonding points with:

Non Aqueous

Cleaner-General

08BAA9 As required

Textile-Lint Free

Cotton

14SBA1 As required

4 Apply to the bonding points a thin coat of:

Mineral Oil Base

Grease

03FAB1 As required

NOTE: The application of the grease is only necessary if you can

not install the bonding leads (SUBTASK 253534-831-203 002

Install Bonding-Leads to the Upper Cockpit Door Frame ) in

the next 4 hours.

(h) Install the keypad to the gap cover, refer to AMM Task 52-51-15-400-801.

(i) Do the operational test of the cockpit door emergency access, refer to AMM Task

52-51-00-710-803.

(2) Subtask 253534-831-203-002 - Install Bonding-Leads to the Upper Cockpit Door

Frame

Work Zones and Access Panels

Zone Access/Work location

220

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 253534D01R08

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 NAS1802-3-9 2 SCREW

10 ABS0916B05 0.6 TUBING

11 E0090-10-125NN 2 LEAD

12 NAS1802-3-7 4 SCREW

13 NAS1149C0332R 6 WASHER

14 F2529200920000 2 WASHER

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 47

6

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@A330

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

15 NAS1726C3P 4 NUT

16 E0090-10-100NN 1 LEAD

19 NAS1802-08-7 1 SCREW

20 NAS1149CN832R 1 WASHER

21 E0090-18-100NN 1 LEAD

22 E0090-18-200NN 1 LEAD

Component COMPD01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

19 NAS1802-08-7 1 SCREW

20 NAS1149CN832R 1 WASHER

21 E0090-18-100NN 1 LEAD

22 E0090-18-200NN 1 LEAD

NOTE: Operators having Kit 253534D01R07 will require COMPD01.

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

shall be ordered as necessary through the given channel.

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Varnish - Electrical Bonding 04TMB2 As required

Non Aqueous CleanerGeneral08BAA9 As required

Textile-Lint Free Cotton 14SBA1 As required

References

Aircraft Maintenance Manual (AMM) Task 52-51-11-400-802

Task 52-51-11-820-801

Fig. A-GBDAB

Install the bonding-leads at the upper

door frame

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Install the bonding-leads at the RH door post as follows:

1 Remove as shown on Fig. A-GBDAB Sheet 03, View E:

1 Screw Item (1) Discard

2 Remove the surface protection around the screw hole to a diameter

approximately 3 mm (0.12 in.) larger than the diameter of the washer, item 14

as shown on Fig. A-GBDAB Sheet 03, View F.

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 48

6

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@A330

SERVICE BULLETIN

3 Clean the bonding points at the wire protection and the door post with:

Non Aqueous

Cleaner-General

08BAA9 As required

Textile-Lint Free

Cotton

14SBA1 As required

4 Cut two pieces of tubing to a length of 0.11 m (4.33 in.) from:

0.6 Tubing ABS0916B05 Item 10

5 Push the tubings, item 10 over the bonding-leads, item 11 and shrink them.

6 Install at the door post as shown on Fig. A-GBDAB Sheet 03, View F:

2 Bonding-Lead E0090-10-125NN Item 11

1 Screw NAS1802-3-9 Item 9

1 Washer NAS1149C0332R Item 13

1 Washer F2529200920000 Item 14

NOTE: The bonding lead length may be adapted if necessary.

7 Attach the bonding-lead, item 11 to the wire protection as shown on Fig. AGBDAB Sheet 03, View F with:

1 Screw NAS1802-3-7 Item 12

1 Washer NAS1149C0332R Item 13

1 Nut NAS1726C3P Item 15

8 Clean the bonding point at the web with:

Non Aqueous

Cleaner-General

08BAA9 As required

Textile-Lint Free

Cotton

14SBA1 As required

9 Attach the bonding-lead, item 11 to the web as shown on Fig. A-GBDAB

Sheet 05, View J with:

1 Screw NAS1802-3-7 Item 12

1 Washer NAS1149C0332R Item 13

1 Nut NAS1726C3P Item 15

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 49

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SERVICE BULLETIN

10 Apply to the Screw, item 12 and the nut, item 15 as shown on Fig. A-GBDAB

Sheet 05, View J:

Varnish - Electrical

Bonding

04TMB2 As required

11 Apply to the Screws, item 9 and 12 and the nut, item 15 as shown on Fig. AGBDAB Sheet 03, View F:

Varnish - Electrical

Bonding

04TMB2 As required

(b) Install the bonding-leads at the LH door post as follows:

1 Remove as shown on Fig. A-GBDAB Sheet 04, View G:

1 Screw Item (1) Discard

2 Remove the surface protection around the screw hole to a diameter

approximately 3 mm (0.12 in.) larger than the diameter of the washer, item 14

as shown on Fig. A-GBDAB Sheet 04, View H.

3 Make sure that there is no surface protection at the bonding point from the

bracket.

4 Clean the bonding points at the wire protection, the bracket and the door post

with:

Non Aqueous

Cleaner-General

08BAA9 As required

Textile-Lint Free

Cotton

14SBA1 As required

5 Cut two pieces of tubing to a length of 0.085 m (3.35 in.) and one piece to a

length of 0.185 m (7.28 in.) from:

0.6 Tubing ABS0916B05 Item 10

6 Push the tubings, item 10 over the bonding-leads, item 16, 21 and 22 and

shrink them.

7 Install at the door post as shown on Fig. A-GBDAB Sheet 04, View H:

1 Bonding-Lead E0090-10-100NN Item 16

1 Bonding Lead E0090-18-200NN Item 22

1 Screw NAS1802-3-9 Item 9

1 Washer NAS1149C0332R Item 13

1 Washer F2529200920000 Item 14

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 50

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SERVICE BULLETIN

For operators with Kit 253534D01R07, get this item from COMPD01:

1 Bonding Lead E0090-18-200NN Item 22

NOTE: The bonding lead length may be adapted if necessary.

8 Attach the bonding-lead, item 22 to the bracket as shown on Fig. A-GBDAB

Sheet 04, View H with:

1 Bonding Lead E0090-18-100NN Item 21

1 Screw NAS1802-08-7 Item 19

1 Washer NAS1149CN832R Item 20

For operators with Kit 253534D01R07, get these items from COMPD01:

1 Bonding Lead E0090-18-100NN Item 21

1 Screw NAS1802-08-7 Item 19

1 Washer NAS1149CN832R Item 20

9 Attach the bonding-lead, item 21, to the wire protection as shown on Fig. AGBDAB Sheet 04, View H with:

1 Screw NAS1802-3-7 Item 12

1 Washer NAS1149C0332R Item 13

1 Nut NAS1726C3P Item 15

10 Clean the bonding point at the web with:

Non Aqueous

Cleaner-General

08BAA9 As required

Textile-Lint Free

Cotton

14SBA1 As required

11 Attach the bonding-lead, item 16 to the web as shown on Fig. A-GBDAB

Sheet 05, View K with:

1 Screw NAS1802-3-7 Item 12

1 Washer NAS1149C0332R Item 13

1 Nut NAS1726C3P Item 15

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 51

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SERVICE BULLETIN

12 Apply to the Screw, item 12 and the nut, item 15 as shown on Fig. A-GBDAB

Sheet 05, View K:

Varnish - Electrical

Bonding

04TMB2 As required

13 Apply to the Screws, item 9 and 12 and the nut, item 15 as shown on Fig. AGBDAB Sheet 04, View H:

Varnish - Electrical

Bonding

04TMB2 As required

(c) Install the wire harness to the wire protection as shown on Fig. A-GBDAB Sheet

06, View L.

(d) Install the damper unit to the pelmet, refer to AMM Task 52-51-11-400-802.

(e) Make sure that cockpit door operates easily and closes correctly, refer to AMM

Task 52-51-11-820-801.

**CONF 003

(1) Subtask 253534-831-201-004 - Modify the Cockpit Door Frame Structure

Work Zones and Access Panels

Zone Access/Work location

220

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

Material necessary to do the job

Kit 253534D03R06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

18 F2529200700000 3 PLACARD

19 NAS1102-08-6 4 SCREW

20 F2528707102800 1 BRACKET

21 F2528707102600 1 BRACKET

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Mineral Oil Base Grease 03FAB1 As required

Non Aqueous CleanerGeneral08BAA9 As required

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 52

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SERVICE BULLETIN

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Textile-Lint Free Cotton 14SBA1 As required

References

Aircraft Maintenance Manual (AMM) Task 25-26-41-000-801

Task 25-26-41-000-802

Fig. A-GBAAC

Remove curtain rail brackets

Sheet 01

Sheet 02

Fig. A-GBBAC

Install curtain rail bracket

Sheet 01

Sheet 02

Fig. A-GBEAC

Prepare the bonding points at the webs

Sheet 01

Sheet 02

Sheet 03

(a) Remove the curtain, refer to AMM Task 25-26-41-000-801.

(b) Remove the curtain rail, refer to AMM Task 25-26-41-000-802.

(c) Replace the curtain rail brackets as follows:

1 Remove as shown on Fig. A-GBAAC Sheet 02, View D:

4 Screw Item (19) Discard

2 Bracket Item (20) Discard

2 From the brackets, item 20 and 21 remove the surface protection to a

diameter of 12.5 mm (0.49 in.) as shown on Fig. A-GBBAC Sheet 02, Section

A-A.

3 Clean the bonding points with:

Non Aqueous

Cleaner-General

08BAA9 As required

Textile-Lint Free

Cotton

14SBA1 As required

4 Apply to the bonding points a thin coat of:

Mineral Oil Base

Grease

03FAB1 As required

NOTE: The application of the grease is only necessary if you can

not install the bonding leads (SUBTASK 253534-831-203 003

Install Bonding-Leads to the Upper Cockpit Door Frame ) in

the next 4 hours.

5 Install as shown on Fig. A-GBBAC Sheet 02, View E:

1 Bracket F2528707102800 Item 20

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 53

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SERVICE BULLETIN

2 Screw NAS1102-08-6 Item 19

6 Install as shown on Fig. A-GBBAC Sheet 02, View D:

1 Bracket F2528707102600 Item 21

2 Screw NAS1102-08-6 Item 19

7 Install as shown on Fig. A-GBBAC Sheet 02, View C:

1 Placard F2529200700000 Item 18

(d) Modify the webs as follows:

1 Prepare the bonding points at the RH web:

a Mark the position of the bonding point as shown on Fig. A-GBEAC Sheet

02, View D.

b Drill a pilot hole to a diameter of 2.5 mm (0.1 in.).

c Remove the metal surface protection to a diameter of 17 mm (0.7 in.) as

shown on Fig. A-GBEAC Sheet 02, View D.

d Drill the hole to a final diameter of 5.1 mm (0.2 in.) as shown on Fig. AGBEAC Sheet 02, View D.

e Install as shown on Fig. A-GBEAC Sheet 02, View D:

1 Placard F2529200700000 Item 18

2 Prepare the bonding points at the LH web:

a Mark the position of the bonding point as shown on Fig. A-GBEAC Sheet

03, View F.

b Drill a pilot hole to a diameter of 2.5 mm (0.1 in.).

c Remove the metal surface protection to a diameter of 17 mm (0.7 in.) as

shown on Fig. A-GBEAC Sheet 03, View F.

d Drill the hole to a final diameter of 5.1 mm (0.2 in.) as shown on Fig. AGBEAC Sheet 03, View F.

e Install as shown on Fig. A-GBEAC Sheet 03, View F:

1 Placard F2529200700000 Item 18

3 Clean the bonding points with:

Non Aqueous

Cleaner-General

08BAA9 As required

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 54

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SERVICE BULLETIN

Textile-Lint Free

Cotton

14SBA1 As required

4 Apply to the bonding points a thin coat of:

Mineral Oil Base

Grease

03FAB1 As required

NOTE: The application of the grease is only necessary if you can

not install the bonding leads (SUBTASK 253534-831-203 003

Install Bonding-Leads to the Upper Cockpit Door Frame ) in

the next 4 hours.

(2) Subtask 253534-831-203-003 - Install Bonding-Leads to the Upper Cockpit Door

Frame

Work Zones and Access Panels

Zone Access/Work location

220

Manpower Resources

Manhours 1.50

Minimum number of person 1

Subtask elapsed time 1.50

Skills AIRFRAME

Material necessary to do the job

Kit 253534D03R06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 NAS1102-3-8 2 SCREW

9 NAS1802-3-9 2 SCREW

10 ABS0916B05 0.6 TUBING

11 E0090-10-125NN 1 LEAD

12 NAS1802-3-7 4 SCREW

13 NAS1149C0332R 6 WASHER

14 F2529200920000 2 WASHER

15 NAS1726C3P 2 NUT

17 E0090-10-200NN 2 LEAD

18 F2529200700000 2 PLACARD

22 E0090-10-160NN 1 LEAD

Component COMPD02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

17 E0090-10-200NN 2 LEAD

NOTE: Operators having Kit 253534D03R05 will require COMPD02.

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 55

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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.

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Varnish - Electrical Bonding 04TMB2 As required

Non Aqueous CleanerGeneral08BAA9 As required

Textile-Lint Free Cotton 14SBA1 As required

References

Aircraft Maintenance Manual (AMM) Task 25-26-41-400-801

Task 25-26-41-400-802

Fig. A-GBDAC

Install the bonding-leads at the upper

door frame

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

(a) Install the bonding-leads at the RH door post as follows:

1 Remove as shown on Fig. A-GBDAC Sheet 03, View E:

2 Screw Item (1) Discard

2 Remove the surface protection around the screw hole to a diameter

approximately 3 mm (0.12 in.) larger than the diameter of the washer, item 14

as shown on Fig. A-GBDAC Sheet 03, View F.

3 Remove the surface protection around the screw hole to a diameter

approximately 3 mm (0.12 in.) larger than the countersink diameter as shown

on Fig. A-GBDAC Sheet 03, View F.

4 Clean the bonding points at the bracket and the door post with:

Non Aqueous

Cleaner-General

08BAA9 As required

Textile-Lint Free

Cotton

14SBA1 As required

5 Cut two pieces of tubing to a length of 0.11 m (4.33 in.) from:

0.6 Tubing ABS0916B05 Item 10

6 Push the tubings, item 10 over the bonding-leads, item 11 and 17 and shrink

them.

7 Install at the door post as shown on Fig. A-GBDAC Sheet 03, View F:

1 Screw NAS1102-3-8 Item 1

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 56

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SERVICE BULLETIN

8 Install at the door post as shown on Fig. A-GBDAC Sheet 03, View F:

1 Bonding-Lead E0090-10-125NN Item 11

1 Bonding-Lead E0090-10-200NN Item 17

1 Screw NAS1802-3-9 Item 9

1 Washer NAS1149C0332R Item 13

1 Washer F2529200920000 Item 14

For operators with Kit 253534D03R05, get this item from COMPD02:

1 Bonding-Lead E0090-10-200NN Item 17

NOTE: The bonding lead length may be adapted if necessary.

9 Attach the bonding-lead, item 11 to the bracket as shown on Fig. A-GBDAC

Sheet 03, View F with:

1 Screw NAS1802-3-7 Item 12

1 Washer NAS1149C0332R Item 13

10 Clean the bonding point at the web with:

Non Aqueous

Cleaner-General

08BAA9 As required

Textile-Lint Free

Cotton

14SBA1 As required

11 Attach the bonding-lead, item 11 to the web as shown on Fig. A-GBDAC

Sheet 05, View J with:

1 Screw NAS1802-3-7 Item 12

1 Washer NAS1149C0332R Item 13

1 Nut NAS1726C3P Item 15

12 Apply to the Screw, item 12 and the nut, item 15 as shown on Fig. A-GBDAC

Sheet 05, View J:

Varnish - Electrical

Bonding

04TMB2 As required

13 Apply to the Screws, item 1, 9 and 12 as shown on Fig. A-GBDAC Sheet 03,

View F:

Varnish - Electrical

Bonding

04TMB2 As required

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 57

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SERVICE BULLETIN

(b) Install the bonding-leads at the LH door post as follows:

1 Remove as shown on Fig. A-GBDAC Sheet 04, View G:

2 Screw Item (1) Discard

2 Remove the surface protection around the screw hole to a diameter

approximately 3 mm (0.12 in.) larger than the diameter of the washer, item 14

as shown on Fig. A-GBDAC Sheet 04, View H.

3 Remove the surface protection around the screw hole to a diameter

approximately 3 mm (0.12 in.) larger than the countersink diameter as shown

on Fig. A-GBDAC Sheet 04, View H.

4 Clean the bonding points at the bracket and the door post with:

Non Aqueous

Cleaner-General

08BAA9 As required

Textile-Lint Free

Cotton

14SBA1 As required

5 Cut two pieces of tubing to a length of 0.185 m and 0.145 m (7.28 in. and

5.71 in.) from:

0.6 Tubing ABS0916B05 Item 10

6 Push the tubings, item 10 over the bonding-leads, item 17 and 22 and shrink

them.

7 Install at the door post as shown on Fig. A-GBDAC Sheet 04, View H:

1 Screw NAS1102-3-8 Item 1

8 Install at the door post as shown on Fig. A-GBDAC Sheet 04, View H:

1 Bonding-Lead E0090-10-200NN Item 17

1 Bonding-Lead E0090-10-160NN Item 22

1 Screw NAS1802-3-9 Item 9

1 Washer NAS1149C0332R Item 13

1 Washer F2529200920000 Item 14

For operators with Kit 253534D03R05, get these items from COMPD02:

1 Bonding-Lead E0090-10-200NN Item 17

NOTE: The bonding lead length may be adapted if necessary.

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 58

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SERVICE BULLETIN

9 Attach the bonding-lead, item 17 to the bracket as shown on Fig. A-GBDAC

Sheet 04, View H with:

1 Screw NAS1802-3-7 Item 12

1 Washer NAS1149C0332R Item 13

10 Clean the bonding point at the web with:

Non Aqueous

Cleaner-General

08BAA9 As required

Textile-Lint Free

Cotton

14SBA1 As required

11 Attach the bonding-lead, item 22 to the web as shown on Fig. A-GBDAC

Sheet 05, View K with:

1 Screw NAS1802-3-7 Item 12

1 Washer NAS1149C0332R Item 13

1 Nut NAS1726C3P Item 15

12 Apply to the Screw, item 12 and the nut, item 15 as shown on Fig. A-GBDAC

Sheet 05, View K:

Varnish - Electrical

Bonding

04TMB2 As required

13 Apply to the Screws, item 1, 9 and 12 as shown on Fig. A-GBDAC Sheet 04,

View H:

Varnish - Electrical

Bonding

04TMB2 As required

(c) Install as shown on Fig. A-GBDAC Sheet 01, View B:

2 Placard F2529200700000 Item 18

(d) Install the curtain rail, refer to AMM Task 25-26-41-400-802.

(e) Install the curtain, refer to AMM Task 25-26-41-400-801.

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 59

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@A330

SERVICE BULLETIN

**CONF ALL

D. TEST

**CONF 001

(1) Subtask 253534-760-201-001 - Bonding Test

Work Zones and Access Panels

Zone Access/Work location

220

Manpower Resources

Skills ELECTRICAL

References

Aircraft Maintenance Manual (AMM) Task 20-28-00-720-805

(a) This Service Bulletin requires the accomplishment of the following Test which is

given in SUBTASK 253534-831-201 001 Modify the Cockpit Door Frame Structure :

- operational test of the cockpit door emergency access

- test of easy operation and correct close of the cockpit door

The manhours for the tests are included in the referenced Service Bulletin

subtasks.

(b) Do a check of the electrical bonding, refer to AMM Task 20-28-00-720-805.

**CONF 002

(1) Subtask 253534-760-201-002 - Bonding Test

Work Zones and Access Panels

Zone Access/Work location

220

Manpower Resources

Skills ELECTRICAL

References

Aircraft Maintenance Manual (AMM) Task 20-28-00-720-805

(a) This Service Bulletin requires the accomplishment of the following Tests which are

given in SUBTASK 253534-831-201 002 Modify the Cockpit Door Frame Structure

and SUBTASK 253534-831-203 002 Install Bonding-Leads to the Upper Cockpit

Door Frame :

- operational test of the cockpit door emergency access

- test of easy operation and correct close of the cockpit door

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 60

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SERVICE BULLETIN

The manhours for the tests are included in the referenced Service Bulletin

subtasks.

(b) Do a check of the electrical bonding, refer to AMM Task 20-28-00-720-805.

**CONF 003

(1) Subtask 253534-760-201-003 - Bonding Test

Work Zones and Access Panels

Zone Access/Work location

220

Manpower Resources

Skills ELECTRICAL

References

Aircraft Maintenance Manual (AMM) Task 20-28-00-720-805

(a) Do a check of the electrical bonding, refer to AMM Task 20-28-00-720-805.

**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 253534-942-201-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 25-13-44-400-801

Task 25-13-46-400-801

Task 25-23-42-400-801

Task 25-23-42-400-808

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

equipment.

(b) Install the ceiling panel 211MC and 211LC, refer to AMM Task 25-13-44-400-801.

(c) Based on aircraft configuration, if removed, install the coat stowage, refer to AMM

Task 25-13-46-400-801.

(d) Install the ceiling panel 221AC, refer to AMM Task 25-23-42-400-801 or AMM Task

25-23-42-400-808.

(e) Put the aircraft back to its initial configuration.

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 61

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@A330

SERVICE BULLETIN

**CONF 002

(1) Subtask 253534-942-201-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 25-13-44-400-801

Task 25-13-46-400-801

Task 25-23-42-400-801

Task 25-23-42-400-808

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

equipment.

(b) Install the ceiling panel 211MC and 211LC, refer to AMM Task 25-13-44-400-801.

(c) Based on aircraft configuration, if removed, install the coat stowage, refer to AMM

Task 25-13-46-400-801.

(d) Install the ceiling panel 221AC, refer to AMM Task 25-23-42-400-801 or AMM Task

25-23-42-400-808.

(e) Put the aircraft back to its initial configuration.

**CONF 003

(1) Subtask 253534-942-201-002 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 25-13-44-400-801

Task 25-13-46-400-801

Task 25-23-42-400-808

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

equipment.

(b) Install the ceiling panel 211MC and 211LC, refer to AMM Task 25-13-44-400-801.

(c) Based on aircraft configuration, if removed, install the coat stowage, refer to AMM

Task 25-13-46-400-801.

(d) Install the ceiling panel 221AC, refer to AMM Task 25-23-42-400-808.

(e) Put the aircraft back to its initial configuration.

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 62

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@A330

SERVICE BULLETIN

**CONF 001

A

FR11

FR16A

B

A

Z220

C

B

G_SB_253534_6_BAAA_01_00

Figure A-GBAAA - Sheet 01

Prepare the bonding points at the wire protection

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 63

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@A330

SERVICE BULLETIN

**CONF 001

C

01

01

01

01

NOTE:

01 LOOSEN ONLY THE NUTS TO REMOVE THE ELECTRICAL HARNESS

D

E

18 SB25−3534

G_SB_253534_6_BAAA_02_00

Figure A-GBAAA - Sheet 02

Prepare the bonding points at the wire protection

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 64

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@A330

SERVICE BULLETIN

**CONF 001

12.24 mm

(0.48 in)

12.0 mm

(0.47 in)

5.1 mm DIA

(0.20 in)

D

46.8 mm

(1.84 in)

17.7 mm

(0.70 in)

5.1 mm DIA

(0.20 in)

E

12.5 mm DIA

(0.49 in)

12.5 mm DIA

(0.49 in)

G_SB_253534_6_BAAA_03_01

Figure A-GBAAA - Sheet 03

Prepare the bonding points at the wire protection

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 65

6

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@A330

SERVICE BULLETIN

**CONF 002

A

FR11

FR16A

B

A

Z220

C

B

G_SB_253534_6_BAAB_01_00

Figure A-GBAAB - Sheet 01

Prepare the bonding points at the wire protection

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 66

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@A330

SERVICE BULLETIN

**CONF 002

C

01

01

01

01

NOTE:

01 LOOSEN ONLY THE NUTS TO REMOVE THE ELECTRICAL HARNESS

D

E

18 SB25−3534

G_SB_253534_6_BAAB_02_00

Figure A-GBAAB - Sheet 02

Prepare the bonding points at the wire protection

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 67

6

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@A330

SERVICE BULLETIN

**CONF 002

12.24 mm

(0.48 in)

12.0 mm

(0.47 in)

5.1 mm DIA

(0.20 in)

D

46.8 mm

(1.84 in)

17.7 mm

(0.70 in)

5.1 mm DIA

(0.20 in)

E

12.5 mm DIA

(0.49 in)

12.5 mm DIA

(0.49 in)

G_SB_253534_6_BAAB_03_01

Figure A-GBAAB - Sheet 03

Prepare the bonding points at the wire protection

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 68

6

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

SERVICE BULLETIN

**CONF 003

C

A

Z220

B

FR11

FR16A

B

A

G_SB_253534_6_BAAC_01_01

Figure A-GBAAC - Sheet 01

Remove curtain rail brackets

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 69

6

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

SERVICE BULLETIN

**CONF 003

(20)

(19)

C

D

D

D

G_SB_253534_6_BAAC_02_00

Figure A-GBAAC - Sheet 02

Remove curtain rail brackets

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 70

6

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

SERVICE BULLETIN

**CONF 001

A

FR11

FR16A

B

A

Z220

B

C

G

D

G_SB_253534_6_BCAA_01_00

Figure A-GBCAA - Sheet 01

Prepare the bonding points at the door posts

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 71

6

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

SERVICE BULLETIN

**CONF 001

(1)

FWD FWD

BEFORE

AFTER

1

NOTE:

02 REMOVE SURFACE PROTECTION TO A DIA APPROX.

3.0 mm (0.12 in) LARGER THAN THE COUNTERSINK DIA.

03 APPLY VARNISH (MAT.NO.04TMB2)

02

03

RH SIDE LH SIDE

C D

E

F

E F

E F

18

SB25−3534

18

SB25−3534

G_SB_253534_6_BCAA_02_01

Figure A-GBCAA - Sheet 02

Prepare the bonding points at the door posts

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 72

6

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

SERVICE BULLETIN

**CONF 001

(2)

2 6X

(3)

(4)

BEFORE

AFTER

(5)

(6)

5

6

04

03

G

H

J

H J

NOTE:

04 REMOVE SURFACE PROTECTION TO A

LARGER THAN THE SCREW HEAD DIA.

03 APPLY VARNISH (MAT.NO.04TMB2)

DIA APPROX. 3.0 mm (0.12 in)

05 05 TYPICAL INSTALLATION

G_SB_253534_6_BCAA_03_02

Figure A-GBCAA - Sheet 03

Prepare the bonding points at the door posts

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 73

6

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

SERVICE BULLETIN

**CONF 002

A

FR11

FR16A

B

A

Z220

B

C

G

D

G_SB_253534_6_BCAB_01_00

Figure A-GBCAB - Sheet 01

Prepare the bonding points at the door posts

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 74

6

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

SERVICE BULLETIN

**CONF 002

(1)

FWD FWD

BEFORE

AFTER

1

NOTE:

02 REMOVE SURFACE PROTECTION TO A DIA APPROX.

3.0 mm (0.12 in) LARGER THAN THE COUNTERSINK DIA.

03 APPLY VARNISH (MAT.NO.04TMB2)

02

03

RH SIDE LH SIDE

C D

E

F

E F

E F

18

SB25−3534

18

SB25−3534

G_SB_253534_6_BCAB_02_01

Figure A-GBCAB - Sheet 02

Prepare the bonding points at the door posts

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 75

6

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

SERVICE BULLETIN

**CONF 002

(2)

2 6X

(3)

(4)

BEFORE

AFTER

(5)

(6)

5

6

NOTE:

04 REMOVE SURFACE PROTECTION TO A

LARGER THAN THE SCREW HEAD DIA.

03 APPLY VARNISH (MAT.NO.04TMB2)

04

03

DIA APPROX. 3.0 mm (0.12 in)

G

H

J

H J

05 TYPICAL INSTALLATION 05

G_SB_253534_6_BCAB_03_02

Figure A-GBCAB - Sheet 03

Prepare the bonding points at the door posts

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 76

6

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

SERVICE BULLETIN

**CONF 001

A

FR11

FR16A

B

A

Z220

C

B

G_SB_253534_6_BBAA_01_00

Figure A-GBBAA - Sheet 01

Install the bracket at the pelmet

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 77

6

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

SERVICE BULLETIN

**CONF 001

C

D

7

18 SB25−3534

8

D

NOTE:

01 REMOVE SURFACE PROTECTION TO A DIA 

APPROX. 3.0 mm (0.12 in) LARGER THAN THE 

E

DIA OF THE RIVET HEAD.

02 REMOVE SURFACE PROTECTION FROM

THE CONTACT AREA.

02

01

G_SB_253534_6_BBAA_02_00

Figure A-GBBAA - Sheet 02

Install the bracket at the pelmet

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 78

6

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

SERVICE BULLETIN

**CONF 001

4.0 mm

(0.16 in)

7

E

A A

NOTE:

03 MAKE SURE THAT YOU DO NOT DRILL TO MORE THAN A DEPTH

VIEW FROM COCKPIT SIDE

OF 21.0 mm (0.83 in) TO AVOID DAMAGE TO THE S−GLASS ON THE CABIN SIDE.

FLUSH WITH CHANNEL EDGE

A

A

A

A

21.0 mm −1.0 mm

(0.83 in −0.039 in)

4.1 mm DIA

(0.16 in)

S−GLASS

03

7

8

04

04

04

04 APPLY VARNISH (MAT.NO.04TMB2) AND SEALANT (MAT.NO.06AAB1).

G_SB_253534_6_BBAA_03_00

Figure A-GBBAA - Sheet 03

Install the bracket at the pelmet

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 79

6

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

SERVICE BULLETIN

**CONF 002

A

FR11

FR16A

B

A

Z220

C

B

G_SB_253534_6_BBAB_01_00

Figure A-GBBAB - Sheet 01

Install the bracket at the pelmet

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 80

6

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

SERVICE BULLETIN

**CONF 002

C

D

7

18 SB25−3534

8

D

NOTE:

01 REMOVE SURFACE PROTECTION TO A DIA 

APPROX. 3.0 mm (0.12 in) LARGER THAN THE 

E

DIA OF THE RIVET HEAD.

02 REMOVE SURFACE PROTECTION FROM

THE CONTACT AREA.

02

01

G_SB_253534_6_BBAB_02_00

Figure A-GBBAB - Sheet 02

Install the bracket at the pelmet

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 81

6

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

SERVICE BULLETIN

**CONF 002

4.0 mm

(0.16 in)

7

E

A A

NOTE:

03 MAKE SURE THAT YOU DO NOT DRILL TO MORE THAN A DEPTH

VIEW FROM COCKPIT SIDE

OF 21.0 mm (0.83 in) TO AVOID DAMAGE TO THE S−GLASS ON THE CABIN SIDE.

FLUSH WITH CHANNEL EDGE

A

A

A

A

21.0 mm −1.0 mm

(0.83 in −0.039 in)

4.1 mm DIA

(0.16 in)

S−GLASS

03

7

8

04

04

04

04 APPLY VARNISH (MAT.NO.04TMB2) AND SEALANT (MAT.NO.06AAB1).

G_SB_253534_6_BBAB_03_00

Figure A-GBBAB - Sheet 03

Install the bracket at the pelmet

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 82

6

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

SERVICE BULLETIN

**CONF 003

C

A

Z220

B

FR11

FR16A

B

A

G_SB_253534_6_BBAC_01_01

Figure A-GBBAC - Sheet 01

Install curtain rail bracket

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 83

6

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

SERVICE BULLETIN

**CONF 003

A

A

20

19

C

12.5 mm DIA

(0.49 in)

19

21

F

W

D

A

A

A A

E D

21

20

D

E

18 SB25−3534

G_SB_253534_6_BBAC_02_01

Figure A-GBBAC - Sheet 02

Install curtain rail bracket

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 84

6

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

SERVICE BULLETIN

**CONF 001 thru 002

A

FR11

FR16A

B

A

Z220

B

FR11

FR11A

E

C

G_SB_253534_6_BEAA_01_03

Figure A-GBEAA - Sheet 01

Prepare the bonding points at the webs

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 85

6

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

SERVICE BULLETIN

**CONF 001 thru 002

21.5 mm

(0.85 in)

18.0 mm

(0.71 in)

FR11A

FWD

5.1mm DIA

(0.20 in)

17.0 mm DIA

(0.70 in)

D

FR11

18 SB25−3534

C

D

RH DOOR POST

G_SB_253534_6_BEAA_02_03

Figure A-GBEAA - Sheet 02

Prepare the bonding points at the webs

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 86

6

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

SERVICE BULLETIN

**CONF 001 thru 002

LH DOOR POST

E

F

FR11A

FR11

5.1mm DIA

(0.20 in)

17.0 mm DIA

(0.70 in)

19.0 mm

(0.75 in)

17.5 mm

(0.69 in)

F FWD

18 SB25−3534

G_SB_253534_6_BEAA_03_03

Figure A-GBEAA - Sheet 03

Prepare the bonding points at the webs

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 87

6

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

SERVICE BULLETIN

**CONF 003

A

Z220

B

FR11

FR11A

FR11

FR16A

B

A

E

C

G_SB_253534_6_BEAC_01_03

Figure A-GBEAC - Sheet 01

Prepare the bonding points at the webs

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 88

6

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

SERVICE BULLETIN

**CONF 003

21.5 mm

(0.85 in)

18.0 mm

(0.71 in)

FR11A

FWD

5.1mm DIA

(0.20 in)

17.0 mm DIA

(0.70 in)

D

FR11

18 SB25−3534

C

D

RH DOOR POST

G_SB_253534_6_BEAC_02_03

Figure A-GBEAC - Sheet 02

Prepare the bonding points at the webs

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 89

6

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

SERVICE BULLETIN

**CONF 003

LH DOOR POST

E

F

FR11A

FR11

5.1mm DIA

(0.20 in)

17.0 mm DIA

(0.70 in)

19.0 mm

(0.75 in)

17.5 mm

(0.69 in)

F FWD

18 SB25−3534

G_SB_253534_6_BEAC_03_03

Figure A-GBEAC - Sheet 03

Prepare the bonding points at the webs

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 90

6

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

SERVICE BULLETIN

**CONF 001

A

FR11

FR16A

B

A

Z220

B

FR11

FR11A

C L

J

K

G_SB_253534_6_BDAA_01_03

Figure A-GBDAA - Sheet 01

Install the bonding-leads at the upper door frame

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 91

6

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

SERVICE BULLETIN

**CONF 001

C

D

E F

D

G H

G_SB_253534_6_BDAA_02_00

Figure A-GBDAA - Sheet 02

Install the bonding-leads at the upper door frame

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 92

6

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

SERVICE BULLETIN

**CONF 001

AFTER

9

13

11

14

10

11

10

12

13

15

BEFORE

(1)

E

F

NOTE:

01 APPLY VARNISH (MAT.NO.04TMB2)

01

01

01

02 REMOVE SURFACE PROTECTION AROUND THE SCREW HOLE TO A DIA APPROX.

3.0 mm (0.12 in) LARGER THAN THE DIA OF THE WASHER, ITEM 14.

02

G_SB_253534_6_BDAA_03_01

Figure A-GBDAA - Sheet 03

Install the bonding-leads at the upper door frame

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 93

6

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

SERVICE BULLETIN

**CONF 001

AFTER

BEFORE

(1)

9

13

16

14

10

19

22

20

21

12

13

15

10

10

G

H

01

01

01

01

NOTE:

01 APPLY VARNISH (MAT.NO.04TMB2)

02

02

REMOVE SURFACE PROTECTION AROUND THE SCREW HOLE TO A DIA APPROX.

3.0 mm (0.12 in) LARGER THAN THE DIA OF THE WASHER, ITEM 14. G_SB_253534_6_BDAA_04_02

Figure A-GBDAA - Sheet 04

Install the bonding-leads at the upper door frame

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 94

6

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

SERVICE BULLETIN

**CONF 001

15

16

13

12

LH DOOR POST

K

NOTE:

01 APPLY VARNISH (MAT.NO.04TMB2)

01

01

13

12 01

11

J

RH DOOR POST

01 15

G_SB_253534_6_BDAA_05_03

Figure A-GBDAA - Sheet 05

Install the bonding-leads at the upper door frame

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 95

6

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

SERVICE BULLETIN

**CONF 001

04 MAKE SURE THAT THERE IS NO CHAFING

BETWEEN THE WIRE HARNESS AND THE BONDING LEAD

L

03

03

03

03

04

NOTE:

03 TIGHTEN THE NUTS TO FIX THE ELECTRICAL HARNESS

TO THE WIRE PROTECTOR

G_SB_253534_6_BDAA_06_01

Figure A-GBDAA - Sheet 06

Install the bonding-leads at the upper door frame

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 96

6

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

SERVICE BULLETIN

**CONF 002

A

FR11

FR16A

B

A

Z220

B

FR11

FR11A

C L

J

K

G_SB_253534_6_BDAB_01_03

Figure A-GBDAB - Sheet 01

Install the bonding-leads at the upper door frame

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 97

6

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

SERVICE BULLETIN

**CONF 002

C

D

E F

D

G H

G_SB_253534_6_BDAB_02_00

Figure A-GBDAB - Sheet 02

Install the bonding-leads at the upper door frame

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 98

6

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

SERVICE BULLETIN

**CONF 002

AFTER

9

13

11

14

10

11

10

12

13

15

BEFORE

(1)

E

F

NOTE:

01 APPLY VARNISH (MAT.NO.04TMB2)

01

01

01

02

02

REMOVE SURFACE PROTECTION AROUND THE SCREW HOLE TO A DIA APPROX.

3.0 mm (0.12 in) LARGER THAN THE DIA OF THE WASHER, ITEM 14. G_SB_253534_6_BDAB_03_00

Figure A-GBDAB - Sheet 03

Install the bonding-leads at the upper door frame

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 99

6

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

SERVICE BULLETIN

**CONF 002

AFTER

BEFORE

(1)

9

13

16

14

10

19

22

20

21

12

13

15

10

10

G

H

01

01

01

01

NOTE:

01 APPLY VARNISH (MAT.NO.04TMB2)

02

02

REMOVE SURFACE PROTECTION AROUND THE SCREW HOLE TO A DIA APPROX.

3.0 mm (0.12 in) LARGER THAN THE DIA OF THE WASHER, ITEM 14. G_SB_253534_6_BDAB_04_01

Figure A-GBDAB - Sheet 04

Install the bonding-leads at the upper door frame

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 100

6

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

SERVICE BULLETIN

**CONF 002

15

16

13

12

LH DOOR POST

K

NOTE:

01 APPLY VARNISH (MAT.NO.04TMB2)

01

01

13

12 01

11

J

RH DOOR POST

01 15

G_SB_253534_6_BDAB_05_03

Figure A-GBDAB - Sheet 05

Install the bonding-leads at the upper door frame

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 101

6

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

SERVICE BULLETIN

**CONF 002

04 MAKE SURE THAT THERE IS NO CHAFING

BETWEEN THE WIRE HARNESS AND THE BONDING LEAD

L

03

03

03

03

04

NOTE:

03 TIGHTEN THE NUTS TO FIX THE ELECTRICAL HARNESS

TO THE WIRE PROTECTOR

G_SB_253534_6_BDAB_06_01

Figure A-GBDAB - Sheet 06

Install the bonding-leads at the upper door frame

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 102

6

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

SERVICE BULLETIN

**CONF 003

C

A

Z220

B

FR11

FR11A

K

18

SB25−3534

18

SB25−3534

FR11

FR16A

B

A

J

G_SB_253534_6_BDAC_01_04

Figure A-GBDAC - Sheet 01

Install the bonding-leads at the upper door frame

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 103

6

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

SERVICE BULLETIN

**CONF 003

C

D

D

G H

E F

G_SB_253534_6_BDAC_02_01

Figure A-GBDAC - Sheet 02

Install the bonding-leads at the upper door frame

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 104

6

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

SERVICE BULLETIN

**CONF 003

9

13

11

14 10

10

12

13

BEFORE

(1)

AFTER

(1)

1

NOTE:

03 APPLY VARNISH (MAT.NO.04TMB2)

03

03

03

01 REMOVE SURFACE PROTECTION TO A DIA APPROX. 3.0 mm (0.12 in)

LARGER THAN THE DIA OF THE WASHER, ITEM 14.

02 REMOVE SURFACE PROTECTION TO A DIA APPROX. 3.0 mm (0.12 in)

LARGER THAN THE COUNTERSINK DIA.

01

02

E

F

17

G_SB_253534_6_BDAC_03_01

Figure A-GBDAC - Sheet 03

Install the bonding-leads at the upper door frame

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 105

6

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

SERVICE BULLETIN

**CONF 003

AFTER

BEFORE

(1)

12

13

10

9

13

22

14

10

(1)

1

03

03 03

NOTE:

03 APPLY VARNISH (MAT.NO.04TMB2)

01 REMOVE SURFACE PROTECTION TO A DIA APPROX. 3.0 mm (0.12 in)

LARGER THAN THE DIA OF THE WASHER, ITEM 14.

02 REMOVE SURFACE PROTECTION TO A DIA APPROX. 3.0 mm (0.12 in)

LARGER THAN THE COUNTERSINK DIA.

01

02

17

G

H

G_SB_253534_6_BDAC_04_00

Figure A-GBDAC - Sheet 04

Install the bonding-leads at the upper door frame

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 106

6

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

SERVICE BULLETIN

**CONF 003

15

22

13

12

LH DOOR POST

K

NOTE:

03 APPLY VARNISH (MAT.NO.04TMB2)

03

03

13

12 01

11

J

RH DOOR POST

01 15

G_SB_253534_6_BDAC_05_03

Figure A-GBDAC - Sheet 05

Install the bonding-leads at the upper door frame

DATE: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 107

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@A330

SERVICE BULLETIN

REPORTING SHEET

TITLE: EQUIPMENT/FURNISHINGS - CURTAINS AND PARTITIONS -

INTRODUCE MODIFIED ELECTRICAL BONDING OF COCKPIT DOOR.

MODIFICATION No.: 203228D50684 203229D61659 203371D48094

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: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 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: May 27/14 SERVICE BULLETIN No.: A330-25-3534

REVISION No.: 02 - May 18/15 Page: 1

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